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Eng. Proc., 2026, IOCAE 2026

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22 pages, 2261 KB  
Proceeding Paper
Physics-Regularized Transfer Learning for Cross-Alloy Generalization in Aerospace Additive Manufacturing
by Aswin Karkadakattil
Eng. Proc. 2026, 142(1), 1; https://doi.org/10.3390/engproc2026142001 - 3 Jun 2026
Viewed by 715
Abstract
Additive manufacturing (AM) is increasingly used in aerospace applications; however, most machine-learning (ML) models remain alloy-specific and require retraining when applied to new materials. To address this limitation, this study proposes a Physics-Regularized Transfer Learning (Physics-TL) framework for cross-alloy prediction in additive manufacturing. [...] Read more.
Additive manufacturing (AM) is increasingly used in aerospace applications; however, most machine-learning (ML) models remain alloy-specific and require retraining when applied to new materials. To address this limitation, this study proposes a Physics-Regularized Transfer Learning (Physics-TL) framework for cross-alloy prediction in additive manufacturing. A neural network was first trained using Ti-6Al-4V as a source alloy and subsequently adapted to AlSi10Mg and 316L stainless steel using approximately 40 samples per alloy. Physics-based descriptors, including volumetric energy density and thermal diffusivity, were incorporated through a regularized loss function to improve physical consistency and data efficiency. The proposed framework was compared with a baseline neural network trained without transfer learning or physics-based constraints. Across repeated randomized train–test evaluations, the Physics-TL model achieved lower prediction errors, improved training stability, and better agreement with physically meaningful process–property relationships. Additional dataset sensitivity, ablation, and training–validation analyses provided supporting evidence of stable learning behaviour under limited-data conditions. Although the study is limited by dataset size and should be regarded as a proof-of-concept investigation, the results demonstrate the feasibility of combining transfer learning with physics-guided learning to support cross-alloy knowledge transfer in additive manufacturing. The proposed framework offers a promising pathway toward more data-efficient and physically informed predictive modelling for aerospace material qualification, process optimization, and future multi-material manufacturing systems. Full article
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14 pages, 61276 KB  
Proceeding Paper
SMART Hawk: A Shape-Morphing Artificial Red-Tailed Hawk
by Peter L. Bishay, Leo Haroutoonian, Victoria Bures, Caleb Wilmarth, Chaya Rubinstein, Arman Geghamyan, Gustavo Vela, Nico Alexander, Evelyn Herrera, Christian Guerrero, Cassidy Lai, Angelina Argott, Rogelio Banales, Johnathon Moore, Alicia Schwartz, Levon Ananyan, Adrian Gutierrez Corral and John Cannon
Eng. Proc. 2026, 142(1), 2; https://doi.org/10.3390/engproc2026142002 - 5 Jun 2026
Viewed by 822
Abstract
Birds actively modulate their wing and tail morphologies to achieve high aerodynamic efficiency and maneuverability, enabling long-duration gliding while retaining the ability to execute rapid maneuvers. Innovations in aircraft design and control are increasingly inspired by these avian flight characteristics through control surfaces [...] Read more.
Birds actively modulate their wing and tail morphologies to achieve high aerodynamic efficiency and maneuverability, enabling long-duration gliding while retaining the ability to execute rapid maneuvers. Innovations in aircraft design and control are increasingly inspired by these avian flight characteristics through control surfaces that imitate the natural wing and tail movements of birds. This paper presents a non-flapping, unmanned aerial vehicle (UAV), called “SMART Hawk” (Shape-Morphing Artificial Red-Tailed Hawk), inspired by the flight and physical characteristics of Buteo jamaicensis, known as the Red-Tailed Hawk (RTH), which exhibits excellent soaring abilities and agility characteristic of birds of prey. To determine the design parameters required for flight, a mathematical model was developed in MachUpX, then validated and refined using Reynolds-averaged computational fluid dynamics (CFD) models in ANSYS Fluent. SMART Hawk incorporates biomimetic wing and tail morphing, including coordinated forward sweep of the mid-wing and aft sweep of the outer wing, as well as active tail pitch, roll, and feather tucking and expansion. The drone was manufactured from a combination of composite, wood, and 3D-printed components. Multiple flight tests were conducted with proof-of-concept prototypes to demonstrate the design’s effectiveness. Full article
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10 pages, 3249 KB  
Proceeding Paper
Analytical Prediction of Propeller Thrust for Lift-Plus-Cruise Tilt-Rotor Configurations with Wind Tunnel Validation
by Néstor Alcañiz-Brull, Pau Varela, Jorge García-Tíscar and Luis Miguel García-Cuevas
Eng. Proc. 2026, 142(1), 3; https://doi.org/10.3390/engproc2026142003 - 17 Jun 2026
Viewed by 552
Abstract
Continuous population growth will lead to further expansion and densification of urban environments. In this context, Urban Air Mobility (UAM) has emerged as a new transportation solution through the use of Vertical Take-Off and Landing (VTOL) aircraft, more precisely, configurations such as lift-plus-cruise [...] Read more.
