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6 pages, 1266 KB

Open AccessProceeding Paper

Application of Artificial Neural Networks in Unmanned Aircraft Vehicle Control and Surveillance System

by Dariusz Rykaczewski and Mirosław Gerigk

Eng. Proc. 2026, 133(1), 1; https://doi.org/10.3390/engproc2026133001 - 13 Apr 2026

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The paper focuses on the practical benefits of using artificial neural networks (ANNs) in the control of unmanned aircraft vehicles (UAVs) and for the purposes of identification and surveillance. The presented methodology for modeling flight dynamics uses ANNs. Modeling of the object dynamics [...] Read more.

The paper focuses on the practical benefits of using artificial neural networks (ANNs) in the control of unmanned aircraft vehicles (UAVs) and for the purposes of identification and surveillance. The presented methodology for modeling flight dynamics uses ANNs. Modeling of the object dynamics was based on experimental results obtained during flight tests. The aerodynamic g-loads were derived as a function of the flow parameters. The aim of ANN is to select weights of the neural network in such a way that it simultaneously generates all the necessary parameters to implement into the model with a high fidelity. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 1066 KB

Open AccessProceeding Paper

Zonal Simulation of Air Flow Dynamics in the Leakage Case of a Liquid Hydrogen Tank in a Hybrid-Electric Regional Aircraft

by Christina Matheis and Victor Norrefeldt

Eng. Proc. 2026, 133(1), 2; https://doi.org/10.3390/engproc2026133002 - 13 Apr 2026

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Abstract

This study investigates the spread and removal of emissions from a liquid hydrogen tank in a leakage case in the rear area of a hybrid-electric regional aircraft. The aim of the research is to determine the air volume flows that a fan is [...] Read more.

This study investigates the spread and removal of emissions from a liquid hydrogen tank in a leakage case in the rear area of a hybrid-electric regional aircraft. The aim of the research is to determine the air volume flows that a fan is required to supply to keep the hydrogen concentration below 1% by volume in the event of a leak. In addition, the fan position with the best possible hydrogen removal is to be identified. For this purpose, the geometry of a 10.6 m³ sized tank and compartment is reconstructed, and a zonal simulation model is created that represents the air flow patterns within the domain. Using this simulation model, a comprehensive parameter study is carried out in which different configurations of fan arrangements and leakage scenarios are simulated. The results of these simulations are analyzed and compared to determine the most efficient ventilation to maintain safe hydrogen concentrations. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 5498 KB

Open AccessProceeding Paper

Surrogate Modeling of Non-Linear Folding Wing Tip Aerodynamic Coefficients

by Andreas Molz and Christian Breitsamter

Eng. Proc. 2026, 133(1), 3; https://doi.org/10.3390/engproc2026133003 - 14 Apr 2026

Viewed by 363

Abstract

The development of sustainable and efficient aircraft concepts, such as those featuring flared folding wing tips (FWTs), introduces both aerodynamic and structural challenges. FWTs have demonstrated strong potential for enhancing aerodynamic performance and alleviating gust-induced loads, making them an attractive option for next-generation [...] Read more.

The development of sustainable and efficient aircraft concepts, such as those featuring flared folding wing tips (FWTs), introduces both aerodynamic and structural challenges. FWTs have demonstrated strong potential for enhancing aerodynamic performance and alleviating gust-induced loads, making them an attractive option for next-generation transport aircraft. This study investigates the load reduction potential of transonic transport aircraft configurations equipped with hinged FWTs, with particular focus on gust impact. Reynolds Averaged Navier Stokes simulations are combined with Gaussian Process regression to evaluate the influence of the fold angle, flare angle, and angle of attack on key quantities of interest, including lift and wing root bending moment coefficients. The GP surrogate model, developed within the Gust Load Alleviation by Non-linear Folding Wing Tip (GUSTAFO) project, accurately reproduces the high-fidelity data while capturing the underlying system uncertainties. The results show that increasing the flare angle within a given folding deflection can reduce the wing root bending moment by up to 38% for flare angles between 0–

45^{\circ}

and fold angles between 0–

15^{\circ}

. These findings highlight the effectiveness of surrogate-based modeling for early-stage design and emphasize the importance of incorporating FWT behavior to achieve accurate, efficient, and robust load predictions. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 9304 KB

Open AccessProceeding Paper

Investigations of Transport Aircraft Shock Buffet Under Forced Wing Motions

by Vinzenz Völkl and Christian Breitsamter

Eng. Proc. 2026, 133(1), 4; https://doi.org/10.3390/engproc2026133004 - 15 Apr 2026

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Abstract

Transonic buffet is a critical self-sustained shock/boundary-layer instability limiting the flight envelope of modern transport aircraft. This study investigates the interaction between shock buffet and forced wing motion on the Airbus XRF-1 wind tunnel model, using unsteady Reynolds-Averaged Navier–Stokes (URANS) simulations with the [...] Read more.

Transonic buffet is a critical self-sustained shock/boundary-layer instability limiting the flight envelope of modern transport aircraft. This study investigates the interaction between shock buffet and forced wing motion on the Airbus XRF-1 wind tunnel model, using unsteady Reynolds-Averaged Navier–Stokes (URANS) simulations with the DLR TAU code. The investigation is carried out in deep buffet condition (

Ma = 0.84

,

α = 4 . 5^{\circ}

,

Re = 25 \times 10^{6}

) and validated against wind tunnel data at the same flow condition. The buffet flow is superimposed with forced wing motions derived from a symmetric wing eigenmode at

Sr = 0.164

. Two different amplitudes scaled with the half-span s are considered:

A_{t i p} = 0.0025 \cdot s

and

0.01 \cdot s

. The baseline no-forcing URANS captures the buffet flow quite well with only small deviations in the standard deviation of the surface pressure coefficient

c_{p, r m s}

. A special variant of the Discrete Fourier Transformation for the whole wing upper surface

c_{p}

distribution revealed that the typical buffet frequencies are also matched. The analysis of the forced simulations revealed a strong influence of the local wing motion on the increase of

c_{p, r m s}

. The spectral content showed a shift and damping or amplification of different buffet modes, which is relevant for the interaction of motion induced and buffed induced aerodynamic forces. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 2093 KB

Open AccessProceeding Paper

Development of Short-Medium Range Laminar Aircraft: Conceptual Design with Integrated System Sizing

by Petr Martínek, Benjamin M. H. J. Fröhler, Maurice F. M. Hoogreef and Thomas Zill

Eng. Proc. 2026, 133(1), 5; https://doi.org/10.3390/engproc2026133005 - 15 Apr 2026

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Abstract

The aviation industry is under increasing pressure to enhance sustainability by improving energy efficiency and reducing climate impact. A promising approach is to reduce aerodynamic drag using laminar flow technologies, particularly Natural Laminar Flow (NLF) and Hybrid Laminar Flow Control (HLFC). Previous research [...] Read more.

The aviation industry is under increasing pressure to enhance sustainability by improving energy efficiency and reducing climate impact. A promising approach is to reduce aerodynamic drag using laminar flow technologies, particularly Natural Laminar Flow (NLF) and Hybrid Laminar Flow Control (HLFC). Previous research has primarily focused on aerodynamic performance, often considering only one technology at a time, using simplified HLFC system design models, and targeting long-range aircraft. This study adopts a more holistic approach by conducting a conceptual design of a short-medium range (SMR) aircraft equipped with both NLF and HLFC. The technologies are applied to the wing and empennage, with detailed HLFC system modelling integrated into the conceptual design process using established methods. A failure analysis is also performed to assess the performance impact of potential malfunctions. Results indicate that combining NLF and HLFC can reduce fuel consumption by 5.9% on the design mission compared to a fully turbulent reference aircraft. Moreover, selectively applying the technologies to specific components enhances fuel savings while reducing system complexity. These findings demonstrate the potential of laminar flow technologies to improve fuel efficiency in SMR aircraft and highlight the importance of integrated aerodynamic and systems-level evaluation. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 1017 KB

Open AccessProceeding Paper

Continuous Movable Layout Parameterisation for Gust Load Alleviation

by Stefan de Boer, Jurij Sodja and Roeland De Breuker

Eng. Proc. 2026, 133(1), 6; https://doi.org/10.3390/engproc2026133006 - 17 Apr 2026

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Abstract

This paper extends the continuous movable parameterisation framework to allow for the consideration of gust load alleviation in the movable layout optimisation process. A finite impulse response filter was introduced to model the feed-forward controller and allow for the dynamic response of the [...] Read more.

This paper extends the continuous movable parameterisation framework to allow for the consideration of gust load alleviation in the movable layout optimisation process. A finite impulse response filter was introduced to model the feed-forward controller and allow for the dynamic response of the movables. The extended framework was demonstrated using an ultra-high-aspect-ratio cantilever wing aircraft model. The optimisation reduced the root bending moment by 46% when both the wing movables and horizontal tailplane were used, and by 14% when only the wing movables were available. The optimisation positioned the movables to satisfy the handling qualities constraint, while having the largest effect on the root bending moment. Finally, the results show that the framework can be efficiently used to explore the movable layout design space. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 1057 KB

Open AccessProceeding Paper

Aerodynamic Advances Through Laminar Flow: A Conceptual Aircraft Design Study

by Benjamin M. H. J. Fröhler, Petr Martínek, Jannik Häßy, Tobias Wunderlich, Martin Hepperle and Thomas Kilian

Eng. Proc. 2026, 133(1), 7; https://doi.org/10.3390/engproc2026133007 - 16 Apr 2026

Viewed by 719

Abstract

Improving fuel efficiency is a primary challenge in modern aviation, with aerodynamics serving as a key enabler. Aerodynamic friction drag accounts for more than 50% of total drag, highlighting a significant opportunity for efficiency gains through laminar flow, which reduces skin friction drag. [...] Read more.

Improving fuel efficiency is a primary challenge in modern aviation, with aerodynamics serving as a key enabler. Aerodynamic friction drag accounts for more than 50% of total drag, highlighting a significant opportunity for efficiency gains through laminar flow, which reduces skin friction drag. In addition, increasing the wing aspect ratio while maintaining a constant lift coefficient to achieve maximum lift-to-drag ratio can further improve aerodynamic performance. However, evaluating laminar flow in isolation, without considering overall mass, system power requirements, or engine performance, can lead to an incomplete assessment of its true technological potential. In this study, a conceptual design methodology was applied to integrate laminar-flow technologies (natural and hybrid) across the wing, empennage, nacelle, and fuselage of a 2035 long-haul reference aircraft. Results indicate a potential for 16% block fuel reduction at the aircraft level, with wing aspect-ratio tailoring delivering up to 24% fuel savings. These findings will be refined through detailed disciplinary analyses in future work. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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10 pages, 3760 KB

Open AccessProceeding Paper

Design and Integrated Verification of Hybrid-Electric Power System for Regional Aircraft

by Andrea Terracciano, Pierpaolo Borrelli, Elias Allegaert, Gerardo Carbonaro, Danilo Ciliberti, Vito Primavera, Alfredo Renzetti, Fabien Retho and Novella Saccenti

Eng. Proc. 2026, 133(1), 8; https://doi.org/10.3390/engproc2026133008 - 16 Apr 2026

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Abstract

The design of Hybrid-Electric Regional (HER) aircraft represents a great challenge due to the systems’ complexity and their level of integration and results in a great expense of resources. To overcome these issues, the Open Digital Environment for Hybrid-Electric Regional Architecture (ODE4HERA) project [...] Read more.

The design of Hybrid-Electric Regional (HER) aircraft represents a great challenge due to the systems’ complexity and their level of integration and results in a great expense of resources. To overcome these issues, the Open Digital Environment for Hybrid-Electric Regional Architecture (ODE4HERA) project is developing an Open Digital Platform (ODP) to accelerate the design process. The platform is validated using a pilot case which focuses on powertrain systems and covers the entire development process, from requirements definition to Virtual Integrated Verification and Validation (IV&V). At first, the design is performed using state-of-the-art tools; then it is repeated using preliminary ODP modules to evaluate the achieved benefits. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 1128 KB

Open AccessProceeding Paper

Possibilities of Using Quaternion Methods in Helmet-Mounted Cueing Systems in Order to Increase Their Operation Reliability

by Sławomir Michalak, Andrzej Szelmanowski, Andrzej Pazur and Pawel Janik

Eng. Proc. 2026, 133(1), 9; https://doi.org/10.3390/engproc2026133009 - 16 Apr 2026

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Abstract

The article reviews the methods of determining the angular position of a pilot’s helmet used on board modern aircraft, and analyzes the methods of determining the angular position of an object used in aviation spatial orientation and inertial navigation systems. A functional analysis [...] Read more.

The article reviews the methods of determining the angular position of a pilot’s helmet used on board modern aircraft, and analyzes the methods of determining the angular position of an object used in aviation spatial orientation and inertial navigation systems. A functional analysis of the NSC-1 Orion helmet-mounted targeting system developed at AFIT was performed. The main part of the work consists of the development of new, original mathematical models for determining the angular position of the pilot’s helmet using quaternions, simulation studies of these models, and experimental verification of their results. The stages necessary for the development of mathematical models and their proper testing for disturbances occurring in the measurement of gravitational acceleration (sensor errors and acceleration from maneuvers) and the magnetic field (sensor errors and the influence of the aircraft’s own magnetic field) are presented. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 4573 KB

Open AccessProceeding Paper

Performance Analysis of a Commercial Aircraft Liquid Hydrogen Storage System

by Alireza Ebrahimi, Andrew Rolt, Drewan Sanders and B. Deneys J. Schreiner

Eng. Proc. 2026, 133(1), 10; https://doi.org/10.3390/engproc2026133010 - 16 Apr 2026

Viewed by 804

Abstract

Liquid hydrogen (LH₂) fuel system architectures for aviation remain at low Technology Readiness Levels (TRLs) due to limited experimental data and the challenges of modelling cryogenic hydrogen’s behavior. This paper presents a computationally efficient framework for sensitivity analysis that integrates cryogenic [...] Read more.

Liquid hydrogen (LH₂) fuel system architectures for aviation remain at low Technology Readiness Levels (TRLs) due to limited experimental data and the challenges of modelling cryogenic hydrogen’s behavior. This paper presents a computationally efficient framework for sensitivity analysis that integrates cryogenic thermodynamics, tank geometry, external heat ingress, engine mass flow demands, and pressurization control strategies. A set of operational scenarios was modeled to demonstrate how tank pressure and temperature evolve under various control and geometric conditions, delivering five key insights: (1) Passive tank self-pressurization leads to continuous pressure rise and subcooled liquid. (2) LH₂ withdrawal alone may not fully stop pressurization with high heat ingress. (3) Gaseous hydrogen (GH₂) injection stabilizes pressure only up to moderate heat ingress during LH₂ extraction. (4) The addition of venting enables full pressure control. (5) Tank geometry and heat flux govern transient behavior. Spherical tanks show slower pressure and temperature rise than cylindrical ones, and both geometries maintain near-constant pressure at low heat flux. These insights offer practical guidance for designing reliable and thermally stable LH₂ storage systems for future aircraft applications, paving the way towards sustainable and zero-emission aviation. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 457 KB

Open AccessProceeding Paper

UAV Guidance with Concurrent Evasion and Terminal Angle Constraints

by Ekrem Berkcan Bavbek and Ilker Murat Koç

Eng. Proc. 2026, 133(1), 11; https://doi.org/10.3390/engproc2026133011 - 17 Apr 2026

Viewed by 547

Abstract

This paper proposes a 3D terminal-constraint guidance framework for a UAV, modeled here as a missile-like attacker vehicle, that improves survivability against an incoming anti-air missile (AAM) while enforcing a prescribed terminal approach direction to a stationary ground target. The UAV uses Generalized [...] Read more.

This paper proposes a 3D terminal-constraint guidance framework for a UAV, modeled here as a missile-like attacker vehicle, that improves survivability against an incoming anti-air missile (AAM) while enforcing a prescribed terminal approach direction to a stationary ground target. The UAV uses Generalized Vector Explicit Guidance (GENEX) augmented by a rotating lateral sinusoidal bias that generates a barrel-roll-like evasive motion. The AAM employs classical proportional navigation (PNG). Both vehicles include a fifth-order binomial acceleration-command realization with explicit lateral saturation. Parametric simulations show that the proposed bias can increase survivability while maintaining terminal accuracy. Performance is primarily governed by the evasive frequency and amplitude, the guidance time constants, and the available lateral acceleration budget. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 947 KB

Open AccessProceeding Paper

Common Unit Competence Scheme Framework: A Methodology for Facilitating Enhancement and Unification of Different ANSPs Currency Requirements

by Francisco Pérez Moreno, Mateo Hermida Santos, Raquel Delgado-Aguilera Jurado, María Zamarreño Suárez, César Gómez Arnaldo and Víctor Fernando Gómez Comendador

Eng. Proc. 2026, 133(1), 12; https://doi.org/10.3390/engproc2026133012 - 17 Apr 2026

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Abstract

Air traffic controllers (ATCOs) are currently constrained by a sector-based competence endorsement model that requires extensive, sector-specific training and limits operational flexibility. To address this, the SESAR project IFAV3 proposes solutions to facilitate service provision flexibility. A fundamental part of achieving this objective [...] Read more.

Air traffic controllers (ATCOs) are currently constrained by a sector-based competence endorsement model that requires extensive, sector-specific training and limits operational flexibility. To address this, the SESAR project IFAV3 proposes solutions to facilitate service provision flexibility. A fundamental part of achieving this objective is to have a common regulatory framework which allows one to provide a service in a different airspace. The Common Unit Competence Scheme (CUCS) is a unified framework designed to harmonize the endorsement process across Europe. The CUCS is a methodology that aims to create a framework for Air Navigation Services Providers (ANSPs), which emphasizes training, planning and endorsement processes across multiple sector groups and Air Traffic Service Units (ATSUs) while remaining compliant with Regulation (EU) 2015/340 and Regulation (EU) 2017/373. CUCS intends to enhance interoperability and workforce adaptability, being a necessary step towards ATCO’s flexibility to operate across a wider range of sectors. This paper outlines the CUCS methodology, detailing its intended benefits and its limitations, and concludes by presenting a set of practical use cases that illustrates its potential implementation in diverse operational scenarios. The methodology allows any ANSP to implement the operational strategy that best suits its needs, guaranteeing compliance with regulations and favouring greater flexibility in the provision of ATC services. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 2771 KB

Open AccessProceeding Paper

Investigation of Leading-Edge Dogtooth Extensions on the Low-Speed Aerodynamics of a BWB UAV

by Spyridon Antoniou, Petros Dimitrentsis, Pericles Panagiotou and Kyros Yakinthos

Eng. Proc. 2026, 133(1), 13; https://doi.org/10.3390/engproc2026133013 - 17 Apr 2026

Viewed by 524

Abstract

This study investigates the effect of passive leading-edge dogtooth extensions on the low-speed aerodynamic performance and pitch stability of a tactical Blended-Wing-Body (BWB) Unmanned Aerial Vehicle (UAV). The focus is the mitigation and the delay of the pitch break phenomenon, i.e., the sudden [...] Read more.

This study investigates the effect of passive leading-edge dogtooth extensions on the low-speed aerodynamic performance and pitch stability of a tactical Blended-Wing-Body (BWB) Unmanned Aerial Vehicle (UAV). The focus is the mitigation and the delay of the pitch break phenomenon, i.e., the sudden loss of longitudinal stability occurring at high angles of attack, during critical flight segments such as take-off and landing. A total of 15 dogtooth configurations are examined, where high-fidelity CFD simulations are conducted over a range of angles of attack, under both low- and high-speed flight conditions for the determination of the aerodynamic behavior of the UAV. The analysis focuses on extracting the key metrics related to pitch stability, including the speed at which pitch break appears, the deviation in pitching moment coefficient (ΔCm) at pitch break, and the corresponding angle of attack at which the phenomenon occurs. The results show that several configurations contribute to delaying the onset of pitch break and reducing ΔCm, indicating improved longitudinal stability. Notch-assisted dogtooth configurations further enhance these effects with minimal aerodynamic penalties. Overall, the study demonstrates that passive leading-edge modifications offer a viable and efficient solution for enhancing the low-speed aerodynamic behavior and control characteristics of BWB UAVs. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 1234 KB

Open AccessProceeding Paper

Advancing Sustainable Aviation: Insights from Methodologies, Technologies, and Policy Frameworks for Climate Impact Mitigation

by Edoardo Bucchignani, Alessandra L. Zollo, Veronica Villani, Lidia Travascio, Mario A. Solazzo and Angela Vozella

Eng. Proc. 2026, 133(1), 14; https://doi.org/10.3390/engproc2026133014 - 17 Apr 2026

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Abstract

This work provides an extensive analysis of the different methodologies and related findings and implications of several projects that address the climate impact of aviation. By analyzing EU-funded initiatives and other significant projects worldwide, several critical insights have been drawn about how aviation [...] Read more.

This work provides an extensive analysis of the different methodologies and related findings and implications of several projects that address the climate impact of aviation. By analyzing EU-funded initiatives and other significant projects worldwide, several critical insights have been drawn about how aviation contributes to climate change and the potential pathways to mitigate these impacts. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 2385 KB

Open AccessProceeding Paper

A Parametric APDL-Based Workflow for Efficient Structural Design of a Civil Aircraft Tailplane

by Concetta Palumbo, Gaetano Perillo, Antonio Sodano, Domenico Cristillo, Marika Belardo and Antonio Chiariello

Eng. Proc. 2026, 133(1), 15; https://doi.org/10.3390/engproc2026133015 - 17 Apr 2026

Viewed by 401

Abstract

This paper presents a parametric finite element procedure developed in ANSYS APDL to support the early structural design of a civil aircraft horizontal tailplane (HTP). The automated workflow generates geometry, mesh, material definition, load application, and structural analyses through a fully parametric script, [...] Read more.

This paper presents a parametric finite element procedure developed in ANSYS APDL to support the early structural design of a civil aircraft horizontal tailplane (HTP). The automated workflow generates geometry, mesh, material definition, load application, and structural analyses through a fully parametric script, enabling rapid and repeatable design iterations. Key geometric and structural parameters can be easily adjusted to evaluate alternative configurations. Developed within the HERFUSE project under the Clean Aviation program, this method provides early metrics such as stress, displacement, and mass. Its modular structure also allows adaptation to other aircraft components and integration into multidisciplinary design and optimization frameworks. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 963 KB

Open AccessProceeding Paper

A Systematic Review of Circularity and Sustainability Strategies in the Space Industry

by Joanna Steiner, Sebastian Wehking, Theresa Riedelsheimer and Kai Lindow

Eng. Proc. 2026, 133(1), 16; https://doi.org/10.3390/engproc2026133016 - 19 Apr 2026

Viewed by 687

Abstract

This study presents a systematic analysis of circular economy (CE) and sustainability strategies in the space industry. Based on a comprehensive literature review across Scopus, IEEE Xplore and Web of Science, it identifies current and future needs as well as digital technology and [...] Read more.

This study presents a systematic analysis of circular economy (CE) and sustainability strategies in the space industry. Based on a comprehensive literature review across Scopus, IEEE Xplore and Web of Science, it identifies current and future needs as well as digital technology and organizational demands for implementing circularity in space systems. Findings reveal that established CE strategies are scarcely applied to space missions, while digitalization efforts mainly focus on system optimization. Furthermore, the most relevant CE strategies for the space industry were determined. Future research should explore the transfer of proven CE approaches from terrestrial industries beyond the Kármán line and assess the potential of orbital resource loops. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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7 pages, 16795 KB

Open AccessProceeding Paper

Process Optimization and Automated Manufacturing of Type V Hydrogen Storage Tank

by Prasad Shimpi, Beatriz Gomes, Mario Fernández-Pedrera, Maria Ivette Coto and Pablo Romero-Rodriguez

Eng. Proc. 2026, 133(1), 17; https://doi.org/10.3390/engproc2026133017 - 20 Apr 2026

Viewed by 643

Abstract

This research work is aimed at developing and manufacturing thermoplastic-composite parts for a Type V hydrogen storage tank based on a patented design. A 57% fibre volume fraction of a carbon fibre and polyamide 11 (PA11) thermoplastic matrix was used in an automated [...] Read more.

This research work is aimed at developing and manufacturing thermoplastic-composite parts for a Type V hydrogen storage tank based on a patented design. A 57% fibre volume fraction of a carbon fibre and polyamide 11 (PA11) thermoplastic matrix was used in an automated tape layup (ATL) process to manufacture a laser-assisted in situ-consolidated composite part for a hydrogen storage vessel. A series of mechanical and thermal tests were performed to optimize the process parameters for composite manufacturing. Based on the optimized process parameters, a scaled-up demonstrator composite part was manufactured and demoulded using pressurized air. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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11 pages, 5292 KB

Open AccessProceeding Paper

Elaboration and Evaluation of Concepts for Battery Modules in Electrified Aircraft Propulsion Systems

by Alperen Oğuzhan Altun, Florian Franke and Stefan Kazula

Eng. Proc. 2026, 133(1), 18; https://doi.org/10.3390/engproc2026133018 - 20 Apr 2026

Viewed by 699

Abstract

The weight of battery modules keeps hindering them from being commercially attractive as the sole power supply for short-range electric passenger flights. Furthermore, the challenging requirements for aerospace applications limit the range of options for module elements and complicate the implementation of lightweight [...] Read more.

The weight of battery modules keeps hindering them from being commercially attractive as the sole power supply for short-range electric passenger flights. Furthermore, the challenging requirements for aerospace applications limit the range of options for module elements and complicate the implementation of lightweight solutions. Hence, the objective of this study is to elaborate and evaluate concepts for battery modules to identify promising solutions for electrified aircraft propulsion systems. For that purpose, a house of quality is compiled to assess the relations between options for module elements and module requirements, as well as correlations between options. Potential concepts are elaborated by combining suitable elements. Finally, the concepts are evaluated to highlight the most preferable and compatible ones for aircraft battery modules. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 1759 KB

Open AccessProceeding Paper

Overall Design and Technology Integration for a Nine-Seater Hydrogen-Electric Commuter Aircraft Concept

by Sören Kolb-Geßmann, Jonas Ludowicy, Ivo Zell and Thomas Zill

Eng. Proc. 2026, 133(1), 19; https://doi.org/10.3390/engproc2026133019 - 20 Apr 2026

Viewed by 458

Abstract

New propulsion technologies not only allow reducing the climate effect of aircraft, but also enable new architectures and integration options. To make use of this increased design space variety, new design methods need to be developed. In this work, an existing design process [...] Read more.

New propulsion technologies not only allow reducing the climate effect of aircraft, but also enable new architectures and integration options. To make use of this increased design space variety, new design methods need to be developed. In this work, an existing design process for CS-23 hydrogen-electric aircraft is expanded with the capability to design various powertrain options. These methods are used to evaluate the designs of two different concepts for small commuter aircraft with centralized and distributed fuel cell (FC) systems, respectively. The results show that the overall mass and performance of both concepts are very similar. However, the concept with distributed FC systems has a lower energy consumption, better FC cooling, and improved maintainability. Thus, the distributed concept is chosen. The final design has the powertrain components distributed among 10 engine pods. To transport nine passengers over 600 km without exceeding the targeted Maximum Take-off Mass (MTOM) of 5700 kg, the propulsion system’s power-to-weight ratio needs to be improved by 1.2% from the current technology level. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 1856 KB

Open AccessProceeding Paper

Vision-Based Relative Attitude and Position Estimation for Small Satellites with Robust Filtering Technique

by Elif Koc and Halil Ersin Soken

Eng. Proc. 2026, 133(1), 20; https://doi.org/10.3390/engproc2026133020 - 20 Apr 2026

Viewed by 604

Abstract

Relative satellite navigation is critical for formation flying, rendezvous, and docking. This study augments a vision-based relative navigation framework with a robust multiplicative extended Kalman filter (RMEKF) that adaptively scales the measurement covariance using innovation-based covariance matching and a chi-square fault-detection test. A [...] Read more.

Relative satellite navigation is critical for formation flying, rendezvous, and docking. This study augments a vision-based relative navigation framework with a robust multiplicative extended Kalman filter (RMEKF) that adaptively scales the measurement covariance using innovation-based covariance matching and a chi-square fault-detection test. A two-spacecraft scenario is simulated in which a deputy monocular camera observes six active beacons on a chief spacecraft. To evaluate fault tolerance, constant line-of-sight (LOS) errors are injected on two beacon measurements during a fixed interval. Over the fault-centered evaluation window, the RMEKF reduces attitude root mean square error (RMSE) by approximately 71–73% compared to the conventional multiplicative extended Kalman filter (MEKF), while also improving relative/orbital state accuracy by 19–93%. These results indicate improved robustness to LOS measurement faults without degrading overall estimation stability. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 1900 KB

Open AccessProceeding Paper

Enhancing Product Design in Electric Aviation Through Digital Twins and Production Feedback Integration

by Jörg Brünnhäußer, Magdalena Dziubinska, Umer Zakheer, Vadym Bilous, Thomas Zimmermann, Robert Joost and Kai Lindow

Eng. Proc. 2026, 133(1), 21; https://doi.org/10.3390/engproc2026133021 - 20 Apr 2026

Viewed by 500

Abstract

Electric flight accelerates innovation and demands digitalization. DIREKT develops digital twins across the lifecycle of (hybrid) electric propulsion systems to fuse data, cut costs, and shorten time-to-market. In this context we present a production-to-design feedback approach. A system is developed which compares the [...] Read more.

Electric flight accelerates innovation and demands digitalization. DIREKT develops digital twins across the lifecycle of (hybrid) electric propulsion systems to fuse data, cut costs, and shorten time-to-market. In this context we present a production-to-design feedback approach. A system is developed which compares the scanned manufactured part with the design to visualize manufacturing deviations to improve upcoming designs. The system is tested with three different additive manufacturing technologies and two parts from an urban air mobility electric propulsion system. Furthermore, the comparison data is stored in a knowledge base for machine-learning-driven deviation prediction later on. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 2191 KB

Open AccessProceeding Paper

Dynamic Simulation and Comparison of Nanofluid Applications on Aircraft Thermal Management System

by Sofia Caggese, Flavio Di Fede, Marco Fioriti and Grazia Accardo

Eng. Proc. 2026, 133(1), 22; https://doi.org/10.3390/engproc2026133022 - 20 Apr 2026

Viewed by 459

Abstract

Due to advancements in thermal engineering and nanotechnology, nanofluids—base fluids containing dispersed nanoparticles (1–100 nm)—have emerged as promising high-performance coolants. Their enhanced thermal properties make them attractive for application in hybrid-electric aircraft, which require efficient Thermal Management Systems (TMS) to dissipate significant heat [...] Read more.

Due to advancements in thermal engineering and nanotechnology, nanofluids—base fluids containing dispersed nanoparticles (1–100 nm)—have emerged as promising high-performance coolants. Their enhanced thermal properties make them attractive for application in hybrid-electric aircraft, which require efficient Thermal Management Systems (TMS) to dissipate significant heat loads. This study employs a dynamic TMS model to assess the influence of key nanofluid features, including nanoparticle type, volume fraction, particle diameter, and base fluid. Metal nanoparticles provided the greatest thermal improvement (up to 19%). Increasing concentration enhanced cooling efficiency, with 0.5%, 1%, and 2% volume fractions reducing mean temperature by 14%, 19%, and 24%, respectively. Smaller particles performed better, as 20 nm nanoparticles achieved a 21.3% temperature reduction compared to 17.5% for 60 nm. Water-based nanofluids exhibited the best overall thermal behaviour, although they remain unsuitable for aeronautical applications. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 3104 KB

Open AccessProceeding Paper

Integration of Functional Mock-Up Units into Digital Twins of Aircraft Thermal Management Systems

by Tobias Reischl, Corentin Lepais and Raphael Gebhart

Eng. Proc. 2026, 133(1), 23; https://doi.org/10.3390/engproc2026133023 - 20 Apr 2026

Viewed by 385

Abstract

Hybrid-electric regional aircraft require detailed thermal management digital twins to assess performance and feasibility while reducing physical test effort. The Functional Mock-Up Interface (FMI) enables partners to exchange subsystem models as Functional Mock-Up Units (FMUs) for gate-to-gate simulation while preserving intellectual property. However, [...] Read more.

Hybrid-electric regional aircraft require detailed thermal management digital twins to assess performance and feasibility while reducing physical test effort. The Functional Mock-Up Interface (FMI) enables partners to exchange subsystem models as Functional Mock-Up Units (FMUs) for gate-to-gate simulation while preserving intellectual property. However, FMU integration introduces numerical coupling challenges, interface overhead, and potential loss of accuracy depending on the integration method. Benchmarking against a DLR Thermofluid Stream (TFS) reference model showed that FMU-based co-simulation can significantly increase computational effort, specifically from 8 min up to 2.5 h. Control-based integration further implicates transient deviations due to filtering, although steady-state accuracy generally remains unchanged. Therefore, it is mandatory to evaluate and compare FMU integration strategies to show that digital twin performance targets remain achievable when design, solver settings, and filtering are only applied selectively and systematically. The results show clear design guidance: employ native fluid libraries when possible for speed and accuracy, use FMU paired with adapters and without filters for accuracy, and reserve filtering for numerical stabilization only. Using a control approach to integrate the FMU improves simulation speed compared to adapters but introduces a small error, which in turn reduces simulation accuracy. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 378 KB

Open AccessProceeding Paper

2U CubeSat Design to Provide Space-Based ICNS Services

by Alex Ganau and Amilcar Rincon Charris

Eng. Proc. 2026, 133(1), 24; https://doi.org/10.3390/engproc2026133024 - 20 Apr 2026

Viewed by 638

Abstract

This project focuses on the development of a 2U CubeSat intended for potential integration into an LEO constellation. The CubeSat is designed to deliver space-based CNS services, supporting the evolving needs of next-generation airspace and global communication networks. The primary objective is to [...] Read more.

This project focuses on the development of a 2U CubeSat intended for potential integration into an LEO constellation. The CubeSat is designed to deliver space-based CNS services, supporting the evolving needs of next-generation airspace and global communication networks. The primary objective is to enhance global connectivity and demonstrate how compact satellite platforms can contribute to modern ICNS systems. By leveraging the flexibility, scalability, and cost-efficiency of CubeSat technology, the mission aims to validate the role of small satellites in delivering reliable and responsive CNS capabilities. This approach provides a foundation for future advancements in satellite constellations tailored for airspace management and communication services. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 358 KB

Open AccessProceeding Paper

Air Traffic Demand Forecasting for Origin–Destination Airport Pairs Using Artificial Intelligence

by Alicia Serrano Ortega, Albert Ruiz Martín and Clara Argerich Martín

Eng. Proc. 2026, 133(1), 25; https://doi.org/10.3390/engproc2026133025 - 20 Apr 2026

Viewed by 715

Abstract

The accurate anticipation of passenger demand across specific origin–destination (OD) airport routes is a cornerstone of strategic and operational decision-making within the global aviation sector, including airlines optimizing fleet and route management, airports planning infrastructure development, and regulatory bodies overseeing airspace efficiency. However, [...] Read more.

The accurate anticipation of passenger demand across specific origin–destination (OD) airport routes is a cornerstone of strategic and operational decision-making within the global aviation sector, including airlines optimizing fleet and route management, airports planning infrastructure development, and regulatory bodies overseeing airspace efficiency. However, conventional forecasting techniques frequently encounter limitations when confronted with the inherent complexities and non-linear interdependencies that characterize air travel demand patterns. These patterns are shaped by an array of dynamic variables, including macroeconomic trends, population dynamics, distinct seasonal variations, and emergent phenomena. This investigation evaluates the utility of Artificial Intelligence (AI) paradigms in constructing predictive models for monthly passenger volumes between international OD airport pairs. This work highlights the ongoing transformative impact of AI methodologies on forecasting tasks within the aviation industry. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 1426 KB

Open AccessProceeding Paper

Electrical Energy Storage and Conversion System Sizing, Performance and Battery Degradation in Hybrid Electric Regional Aircraft

by Emina Hadžialić, Paolo Aliberti, Alexander Ryzhov, Helmut Kühnelt and Marco Sorrentino

Eng. Proc. 2026, 133(1), 26; https://doi.org/10.3390/engproc2026133026 - 21 Apr 2026

Viewed by 484

Abstract

To meet aviation decarbonization goals, novel electric energy storage systems are required. A promising approach combines a Li-ion battery with a hydrogen proton exchange membrane fuel cell system (PEMFCS) into an electrochemical energy storage and conversion (EC-ESC) system. Proper power management ensures efficiency, [...] Read more.

To meet aviation decarbonization goals, novel electric energy storage systems are required. A promising approach combines a Li-ion battery with a hydrogen proton exchange membrane fuel cell system (PEMFCS) into an electrochemical energy storage and conversion (EC-ESC) system. Proper power management ensures efficiency, reliability and durability. The study investigates EC-ESC performance for regional hybrid electric aircraft under varying degrees of hybridization. By systematically adjusting the power split between the battery and FCS, we quantify its impacts on system sizing, energy efficiency and battery degradation. The results show that a well-balanced power distribution enhances overall efficiency and energy density while extending system lifetime. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 1721 KB

Open AccessProceeding Paper

DFKI-X2D: Design and Testing of a Quasi-Direct Drive Motor for Space Applications

by Jonas Eisenmenger, Zhongqian Zhao, Pierre Willenbrock and Wiebke Brinkmann

Eng. Proc. 2026, 133(1), 27; https://doi.org/10.3390/engproc2026133027 - 21 Apr 2026

Viewed by 289

Abstract

Due to the high level of innovation involved, and the requirements arising from a new environment, the use of a quasi-direct drive motor for space applications presents not only several challenges, but also great opportunities. Such a motor is particularly well-suited to dynamic [...] Read more.

