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Eng. Proc., 2026, EASN 2025

The 15th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”

Madrid, Spain | 14–17 October 2025

Volume Editors:
Spiros Pantelakis, University of Patras, Greece
Andreas Strohmayer, University of Stuttgart, Germany
Gustavo Alonso, Universidad Politécnica de Madrid, Spain

Number of Papers: 124

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Cover Story (view full-size image): The EASN Conference Series, an annual event organized by the European Aerospace Science Network (EASN), is dedicated to advancing research, innovation, and collaboration in the field of aeronautics [...] Read more.

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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

Viewed by 332

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

Viewed by 251

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 273

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

Viewed by 218

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

Viewed by 171

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

Viewed by 185

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 431

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

Viewed by 254

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

Viewed by 183

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 472

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 304

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

Viewed by 184

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 287

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

Viewed by 150

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 186

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 418

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 303

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 431

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 254

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 235

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 278

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 228

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

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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

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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 399

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 226

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 189

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 427

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 271

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 221

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 294

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 152

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

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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 242

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

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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

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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 294

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

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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

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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

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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

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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 209

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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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

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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 270

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 243

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

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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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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 266

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 347

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 146

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

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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

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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 196

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

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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

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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

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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 242

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

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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 192

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

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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

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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 248

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 180

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

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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

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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 149

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

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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

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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 220

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

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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

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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 144

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 126

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 140

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

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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

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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

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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 120

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 110

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 193

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

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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

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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 125

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 106

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 142

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

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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

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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

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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

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

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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

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

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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 149

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 145

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

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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 79

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

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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

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

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

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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

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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

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 (registering DOI) - 11 May 2026

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

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

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

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

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

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 (registering DOI) - 13 May 2026

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 (registering DOI) - 13 May 2026

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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