Continuous population growth will lead to further expansion and densification of urban environments. In this context, Urban Air Mobility (UAM) has emerged as a new transportation solution through the use of Vertical Take-Off and Landing (VTOL) aircraft, more precisely, configurations such as lift-plus-cruise tilt-rotors. During the conceptual design phase, propeller design methodologies commonly reported in the literature rely on vortex-based approaches or actuator disk theory. However, the accuracy of these methods strongly depends on the inflow angle and operating conditions. This paper introduces an analytical model to predict propeller thrust at a 90° inflow angle (edgewise flight), based on a correction of the thrust under axial flight conditions and the propeller geometry evaluated at 75% span. The approach relies on local velocity and angle of attack estimations derived from classical Blade Element Momentum Theory (BEMT) with an additional correction to account for stall effects at high angles of attack. This capability is particularly relevant for modeling lift-plus-cruise tilt-rotor configurations cruise phase during early design stages while maintaining minimal computational cost. The proposed model is validated against wind tunnel measurements for several propellers tested at different global pitch angles, varying from 0 m/s to 9.1 m/s of windspeed and 1300 to 6200 rpms, demonstrating the applicability of the developed formulation for blades with twist angles up to 16°. Full article
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9 pages, 2732 KB  
Proceeding Paper
Multi-Level Aircraft Design Modelling Including the Effects of Disruptive Propulsion Technologies on Environmental Impact
by Oleksandr Zaporozhets
Eng. Proc. 2026, 142(1), 4; https://doi.org/10.3390/engproc2026142004 - 22 Jun 2026
Viewed by 207
Abstract
The EU EFACA project considers two conceptual aircraft design configurations for cleaning European air traffic in future decades. Recently, several different technologies have led to propulsion designs with potential to reduce greenhouse gas emissions and replace existing conventional engine technologies—such as the use [...] Read more.
The EU EFACA project considers two conceptual aircraft design configurations for cleaning European air traffic in future decades. Recently, several different technologies have led to propulsion designs with potential to reduce greenhouse gas emissions and replace existing conventional engine technologies—such as the use of fossil fuel—for aviation. The results of an assessment of the environmental impacts of new technologies are considered using a multidimensional approach, ranging from aircraft certification requirements (noise, local and global engine emission, and aircraft fuel efficiency) to regional/global assessments of new designs in air traffic. Each technology for factor reduction is simulated and compared to a reference, usually the aircraft currently best in its class, providing the possibility of assessing the efficiency of the technology, both for necessary certification requirements and for the forecasted operational conditions due to ICAO long-term aspirational goals and ACARE Fly Green Deal goals. Full article
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12 pages, 5743 KB  
Proceeding Paper
A Geometry-Aware MPC-Inspired Predictive Control Framework for UAVs Using a Two-Manifold-Based Representation
by Yuvaraj George and Mani Sankar Kadali
Eng. Proc. 2026, 142(1), 5; https://doi.org/10.3390/engproc2026142005 - 29 Jun 2026
Viewed by 495
Abstract
UAVs operating in cluttered and dynamic environments face limitations when controlled using conventional Euclidean frameworks, which leads to degraded performance during aggressive maneuvers. This paper presents a geometry-aware predictive control framework for multirotor UAVs based on a two-manifold-inspired representation of actuator geometry. The [...] Read more.