Due to the high level of innovation involved, and the requirements arising from a new environment, the use of a quasi-direct drive motor for space applications presents not only several challenges, but also great opportunities. Such a motor is particularly well-suited to dynamic applications like walking robots or robotic arms. To ensure that it can withstand the environmental challenges, the motor must undergo extensive testing. This paper briefly outlines the development of such a motor based on prior prototypes with different design concepts. It addresses the specific requirements of a space variant and describes the selected final design. Additionally, the development of corresponding motor electronics is described. Finally, the results of a test campaign are presented. The campaign included internal functional tests to characterize the motor and external environmental tests necessary for space qualification. These tests included vibration, thermal vacuum chamber (TVAC) and electromagnetic compatibility (EMC) tests. Together, they showcased a highly dynamic motor with an efficiency of up to 90% and moved it towards a technology readiness level (TRL) of 5. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 199 KB

Open AccessProceeding Paper

The Impact of Environmental Taxation on Airline Supply Decisions in Europe: Low-Cost Carrier Responses and Regional Implications

by Michał J. Wichrowski and Viktor Trasberg

Eng. Proc. 2026, 133(1), 28; https://doi.org/10.3390/engproc2026133028 - 21 Apr 2026

Viewed by 753

Abstract

This paper studies how European low-cost carriers (LCCs) adjust and mitigate in response to environmental taxation over the past decade. Global and EU frameworks—most prominently the Emissions Trading System (EU-ETS) and CORSIA—have raised carbon-related compliance costs, while several European states have introduced or [...] Read more.

This paper studies how European low-cost carriers (LCCs) adjust and mitigate in response to environmental taxation over the past decade. Global and EU frameworks—most prominently the Emissions Trading System (EU-ETS) and CORSIA—have raised carbon-related compliance costs, while several European states have introduced or increased aviation-specific taxes. Given their cost-sensitive business models, LCCs are especially responsive to tax-induced cost shocks. The paper is structured in three parts: an overview of global aviation taxation, a review of national initiatives in selected European countries and an analysis of how LCCs respond to mitigate these impacts. We assemble a hand-collected panel of ten European LCCs and conduct qualitative documentary analysis of annual and sustainability reports (2020–2024), triangulated with regulatory and policy documents. The findings indicate consistent adaptation via selective airfare price pass-through, capacity reallocation away from higher-tax, price-elastic short-haul routes and efficiency gains through fleet renewal and operational measures. We also document targeted stakeholder messaging and advocacy—public campaigns, legal challenges, and, in some jurisdictions, legal disputes—aimed at softening tax design burden. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

9 pages, 3103 KB

Open AccessProceeding Paper

Experimental Sloshing Regimes in Horizontal Cylindrical Tanks

by Florin Feștilă, Lucian Constantin, Maria Casapu, Amado Ștefan and Paul-Virgil Roșu

Eng. Proc. 2026, 133(1), 29; https://doi.org/10.3390/engproc2026133029 - 21 Apr 2026

Viewed by 1204

Abstract

The use of liquid hydrogen (LH₂) as a civil aircraft fuel is gaining attention due to increasing environmental concerns associated with conventional fossil fuels. The EU-funded HASTA (Hydrogen Aircraft Sloshing Tank Advancement) project aims to investigate, both experimentally and numerically, the [...] Read more.

The use of liquid hydrogen (LH₂) as a civil aircraft fuel is gaining attention due to increasing environmental concerns associated with conventional fossil fuels. The EU-funded HASTA (Hydrogen Aircraft Sloshing Tank Advancement) project aims to investigate, both experimentally and numerically, the storage of LH₂ in civil aircraft, ultimately providing design guidelines for cryogenic fuel tanks. A critical phenomenon affecting airborne cryogenic tanks is the ullage pressure drop, which can occur due to in-flight excitations that induce mixing between the liquid and gas phases. As an initial step toward understanding the sloshing dynamics in LH₂ tanks, this study investigated isothermal sloshing in a small-scale, horizontal cylindrical tank. An experimental campaign was conducted using an 80 mm × 120 mm cylindrical horizontal tank, partially filled with deionised water and subjected to vertical sinusoidal excitation. The objective was to map the liquid response regimes to the excitation frequency–amplitude range of interest. A sloshing regime map was obtained, providing a key understanding of the liquid dynamics, indicating excitation amplitudes and frequencies that can lead to phase mixing. Ten distinct sloshing modes were observed within the 4–10 Hz excitation frequency range, with this study focusing on mode (1 0), the lowest-frequency response and particularly critical for such systems. The modal frequency and damping were obtained using a sloshing surface identification algorithm, and the relationship between the sloshing force and tank displacement/velocity was analysed to provide insight into the sloshing regime. Apart from providing important insights into the sloshing regimes inside horizontal cylindrical tanks, this research also establishes the experimental characteristics needed for future numerical model calibration. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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6 pages, 197 KB

Open AccessProceeding Paper

Overview of Research on Multi-Robot Teams for Space Applications in Europe

by Malte Wirkus, Wiebke Brinkmann and Carlos J. Perez del Pulgar Mancebo

Eng. Proc. 2026, 133(1), 30; https://doi.org/10.3390/engproc2026133030 - 21 Apr 2026

Viewed by 297

Abstract

Multi-robot systems (MRSs) are promising solutions for complex tasks because different capabilities can be distributed among several systems, resulting in simpler systems, redundancy, and scalability opportunities. This makes MRSs well-suited for planetary and space operation missions. This work reviews and categorizes several approaches [...] Read more.

Multi-robot systems (MRSs) are promising solutions for complex tasks because different capabilities can be distributed among several systems, resulting in simpler systems, redundancy, and scalability opportunities. This makes MRSs well-suited for planetary and space operation missions. This work reviews and categorizes several approaches to multi-robotic teams in Europe into an adapted and extended classification scheme from the MRS literature. This paper presents the classification scheme and interprets the results of the literature review to identify research trends within the European space robotics community and pinpoint research gaps. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 2511 KB

Open AccessProceeding Paper

Conceptual Study of 80-Pax Fuel Cell-Driven Aircraft for Sustainable Aviation

by Diego Giuseppe Romano, Etienne Guillame Behar, Riccardo Premuni, Mattia Barbarino, Gianpiero Buzzo and Giovanni Fasulo

Eng. Proc. 2026, 133(1), 31; https://doi.org/10.3390/engproc2026133031 - 21 Apr 2026

Viewed by 522

Abstract

The growing need to reduce aviation’s carbon footprint and reliance on fossil fuels has prompted the exploration of alternative propulsion technologies. Fuel cell (FC) systems offer a sustainable solution, generating only water vapor as a by-product. This paper presents a conceptual study, focusing [...] Read more.

The growing need to reduce aviation’s carbon footprint and reliance on fossil fuels has prompted the exploration of alternative propulsion technologies. Fuel cell (FC) systems offer a sustainable solution, generating only water vapor as a by-product. This paper presents a conceptual study, focusing on subsystem integration and safety aspects, for an 80-passenger, hydrogen-powered aircraft developed within the European Union (EU) co-funded NEWBORN (NExt generation high poWer fuel cells for airBORNe applications) Project. The designed configuration incorporates wing-mounted pods housing fuel cells, an electric motor, an inverter, a Thermal Management System (TMS), and Balance of Performance (BoP). This configuration is an effort towards environmentally friendly solutions, addressing climate change and paving the way towards greener aviation. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 1185 KB

Open AccessProceeding Paper

Tangential Interpolation for the Operational Modal Analysis of Aeronautical Structures

by Gabriele Dessena, Marco Civera and Oscar E. Bonilla-Manrique

Eng. Proc. 2026, 133(1), 32; https://doi.org/10.3390/engproc2026133032 - 21 Apr 2026

Cited by 1 | Viewed by 381

Abstract

Notable advances in modal analysis in the last 50 years have paved the way for more widespread use of modal parameters, including those from in situ measurements, in Structural Health Monitoring and finite element model updating. Current state-of-the-art techniques in output-only modal analysis [...] Read more.

Notable advances in modal analysis in the last 50 years have paved the way for more widespread use of modal parameters, including those from in situ measurements, in Structural Health Monitoring and finite element model updating. Current state-of-the-art techniques in output-only modal analysis include Stochastic Subspace Identification techniques, such as Canonical Variate Analysis (SSI), and the Natural Excitation Technique with the Eigensystem Realization Algorithm (NExT-ERA). The former have been shown to struggle on very large systems and the latter suffers from the usual fitting problems arising in noisy environments. In this work, an output-only version of the frequency domain technique known as the Loewner Framework (LF) is pioneeringly applied to an aeronautical system. The implementation pairs the LF with NExT (NExT-LF) to exploit the fitting process efficiency of the former and robustness to noise of the latter. The thus-defined NExT-LF is then applied to the well-known experimental benchmark of the eXperimental BeaRDS 2 high-aspect-ratio wing main spar. The results are compared to the known experimental values and those obtained from SSI and NExT-ERA. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 1787 KB

Open AccessProceeding Paper

Flow Characterization Around a Mars Rover Model at Extremely Low Reynolds Number

by Jaime Fernández-Antón, Rafael Bardera-Mora, Ángel Rodríguez-Sevillano, Juan Carlos Matías-García and Estela Barroso-Barderas

Eng. Proc. 2026, 133(1), 33; https://doi.org/10.3390/engproc2026133033 - 22 Apr 2026

Viewed by 318

Abstract

This work presents an experimental aerodynamic study of a Mars rover model, aimed at characterizing its flow behavior under Martian environmental conditions. Due to the extremely low Reynolds numbers associated with Mars’ thin atmosphere, the experiments were conducted using a scaled model of [...] Read more.

This work presents an experimental aerodynamic study of a Mars rover model, aimed at characterizing its flow behavior under Martian environmental conditions. Due to the extremely low Reynolds numbers associated with Mars’ thin atmosphere, the experiments were conducted using a scaled model of the rover manufactured via additive techniques. The study first focuses on understanding how the geometry of the rover influences the overall flow field, identifying key aerodynamic features such as separation zones, vortical structures, and flow reattachment regions driven by the complexity of the vehicle. A comprehensive investigation of the flow around the model was performed using both a hydrodynamic towing tank with dye injection for qualitative visualization, and particle image velocimetry (PIV) for quantitative flow field analysis in wind tunnel tests. After the general flow characterization, a more detailed local analysis was conducted using laser Doppler anemometry (LDA). This phase of the study targeted precise velocity measurements at specific locations corresponding to the MEDA (Mars Environmental Dynamics Analyzer) wind sensors onboard the rover. Quantitative results indicate that the central body induces a local flow acceleration of 20% to 40% relative to the free stream while severe turbulence was recorded in specific angular sectors, with velocity fluctuations reaching up to 120% for Sensor 1 and 90% for Sensor 2. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 2012 KB

Open AccessProceeding Paper

Measurement-Based Investigation of Energy-Efficient and Comfortable Air Conditioning in Urban Air Mobility

by Christina Matheis, Victor Norrefeldt and Michael Visser

Eng. Proc. 2026, 133(1), 34; https://doi.org/10.3390/engproc2026133034 - 22 Apr 2026

Viewed by 316

Abstract

The idea of using air cabs urban mobility is increasingly becoming a reality. In this project, research is conducted on an energy-efficient air conditioning system for an air cab to efficiently combine range and comfort in the cabin. For this, both simulations using [...] Read more.

The idea of using air cabs urban mobility is increasingly becoming a reality. In this project, research is conducted on an energy-efficient air conditioning system for an air cab to efficiently combine range and comfort in the cabin. For this, both simulations using a zonal model are conducted, and a thermal air cab demonstrator platform is developed. Measurements in the air cab demonstrator are used to investigate passenger comfort under various climatic conditions, including warm and moderate environments. In addition, the study focuses on evaluating the energetic efficiency of various air conditioning systems such as air cooling and close-to-body climatization. The data analysis compares user comfort and energy efficiency across technologies based on established comfort standards. This allows recommendations for energy-efficient air conditioning to be identified. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 3717 KB

Open AccessProceeding Paper

A Machine Learning Approach to Predicting the Climate Impact of North Atlantic Flights

by Carlo Abate, Natalia Kravchenko, Nicolas Bellouin and Lydia Hill

Eng. Proc. 2026, 133(1), 35; https://doi.org/10.3390/engproc2026133035 - 22 Apr 2026

Viewed by 481

Abstract

Aviation emissions significantly contribute to climate change, with both CO₂ and non-CO₂ effects, such as contrails and nitrogen oxides. The aim of this paper was to develop a machine learning-based model to predict the climate impact of flights using atmospheric and [...] Read more.

Aviation emissions significantly contribute to climate change, with both CO₂ and non-CO₂ effects, such as contrails and nitrogen oxides. The aim of this paper was to develop a machine learning-based model to predict the climate impact of flights using atmospheric and emissions data. The proposed model, an LGMB Regressor algorithm, was trained on a dataset of atmospheric variables and algorithmic Climate Change Functions to forecast the cumulative impact of these emissions measured via the total average temperature response at 20 years (ATR20). In a test on five months of data pertaining to the North Atlantic Corridor, the LGBM Regressor model exhibited strong predictive performance, with an

R^{2}

score between 0.41 and 0.55 and a Mean Absolute Percentage Error between 2.68% and 5.11% depending on the month. This study shows the potential of machine learning to provide efficient, accurate climate impact assessments for aviation. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 2177 KB

Open AccessProceeding Paper

Numerical Assessment of the Tailplane Structure for a Civil Aircraft: Static, Modal, and Buckling Analysis in APDL

by Gaetano Perillo, Concetta Palumbo, Antonio Sodano, Domenico Cristillo, Antonio Chiariello and Marika Belardo

Eng. Proc. 2026, 133(1), 36; https://doi.org/10.3390/engproc2026133036 - 22 Apr 2026

Viewed by 302

Abstract

This work presents the numerical assessment of a civil aircraft horizontal tailplane (HTP) using a fully parametric structural model developed through the Ansys Parametric Design Language (APDL). The objective is to evaluate the structural integrity, efficiency, and dynamic behavior of the HTP under [...] Read more.

This work presents the numerical assessment of a civil aircraft horizontal tailplane (HTP) using a fully parametric structural model developed through the Ansys Parametric Design Language (APDL). The objective is to evaluate the structural integrity, efficiency, and dynamic behavior of the HTP under realistic operational conditions within the HERFUSE Clean Aviation framework. The study includes linear static analyses for load distribution and critical stress regions, modal analysis for dynamic response characterization, and linear buckling analyses to determine stability assessment. Safety margins are computed for representative load cases across spars, skins, and ribs. The workflow will be integrated and connected to Multidisciplinary Optimization (MDO) loops for higher-level design trade-offs. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 2321 KB

Open AccessProceeding Paper

Characterization of Dissimilar Titanium–Carbon Fiber Joints Manufactured by One-Shot Resin Transfer Molding for Aerospace Components

by Mario Román Rodríguez, Cristian Builes Cárdenas, Elena Rodríguez Senín and Adrián López González

Eng. Proc. 2026, 133(1), 37; https://doi.org/10.3390/engproc2026133037 - 22 Apr 2026

Viewed by 460

Abstract

The CAELESTIS project aims to promote the development and design of innovative aircraft and engine structures through an integrated ecosystem of simulations and digital tools, enabling synergy across all stages of the manufacturing process. The component selected was an Outlet Guide Vane (OGV), [...] Read more.

The CAELESTIS project aims to promote the development and design of innovative aircraft and engine structures through an integrated ecosystem of simulations and digital tools, enabling synergy across all stages of the manufacturing process. The component selected was an Outlet Guide Vane (OGV), a static engine part composed of a central composite section and titanium inserts at both ends, joined in a single manufacturing step. A detailed investigation of the joints between these materials was carried out using surface treatments of different natures to evaluate properties that directly influence the final joint quality. Optical analysis techniques were employed to characterize the morphology, roughness and surface free energy (SFE), complemented by mechanical tests to determine the adhesion and shear strength. All specimens were manufactured using the Resin Transfer Molding (RTM) “one-shot” process. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 3671 KB

Open AccessProceeding Paper

EFACA Aircraft Noise in Flight and Ground Operations on a Roadmap to ACARE Noise Goals

by Vitalii Makarenko, Kateryna Kazhan, Vadim Tokarev, Oleksandr Zaporozhets and Andrzej Chyla

Eng. Proc. 2026, 133(1), 38; https://doi.org/10.3390/engproc2026133038 - 22 Apr 2026

Viewed by 391

Abstract

This paper presents an integrated assessment of aircraft noise in flight and ground operations within the EFACA project, supporting the roadmap toward ACARE Flightpath-2050 noise goals. It summarizes required reductions, evaluates current technology readiness, and analyzes contributions from advanced propulsion concepts, propeller-noise modeling, [...] Read more.

This paper presents an integrated assessment of aircraft noise in flight and ground operations within the EFACA project, supporting the roadmap toward ACARE Flightpath-2050 noise goals. It summarizes required reductions, evaluates current technology readiness, and analyzes contributions from advanced propulsion concepts, propeller-noise modeling, and operational procedures. New seven-bladed propeller designs, validated through semi-empirical, analytical, and CAA methods, demonstrate substantial tonal-noise improvements, influencing the aircraft noise reductions by 2–4 dB depending on the fight stage, and during the ground operation by up to 5 dB. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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7 pages, 927 KB

Open AccessProceeding Paper

Smart Design of an Innovative Generation of Structural Resins Loaded with Carbon Nanostructured Forms

by Liberata Guadagno, Marialuigia Raimondo, Francesca Aliberti, Raffaele Longo, Michelina Catauro and Luigi Vertuccio

Eng. Proc. 2026, 133(1), 39; https://doi.org/10.3390/engproc2026133039 - 23 Apr 2026

Viewed by 278

Abstract

This study introduces advanced epoxy formulations incorporating carbon-based nanofillers, carbon nanotubes, nanofibers, and functionalized graphene. The epoxy matrix was optimized to lower moisture absorption and enhance multifunctional properties. A non-stoichiometric epoxy/hardener ratio reduced equilibrium water concentration (C_eq) by up to 30% [...] Read more.

This study introduces advanced epoxy formulations incorporating carbon-based nanofillers, carbon nanotubes, nanofibers, and functionalized graphene. The epoxy matrix was optimized to lower moisture absorption and enhance multifunctional properties. A non-stoichiometric epoxy/hardener ratio reduced equilibrium water concentration (C_eq) by up to 30% compared to unmodified epoxy, achieved by minimizing polar groups responsible for water bonding. These improvements benefit the aerospace, marine, and wind energy sectors. All nanofillers form a secondary phase with reduced glass transition temperature (T_g), but functionalized graphene performs best. Its self-assembled sheet architectures trap resin, limit water interaction, and create conductive pathways, improving strength, reducing moisture uptake, and achieving a low electrical percolation threshold (EPT). Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 3358 KB

Open AccessProceeding Paper

Connecting Simulation and Data Management Tools Through Open Standards to Support Hybrid Aircraft Design

by Klara Ziegler, Rafael Parzeller, Olexiy Kupriyanov, Elias Allegaert, Pierre Brionne, Roland Wüchner, Philippe Barabinot, Juan Manuel Lorenzi and Fabien Retho

Eng. Proc. 2026, 133(1), 40; https://doi.org/10.3390/engproc2026133040 - 22 Apr 2026

Viewed by 517

Abstract

The design process of complex systems, such as hybrid aircraft, consists of several stages that depend on each other. The product is virtually validated by simulations in various disciplines. Each of these stages and simulation disciplines is carried out by different experts and [...] Read more.

The design process of complex systems, such as hybrid aircraft, consists of several stages that depend on each other. The product is virtually validated by simulations in various disciplines. Each of these stages and simulation disciplines is carried out by different experts and they can choose from different tools in their field. The models created during this process are highly interdependent but are typically managed independently by each team. In this paper the first implementation of an open digital platform (ODP) is presented to provide a common data backbone for models from various tools and enable traceability across domains. An open data schema is used to ensure an open interface for the platform. This is implemented with SysML v2. In a proof of concept, two tools from different domains, simulation process and data management (SPDM) and product lifecycle management (PLM) using Teamcenter^® Simulation software and model-based design (MBD) using Simcenter™ Amesim™ software, are connected through this open standard. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 2056 KB

Open AccessProceeding Paper

ORCI: An Exploratory Data-Driven and Machine Learning Framework to Predict Aircraft Spacing on Final Approach—Case Study in Barcelona (LEBL)

by Rita Bañón, Alejandro Mateo-Vendrell and José Manuel Rísquez

Eng. Proc. 2026, 133(1), 41; https://doi.org/10.3390/engproc2026133041 - 24 Apr 2026

Viewed by 465

Abstract

The ORCI project aims to develop an AI-based decision-support tool to assist air traffic controllers in complex TMA operations, taking Barcelona’s transitions as the primary use case. Using historical radar data, the tool has been trained to predict spacing between consecutive arrivals based [...] Read more.

The ORCI project aims to develop an AI-based decision-support tool to assist air traffic controllers in complex TMA operations, taking Barcelona’s transitions as the primary use case. Using historical radar data, the tool has been trained to predict spacing between consecutive arrivals based on real-time vectoring commands. A data-processing pipeline was developed to clean, classify and validate flight trajectories, and synthetic samples were generated to enable a wider variety of situations. Explainable ML models achieved a mean absolute error of around 0.38 NM, demonstrating strong predictive capability. The results show the potential of ORCI to improve sequencing efficiency and runway throughput. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 1374 KB

Open AccessProceeding Paper

Collaborative Propulsion System Design: A Framework for the Sizing of a Plug-In Hybrid Electric Aircraft Powertrain

by Niels Weber, Tim Burschyk and Sparsh Garg

Eng. Proc. 2026, 133(1), 42; https://doi.org/10.3390/engproc2026133042 - 24 Apr 2026

Cited by 1 | Viewed by 323

Abstract

The design of novel aircraft concepts powered by electric propulsion systems is a highly multidisciplinary task that requires expert knowledge to be included in the early design phase. Such expertise is typically provided by engineering routines that are not directly linked to the [...] Read more.

The design of novel aircraft concepts powered by electric propulsion systems is a highly multidisciplinary task that requires expert knowledge to be included in the early design phase. Such expertise is typically provided by engineering routines that are not directly linked to the overall aircraft design. This paper presents a digital framework to employ heterogeneous methods at component level to size a complete electrical powertrain within the aircraft design process. A standardized interface and an automated execution workflow are developed to enable consistent data exchange between disciplines, integration of the powertrain architecture into the data model, and synthesis of component results within the overall aircraft design process. The framework is applied for the sizing of the powertrain of a plug-in hybrid electric aircraft. By supporting the integration of expert knowledge at component level in the aircraft design process, this paper facilitates technology assessment at the early design stage. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 620 KB

Open AccessProceeding Paper

On the Assessment of Drone Noise for Sustainable Urban Air Mobility Operations

by Marco Rinaldi, Saeed Maghsoodi and Stefano Primatesta

Eng. Proc. 2026, 133(1), 43; https://doi.org/10.3390/engproc2026133043 - 24 Apr 2026

Viewed by 995

Abstract

Drone noise-induced human annoyance is emerging as one of the main barriers to socially acceptable large-scale urban air mobility (UAM) operations, which have the potential to revolutionize urban transportation systems in the next few decades. This paper investigates the state-of-the-art technology in the [...] Read more.

Drone noise-induced human annoyance is emerging as one of the main barriers to socially acceptable large-scale urban air mobility (UAM) operations, which have the potential to revolutionize urban transportation systems in the next few decades. This paper investigates the state-of-the-art technology in the assessment of drone noise and its impact on individuals, focusing on measurement and evaluation methodologies, as well as subjective evaluations. Various acoustic metrics are reviewed to characterize drone noise, including sound pressure levels, spectral analysis, and psychoacoustic parameters such as loudness and annoyance. Preliminary experimental investigations to identify key frequencies and tonal components that significantly contribute to drone noise-induced public annoyance are also discussed. Interdisciplinary approaches integrating pure technical acoustics, human perception, and subjectivity emerge as promising solutions for a comprehensive understanding of drone noise effects. Finally, a preliminary framework for drone noise assessment towards noise-aware UAM operations is proposed. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 3447 KB

Open AccessProceeding Paper

Vibration-Based Damage Detection and Localisation on a Trainer Jet Aircraft Wing

by Gabriele Dessena, Marco Civera, Andrés Marcos, Bernardino Chiaia and Oscar E. Bonilla-Manrique

Eng. Proc. 2026, 133(1), 44; https://doi.org/10.3390/engproc2026133044 - 27 Apr 2026

Viewed by 431

Abstract

Damage detection and identification are important for many aerospace and aeronautical structures. Vibration-based methods check changes in modal parameters, such as natural frequencies and mode shapes, usually indicating damage. For large structures, comparing each mode and parameter separately is impractical. This study proposes [...] Read more.

Damage detection and identification are important for many aerospace and aeronautical structures. Vibration-based methods check changes in modal parameters, such as natural frequencies and mode shapes, usually indicating damage. For large structures, comparing each mode and parameter separately is impractical. This study proposes the modified total modal assurance criterion (MTMAC) as a single index for damage detection. To provide localisation, MTMAC is paired with the coordinate modal assurance criterion (COMAC), a standard tool for locating damage using mode shapes. Accurate modal identification is required to support structural health monitoring (SHM). For this purpose, the recently introduced improved Loewner Framework (iLF) is used. Noting that this is its first application to SHM, its performance on an undamaged BAE Systems Hawk T1A jet trainer wing is compared with literature results. Then, the iLF is applied to damaged states of the same airframe. In all cases, the aircraft vibration testing is carried out under multiple-input, multiple-output conditions. The identified modal sets are used to compute the MTMAC for detection and severity, and COMAC for localisation. Results show that the iLF provides robust modal identification for SHM and that the MTMAC effectively detects damage. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 3651 KB

Open AccessProceeding Paper

Sensitivity of LH2 Aircraft Refueling to Process Parameters

by Francesco Mastropierro, Michael Quaglia, Enrico De Betta, Damiano Tormen, Michele De Gennaro and Gianvito Apuleo

Eng. Proc. 2026, 133(1), 45; https://doi.org/10.3390/engproc2026133045 - 27 Apr 2026

Viewed by 648

Abstract

A preliminary analysis of aircraft refueling using liquid hydrogen (LH2) for a future short–medium-range aircraft is presented. The focus is on how selected refueling parameters influence pressure buildup and the release of boil-off gas (BOG), in order to establishing guidelines towards efficient refueling. [...] Read more.

A preliminary analysis of aircraft refueling using liquid hydrogen (LH2) for a future short–medium-range aircraft is presented. The focus is on how selected refueling parameters influence pressure buildup and the release of boil-off gas (BOG), in order to establishing guidelines towards efficient refueling. The flow physics uses a 0-D multi-phase lump model, which accounts for the effects of the injected LH2, BOG release, heat fluxes and phase changes. Refueling is controlled by volumetric compression during the filling, and relaxation afterwards. Mass-flow profile and refueling protocol have little influence on the amount of BOG vented (~1%), but control the duration of the process, with variations close to 50%. Low initial pressure can significantly reduce the amount of BOG. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 1446 KB

Open AccessProceeding Paper

A New Approach to the Application of SMA Strain Sensors for Structural Health Monitoring of COPVs

by Alexander Hiekel, Björn Senf and Welf-Guntram Drossel

Eng. Proc. 2026, 133(1), 46; https://doi.org/10.3390/engproc2026133046 - 27 Apr 2026

Viewed by 528

Abstract

Type-IV composite overwrapped pressure vessels (COPVs) enable efficient hydrogen storage but experience severe thermal and mechanical loads that threaten structural integrity, necessitating reliable condition monitoring. This work investigates pseudo-elastic shape-memory alloy (SMA) strain gauges as a cost-effective alternative to fiber-optic systems for monitoring [...] Read more.

Type-IV composite overwrapped pressure vessels (COPVs) enable efficient hydrogen storage but experience severe thermal and mechanical loads that threaten structural integrity, necessitating reliable condition monitoring. This work investigates pseudo-elastic shape-memory alloy (SMA) strain gauges as a cost-effective alternative to fiber-optic systems for monitoring COPVs. Their performance was characterized on composite specimens using four-point bending tests. Additionally, a finite element model analyzed surface-strain behavior as a function of COPV geometry parameters and ambient temperature, enabling identification of optimal quarter-bridge measurement configurations. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 18440 KB

Open AccessProceeding Paper

Manufacturing of an Engine Outlet Guide Vane with Automated Fiber Placement and One-Shot Resin Transfer Molding Process

by Cristian Builes Cárdenas, Elena Rodríguez Senín, Mario Román Rodríguez, Adrián López González and Gianna Avgousti

Eng. Proc. 2026, 133(1), 47; https://doi.org/10.3390/engproc2026133047 - 24 Apr 2026

Viewed by 611

Abstract

The combination of the dry fiber AFP preforming process and RTM injection process brings new possibilities with regard to automation, high-quality manufacturing, and high-performance characteristics for out-of-autoclave composite manufacturing, particularly in aerospace industry. This paper describes the manufacturing of an aircraft engine Outlet [...] Read more.

The combination of the dry fiber AFP preforming process and RTM injection process brings new possibilities with regard to automation, high-quality manufacturing, and high-performance characteristics for out-of-autoclave composite manufacturing, particularly in aerospace industry. This paper describes the manufacturing of an aircraft engine Outlet Guide Vane (OGV), made with a dry carbon fiber preform manufactured with Automated Fiber Placement (AFP) and co-injected, co-cured, and co-bonded with titanium fittings through the Resin Transfer Molding (RTM) Process. The details of the assembly process and necessary steps are described. Parts of the digitalization process behind the manufacturing are described, including information about integrated sensors and data management. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 2149 KB

Open AccessProceeding Paper

Sustainable and Efficient Manufacture of Hollow Propeller Blades from Carbon Fiber-Reinforced Plastic and Lost Salt Core in HP-RTM Process

by Feiyun Zhang, Michael Wilhelm, Tatjana Vaccaro and Markus Reeb

Eng. Proc. 2026, 133(1), 48; https://doi.org/10.3390/engproc2026133048 - 27 Apr 2026

Viewed by 575

Abstract

Urban Air Mobility (UAM) is increasingly recognized as one of the promising methods for future urban transportation, offering higher average speeds than conventional means of transportation. This study investigates the sustainable and efficient production of hollow propeller blades (837 × 85 × 40 [...] Read more.

Urban Air Mobility (UAM) is increasingly recognized as one of the promising methods for future urban transportation, offering higher average speeds than conventional means of transportation. This study investigates the sustainable and efficient production of hollow propeller blades (837 × 85 × 40 mm) using high pressure resin transfer molding (HP-RTM), driven by high demand for UAM, particularly for wingless multicopters. Unlike conventional monolithic or sandwich structures, the propeller blade in this project features a hollow design using a lost core made from water soluble salt. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 1376 KB

Open AccessProceeding Paper

Metamodeling Approach for Comparison of Linear Flux-Switching and Permanent Magnet Synchronous Machines for Electric Aircraft Propulsion

by Enrico Teichert, Matthias Lang, Ilja Koch and Stefan Kazula

Eng. Proc. 2026, 133(1), 49; https://doi.org/10.3390/engproc2026133049 - 17 Apr 2026

Viewed by 201

Abstract

The increasing demand for electric, direct-drive propulsion systems with high torque density and high efficiency is driving the development of novel topologies in aviation. Conventional surface-mounted permanent magnet machines offer high efficiency with medium gravimetric shear force density. Flux-switching machines have a significantly [...] Read more.

The increasing demand for electric, direct-drive propulsion systems with high torque density and high efficiency is driving the development of novel topologies in aviation. Conventional surface-mounted permanent magnet machines offer high efficiency with medium gravimetric shear force density. Flux-switching machines have a significantly higher specific force density and offer attractive advantages such as structural robustness, favorable permanent magnet utilization and simplified cooling options. In this work, two FSM variants and an SPM benchmark are investigated. A metamodel-based optimization framework is employed to efficiently explore a parameterized design space, allowing the identification of pareto-optimal solutions. Selected designs are analyzed in detail and compared with each other. The results show that high-pole FSM configurations are particularly suitable for torque-dense electric machines in aviation due to their high shear force density and scalability. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 581 KB

Open AccessProceeding Paper

‘Flexible’ Project Management: A Guideline to Forming, Managing and Leading Student Teams for Technical Projects

by Efstratios Rigas, Thomas Kalampoukas, Athina Theochari, Konstantinos Giotis, Evangelos Ch. Tsirogiannis, Christos Belogiannis, Panagiotis Kardaras, Antonis Spanos, Thodoris Domvoglou and Michalis Diakonikolis

Eng. Proc. 2026, 133(1), 50; https://doi.org/10.3390/engproc2026133050 - 28 Apr 2026

Viewed by 697

Abstract

This paper analyzes the creation and management of a robotics student team, introducing a “flexible project management” approach tailored to educational, voluntary and competitive settings. Drawing on the Beyond Robotics team as a case study, it presents adaptable methodologies addressing challenges such as [...] Read more.

This paper analyzes the creation and management of a robotics student team, introducing a “flexible project management” approach tailored to educational, voluntary and competitive settings. Drawing on the Beyond Robotics team as a case study, it presents adaptable methodologies addressing challenges such as voluntary participation, limited resources, and member turnover. The framework covers recruitment, skill development, communication, creativity, and continuity planning through mentorship and knowledge transfer. By applying agile and lean methods, it identifies best practices to enhance team resilience, innovation, and sustainability, offering educators and student leaders a practical guide for effective organization and long-term success. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 6932 KB

Open AccessProceeding Paper

Integrated Aerial System Design for Wildfire Fighting and Surveillance with Tactical Considerations

by Giho Lee, Sewoong Park, Soungmin Choi, Sewoong Oh, Byeongjun Park, Minseong Kim, Nikolaos Kalliatakis, Nabih Naeem, Prajwal Shiva Prakasha and Donguk Lee

Eng. Proc. 2026, 133(1), 51; https://doi.org/10.3390/engproc2026133051 - 28 Apr 2026

Viewed by 508

Abstract

Wildfire disasters are increasing in scale and severity, underscoring the need for more capable and coordinated aerial firefighting systems. This work presents a performance-based integrated aerial system framework that links the aircraft design tool RISPECT+ with the wildfire mission analysis tool SoSID Toolkit+ [...] Read more.

Wildfire disasters are increasing in scale and severity, underscoring the need for more capable and coordinated aerial firefighting systems. This work presents a performance-based integrated aerial system framework that links the aircraft design tool RISPECT+ with the wildfire mission analysis tool SoSID Toolkit+ to evaluate and optimize system-level effectiveness. Incorporating terrain-specific wildfire characteristics, the framework identifies optimal aircraft configurations and deployment strategies that maximize integrated measurement of effectiveness across diverse regions. A unified surveillance platform strengthens the system of systems architecture and supports the operation of aerial firefighting aircraft. Results show enhanced system-oriented design and multi-agent coordination, with future work focused on optimal designs across diverse aircraft configurations and integrating operational environmental factors relevant to aerial firefighting. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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7 pages, 285 KB

Open AccessProceeding Paper

The Well-to-Wake Emissions of Conventional and Emerging Propulsion Technologies Across Current and Future Scenarios: Insights from the exFAN Project

by Athanasios Pappas, Anastasia Gkika and Elias Koumoulos

Eng. Proc. 2026, 133(1), 52; https://doi.org/10.3390/engproc2026133052 - 28 Apr 2026

Viewed by 598

Abstract

As aviation faces growing pressure to reduce its climate impact, the exFAN project investigates a hydrogen fuel cell aircraft concept equipped with a heat recuperation system that reuses waste thermal energy to improve efficiency and lower fuel demand. This study compares the exFAN [...] Read more.

As aviation faces growing pressure to reduce its climate impact, the exFAN project investigates a hydrogen fuel cell aircraft concept equipped with a heat recuperation system that reuses waste thermal energy to improve efficiency and lower fuel demand. This study compares the exFAN configuration with five major propulsion pathways, kerosene, bio-fuel, e-fuel, hydrogen combustion, and standard fuel cell systems, through an integrated well-to-wake (WTT + TTW) assessment including both CO₂ and non-CO₂ effects. The exFAN results are preliminary and based on analytical estimations regarding potential efficiency gains and fuel savings, providing an indicative view of hydrogen aviation’s lowest achievable climate footprint. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 1166 KB

Open AccessProceeding Paper

Heat Pipe-Assisted Air Cooling for Fuel Cells in Aviation: Heat Transfer Modeling and Design Modifications

by Friedrich Franke, Fabian Kramer, Markus Kober and Stefan Kazula

Eng. Proc. 2026, 133(1), 53; https://doi.org/10.3390/engproc2026133053 - 29 Apr 2026

Viewed by 390

Abstract

Decarbonizing air travel poses a major technological challenge, driven by the substantial power requirements of the drivetrain and the demanding weight and volume constraints of airborne systems. One promising avenue involves leveraging the high specific energy of hydrogen by designing compact, high-power fuel [...] Read more.

Decarbonizing air travel poses a major technological challenge, driven by the substantial power requirements of the drivetrain and the demanding weight and volume constraints of airborne systems. One promising avenue involves leveraging the high specific energy of hydrogen by designing compact, high-power fuel cell stacks to supply power for electric drivetrains. However, a key drawback of such propulsion architectures is the substantial heat generated within the fuel cells, which necessitates bulky and heavy thermal management systems to ensure safe and continuous operation. This study investigates a proposed air-based thermal management system, which operates by introducing pulsating heat pipes into the bipolar plates of a High-Temperature Polymer Electrolyte Membrane Fuel Cell (HT-PEM FC) stack. If proven to be feasible, heat pipe assisted air cooling may provide the benefit of reducing overall system complexity by decreasing the number of components in the thermal management system. To evaluate the thermal performance of the proposed system, a one-dimensional thermal model was initially developed in a previous study to describe the temperature distribution along the length of a heat pipe. Building upon this foundation, the present work extends the model by incorporating a two-dimensional Computational Fluid Dynamic (CFD) analysis to account for geometry-specific effects within the hexagonal design. Results indicate that the heat transfer from the hexagonal heat pipe geometry to the coolant air flow was marginally overestimated in previous analytical calculations. Revised heat transfer rates led to a shift in the predicted temperature distributions, resulting in the need for either increased external airflow, extended condenser sections, or reduced inlet temperatures to maintain target operating conditions. Although these adjustments may result in a slight increase in system mass and parasitic power consumption, the overall impact is limited, and the heat pipe-assisted air cooling approach remains theoretically feasible. Based on the results, design modifications are proposed and their impact on thermal performance is evaluated to address the challenges of heat rejection and temperature uniformity. A modification based on variation and optimization of PHP meander lengths was evaluated using the updated model and it significantly improved temperature homogeneity across the evaporator. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 985 KB

Open AccessProceeding Paper

Battery-Powered Aircraft: Technologies and Designs

by María Zamarreño Suárez, Rosa María Arnaldo Valdés, César Gómez Arnaldo, Raquel Delgado-Aguilera Jurado, Francisco Pérez Moreno and Víctor Fernando Gómez Comendador

Eng. Proc. 2026, 133(1), 54; https://doi.org/10.3390/engproc2026133054 - 29 Apr 2026

Viewed by 626

Abstract

Sustainability is one of the guiding principles of the aviation industry. In the coming years, new sustainable aircraft concepts and propulsion technologies are expected to be developed and scaled up. One of the most promising solutions is the development of battery-powered aircraft. This [...] Read more.