UAVs operating in cluttered and dynamic environments face limitations when controlled using conventional Euclidean frameworks, which leads to degraded performance during aggressive maneuvers. This paper presents a geometry-aware predictive control framework for multirotor UAVs based on a two-manifold-inspired representation of actuator geometry. The proposed control strategy adopts an MPC-inspired prediction structure without solving a full online optimization problem. A comparative simulation study is conducted in MATLAB/Simulink under identical mission, obstacle, and noise conditions for both the conventional point-mass controller and the proposed two-manifold-based controller. Performance is evaluated in terms of trajectory tracking accuracy and control effort. Results indicate that the proposed framework achieves modest improvements in tracking accuracy and produces smoother control inputs compared to the point-mass model. It suggests that geometry-aware representations may enhance predictive control performance in obstacle-rich environments, although further validation under diverse scenarios is required. Full article
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14 pages, 5319 KB  
Proceeding Paper
Experimental Study of Cryogenic Fill-Level Sensors for Liquid-Hydrogen Aircraft Applications
by Adrian Josua Orlando Winter, Yannick Pott and Kay Kochan
Eng. Proc. 2026, 142(1), 6; https://doi.org/10.3390/engproc2026142006 - 29 Jun 2026
Viewed by 629
Abstract
The safe and accurate measurement of liquid hydrogen (LH2) tank fill levels is a critical enabling technology for the adoption of hydrogen as a sustainable aviation fuel. Although LH2 fill level measurement techniques have been applied in industrial, automotive, and [...] Read more.
The safe and accurate measurement of liquid hydrogen (LH2) tank fill levels is a critical enabling technology for the adoption of hydrogen as a sustainable aviation fuel. Although LH2 fill level measurement techniques have been applied in industrial, automotive, and space applications, no system has yet been validated at the scale, robustness, and precision required for modern aircraft Fuel Quantity Indication Systems (FQIS). Differentialpressure sensors are commonly employed in industrial cryogenic systems and hydrogen refueling stations; however, their accuracy is strongly influenced by dynamic effects such as filling transients and liquid sloshing, rendering them unsuitable for aviation-grade FQIS requirements which call for high accuracy and reliability. While simulations and analytical studies propose alternative LH2 level sensing concepts, experimental validation and direct comparative assessments of different sensor architectures remain scarce. Furthermore, although several manufacturers offer LH2 fill-level sensors, the stated measurement accuracies have not been independently verified, highlighting the need for systematic experimental investigation under representative operating conditions. A complete evaluation of an LH2 FQIS requires testing under anticipated flight conditions, including accelerations, varying attitudes, vibrations, dynamic sloshing, and long-term cycling. As a preliminary investigation, this work experimentally evaluates five liquid level sensing concepts based on measurements of dielectric constant, thermal capacity, and optical absorption properties using liquid nitrogen (LN2) as a representative surrogate for LH2 under quasi-static conditions. The results demonstrate that optical absorption-based sensors in the near-infrared spectrum are unsuitable for LH2 and LN2 liquid level measurement. In contrast, capacitive probes and resistive thermal devices (RTDs) exhibit robust and repeatable performance under cryogenic conditions, demonstrating measurement resolutions of better than 5.1mm. These findings provide experimentally grounded guidance for the development of future LH2-compatible FQIS architectures for aviation applications. Full article
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7 pages, 1012 KB  
Proceeding Paper
Numerical Analysis of Boundary Layer Ingestion for Electrified Aft-Fuselage Propulsion
by Siddharth M., Neha Sandeep Naidu and Parthasarathy Vasanthakumar
Eng. Proc. 2026, 142(1), 7; https://doi.org/10.3390/engproc2026142007 - 3 Jul 2026
Viewed by 463
Abstract
Boundary Layer Ingestion (BLI) is a propulsion integration concept that improves aircraft efficiency by recovering wake momentum deficit and reducing propulsive power requirements. In this study, a numerical methodology is created to study electrified aft-fuselage BLI on a simplified A320 aircraft model across [...] Read more.
Boundary Layer Ingestion (BLI) is a propulsion integration concept that improves aircraft efficiency by recovering wake momentum deficit and reducing propulsive power requirements. In this study, a numerical methodology is created to study electrified aft-fuselage BLI on a simplified A320 aircraft model across multiple operating conditions. Three configurations were developed: a baseline aircraft, a cruciform-tail configuration in OpenVSP and CFD simulations performed in ANSYS Fluent 2025 R2 using the Spalart–Allmaras turbulence model. The results demonstrate reduced drag, improved lift-to-drag ratio, and a Power Saving Coefficient (PSC) of approximately 5–14%, highest during cruise, climb, and descent conditions at higher altitudes. Full article
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9 pages, 2011 KB  
Proceeding Paper
Design-Oriented Multi-Load Stiffness Assessment of Composite Aircraft Panels Through Pareto-Based Evaluation
by Dimitrios G. Stamatelos
Eng. Proc. 2026, 142(1), 8; https://doi.org/10.3390/engproc2026142008 - 6 Jul 2026
Viewed by 189
Abstract
Composite aircraft panels are subjected to combined mechanical and thermal loading conditions requiring assessment approaches beyond conventional single-load stiffness evaluation. A design-oriented finite element framework is presented for the comparative assessment of symmetric composite laminate configurations under compression, pressure, and thermal loading. Normalized [...] Read more.