Sustainability is one of the guiding principles of the aviation industry. In the coming years, new sustainable aircraft concepts and propulsion technologies are expected to be developed and scaled up. One of the most promising solutions is the development of battery-powered aircraft. This paper aims to present the key concepts associated with these new aircraft designs. The first part of the paper provides an overview of the key advantages of battery-powered aircraft. It also identifies limitations that these designs will need to overcome to be scaled up. The second part focuses on the two main types of battery-powered aircraft. The difference between all-electric aircraft (AEA) and hybrid-electric aircraft is explained. The main advantages and limitations of each type are also discussed. The third part of the paper analyses the impact of introducing battery-powered aircraft on different aviation markets. Due to its relevance, the analysis of a new business model—Innovative Air Mobility (IAM)—is detailed. The development of battery-powered aircraft is discussed as a key driver for this business model. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 2259 KB

Open AccessProceeding Paper

SATERA PPT: A Performance Prediction Tool for Satellite-Based Air Traffic Independent Localization and Surveillance ^†

by Giulio Sidoretti, Victor Monzonis Melero, Juan Vicente Balbastre Tejedor, Mauro Leonardi and Mahsa Mohebbi

Eng. Proc. 2026, 133(1), 55; https://doi.org/10.3390/engproc2026133055 - 29 Apr 2026

Viewed by 650

Abstract

This paper presents the Performance Prediction Tool developed within the SATERA project. The tool evaluates the performance of a space-based composite ADS-B and multilateration system for independent aircraft localization. It uses receivers deployed onboard a constellation of LEO satellites. Multilateration can be evaluated [...] Read more.

This paper presents the Performance Prediction Tool developed within the SATERA project. The tool evaluates the performance of a space-based composite ADS-B and multilateration system for independent aircraft localization. It uses receivers deployed onboard a constellation of LEO satellites. Multilateration can be evaluated using time-based measurements, as well as additional measurements such as, frequency and angle of arrival of the received signals. The tool is based on the evaluation of the Cramér–Rao lower bound and it is implemented in MATLAB with a user-friendly graphical interface. The tool allows the user to define the satellite constellation, link budget, measurement types and errors, and to simulate the system performance over an aircraft trajectory or an area. Moreover, the outputs include DOP, number of visible satellites and system availability, which can be visualized and exported for further analysis. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 2941 KB

Open AccessProceeding Paper

Smart Sector Grouping Tool Prototype

by Teresa Arangüete, José Manuel Rísquez, Mariano Rubio Diaz and David Rodríguez-Madridejos

Eng. Proc. 2026, 133(1), 56; https://doi.org/10.3390/engproc2026133056 - 28 Apr 2026

Viewed by 346

Abstract

European airspace is currently facing significant challenges due to increasing traffic demand and limited sector capacity. This situation leads to an overload of demand, so Air Traffic Controllers (hereinafter ATCOs) are often forced to implement regulations that cause delays. Moreover, an ATCO cannot [...] Read more.

European airspace is currently facing significant challenges due to increasing traffic demand and limited sector capacity. This situation leads to an overload of demand, so Air Traffic Controllers (hereinafter ATCOs) are often forced to implement regulations that cause delays. Moreover, an ATCO cannot be endorsed in an unlimited number of sectors, as doing so would compromise the maintenance of operational proficiency and specific sector skills. Consequently, the limited cross-sector flexibility of controllers has become a key constraint in optimizing airspace management. Additionally, the strategic definition of sector groups has a direct impact on which sector configurations can be activated. An inadequate sector grouping strategy may hinder operations by restricting access to more efficient sector configurations. While in some cases, controllers may be endorsed for multiple sectors (up to ten), this flexibility remains insufficient to mitigate capacity and efficiency challenges fully. IFAV3 (Increased Flexibility of ATCO Validation En-Route) project has been developed within the Single European Sky ATM Research (hereinafter SESAR) framework, aiming to maximize flexibility in ATCO rostering. Its main expected benefits include an improvement in cost efficiency in Air Traffic Control (hereinafter ATC) through reduced training costs and optimized rostering by a better utilization of existing capacity. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 12095 KB

Open AccessProceeding Paper

Optical Analysis of an Origami-Inspired Self-Deployable Baffle

by Ester Velázquez-Navarro, Diego Rodríguez-Díaz, Pablo Solano-López, Ruy Sanz and Tomás Belenguer

Eng. Proc. 2026, 133(1), 57; https://doi.org/10.3390/engproc2026133057 - 29 Apr 2026

Viewed by 512

Abstract

As origami-inspired solutions become more mature in spacecraft structures and applications, new alternatives are arising for traditional designs, allowing for creative and innovative answers to common problems. In this work, we look into space telescopes, one of the most feasible applications for new [...] Read more.

As origami-inspired solutions become more mature in spacecraft structures and applications, new alternatives are arising for traditional designs, allowing for creative and innovative answers to common problems. In this work, we look into space telescopes, one of the most feasible applications for new tubular solutions, using origami structures to propose the design of a self-retractable baffle. An element needed for mitigating both in-field and out-of-field stray light and helping to improve the image quality of the optical system. This baffle is rethought as a tubular, origami-inspired structure, built over a Kresling origami pattern. This choice can be traced back to the properties such structure has to offer: bi-stability, packaging ratio and controllability. Thus, it is becoming a promising alternative to standard baffles and helping to reduce key factors in spacecraft design, such as weight and complexity of the optomechanical mechanism. To demonstrate its effectiveness in an optical system, the professional software ASAP (Advanced System Analysis Program) is utilised to assess the optical performance of the new baffle design. As a result, we verify the applicability of these patterns and, therefore, the whole structure from an optical point of view, confirming the interest of its application as a telescope baffle. This solution also allows moving and modifying the inclination, shape or size of the baffle, selecting the amount of screening and light incidence into the telescope in a controlled manner depending on the orbit and attitude of interest. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 3143 KB

Open AccessProceeding Paper

Assessing Bi-Stability in 3D-Printed Origami Deployable Structures

by Ester Velázquez-Navarro, Pablo Solano-López, Marta Maria Moure, Ines Uriol Balbin, Santiago Martín Iglesias, Pablo Arribas and Boris Martín

Eng. Proc. 2026, 133(1), 58; https://doi.org/10.3390/engproc2026133058 - 29 Apr 2026

Viewed by 511

Abstract

Deployable structures offer new solutions in space, and among them, tubular origami-inspired space structures have proven to be a robust solution for packaging problems. This study focuses on the analysis of the Kresling origami pattern, which theoretically offers bi-stability during its folding process. [...] Read more.

Deployable structures offer new solutions in space, and among them, tubular origami-inspired space structures have proven to be a robust solution for packaging problems. This study focuses on the analysis of the Kresling origami pattern, which theoretically offers bi-stability during its folding process. The bi-stability of this pattern is a well-known property for paper models. However, it cannot be generalised for any material or geometry, as this property can be traced back to the manufacturing process and the materials being used. Consequently, we propose and test additive manufacturing models implementing different geometry parameters with the materials of interest. In parallel, a parametrised numerical model was developed in the commercial software Abaqus, replicating the structural behaviour of these test specimens under displacement-controlled compression. The aim is to obtain a final validated numerical model from where the entire behaviour and energetic response of each sample and, thus, their stability can be tested. Combining experimental and numerical results paints a whole picture of bi-stability, verifying this useful property for different space materials and configurations. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 2811 KB

Open AccessProceeding Paper

Prototype Wing Design and Manufacturing for Reflexed Airfoil Morphing

by Panagiotis Georgopoulos, Jurij Sodja and Roeland De Breuker

Eng. Proc. 2026, 133(1), 59; https://doi.org/10.3390/engproc2026133059 - 28 Apr 2026

Viewed by 500

Abstract

This paper presents the development of a novel morphing wing prototype with three camber-twist morphing flaps. Reflexed airfoil morphing is achieved by means of two chordwise degrees-of-freedom, thereby decoupling lift from the aerodynamic moment with respect to the aerodynamic centre. The prototype wing [...] Read more.

This paper presents the development of a novel morphing wing prototype with three camber-twist morphing flaps. Reflexed airfoil morphing is achieved by means of two chordwise degrees-of-freedom, thereby decoupling lift from the aerodynamic moment with respect to the aerodynamic centre. The prototype wing design is characterised by a novel morphing flap concept and driven by the boundary conditions pertinent to the wind tunnel testing facilities and the choice of research questions. The flaps’ spanwise ends are adapted to represent a seamless and a discontinuous transition between adjacent flaps. Linear electric motors induce the morphing shapes, equipped with load cells on their respective push rods, for actuator force measurement. Pressure taps are included to measure the pressure distribution along the wing section. Upon manufacturing, preliminary static test results validate the wing’s morphing functionality. The morphing trailing edge demonstrates a range of camber morphing and twist morphing shapes, as well as the ability to support asymmetric morphing between adjacent flaps. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 3978 KB

Open AccessProceeding Paper

Development of the Architecture of a Conceptual Design Tool for Manned and Unmanned Fixed-Wing Aircraft

by Rebeca González-Pérez, Alejandro Sanchez-Carmona and Cristina Cuerno-Rejado

Eng. Proc. 2026, 133(1), 60; https://doi.org/10.3390/engproc2026133060 - 29 Apr 2026

Viewed by 534

Abstract

Aircraft conceptual design is an iterative process that seeks to obtain a feasible design that meets a series of mission and configuration requirements. Starting with several guesses regarding the initial sizing and aerodynamics of the future aircraft, a first resulting general layout is [...] Read more.

Aircraft conceptual design is an iterative process that seeks to obtain a feasible design that meets a series of mission and configuration requirements. Starting with several guesses regarding the initial sizing and aerodynamics of the future aircraft, a first resulting general layout is found, which is then subjected to trade studies where initial assumptions are altered in search of a refined design. With the aim of enhancing design solutions and reducing time costs derived from calculations, the authors of the present paper have developed ARCADE (AiRcraft ConceptuAl DEsign Tool), a framework that automates, in multiple thematic modules, the steps and calculations needed for the conceptual design process of fixed-wing aircraft. This work presents the basis for the early architecture of ARCADE, developed in Python and focused on the use of data retrieved from existing aircraft for the first design hypotheses. Initial findings of the use of ARCADE show a small relative error between the first parameter guesses, made based on similar aircraft, and the results of the next design iteration, which are independent of reference aircraft. This suggests that the design parameters of the target aircraft are accurately guessed when using existing aircraft information for the initial estimations of this process. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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6 pages, 4345 KB

Open AccessProceeding Paper

Optimization of the Flap Position of a High-Lift Multi-Element Airfoil Using a Body-Fitted Mesh Along with Immersed Boundary Methods

by Jonatan Núñez-de la Rosa, Andrés Mateo, Esteban Ferrer and Eusebio Valero

Eng. Proc. 2026, 133(1), 61; https://doi.org/10.3390/engproc2026133061 - 30 Apr 2026

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Abstract

In this work we propose a new strategy for the optimization of the flap position of a high-lift configuration in the framework of a hybrid electric regional aircraft. The approach is based on the multidisciplinary design optimization software GEMSEO and the high-performance CFD [...] Read more.

In this work we propose a new strategy for the optimization of the flap position of a high-lift configuration in the framework of a hybrid electric regional aircraft. The approach is based on the multidisciplinary design optimization software GEMSEO and the high-performance CFD solver CODA. The CFD solver CODA solves the RANS equations on a body-fitted mesh along with immersed boundary methods, while the package GEMSEO employs the COBYQA optimization algorithm. The main airfoil is meshed in a body-fitted fashion, and a refined region is created just where the flap can be located. The employment of immersed boundary methods allows us to arbitrarily change the deflection angle and leading edge position of the flap inside this refined region without the need of remeshing the whole computational domain. The main advantage of this methodology with respect to a full body-fitted mesh scheme is the computational efficiency when hundreds or thousands of CFD-RANS simulations are required by the optimizer. We demonstrate the effectiveness of this optimization methodology in the computation of the optimal configuration of the flap during takeoff and landing phases of a high-lift airfoil. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 7904 KB

Open AccessProceeding Paper

Mesh Adaptation on Hybrid Unstructured Meshes for Immersed Boundary Methods with Applications to Industrial Aerodynamics

by Jonatan Núñez-de la Rosa, Esteban Ferrer and Eusebio Valero

Eng. Proc. 2026, 133(1), 62; https://doi.org/10.3390/engproc2026133062 - 30 Apr 2026

Viewed by 497

Abstract

In this work we present the development and application of a mesh adaptation tool on hybrid unstructured meshes for immersed boundary volume penalization methods in the computational fluid dynamics software from ONERA, DLR, and Airbus. This mesh adaptation tool is capable of refining [...] Read more.

In this work we present the development and application of a mesh adaptation tool on hybrid unstructured meshes for immersed boundary volume penalization methods in the computational fluid dynamics software from ONERA, DLR, and Airbus. This mesh adaptation tool is capable of refining elements around geometries immersed in unstructured meshes made of different types of elements, like tetrahedra, hexahedra, prisms, and pyramids. This feature allows us to simulate fluid flow problems with the immersed boundary method not only on Cartesian meshes but on general hybrid unstructured meshes. Of special interest in this work is the simulation of turbulent fluid flows in aerodynamics through the numerical solution of the Reynolds-averaged Navier–Stokes equations either on unstructured meshes with only immersed geometries or on unstructured body-fitted meshes along with immersed geometries. As part of the benchmarking, we simulate the subsonic flow past the high-lift multi-element airfoil. The reported numerical simulations are in good agreement with their corresponding full body-fitted meshes. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 2856 KB

Open AccessProceeding Paper

Development and Integration of a Flight Dynamics Module into the ODE4HERA Open Digital Platform

by Danilo Ciliberti, Agostino De Marco and Fabrizio Nicolosi

Eng. Proc. 2026, 133(1), 63; https://doi.org/10.3390/engproc2026133063 - 30 Apr 2026

Viewed by 485

Abstract

The pursuit for cleaner aviation pushes research in hybrid-electric aircraft, which are far more complex systems than conventional airplanes. In this respect, the ODE4HERA European project aims to accelerate the development of such systems with the implementation of a solution-neutral Open Digital Platform, [...] Read more.

The pursuit for cleaner aviation pushes research in hybrid-electric aircraft, which are far more complex systems than conventional airplanes. In this respect, the ODE4HERA European project aims to accelerate the development of such systems with the implementation of a solution-neutral Open Digital Platform, driving the design from top level requirements to virtual verification and validation. In this respect, the authors developed and integrated a flight dynamics module in a co-simulation environment aiming at the performance verification of the reference hybrid-electric aircraft through flight simulation. The implementation of a point mass model was sufficiently accurate to comply with the preliminary objectives of the project, paving the way for a higher-fidelity and more complex flight dynamics and control systems. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 947 KB

Open AccessProceeding Paper

Navigating Passengers Through Sustainability Initiatives Within Air Travel—WTP for VCOs and SAF

by Naomi Sieben and Christopher Schruba

Eng. Proc. 2026, 133(1), 64; https://doi.org/10.3390/engproc2026133064 - 1 May 2026

Viewed by 454

Abstract

To reduce the environmental impact of aviation, airlines are offering Voluntary Carbon Offset (VCO) programs and Sustainable Aviation Fuel (SAF) contributions, which are rarely purchased by consumers. This quantitative survey study examines how passengers’ willingness to pay (WTP) for VCOs and SAF differs [...] Read more.

To reduce the environmental impact of aviation, airlines are offering Voluntary Carbon Offset (VCO) programs and Sustainable Aviation Fuel (SAF) contributions, which are rarely purchased by consumers. This quantitative survey study examines how passengers’ willingness to pay (WTP) for VCOs and SAF differs across ticket price levels and communication contexts. Findings indicate that, at higher ticket prices, lower stated WTP for carbon offsetting was observed when ticket price increases were presented within a more detailed communication context. Differences in communication context were not significantly associated with stated WTP for SAF, while SAF was indicated as a preferred mitigation strategy than VCOs. This study highlights the complexity of consumer decision-making regarding voluntary sustainable initiatives in aviation. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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11 pages, 2067 KB

Open AccessProceeding Paper

Aerial Firefighting Fleet for Wildfire Suppression: A System of Systems Approach

by Auraluck Pichitkul, Kaung Sett Toe, Kyaw Zaw Hlyan, Soe Yu Waddy, Aung Hein Kyaw, Nikolaos Kalliatakis, Nabih Naeem and Prajwal Shiva Prakasha

Eng. Proc. 2026, 133(1), 65; https://doi.org/10.3390/engproc2026133065 - 5 May 2026

Viewed by 551

Abstract

This study documents the design, development, and evaluation of a purpose-built aerial firefighting fleet optimized for diverse wildfire suppression environments as part of the COLOSSUS project’s X-Challenge. The multidisciplinary effort encompassed aerodynamic design, propulsion system, systems integration, cost estimation, simulation, design of experiments, [...] Read more.

This study documents the design, development, and evaluation of a purpose-built aerial firefighting fleet optimized for diverse wildfire suppression environments as part of the COLOSSUS project’s X-Challenge. The multidisciplinary effort encompassed aerodynamic design, propulsion system, systems integration, cost estimation, simulation, design of experiments, and fleet optimization. Key technical advancements include a conceptual hybrid electric Vertical Takeoff and Landing (eVTOL) aircraft design, and the integration of a series hybrid propulsion model into the System of Systems Inverse Design (SoSID) simulation toolkit, in which evaluation takes place at fleet level. Simulation results indicate that the proposed aircraft achieves competitive or superior effectiveness across all test scenarios, with the series hybrid configuration offering notable endurance and tactical adaptability. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 694 KB

Open AccessProceeding Paper

Design Aspects of 80-Seats 1000 km Range Hybrid Regional Aircraft

by Serhii Fil, Dmytro Berbenets, Andrii Khaustov, Oleksandra Urban and Oleksandr Bondarchuk

Eng. Proc. 2026, 133(1), 66; https://doi.org/10.3390/engproc2026133066 - 5 May 2026

Viewed by 380

Abstract

One of the most future-focused approaches to cleaner regional air transport is to introduce advanced propulsion concepts based on hybrid-electric systems. This study presents an initial design concept for a regional passenger aircraft, providing a detailed justification for the chosen configuration. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 1319 KB

Open AccessProceeding Paper

Electro-Heating of Polymer Nanocomposites for Aeronautical Composite Structures

by Liberata Guadagno, Andrea Sorrentino, Barbara Palmieri, Luigi Vertuccio, Giuseppe De Tommaso, Roberto Pantani, Alfonso Martone and Francesca Aliberti

Eng. Proc. 2026, 133(1), 67; https://doi.org/10.3390/engproc2026133067 - 5 May 2026

Viewed by 342

Abstract

This work presents an approach for designing 3D-printed heaters with tunable electrical resistance by optimizing both printing and geometrical parameters. To this end, acrylonitrile butadiene styrene reinforced with carbon nanotubes (ABS-CNTs) has been processed through fused filament fabrication (FFF) in a manner that [...] Read more.

This work presents an approach for designing 3D-printed heaters with tunable electrical resistance by optimizing both printing and geometrical parameters. To this end, acrylonitrile butadiene styrene reinforced with carbon nanotubes (ABS-CNTs) has been processed through fused filament fabrication (FFF) in a manner that favors electrical current flow along the printing direction and enables adjustment of electrical resistance to meet the scalability needs and limitations of the power supplier available in the application field. The as-developed 3D-printed heater has been integrated into an aeronautical fiberglass composite as proof of its possible application as a de-icing system. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 1710 KB

Open AccessProceeding Paper

Modelling of Electrodes in Perovskite Solar Cells for Aerospace Applications

by Noor ul Ain Ahmed, Monica La Mura, Polina Kuzhir, Renata Karpicz, Vincenzo Tucci and Patrizia Lamberti

Eng. Proc. 2026, 133(1), 68; https://doi.org/10.3390/engproc2026133068 - 5 May 2026

Viewed by 452

Abstract

Perovskite solar cells in aerospace applications are promising due to their high power output, radiation tolerance, and ability to extend spacecraft operational lifetimes. Numerical modelling is widely used to optimize solar cells as it can predict the real-world behavior of a device. In [...] Read more.

Perovskite solar cells in aerospace applications are promising due to their high power output, radiation tolerance, and ability to extend spacecraft operational lifetimes. Numerical modelling is widely used to optimize solar cells as it can predict the real-world behavior of a device. In this work, we present a numerical simulation of CsMAFA-based perovskite solar cells with monolayer graphene as the front electrode. The model is implemented in the COMSOL Multiphysics^® finite-element environment. Graphene is modelled using the Kubo formula to account for its frequency-dependent surface conductivity, and the electromagnetic wavs interface is coupled with the semiconductor module to capture optical–electrical interactions. The influence of absorber layer thickness on the current density is also examined by sweeping the perovskite absorber thickness (300–450 nm). The current voltage characteristic demonstrates higher current density (27 mA/cm²) at an absorber thickness of ~450 nm. Shockley–Read–Hall recombination (SRH) is studied inside the model and maximum recombination was found to be centred in the absorber layer. The graphene/HTL side shows an SRH recombination of 2 × 10²⁰ cm⁻³ s⁻¹, which is much lower than what is typically seen at ITO-based HTL interfaces. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 1513 KB

Open AccessProceeding Paper

Off-the-Shelf Simulation for Demoldable Mandrels: An Experimental and Numerical Approach to Thermoplastic Shape-Memory Polymers

by Fabian Flüh, Parth Shingte, Óscar Ludeña Navarro and Jonas Wermter

Eng. Proc. 2026, 133(1), 69; https://doi.org/10.3390/engproc2026133069 - 5 May 2026

Viewed by 540

Abstract

The production of one-piece composite hollow profiles with undercuts presents significant challenges to conventional mold concepts. Mandrels made of thermoplastic shape-memory polymers could facilitate demolding and reduce tooling costs. To design molds in a commercial environment, it is critical to determine their behavior [...] Read more.

The production of one-piece composite hollow profiles with undercuts presents significant challenges to conventional mold concepts. Mandrels made of thermoplastic shape-memory polymers could facilitate demolding and reduce tooling costs. To design molds in a commercial environment, it is critical to determine their behavior using off-the-shelf Finite Element Analysis (FEA) software Ansys 2024R1. This study presents a shape-memory test procedure for coupon test specimens under tensile load. Furthermore, the test is used to validate a simulation using a generalized Maxwell model, a linear viscoelastic material model implemented in off-the-shelf commercial FEA software Ansys 2024R1. The material investigated is amorphous PET. The simulation shows good results in comparison with the thermo-mechanical shape-memory test. The results are then transferred to blow-molded bottle-shaped mandrels, e.g., for the manufacturing of Type V pressure vessels. Test results are compared with the simulation results and deviations are discussed. In conclusion, the straightforward “from material to solution” approach presented allows us to model and simulate the shape-memory behavior of linear viscoelastic polymers with off-the-shelf commercial FEA software. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 1615 KB

Open AccessProceeding Paper

Bridging Scale and Sustainability: A Battery-Electric Aircraft with Range Extenders for Flexible Short- to Medium-Range Operations

by Georgi Atanasov and Daniel Silberhorn

Eng. Proc. 2026, 133(1), 70; https://doi.org/10.3390/engproc2026133070 - 6 May 2026

Cited by 1 | Viewed by 656

Abstract

This paper presents the development and assessment of a 250-seat battery-electric aircraft with range extenders, designated D250-PHEP, developed within the DLR project EXACT. The concept investigates how hybrid-electric propulsion can combine the high efficiency of battery-electric operation on short routes with the range [...] Read more.

This paper presents the development and assessment of a 250-seat battery-electric aircraft with range extenders, designated D250-PHEP, developed within the DLR project EXACT. The concept investigates how hybrid-electric propulsion can combine the high efficiency of battery-electric operation on short routes with the range flexibility granted by gas-turbine-based range extenders. The propulsion system features four electrically driven propellers powered either by onboard batteries or by two gas turbines operating through a partially turbo-electric drive. In its base configuration, the aircraft carries a large battery enabling highly efficient hybrid operation up to 700–800 nautical miles. For improved performance at longer ranges, the design allows most battery modules to be removed, creating a mild-hybrid configuration with substantially lower mass and extended range capability. The modelling framework developed within EXACT enables a direct comparison with a turbofan and a turboprop baseline aircraft under consistent boundary conditions. The results indicate that large-scale battery-based energy storage becomes feasible once high-energy battery technology suitable for aviation reaches a pack-level specific energy of roughly 400 Wh/kg. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 3696 KB

Open AccessProceeding Paper

Safety Case Modeling for Fire Risks in Liquid Hydrogen-Fueled Aircraft

by Joël Jézégou and Juan Pedro de Gracia Roca

Eng. Proc. 2026, 133(1), 71; https://doi.org/10.3390/engproc2026133071 - 6 May 2026

Viewed by 413

Abstract

The aviation industry is transitioning toward hydrogen propulsion to meet sustainability goals, introducing novel fire safety risks that require updated regulatory frameworks. This study addresses the certification challenges for liquid hydrogen fuel systems by advancing the Certification Readiness Level through a model-driven approach. [...] Read more.

The aviation industry is transitioning toward hydrogen propulsion to meet sustainability goals, introducing novel fire safety risks that require updated regulatory frameworks. This study addresses the certification challenges for liquid hydrogen fuel systems by advancing the Certification Readiness Level through a model-driven approach. Using a Model-Based Safety Assessment, this research applies Bow-Tie Diagrams within the NASA AdvoCATE software to analyze in-flight fire risks for a tube-and-wing aircraft architecture. The study models critical threats, including cryogenic embrittlement and leakage, mapping them to specific prevention and protection barriers derived from a regulatory gap analysis. The assessment identifies leakage as the primary failure condition and proposes a safety architecture that emphasizes prevention barriers. Quantitative safety case modeling demonstrates, with proposed means of mitigation and barrier integrity, the feasibility to compute the residual probability of a catastrophic in-flight fire according to EASA CS 25.1309 requirements. These findings validate the use of safety architectures to bridge the gap between design and rulemaking, offering a scalable framework to support early-stage certification and the safe integration of hydrogen technologies into commercial aviation. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 7899 KB

Open AccessProceeding Paper

Spatially Resolved Monitoring of the Curing Degree in the Liquid Resin Infusion Process Using Near-Infrared Hyperspectral Imaging

by Xabier Zurutuza, Laura Arévalo, Janusz Poplawski, Cristian Builes, Mario Román, Tania Grandal, Arantzazu Núñez, Rubén Ruiz, Daniel Maestro-Watson and Luka Eciolaza

Eng. Proc. 2026, 133(1), 72; https://doi.org/10.3390/engproc2026133072 - 6 May 2026

Viewed by 506

Abstract

To ensure consistent quality in composite aerostructures, advanced non-invasive monitoring techniques are needed to detect global and local deviations during manufacturing. This study presents a real-time, spatially resolved method for monitoring the curing stage of Liquid Resin Infusion (LRI) using Near-Infrared Hyperspectral Imaging [...] Read more.

To ensure consistent quality in composite aerostructures, advanced non-invasive monitoring techniques are needed to detect global and local deviations during manufacturing. This study presents a real-time, spatially resolved method for monitoring the curing stage of Liquid Resin Infusion (LRI) using Near-Infrared Hyperspectral Imaging (NIR-HSI). Unlike traditional point-based tools such as disposable dielectric sensors, NIR-HSI enables full-field, non-contact assessment of the chemical evolution of the resin, providing valuable spatial information for detecting inhomogeneities caused by temperature gradients or uneven resin flow, factors known to affect the final mechanical properties of composites. Previous investigations demonstrated that hyperspectral data acquired during LRI correlate with the degree of cure estimated from a dielectric sensor. In the present study, we extend this analysis through a new experimental campaign designed to validate our earlier findings and strengthen the predictive model. To improve robustness and generalizability, the curing temperature, a key driver of cure kinetics, was systematically varied to introduce controlled changes in cure behavior. This increased variability enhances model reliability and supports more accurate prediction of curing progression under realistic manufacturing conditions. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 2330 KB

Open AccessProceeding Paper

Thermal and Pressure Digital Twins from Online Process Control for Data-Based Optimization of Laser-Assisted In Situ Consolidation of High-Performance Composite Parts

by Beatriz Gomes, Sabela Sánchez, Mario Fernández-Pedrera, Prasad Shimpi and Pablo Romero-Rodríguez

Eng. Proc. 2026, 133(1), 73; https://doi.org/10.3390/engproc2026133073 - 6 May 2026

Viewed by 376

Abstract

Automated Fiber Placement (AFP) enables precise deposition of thermoplastic tapes on complex geometries, however variations in temperature, compaction pressure, deposition speed, and tooling conditions can affect the final laminate quality. This study presents an integrated real-time monitoring system and a systematic methodology for [...] Read more.

Automated Fiber Placement (AFP) enables precise deposition of thermoplastic tapes on complex geometries, however variations in temperature, compaction pressure, deposition speed, and tooling conditions can affect the final laminate quality. This study presents an integrated real-time monitoring system and a systematic methodology for process/product data analysis linking process parameters to mechanical and microstructural performance. Mechanical testing evaluation by interlaminar shear strength (ILSS), thermal analysis, and microscopy studies identified both the consolidation and mold temperatures as the critical parameters for optimized mechanical properties. Results showed ILSS above 45 MPa, crystallinity up to 37.9%, and minimal porosity (~1%). Digital tools developed provided full traceability, early instability detection, and continuous optimization, enhancing reliability and repeatability in high-performance thermoplastic composite manufacturing, which paves the way towards zero-defect manufacturing. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 481 KB

Open AccessProceeding Paper

Heatwave Impacts on Airport Operations Under Future Climate Scenarios: A Climate Risk Assessment

by Lorenzo Cane, Carlo Abate, Sara Dal Gesso, Alessandro Moser and Giulia Maggioni

Eng. Proc. 2026, 133(1), 74; https://doi.org/10.3390/engproc2026133074 - 7 May 2026

Viewed by 542

Abstract

Rising air temperatures are expected to increasingly affect aircraft take-off performance, potentially causing disruption in airport operations. This study develops an airport climate-risk assessment framework combining aircraft performance modeling with the IPCC hazard–exposure–vulnerability approach, using publicly available data. The Take-Off Distance Required (TODR) [...] Read more.

Rising air temperatures are expected to increasingly affect aircraft take-off performance, potentially causing disruption in airport operations. This study develops an airport climate-risk assessment framework combining aircraft performance modeling with the IPCC hazard–exposure–vulnerability approach, using publicly available data. The Take-Off Distance Required (TODR) was simulated for an A320-231 aircraft under varying temperature conditions, and threshold temperatures, above which fully-laden aircraft cannot depart for a given runway length, were derived for six European airports. Climate projections for 2050 were used to forecast frequency of threshold exceedance (hazard), while exposure and vulnerability were estimated through traffic volume and infrastructure-related factors. Results show that mid-century warming will raise the number of days when temperature is so high that the TODR is longer than the available runway length. Airports with shorter runways, frequent departures, and infrastructure constraints exhibit the highest projected risk levels. The findings indicate that increasing temperatures may impose growing operational constraints. The proposed framework provides an accessible preliminary tool for screening climate-related operational risks, supporting early identification of airports that may require targeted adaptation measures. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 753 KB

Open AccessProceeding Paper

Controlling a Dynamic Fuel Cell System for the Propulsion of a Regional Aircraft

by Niclas A. Dotzauer

Eng. Proc. 2026, 133(1), 75; https://doi.org/10.3390/engproc2026133075 - 6 May 2026

Viewed by 471

Abstract

In this work, a dynamic polymer electrolyte membrane (PEM) fuel cell system is modelled in Modelica using the in-house developed, open-source library ThermoFluidStream. The focus lies on the fuel cell stack, the hydrogen fuel supply and the air supply. Additionally, the thermal management [...] Read more.

In this work, a dynamic polymer electrolyte membrane (PEM) fuel cell system is modelled in Modelica using the in-house developed, open-source library ThermoFluidStream. The focus lies on the fuel cell stack, the hydrogen fuel supply and the air supply. Additionally, the thermal management and the power electronics are considered in a simplified manner. Dynamic simulations are carried out for this system over an exemplary aircraft gate-to-gate mission. Simultaneously, a baseline control scheme is developed to provide the fuel cell with sufficient product gases in a suitable state regarding the temperature, pressure and relative humidity. The results indicate that the fuel cell system performs well with standard PI controllers. Only when strong dynamics occur, such as when going from taxi to take-off, does the control scheme show some weaknesses, as expected. This fuel cell system together with its control is a powerful baseline for future investigations. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 2955 KB

Open AccessProceeding Paper

Improving Flexibility in Modular Space Robots: An Adapter to Connect a Research-Related Electromechanical Interface with a Commercial One

by Jonas Benz, Hilmi Dogu Kücüker, Wiebke Brinkmann, Mehmed Yüksel, Utku Akinci and Jonas Eisenmenger

Eng. Proc. 2026, 133(1), 76; https://doi.org/10.3390/engproc2026133076 - 7 May 2026

Viewed by 891

Abstract

With the increasing number of space research projects, systems that can be flexibly adapted to the respective orbital and planetary mission requirements and modified retrospectively as needed are becoming increasingly interesting. One application for this is modular robot systems that can be combined [...] Read more.

With the increasing number of space research projects, systems that can be flexibly adapted to the respective orbital and planetary mission requirements and modified retrospectively as needed are becoming increasingly interesting. One application for this is modular robot systems that can be combined or exchanged as needed via electromechanical interfaces without having to replace the entire system. Due to current activities in the EU, such as the Space USB project, the trend is going towards the development of a universal standard interface (USI) that, among other things, has functions for mechanical coupling and the transmission of electrical energy and data. To be able to couple different USIs with each other, one possible solution will be the use of an adapter. This paper presents such an adapter, as well as tests that have been carried out and the lessons learned from them. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 2381 KB

Open AccessProceeding Paper

Qualification Process for Additive Manufactured Metallic Connecting Flanges for Space Launcher

by Stefania Franchitti, Rosario Borrelli, Francesco Di Caprio, Giorgio Buonaiuto and Antonino Squillace

Eng. Proc. 2026, 133(1), 77; https://doi.org/10.3390/engproc2026133077 - 7 May 2026

Viewed by 442

Abstract

Additive layer manufacturing is changing the industrial landscape worldwide, particularly in high-end technology sectors, including aerospace applications. In mechanical engineering, and particularly in the aerospace industry, it is essential for quality certification that components are produced using qualified and robust manufacturing processes that [...] Read more.

Additive layer manufacturing is changing the industrial landscape worldwide, particularly in high-end technology sectors, including aerospace applications. In mechanical engineering, and particularly in the aerospace industry, it is essential for quality certification that components are produced using qualified and robust manufacturing processes that guarantee high product repeatability. Unfortunately, nowadays, too few standards are available for the qualification of products manufactured by additive technologies for the aerospace sector. The aim of this work is to qualify a metallic space component, manufactured by additive technology, according to ESA ECSS standards: in particular, the qualification of a non-conventional configuration of the interfacing flanges used to connect two adjacent space launcher’s stages, manufactured by Electron Beam-Powder Bed Fusion (EB-PBF) additive technology, is presented in the present work. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 3278 KB

Open AccessProceeding Paper

Experimental Characterization of a Compact Gyroid-Pipe Heat Exchanger for Fuel Cell Powered Electric Aircraft Propulsion

by Chetan Kumar Sain, Jeffrey Haensel, Sebastian Merbold, Franz-Theo Schoen and Stefan Kazula

Eng. Proc. 2026, 133(1), 78; https://doi.org/10.3390/engproc2026133078 - 24 Apr 2026

Viewed by 201

Abstract

The future of low-emission aviation lies in electric aircraft propulsion systems based on fuel cells. One of the challenge lies in designing and testing critical components, such as heat exchangers, and studying their impact on system-level performance and power densities. This paper presents [...] Read more.

The future of low-emission aviation lies in electric aircraft propulsion systems based on fuel cells. One of the challenge lies in designing and testing critical components, such as heat exchangers, and studying their impact on system-level performance and power densities. This paper presents the design and experimental characterization of a compact TPMS gyroid-pipe heat exchanger with embedded coolant channels. Thermal–hydraulic performance is quantified using heat transfer rates and pressure drop measurements. Three design variants of the gyroid pipe are prototyped and experiments are performed for a range of mass flow rates and temperatures. The results are presented in terms of heat exchanger characteristics and the design operating points are determined. A comparison is made between the gyroid-pipe design and a conventional louvered-fin-plate heat exchanger. The results show that the louvered-fin-plate design outperforms the gyroid-pipe design, mainly due to higher pressure loss. Additional design variants of the gyroid-pipe heat exchanger, in which the TPMS curvatures are stretched along the air length, improve the thermal and hydraulic performance. The gyroid-pipe heat exchanger design is beneficial as its volumetric and gravimetric power densities are higher than those of a conventional heat exchanger. This is important for reducing the mass of the system and ensuring the feasibility of a fuel cell system in aviation. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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10 pages, 3673 KB

Open AccessProceeding Paper

Advancements in Liquid Hydrogen Aircraft Configuration Design and Assessment

by Felix Fritzsche, Daniel Silberhorn, Vincenzo Nugnes, Tim Burschyk and Michael Kotzem

Eng. Proc. 2026, 133(1), 79; https://doi.org/10.3390/engproc2026133079 - 7 May 2026

Viewed by 462

Abstract

Liquid Hydrogen (LH2) as an energy carrier for passenger aircraft has the potential to combine low climate impact and high lifecycle energy efficiency. Due to its significantly different physical properties compared to kerosene, the integration of LH2 fuel storage and distribution systems interacts [...] Read more.

Liquid Hydrogen (LH2) as an energy carrier for passenger aircraft has the potential to combine low climate impact and high lifecycle energy efficiency. Due to its significantly different physical properties compared to kerosene, the integration of LH2 fuel storage and distribution systems interacts with the general configuration of the aircraft. In order to assess promising configuration combinations quantitatively, an aircraft design and assessment framework is further developed. These additions are aimed at capturing the interdependencies originating from the fuel system integration choices at the aircraft level and quantifying the effect of trim drag. The framework is applied to a selection of LH2 mid-to-long-range aircraft designs. A comparison of the mass breakdown, aerodynamics breakdown and performance indicators such as specific energy consumption is carried out for the framework-generated aircraft models. A trim drag induced block fuel penalty is quantified for the aircraft selection as well as a mitigation strategy based on operational constraints. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 1465 KB

Open AccessProceeding Paper

Analytical and Experimental Investigation of a Novel Piezoelectric Actuator Configuration for Resonant De-Icing Applications

by Yohan Sabathé, Valérie Pommier-Budinger and Marc Budinger

Eng. Proc. 2026, 133(1), 80; https://doi.org/10.3390/engproc2026133080 - 7 May 2026

Viewed by 309

Abstract

Resonant electromechanical de-icing uses piezoelectric actuators to generate stresses high enough to fracture and shed ice, offering an energy-efficient alternative to conventional systems. This work focuses on prestressed piezoelectric actuators composed of a ceramic stack clamped between two brackets, addressing limitations of previous [...] Read more.

Resonant electromechanical de-icing uses piezoelectric actuators to generate stresses high enough to fracture and shed ice, offering an energy-efficient alternative to conventional systems. This work focuses on prestressed piezoelectric actuators composed of a ceramic stack clamped between two brackets, addressing limitations of previous designs such as mechanical losses and screw fatigue. A new architecture is proposed, featuring a variable-cross-section screw that concentrates deformation in a thinned central region and brackets bonded to the structure to reduce losses. An analytical sizing method is developed using multi-beam longitudinal vibration modelling and two de-icing criteria, including a newly introduced one. The analysis shows how actuator geometry and modal shapes influence de-icing performance, required voltage, and mechanical stresses, highlighting key trade-offs. A dedicated prototype is designed and experimentally tested, with results in good agreement with the analytical predictions. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 4453 KB

Open AccessProceeding Paper

Future High-Efficient Engines with Solid Oxide Fuel Cell–Gas Turbine Coupling: System Modeling and Comparison of Directly and Indirectly Coupled SOFC-GT Systems

by Pascal Köhler, Jan Hollmann, Anis Taissir, Marc P. Heddrich and Stephan Kabelac

Eng. Proc. 2026, 133(1), 81; https://doi.org/10.3390/engproc2026133081 - 5 May 2026

Viewed by 536

Abstract

Aviation demand is projected to surpass 8 billion passengers per year by 2040, increasing the climate burden of kerosene-fueled propulsion. Conventional engines emit CO₂ and non-CO₂ species such as nitrogen oxides and soot, which significantly contribute to global warming. Hydrogen-based propulsion [...] Read more.

Aviation demand is projected to surpass 8 billion passengers per year by 2040, increasing the climate burden of kerosene-fueled propulsion. Conventional engines emit CO₂ and non-CO₂ species such as nitrogen oxides and soot, which significantly contribute to global warming. Hydrogen-based propulsion combining Solid Oxide Fuel Cells (SOFCs) with a Gas Turbine (SOFC–GT) can offer a carbon-neutral alternative with the potential for higher efficiencies than current turbofan and turboprop systems. In an SOFC–GT concept, waste heat from the SOFC is recovered in the turbine cycle, while the electrical output drives an electric motor, forming a hybrid turbomachinery–electric powertrain. Achieving SOFC operating temperatures of 650–800 °C at cruise conditions represents a key thermodynamic challenge, as compressor outlet conditions are insufficient. Two architectures are analyzed: direct coupling, where SOFC requirements define turbomachinery operation, and indirect coupling, which introduces air bypasses to increase flexibility. The results show that direct coupling enables higher cycle efficiency, whereas indirect coupling improves off-design operability at the expense of performance. Cross-validation of independent simulation frameworks strengthens the reliability of the findings and provides a foundation for evaluating SOFC–GT propulsion feasibility. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 4194 KB

Open AccessProceeding Paper

Design of a Scissor-Structural Mechanism for a Morphing Missile Nose Cone

by Koray Özdemir and Yavuz Yaman

Eng. Proc. 2026, 133(1), 82; https://doi.org/10.3390/engproc2026133082 - 7 May 2026

Viewed by 399

Abstract

In this paper, the design of a novel deployable scissor-structural mechanism (SSM) for the morphing of a generic missile nose cone is presented. The aim of the study is to explore a geometric transformation specially designed for the missile’s flight envelope, ensuring optimal [...] Read more.

In this paper, the design of a novel deployable scissor-structural mechanism (SSM) for the morphing of a generic missile nose cone is presented. The aim of the study is to explore a geometric transformation specially designed for the missile’s flight envelope, ensuring optimal aerodynamic performance and decreasing the aerodynamic drag coefficient across different flight conditions, then to apply it. For the geometric transformation the proposed mechanism is composed of multiple scissor-like elements (SLEs), providing a reconfigurable structure capable of adjusting the nose cone shape dynamically. To achieve a continuous and smooth missile nose cone surface the study incorporates a superelastic alloy (SEA) skin, which can deform compatibly with the SLE movements. A computational routine provides the study with an optimum SSM configuration which makes the geometric transformation the best. The computational routine minimizes the structural error between deformed nose cone shape and target nose cone shape. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 793 KB

Open AccessProceeding Paper

Architectural Design Considerations for Electric Power Systems in Future (More) Electric Aircraft

by Andrea Reindl, Rushikesh Mali and Franciscus L. J. van der Linden

Eng. Proc. 2026, 133(1), 83; https://doi.org/10.3390/engproc2026133083 - 9 May 2026

Viewed by 594

Abstract

Future More-Electric and All-Electric Aircraft (MEA/AEA) require electric power systems (EPS) with higher installed power, improved reliability, and reduced complexity, motivating a fundamental reshape of the architecture and key system-level design choices. This paper applies a structured design process to future DC-based EPS [...] Read more.

Future More-Electric and All-Electric Aircraft (MEA/AEA) require electric power systems (EPS) with higher installed power, improved reliability, and reduced complexity, motivating a fundamental reshape of the architecture and key system-level design choices. This paper applies a structured design process to future DC-based EPS and derives justified decisions from a comprehensive assessment of state-of-the-art research. Among three possible topologies, the bipolar three-wire DC grid is selected as the preferred architecture due to its superior corona suppression, insulation behavior, electromagnetic compatibility, safety, and reliability. A voltage-level study shows that increasing the low-voltage bus from 28 V to 48 V yields the most significant wiring-weight reduction (∼20%), while increasing the high-voltage level from 800 V to 1200 V offers only marginal benefits and introduces additional insulation and partial-discharge challenges. For power conversion, both isolated and non-isolated DC/DC converters are required: non-isolated multiphase interleaved converters are suited for smaller subnetworks, whereas isolated dual active bridge converters are foreseen for inter-grid power exchange. Midpoint grounding via a resistor is identified as a robust baseline concept that ensures fault detectability and operational continuity while providing controlled fault currents and limited voltage deviations, with the final resistance value to be refined based on the finalized grid configuration. The study focuses on architecture-level assessment and does not include dynamic simulations or experimental validation, which are identified as areas for future work. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 897 KB

Open AccessProceeding Paper

Design, Fabrication and Launching of CanSat-Deploying High-Power Rockets

by Eleftherios Karampasis, Vasilis Kiosoglou, Styliani Chatzipetrou, Christina Konstantinidou, Konstantinos Marsouvanidis, Emmanouil Minoudis, Antonios Mouratidis and Pericles Panagiotou

Eng. Proc. 2026, 133(1), 84; https://doi.org/10.3390/engproc2026133084 - 30 Apr 2026

Viewed by 531

Abstract

This work presents a service-oriented launcher for ESERO Greece’s CanSat 2025, delivering four reusable rockets that reach 1000 m and perform clean, near-apogee payload deployment with safe recovery. A requirements-driven process combined with systems engineering principals that utilized simulation based conceptual design, trajectory [...] Read more.

This work presents a service-oriented launcher for ESERO Greece’s CanSat 2025, delivering four reusable rockets that reach 1000 m and perform clean, near-apogee payload deployment with safe recovery. A requirements-driven process combined with systems engineering principals that utilized simulation based conceptual design, trajectory analyses and subsystem ground testing managing to deliver a modular, cost-effective and reusable system. All vehicles were used offering 12 flawless flights, fulfilling their missions. Overall, results validate the architecture and methodology under competition constraints, with vehicles ready for reuse and clear avenues for simplification offering directions for further future improvements. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 810 KB

Open AccessProceeding Paper

Reduced-Order Active Disturbance Rejection Control for the Roll Channel of Small Fixed-Wing UAVs

by Furkan Leblebici and Ozan Tekinalp

Eng. Proc. 2026, 133(1), 85; https://doi.org/10.3390/engproc2026133085 - 7 May 2026

Viewed by 408

Abstract

Roll autopilots of small fixed-wing unmanned aerial vehicles (UAVs) should reject roll disturbances and compensate for parameter variations during flight. This study investigates an active disturbance rejection control (ADRC) architecture based on an extended state observer (ESO), with emphasis on a reduced-order ESO [...] Read more.

Roll autopilots of small fixed-wing unmanned aerial vehicles (UAVs) should reject roll disturbances and compensate for parameter variations during flight. This study investigates an active disturbance rejection control (ADRC) architecture based on an extended state observer (ESO), with emphasis on a reduced-order ESO (RESO), for the roll channel of a small fixed-wing UAV. The roll axis is represented by a first-order roll-rate model augmented with actuator and rate-gyro dynamics; a proportional–derivative law is applied to the tracking error, while an extended state observer estimates a lumped total disturbance, and this estimate is fed forward for real-time disturbance compensation. Two observer designs are considered: a second-order linear ESO (LESO) and a first-order RESO using roll-rate and actuator feedback. Frequency-domain and time-domain analyses are carried out under aerodynamic uncertainty, actuator limits, sensor noise, and sinusoidal roll disturbances, and the RESO-based ADRC is compared with LESO-ADRC, a linear quadratic integral (LQI) controller, and a classical proportional–integral–derivative (PID) design. The simulations show that the RESO implementation retains the disturbance rejection and robustness of LESO-ADRC while reducing the observer order, and it offers improved disturbance rejection capability with acceptable noise sensitivity. These properties make RESO-based ADRC a promising candidate for real-time roll autopilots in small fixed-wing UAV applications. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 2238 KB

Open AccessProceeding Paper

Requirement-Based Component Placement for Aircraft Design

by Brigitte Boden and Tim Burschyk

Eng. Proc. 2026, 133(1), 86; https://doi.org/10.3390/engproc2026133086 - 7 May 2026

Viewed by 270

Abstract

In this paper, we present an approach to automate the evaluation and improvement of geometric requirements during preliminary aircraft design, specifically focusing on the complex integration of subsystems like fuel systems. Utilizing the Codex (COllaborative DEsign and eXploration) platform and its submodule codex-geometry, [...] Read more.

In this paper, we present an approach to automate the evaluation and improvement of geometric requirements during preliminary aircraft design, specifically focusing on the complex integration of subsystems like fuel systems. Utilizing the Codex (COllaborative DEsign and eXploration) platform and its submodule codex-geometry, we use Semantic Web Technologies (SWTs) to create a domain-neutral, integrated data representation. The system checks for compliance with geometric constraints in order to reduce manual work in the design. Building on previous work for requirement evaluation, this current research expands the system’s capabilities to suggest improved component placements when geometric inconsistencies are detected. The capabilities of this approach are demonstrated in an example use case placing fuel system components. Furthermore, we explore the use case of design space allocation impacted by an uncontained engine rotor failure. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 604 KB

Open AccessProceeding Paper

uqStudio: A Modular Framework for Uncertainty Quantification in Multidisciplinary Design

by Tawfiq Ahmed and Marko Alder

Eng. Proc. 2026, 133(1), 87; https://doi.org/10.3390/engproc2026133087 - 7 May 2026

Viewed by 268

Abstract

Uncertainty quantification (UQ) is essential for the robust and competitive design of climate-friendly transportation systems, such as aircraft and space launch systems. However, supporting software applications for UQ are fragmented across numerous open-source libraries, often require in-depth knowledge of the mathematics underlying UQ, [...] Read more.

Uncertainty quantification (UQ) is essential for the robust and competitive design of climate-friendly transportation systems, such as aircraft and space launch systems. However, supporting software applications for UQ are fragmented across numerous open-source libraries, often require in-depth knowledge of the mathematics underlying UQ, and commercial solutions often involve licensing costs. This can make it difficult for design experts to take uncertainties into account. To address this issue, we propose a modular, web-based framework that will guide practitioners through the most common UQ processes, such as statistical sampling, propagation through design workflows, and statistical analysis of the results. Adopting a modern client-server architecture, a backend service, called uqFramework, wraps relevant software libraries for each of the aforementioned steps. The current version focuses on probabilistic approaches, enabling the generation of Design-of-Experiment (DOE) inputs via Quasi-Monte Carlo, Latin Hypercube, and Low Discrepancy Sequence sampling methods. Furthermore, it enables the parallel execution of design and analysis workflows via DLR’s Remote Component Environment (RCE) or Python scripts. Finally, uqFramework performs global sensitivity analyses using Sobol, FAST, or Morris techniques. An interactive front-end application called uqStudio connects to uqFramework through a Representational State Transfer (REST) interface. It guides users through the UQ process via an intuitive, step-by-step interface. Interactive visualizations enable detailed exploration of each step. The framework’s capabilities are illustrated through two examples, the Ishigami function and a multidisciplinary UAV design study, verifying its precision, adaptability, and user-friendliness. We demonstrate that uqStudio enables researchers to conduct integrated UQ studies covering uncertainty specification, propagation, and sensitivity analysis without the difficulty of installing and properly using fragmented libraries. Future work includes extending visualization capabilities and integrating surrogate-modeling capabilities to enable faster workflow execution. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 442 KB

Open AccessProceeding Paper

A Behavioural Economics Approach to Demand Management for the Airport Capacity Problem

by Alvaro Rodriguez-Sanz and Luis Rubio Andrada

Eng. Proc. 2026, 133(1), 88; https://doi.org/10.3390/engproc2026133088 - 7 May 2026

Viewed by 232

Abstract

Airports face persistent capacity constraints and increasing delays. This study introduces a behavioural framework for demand management that integrates airport and airline preferences with principles from Prospect Theory. By incorporating concepts from behavioural economics—such as loss aversion, reference dependence, and non-linear probability weighting—into [...] Read more.

Airports face persistent capacity constraints and increasing delays. This study introduces a behavioural framework for demand management that integrates airport and airline preferences with principles from Prospect Theory. By incorporating concepts from behavioural economics—such as loss aversion, reference dependence, and non-linear probability weighting—into choice architectures, we explore how adaptive decision environments can influence airline scheduling and demand distribution. A practical example illustrates the applicability of the proposed methodology. Results suggest that behavioural interventions can sustain economically viable schedules while maximising total prospect value. This approach provides policymakers and operators with innovative tools to address complex capacity challenges in air transport systems. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 2662 KB

Open AccessProceeding Paper

From Ground to Orbit: Adapting CMB Calibration Technology for Space

by Irene Sánchez-Ramos, Francisco Javier Casas, Javier Cubas, Guillermo Pascual-Cisneros, Laura Castelló, Enrique Martínez-González, Rita Belén Barreiro and Patricio Vielva

Eng. Proc. 2026, 133(1), 89; https://doi.org/10.3390/engproc2026133089 - 7 May 2026

Viewed by 234

Abstract

The Cosmic Microwave Background (CMB) carries crucial information about the origin and evolution of the Universe, with its polarization patterns providing potential evidence of primordial gravitational waves. Achieving the precision required for these measurements demands highly accurate calibration methods. This study presents the [...] Read more.

The Cosmic Microwave Background (CMB) carries crucial information about the origin and evolution of the Universe, with its polarization patterns providing potential evidence of primordial gravitational waves. Achieving the precision required for these measurements demands highly accurate calibration methods. This study presents the development of a reference signal source to be integrated as the payload of LEO-CalSat, a Low-Earth Orbit satellite designed to serve as an artificial, far-field calibration tool for ground-based CMB polarization experiments. The system aims both to validate the technological readiness of a compact calibration payload for future L2 missions and to provide reference signals in the W-band (75–110 GHz) for current observatories. The calibration source, integrated within the volume of a CubeSat’s 2 U, was designed to balance miniaturization with performance, incorporating key components such as a frequency multiplier with a Voltage-Controlled Oscillator, horn antenna, and polarizer. Laboratory tests demonstrated fully polarized emission with output powers up to 6 dBm and a signal-to-noise ratio of approximately 30 dB, confirming the feasibility of precise polarization calibration. The reduced mass and power consumption (1 kg, 9 W) ensure compatibility with CubeSat constraints. The results validate the core concept and readiness of LEO-CalSat for space operation, representing a significant step toward establishing standardized, space-based calibration for future CMB missions and advancing precision cosmology. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 1618 KB

Open AccessProceeding Paper

Cooldown Analysis of a Foam-Based LH₂ Aircraft Storage Tank

by Carles Oliet, Marcial Mosqueda-Otero, Eugenio Schillaci and Jesus Castro

Eng. Proc. 2026, 133(1), 90; https://doi.org/10.3390/engproc2026133090 - 7 May 2026

Viewed by 268

Abstract

The transport sector, and aviation in particular, is strongly involved in the decarbonization process. The Clean Aviation Programme provides strong support through its funded research projects, with H₂-powered aircraft being one of the main alternatives. Storage of LH₂, as [...] Read more.

The transport sector, and aviation in particular, is strongly involved in the decarbonization process. The Clean Aviation Programme provides strong support through its funded research projects, with H₂-powered aircraft being one of the main alternatives. Storage of LH₂, as a cryogenic fluid, implies inherent particularities and complexities, which combine with those derived from integration in an aircraft (weight, functionalities, safety). The support of simulation tools is crucial to facilitate the process of designing storage tanks and their behaviour in operation or during testing. The present paper presents the cooldown studies under development within the H2ELIOS project, extending previous work more focused on dormancy and boil-off phenomena. The attention is now shifted to investigating the transient effects during the initial gas cooldown process, where the thermal inertia of the foams used in the current design plays a crucial role. This document describes a modelling approach oriented towards fast and lightweight simulation. After that, some results are presented to highlight the role of tank foam thermal inertia and the flow resistances of the inlet and outlet piping. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 2840 KB

Open AccessProceeding Paper

Experiences from Designing, Authorizing and Procuring a Liquid Hydrogen Infrastructure at the Laboratory Scale

by Daniel Terlizzi, Abdullah Bamoshmoosh and Gianluca Valenti

Eng. Proc. 2026, 133(1), 91; https://doi.org/10.3390/engproc2026133091 - 7 May 2026

Viewed by 385

Abstract

Europe’s global liquid hydrogen production share remains limited at 7%, while research institutions face an inadequate supply chain for laboratory-scale procurement. The Department of Energy at Politecnico di Milano addresses this gap through the procurement of Italy’s first laboratory-scale LH₂ liquefaction system, [...] Read more.

Europe’s global liquid hydrogen production share remains limited at 7%, while research institutions face an inadequate supply chain for laboratory-scale procurement. The Department of Energy at Politecnico di Milano addresses this gap through the procurement of Italy’s first laboratory-scale LH₂ liquefaction system, designed with 70 L/day capacity, a 200 L ATEX-classified storage tank, and a 50 L mobile transport tank for investigations into heat transfer, cryogenic valve and sensor testing, superconducting electronics, and material compatibility. The absence of Italian standards and limited European precedents necessitated a comprehensive review of relevant European safety projects and industrial guidelines. Regulatory compliance is ongoing under ATEX directives, with safety consultants defining critical parameters via leakage simulations. The project requires around three years from conception to commissioning; this paper aims to accelerate similar implementations by sharing the experience at Politecnico di Milano for future laboratory-scale facilities. Systematic coordination among engineering design, safety consultation, and regulatory authorities remains essential for viable LH₂ infrastructure implementation. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 1839 KB

Open AccessProceeding Paper

Comparative Wing Stiffness Analysis of a Dynamically Scaled Model and a Reference Aircraft Taking into Account Diverse Manufacturing Technologies

by Milczarczyk Jarosław, Rogólski Robert and Olejnik Aleksander

Eng. Proc. 2026, 133(1), 92; https://doi.org/10.3390/engproc2026133092 - 7 May 2026

Viewed by 214

Abstract

A fundamental requirement for building scale models of newly designed aircraft for the purpose of examining their flight characteristics is achieving dynamic similarity, resulting from scaling dimensions and masses. This is relatively easy to achieve, provided that specific similarity values for geometry and [...] Read more.

A fundamental requirement for building scale models of newly designed aircraft for the purpose of examining their flight characteristics is achieving dynamic similarity, resulting from scaling dimensions and masses. This is relatively easy to achieve, provided that specific similarity values for geometry and mass scaling are maintained. An additional requirement, much more difficult to achieve and therefore not always met, is ensuring stiffness similarity. This article presents the issue of scaling structural stiffness by imposing similarity conditions on the torsional and bending stiffness parameters of the wing structure. The work provides an example of utilizing selected advantages of composite technologies to design structures with the required properties. The airframe of the reference aircraft is made of metal, while its scaled model is a purely composite structure. Both the actual wing and the wing model were designed and manufactured as part of research and development work conducted at the Faculty of Mechatronics, Armament and Aviation of the Military University of Technology. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 687 KB

Open AccessProceeding Paper

Proposal of an Approach to Dimensioning the Protection Buffers of Different UAS Categories for the U-Space Separation Management Service

by Brando Fraiz, Sandra Amarillo, Alex Sanchis and Juan V. Balbastre

Eng. Proc. 2026, 133(1), 93; https://doi.org/10.3390/engproc2026133093 - 8 May 2026

Viewed by 228

Abstract

The development of a highly parallel Monte Carlo simulation framework for assessing conflict risk and dimensioning protection buffers in U-space environments provides a robust, scientifically grounded, and computationally feasible method for establishing the necessary separation standards. The simulation framework and the normalized metric [...] Read more.

The development of a highly parallel Monte Carlo simulation framework for assessing conflict risk and dimensioning protection buffers in U-space environments provides a robust, scientifically grounded, and computationally feasible method for establishing the necessary separation standards. The simulation framework and the normalized metric provide a reliable, scientific, and scalable method for setting the required separation standards, allowing regulatory bodies to dimension buffers that are both compliant with acceptable level of safety requirements and scalable with increasing traffic density. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 1074 KB

Open AccessProceeding Paper

Combining Life Support Systems with Digital Twins: A New Potential?

by Felicitas Leese and Claas Olthoff

Eng. Proc. 2026, 133(1), 94; https://doi.org/10.3390/engproc2026133094 - 8 May 2026

Viewed by 526

Abstract

The next generation of crewed space missions will take astronauts farther away from Earth than ever before. These missions will necessitate increasingly sophisticated and autonomous control of Life Support Systems (LSS) to ensure astronauts stay alive, healthy and happy. High system autonomy and [...] Read more.

The next generation of crewed space missions will take astronauts farther away from Earth than ever before. These missions will necessitate increasingly sophisticated and autonomous control of Life Support Systems (LSS) to ensure astronauts stay alive, healthy and happy. High system autonomy and resilience are therefore critical to mission success. A key enabler for future space missions are Digital Twins (DTs) of LSSs. The use of DTs to date includes a wide range of applications. Nevertheless, they have not yet been adopted for LSSs. Combining LSSs with DTs offers benefits in the development and testing of new LSS technologies, as well as their monitoring once missions are underway. Together with the DT, astronauts can make time-critical decisions on their own, which is a crucial factor for enabling deep space missions. However, implementing DTs comes with its own challenges, such as collecting all the necessary data with appropriate sensors and handling the vast amounts of data generated. Additionally, the DT must be given boundaries in which it can control its physical counterpart so as not to harm valuable equipment. These development issues and possible shortcomings of DTs, as well as the potential of DTs of LSSs are discussed in this paper. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 4252 KB

Open AccessProceeding Paper

Assessment of C-Type Winglet Integration Impact on the Performance of a Fixed-Wing BWB UAV

by Stavros Kapsalis, Thomas Dimopoulos, Pavlos Kaparos, Georgios Iatrou, Pericles Panagiotou and Kyriakos Yakinthos

Eng. Proc. 2026, 133(1), 95; https://doi.org/10.3390/engproc2026133095 - 7 May 2026

Viewed by 268

Abstract

This work examines the aerodynamic efficiency improvement achieved by integrating C-type winglets into a small-scale Blended Wing Body (BWB) Unmanned Aerial Vehicle (UAV). The platform, designated S-3M, is an evolution of the RX-3 1:3 sub-scale demonstrator developed and flight-tested by the Laboratory of [...] Read more.

This work examines the aerodynamic efficiency improvement achieved by integrating C-type winglets into a small-scale Blended Wing Body (BWB) Unmanned Aerial Vehicle (UAV). The platform, designated S-3M, is an evolution of the RX-3 1:3 sub-scale demonstrator developed and flight-tested by the Laboratory of Fluid Mechanics and Turbomachinery (LFMT) during the DELAER project. The S-3M is redesigned for catapult launch and Intelligence–Surveillance–Reconnaissance (ISR) missions, supporting a useful payload of up to 5 kg. Strict dimensional, cost, and development constraints posed challenges in preserving aerodynamic efficiency and achieving sufficient stability margins. To meet these requirements, the design incorporates C-type winglets, tailored to enhance aerodynamic performance while providing stabilizing effects. Their integration enabled an increase in gross take-off weight (GTOW) and payload capacity, while ensuring adequate trimming without the need for a conventional horizontal tail. The aerodynamic development of the winglets and the overall configuration is supported by Computational Fluid Dynamics (CFD) analyses, followed by performance calculations. S-3M was manufactured by Carbon Fiber Technologies (CFT) and successfully flight-tested by LFMT, validating the design choices. Overall, the study demonstrates that C-type winglets can significantly improve efficiency and expand the operational envelope of BWB UAVs, highlighting the value of non-planar lifting surfaces in modern UAV design. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 735 KB

Open AccessProceeding Paper

Rethinking Cabin Linings: From Waste Carbon to High-Performance Structures

by Moritz Bäß, Kai-Uwe Schröder, Maximilian Weber, Benedikt Auernhammer and Mesut Cetin

Eng. Proc. 2026, 133(1), 96; https://doi.org/10.3390/engproc2026133096 - 8 May 2026

Viewed by 210

Abstract

Reducing the ecological footprint of aviation is a key objective in the development of future aircraft. This is particularly relevant in the emerging field of Urban Air Mobility, which demands sustainable yet industrially feasible solutions due to expected high production rates. As part [...] Read more.

Reducing the ecological footprint of aviation is a key objective in the development of future aircraft. This is particularly relevant in the emerging field of Urban Air Mobility, which demands sustainable yet industrially feasible solutions due to expected high production rates. As part of the cooperative research project KONKAV, innovative materials and manufacturing methods are being explored to meet these demands. One such approach is the partial consolidation of nonwovens made from recycled carbon fibers, aimed at producing multifunctional, recyclable components for Urban Air Mobility cabin linings for high bending stiffness requirements. This study presents the experimental characterization of various nonwoven architectures, focusing on how different levels of consolidation affect their specific mechanical properties. The partially consolidated structure enables tailored stiffness profiles, making it possible to optimize structural performance while integrating functions such as thermal insulation and acoustic damping directly into the lining. An analytical material model has been developed by analyzing the experimental results. The findings demonstrate that partially consolidated nonwovens can achieve a competitive stiffness-to-weight ratio, with advantages over conventional glass-fiber-reinforced composites in terms of eco-efficiency and circularity. The proposed construction method offers potential for cost-effective, lightweight solutions that support closed-loop material use in aviation interiors. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 3613 KB

Open AccessProceeding Paper

Virtual Manufacturing Finite Element Framework for Defect Prediction in Resin Impregnation Processes

by Giorgio Maria D’Orazi, Antonio Raimondo and Andrea Cini

Eng. Proc. 2026, 133(1), 97; https://doi.org/10.3390/engproc2026133097 - 8 May 2026

Viewed by 298

Abstract

In resin impregnation processes for composite manufacturing, proper infusion of the preform is essential to achieve optimal component quality. Manufacturing-induced defects, such as voids, are commonly present in the final product; however, minimizing their occurrence is critical to preserving the component’s mechanical properties. [...] Read more.

In resin impregnation processes for composite manufacturing, proper infusion of the preform is essential to achieve optimal component quality. Manufacturing-induced defects, such as voids, are commonly present in the final product; however, minimizing their occurrence is critical to preserving the component’s mechanical properties. This study aims to provide a predictive tool for defect analysis and composite manufacturing process optimization. A finite element-based multi-scale framework is developed to simulate resin impregnation, coupling macro-scale multiphase flow analysis with meso-scale modeling of unsaturated porous media. The model is verified against commercial software and used to perform a parametric study. Results demonstrate the framework capability to predict filling times, resin front progression, and defect formation, providing insights onto the correlation between material behavior and flow kinetics. The proposed simulation tool enables process optimization and defect minimization, offering a flexible and efficient alternative to heuristic process setting. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 753 KB

Open AccessProceeding Paper

Gradient-Based Optimisation of Composite Aircraft Structures Using High-Order Beam Models

by Donato Cardone, Rauno Cavallaro and Andrea Cini

Eng. Proc. 2026, 133(1), 98; https://doi.org/10.3390/engproc2026133098 - 8 May 2026

Viewed by 364

Abstract

The structural design of aeronautical composite components requires numerical models which capture multilayer behaviour while keeping computational costs manageable. High-fidelity three-dimensional (3D) finite element models are often too expensive for systematic optimisation, whereas classical 1D and 2D formulations rely on simplifying assumptions. This [...] Read more.

The structural design of aeronautical composite components requires numerical models which capture multilayer behaviour while keeping computational costs manageable. High-fidelity three-dimensional (3D) finite element models are often too expensive for systematic optimisation, whereas classical 1D and 2D formulations rely on simplifying assumptions. This work investigates the Carrera Unified Formulation (CUF) as a cost-effective composite simulation tool, using Equivalent Single-Layer (ESL) and Layer-Wise (LW) beam models whose hierarchical cross-sectional expansions approximate 2D/3D behaviour within a one-dimensional framework. A representative composite stiffened panel is analysed to compare 3D solid, 2D shell, CUF-ESL, and CUF-LW models in terms of static response and computational cost. High-order CUF-ESL models reproduce 3D strain fields with 2–7% error while reducing analysis time by over 89%. The CUF–FEM framework is then integrated into a gradient-based optimisation scheme with Automatic Differentiation, adjoint sensitivities, and Kreisselmeier–Steinhauser constraint aggregation. Panel optimisation achieves a 64% mass reduction in six iterations with CUF-ESL, compared with 56% in 18 iterations for the 2D shell model. The results prove that CUF-ESL beam models are a computationally cost-effective tool for preliminary sizing of composite structures. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 1011 KB

Open AccessProceeding Paper

Current Trends and Challenges in Unconventional Aircraft Conceptual Design

by Álvaro Cobo-González and Cristina Cuerno-Rejado

Eng. Proc. 2026, 133(1), 99; https://doi.org/10.3390/engproc2026133099 - 8 May 2026

Viewed by 505

Abstract

Unconventional aircraft configurations hold great potential for improving air transport efficiency and reducing aviation’s contribution to global warming. However, these novel layouts require robust evidence of their advantages from the conceptual design phase to justify the substantial development costs they entail. Computerized design [...] Read more.

Unconventional aircraft configurations hold great potential for improving air transport efficiency and reducing aviation’s contribution to global warming. However, these novel layouts require robust evidence of their advantages from the conceptual design phase to justify the substantial development costs they entail. Computerized design environments provide the most suitable framework for the conceptual design of unconventional aircraft. This paper proposes an original taxonomy of unconventional aircraft configurations tailored to computerized design environments, reviews the existing tools with such design capabilities, and identifies the current trends and challenges in this field. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 3075 KB

Open AccessProceeding Paper

Numerical Analysis of Experimental Uncertainties in Ultrasonic Guided Waves Propagation for Damage Monitoring in Composite Structures

by Javier Hernandez-Olivan, Panagiotis Kolozis, Andrea Calvo-Echenique, José Manuel Royo, Susana Calvo and Elias P. Koumoulos

Eng. Proc. 2026, 133(1), 100; https://doi.org/10.3390/engproc2026133100 - 9 May 2026

Viewed by 234

Abstract

Ultrasonic Guided Wave (UGW)-based Structural Health Monitoring (SHM) is a promising strategy for detecting damage to aeronautical structures, although its application is complicated by signal complexity and experimental uncertainty. This work seeks to identify damage-sensitive signal features for integration into Machine Learning (ML) [...] Read more.

Ultrasonic Guided Wave (UGW)-based Structural Health Monitoring (SHM) is a promising strategy for detecting damage to aeronautical structures, although its application is complicated by signal complexity and experimental uncertainty. This work seeks to identify damage-sensitive signal features for integration into Machine Learning (ML) frameworks, offering physics-informed indicators. The study combined experimental monitoring of damage to Carbon Fibre Reinforced Polymer (CFRP) plates and finite element models. To overcome the numerical–experimental mismatch, an ML algorithm predicted experimental characteristics from numerical data. The robustness of the model was validated by extrapolation (prediction of future damage) and generalization (prediction on unseen plates) strategies, confirming that ML can robustly correct for uncertainty. These results validate hybrid strategies that feed Digital Twin approaches to structural diagnosis and real-time forecasting. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 2928 KB

Open AccessProceeding Paper

2D Nanomaterial-Based Transparent Electrodes for Next-Generation III–V Multijunction Space Solar Cells

by Noor ul Ain Ahmed, Maksim Shundalau, Marialuigia Raimondo, Vidmantas Gulbinas, Maria Sarno, Claudia Cirillo and Patrizia Lamberti

Eng. Proc. 2026, 133(1), 101; https://doi.org/10.3390/engproc2026133101 - 9 May 2026

Viewed by 278

Abstract

Multijunction solar cells employing a GaInP/GaAs/Ge triple-junction configuration are the dominant technology for space photovoltaic applications. The choice of an efficient electrode is crucial in solar cells, as it enables effective charge carrier collection and transport while allowing maximum light to reach the [...] Read more.

Multijunction solar cells employing a GaInP/GaAs/Ge triple-junction configuration are the dominant technology for space photovoltaic applications. The choice of an efficient electrode is crucial in solar cells, as it enables effective charge carrier collection and transport while allowing maximum light to reach the active layer. Indium tin oxide (ITO)/graphene hybrid electrodes have emerged as smart transparent conductors offering significant advantages over conventional brittle ITO films. Graphene electrodes were prepared by cold-wall chemical vapor deposition and ITO electrodes were commercially obtained and used as a base for hybrid ITO/graphene electrodes. Raman spectroscopy confirmed the successful integration and characteristic G and 2D bands on the ITO surface. Nanoscale current mapping via Tunneling Atomic Force Microscopy (TUNA-AFM) verified continuous conductive pathways throughout the film with ~60% increase in nanoscale tunneling current at graphene/ITO interfaces, indicating improved local charge transport pathways. These results demonstrate the suitability of ITO/graphene hybrid electrodes a promising material for multijunction solar cells and other aerospace technologies. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 748 KB

Open AccessProceeding Paper

Gust Behaviour Analysis of Fixed-Wing Multi-Mission Remotely Piloted Aircraft

by Carmelo-Javier Villanueva-Cañizares, Álvaro Gómez-Rodríguez and Cristina Cuerno-Rejado

Eng. Proc. 2026, 133(1), 102; https://doi.org/10.3390/engproc2026133102 - 9 May 2026

Viewed by 247

Abstract

Studying the effect of gusts on aircraft is an essential task in aerodynamic and structural design and analysis, as well as in airworthiness certification. The singular design and operational characteristics of Remotely Piloted Aircraft (RPA) demand a specific study of gust effects on [...] Read more.

Studying the effect of gusts on aircraft is an essential task in aerodynamic and structural design and analysis, as well as in airworthiness certification. The singular design and operational characteristics of Remotely Piloted Aircraft (RPA) demand a specific study of gust effects on these vehicles. This investigation uses the discrete gust criterion prescribed in current fixed-wing RPA codes to analyse the gust behaviour of RPA from a conceptual design viewpoint. The results obtained from the flight envelope analysis allow us to assess the influence of stall, manoeuvring, and gust effects on the overall envelope, with these aspects showing significant differences with respect to conventionally piloted aircraft. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 1402 KB

Open AccessProceeding Paper

Managing Thermal Emission for Reliable Deep Space Trajectory Control

by Fermin Navarro-Medina, Pablo Solano-López, Ester Velázquez-Navarro and Marta Moure Cuadrado

Eng. Proc. 2026, 133(1), 103; https://doi.org/10.3390/engproc2026133103 - 9 May 2026

Viewed by 170

Abstract

Deep space missions face challenges in guidance, navigation, and control due to subtle non-gravitational forces, such as the Pioneer Anomaly—an unexplained acceleration toward the Sun observed in Pioneer 10 and 11. The most plausible cause is thermal recoil from anisotropic infrared emission by [...] Read more.

Deep space missions face challenges in guidance, navigation, and control due to subtle non-gravitational forces, such as the Pioneer Anomaly—an unexplained acceleration toward the Sun observed in Pioneer 10 and 11. The most plausible cause is thermal recoil from anisotropic infrared emission by onboard systems, RTGs, and radiators. This study models thermal acceleration based on spacecraft geometry and heat-source placement, analyzing two spacecraft configurations for outer solar system missions. By parametric analysis, we assess the influence of geometric, thermo-optical properties, and emitted power, and we propose design recommendations—symmetrical layouts, optimized materials, and heat management—to mitigate or exploit thermal forces for improved navigation passive control. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 1344 KB

Open AccessProceeding Paper

Preliminary Study on the Impact of the Ad Hoc Separation Concept in Free Route Airspace

by Lidia Serrano-Mira, Marta Sánchez-Aguilera Roncero, Javier A. Pérez-Castán, Eduardo S. Ayra, Marta Pérez Maroto and Luis Pérez Sanz

Eng. Proc. 2026, 133(1), 104; https://doi.org/10.3390/engproc2026133104 - 6 May 2026

Viewed by 273

Abstract

One of today’s major challenges in air transport is accommodating future growth in traffic demand, which requires addressing capacity limitations. Since separation minima influence airspace capacity, technological progress enables exploring innovative approaches. This paper presents the Ad Hoc Separation concept, which involves applying [...] Read more.