Composite aircraft panels are subjected to combined mechanical and thermal loading conditions requiring assessment approaches beyond conventional single-load stiffness evaluation. A design-oriented finite element framework is presented for the comparative assessment of symmetric composite laminate configurations under compression, pressure, and thermal loading. Normalized stiffness metrics derived from displacement-based responses are combined with Pareto-based comparative interpretation, stiffness anisotropy indices, and robustness evaluation to identify laminate configurations exhibiting either specialized or balanced structural behavior. The results highlight the importance of trade-off-driven laminate selection during preliminary aircraft structural design. The proposed methodology provides a computationally efficient framework suitable for early-stage composite structural assessment and future extension toward stiffened panel applications. Full article
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13 pages, 4347 KB  
Proceeding Paper
Technological Advancements of Hybrid Rocket Engines for Sustainable and Competitive In-Space Propulsion Applications
by Ryan J. Thibaudeau, Stephen A. Whitmore, Jared Coen, Joshua Sorenson, Logan Mecham and Ava Wilkey
Eng. Proc. 2026, 142(1), 9; https://doi.org/10.3390/engproc2026142009 - 16 Jul 2026
Viewed by 1141
Abstract
Hybrid rocket engines (HREs), which pair a fluid oxidizer with a solid fuel, offer safety and handling advantages, can reduce environmental impact relative to selected legacy systems, and are capable of deep throttling and restart, making them strong candidates for “green” in-space propulsion [...] Read more.
Hybrid rocket engines (HREs), which pair a fluid oxidizer with a solid fuel, offer safety and handling advantages, can reduce environmental impact relative to selected legacy systems, and are capable of deep throttling and restart, making them strong candidates for “green” in-space propulsion applications. However, until very recently, there has not been any flight heritage of an HRE used in a spaceflight mission. Over the past decade, the Propulsion Research Laboratory at Utah State University (PRL-USU) has matured a portfolio of HRE technologies—low-energy arc ignition, digital throttling, additively manufactured sustainable fuels, the Nytrox green oxidizer, and electroplated thruster assemblies—that together address the historical barriers to spaceflight adoption. This paper summarizes that progress, describes two flight systems built upon it, and presents a roadmap for future applications. Full article
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8 pages, 2541 KB  
Proceeding Paper
Multi-Objective Material Selection Framework for Additively Manufactured Aircraft Wing Ribs
by Venkata Aditya Nag Mannepalli and Sudhir Sastry Yedla Bala
Eng. Proc. 2026, 142(1), 10; https://doi.org/10.3390/engproc2026142010 - 20 Jul 2026
Viewed by 231
Abstract
Aircraft wing ribs form the skeletal backbone of the wing. They maintain the aerodynamic profile and transfer structural loads from the skin to the spars. Conventional manufacturing processes struggle to produce complex geometries, making these components difficult and expensive to manufacture. Recent advances [...] Read more.