One of today’s major challenges in air transport is accommodating future growth in traffic demand, which requires addressing capacity limitations. Since separation minima influence airspace capacity, technological progress enables exploring innovative approaches. This paper presents the Ad Hoc Separation concept, which involves applying different separation minima between aircraft pairs based on aircraft type, weight, encounter geometry, flight level, or wind. As a novel approach requiring operational changes to the current ATM system, further research is justified only if tangible benefits are demonstrated. Fast-time simulations in European en-route sectors, both conventional and Free Route Airspace, are performed to assess the benefits. The results show a capacity gain of about one aircraft per hour, along with positive environmental and cost-efficiency benefits. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 2232 KB

Open AccessProceeding Paper

Experimental and Numerical Investigation of Cooling Ducts for Thermal Management of Fuel Cell-Based Aero Engines

by Sebastian Merbold, Franz-Theo Schön, Prabhjot Singh, Chetan Sain, Jeffrey Hänsel, Stefan Kazula and Stefanie de Graaf

Eng. Proc. 2026, 133(1), 105; https://doi.org/10.3390/engproc2026133105 - 10 May 2026

Viewed by 322

Abstract

Effective thermal management is crucial for the development of future electrified aircraft propulsion systems. One of the most challenging phases is the take-off phase, which imposes particularly high demands on cooling systems. In addition, the aerodynamic drag during cruise flight has to be [...] Read more.

Effective thermal management is crucial for the development of future electrified aircraft propulsion systems. One of the most challenging phases is the take-off phase, which imposes particularly high demands on cooling systems. In addition, the aerodynamic drag during cruise flight has to be kept to a minimum. This study introduces a novel experimental thermal management system using a test stand with a modular air duct (TMTmad), which is designed specifically to investigate different configurations of air supply and heat exchanger in fuel cell-based electrified propulsion systems. Given the versatility of nacelle-integrated electrified propulsion architectures, this approach offers high flexibility in the design and integration of thermal management systems. This includes aspects such as the location, orientation and geometry of an air-cooled heat exchanger (HEX), as well as the inlet and outlet configurations. Moreover, the optimization of the uniform flow guidance of the duct flow within the nacelle and the integration of additional fans to ensure airflow under critical conditions can be studied. The main heat source delivers up to 6

k W

of heating power with a temperature range from −20 °C to 200 °C. The study measures the heat flux and pressure losses within these systems and includes a thorough fluid flow analysis. Furthermore, the experimental data serves as a valuable resource for validating numerical models of cooling ducts, enhancing the accuracy and reliability of future design iterations. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 1450 KB

Open AccessProceeding Paper

Flight Tests of Scaled Demonstrator for General Aviation Aircraft Concept

by Thorben Hammer, Stefanie de Graaf and Anne Treder

Eng. Proc. 2026, 133(1), 106; https://doi.org/10.3390/engproc2026133106 - 9 May 2026

Viewed by 370

Abstract

The present work investigates the flight characteristics and handling qualities of the novel aircraft concept “HyBird” through multiple scaled flight experiments. Various adaptations were made to the demonstrator—especially to the placement of the electrically driven propeller. The first flight experiment revealed drawbacks of [...] Read more.

The present work investigates the flight characteristics and handling qualities of the novel aircraft concept “HyBird” through multiple scaled flight experiments. Various adaptations were made to the demonstrator—especially to the placement of the electrically driven propeller. The first flight experiment revealed drawbacks of the positioning of the electric propeller at the wing tips and tips of the V-Tail. In further experiments, the propeller positioning was changed to investigate a modified aircraft configuration. These flight tests showed significantly improved flight characteristics. The findings substantiate the critical role of propeller positioning in the design of novel aircraft concepts. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 1964 KB

Open AccessProceeding Paper

ERGO: An Autonomy Framework for Space Robotics and Beyond

by Francisco Javier Colmenero, Jorge Ocón, Mercedes Alonso, Raquel Jalvo and Javier Ramos

Eng. Proc. 2026, 133(1), 107; https://doi.org/10.3390/engproc2026133107 - 9 May 2026

Viewed by 535

Abstract

A software autonomy framework provides a vital solution to the challenges posed by growing congestion in Earth’s orbits and the increasing complexity of planetary exploration. For satellite constellations, IOS & ISAM missions, autonomy minimizes dependence on ground control by enabling real-time decision-making for [...] Read more.

A software autonomy framework provides a vital solution to the challenges posed by growing congestion in Earth’s orbits and the increasing complexity of planetary exploration. For satellite constellations, IOS & ISAM missions, autonomy minimizes dependence on ground control by enabling real-time decision-making for spacecraft collision avoidance, client capture, robotic servicing operations, resource optimization, and resilience against cyber threats in a crowded and geopolitically sensitive space environment. Similarly, autonomous frameworks allow rovers to operate efficiently on distant planets, where communication delays make manual control impractical. By integrating adaptive navigation, fault management, and cooperative behaviors, these systems enhance mission success, reduce operational costs, and ensure rapid responses to dynamic conditions, both in orbit and on planetary surfaces. This paper presents the ERGO Autonomy SW Framework as a mature solution to deal with these space challenges. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 3397 KB

Open AccessProceeding Paper

Multidisciplinary Design Optimisation of Flexible Aircraft: Advancing Aeroelastic Co-Design with Active Load Alleviation

by Armand-Ioan Curpanaru, Philippe Pastor, Fabrice Demourant and Eric Nguyen Van

Eng. Proc. 2026, 133(1), 108; https://doi.org/10.3390/engproc2026133108 - 9 May 2026

Viewed by 411

Abstract

The development of aircraft with high-aspect-ratio (HAR) wings and flexible lightweight structures is at the forefront of efforts for a more sustainable aviation. Nevertheless, this change in aircraft configuration is accompanied by significant complexity. Specifically, it calls for the modelling of strong aero-structural [...] Read more.

The development of aircraft with high-aspect-ratio (HAR) wings and flexible lightweight structures is at the forefront of efforts for a more sustainable aviation. Nevertheless, this change in aircraft configuration is accompanied by significant complexity. Specifically, it calls for the modelling of strong aero-structural couplings and the concurrent synthesis of active control laws to mitigate the higher structural loads generated by HAR wings. Managing these challenges from the very onset of the preliminary design phase demands a unified approach. Consequently, this paper leverages a Flexible Wing Co-design framework that integrates aeroelastic wing design and robust

H_{\infty}

controller synthesis for gust load alleviation (GLA). This co-design capability is deployed to conduct a sensitivity analysis of wing aspect ratio effects, as well as a multidisciplinary design optimisation (MDO) approach focused on minimising mission block fuel. The results confirm that the proposed approach delivers substantial mass savings and superior aircraft performance, establishing it as an indispensable tool for the early stage development of next generation configurations. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 2630 KB

Open AccessProceeding Paper

Numerical Modeling of Annular-Mist Flow Within a Water Recovery Unit

by Georgios Iosifidis, Richard Haidl, Koji Hasegawa and Bernhard Weigand

Eng. Proc. 2026, 133(1), 109; https://doi.org/10.3390/engproc2026133109 - 9 May 2026

Viewed by 287

Abstract

Future aircraft propulsion concepts (e.g., water-enhanced engines and fuel cells) will depend on efficient water recovery to enhance cycle efficiency and environmental performance. Operating conditions commonly involve droplet (mist) transport in turbulent air and wall-bounded films formed by droplet–wall interactions. This work develops [...] Read more.

Future aircraft propulsion concepts (e.g., water-enhanced engines and fuel cells) will depend on efficient water recovery to enhance cycle efficiency and environmental performance. Operating conditions commonly involve droplet (mist) transport in turbulent air and wall-bounded films formed by droplet–wall interactions. This work develops an Eulerian–Lagrangian model within the RANS/URANS framework that accounts for air–droplet–wall phenomena—interfacial shear, impingement, and film advection. A dynamic contact-angle model, implemented and calibrated from static contact angle measurements performed in this study, represents wall wetting at the liquid–solid interface. The model is validated against experiments using two design metrics: pressure loss across the unit and recovered water mass fraction. At a low Mach number (

M a = 0.1

), saturated and dry air produce nearly identical pressure losses in the circular test section, whereas the separation lip geometry exerts a strong influence via local acceleration and separation. The simulations reproduce measured pressure drops and water mass recovery with close agreement. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 443 KB

Open AccessProceeding Paper

Curved Shear Panel Theory as an Enabler for Gradient-Based Wing Optimization

by Moritz Bäß, Lukas Kettenhofen and Kai-Uwe Schröder

Eng. Proc. 2026, 133(1), 110; https://doi.org/10.3390/engproc2026133110 - 11 May 2026

Viewed by 204

Abstract

In the preliminary design of aircraft structures, efficient modelling techniques are essential to balance accuracy and computational cost. Shear Panel Theory (SPT) offers a simple yet effective idealisation of thin-walled, stiffened structures such as wings. It captures more structural detail—like ribs, sweep and [...] Read more.

In the preliminary design of aircraft structures, efficient modelling techniques are essential to balance accuracy and computational cost. Shear Panel Theory (SPT) offers a simple yet effective idealisation of thin-walled, stiffened structures such as wings. It captures more structural detail—like ribs, sweep and taper—than traditional beam idealisation and would otherwise require detailed finite element analysis. However, compared to a finite element model, the degrees of freedom of the structure as well as the meshing effort are significantly reduced, as SPT idealisation uses a structural element approach. This improves mass estimation and structural response calculation and makes SPT particularly well-suited for optimisation tasks in early design phases. This work presents a methodology to derive structural properties of wing segments based on NACA airfoils using SPT. This offers adjustment of the wing’s geometry for use in aeroelastic analysis and enables fast evaluation of structural behaviour and gradient computation, supporting integration into multidisciplinary design optimisation frameworks. The proposed methodology advances the use of idealised structural models in aircraft design by bridging the gap between high-fidelity analysis and system-level aeroelastic simulations, supporting faster and more informed early design iterations. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 15758 KB

Open AccessProceeding Paper

Additional Mitigation Means Against the Thermal Runaway of Portable Electronic Devices in Cabin and Cockpit

by Victor Norrefeldt, Arnav Pathak, Simon Holz, Jonas Pfaff, Marie Pschirer, Sebastian Schopferer and Jürgen Kuder

Eng. Proc. 2026, 133(1), 111; https://doi.org/10.3390/engproc2026133111 - 11 May 2026

Viewed by 245

Abstract

The carriage of portable electronic devices (PED) powered by lithium-ion batteries in the aircraft cabin today is a fact. Passengers carry several such batteries in mobile phones, tablets, laptops, e-cigarettes, power banks, etc. Even though rare, there is a remaining risk that a [...] Read more.

The carriage of portable electronic devices (PED) powered by lithium-ion batteries in the aircraft cabin today is a fact. Passengers carry several such batteries in mobile phones, tablets, laptops, e-cigarettes, power banks, etc. Even though rare, there is a remaining risk that a Li-ion battery experiences thermal runaway. This typically results in the emission of smoke and gas as well as the emergence of flames and fire, thus posing a threat to safe operation. To meet this challenge, procedures have been defined, and additional mitigation means have emerged on the market. This study presents an anonymized assessment of additional mitigation means. For this, manufacturers provided samples of their product on a voluntary basis to test the potential to contain a Li-ion battery fire. Furthermore, handling was evaluated by a panel of cabin crew members. As a result, a series of recommendations for additional mitigation means and procedures was derived. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 2685 KB

Open AccessProceeding Paper

Dual-Redundant Broadband Low-Noise Amplifier Module for Inter-Satellite Links at V-Band

by Peiman Parand, Hermann Barbato, Patrick Ettore Longhi, Alessandro Barigelli, Francesco Vitulli and Ernesto Limiti

Eng. Proc. 2026, 133(1), 112; https://doi.org/10.3390/engproc2026133112 - 9 May 2026

Viewed by 270

Abstract

This paper presents the design and simulation of a dual-redundant broadband low-noise amplifier (LNA) module for inter-satellite communication links operating in the V-band (59–71 GHz). The growing demand for high-capacity space communication systems requires highly reliable, low-noise front-end architectures capable of maintaining performance [...] Read more.

This paper presents the design and simulation of a dual-redundant broadband low-noise amplifier (LNA) module for inter-satellite communication links operating in the V-band (59–71 GHz). The growing demand for high-capacity space communication systems requires highly reliable, low-noise front-end architectures capable of maintaining performance over long mission lifetimes. To address these needs, a selectable dual-input receiver architecture is proposed, integrating a waveguide dual-probe, redundant switching, and a two-stage LNA within a single Gallium Arsenide (GaAs) MMIC. The design methodology accounts for the non-ideal behavior of the redundant branch and its impact on noise figure and insertion loss. The front-end is implemented using a 70 nm GaAs mHEMT technology optimized for millimeter-wave low-noise applications. Simulations show an insertion gain higher than 15 dB across the operational band, with gain ripple below 1.3 dB peak-to-peak. The simulated system noise figure is approximately 3.0 dB, closely matching the target specification. The results demonstrate that the proposed architecture provides improved reliability through redundancy while maintaining competitive noise and gain performance for future V-band inter-satellite links. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 4670 KB

Open AccessProceeding Paper

Experimental Results of the Distribution of Halon-Free Cargo Fire Suppression Agents in a Cargo Hold Demonstrator

by Victor Norrefeldt, Arnav Pathak and Marie Pschirer

Eng. Proc. 2026, 133(1), 113; https://doi.org/10.3390/engproc2026133113 - 11 May 2026

Viewed by 286

Abstract

Today’s cargo bay uses Halon 1301 gas for fire suppression. While effective, this fluid is broadly banned due to its high global warming potential (GWP) of 5700 and its high ozone depletion potential. Hence, alternative agents for cargo fire protection are being sought. [...] Read more.

Today’s cargo bay uses Halon 1301 gas for fire suppression. While effective, this fluid is broadly banned due to its high global warming potential (GWP) of 5700 and its high ozone depletion potential. Hence, alternative agents for cargo fire protection are being sought. In this framework, tests were conducted in the Fraunhofer Flight Test Facility with the goal of evaluating the uniformity of spread of various fire suppression agents, specifically a blend of a Hydrofluoroolefine (HFO) and CO₂. The facility’s cargo area, with a volume of 38 m³, features a low-pressure vessel integrating a previously operated aircraft segment. In a series of tests, the alternative extinguishing agent was supplied into the cargo hold demonstrator and concentrations were measured in different locations to understand the uniformity of distribution and the system behaviour under a realistic flight envelope. Test results show several interesting outcomes. In the empty cargo hold with air movement due to leakage, initial bottle filling weight and extinguishing agent initial concentration are consistent. When no flow movement is applied to the cargo hold, a separation between upper and lower cargo hold concentrations is found. The heavy extinguishing agent necessitates a buoyancy correction of the measured pressure differential by air density and elevation. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 2222 KB

Open AccessProceeding Paper

Automated Parametric Finite-Element-Model Generation and Optimization of a Composite Aircraft Wing

by Nikolaos Ziakos and Andrea Cini

Eng. Proc. 2026, 133(1), 114; https://doi.org/10.3390/engproc2026133114 - 9 May 2026

Viewed by 432

Abstract

An automated framework for the parametric FE model generation and sizing of composite aircraft wings suitable for early-stage studies is presented. Implemented in Python and HyperMesh TCL, the tool controls both outer-geometry parameters, such as span, taper ratio, and twist, and internal-structural layout [...] Read more.

An automated framework for the parametric FE model generation and sizing of composite aircraft wings suitable for early-stage studies is presented. Implemented in Python and HyperMesh TCL, the tool controls both outer-geometry parameters, such as span, taper ratio, and twist, and internal-structural layout parameters, such as spar locations, rib spacing, and stringer layouts, and generates analysis-ready 2D composite GFEM models with material assignment and layups for size optimization. To demonstrate the workflow, a Design of Experiments (DoE) is performed on a representative transport wing internal structural layout, while keeping the outer geometry fixed. For each DoE point, OptiStruct performs gradient-based composite-size optimization to minimize structural mass, subject to composite strength (max strain), buckling, and metallic no-yielding constraints. A staged multi-run strategy is implemented to mitigate the effects of local minima. DoE results show a strong correlation and a non-monotonic effect of stringer number, an increase in mass as the front spar moves aft, and a comparatively weaker effect of the number of aluminum ribs. As a preliminary baseline, a Random Forest surrogate trained on the DoE predicts the wing structural mass with reasonable accuracy (RMSE

= 0.081

), motivating the future implementation of Gaussian process models with uncertainty modeling. The framework accelerates early-stage structural design exploration and is amenable to surrogate-based optimization. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 2854 KB

Open AccessProceeding Paper

Development of an Air Curtain to Improve Thermal Comfort in Cargo Aircraft

by Jorge García Rodríguez, Pablo Lopez Domene and Alejandro Camps Cabezas

Eng. Proc. 2026, 133(1), 115; https://doi.org/10.3390/engproc2026133115 - 9 May 2026

Cited by 1 | Viewed by 349

Abstract

In long-haul flights, cold non-insulated structural zones within aircraft cabins can lead to discomfort for passengers and crew, particularly during cruise phases. Moreover, during ground operations in cold weather, maintaining the thermal conditioning of the cabin becomes challenging, especially with open doors. This [...] Read more.

In long-haul flights, cold non-insulated structural zones within aircraft cabins can lead to discomfort for passengers and crew, particularly during cruise phases. Moreover, during ground operations in cold weather, maintaining the thermal conditioning of the cabin becomes challenging, especially with open doors. This article presents the development of an active air curtain designed to address these issues by isolating significant cold zones and enhancing cabin comfort. The conceptual design is based on redirecting conditioned air to form a controlled barrier, which reduces thermal gradients and air mixing. The cold stream infiltrating from non-insulated structures was characterized under typical cruise scenarios using flight test data, while the open-door scenario on the ground was characterized analytically. A CFD analysis was performed to optimize nozzle geometry, airflow rate, and placement. Based on simulation results, a prototype was manufactured and tested in a controlled laboratory environment. The experimental validation confirmed the effectiveness of the air curtain in minimizing heat loss and improving thermal comfort. This paper discusses design trade-offs, thermal performance, and integration considerations, highlighting the potential of air curtains as a lightweight and low-impact solution for environmental control systems in modern transport cargo aircraft. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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10 pages, 1236 KB

Open AccessProceeding Paper

Electrical System Architectures for Future Electric Aircraft

by Andrea Reindl and Franciscus L. J. van der Linden

Eng. Proc. 2026, 133(1), 116; https://doi.org/10.3390/engproc2026133116 - 13 May 2026

Cited by 1 | Viewed by 506

Abstract

The electrification of future aircraft poses significant challenges to existing electrical power system (EPS) architectures, particularly due to increasing installed power levels, the introduction of electric flight control, and the (partial) electrification of propulsion systems. The transition to AEA requires more than simply [...] Read more.

The electrification of future aircraft poses significant challenges to existing electrical power system (EPS) architectures, particularly due to increasing installed power levels, the introduction of electric flight control, and the (partial) electrification of propulsion systems. The transition to AEA requires more than simply replacing conventional systems with electrical counterparts. It demands a fundamental redesign of the electrical system architecture. This study investigates three novel EPS architectures for More Electric Aircraft (MEA) and three corresponding ones for All Electric Aircraft (AEA). All concepts are based on the segmentation of the EPS into electrically isolated microgrids and the separation between propulsion and on-board systems, aiming to improve system reliability, efficiency, fault management, and certification flexibility. The disruptive architecture proposes islanded microgrids, where electrical loads are grouped by Design Assurance Level (DAL) and spatial distribution. Each microgrid is powered locally by batteries, which significantly reduces cabling mass, electromagnetic interference (EMI), and system complexity. By decoupling safety-critical from non-critical loads and reducing reliance on centralized distribution, the proposed architectures increase reliability and reduce complexity. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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11 pages, 408 KB

Open AccessProceeding Paper

Prevention of Contrail Formation in Hydrogen Fuel Cell Aircraft

by Raphael Gebhart and Franciscus L. J. van der Linden

Eng. Proc. 2026, 133(1), 117; https://doi.org/10.3390/engproc2026133117 - 11 May 2026

Viewed by 245

Abstract

Contrail emissions are aviation’s largest non-CO₂ contribution to global climate change. According to the Schmidt–Appleman criterion, potential future aircraft propulsion systems may enhance contrail formation relative to conventional engines through three mechanisms: (1) increased overall efficiency, (2) the use of hydrogen as [...] Read more.

Contrail emissions are aviation’s largest non-CO₂ contribution to global climate change. According to the Schmidt–Appleman criterion, potential future aircraft propulsion systems may enhance contrail formation relative to conventional engines through three mechanisms: (1) increased overall efficiency, (2) the use of hydrogen as fuel, and (3) external cooling in low-temperature fuel cell propulsion systems, which is the most critical factor. This paper presents the thermodynamic background and a system concept for contrail prevention applicable to conventional gas turbines, hydrogen combustion, and fuel cell propulsion systems. First, it is shown that fuel cell propulsion and hydrogen combustion exhibit equivalent thermodynamic contrail propensity when fuel cell exhaust is mixed with cooling air, analogous to core–bypass mixing in a conventional turbofan engines. Second, contrail mitigation via controlled condensation of exhaust water vapor is analyzed. It is demonstrated that the required cooling for LT-PEM fuel cell systems is 3–5 times lower than for turbofan engines, due to the already extensive thermal management in fuel cells. Since contrail avoidance is only necessary in ice supersaturated regions, a control scheme is proposed that limits condensation to the minimum required amount of water, thereby significantly reducing the overall drag impact. Avoiding contrail formation could provide a substantial climate benefit for future propulsion architectures. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 3300 KB

Open AccessProceeding Paper

Investigation of a Lightweight, Fire-Resistant Composite Battery Housing

by Leonard John, Arne Dekeyser, Lars-Fredrik Berg and Jens Tübke

Eng. Proc. 2026, 133(1), 118; https://doi.org/10.3390/engproc2026133118 - 11 May 2026

Viewed by 243

Abstract

The increasing electrification in aircraft propulsion and assistant systems necessitates innovative approaches in battery safety design. This work presents an investigation into a lightweight, fire-resistant composite battery housing tailored for modular battery applications with potential for high-volume production. Utilizing the promising thermal capabilities [...] Read more.

The increasing electrification in aircraft propulsion and assistant systems necessitates innovative approaches in battery safety design. This work presents an investigation into a lightweight, fire-resistant composite battery housing tailored for modular battery applications with potential for high-volume production. Utilizing the promising thermal capabilities of phenolic polymers, the housing parts were tailored around the identified fire protection baseline functions like bulkheads, outer walls and a venting concept consisting of burst valves and a venting channel. Component-level fire resistance tests were performed to close the testing gap between material and battery module-level testing. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 1313 KB

Open AccessProceeding Paper

Degradation-Aware Preliminary Sizing and Control Framework for Regional Aircraft Hybrid Fuel Cell–Battery Systems

by Paolo Aliberti, Emina Hadžialić, Marco Sorrentino and Helmut Kühnelt

Eng. Proc. 2026, 133(1), 119; https://doi.org/10.3390/engproc2026133119 - 11 May 2026

Viewed by 306

Abstract

The aviation sector is under increasing pressure to cut emissions, prompting strong interest in alternative propulsion systems. This study examines the potential of hybrid-electric aircraft relying on electrochemical energy storage and conversion units (EC-ESC), consisting of proton exchange membrane fuel cell systems coupled [...] Read more.

The aviation sector is under increasing pressure to cut emissions, prompting strong interest in alternative propulsion systems. This study examines the potential of hybrid-electric aircraft relying on electrochemical energy storage and conversion units (EC-ESC), consisting of proton exchange membrane fuel cell systems coupled with batteries. A design space exploration framework is proposed to size and control these systems for regional aircraft, treating fuel cell system nominal power and battery C-rate as key design variables, while also accounting for in-flight degradation. A flexible degradation-aware control strategy manages power sharing within the co-design strategy, which seeks a configuration minimizing the total EC-ESC equivalent mass. The entire procedure is designed versatilely enough to be applicable for the model-based design and energy management of EC-ESC units destined for several end uses, e.g., short/medium-haul, and long-haul aircraft or automotive. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 3591 KB

Open AccessProceeding Paper

Structural Model of a Very Light Airplane for Flutter Analyses Considering Pilot’s Effect on Flight Control System

by Robert Rogólski

Eng. Proc. 2026, 133(1), 120; https://doi.org/10.3390/engproc2026133120 - 12 May 2026

Viewed by 373

Abstract

This paper presents the application of a structural finite element model (FEM) of a light patrol aircraft for numerical flutter analysis. The thin-walled structure was developed using 2D shells and additional 1D beam elements. The virtual structure was supplemented with additional point elements [...] Read more.

This paper presents the application of a structural finite element model (FEM) of a light patrol aircraft for numerical flutter analysis. The thin-walled structure was developed using 2D shells and additional 1D beam elements. The virtual structure was supplemented with additional point elements imitating lumped masses of non-structural on-board components. The model was subjected to validation for qualities such as the mass distribution, its CG location, the structural stiffness of its airframe units, and the similarity of natural modes. The comparative analyses showed satisfactory consistency of the mass and stiffness properties of the FEM with the actual aircraft. Numerical flutter analysis was then performed with the MD Nastran for an integrated aeroelastic model consisting of the FEM and the simplified aerodynamic model. The critical velocities of basic flutter modes were determined. Using simplified kinematic models of flight control systems built into the FEM, an analysis of the sensitivity of control surface flutter due to the pilot’s influence was carried out. The stick grip and the support of control pedals with the pilot’s legs cause specific conditions related to the imposition of additional stiffness and mass on the control manipulators. These conditions directly affect the natural frequencies of control surface modes, which translates into a change in the critical flutter speed of the tail. For the established range of changes in stiffness and mass added to the stick and pedals, a series of analyses of natural vibrations and flutter were carried out. The influence of the change in the support conditions of control manipulators was illustrated in graphs. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 3747 KB

Open AccessProceeding Paper

System-of-Systems Guided Agent Communication and Collaboration in Aerial Wildfire Fighting

by Nikolaos Kalliatakis, Nabih Naeem and Prajwal Shiva Prakasha

Eng. Proc. 2026, 133(1), 121; https://doi.org/10.3390/engproc2026133121 - 12 May 2026

Viewed by 362

Abstract

The year 2025 saw the continuing trend of worsening wildfire severity and impact with escalating costs, burnt area and casualties. Subsequently, the capability for a rapid response operation is ever-growing, with aerial assets providing a key role in fulfilling this function. One problem [...] Read more.

The year 2025 saw the continuing trend of worsening wildfire severity and impact with escalating costs, burnt area and casualties. Subsequently, the capability for a rapid response operation is ever-growing, with aerial assets providing a key role in fulfilling this function. One problem with aerial suppression is the reliance on updated fire data and precise fire front information. Drones or other long-endurance vehicles are commonly used to assist in this matter, providing real-time data and imagery to the manned suppression bombers. The interactions and collaboration between these systems to achieve an improved wildfire suppression can be classified as a system-of-systems (SoS). To facilitate the design, interaction and communication of the surveillance drones and suppression aircraft, this paper develops a holistic framework using an agent-based simulation. The framework allows for the analysis of top-level drone design parameters and operational considerations with their communication and collaboration both with each other and the suppressive agents. The results showcase the importance of swath radius for better wildfire coverage and suppression, with radii less than 50 m preventing successful exploration of the fire. The importance of monitoring is highlighted by the observed greater reductions in burnt area and fleet energy usage when increasing the monitoring agent fleet size by 50% compared to the same increase in suppression agent fleet size. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 2791 KB

Open AccessProceeding Paper

Modeling and Flight Control Design of a Tilt-Wing Aircraft

by Pavel Hospodář and Robert Kulhánek

Eng. Proc. 2026, 133(1), 122; https://doi.org/10.3390/engproc2026133122 - 8 May 2026

Viewed by 206

Abstract

The main objective of this study is to analyze the dynamic of a tilt-wing aircraft. The dynamic model of the airplane considers non-linear aerodynamic characteristics as a function of wing angle, angle of attack, engine thrust and propeller advanced ratio. The effect of [...] Read more.

The main objective of this study is to analyze the dynamic of a tilt-wing aircraft. The dynamic model of the airplane considers non-linear aerodynamic characteristics as a function of wing angle, angle of attack, engine thrust and propeller advanced ratio. The effect of the propellers is modeled with respect to angular misalignment and interaction with the flow. Aerodynamic characteristics were obtained by a combination of CFD calculations and wind tunnel measurements. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 749 KB

Open AccessProceeding Paper

AI-Driven Non-Intrusive Aircraft Icing Detection Using Control Surface Sensors

by Gabriel Meisler, Ouassim Bara, Valérie Pommier-Budinger and Michael Bauerheim

Eng. Proc. 2026, 133(1), 123; https://doi.org/10.3390/engproc2026133123 - 13 May 2026

Viewed by 400

Abstract

Ice accretion can significantly degrade aircraft performance and hinder its operational capacities. The ability to detect and characterize ice formation in real time is paramount for enabling timely mitigation strategies. Existing solutions for in-flight ice detection are either physically intrusive, require dedicated hardware [...] Read more.

Ice accretion can significantly degrade aircraft performance and hinder its operational capacities. The ability to detect and characterize ice formation in real time is paramount for enabling timely mitigation strategies. Existing solutions for in-flight ice detection are either physically intrusive, require dedicated hardware that offers only localized readings, or are operationally impractical, depending on complex dynamic models or flight maneuvers unsuitable for standard commercial use. This context highlights a pertinent need for non-intrusive and robust methodologies for detecting actual ice accretion on aircraft. This article proposes a novel, non-intrusive Artificial Intelligence (AI)-driven methodology for real-time aircraft icing detection through the leveraging of data obtained from existing control surface sensors, namely from the aircraft’s ailerons. A supervised learning database was compiled from an Airbus aircraft flight test campaign. In this dataset, flight tests with artificial ice shapes model aircraft behavior under icing conditions, while ice-free tests performed under analogous flight domains represent the nominal scenario. A gradient boosting model was trained on the dataset and evaluated for its performance in accurately identifying the presence of ice accretion. The research shows that aileron sensor data provides sufficient discriminating capacity for in-flight ice accretion detection. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 480 KB

Open AccessProceeding Paper

Preliminary Design and Aircraft-Level Assessment of Piezoelectric Resonant Ice Protection Systems

by Pierre Bonhomme, Valérie Pommier-Budinger, Marc Budinger and Valerian Palanque

Eng. Proc. 2026, 133(1), 124; https://doi.org/10.3390/engproc2026133124 - 13 May 2026

Viewed by 317

Abstract

In the context of reducing air transport emissions, operational costs and transitioning to more electric aircraft, there is a growing need to develop new ice protection systems. Resonant electromechanical de-icing (EM-DI) systems take advantage of the resonance to amplify vibration amplitudes applied through [...] Read more.

In the context of reducing air transport emissions, operational costs and transitioning to more electric aircraft, there is a growing need to develop new ice protection systems. Resonant electromechanical de-icing (EM-DI) systems take advantage of the resonance to amplify vibration amplitudes applied through piezoelectric actuators, generating stress in the ice layer, enabling its removal. Research conducted on such systems has been focused on simplified or reduced models, and assessment of aircraft-level requirements has seldom been conducted. To overcome this shortcoming, this work proposes a pre-sizing methodology to evaluate the requirements (power consumption and piezoelectric mass) of EM-DI systems. After dividing the protected area into modules to cycle the aircraft de-icing, finite element models including the ice and the modules’ structure are developed. A modal analysis is performed to identify the extensional resonance modes that enable de-icing, and to calculate the necessary power and piezoelectric mass based on shedding criteria. The methodology is illustrated for two typical aircraft configurations: a jet engine single-aisle aircraft (SA) and a regional turboprop aircraft (TP). The results obtained for the EM-DI technology are promising, with apparent power estimates of as little as

2.7 kVA / m^{2}

for the SA and

1.28 kVA / m^{2}

for the TP. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 1730 KB

Open AccessProceeding Paper

Design of a 150-Seat, 2000 km-Range LH-Fuelled Jetliner

by Serhii Fil, Dmytro Berbenets, Andrii Khaustov, Oleksandra Urban and Oleksandr Bondarchuk

Eng. Proc. 2026, 133(1), 125; https://doi.org/10.3390/engproc2026133125 - 13 May 2026

Viewed by 274

Abstract

The use of hydrogen to power aircraft is considered as a promising direction for the future of air travel, as it enables CO₂-free operation and supports long-term climate goals. This study considers the feasibility of developing an aircraft with a gas [...] Read more.

The use of hydrogen to power aircraft is considered as a promising direction for the future of air travel, as it enables CO₂-free operation and supports long-term climate goals. This study considers the feasibility of developing an aircraft with a gas turbine power plant fuelled by liquid hydrogen. The aircraft is designed to carry 150 passengers over a distance of 2000 km, taking into account design features, technological challenges and operational advantages. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 620 KB

Open AccessProceeding Paper

Exploration of Strut-Braced High-Aspect-Ratio Wings: A Low-Fidelity Framework for Early Aircraft Design

by Ousmane Sy, Shantanu Sapre, Emmanuel Benard, Joseph Morlier and Yoann Le Lamer

Eng. Proc. 2026, 133(1), 126; https://doi.org/10.3390/engproc2026133126 - 13 May 2026

Viewed by 340

Abstract

As the aviation industry explores sustainable solutions for next-generation aircraft, the strut-braced wing (SBW) concept has emerged as a promising configuration, combining the enhanced aerodynamic efficiency of high-aspect-ratio (HAR) wings with a significant reduction in wing structural weight compared to conventional cantilever designs. [...] Read more.

As the aviation industry explores sustainable solutions for next-generation aircraft, the strut-braced wing (SBW) concept has emerged as a promising configuration, combining the enhanced aerodynamic efficiency of high-aspect-ratio (HAR) wings with a significant reduction in wing structural weight compared to conventional cantilever designs. Given the inherent aerodynamics and structural complexities of SBW concepts, developing innovative design methodologies is essential for fully investigating their potential. This work presents a low-fidelity, two-fold design methodology combining an overall aircraft design framework with finite element structural analysis. The approach enables overall aircraft design (OAD) sizing, exploration, and optimization of regional strut-braced wing configurations and assessing the effects of strut connections and jury on the wing’s static and buckling behavior. Trade-off and optimization studies based on the reference ATR-72 aircraft led to an optimal SBW configuration with an aspect ratio of 17.64 and a strut position ratio of 0.543, achieving reductions of about 24% in wing weight and 6.78% in fuel burn. The structural analysis of the optimized SBW indicates that a clamped–clamped strut connection provides superior buckling performance, and incorporating a jury strut effectively mitigates buckling issues while achieving approximately 20% wing weight reduction compared to the configuration without a jury. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 3294 KB

Open AccessProceeding Paper

Conceptualization and Numerical Optimization of an Energy-Efficient Electrothermal Ice Protection System for a Ducted Fan Propeller

by Cedric Obatolu, Rainer Bartels and Sebastian Neveling

Eng. Proc. 2026, 133(1), 127; https://doi.org/10.3390/engproc2026133127 - 13 May 2026

Viewed by 253

Abstract

In-flight icing poses a major risk to the flight safety and operational availability in aviation and particularly to small electric aircraft. One suitable ice protection system (IPS) concept is the electrothermal IPS; however, it often suffers from high power consumption if not properly [...] Read more.

In-flight icing poses a major risk to the flight safety and operational availability in aviation and particularly to small electric aircraft. One suitable ice protection system (IPS) concept is the electrothermal IPS; however, it often suffers from high power consumption if not properly optimized. Ducted fans are a promising propulsion technology for urban air mobility applications, but effective IPSs for ducted fan propellers have been rare thus far. This work thus presents a framework for the development of an energy-efficient electrothermal IPS for application in an off-the-shelf ducted fan propeller. Three-dimensional ice accretion simulations of the ducted fan’s assembly were performed under centrifugal loads using the commercial icing simulation code ANSYS^® FENSAP-ICE-TURBO^™ and the most critical areas for ice accretion on the ducted fan were identified. On the basis of the ice accretion simulations, the expected performance change of the ducted fan due to ice accretion on the rotor blades was evaluated. The placement and activation of the heating elements on the rotor blades were investigated and optimized using a one-dimensional electrothermal de-icing solver. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 12917 KB

Open AccessProceeding Paper

Simulation of the Passenger and Crew Exposure Resulting from the Thermal Runaway of Portable Electronic Devices in the Cabin and Cockpit

by Arnav Pathak, Victor Norrefeldt, Simon Holz, Jonas Pfaff, Sebastian Schopferer and Jürgen Kuder

Eng. Proc. 2026, 133(1), 128; https://doi.org/10.3390/engproc2026133128 - 7 May 2026

Viewed by 124

Abstract

Passengers routinely carry numerous Portable Electronic Devices (PEDs) powered by lithium-ion batteries, which present hazards when subjected to thermal runaway, including emission of toxic gases, smoke generation and potential fires. The LOKI-PED project investigates the severity of such events in aircraft cabins by [...] Read more.

Passengers routinely carry numerous Portable Electronic Devices (PEDs) powered by lithium-ion batteries, which present hazards when subjected to thermal runaway, including emission of toxic gases, smoke generation and potential fires. The LOKI-PED project investigates the severity of such events in aircraft cabins by experimentally characterizing combustion gases, validating a zonal cabin model and predicting exposure to harmful substances and smoke. PEDs were deliberately forced into thermal runaway in both burn chamber and A320 cabin mockup tests, enabling the quantification of emitted carbon dioxide and toxic compounds such as carbon monoxide, formaldehyde, hydrogen fluoride, and hydrogen chloride. These measurements were correlated to CO₂ peak concentrations, enabling a factor-based scaling approach for full-scale cabin simulations. A validated zonal model was then used to predict the temporal and spatial spread of gases and smoke in the cabin, cockpit and galley. Results show that while cabin ventilation generally keeps exposure below harmful levels, the cockpit and galley are significantly more vulnerable. The study highlights the importance of rapid crew response, limitations on PED battery capacities and operational mitigation strategies to ensure flight safety. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 1343 KB

Open AccessProceeding Paper

Multi-Orbit, Multi-Resolution Earth Observation for Intelligent Target Scheduling

by Antonio M. Mercado-Martínez, José Blanco-Chica, Antonio Jurado-Navas and Beatriz Soret

Eng. Proc. 2026, 133(1), 129; https://doi.org/10.3390/engproc2026133129 - 14 May 2026

Viewed by 284

Abstract

The growing demand for accurate and timely Earth observation (EO) data has made autonomous mission planning increasingly essential. In particular, data acquisition planning has gained attention in recent years with the advent of agile Earth observation satellites (AEOSs). This process involves two main [...] Read more.