Aircraft wing ribs form the skeletal backbone of the wing. They maintain the aerodynamic profile and transfer structural loads from the skin to the spars. Conventional manufacturing processes struggle to produce complex geometries, making these components difficult and expensive to manufacture. Recent advances in additive manufacturing (AM) address these limitations. Additive manufacturing enables the production of complex geometries that significantly reduce weight. Most designers use the standard Ashby method to identify the strongest or lightest metal. However, they often overlook whether the material will behave as expected during additive printing. This research focuses on Multi-Objective Material Selection for the design of the additive manufacturability of aircraft wing ribs using aluminium-based alloys. A key innovation in this research is the formulation of hybrid performance indices (HPIs). These indices go beyond the traditional Ashby methodology. They mathematically couple structural efficiency metrics with a weighted Processability Factor. The structural metrics include specific density, stiffness, specific strength, and Embodied-Energy-Strength-to-Embodied-Energy Index. The Processability Factor accounts for local material availability, thermal conductivity, printability, recyclability and material cost. This dual evaluation assesses both structural integrity and manufacturing risk simultaneously. The process produces an Additive Pareto Optimal set of candidate materials. This helps engineers predict and prevent issues like warping and residual stress before printing begins. The framework also emphasises sustainability. It prioritises materials that minimise waste and considers embodied energy in the selection process. The framework identifies high-performance aluminium alloys that are specifically optimised for the additive manufacturing of aircraft wing ribs. It provides a definitive ranking based on their ability to withstand aerodynamic loads while remaining easy to print. This data-driven approach replaces trial and error with a clear selection matrix for the early design stage. It ensures that the chosen alloy is both structurally sound and manufacturable for aerospace applications. Full article
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15 pages, 902 KB  
Proceeding Paper
More TOPS, Less Mass: Compute-Density Metrics for Enabling Future AI Missions in Space
by Jeremiah Gayle and Josh Kalin
Eng. Proc. 2026, 142(1), 11; https://doi.org/10.3390/engproc2026142011 - 20 Jul 2026
Viewed by 413
Abstract
Onboard artificial intelligence (AI) is increasingly limited less by raw processor availability than by spacecraft-level integration constraints. Modern commercial edge-AI processors can provide orders of magnitude more inference capability than traditional spacecraft processors and, when normalized by spacecraft mass, CubeSat-class platforms can exhibit [...] Read more.
Onboard artificial intelligence (AI) is increasingly limited less by raw processor availability than by spacecraft-level integration constraints. Modern commercial edge-AI processors can provide orders of magnitude more inference capability than traditional spacecraft processors and, when normalized by spacecraft mass, CubeSat-class platforms can exhibit a very high compute density. This paper introduces compute density, expressed as operations per kilogram and paired with operations per watt, as a practical systems metric for comparing onboard AI capabilities across spacecraft classes. A representative 6U CubeSat case study is used to show that Jetson-class and space-adapted edge processors can enable computer vision, data triage, change detection, and autonomy workloads that were previously impractical on small spacecraft. However, compute density alone is incomplete: useful onboard AI capability is constrained by available power, thermal rejection, radiation tolerance, duty cycle, memory and data movement, and downlink strategy. This paper concludes that future AI spacecraft should be architected through compute power thermal communications co-optimization rather than by selecting the highest peak tera-operations-per-second (TOPS) processor. Full article
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9 pages, 6052 KB  
Proceeding Paper
Space Application of Austenitic Stainless Steels—DED Possibilities
by Svetlana Boshnakova
Eng. Proc. 2026, 142(1), 12; https://doi.org/10.3390/engproc2026142012 - 20 Jul 2026
Viewed by 700
Abstract
With contemporary advancements in additive manufacturing (AM), it has become possible to obtain hull structures for spacecraft made of relatively cheap materials. The possibility of substituting super-austenitic stainless steel Avesta SMO 254 X1NiCrMoCuN20-18-7 (EN 10088) for that already used in the Starship SpaceX [...] Read more.