The growing demand for accurate and timely Earth observation (EO) data has made autonomous mission planning increasingly essential. In particular, data acquisition planning has gained attention in recent years with the advent of agile Earth observation satellites (AEOSs). This process involves two main stages: target identification and observation scheduling. Traditionally, the former is performed manually, while the latter requires solving the agile Earth observation satellite scheduling problem (AEOSSP), a complex combinatorial optimization problem. In this work, we propose a constellation design comprising EO satellites deployed in medium Earth orbit (MEO) and low Earth orbit (LEO). The MEO satellites acquire low-resolution (LR) images for onboard target identification and subsequently schedule high-resolution (HR) observations by a set of LEO AEOSs. We adapt the AEOSSP to this multi-orbit context by explicitly considering communication constraints between MEO and LEO satellites and propose several heuristic solution methods. Among them, the quality-based greedy algorithm yields up to a 35.5% improve in observation profit in simple, low-conflict scenarios, while the structured heuristic algorithm proves the most robust, achieving up to a 21.5% increase in challenging schedules. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 450 KB

Open AccessProceeding Paper

Analyzing the Transparency and the Efficiency of Innovative Transparent Electrodes for Space Solar Cell Applications

by Francesco Cipriani, Maksim Shundalau and Patrizia Lamberti

Eng. Proc. 2026, 133(1), 130; https://doi.org/10.3390/engproc2026133130 - 13 May 2026

Viewed by 299

Abstract

In this work a study about the behavior of nanomaterial-based innovative transparent electrodes is presented, with a special focus on graphene, for space photovoltaic applications, in particular their transparency and the efficiency of the final device. The efficiency of a solar cell is [...] Read more.

In this work a study about the behavior of nanomaterial-based innovative transparent electrodes is presented, with a special focus on graphene, for space photovoltaic applications, in particular their transparency and the efficiency of the final device. The efficiency of a solar cell is characterized by referring to Power Conversion Efficiency and External/Internal Quantum Efficiency. Starting from the literature results, it is possible to observe that solar cells realized by innovative nanomaterial-based transparent electrodes show promising results in terms of efficiency in the Earth environment. It is known that the space environment is characterized by extreme conditions including high-energy radiation, strong temperature variations and high vacuum, which can damage materials and, consequentially, influence their performances. Among all the properties like transmittance and sheet resistance, which are the main requirements for a good transparent electrode, could change their value and, therefore, influence the efficiency of the solar cell adopting this kind of electrode. In this paper, a theoretical analysis on the effects of high-energy radiation on the transmittance of graphene layers is given, leading to the observation that in the UV frequency range, it shows a sharp fall. Moreover, the effect of temperature varying is studied by an theoretical analysis on the resistivity of the twisted graphene bilayer. It is possible to observe that, in this configuration, the system moves from a superconductor to a metal, according to temperature and twist angle. This represents a starting point to have good efficiency of solar devices in a space environment by keeping high the transparency of their electrodes. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 2818 KB

Open AccessProceeding Paper

COLOSSUS X-Challenge Student Competition-Exploring Solutions to Wildfire Fighting Using System of Systems Analysis

by Nikolaos Kalliatakis, Nabih Naeem and Prajwal Shiva Prakasha

Eng. Proc. 2026, 133(1), 131; https://doi.org/10.3390/engproc2026133131 - 14 May 2026

Cited by 2 | Viewed by 207

Abstract

Throughout history, wildfires have been prominent natural disasters that cause pollution, environmental damage and loss of lives. Local firefighting agencies and disaster response initiatives have typically managed to contain fires and limit damage to controllable levels. However, in recent times, due to climate [...] Read more.

Throughout history, wildfires have been prominent natural disasters that cause pollution, environmental damage and loss of lives. Local firefighting agencies and disaster response initiatives have typically managed to contain fires and limit damage to controllable levels. However, in recent times, due to climate change and human population growth, wildfire occurrences are becoming less predictable and result in greater cost and damage. Solutions employing new technologies and a more operations-oriented analysis, through system-of-systems (SoS), could be a promising way to combat further wildfire devastation. Designing new aircraft and strategies that can be used in human transport and firefighting is one of the goals of the COLOSSUS project. To enable international innovation, especially amongst young researchers, a student competition called the X-Challenge was released. This paper will deal with the overview of the challenge, breaking down its objectives, constraints, research contributions and outcomes. Following this paper, four different student teams will present their solutions, including innovative aircraft designs and SoS analysis methods. The knowledge gained, and successes and failures from the challenge, alongside outlook and recommendations for future challenges and SoS exploration, will be discussed in this paper. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 1550 KB

Open AccessProceeding Paper

A Holistic Approach to Wildfire Suppression Aircraft Fleet Design Using Operational Considerations and Evaluation Metrics

by Somrick Das Biswas, Jonah Gerardus, Adler Edsel, Ece Inanc, Nikolaos Kalliatakis, Nabih Naeem and Prajwal Shiva Prakasha

Eng. Proc. 2026, 133(1), 132; https://doi.org/10.3390/engproc2026133132 - 14 May 2026

Viewed by 190

Abstract

Wildfires are increasing in frequency, intensity, and duration, driving up suppression and damage costs and motivating a more coordinated use of aerial firefighting assets. Within this context, we extend the COLOSSUS Project’s X-Challenge System-of-Systems (SoS) simulation toolkit with an integrated aircraft sizing and [...] Read more.

Wildfires are increasing in frequency, intensity, and duration, driving up suppression and damage costs and motivating a more coordinated use of aerial firefighting assets. Within this context, we extend the COLOSSUS Project’s X-Challenge System-of-Systems (SoS) simulation toolkit with an integrated aircraft sizing and fleet assessment methodology that links conceptual aircraft design with tactic selection. Two platforms are sized under 2035 technology assumptions—a 2000 kg payload electric Vertical Takeoff Landing (eVTOL) and a 3000 kg payload Single Engine Air Tanker (SEAT) using physics-based performance and parametric cost models. A Design of Experiments (DoE) workflow coupled with the SoS toolkit evaluates mixed fleets and tactic assignments in three representative regions. Effectiveness is quantified via a weighted, normalized Measure of Effectiveness that aggregates burnt area, emissions, and cost metrics into a single scalar. Results show that acquisition cost dominates overall effectiveness and that location-specific fleet compositions can outperform a single fixed fleet without degrading suppression outcomes, motivating future work on adaptive, region-specific fleet design and sensitivity analyses. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 7560 KB

Open AccessProceeding Paper

Advancing Aerial Firefighting with Extended Operational Design Using Novel Strategies and Aircraft Concepts

by Shraddha Meda Sheshadri, Alex Mercier, Sarah Treece, Cristian Puebla Menne, Burak Bagdatli, Dimitri Mavris, Nikolaos Kalliatakis, Nabih Naeem and Prajwal Shiva Prakasha

Eng. Proc. 2026, 133(1), 133; https://doi.org/10.3390/engproc2026133133 - 14 May 2026

Viewed by 307

Abstract

Wildfire severity and frequency continue to increase worldwide, making effective aerial wildfire suppression a critical component of wildfire response. The COLOSSUS (Collaborative SoS) X-Challenge project established a system-of-systems (SoS) framework to design and evaluate next-generation firefighting capabilities and operational concepts. Building on this [...] Read more.

Wildfire severity and frequency continue to increase worldwide, making effective aerial wildfire suppression a critical component of wildfire response. The COLOSSUS (Collaborative SoS) X-Challenge project established a system-of-systems (SoS) framework to design and evaluate next-generation firefighting capabilities and operational concepts. Building on this framework, this paper presents a simulation environment that jointly evaluates conventional fixed-wing and electric vertical takeoff and landing (eVTOL) firefighting aircraft concepts by integrating aircraft design, fleet-level coordination, and mission-level tactics into the unified SoS assessment, enabling performance-driven design exploration. The framework was expanded with new tactics, including a ridge-based drop method, and a flanking selection algorithm that leverages road networks to establish anchor points and construct fire lines. Simulations across three representative wildfire locations (Salamis, Pyrenees, and Palisades) demonstrate that combining purpose-built aircraft with adaptive tactics can significantly improve mission effectiveness. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 896 KB

Open AccessProceeding Paper

OSIRIS—Generation of System-Specific Failure Cases Using Artificial Intelligence Based on Information from Abstract System Models

by Durga Sri Sharan Katabathula, Marcel Mischke, Sebastian Stoppa and Robin Frank

Eng. Proc. 2026, 133(1), 134; https://doi.org/10.3390/engproc2026133134 - 13 May 2026

Viewed by 210

Abstract

The importance of system safety elevates with the introduction of novel technologies in the aviation industry. With the rise of system complexity, regular safety practices include iterative workflows and heavy reliance on expert knowledge. For the development of modern, efficient aircraft systems, there [...] Read more.

The importance of system safety elevates with the introduction of novel technologies in the aviation industry. With the rise of system complexity, regular safety practices include iterative workflows and heavy reliance on expert knowledge. For the development of modern, efficient aircraft systems, there is a need for innovative approaches. This paper presents a tool, OSIRIS (operational safety and integrated risk analysis), that supports safety and risk analyses utilizing artificial intelligence (AI) concepts. Developed as a key safety feature within the HADES modeling framework, OSIRIS aligns with an architecture-based design approach for abstract system modeling, adhering to model-based systems engineering (MBSE) principles and standards. It currently aids safety engineers in formulating system failure cases consistent with functional hazard assessments (FHA), representing model-based safety assessment (MBSA) in compliance with SAE ARP4761A. The methodological concepts and their implementation in OSIRIS are demonstrated considering an abstract system model from aeronautical applications. The generated results were evaluated against the system context to confirm compliance with the FHA process required for certification. Further, the future work will explore refining OSIRIS’s capabilities and its application cases. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 1093 KB

Open AccessProceeding Paper

A Generic Tool for Multi-Fidelity MDO Under Uncertainty, with Application on Hybrid Electric Regional Aircraft

by Romain Espoeys, Matthias De Lozzo, Sylvain Béchet, Jean-Christophe Giret, François Gallard, Simone Mancini and Tim Klaproth

Eng. Proc. 2026, 133(1), 135; https://doi.org/10.3390/engproc2026133135 - 14 May 2026

Viewed by 255

Abstract

Modern engineering systems may require multidisciplinary design optimization (MDO) to account for the interactions between coupled physical phenomena. When uncertainties affect model parameters or design variables, these analyses must be extended to uncertainty-based MDO (UMDO), in which objectives and/or constraints are expressed as [...] Read more.

Modern engineering systems may require multidisciplinary design optimization (MDO) to account for the interactions between coupled physical phenomena. When uncertainties affect model parameters or design variables, these analyses must be extended to uncertainty-based MDO (UMDO), in which objectives and/or constraints are expressed as statistical quantities. However, solving UMDO problems is computationally demanding, especially when costly simulators are involved and the budget must be allocated among uncertainty quantification, multidisciplinary coupling resolution, and optimization. This article introduces a generic multi-fidelity strategy, implemented in the open-source GEMSEO framework, to efficiently address UMDO problems. A fidelity level is defined by a number of samples to estimate the statistics; the higher the fidelity, the higher the number. The strategy solves the UMDO problem for each level by using the solution of the previous level as an initial guess. Numerical experiments are deployed on a simplified overall aircraft design (OAD) problem and a hybrid electric regional aircraft (HERA) case. The results show that, with two fidelity levels, restricting samples and iterations at the low-fidelity stage improves overall performance. This allows the multi-fidelity framework to significantly reduce computational cost compared with single-fidelity approaches (up to 45% for OAD and 40% for HERA) while maintaining or improving solution accuracy. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 5184 KB

Open AccessProceeding Paper

AFP Defect Characterisation: The Importance of Testing Scale and Defect Interaction

by Leith Afilal, Daniël Peeters, John-Alan Pascoe and René Alderliesten

Eng. Proc. 2026, 133(1), 136; https://doi.org/10.3390/engproc2026133136 - 14 May 2026

Viewed by 276

Abstract

Automated Fibre Placement (AFP) enables the rapid and precise manufacturing of composite structures, but the process inherently introduces defects such as gaps and overlaps, which can significantly affect structural performance. Most existing studies assess these effects through coupon-scale testing; however, such an approach [...] Read more.

Automated Fibre Placement (AFP) enables the rapid and precise manufacturing of composite structures, but the process inherently introduces defects such as gaps and overlaps, which can significantly affect structural performance. Most existing studies assess these effects through coupon-scale testing; however, such an approach may not capture the influence of structural scale and defect interaction. This study investigates the combined effects of specimen dimension and defect configuration on stiffness, strength, and damage evolution. Two characteristic defect patterns were examined—aligned and staggered gaps—across two specimen dimensions. The results reveal different scaling trends for strength and stiffness between the two configurations. They also show the influence of specimen size on damage initiation and delamination behaviour. The findings demonstrate that coupon-based knockdowns cannot be directly extrapolated to structural components without accounting for defect interaction and scale effects. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 1906 KB

Open AccessProceeding Paper

Estimation of Costs and Environmental Impacts of a Cryogenic H2 Tank

by Christian Bülow, Karina Kroos and Steffen Opitz

Eng. Proc. 2026, 133(1), 137; https://doi.org/10.3390/engproc2026133137 - 14 May 2026

Viewed by 362

Abstract

Aviation faces major challenges in meeting EU decarbonization goals, and liquid hydrogen is a promising alternative fuel. This study evaluates the environmental and economic performance of composite liquid hydrogen tanks for aircraft. A combined Life Cycle Assessment (LCA) and Life Cycle Costing (LCC) [...] Read more.

Aviation faces major challenges in meeting EU decarbonization goals, and liquid hydrogen is a promising alternative fuel. This study evaluates the environmental and economic performance of composite liquid hydrogen tanks for aircraft. A combined Life Cycle Assessment (LCA) and Life Cycle Costing (LCC) approach was applied to two tank configurations from the HyStor and TACOMA projects, based on Automated Fiber Placement (AFP) manufacturing data. Results show that tooling dominates prototype costs but becomes negligible in serial production, enabling reductions of up to 89%. The AFP process and carbon-fiber prepreg material are the main environmental impact drivers. Despite these, the lightweight composite design can offset its production footprint through operational fuel savings. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 1783 KB

Open AccessProceeding Paper

CFD Modelling of Di-Phasic Refrigerant Inside an Aircraft Skin Heat Exchanger as a Condenser for Hybrid-Electric Regional Aircraft

by Iván González-Nieves, Andrés Felgueroso-Rodríguez, Miguel Díaz-Barja and Jorge García-Rodríguez

Eng. Proc. 2026, 133(1), 138; https://doi.org/10.3390/engproc2026133138 - 13 May 2026

Viewed by 331

Abstract

The development of future electrical aircraft, such as the Hybrid-Electric Regional Aircraft (HERA) platform, presents challenging cooling demands due to the heat generated by electric powerplants, fuel cells and power electronics. Traditional heat exchangers in ram air channels may not be sufficient, necessitating [...] Read more.

The development of future electrical aircraft, such as the Hybrid-Electric Regional Aircraft (HERA) platform, presents challenging cooling demands due to the heat generated by electric powerplants, fuel cells and power electronics. Traditional heat exchangers in ram air channels may not be sufficient, necessitating alternative solutions like Skin Heat Exchangers (SHXs) to enhance heat transfer and reduce parasitic drag. Aircraft drag reduction and efficiency increase are expected with the integration of SHXs in two-phase cooling systems. This study employs Computational Fluid Dynamics (CFD) models, specifically the Volume of Fluid (VOF) multiphase model together with the Lee model, to simulate the condensation process of two Hydrofluoroolefin (HFO) refrigerants in SHX channels (R1233zd(E) and R1234yf). An analytical model based on empirical equations is used to preliminarily correlate and validate the CFD results, showing deviations below 15%. The simulations reveal distinct flow behaviours for each refrigerant, influenced by the differences in liquid and gas densities. The study also establishes a basis for understanding and selecting the inverse of the relaxation time coefficient, which is crucial for multiphase CFD modelling. The CFD models used in this article could be of great importance for future SHX design optimization. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 338 KB

Open AccessProceeding Paper

Evaluation of One Engine Inoperative Scenarios for Electrified Multi-Engine Aircraft from the Certification Perspective

by Robin Frank and Stephan Rempe

Eng. Proc. 2026, 133(1), 139; https://doi.org/10.3390/engproc2026133139 - 13 May 2026

Viewed by 187

Abstract

One approach to make the aviation sector climate-compatible is to minimize greenhouse gas emissions by employing electric and hybrid electric propulsion system concepts. The introduction of novel technologies introduces novel failure modes and consequently effects of failure conditions on the aircraft. This study [...] Read more.

One approach to make the aviation sector climate-compatible is to minimize greenhouse gas emissions by employing electric and hybrid electric propulsion system concepts. The introduction of novel technologies introduces novel failure modes and consequently effects of failure conditions on the aircraft. This study examines the safety of distributed electrified aircraft propulsion systems and evaluates individual failure scenarios in the context of the relevant certification requirements. A comparison of the functional architectures of legacy and Electric Hybrid Propulsion Systems (EHPSs) is conducted and the existing aircraft-level requirements, that are based on experience with conventional propulsion systems, are assessed for their applicability to the certification of novel propulsion systems. Subsequently the relevant safety items from these requirements are identified in the context of a critical loss of thrust scenario. Analysis methods are assigned to these safety items in order to prove the compliance of the novel systems with the legacy certification documentation. This results in a validation concept for EHPS at the aircraft level in the context of a critical loss of thrust. In particular, the distribution of individual subsystems and components throughout the aircraft leads to reduced isolation of the respective propulsion systems and thus potential safety-critical interactions with adjacent systems. The analysis demonstrates that the use of distributed propulsion systems increases the risk of multiple failures of redundant systems and cascading failure propagation, highlighting the need to develop targeted means of prevention and the mitigation of failure conditions for these systems. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 2605 KB

Open AccessProceeding Paper

Comparative Study of CFD Solvers in the Aerodynamic Analysis of a Miniature Unmanned Aerial Vehicle

by Borys Syta, Paweł Czerniszewski, Stanisław Kachel and Robert Rogólski

Eng. Proc. 2026, 133(1), 140; https://doi.org/10.3390/engproc2026133140 - 14 May 2026

Viewed by 314

Abstract

This study is part of a research program at the Military University of Technology aimed at creating a tool to support light aircraft design at the conceptual stage. The project seeks to develop a method for optimizing a conceptual model of a small [...] Read more.

This study is part of a research program at the Military University of Technology aimed at creating a tool to support light aircraft design at the conceptual stage. The project seeks to develop a method for optimizing a conceptual model of a small manned or unmanned aircraft based on specific mission requirements and aerodynamics. Recognizing the need for a reliable CFD analysis tool in this process, the focus was placed on investigating popular tools utilizing panel methods. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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6 pages, 2682 KB

Open AccessProceeding Paper

Exoskeleton-Based Microgravity Simulation for Astronaut Training

by Mathias Trampler, Marc Tabie, Julia Habenicht and Elsa Andrea Kirchner

Eng. Proc. 2026, 133(1), 141; https://doi.org/10.3390/engproc2026133141 - 14 May 2026

Viewed by 633

Abstract

Performance of fine motor tasks during the initial phase of space missions is often compromised by the adaptation to microgravity. Since traditional Earth-based training methods are limited and struggle to replicate these conditions without strict time constraints, we propose the training of fine [...] Read more.

Performance of fine motor tasks during the initial phase of space missions is often compromised by the adaptation to microgravity. Since traditional Earth-based training methods are limited and struggle to replicate these conditions without strict time constraints, we propose the training of fine motor tasks with simulated microgravity on earth using an upper limb active exoskeleton. With a model-based control approach, we create a state of microgravity for both arms. To enable realistic microgravity simulation, a suitable model of the human arm is needed. We developed a method to identify the parameters of an arm model by leveraging the computational graph of the inverse dynamics algorithm and utilizing gradient descent to minimize the discrepancy between model and reality. Preliminary data from parabolic flights show that subjects trained with our exoskeleton achieved higher accuracy in a fine motor task during their first exposure to real microgravity compared to untrained subjects. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 5794 KB

Open AccessProceeding Paper

Thermodynamic Pathways Towards Sustainable Aviation—A Synergistic Research Perspective

by Pascal Köhler, Marius Nozinski, Felix Müller, Lauris Richter, Jonas Hesse, Cagatay N. Dagli, Markus Richter and Stephan Kabelac

Eng. Proc. 2026, 133(1), 142; https://doi.org/10.3390/engproc2026133142 - 14 May 2026

Viewed by 407

Abstract

Decarbonizing aviation requires innovative propulsion technologies and thermodynamic systems that enable efficient, sustainable energy conversion. The Institute of Thermodynamics at Leibniz University Hannover is engaged in several interdisciplinary research projects focusing on advanced, low-emission aircraft propulsion solutions. Two major areas of research are [...] Read more.

Decarbonizing aviation requires innovative propulsion technologies and thermodynamic systems that enable efficient, sustainable energy conversion. The Institute of Thermodynamics at Leibniz University Hannover is engaged in several interdisciplinary research projects focusing on advanced, low-emission aircraft propulsion solutions. Two major areas of research are presented: high-temperature solid oxide fuel cells (SOFCs) for hybrid aircraft propulsion and thermal management systems for proton exchange membrane (PEM) fuel cell propulsion, including additively manufactured heat exchangers for aviation applications. These research activities contribute to the technological foundation of more climate-friendly aviation. Concepts are investigated through numerical simulations, experiments, and system-level analyses to develop future propulsion solutions. This paper provides a comprehensive overview of the Institute of Thermodynamics’ ongoing research and the synergies between its various fields. It offers insights into the challenges and opportunities of more sustainable aviation technologies. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 2266 KB

Open AccessProceeding Paper

Thermal Management Concepts: Application Examples Using a Convective Heat Transfer Measurement Sensor

by Arnav Pathak, Victor Norrefeldt and Marie Pschirer

Eng. Proc. 2026, 133(1), 143; https://doi.org/10.3390/engproc2026133143 - 14 May 2026

Viewed by 316

Abstract

The shift toward more electric aircraft has intensified thermal management challenges due to increased heat load from electrical actuators, power electronics and energy storage systems concentrated within confined fuselage bays. A Conventional Environmental Control System (ECS) alone is not sufficient to dissipate such [...] Read more.

The shift toward more electric aircraft has intensified thermal management challenges due to increased heat load from electrical actuators, power electronics and energy storage systems concentrated within confined fuselage bays. A Conventional Environmental Control System (ECS) alone is not sufficient to dissipate such high localized heat loads. This creates the need for innovative heat dissipation and heat reuse strategies. This paper presents two thermal management concepts evaluated at the Fraunhofer Flight Test Facility. The first, developed in the ORCHESTRA project, integrates a bilge skin heat exchanger with modified ventilation to dissipate elevated heat loads. The second, under investigation in the TheMa4HERA project, focuses on reusing avionics heat to warm the FWD cargo hold, thereby reducing ECS power demand. Both concepts depend on convective heat exchange, characterized using Fraunhofer’s Convective Heat Transfer Meter (CHM) to determine key heat transfer coefficients. In parallel, an aircraft-level thermal model was developed, validated against experimental data and subsequently used for virtual demonstration of a ground test scenario. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 2027 KB

Open AccessProceeding Paper

Using Bayesian Networks for Fault Diagnosis: An Application to a Small Unmanned Aerial Vehicle

by Alexander Athanasios Kamtsiuris, Ann-Kathrin Koschlik, Florian Raddatz and Gerko Wende

Eng. Proc. 2026, 133(1), 144; https://doi.org/10.3390/engproc2026133144 - 13 May 2026

Viewed by 197

Abstract

In modern complex engineering systems, making well-informed maintenance decisions requires processing multiple sources of information. This is particularly crucial in autonomous operations, where systems must have the capability to automatically perform accurate diagnostic analyses to ensure safe and sustainable functioning. By leveraging Bayesian [...] Read more.

In modern complex engineering systems, making well-informed maintenance decisions requires processing multiple sources of information. This is particularly crucial in autonomous operations, where systems must have the capability to automatically perform accurate diagnostic analyses to ensure safe and sustainable functioning. By leveraging Bayesian networks, data from various sensors can be integrated to infer the likelihood of different faults and failure modes. This approach not only identifies potential issues but also provides a measure of confidence in the diagnosis. This work investigates the use of Bayesian networks (BNs) for fault diagnosis in small unmanned aerial vehicles (UAVs). A diagnostic BN specifically designed for a small UAV is introduced and its functionality is demonstrated. In summary, Bayesian networks provide a robust method for supporting diagnostics in complex systems. They enhance the ability to make informed maintenance decisions, thereby ensuring the reliability and safety of advanced engineering systems. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 525 KB

Open AccessProceeding Paper

Water-Evaporation Supported Fuel-Cell Cooling Architectures for Aircraft

by Raphael Gebhart, Luis Weber and Franciscus L. J. van der Linden

Eng. Proc. 2026, 133(1), 145; https://doi.org/10.3390/engproc2026133145 - 13 May 2026

Viewed by 253

Abstract

The thermal management-induced drag of conventional ram-air cooling systems for low-temperature fuel-cell propulsion can account for roughly 20% to 25% of total drag in fuel-cell aircraft concepts, while its mass and power impact at the overall aircraft level are far less significant. This [...] Read more.

The thermal management-induced drag of conventional ram-air cooling systems for low-temperature fuel-cell propulsion can account for roughly 20% to 25% of total drag in fuel-cell aircraft concepts, while its mass and power impact at the overall aircraft level are far less significant. This drag penalty can severely reduce efficiency, especially when additional parallel power sources for takeoff such as gas turbine engines are undesirable. To address this, we propose augmenting low- and medium-temperature fuel-cell cooling with an auxiliary water-evaporation system. This mechanism is used only when needed, primarily during takeoff in hot ambient conditions, while the ram-air system can be downsized to meet cruise requirements. Water evaporation can achieve coefficients of performance of 50 to 100, while reducing the required mass flow by two orders of magnitude. It provides a heat-rejection energy density of approximately 670

Wh

/

k g

, far exceeding that of state-of-the-art high-power-density batteries. Furthermore, the resulting vapor can be vented overboard, and the system is expected to outperform batteries in reliability, durability, and environmental impact. The paper introduces several architectures for integrating water-evaporation cooling into aircraft systems and discusses their respective advantages, limitations, and implications for overall aircraft performance. Initial results indicate that enabling evaporative cooling can significantly reduce the required ram-air channel size and drag, offering a promising pathway to more efficient fuel-cell-powered aircraft. In the EU project TheMa4HERA, aircraft-level design trades and scaled experimental validation for aviation applications of water evaporation are planned in 2026. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 944 KB

Open AccessProceeding Paper

OLIVIA: Enabling Joint Cognitive Work in Aircraft Divert Scenario Through Operational Intentions

by Ricardo J. N. dos Reis, Anaisa Villani, Silvio Romero Oliveira do Nascimento Filho, Charles Dormoy, Jaime Diaz-Pineda and Théodore Letouzé

Eng. Proc. 2026, 133(1), 146; https://doi.org/10.3390/engproc2026133146 - 14 May 2026

Viewed by 197

Abstract

OLIVIA (OperationaL Intentions adVIser for Aviation) was developed in the HAIKU project. It is a flight deck tool providing support to mission-level decisions in complex situations by assessing and prioritizing route options according to operational intentions. [...] Read more.

OLIVIA (OperationaL Intentions adVIser for Aviation) was developed in the HAIKU project. It is a flight deck tool providing support to mission-level decisions in complex situations by assessing and prioritizing route options according to operational intentions. It uses Artificial Intelligence to translate (1) operational intentions from pilots to route generation and optimization inputs and (2) route proposal KPIs into operational intention assessments. This paper reports on the final development of OLIVIA, the results from the human-in-the-loop experiments, and insights and recommendations regarding the development of similar assistants for the flight deck. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 213 KB

Open AccessProceeding Paper

The Effectiveness of Employing AS9100D on the Processes of Aviation, Space, and Defense Organizations in Terms of Cost, Safety, Quality, and Logistics

by Bahtiyar Eren and Ahmet Bengöz

Eng. Proc. 2026, 133(1), 147; https://doi.org/10.3390/engproc2026133147 - 14 May 2026

Viewed by 304

Abstract

Although AS9100D is essential in the aviation industry, its impact on cost, safety, quality, and logistics remains uncertain. This study surveyed AS9100D-certified IAQG organizations across five domains: cost, process effectiveness, product safety, on-time delivery, and customer satisfaction. Using 25 Likert-scale questions and binomial [...] Read more.

Although AS9100D is essential in the aviation industry, its impact on cost, safety, quality, and logistics remains uncertain. This study surveyed AS9100D-certified IAQG organizations across five domains: cost, process effectiveness, product safety, on-time delivery, and customer satisfaction. Using 25 Likert-scale questions and binomial tests, 40% reported a significant impact, 30% a moderate impact, 21% a low impact, and 9% lacked data. While all domains influenced processes, only 11 of 25 items showed strong significance individually. The findings highlight where resources should be prioritized to strengthen core activities and guide improvements toward AS9100E. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

8 pages, 949 KB

Open AccessProceeding Paper

Hydrophobic and Icephobic Epoxy Coatings Containing Silane Agents and Functional Additives

by Viviana Nebbioso, Aurelio Bifulco, Claudio Imparato, Liberata Guadagno, Marialuigia Raimondo, Jessica Passaro, Pietro Russo, Giuseppe Vitiello, Giulio Malucelli, Antonio Aronne and Amedeo Amoresano

Eng. Proc. 2026, 133(1), 148; https://doi.org/10.3390/engproc2026133148 - 14 May 2026

Viewed by 356

Abstract

Ice accumulation on aircraft surfaces severely affects aerodynamic performance by increasing drag and reducing lift, leading to stall conditions. Conventional thermal and pneumatic anti-/de-icing systems, although widely used, have some disadvantages, including high cost, inefficiency, and environmental unsustainability. Hydrophobic and icephobic coatings have [...] Read more.

Ice accumulation on aircraft surfaces severely affects aerodynamic performance by increasing drag and reducing lift, leading to stall conditions. Conventional thermal and pneumatic anti-/de-icing systems, although widely used, have some disadvantages, including high cost, inefficiency, and environmental unsustainability. Hydrophobic and icephobic coatings have emerged as a promising alternative to reduce ice adhesion and delay ice formation. This paper reviews the use of silane agents in epoxy-based coatings, incorporating functional additives such as natural fibers, quantum dots, and nanoparticles, to enhance hydrophobicity. Results demonstrated that the combination of silanes and functional additives affects surface features and wettability, improving hydrophobicity. These case studies show the potential of this approach in the development of coatings for advanced aircraft ice-protection applications. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 763 KB

Open AccessProceeding Paper

Material Composition Based Aerostructural Optimization of High-Aspect Ratio Wings for Reducing Life-Cycle Environmental Impact

by Shantanu Sapre, Ousmane Sy, Joseph Morlier, Christian Gogu and Emmanuel Benard

Eng. Proc. 2026, 133(1), 149; https://doi.org/10.3390/engproc2026133149 - 15 May 2026

Viewed by 316

Abstract

The rapid growth of global air traffic places the aviation industry under dual pressure: meeting increasing demand for aircraft while substantially reducing life-cycle environmental impacts. As advancements in aerodynamics, propulsion, and the adoption of lightweight composite materials continue to reduce operational fuel burn, [...] Read more.

The rapid growth of global air traffic places the aviation industry under dual pressure: meeting increasing demand for aircraft while substantially reducing life-cycle environmental impacts. As advancements in aerodynamics, propulsion, and the adoption of lightweight composite materials continue to reduce operational fuel burn, the relative significance of manufacturing and End-of-Life phases is expected to increase. This study develops a low-fidelity aerostructural optimization framework for high aspect ratio wings that integrates life-cycle considerations into early-stage material selection. Using aluminum and carbon fiber reinforced polymers (CFRP) as reference materials, the framework quantifies trade-offs in mass savings, fuel burn, and CO₂ equivalent emissions across production, operations, and disposal phases. Results show that while CFRP offers substantial benefits in structural efficiency and operational emissions, aluminum performs more favorably in End-of-Life scenarios due to its high recyclability. The study further evaluates the potential of Sustainable Aviation Fuel (SAF) blending as a complementary decarbonization lever, revealing that moderate SAF adoption can offset part of the operational advantage of CFRP. Overall, this work demonstrates the importance of coupling material choice with life-cycle assessment in aerostructural design and outlines a pathway toward multi-objective optimization frameworks that balance performance with environmental sustainability. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 20906 KB

Open AccessProceeding Paper

Vibroacoustic Optimization of the Airframe Using Energy Harvesting Resonators: An Experimental and Numerical Approach

by Florian Mock, Lukas Kettenhofen, Daniel Alboldt and Kai-Uwe Schröder

Eng. Proc. 2026, 133(1), 150; https://doi.org/10.3390/engproc2026133150 - 15 May 2026

Viewed by 209

Abstract

The open fan as a highly efficient propulsion concept is a promising approach to reduce climate-damaging emissions in aviation. However, the increased vibroacoustic emissions of the fan resulting from the open design lead to elevated cabin noise. Energy harvesting resonators can be used [...] Read more.

The open fan as a highly efficient propulsion concept is a promising approach to reduce climate-damaging emissions in aviation. However, the increased vibroacoustic emissions of the fan resulting from the open design lead to elevated cabin noise. Energy harvesting resonators can be used to leverage the piezoelectric effect and to attenuate structural vibrations caused by the acoustic loading simultaneously. To evaluate the potential of a specific configuration of energy harvesting resonators, an investigation of the dynamic interaction between the airframe and the resonators is necessary. Therefore, the eigenmodes and eigenfrequencies of a representative stiffened plate are determined experimentally using modal analysis via laser scanning vibrometry. A finite element model of the stiffened plate with the resonator idealized as a mass–spring element is implemented. The stiffness of this simplified resonator model is calibrated by correlating simulated with experimental results following a model updating approach. Finally, an optimization framework designed to determine the optimal quantity and placement of resonators using the experimentally validated model and representative loads is implemented to maximize both vibroacoustic attenuation and energy harvesting efficiency. The resulting framework serves as a generalized optimization tool capable of systematically optimizing the resonator configuration based on airframe geometry and specified vibroacoustic loading scenarios. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 7874 KB

Open AccessProceeding Paper

Engine-Airframe Integration—From Froude Theorem to Numerical Flow Simulation

by Jan Hartmann and Stephan Staudacher

Eng. Proc. 2026, 133(1), 151; https://doi.org/10.3390/engproc2026133151 - 15 May 2026

Viewed by 127

Abstract

The reduction of the overall emissions of the aviation sector require the improvement of the overall aircraft efficiency. In the current aircraft design, the airframe and the propulsion system are designed separately and expected to reach limits for the overall aircraft efficiency. The [...] Read more.

The reduction of the overall emissions of the aviation sector require the improvement of the overall aircraft efficiency. In the current aircraft design, the airframe and the propulsion system are designed separately and expected to reach limits for the overall aircraft efficiency. The integration of the engine into the airframe and the implementation of boundary layer ingestion (BLI) is a promising concept to improve the overall aircraft efficiency. However, this integration alters the engine intake flow and influences the intake characteristics significantly. In this study, numerical simulations as well as water channel experiments are performed to get insights into the challenges that occur due to BLI. An actuator disc simulation is performed to validate the Froude theorem with the numerical simulations. The water channel experiments are used to perform BLI experiments for different fuselage contours and operation points of the engine. In the last step, numerical simulations of the flow into an under-wing intake are compared to an BLI intake. The studies show that the BLI can cause flow separation in different regions of the intake and the intake characteristic is altered. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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10 pages, 5928 KB

Open AccessProceeding Paper

Artificial Intelligence for Planetary Exploration: Lessons Learned from a Decade of Analog Field Tests

by Steffen Planthaber, Udo Frese, Wiebke Brinkmann, Raúl Domínguez, Melvin Laux, Mehmed Yüksel, Andreas Bresser and Frank Kirchner

Eng. Proc. 2026, 133(1), 152; https://doi.org/10.3390/engproc2026133152 - 15 May 2026

Viewed by 471

Abstract

Celestial bodies in the solar system have long been of particular interest in space science. Some questions, e.g., those concerning the origin of life, require on-site landing and exploration. Due to signal delay, some degree of autonomy provided by artificial intelligence (AI) is [...] Read more.

Celestial bodies in the solar system have long been of particular interest in space science. Some questions, e.g., those concerning the origin of life, require on-site landing and exploration. Due to signal delay, some degree of autonomy provided by artificial intelligence (AI) is needed. Motivated by planetary exploration missions, the German Research Center for Artificial Intelligence (DFKI) has developed methods for (semi-)autonomous control of vehicles and robots on extraterrestrial bodies. To validate the software, we conduct extensive field tests in terrestrial analog environments. Field tests can be seen as an intermediate step between development and laboratory testing and real-world deployment in an extraterrestrial environment. This paper describes the challenges of testing AI and robotic systems in analog environments, with a focus on the additional dependencies that arise during the preparation and execution of such field tests. The robots and software tested in these field tests are based on more than a decade of development across various projects, covering a wide range of AI systems and applications, including geometric planning, probabilistic perception, deep learning, and robot construction for open challenges in planetary exploration. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 3182 KB

Open AccessProceeding Paper

Self-Healing Thermosetting Load-Bearing Resins: Morphological and Mechanical Properties

by Marialuigia Raimondo, Elisa Calabrese, Luigi Vertuccio and Liberata Guadagno

Eng. Proc. 2026, 133(1), 153; https://doi.org/10.3390/engproc2026133153 - 18 May 2026

Viewed by 165

Abstract

This paper focuses on developing reinforced self-healing supramolecular resins that meet both functional and structural needs for industrial use. The formulated advanced nanocomposites are made from compounds that allow for reversible self-healing interactions. The self-healing molecules bond with the toughened epoxy matrix using [...] Read more.