With contemporary advancements in additive manufacturing (AM), it has become possible to obtain hull structures for spacecraft made of relatively cheap materials. The possibility of substituting super-austenitic stainless steel Avesta SMO 254 X1NiCrMoCuN20-18-7 (EN 10088) for that already used in the Starship SpaceX 304 L-Modified is focused on achieving better thermal stability and durability in extreme conditions. The Directed Energy Deposition Arc (DED-Arc) method for AM has enabled the production of high-strength-to-weight ratios. The aim is to engage low-cost material with treatment optimization to provide greater corrosion resistance and high yield and tensile strength. For the DED-Arc, a filler wire was selected for the welding source, Fronius TPS 400i. A simulation via the RoboDK Robot Development Kit for the FANUC ARC Mate 100ID10L is provided. Additional shot pining/vibration treatment is proposed for the finished structure, which can be a substitute for the cold-worked initial metal. A comparison is made for stainless steel that has already been tested for space travel. Regimes for the manufacturing process are proposed, with representative samples of Avesta SMO 254 obtained and tested using microhardness measurements, microcracking detection, porosity measurements, interface zone assessment, and microstructural analysis. The DED-Arc process can be applied to large-space shell manufacturing. A comparison is made with a focus on the mechanical and corrosion advantages. For Avesta SMO 254, microhardness measurements ranged from 235 to 246 HV1 and increased after treatment. The controlled parameters provided a maximum heat input of 0.7 KJ/mm, no defects, and a fine microstructure. The successful use of stainless steel with AM increases the potential for multiple space missions. The advanced method shows high quality, allows cost savings and provides extended service life. Full article
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8 pages, 1421 KB  
Proceeding Paper
Flight-Test-Based Analysis of Blowing Effects on Trimmed Aerodynamic Polars of a Distributed Electric Propulsion Aircraft Demonstrator
by Giorgio Filippoli, Beniamino M. Perri, Stefano Cacciola, Carlo E. D. Riboldi and Lorenzo Trainelli
Eng. Proc. 2026, 142(1), 13; https://doi.org/10.3390/engproc2026142013 - 23 Jul 2026
Viewed by 344
Abstract
Distributed Electric Propulsion (DEP) offers new opportunities for improving aircraft efficiency and control authority, but the strong interaction between propeller slipstreams and lifting surfaces makes aerodynamic behavior difficult to predict with conventional models. In particular, the effect of propeller blowing on trimmed aerodynamic [...] Read more.
Distributed Electric Propulsion (DEP) offers new opportunities for improving aircraft efficiency and control authority, but the strong interaction between propeller slipstreams and lifting surfaces makes aerodynamic behavior difficult to predict with conventional models. In particular, the effect of propeller blowing on trimmed aerodynamic characteristics must be assessed directly from flight data. An autonomous flight-test campaign was therefore conducted with the SwitchMaster, a six-propeller DEP demonstrator, using a TECS-based control architecture to acquire repeatable trim conditions over different advance ratio ranges. Identified longitudinal derivatives were used to reconstruct lift, drag and trimmed polar curves. The results show increased lift, reduced drag and improved aerodynamic efficiency in high-blowing, high-lift conditions, while highlighting nonlinear and non-monotonic aero-propulsive trends at intermediate propeller advance ratios. Full article
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9 pages, 2657 KB  
Proceeding Paper
A Unified Design Methodology for Unmanned Airships: From Preliminary Sizing to Lofting
by Carlo E.D. Riboldi and Luca Alessi
Eng. Proc. 2026, 142(1), 14; https://doi.org/10.3390/engproc2026142014 - 23 Jul 2026
Viewed by 135
Abstract
This research proposes a unified, modular method for the preliminary design of unmanned airships, bridging the gap between static balance and dynamic performance. While traditional algorithms focus solely on global parameters like mass and volume, this approach integrates three original, in-house assembled tools [...] Read more.
This research proposes a unified, modular method for the preliminary design of unmanned airships, bridging the gap between static balance and dynamic performance. While traditional algorithms focus solely on global parameters like mass and volume, this approach integrates three original, in-house assembled tools for preliminary sizing, lofting and inertial modeling, and dynamic analysis. By synergically combining these modules, the system automatically solves weight and volume requirements while optimizing internal mass distribution for static balance. Furthermore, it extracts a linearized dynamic model from non-linear physics to evaluate and enhance flying qualities, like damping and eigenmode characteristic times, demonstrating the optimal procedure using an existing prototype. Full article
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9 pages, 23760 KB  
Proceeding Paper
Analysis of the Interaction Mechanisms Between Rocket Exhaust Plume and Sea Surface in Maritime Launch Conditions
by Zhengxun Zhou, Yutao Tian, Zehan Chen, Pengji Li, Zeyu Cao, Sixing Guo and Dapeng Zhang
Eng. Proc. 2026, 142(1), 15; https://doi.org/10.3390/engproc2026142015 - 31 Jul 2026
Viewed by 439
Abstract
Existing studies mainly address single launch configurations and provide limited comparison across thrust levels, engine layouts, and launch altitudes. This study establishes a CFD framework coupling rocket dynamics, the VOF multiphase model, overset mesh, and dynamic mesh techniques to simulate three sub-scale offshore [...] Read more.
Existing studies mainly address single launch configurations and provide limited comparison across thrust levels, engine layouts, and launch altitudes. This study establishes a CFD framework coupling rocket dynamics, the VOF multiphase model, overset mesh, and dynamic mesh techniques to simulate three sub-scale offshore launch variants. Five transient stages are identified from free-jet development to plume detachment. The results show that jet stagnation pressure excavates a water cavity, promotes reverse entrainment of high-enthalpy gas near the rocket base, and produces configuration-dependent drag recovery. Type B requires a higher initial launch height to avoid strong plumewater coupling, whereas Types A and C allow lower preliminary height windows when drag benefit and thermal recirculation risk are balanced. Full article
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13 pages, 3222 KB  
Proceeding Paper
State-Based Estimation of Future Mission Capability for Degrading Unmanned Aerial Vehicles
by Max Weigert
Eng. Proc. 2026, 142(1), 16; https://doi.org/10.3390/engproc2026142016 - 4 Aug 2026
Viewed by 224
Abstract
Reliability assessment in complex technical systems often involves capturing the interdependency between multiple subsystems and the gradual loss of their functional effectiveness. This challenge becomes particularly critical in the context of Unmanned Aerial Vehicles (UAVs), where sustained operational capability is essential for the [...] Read more.
Reliability assessment in complex technical systems often involves capturing the interdependency between multiple subsystems and the gradual loss of their functional effectiveness. This challenge becomes particularly critical in the context of Unmanned Aerial Vehicles (UAVs), where sustained operational capability is essential for the safe execution of autonomous missions. This work presents a state-based methodology to estimate the future mission capability of UAVs subject to progressive component degradation. To generate a representative dataset, around 600 simulated flight missions for each of the 70 UAV fleet members are conducted, distinguished by randomly varying degradation profiles across multiple actuators. A hidden semi-Markov model (HSMM) is trained on this data to characterize the progressive reduction in system performance over time. To improve model tractability and generalization, raw flight data is first reduced to a concise set of performance-related parameters, from which critical sensor signals, such as roll, pitch, yaw, horizontal and vertical airspeeds, and current consumption, are estimated. The approach is evaluated in comparison to Decision Tree (DT) and XGBoost (XGB) models in a 5-fold cross-validation analysis. It enables the identification of system-wide dependencies between degradation patterns and mission-relevant behavior. By linking current operational states to the likelihood of meeting future performance requirements, it offers a quantitative basis for predictive reliability assessment. The best performance is achieved by an XGB model, whose mission capability estimation roughly doubles the number of conducted missions up to a failure by avoiding risky missions in comparison to unfiltered mission acceptance. Full article
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9 pages, 3547 KB  
Proceeding Paper
Wind Tunnel Investigation of Spoileron Effectiveness on a Low-Aspect-Ratio Swept Wing with Reflex Airfoils
by Riccardo Andrew Oggioni, Carlo Emanuele Dionigi Riboldi and Filippo Coacci
Eng. Proc. 2026, 142(1), 17; https://doi.org/10.3390/engproc2026142017 - 6 Aug 2026
Viewed by 183
Abstract
Politecnico di Milano is undergoing the design of a highly swept, low-aspect-ratio radio-controlled aircraft with reflex airfoils. This model is necessary to expand the automated flight-testing activities conducted inside the university, adding to the flying models a more unconventional one to verify the [...] Read more.
Politecnico di Milano is undergoing the design of a highly swept, low-aspect-ratio radio-controlled aircraft with reflex airfoils. This model is necessary to expand the automated flight-testing activities conducted inside the university, adding to the flying models a more unconventional one to verify the flight-testing technique implemented. Plain-type spoilerons were investigated as primary roll control devices and compared with conventional aerodynamic predictions and wind-tunnel data. The experimental tests assessed performance across spanwise and chordwise positions, angles of attack, and spoileron geometric variations. A normalized control effectiveness parameter, accounting for moment coefficient, spoileron surface area, and moment arm, was introduced to compare configurations. Results show consistent peak performance at intermediate incidence and highlight distinct degradation patterns near stall. Spanwise variations primarily affect roll authority, while yaw response remains weakly sensitive. Geometric analysis indicates span increases are more efficient than chord increases for equivalent performance, reducing actuator loads and aerodynamic penalties. Full article
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8 pages, 8071 KB  
Proceeding Paper
Impact-Induced Fracture in Additively Manufactured AlSi10Mg Using a Fractal Approach
by Md Salah Uddin
Eng. Proc. 2026, 142(1), 18; https://doi.org/10.3390/engproc2026142018 - 13 Aug 2026
Viewed by 263
Abstract
Additively manufactured AlSi10Mg aluminum alloy was investigated at two-layer build orientations: 0° and 90°. Impact-induced fractures were generated per the ASTM standard Charpy test. The resulting fracture surfaces were analyzed using the multi-image-based fractal analysis method. We used a digital microscope to analyze [...] Read more.