This paper focuses on developing reinforced self-healing supramolecular resins that meet both functional and structural needs for industrial use. The formulated advanced nanocomposites are made from compounds that allow for reversible self-healing interactions. The self-healing molecules bond with the toughened epoxy matrix using hydrogen bonding. To enhance the epoxy’s typical insulating properties, electrically conductive carbon nanotubes (CNTs) were added to achieve an electrical percolation threshold (EPT) with a low amount of nanofiller. This study found that self-healing efficiency can reach nearly 99%. The addition of healing compounds significantly raises the glass transition temperature to over 200 °C. Tunneling Atomic Force Microscopy (TUNA), which is an innovative tool for correlating local topography with electrical properties, reveals the structural properties and compatibility of these materials, mapping conductive pathways at the micro- and nanoscale. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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10 pages, 12699 KB

Open AccessProceeding Paper

An Approach to Predict Fatigue Delamination Propagation in Curved Composite Laminates Under Non-Constant Mixed-Mode Conditions: Experiments and Simulation Correlation

by Carlos Mallor, Mario Sanchez, Andrea Calvo, Susana Calvo, Hubert R.-Wasik and Federico Martin de la Escalera

Eng. Proc. 2026, 133(1), 154; https://doi.org/10.3390/engproc2026133154 - 19 May 2026

Viewed by 294

Abstract

Composite laminates experience static and fatigue delamination, presenting significant challenges for failure prediction. This is critical in curved composites, where delamination behavior is complex to predict. In this study, fatigue tests were conducted on curved composite laminates under non-constant mixed-mode conditions. The testing [...] Read more.

Composite laminates experience static and fatigue delamination, presenting significant challenges for failure prediction. This is critical in curved composites, where delamination behavior is complex to predict. In this study, fatigue tests were conducted on curved composite laminates under non-constant mixed-mode conditions. The testing setup involved a four-point bending test using L-shaped, unidirectional carbon-fiber-reinforced polymer curved beam specimens. A Teflon insert placed at the bend was used to initiate delamination. Experimental data acquisition included digital image correlation (DIC) to monitor delamination length during testing. This is important since it enhances subsequent model correlation. A virtual crack closure technique (VCCT)-based method for simulating fatigue-driven delamination under variable mixed-mode conditions was validated against experiments. Delamination growth was modeled using a Paris-like power–law relationship based on the strain energy release rate. The approach was implemented in Abaqus as a user subroutine, incorporating load ratio and mode mixity effects through VCCT-based mode separation. This study demonstrates accurate fatigue delamination prediction and highlights the role of optical measurements in experiments. The model improves our understanding of delamination propagation under varying mode mixity and contributes to structural integrity analysis. The results show how mode mixity influences delamination, impacting the performance and lifecycle of composite structures. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 2195 KB

Open AccessProceeding Paper

HADES—A Framework for Hierarchical Architecture Design for Engineering Systems

by Marcel Mischke, Durga Sri Sharan Katabathula and Leonardo Francelino Melico

Eng. Proc. 2026, 133(1), 155; https://doi.org/10.3390/engproc2026133155 - 19 May 2026

Cited by 1 | Viewed by 136

Abstract

The increasing complexity of technical aeronautical systems requires novel and consistent methods to manage a wide range of dependencies and disciplines. Model-based systems engineering addresses this need by providing a systematic, model-based approach to support development, analysis, and validation within a systemic context. [...] Read more.

The increasing complexity of technical aeronautical systems requires novel and consistent methods to manage a wide range of dependencies and disciplines. Model-based systems engineering addresses this need by providing a systematic, model-based approach to support development, analysis, and validation within a systemic context. This paper presents the strategy behind HADES, an abstract modelling framework that enables a well-structured and generic description of complex systems. The system information is clearly defined in a hierarchical structure and supported by the use of various viewpoints that consistently integrate different systemic aspects. HADES extends the classic RFLP viewpoints with an operational view. In addition, system safety is methodically embedded in the model-based development process from the initial stages as a key aspect. HADES thus supports a traceable development strategy for aeronautical systems according to SAE ARP4754B. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 2049 KB

Open AccessProceeding Paper

AI Assistant for Rapid Modelling and Design of Aircraft

by Sergio Jimeno Altelarrea, Utkarsh Gupta and Atif Riaz

Eng. Proc. 2026, 133(1), 156; https://doi.org/10.3390/engproc2026133156 - 19 May 2026

Viewed by 189

Abstract

Collaborative aircraft design environments face significant challenges in intuitive geometry manipulation and tool integration. This research develops an AI-assisted interface using the Model Context Protocol (MCP) to bridge natural language commands with established aerospace tools. The approach integrates large language models with three [...] Read more.

Collaborative aircraft design environments face significant challenges in intuitive geometry manipulation and tool integration. This research develops an AI-assisted interface using the Model Context Protocol (MCP) to bridge natural language commands with established aerospace tools. The approach integrates large language models with three specialized applications for optimization, visualization, and aircraft geometry modification. Results demonstrate successful implementation, enabling designers to accomplish complex tasks such as multi-objective optimization and empennage reconfiguration through conversational prompts. While occasional AI misinterpretations required prompt refinement, the system proved effective at translating intent into precise tool operations. The study concludes that MCP provides a viable framework for creating intuitive design interfaces while maintaining accuracy via integration with domain-specific computational methods. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 487 KB

Open AccessProceeding Paper

Integrated UAS–Satellite Communications in 6G: An Overview

by Anastasia Yastrebova-Castillo, Sami Tocklin, Heikki Kokkinen, Muhammad Asad Ullah, Marko Höyhtyä and Mikko Majanen

Eng. Proc. 2026, 133(1), 157; https://doi.org/10.3390/engproc2026133157 - 19 May 2026

Cited by 1 | Viewed by 360

Abstract

Efficient communication infrastructure is essential for Unmanned Aircraft Systems (UASs) operating beyond visual line of sight (BVLOS). Both terrestrial and non-terrestrial networks struggle with coverage gaps and are susceptible to disruptions. This paper analyzes integrated terrestrial–non-terrestrial network (TN-NTN) architectures for UAS communications in [...] Read more.

Efficient communication infrastructure is essential for Unmanned Aircraft Systems (UASs) operating beyond visual line of sight (BVLOS). Both terrestrial and non-terrestrial networks struggle with coverage gaps and are susceptible to disruptions. This paper analyzes integrated terrestrial–non-terrestrial network (TN-NTN) architectures for UAS communications in 6G, focusing on three connectivity methods: terrestrial connectivity, indirect satellite connectivity, and direct UAS–satellite links. We provide the assessment of different connectivity options. Major challenges are discussed, including antenna limitations, reliability, channel modeling, and regulatory alignment. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 6644 KB

Open AccessProceeding Paper

A Web-Based Tool for Mission Planning and Risk Assessment of UAS Operations

by Stefano Primatesta and Gianluca Scopelliti

Eng. Proc. 2026, 133(1), 158; https://doi.org/10.3390/engproc2026133158 - 19 May 2026

Viewed by 344

Abstract

This paper presents the preliminary implementation of a web-based tool designed to support UAS operators in mission planning and risk assessment in compliance with the SORA 2.5 methodology. The system integrates risk maps for high-fidelity ground risk assessment and risk-aware path planning to [...] Read more.

This paper presents the preliminary implementation of a web-based tool designed to support UAS operators in mission planning and risk assessment in compliance with the SORA 2.5 methodology. The system integrates risk maps for high-fidelity ground risk assessment and risk-aware path planning to identify minimum-risk flight corridors. The tool guides the operator through the evaluation phase of SORA, allowing the assessment of the iGRC, ARC, and SAIL within an intuitive workflow. A representative use case in an urban area of Turin illustrates how the application highlights the distribution of risk in the urban area and supports SORA-compliant decision-making. The results demonstrate the usefulness of the tool in improving risk awareness and supporting mission preparation. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 1661 KB

Open AccessProceeding Paper

A Study on the Potential of Hydrogen Tankering in the Design and Operation of an Air Transport System with First-Generation Hydrogen-Powered Aircraft

by Sam Randeraad, Pieter-Jan Proesmans and Alexei Sharpanskykh

Eng. Proc. 2026, 133(1), 159; https://doi.org/10.3390/engproc2026133159 - 7 May 2026

Viewed by 163

Abstract

Liquid hydrogen-powered aircraft (LH₂ aircraft) offer the potential for a zero-carbon footprint when hydrogen is produced from renewable sources. However, integrating LH₂ aircraft into the air transport system is complex due to differences in LH₂ supply availability and varying levels [...] Read more.

Liquid hydrogen-powered aircraft (LH₂ aircraft) offer the potential for a zero-carbon footprint when hydrogen is produced from renewable sources. However, integrating LH₂ aircraft into the air transport system is complex due to differences in LH₂ supply availability and varying levels of airport readiness. To address these disparities and comply with anticipated sustainability regulations, hydrogen tankering can serve as a temporary strategy by carrying additional hydrogen to avoid refueling at destinations lacking LH₂ capabilities. This study presents a novel model that evaluates the potential of tankering while accounting for its interaction with strategic LH₂ infrastructure placement, tactical flight scheduling, and operational aircraft routing. Applying the framework to a real-world case in the Baltic Sea region reveals trade-offs between system costs and environmental benefits under different regulatory measures. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 658 KB

Open AccessProceeding Paper

A Fast Design and Performance Prediction Methodology and Tool for Centrifugal Compressors of Aircraft Environmental Control Systems

by Toon Bloem, Gülberg Çelikel, Wilson Casas and Matteo Pini

Eng. Proc. 2026, 133(1), 160; https://doi.org/10.3390/engproc2026133160 - 20 May 2026

Viewed by 349

Abstract

Within the framework of European Union-funded Clean Aviation and TheMa4HERA (Thermal Management for the Hybrid Electric Regional Aircraft) projects, a preliminary performance prediction and design tool for centrifugal compressors has been developed, targeting the turbomachinery components used in environmental control systems (ECS) in [...] Read more.

Within the framework of European Union-funded Clean Aviation and TheMa4HERA (Thermal Management for the Hybrid Electric Regional Aircraft) projects, a preliminary performance prediction and design tool for centrifugal compressors has been developed, targeting the turbomachinery components used in environmental control systems (ECS) in short/medium-range types of aircraft. This tool is an integral part of the objective to establish a complete optimization methodology for the performance assessment and sizing of air generation systems for next-generation aircraft. The methodology is based on mean-line analysis for the impeller, vaneless and vaned (including variable-vaned) diffusers, and volute, with a two-zone approach for the flow analysis in the vaned diffuser passage. The results of the model are validated against experimental data related to two different open-source compressor designs with both diffuser types. It is concluded from these cases that, for the purpose of the design tool, the model provides accurate results for the impeller and both diffuser types. Extreme conditions such as stall and choke remain difficult to accurately predict due to the complex three-dimensional nature of these phenomena. Future developments of the tool will include modeling capabilities for radial turbines and heat exchangers. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 1440 KB

Open AccessProceeding Paper

Numerical Investigation of Unsteady Fluid Flow Inside Air Cooling Ducts with Tilted Heat Exchanger for Electrified Aero Engines

by Prabhjot Singh, Florian Nils Schmidt, Sebastian Merbold, Ralf Rudnik and Stefanie de Graaf

Eng. Proc. 2026, 133(1), 161; https://doi.org/10.3390/engproc2026133161 - 20 May 2026

Viewed by 213

Abstract

Integrating a heat exchanger (HEX) into the cooling duct of a high-power fuel-cell-based aircraft presents a critical trade-off between thermal performance and aerodynamic penalties. The present study addresses this challenge through the design and system-level analysis of a HEX integrated into the cooling [...] Read more.

Integrating a heat exchanger (HEX) into the cooling duct of a high-power fuel-cell-based aircraft presents a critical trade-off between thermal performance and aerodynamic penalties. The present study addresses this challenge through the design and system-level analysis of a HEX integrated into the cooling duct. Developed as part of the Clean Aviation project FAME, the design features a rectangular inlet, a circular outlet, and a tilted HEX. The evaluation is performed using high-fidelity Large Eddy Simulations (LESs). The HEX is modeled with a porous media approach based on the Darcy–Forchheimer equation, while the simulations are carried out using a self-adapted version of the pisoFoam solver, termed pisoTempFoam, to account for heat transfer. The study reveals that while component-level design choices, such as a straight inlet and tilted HEX configuration, successfully mitigate local flow separation and duct-induced losses, a critical system-level performance issue emerges. The analysis demonstrates that the cooling duct design, when subjected to realistic operational conditions, generates the high pressure head to overcome the resistance of the HEX. The external aerodynamic analysis also indicates that the HEX resistance is a critical factor, and without overcoming it the system fails to capture the required air mass flow rate, compromising thermal management. The findings highlight the necessity to optimize the design, by an adapted duct shape or an auxiliary fan, to overcome the HEX-induced pressure drop. The porous media approach is thereby validated as an effective tool for rapid system-level design analysis, despite its inherent limitation in capturing detailed downstream turbulence. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 1569 KB

Open AccessProceeding Paper

Multi-Input Multi-Output Fast and Relaxed Vector Fitting for Aircraft Ground Vibration Testing

by Beatrice E. Bauret Martínez, Gabriele Dessena, Marco Civera and Oscar E. Bonilla-Manrique

Eng. Proc. 2026, 133(1), 162; https://doi.org/10.3390/engproc2026133162 - 21 May 2026

Viewed by 231

Abstract

Fast and Relaxed Vector Fitting (FRVF) is a frequency domain system identification method widely used in electrical network modelling, but its application to mechanical systems remains limited. This study adapts FRVF to identify modal parameters of aircraft structures from Ground Vibration Test (GVT) [...] Read more.

Fast and Relaxed Vector Fitting (FRVF) is a frequency domain system identification method widely used in electrical network modelling, but its application to mechanical systems remains limited. This study adapts FRVF to identify modal parameters of aircraft structures from Ground Vibration Test (GVT) data in multi-input multi-output (MIMO) configurations. The methodology involves: (1) rational approximation of frequency response functions using enhanced input stacking, (2) extraction of poles from the fitted model, and (3) computation of modal parameters from pole locations and residues. Numerical validation is performed on a 2D MIMO beam model, assessing accuracy and robustness under increasing noise levels. Experimental validation uses the BAE Hawk T1A aircraft dataset, demonstrating performance comparable to the improved Loewner Framework (iLF) method. The results demonstrate that the MIMO-extended FRVF approach performs reliably in terms of accuracy, noise resistance, and computational efficiency. These findings suggest that the method holds significant promise for use in GVTs and subsequently damage detection of aerospace structures. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 1410 KB

Open AccessProceeding Paper

Life Cycle Assessment Activities in HERFUSE Project

by Mario A. Solazzo, Deborah Neumann de la Cruz, Umberto Carrotta, Lidia Travascio and Angela Vozella

Eng. Proc. 2026, 133(1), 163; https://doi.org/10.3390/engproc2026133163 - 22 May 2026

Viewed by 249

Abstract

In the frame of the final analysis of the HERFUSE activities a life cycle assessment (LCA) has been planned to support the performance evaluation of the new Clean Aviation (CA) architectural concepts. The HERFUSE project is focused on designing innovative fuselage and empennages [...] Read more.

In the frame of the final analysis of the HERFUSE activities a life cycle assessment (LCA) has been planned to support the performance evaluation of the new Clean Aviation (CA) architectural concepts. The HERFUSE project is focused on designing innovative fuselage and empennages suitable for the future Hybrid-Electric Regional Aircraft (HER) that will contribute to the overall target to reduce greenhouse gas (GHG) emissions. HERFUSE will study the challenges in fuselage and empennage layout, material, components, manufacturing and assembly derived from the integration of the relevant fuselage systems for HER as defined in the strategic research and innovation agenda SRIA for a Hybrid-Electric Regional Aircraft and in HER-01 topic. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 1450 KB

Open AccessProceeding Paper

Autonomous Cooperative Drone Swarms for Countering Drones via Multi-Agent Deep Reinforcement Learning

by Ender Çetin, Cristina Barrado, Jose Luis Muñoz Gamarra and Juan Jose Ramos Gonzalez

Eng. Proc. 2026, 133(1), 164; https://doi.org/10.3390/engproc2026133164 - 22 May 2026

Viewed by 420

Abstract

The integration of artificial intelligence (AI), particularly deep reinforcement learning (DRL), promises to enhance the autonomy and adaptability of drones in complex environments. This research explores the implementation of a cooperative counter-drone swarm solution using multi-agent DRL, such as Multi-Agent Proximal Policy Optimization [...] Read more.

The integration of artificial intelligence (AI), particularly deep reinforcement learning (DRL), promises to enhance the autonomy and adaptability of drones in complex environments. This research explores the implementation of a cooperative counter-drone swarm solution using multi-agent DRL, such as Multi-Agent Proximal Policy Optimization (MAPPO), and the aim is to enhance public security. In this paper, an open-source simulation platform, AirSim, is utilized to train and test the proposed method. A centralized critic architecture within a multi-agent reinforcement learning (MARL) framework using Proximal Policy Optimization (PPO) is implemented. A PettingZoo–Ray RLlib integration provides scalable multi-agent training using shared policies to encourage collaboration. A centralized critic is trained by observing the joint state and action space of all drone agents, while drone agents execute decentralized policies during deployment. We observed that increasing the number of cooperative drones improves performance, achieving a 66.7% increase in episode reward, a 42% improvement in team success rate, and a 65% reduction in geofence violations compared to the two-drone configuration. The proposed framework provides a scalable foundation for real-world cooperative counter-unmanned aerial system (C-UAS) operations using deep reinforcement learning. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 1090 KB

Open AccessProceeding Paper

Design, Analysis and Optimisation of a Vacuum-Insulated Composite Conformal LH₂ Tank

by Bram Noordman, Albert de Wit, Ralf Creemers, Arne te Nijenhuis, Rens Ubels, Karthik Ramaswamy, Amit Kumar Tripathi, Paul Liddel, Jack Cullinan and Leonardo Lecce

Eng. Proc. 2026, 133(1), 165; https://doi.org/10.3390/engproc2026133165 - 19 May 2026

Viewed by 470

Abstract

Hydrogen-propelled aircraft can enable net-zero CO₂ emissions in aviation, which is the goal of the International Civil Aviation Organization (ICAO) for 2050. One drawback of onboard hydrogen storage in aircraft is the necessity for relatively large, pressurised storage volumes. To maximise H [...] Read more.

Hydrogen-propelled aircraft can enable net-zero CO₂ emissions in aviation, which is the goal of the International Civil Aviation Organization (ICAO) for 2050. One drawback of onboard hydrogen storage in aircraft is the necessity for relatively large, pressurised storage volumes. To maximise H₂ volumetric efficiency, the COmposite COnformal LIquid H₂ Tank (COCOLIH₂T) project attempts to design, build and test a vacuum-insulated liner-less cryogenic conformal thermoplastic composite tank with conditioning subsystems for safe operation. The tank must be compatible with the design envelope in the empennage, specifically towards the aft of the pressure bulkhead of an ATR 72-like aircraft. The tank design, analysis, optimisation and demonstrator manufacturing are presented in this paper. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 4726 KB

Open AccessProceeding Paper

Deploying Advanced Air Mobility into an Existing Transport System of Systems: The Product Push Paradigm

by Nabih Naeem, Nazlican Cigal and Prajwal Shiva Prakasha

Eng. Proc. 2026, 133(1), 166; https://doi.org/10.3390/engproc2026133166 - 20 May 2026

Viewed by 427

Abstract

This study presents a system-of-systems simulation framework to evaluate the integration of advanced air mobility (AAM) into intermodal transport. It models door-to-door journeys from Munich to Cres Island via Rijeka, combining intercity modes with intracity AAM or public transport. Mode choice is based [...] Read more.

This study presents a system-of-systems simulation framework to evaluate the integration of advanced air mobility (AAM) into intermodal transport. It models door-to-door journeys from Munich to Cres Island via Rijeka, combining intercity modes with intracity AAM or public transport. Mode choice is based on passenger-specific utility functions that account for time, cost, and emissions. A baseline scenario assesses the impact of AAM on travel performance. A product push paradigm is explored where the focus is on how a known product (eVTOL) can be successfully deployed to satisfy stakeholder requirements. A four-step approach to the product push paradigm is proposed in this work with progressively increasing complexity at each level, exploring the value added, understanding the market, capturing the market, and lastly, trading off stakeholder interests. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 4438 KB

Open AccessProceeding Paper

Visual Analytics Framework for Multi-Objective Optimisation of Aircraft Design

by Shubham Shubham, Andrea Spinelli and Timoleon Kipouros

Eng. Proc. 2026, 133(1), 167; https://doi.org/10.3390/engproc2026133167 - 22 May 2026

Viewed by 375

Abstract

This paper presents a web-based visual analytics framework for robust multi-objective aircraft wing design. Aerodynamic and structural simulation data are generated for a redesigned CRM wing, with aspect ratio and skin root thickness as key variables. Ordinary Kriging surrogates are coupled with NSGA-III [...] Read more.

This paper presents a web-based visual analytics framework for robust multi-objective aircraft wing design. Aerodynamic and structural simulation data are generated for a redesigned CRM wing, with aspect ratio and skin root thickness as key variables. Ordinary Kriging surrogates are coupled with NSGA-III to explore trade-offs among lift-to-drag ratio, wing mass, and range. Input design uncertainties are propagated using Monte Carlo Simulation with Halton sampling, enabling low-cost robustness assessment. An interactive HTML–Python dashboard provides contour plots, sampled design points, and Pareto fronts, allowing engineers to perform what-if analyses and rapidly identify robust Pareto-optimal designs. Results show that a higher aspect ratio with lower skin thickness improves aerodynamic efficiency and range, while structural constraints and uncertainty bounds define feasible regions. The Kriging surrogate achieves a Surrogate Speed-Up Index (SSI) of

O (10^{3})

, offering comparable insight into wing mass, range, and

L / D

at roughly three-orders-of-magnitude-lower computational cost than direct mid-fidelity simulations. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 1740 KB

Open AccessProceeding Paper

Prospects for a More Sustainable Aviation: Roadmap Towards 2050

by María Zamarreño Suárez, Rosa María Arnaldo Valdés, Raquel Delgado-Aguilera Jurado, César Gómez Arnaldo, Francisco Pérez Moreno and Víctor Fernando Gómez Comendador

Eng. Proc. 2026, 133(1), 168; https://doi.org/10.3390/engproc2026133168 - 12 May 2026

Viewed by 340

Abstract

One of the fundamental aspects of achieving sustainability in aviation is reducing aircraft emissions. While the effects of CO₂ have been studied extensively, it is crucial to also consider non-CO₂ emissions. This paper presents the fundamental ideas of the research developed [...] Read more.

One of the fundamental aspects of achieving sustainability in aviation is reducing aircraft emissions. While the effects of CO₂ have been studied extensively, it is crucial to also consider non-CO₂ emissions. This paper presents the fundamental ideas of the research developed to analyse the path to sustainability in aviation within the framework of the European Environmentally Friendly Aviation for All Classes of Aircraft (EFACA) project. Nine scenarios are considered in the analysis: two reference scenarios, the EFACA base scenario and six EFACA variations scenarios. The EFACA base scenario considers the project’s proposal for sustainable aviation for all classes of aircraft. Additionally, the methodology followed in the analysis is presented. The decisions made to calculate carbon and total emissions, costs and investments, and economic effects are specified. The analytical approaches adopted are also discussed. Projections for the different scenarios up to 2050 are calculated and comparative and sensitivity analyses performed. The paper presents the logic behind each stage and demonstrates how this methodological approach can be used as a valuable tool for analysing the prospects for a more sustainable aviation in terms of reducing emissions. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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7 pages, 2008 KB

Open AccessProceeding Paper

New Work in Aerospace Sciences—Two Years of Experience in the CRC SynTrac

by Tobias Ring and Stephan Staudacher

Eng. Proc. 2026, 133(1), 169; https://doi.org/10.3390/engproc2026133169 - 25 May 2026

Viewed by 158

Abstract

Collaborative Research Centres (CRCs) are research institutions in which researchers from several German universities work together within a multidisciplinary research programme. A large number of projects led by one or several researchers from the participating research institutions characterize them. Integrated Research Training Programmes [...] Read more.

Collaborative Research Centres (CRCs) are research institutions in which researchers from several German universities work together within a multidisciplinary research programme. A large number of projects led by one or several researchers from the participating research institutions characterize them. Integrated Research Training Programmes (IRTGs) can be part of the CRC’s supporting structures. They offer a structured training programme with the aim not only of supporting the doctoral researchers in their research activities but also making an engagement in the CRC attractive to young researchers. Key aims are to promote the doctoral researchers’ academic independence and to enable them to gain further qualifications. The integrated research training group of the CRC SFB-TRR 364 SynTrac-Synergies of Highly Integrated Transport Aircraft is inspired by the principles of New Work. This required an adjusted definition of New Work to fit the vision of the CRC SynTrac and the requirements of today’s highly talented doctoral researchers. On this basis, we designed the physical, inter-personal and virtual work-space and the methods which allow the doctoral researchers to perform the activities they “really, really” want to do. We report on two years of experience with this design of the IRTG. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 3096 KB

Open AccessProceeding Paper

Advanced Performance Analysis of Distributed Electric Propulsion Using a Meshless CFD Simulation Approach

by Roberta Bottigliero, Viola Rossano, Joel Guerrero and Giuliano De Stefano

Eng. Proc. 2026, 133(1), 170; https://doi.org/10.3390/engproc2026133170 - 22 May 2026

Viewed by 336

Abstract

Achieving climate-neutral aviation requires propulsion systems capable of reducing emissions and noise while maintaining high aerodynamic efficiency. Distributed Electric Propulsion (DEP) represents a promising solution; however, accurately predicting the unsteady aerodynamic interactions between multiple propellers and lifting surfaces remains challenging. This work investigates [...] Read more.

Achieving climate-neutral aviation requires propulsion systems capable of reducing emissions and noise while maintaining high aerodynamic efficiency. Distributed Electric Propulsion (DEP) represents a promising solution; however, accurately predicting the unsteady aerodynamic interactions between multiple propellers and lifting surfaces remains challenging. This work investigates the aerodynamic performance of two Distributed Propulsion (DP) configurations using FLOWUnsteady, a meshless Computational Fluid Dynamics (CFD) solver based on the reformulated Vortex Particle Method (rVPM) within a Large-Eddy Simulation (LES) framework. The Lagrangian particle formulation eliminates mesh generation and limits numerical dissipation. Two layouts—a twin wingtip-mounted arrangement and a four-propeller configuration including inboard units are analyzed and compared with a clean wing baseline as functions of propeller position, inflow speed (20 and 33 m/s), and angle of attack. Beyond global aerodynamic performance metrics, the rVPM–LES framework provides a time-resolved and spatially resolved characterization of local propeller–wing interference in multi-propulsor configurations, highlighting differences in loading and torque demand between inboard and wingtip propellers that are not typically captured by low- to mid-fidelity modeling approaches. The results show that distributed propulsion increases lift and reduces drag relative to the clean wing by accelerating the local flow, delaying separation, and enhancing wing circulation. Thrust and torque coefficients exhibit a clear dependence on rotational speed and angle of attack: inboard propellers experience stronger aerodynamic interference and higher torque demand, whereas wingtip propellers maintain more uniform loading. These findings confirm the capability of the meshless rVPM approach to accurately and efficiently capture unsteady interactions in distributed propulsion systems, supporting its application to the analysis and design of future DEP aircraft. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 2042 KB

Open AccessProceeding Paper

DEMOCRITE Project: EREA Collaborative Research on H₂ Tank Design and A/C Integration

by Maciej Karny, Cedric Julien, Mircea Bocioaga and Ignazio Dimino

Eng. Proc. 2026, 133(1), 171; https://doi.org/10.3390/engproc2026133171 - 25 May 2026

Viewed by 446

Abstract

Hydrogen has the potential to revolutionize the aviation industry by transitioning aviation into a zero-carbon industry. However, realizing this vision requires overcoming significant technological challenges, particularly in hydrogen storage, distribution, and safety. The DEMOCRITE (Development of Modular Cryogenic Tank system) project is collaborative [...] Read more.

Hydrogen has the potential to revolutionize the aviation industry by transitioning aviation into a zero-carbon industry. However, realizing this vision requires overcoming significant technological challenges, particularly in hydrogen storage, distribution, and safety. The DEMOCRITE (Development of Modular Cryogenic Tank system) project is collaborative research within the EREA, the Association of European Research Establishments in Aviation, focusing on composite cryogenic hydrogen tanks for hydrogen-powered aircraft. This paper addresses the energy storage capability of modular hydrogen tanks and the related A/C integration aspects. Using multiple parameters (weight, center of gravity, passenger count), different tank arrangements are proposed and evaluated in search for the most optimal solution. Pressure management of cryogenic hydrogen tanks is also discussed. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 5168 KB

Open AccessProceeding Paper

Modular Construction for Lunar Infrastructure Using Fibre-Reinforced Composites

by Linda Cortés-Satizábal, Deniz Yesilyurt, Kira Heins and Thomas Gries

Eng. Proc. 2026, 133(1), 172; https://doi.org/10.3390/engproc2026133172 - 25 May 2026

Viewed by 260

Abstract

After establishing a lunar settlement, developing resilient infrastructure becomes essential. Transporting prefabricated materials from Earth is costly and logistically challenging, making lunar regolith a promising in situ alternative. Its natural properties support durable, protective construction suited to harsh lunar conditions. This study examines [...] Read more.

After establishing a lunar settlement, developing resilient infrastructure becomes essential. Transporting prefabricated materials from Earth is costly and logistically challenging, making lunar regolith a promising in situ alternative. Its natural properties support durable, protective construction suited to harsh lunar conditions. This study examines fibre-reinforced composites using LHS-1 and EAC-1 regolith simulants, combining fibre tensile strength with a regolith matrix to improve load-bearing performance. Inspired by textile-reinforced concrete on Earth, this approach enhances tensile capacity and durability compared to unreinforced regolith. Modular components—blocks, panels, structural elements—enable scalable, efficient assembly, supporting adaptable, long-term lunar infrastructure. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 1825 KB

Open AccessProceeding Paper

Modeling Comparison of a Two-Phase Mechanically Pumped Loop with a Conventional Ethylene Glycol Water Single-Phase Mechanically Pumped Loop for Fuel-Cell Cooling in TheMa4HERA

by Tim A. F. van de Weijer, Johannes van Es, Henk Jan van Gerner, Arne K. te Nijenhuis, Julian Biesheuvel, Guilhem Delpu, Fatima Cherdouh, Esli Trejo Peimbert, Ricardo Abib Gantus, Pierre Trolliet, Guillaume Galzin and Laurent Labaste Mauhe

Eng. Proc. 2026, 133(1), 173; https://doi.org/10.3390/engproc2026133173 - 26 May 2026

Viewed by 172

Abstract

The fuel-cell (FC) technology currently being considered to reduce aircraft greenhouse gas emissions may require large and heavy cooling systems. The paper introduces the two-phase (2

Φ

) Mechanically Pumped Loop (MPL) for FC cooling and compares it numerically with the conventional Ethylene [...] Read more.

The fuel-cell (FC) technology currently being considered to reduce aircraft greenhouse gas emissions may require large and heavy cooling systems. The paper introduces the two-phase (2

Φ

) Mechanically Pumped Loop (MPL) for FC cooling and compares it numerically with the conventional Ethylene Glycol Water (EGW) single-phase (1

Φ

) cooling system for a

1.2

MW heat-dissipation load. Considering an operating temperature of 90 °C, the system mass of the 2

Φ

MPL with and without an accumulator is found to be, respectively, 33% and 64% lower than the EGW system. Furthermore, the frontal area of the ram air heat exchanger (HX) was found to be 19% smaller, reducing ram air drag. An increase of the operating temperature to 130 °C was found to reduce the cooling system mass by 21% for the 1

Φ

MPL, and 22 to 29% for the 2

Φ

MPL. The frontal area of the ram air HX was found to be reduced by 44% and 40% for the 1

Φ

and 2

Φ

MPL, respectively. These results demonstrate the considerable performance gain of the 2

Φ

MPL over the 1

Φ

MPL for FC cooling, and the benefits of increasing the operating temperature for the cooling system. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 2110 KB

Open AccessProceeding Paper

Performance and Emissions Analysis of a Microturbine Operated with Sustainable Aviation Fuel

by Maria Grazia De Giorgi, Antonio Greco, Sara Bonuso, Pasquale Di Gloria, Bartosz Gawron, Tomasz Białecki and Andrzej Kulczycki

Eng. Proc. 2026, 133(1), 174; https://doi.org/10.3390/engproc2026133174 - 15 May 2026

Viewed by 341

Abstract

The aviation sector is accelerating the transition toward low-carbon propulsion, and Sustainable Aviation Fuels (SAFs) represent a key leverage to reduce lifecycle emissions without modifying existing turbine architectures. Microturbines offer an effective and low-cost platform for assessing SAF behaviour under engine-representative conditions. In [...] Read more.

The aviation sector is accelerating the transition toward low-carbon propulsion, and Sustainable Aviation Fuels (SAFs) represent a key leverage to reduce lifecycle emissions without modifying existing turbine architectures. Microturbines offer an effective and low-cost platform for assessing SAF behaviour under engine-representative conditions. In this work, a zero-dimensional performance and emission model of the GTM-140 microturbine was developed in GSP and validated against experimental data at 70,000–112,000 rpm for Jet A-1 and HEFA paraffinic blends. The model reproduces thrust and fuel-flow trends with good fidelity, with deviations typically below 6% across all operating points. Introducing 50% HEFA consistently reduces fuel consumption, leading to a TSFC decrease of 3–6%, with the strongest effect at high rotational speed, where compressor efficiency is highest. CO emission indices decrease by 6–9% at mid-load and converge at full power due to enhanced oxidation, while NO_x increases by 6–15%, driven by the higher adiabatic flame temperature associated with HEFA’s increased H/C ratio and heating value. These results confirm that simplified 0D modelling can reliably capture performance and emission trends of SAF-fuelled microturbines and demonstrate the dual effect of HEFA: improved combustion efficiency and CO reduction, at the expense of moderately higher NO_x formation. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 1781 KB

Open AccessProceeding Paper

Proof of Concept of Radars for UAM/IAM Applications

by Juan Felipe González-Pardo, Pablo Carrascosa-Egido and Juan V. Balbastre

Eng. Proc. 2026, 133(1), 175; https://doi.org/10.3390/engproc2026133175 - 26 May 2026

Viewed by 238

Abstract

The increasing use of Unmanned Aerial Systems (UAS) in civil applications has accelerated the development of new Air Traffic Management (ATM) frameworks to ensure the safe and efficient operation. Onboard technology, such as Detect and Avoid (DAA) systems, have been proposed as an [...] Read more.

The increasing use of Unmanned Aerial Systems (UAS) in civil applications has accelerated the development of new Air Traffic Management (ATM) frameworks to ensure the safe and efficient operation. Onboard technology, such as Detect and Avoid (DAA) systems, have been proposed as an alternative to reduce operational risk to acceptable levels. However, these technologies require preliminary validation to meet current regulatory standards, which define the Minimum Operational Performance (MOP). In this work, we propose the architecture of two DAA systems based on frequency-modulated continuous-wave (FMCW) radars operating in the radiolocalization bands at 9.5 GHz and 24 GHz. The performance of both onboard systems was validated through the probability of detection

P_{d}

for different intruder categories, meeting the MOP in accordance with the RTCA DO-366A, DO-396, and ASTM F3442 standards. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 658 KB

Open AccessProceeding Paper

Absorption-Based Laser Mass Flow Meter for Iodine-Fed Electric Propulsion: Design and Experiments

by Carla Guidi, Manuel Martín Saravia, Delfina Pieroni, Luca Bernazzani, Fabrizio Paganucci, Nils Gerrit Kottke, Marco Mugnaini, Enza Panzardi and Alessio Ceccarini

Eng. Proc. 2026, 133(1), 176; https://doi.org/10.3390/engproc2026133176 - 26 May 2026

Viewed by 162

Abstract

In electric propulsion for space applications, searching for alternative propellants is increasingly important due to limited resources and economic considerations. Among the candidates, iodine has emerged as promising thanks to its favorable chemical and physical properties for propulsion and its lower cost and [...] Read more.

In electric propulsion for space applications, searching for alternative propellants is increasingly important due to limited resources and economic considerations. Among the candidates, iodine has emerged as promising thanks to its favorable chemical and physical properties for propulsion and its lower cost and simpler storage compared with xenon. However, its corrosive behavior is a drawback, as iodine reacts with many aerospace materials, and its condensable nature prevents using propellant management systems like those for noble gases. At the University of Pisa, activities on fluidics for iodine-fed electric propulsion systems and material compatibility studies led to the development of a mass flowmeter within the “iFACT-MP” Horizon EU project. The device is a spectrophotometric flow meter measuring instantaneous mass flow through a cell in series with the iodine feeding line, upstream of a thermal throttle. A beam splitter directs part of the light to a reference photodiode to compensate for laser intensity variations. Temperature and absorption measurements allow inferring iodine pressure in the cell, while the thermal throttle ensures sonic conditions, enabling correlation with instantaneous mass flow. The mass flow meter shows good behavior and repeatability, especially at low mass flow rates. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 2510 KB

Open AccessProceeding Paper

Multilayer Satellite Constellation Design for Multipurpose Applications

by Mansoor Jamal, Ernestina Cianca, Tommaso Rossi and Mauro De Sanctis

Eng. Proc. 2026, 133(1), 177; https://doi.org/10.3390/engproc2026133177 - 27 May 2026

Viewed by 453

Abstract

Low and Medium Earth Orbit (LEO/MEO) satellite constellations have emerged as a compelling architectural paradigm for delivering multipurpose services. In this study, we investigate the joint optimization of communication and positioning performance metrics in a multilayer LEO/MEO constellation equipped with inter-satellite links (ISLs). [...] Read more.