Additively manufactured AlSi10Mg aluminum alloy was investigated at two-layer build orientations: 0° and 90°. Impact-induced fractures were generated per the ASTM standard Charpy test. The resulting fracture surfaces were analyzed using the multi-image-based fractal analysis method. We used a digital microscope to analyze the fracture surface and examined compression, neutral, and tension zones on the surface. We found that the crack propagated symmetrically across the surface. The results showed that the compression zone has the lowest fractal dimension compared to the tension and neutral zones. The 0° orientation samples have a higher fractal dimension than the 90° orientation samples. Full article
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9 pages, 1664 KB  
Proceeding Paper
Autonomous Modeling Analytics for Space Ground Vehicles with Multidisciplinary System Design Framework
by Carlos C. Insaurralde
Eng. Proc. 2026, 142(1), 19; https://doi.org/10.3390/engproc2026142019 - 10 Aug 2026
Viewed by 99
Abstract
Aerospace engineering applications typically entail complex high-performance systems with sustainable safety. They are usually designed by multidisciplinary development teams where collaboration efficiency is undermined by the diversity of views (models) provided by the disciplines involved. This produces design deadlocks (augmenting risks and costs) [...] Read more.
Aerospace engineering applications typically entail complex high-performance systems with sustainable safety. They are usually designed by multidisciplinary development teams where collaboration efficiency is undermined by the diversity of views (models) provided by the disciplines involved. This produces design deadlocks (augmenting risks and costs) when crosschecking modeling representations to assess the impact of different models on each other to maintain system integrity. This paper presents details of the design process of a planetary rover in which diverse stakeholders deal with distinct aspects of the above space ground vehicle. It includes preliminary results from requirements analysis and system design that are used to interlink system models for an autonomous model crosschecking design process. The approach reduces collaborative design efforts by enabling multiple developers to minimize potential design inconsistencies by cross-relating their system models. Concluding remarks and future research are also presented. Full article
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17 pages, 2680 KB  
Proceeding Paper
Physics-Informed Operating Region Design of Dual Active Bridge Converters Under Thermal and ZVS Constraints for Spacecraft Electrical Power Systems
by Ahmed A. Hakim Mahmoud, Ibrahim Abdelsalam, Mostafa I. Marei and H.E.A. Ibrahim
Eng. Proc. 2026, 142(1), 20; https://doi.org/10.3390/engproc2026142020 - 7 Sep 2026
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Abstract
The dual active bridge (DAB) converter is one of the most common types of isolated bidirectional power converters in modern spacecraft EPS owing to its galvanic isolation, bidirectionality, soft switching, and good controllability. However, the goal of power transfer maximization often clashes with [...] Read more.
The dual active bridge (DAB) converter is one of the most common types of isolated bidirectional power converters in modern spacecraft EPS owing to its galvanic isolation, bidirectionality, soft switching, and good controllability. However, the goal of power transfer maximization often clashes with real-world spacecraft EPS constraints, namely thermal compliance, reliability, and the accuracy of simplified models used for analysis. This paper proposes a physics-informed methodology to derive the practical operating range under single phase shift (SPS) control based on a rigorous piecewise time-domain representation. From this model, the steady-state initial condition, general closed-form RMS current expression, ZVS boundary condition, and ZVS-aware loss model linked to the junction-temperature estimate are derived. The validity domain of the fundamental harmonic approximation (FHA) is evaluated against the exact model across the full (φ, k) space, and a two-dimensional operating map superposing power contours, the ZVS limit, and the thermal limit is presented. For the baseline case study at k = 1.0, the thermal constraint limits the nominal feasible upper phase shift to approximately 35°, while the broader 15–45° range remains useful for design assessment and operation toward 45° requires lower effective resistance and/or improved thermal management. The normalized SPS power-transfer curve retains the same shape under variations in L and fs, but RMS current, losses, and thermal feasibility must be reassessed for each converter design. The resulting closed-form framework provides a steady-state feasibility-evaluation tool for spacecraft EPS design and offers a computational basis for future supervisory constraint evaluation under varying voltage, load, and thermal conditions. Full article
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