Low and Medium Earth Orbit (LEO/MEO) satellite constellations have emerged as a compelling architectural paradigm for delivering multipurpose services. In this study, we investigate the joint optimization of communication and positioning performance metrics in a multilayer LEO/MEO constellation equipped with inter-satellite links (ISLs). A genetic algorithm framework is employed to optimize key constellation design variables, including the number of satellites per orbital plane, the number of planes, and the inter-plane phase offsets across layers, to minimize end-to-end user latency and Geometric Dilution of Precision (GDOP), subject to coverage and total satellite count constraints. Numerical results highlight the trade-offs among different architectural options. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 6086 KB

Open AccessProceeding Paper

Developing a Qualification and Testing Framework for Cold Spray Repairs in Aerospace Applications

by Konstantinos Stamoulis, Morteza Abouhamzeh, Stratos Koufis, Bernard Bosma, Lars Anderiessen and John-Alan Pascoe

Eng. Proc. 2026, 133(1), 178; https://doi.org/10.3390/engproc2026133178 - 25 May 2026

Viewed by 478

Abstract

Cold spray is a solid-state deposition technology with great potential for coating and repair applications. This study examines the compliance of the cold spray repair process with a qualification and testing framework based on the requirements set by the European Union Aviation Safety [...] Read more.

Cold spray is a solid-state deposition technology with great potential for coating and repair applications. This study examines the compliance of the cold spray repair process with a qualification and testing framework based on the requirements set by the European Union Aviation Safety Agency (EASA). As part of this effort, the case study of a repair of a Main Landing Gear (MLG) aluminium component is investigated to demonstrate the applicability of the proposed framework. This framework integrates mechanical and microstructural evaluations, including bond strength, hardness profiling and microstructural characterisation according to relevant ASTM and ISO standards. Experimental results from post-repair testing indicated promising performance, while ongoing testing is aligning reasonably with expected benchmarks and showing compliance with the EASA requirements. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 1855 KB

Open AccessProceeding Paper

A Modular Assembly Concept for Large-Volume CFRP Hydrogen Tanks for Passenger Aircraft

by Karina Görner, Benjamin Diehl and Simon Kothe

Eng. Proc. 2026, 133(1), 179; https://doi.org/10.3390/engproc2026133179 - 27 May 2026

Viewed by 367

Abstract

This paper presents a novel modular assembly concept for large-volume Carbon Fiber Reinforced Plastics (CFRP) hydrogen tanks, supporting the aviation sector’s transition toward sustainable propulsion. Adhering to VDI 2221 and 2222 design methodologies, four assembly concepts were developed and then evaluated by Airbus, [...] Read more.

This paper presents a novel modular assembly concept for large-volume Carbon Fiber Reinforced Plastics (CFRP) hydrogen tanks, supporting the aviation sector’s transition toward sustainable propulsion. Adhering to VDI 2221 and 2222 design methodologies, four assembly concepts were developed and then evaluated by Airbus, FFT, and Fraunhofer IFAM, to determine the best fit for industrial application. The “Modular Assembly System on Linear Axes” was identified as the best solution, characterized by superior process robustness and efficiency. Utilizing dual linear axes for precise component handling and robotic guidance, this concept ensures structural integrity during joining while offering scalability and seamless integration into existing manufacturing infrastructures. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 3141 KB

Open AccessProceeding Paper

Operational Modal Analysis of the International Space Station via Fast and Relaxed Vector Fitting

by Marina Cózar Alcázar, Gabriele Dessena, Marco Civera and Oscar E. Bonilla-Manrique

Eng. Proc. 2026, 133(1), 180; https://doi.org/10.3390/engproc2026133180 - 28 May 2026

Viewed by 342

Abstract

Recent aerospace safety requirements have increased the demand for reliable structural damage detection. This work presents an output-only operational modal analysis approach that combines the Natural Excitation Technique (NExT) with the Fast and Relaxed Vector Fitting (FRVF) algorithm. The method is validated numerically [...] Read more.

Recent aerospace safety requirements have increased the demand for reliable structural damage detection. This work presents an output-only operational modal analysis approach that combines the Natural Excitation Technique (NExT) with the Fast and Relaxed Vector Fitting (FRVF) algorithm. The method is validated numerically on a beam model against analytical solutions, and the NExT–ERA (Eigensystem Realization Algorithm) technique results, as well as experimentally using acceleration data from the Space Acceleration Measurement System of the International Space Station. NExT-FRVF achieves comparable modal identification to NExT–ERA, with repeated detection confirming mode reliability in both experimental and numerical systems. Additionally, the proposed method can correctly identify higher frequencies, not correctly detected by existing methods, like NExT-ERA, as shown in the numerical case study. The approach shows strong robustness under noise and adaptable fitting, making it an effective tool for monitoring aerospace structures. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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11 pages, 1441 KB

Open AccessProceeding Paper

The Challenges in Extending Engine Performance Modeling for Highly Integrated Transport Aircraft

by Yiwen Yuan, Niraj Iyer, Stephan Staudacher and Jens Friedrichs

Eng. Proc. 2026, 133(1), 181; https://doi.org/10.3390/engproc2026133181 - 28 May 2026

Viewed by 349

Abstract

The utilization of boundary layer ingestion in combination with a turbofan engine with an ultra-high bypass ratio is regarded as one of the possible solutions to increase the energy efficiency of the aircraft as a complete system. However, this concept inevitably leads to [...] Read more.

The utilization of boundary layer ingestion in combination with a turbofan engine with an ultra-high bypass ratio is regarded as one of the possible solutions to increase the energy efficiency of the aircraft as a complete system. However, this concept inevitably leads to strong coupling between the external aircraft flow and engine internal flow, associated with an increased degree of flow non-uniformity. As a consequence, the engine components experience changed matching, and their performance is dependent on the engine power settings, aircraft design and flight conditions. All of these installation effects are reflected in engine performance modeling, which can enable reliable engine performance assessment. In this context, this article investigates the sensitivity of such engines and discusses possible approaches and preliminary ideas in extending engine performance modeling. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 1482 KB

Open AccessProceeding Paper

The Quest for a Digital Safety Thread in End-to-End Aircraft Design

by Loris Dal Lago, Marco Donnarumma, Luigi Di Guglielmo and Vincenzo Petrella

Eng. Proc. 2026, 133(1), 182; https://doi.org/10.3390/engproc2026133182 - 20 May 2026

Viewed by 317

Abstract

Safety is the most critical asset in the aerospace industry, and emerging technology domains like hybrid-electric distribution systems present new challenges. In this context, digitalization plays a crucial role in analyzing and managing different safety aspects within and across companies. This study shows [...] Read more.

Safety is the most critical asset in the aerospace industry, and emerging technology domains like hybrid-electric distribution systems present new challenges. In this context, digitalization plays a crucial role in analyzing and managing different safety aspects within and across companies. This study shows that tools and methods can integrate seamlessly by interfacing safety data throughout aircraft development stages, using standardized representations of digital artifacts. We further argue that the approach can be utilized to provide evidence of regulatory compliance to third parties, such as certification authorities, thereby supporting the certification process and investigations into the certifiability of disruptive technologies. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 712 KB

Open AccessProceeding Paper

Application of a Syntax-Based Text Extraction Algorithm on Airworthiness Security Regulations

by Adrian Hechelmann

Eng. Proc. 2026, 133(1), 183; https://doi.org/10.3390/engproc2026133183 - 29 May 2026

Viewed by 405

Abstract

In the context of digital system development, characterized by the utilization of digital methods and tools such as Model-based Systems Engineering (MBSE) and artificial intelligence (AI), the automated extraction of requirements from text-based documents becomes realizable. As a result, time-consuming tasks regarding the [...] Read more.

In the context of digital system development, characterized by the utilization of digital methods and tools such as Model-based Systems Engineering (MBSE) and artificial intelligence (AI), the automated extraction of requirements from text-based documents becomes realizable. As a result, time-consuming tasks regarding the management of requirements can be optimized. This paper demonstrates the results of the application of a syntax-based text extraction algorithm on different airworthiness security regulations. Extracting non-functional requirements from document-based regulations, as the requirements in airworthiness security regulations, using AI models is complex. This is because there is a lack of appropriate training data sets to train AI models. In addition, the creation of a large, high-quality data set requires time-consuming preparatory work. Consequently, an algorithm was developed that extracts non-functional requirements from document-based regulations independently of the existence of appropriate training data sets. The algorithm compares individually defined templates that are composed of syntactical functions with text-based regulations, stores matches and generates syntax trees. The algorithm further includes an automated data-labeling functionality that enables the simplified creation of training data sets for the training of AI models. It was found that with only a few well-defined individual templates, a large number of requirements can be identified. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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Open AccessProceeding Paper

RF Transmit and Receive MMIC Front-End for V-Band Inter-Satellite Link

by Giulio Venanzoni, Andrea Ricci, Mattia Riccardi, Patrick E. Longhi, Rocco Giofrè and Ernesto Limiti

Eng. Proc. 2026, 133(1), 184; https://doi.org/10.3390/engproc2026133184 - 22 Apr 2026

Viewed by 108

Abstract

This research focuses on developing, manufacturing and testing a V-band single-chip transmit and receive front-end integrating an LNA, PA and switching functions for ISL terminals. A comparison is made between two technologies: a 60 nm GaN/Si HEMT from MESC and a 100 nm [...] Read more.

This research focuses on developing, manufacturing and testing a V-band single-chip transmit and receive front-end integrating an LNA, PA and switching functions for ISL terminals. A comparison is made between two technologies: a 60 nm GaN/Si HEMT from MESC and a 100 nm GaAs HEMT from UMS. In Tx mode, targets include 23 dBm saturated power, ≥20 dBm at 14 dB NPR and ≥5% PAE. In Rx mode, the goal is a 4 dB noise figure. In both cases, the gain must exceed 20 dB across the 59–71 GHz band. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 1673 KB

Open AccessProceeding Paper

Process Strategies for DED-Arc-Manufactured Preforms of Ti-15-3-3-3 in Flowforming Applications

by Robert Lau, Frederik Dahms, Hannes Zapf, Henrik Wünsch, Alexander Mädje and Ingomar Kelbassa

Eng. Proc. 2026, 133(1), 185; https://doi.org/10.3390/engproc2026133185 - 2 Jun 2026

Viewed by 197

Abstract

Arc-based directed energy deposition (DED-Arc) processes represent a promising choice for developing flexible and eco-friendly manufacturing strategies for titanium components within the aerospace sector. Previous work has predominantly focused on using Ti-6Al-4V combined with machining for structural components. This study aims to establish [...] Read more.

Arc-based directed energy deposition (DED-Arc) processes represent a promising choice for developing flexible and eco-friendly manufacturing strategies for titanium components within the aerospace sector. Previous work has predominantly focused on using Ti-6Al-4V combined with machining for structural components. This study aims to establish a hybrid manufacturing route that integrates DED-Arc with flowforming (FF), focusing on the processability of Ti-15-3-3-3 in both stages. Sinusoidal path strategies for DED-Arc yield superior results in terms of process stability and geometrical accuracy, leading to near-net-shape preforms. In the FF process, a reduction of up to 80% in wall thickness across various techniques was achieved. The hybrid approach led to a buy-to-fly (BTF) ratio of 2.5:1, revealing the potential for significant material savings compared to conventional manufacturing routes. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 1842 KB

Open AccessProceeding Paper

Machine Learning-Based Resolution of Strategic Conflicts in U-Space Airspaces

by Manuel González, Sandra Amarillo, Juan Vicente Balbastre and Alex Sanchis

Eng. Proc. 2026, 133(1), 186; https://doi.org/10.3390/engproc2026133186 - 2 Jun 2026

Viewed by 141

Abstract

The rapid expansion of Unmanned Aircraft System (UAS) operations has created an urgent need for scalable strategic conflict resolution methods within the U-space framework. When requested 4D flight plans overlap with previously authorised ones, the Flight Authorisation Service (FAS) denies the request, and [...] Read more.

The rapid expansion of Unmanned Aircraft System (UAS) operations has created an urgent need for scalable strategic conflict resolution methods within the U-space framework. When requested 4D flight plans overlap with previously authorised ones, the Flight Authorisation Service (FAS) denies the request, and can provide the UAS operator with an alternative route, free of conflict. This work introduces a Machine Learning-based tool designed to support this process, which consists of three sequential phases. First, an Octree spatial partitioning technique is proposed, discretising the airspace, further identifying the previously occupied cells and visualising the occupied airspace, so that the UAS operator can manually find an alternative route. Then, the widely known A* pathfinding algorithm is implemented in this discretized airspace, allowing the shortest or most optimal conflict-free alternative route. Finally, the methodology integrates a Machine Learning (Reinforcement Learning) model, created from scratch and trained with realistic flight trajectories from a PX4 Simulator, to further optimise flight paths, explicitly accounting for operational constraints such as distance and battery consumption. In this work, both methods are compared, addressing traditional algorithms limitations with Machine Learning (ML) techniques, showing that a near-optimal behaviour can be achieved with the ML approach, at a fraction of the computation time needed. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 1007 KB

Open AccessProceeding Paper

Satellite and Mobile Network Operator Cooperation Models for Efficient Handover in 6G-TN-NTN

by Tedros Salih Abdu, Eva Lagunas, Flor Ortiz, Jorge Querol, Joel Grotz, Marcele O. K. Mendonça, Ons Aouedi and Symeon Chatzinotas

Eng. Proc. 2026, 133(1), 187; https://doi.org/10.3390/engproc2026133187 - 2 Jun 2026

Viewed by 167

Abstract

Cooperation between satellite and mobile network operators enables the integration of non-terrestrial satellite networks (NTNs) with terrestrial networks (TNs), allowing users to seamlessly switch from Mobile Network Operators (MNOs) to Satellite Network Operators (SNOs) in areas with limited MNO coverage or during high-speed [...] Read more.

Cooperation between satellite and mobile network operators enables the integration of non-terrestrial satellite networks (NTNs) with terrestrial networks (TNs), allowing users to seamlessly switch from Mobile Network Operators (MNOs) to Satellite Network Operators (SNOs) in areas with limited MNO coverage or during high-speed travel. However, mobility issues, such as connection failures, the ping-pong effect, and high interruption times, can occur during these transitions. This paper examines various cooperation models, including roaming and handover protocols, and proposes key enhancements to these models to reduce service interruption time. It also discusses the use of machine learning (ML) techniques to reduce the above mobility issue and increase the success rate of cooperation among network operators. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 2586 KB

Open AccessProceeding Paper

Multi-Agent Deep Reinforcement Learning Framework for Efficient Aerial Wildfire Fighting

by Leonard Bardtke, Nabih Naeem, Nikolaos Kalliatakis, Prajwal Shiva Prakasha and Thomas Clemen

Eng. Proc. 2026, 133(1), 188; https://doi.org/10.3390/engproc2026133188 - 2 Jun 2026

Viewed by 149

Abstract

The increasing severity of global wildfires requires advanced suppression strategies to mitigate impacts on the environment and human life. This work investigates the applicability of Multi-Agent Reinforcement Learning (MARL) to aerial wildfire suppression using the SoSID Toolkit, an agent-based grid simulation grounded in [...] Read more.

The increasing severity of global wildfires requires advanced suppression strategies to mitigate impacts on the environment and human life. This work investigates the applicability of Multi-Agent Reinforcement Learning (MARL) to aerial wildfire suppression using the SoSID Toolkit, an agent-based grid simulation grounded in cellular-automata-based fire propagation. To enhance interpretability and support the reconstruction of learned tactics, this work introduces the Dual Decomposition Framework, providing a modular structure for both the reward function and the observation space. This design enables the systematic evaluation of individual components, allowing the identification of the elements most relevant to effective wildfire suppression. The learned MARL policy is compared against a heuristic strategy inspired by real-world firefighting practice. The reward analysis confirms that the Dual Decomposition Framework enhances transparency in agent behavior by analyzing the contribution of individual components. The experiments further show that the learned policy can outperform the heuristic approach in terms of burned-area reduction when fire spread sensitivity is low, demonstrating the potential of MARL for effective suppression strategies. However, performance declines as spread sensitivity increases, indicating limited generalization and signs of overfitting to training conditions. The findings suggest that approaches such as curriculum learning may improve robustness under faster-spreading fire dynamics. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 3653 KB

Open AccessProceeding Paper

Identification of the Natural Vibration Modes of a Turbine Engine Fan Using One- and Three-Dimensional Laser Vibrometry

by Michał Szcześniak, Aleksander Olejnik and Robert Rogólski

Eng. Proc. 2026, 133(1), 189; https://doi.org/10.3390/engproc2026133189 - 4 Jun 2026

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Abstract

Turbine engine discs operate at high speeds with heavy loads. Any failure may result in the engine stopping or being destroyed. Therefore, it is necessary to check the normal modes and determine the rotational speeds at which they may occur. The aim of [...] Read more.

Turbine engine discs operate at high speeds with heavy loads. Any failure may result in the engine stopping or being destroyed. Therefore, it is necessary to check the normal modes and determine the rotational speeds at which they may occur. The aim of this article is to present a method of non-contact measurement of normal modes using the single and three-dimensional modes. The test element is the isolated first compressor stage of the DGEN-380 miniature jet engine (minijet). The disc has the shape of a hollow truncated cone with large blades. Vibration measurements were carried out in a non-contact manner using a scanning Doppler vibrometer. The measurement was made in 1D and 3D mode. The 1D mode is simpler and easier to prepare. In 3D mode, the calibration of three scanning heads significantly complicates the measurement preparation, but allows researchers to obtain the deformation in three-dimensional space The summary shows the measured frequencies using both modes. The shapes of deformation are also summarized. It is described how close the 1D measurement is to the 3D mode and in what frequency range. Finally, it is shown to what extent it is possible to describe the nature of structural oscillations in the 1D measurement mode. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 2828 KB

Open AccessProceeding Paper

Lider Project–Bus Techno Brick: Sustainable Bumper for a Helicopter by Polycarbonate

by Eduardo Javier Martín, Juan Manuel Jiménez García and Dario Crespo Molera

Eng. Proc. 2026, 133(1), 190; https://doi.org/10.3390/engproc2026133190 - 4 Jun 2026

Viewed by 158

Abstract

Polycarbonate is a thermoplastic material well known for its high impact resistance and thermal stability, making it a strong candidate for non-structural aerospace applications. Within the framework of the LIDER project for the techno brick BUS, the behavior of polycarbonate has been experimentally [...] Read more.

Polycarbonate is a thermoplastic material well known for its high impact resistance and thermal stability, making it a strong candidate for non-structural aerospace applications. Within the framework of the LIDER project for the techno brick BUS, the behavior of polycarbonate has been experimentally assessed under critical conditions, aiming to validate its potential use in a future tail bumper design for helicopters. The experimental campaign included high strain rate impact tests, ageing tests to evaluate water absorption effects, and high-temperature exposure to assess thermal performance. The results of these tests form the core of this study, demonstrating the material’s capabilities and limitations under operationally relevant conditions. These findings aim to support the development of lightweight and robust non-structural components in aerospace systems. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 3147 KB

Open AccessProceeding Paper

Modelling of a Rotor Blade with Piezoelectric MFC Actuators

by Andrejs Kovalovs

Eng. Proc. 2026, 133(1), 191; https://doi.org/10.3390/engproc2026133191 - 4 Jun 2026

Viewed by 157

Abstract

A numerical study was conducted to investigate the effect of embedded piezoelectric actuators integrated into the skin of a model-scale BO105 rotor blade on its torsional behaviour. The analysis was performed for blades with different combinations of spar and skin materials, including UD [...] Read more.

A numerical study was conducted to investigate the effect of embedded piezoelectric actuators integrated into the skin of a model-scale BO105 rotor blade on its torsional behaviour. The analysis was performed for blades with different combinations of spar and skin materials, including UD GFRP and UD CFRP composites. Four finite element models of the helicopter blade were developed in ANSYS 16.0. The piezoelectric response of the MFC (Smart Material Corp., Sarasota, FL, USA) actuators was simulated using a thermal analogy approach. The effects of actuator placement, as well as the selection of spar and airfoil skin materials, on the torsion angle and structural characteristics of the blade were analysed. The largest torsional angle was obtained for rotor blade configurations equipped with MFC actuators and manufactured entirely from UD GFRP composites. The spar material did not affect the torsional angle. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 3021 KB

Open AccessProceeding Paper

Improving Pilot Situational Awareness Using a Gaze-Based Assisted Adaptive Interface

by Eleftheria Lito Michanetzi, Angelos Fotopoulos, Dimosthenis Minas and Michalis Xenos

Eng. Proc. 2026, 133(1), 192; https://doi.org/10.3390/engproc2026133192 - 5 Jun 2026

Viewed by 187

Abstract

Modern flight decks incorporate advanced automation and real-time data systems to improve safety and efficiency. However, maintaining situational awareness under a high workload remains a critical challenge, particularly when attentional resources are stretched. This study investigates how adaptive interfaces, using real-time eye-tracking data, [...] Read more.

Modern flight decks incorporate advanced automation and real-time data systems to improve safety and efficiency. However, maintaining situational awareness under a high workload remains a critical challenge, particularly when attentional resources are stretched. This study investigates how adaptive interfaces, using real-time eye-tracking data, can help pilots maintain their concentration and stay aware of all indications on large-area displays. To this end, we developed a gaze-responsive display that monitors whether the pilot has visually focused on objects displayed on a moving map. When the system detects that the pilot has not noticed an object on the map, it automatically adjusts the interface, highlighting the missed object, thus helping to prevent critical information from being overlooked. The interface was evaluated in a controlled simulation study with 34 participants. By capturing pilots’ gaze behaviour, the system reveals how attention shifts under workload and how adaptive visual cues can complement natural scanning patterns. Participant feedback indicated that adaptive behaviour provided supportive guidance without imposing additional cognitive load. Overall, the study highlights the potential of adaptive gaze-based interfaces to enhance attention strategies and contribute to more resilient situational awareness in aviation. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 2295 KB

Open AccessProceeding Paper

Preliminary Study of the Small Personal Helicopter Intended for Operation in Martian Conditions

by Jakub Kocjan, Robert Rogólski and Łukasz Kiszkowiak

Eng. Proc. 2026, 133(1), 193; https://doi.org/10.3390/engproc2026133193 - 8 Jun 2026

Viewed by 118

Abstract

This study extends a research program exploring innovative rotorcraft design methods, drawing on recent parametric modeling work at the Military University of Technology. Its goal is to assess the feasibility of a rotorcraft capable of operating on Mars—performing vertical takeoff, flight, and landing; [...] Read more.

This study extends a research program exploring innovative rotorcraft design methods, drawing on recent parametric modeling work at the Military University of Technology. Its goal is to assess the feasibility of a rotorcraft capable of operating on Mars—performing vertical takeoff, flight, and landing; sustaining at least two hours of flight; and carrying a pilot plus a passenger or 100 kg of payload. Using atmospheric analysis and analytical performance models, several rotor configurations were evaluated. The results identify key challenges and opportunities and present a conceptual Mars rotorcraft design, outlining its mission potential and directions for future development. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 5810 KB

Open AccessProceeding Paper

Prototyping and Testing System Interconnect Standard Interoperable for Orbital Services

by Raphaël Boissonnade, Come Berger, Montserrat Diaz-Carrasco, Ana Luisa Ruiz-Perez, Mathieu Deremetz, Pierre Letier, Thomas A. Schervan, Christopher Zeis, Mehmed Yüksel, Wiebke Brinkmann, Utku Akinci, Fabien Marty and Matisse Briand

Eng. Proc. 2026, 133(1), 194; https://doi.org/10.3390/engproc2026133194 - 15 May 2026

Viewed by 80

Abstract

The orbital space ecosystem is undergoing significant change, with numerous initiatives focused on in-orbit services, assembly, and manufacturing. These initiatives are being developed globally, with ongoing studies in America, Asia, and Europe. As these technologies evolve, questions arise about their compatibility and interoperability, [...] Read more.

The orbital space ecosystem is undergoing significant change, with numerous initiatives focused on in-orbit services, assembly, and manufacturing. These initiatives are being developed globally, with ongoing studies in America, Asia, and Europe. As these technologies evolve, questions arise about their compatibility and interoperability, especially for long-term in-orbit operations. The Space USB project addresses these challenges by aiming to connect European partners involved in the emerging interconnection systems market for in-orbit services. Its goal is to improve the compatibility and interoperability of these systems across Europe, with perspectives for broader international application. As part of this project, a prototype has been developed to connect with the interconnection systems of three European partners. A test campaign was conducted to assess the prototype’s functionality, using a robotic system. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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12 pages, 2233 KB

Open AccessProceeding Paper

Structural Assessment of a Compact Offset Strip Fin Heat Exchanger for Hydrogen Fuel Cell Electric Aircraft

by Sahil Bhapkar, Siddharth Patkar, Markus Kober and Stefan Kazula

Eng. Proc. 2026, 133(1), 195; https://doi.org/10.3390/engproc2026133195 - 10 Jun 2026

Viewed by 153

Abstract

Hydrogen fuel cells offer strong potential for decarbonizing aviation, yet their megawatt-scale integration is limited by thermal management system (TMS) challenges. In low-temperature Proton Exchange Membrane Fuel Cell (PEMFC) systems, the heat exchanger (HEX) is the key TMS component influencing thermal efficiency, mass, [...] Read more.

Hydrogen fuel cells offer strong potential for decarbonizing aviation, yet their megawatt-scale integration is limited by thermal management system (TMS) challenges. In low-temperature Proton Exchange Membrane Fuel Cell (PEMFC) systems, the heat exchanger (HEX) is the key TMS component influencing thermal efficiency, mass, and reliability. While prior work has focused on thermo-hydraulic optimization, structural behavior under flight conditions remains insufficiently addressed. This study introduces a coupled CFD–FEA methodology for a nacelle-integrated, megawatt-class plate–fin HEX. The model captures the effects of non-uniform thermal loads, constrained thermal expansion, and dynamic excitation. Local flow-induced vibrations are assessed through pre-stressed modal analysis, and global dynamic behavior is predicted using a homogenized approach. Results show that thermally induced stresses dominate over pressure loads, and the introduction of coolant-fin geometries with suitable expansion tolerances mitigates stress and resonance risks. The approach provides design guidance for structurally robust, vibration-tolerant, and aero-thermally efficient HEXs for next-generation PEMFC-powered aircraft. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 2078 KB

Open AccessProceeding Paper

Traceable Intercorporation Data Exchange and Processing Using a Graph-Based Infrastructure

by Paula Ruß, Gerald Schegk, Deoclécio Valente, Jonas Jepsen, Malte Christian Struck, Oliver Bertram, Frank Dressel and Arthur Zamfir

Eng. Proc. 2026, 133(1), 196; https://doi.org/10.3390/engproc2026133196 - 11 Jun 2026

Viewed by 129

Abstract

Designing an aircraft requires multidisciplinary analysis and data processing abilities, which are often spread over various partners. Effective collaboration across organisational boundaries is difficult, but essential. As the aerospace industry becomes increasingly digitalised, ever larger volumes of data and models must be exchanged. [...] Read more.

Designing an aircraft requires multidisciplinary analysis and data processing abilities, which are often spread over various partners. Effective collaboration across organisational boundaries is difficult, but essential. As the aerospace industry becomes increasingly digitalised, ever larger volumes of data and models must be exchanged. Heterogeneous tools, data formats, and infrastructures make it difficult to exchange data and to trace it. We propose using semantic graphs for data exchange to ensure interoperability, while semantic links between data models facilitate multidisciplinary and cross-organisational collaboration. Furthermore, our approach captures comprehensive metadata that describes the creation and modification of each dataset, thereby establishing a fully traceable data provenance chain. We demonstrate its functionality via a design process for an electromechanical actuator (EMA) given requirements from a different stakeholder (simulated). Having the requirements and the EMA models translated in Resource Description Framework (RDF) graphs, we are able to create links between them. This then enables the EMA model to be automatically re-evaluated when requirements change, ensuring that it complies with them. For the data exchange, we use the DLR SemanticHub, which utilises a graph database. By providing traceability of the data results provided in different data formats and the data origins, we enable transparency and accountability across organisational boundaries, which is important for trusted collaboration and compliance in intercorporational data exchange. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 800 KB

Open AccessProceeding Paper

Modeling and Simulation of a Distributed-Electric Propulsion System with PROOSIS

by Maria Aranda Rosales and Luis Sánchez de León

Eng. Proc. 2026, 133(1), 197; https://doi.org/10.3390/engproc2026133197 - 11 Jun 2026

Viewed by 164

Abstract

This paper presents a concise modeling and simulation study of a turboelectric distributed propulsion (TeDP) system for a hybrid wing body (HWB) aircraft. A whole-system 0D model has been implemented in PROOSIS that includes the thermodynamic model of the turboshaft and fan array, [...] Read more.

This paper presents a concise modeling and simulation study of a turboelectric distributed propulsion (TeDP) system for a hybrid wing body (HWB) aircraft. A whole-system 0D model has been implemented in PROOSIS that includes the thermodynamic model of the turboshaft and fan array, as well as an electrical subsystem model addressing generators, motors, and cryogenic cooling for high-temperature superconducting (HTS) machines. Boundary layer ingestion (BLI) was explicitly modeled in the inlet–fan interaction. Parametric studies explored control strategies that minimized fuel consumption across the flight envelope. The design and off-design analyses demonstrated that coupling BLI with distributed fans can deliver significant aerodynamic benefits, while the integrated mission simulation highlighted the system-level implications of electrical conversion and control and quantified potential fuel savings. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 3496 KB

Open AccessProceeding Paper

A Multi-Disciplinary Approach to Concurrent Aero-Structural and On-Board System Design for a Distributed Propulsion HER Configuration

by Simone Mancini, Tim Klaproth, Reinhold Maierl, Ögmundur Petersson, Jean-Christophe Giret and Sylvain Béchet

Eng. Proc. 2026, 133(1), 198; https://doi.org/10.3390/engproc2026133198 - 12 Jun 2026

Viewed by 145

Abstract

This study investigates the integration of hybrid-electric distributed propulsion (DEP) systems in aviation to improve environmental sustainability. It aims to develop practical and integrated aircraft solutions by addressing the architectural complexity of hybrid-electric systems through a concurrent design approach. This approach is crucial [...] Read more.

This study investigates the integration of hybrid-electric distributed propulsion (DEP) systems in aviation to improve environmental sustainability. It aims to develop practical and integrated aircraft solutions by addressing the architectural complexity of hybrid-electric systems through a concurrent design approach. This approach is crucial due to the strong interdependence between aircraft performance and the size of the hybridized propulsion system. The research utilizes a multi-disciplinary Design and Optimisation (MDO) framework, built around GEMSEO, to support aero-structural and system design for a hybrid-electric regional aircraft configuration. The framework combines aerodynamics, structural, and on-board system design using a multi-fidelity approach, facilitating the integration of different design disciplines. Key findings highlight the sensitivity of overall aircraft design to on-board system sizing. We conclude that a concurrent MDO design approach effectively captures the sensitivity of the design to on-board systems sizing. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 36201 KB

Open AccessProceeding Paper

Pre-Experimental Aerodynamic Design Study for a High-Lift Wing FSI Benchmark Model Using the Lattice Boltzmann Method

by Malav Soni, Roland Ewert, Christian Jente and Jan Delfs

Eng. Proc. 2026, 133(1), 199; https://doi.org/10.3390/engproc2026133199 - 16 Jun 2026

Cited by 1 | Viewed by 121

Abstract

A numerical design study is carried out to support the setup of a wind tunnel experiment for the flap cover seal, which will serve as a benchmarking reference database for Fluid–Structure Interaction (FSI) in aeronautics. To this end, 3-D scale-resolving unsteady Large Eddy [...] Read more.

A numerical design study is carried out to support the setup of a wind tunnel experiment for the flap cover seal, which will serve as a benchmarking reference database for Fluid–Structure Interaction (FSI) in aeronautics. To this end, 3-D scale-resolving unsteady Large Eddy Simulation (LES) with the Lattice Boltzmann Method (LBM) is carried out using the simulation software ProLB. A new aerodynamic layout for the chosen F15LS (Large-Scale) high-lift wing model is established to fit the high-lift wing in the DLR-AWB tunnel. The design process involves variations in the leading-edge nose contour’s streamwise length and camber lines (inducing a negative S-shape) to reduce the leading-edge suction peak, thereby lowering the absolute lift while preserving the flap operating conditions. Initial simulations utilize a simplified periodic LES slice and a theory of the method of images to model wind tunnel jet flow deflection, culminating in a full-span 3-D WM-LES-LBM simulation of the entire wind tunnel installation, including free shear layers, to confirm the designed performance of the modified F15LS. This simulation serves to make informed decisions on model settings such as the boundary layer fence and model-nozzle distance. The successful experimental validation of critical performance characteristics, including angle-of-attack requirements and flow deflection, confirms the fidelity of the pre-test WM-LES-LBM evaluation. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 2983 KB

Open AccessProceeding Paper

Complex-Valued Data Partition for the Modal Analysis of a Fighter Jet via the Loewner Framework

by Mikel Janices Chamizo, Gabriele Dessena, Marco Civera and Oscar E. Bonilla-Manrique

Eng. Proc. 2026, 133(1), 200; https://doi.org/10.3390/engproc2026133200 - 18 Jun 2026

Viewed by 160

Abstract

This work examines a complex-valued data partition within the improved Loewner Framework to enhance the efficiency of modal parameter identification for aerospace structures. The method is applied to the General Dynamics F-16 Ground Vibration Test dataset, assessing accuracy and computational performance against the [...] Read more.

This work examines a complex-valued data partition within the improved Loewner Framework to enhance the efficiency of modal parameter identification for aerospace structures. The method is applied to the General Dynamics F-16 Ground Vibration Test dataset, assessing accuracy and computational performance against the standard real-valued formulation. The complex-valued approach reduces execution time by an order of magnitude while preserving the quality of the identified poles. The extracted modal parameters align well with established benchmark results, confirming the suitability of the proposed formulation for reliable and scalable modal analysis of aircraft structures. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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8 pages, 1437 KB

Open AccessProceeding Paper

Structural Health Monitoring on Liquid Hydrogen Tanks for Aviation Using MEMS, Shape Memory Alloy Strain Sensor and H₂ Leakage Sensors

by Ray Saupe, Andrea Boehm, Roy Buschbeck, Daniel Buelz, Jörn Langenickel, Thomas Oehme, Remi Pantou, Bjoern Senf, Alexey Shaporin, Sven Voigt and Sebastian Weidlich

Eng. Proc. 2026, 133(1), 201; https://doi.org/10.3390/engproc2026133201 (registering DOI) - 24 Jun 2026

Viewed by 100

Abstract

The aviation industry is adopting liquid hydrogen (LH₂) for sustainable flight, requiring robust safety systems. This work is an example of adaptation of a Micro-Electro-Mechanical Systems (MEMS)-based structural health monitoring (SHM) system for LH₂ tanks, developed in the H2ELIOS project. [...] Read more.

The aviation industry is adopting liquid hydrogen (LH₂) for sustainable flight, requiring robust safety systems. This work is an example of adaptation of a Micro-Electro-Mechanical Systems (MEMS)-based structural health monitoring (SHM) system for LH₂ tanks, developed in the H2ELIOS project. It uses a multisensor approach that combines MEMS sensors to monitor vibration and acceleration, shape memory alloy (SMA) strain sensors for measuring tank expansion, and hydrogen leakage sensors to prevent false alarms. This SHM technology detects cracks and delamination of material and coating, enabling predictive maintenance via digital twins and ensuring structural integrity. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 725 KB

Open AccessProceeding Paper

Evaluation of an AI-Aided Document Framework for Certification of Novel Aircraft Propulsion Systems

by Sebastian Stoppa, Durga Sri Sharan Katabathula and Robin Frank

Eng. Proc. 2026, 133(1), 202; https://doi.org/10.3390/engproc2026133202 (registering DOI) - 25 Jun 2026

Viewed by 108

Abstract

In contrast to the development of conventional civil aircraft propulsion systems, novel propulsion technology or non-standard energy sources disclose a lack of flexibility in the current aviation certification framework. Additionally, aircraft certification in 2025 relies heavily on manual effort, causing major difficulties in [...] Read more.

In contrast to the development of conventional civil aircraft propulsion systems, novel propulsion technology or non-standard energy sources disclose a lack of flexibility in the current aviation certification framework. Additionally, aircraft certification in 2025 relies heavily on manual effort, causing major difficulties in maintaining the traceability of data across vast sets of regulation documents. One promising solution to overcome such challenges is offered by the field of artificial intelligence (AI), particularly large language models (LLMs). This paper introduces an AI-aided framework designed to streamline the certifiability of novel aircraft propulsion systems. To meet the AI trustworthiness demands set by the European Union Aviation Safety Agency (EASA), the framework proposes a concept for achieving data and model transparency in machine learning (ML) applications. To address the demand for data transparency, aviation regulatory context data will be unified and stored in a Unified Regulations Database (URD). This unified data is classified and enriched with related information for ML purposes. The URD enables the creation of modern, transparent AI features for civil aircraft certification. This AI-aided framework will enable certification measures for the development and allows for certifiability checks for novel aircraft technologies. Both the aviation industry and regulatory authorities may equally benefit from the existence of the URD as a starting point for certifying AI features. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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9 pages, 2994 KB

Open AccessProceeding Paper

Characterizing Fatigue Delamination Growth in Multidirectional CFRP Laminates

by Davide Biagini, Francisco Monticeli, Yasmine Mosleh and John-Alan Pascoe

Eng. Proc. 2026, 133(1), 203; https://doi.org/10.3390/engproc2026133203 (registering DOI) - 26 Jun 2026

Viewed by 92

Abstract

Despite the popularity of multidirectional laminates in many fatigue-prone design applications, there is still little understanding of how the adjacent plies’ fibre orientation affects interfacial crack (delamination) fatigue propagation. To expand our knowledge on this matter, we present a systematic experimental investigation of [...] Read more.

Despite the popularity of multidirectional laminates in many fatigue-prone design applications, there is still little understanding of how the adjacent plies’ fibre orientation affects interfacial crack (delamination) fatigue propagation. To expand our knowledge on this matter, we present a systematic experimental investigation of the delamination growth behaviour for different interfaces and under different opening modes. In mode I, off-axis plies (as in 90//0 and 45//0 interfaces) increase the effects of fibre bridging, shifting the Paris curves to higher strain energy release rates (SERR), and thus making the 0//0 results (highly) conservative. Instead, in the presence of mixed mode, the Paris curves of 0//0 interfaces were not conservative in case of low SERR and low crack growth rates. These effects need to be accounted for when predicting the fatigue behaviour of a multidirectional laminate. Full article

(This article belongs to the Proceedings of The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”)

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