0099
Cheng Chen¹, Zhiqiang Wan¹, Xiaozhe Wang¹
¹Beihang University, CN
Isogeometric Analysis (IGA) is capable to achieve exact geometry representation, higher-order continuity, and flexible refinement strategies, which holds significant importance for the analysis of wings with Variable angle tow (VAT) fibers. Meanwhile, VAT fiber placement introduces spatially varying stiffness characteristics that modify the bending–torsion coupling behavior of wings, thereby jointly influencing their structural dynamic and aeroelastic performance together with wing design parameters. This paper proposes a collaborative optimization framework for wing design parameters and VAT fiber layup parameters in the preliminary design stage, based on IGA. Non-uniform rational B-splines (NURBS) with ?????????1 continuity are employed to provide representations of the wing surface and the paths of VAT fiber. We established the structural dynamics model based on the third-order shear deformation theory (TSDT), and an aeroelastic coupling equation is constructed by integrating Theodorsen aerodynamic theory with the strip theory. The flutter characteristics of VAT composite wings under different parameter combinations are systematically investigated and validated against results from commercial software. On this basis, a genetic algorithm is employed to optimize wing design parameters and the optimal fiber paths for different flight conditions. This study aims to provide a method for the analysis of complex wing structures with VAT fibers by establishing a geometry-consistent aeroelastic analysis framework based on IGA, thereby bridging the gap between design and analysis models and enhancing the optimization efficiency of VAT composite wings.
0102
M. Özkesiciler, Aselsan A.S., TR; T. El Halabi, D-Orbit S.p.A., IT
Presented by: M. Özkesiciler, Aselsan A.S.
Flutter prediction using state-space models is often suffers due to mode switching and inconsistent eigenvalue tracking. This study improves flutter robustness for fixed-wing unmanned eVTOL aircraft by combining LS-RFA-based state-space modeling with eigenvector-based modal tracking and continuation methods. The approach ensures smooth modal trajectories, accurate flutter speed prediction, and reliable aeroelastic stability assessment.
0126
P. Chao¹, Z. Wu¹, C. Yang¹
¹Beihang University, CN
A Co-Kriging-based multi-fidelity framework is proposed for flutter boundary prediction. Low-fidelity data are generated from baseline analytical aeroelastic models, while high-fidelity data are obtained from updated models using sparse flight test data. Preliminary results demonstrate that this method improves robustness and accuracy under limited flight test conditions.
0136
G.X. Huo¹, C.Y. Dong¹, C.C. Xie¹, Chao An¹, Y. Meng¹, J.H. Yan¹
¹Beihang University, CN
Multi-body combined unmanned aerial vehicles (UAVs), formed by mechanically connecting multiple individual UAV units through wing-tip hinges, offer a promising approach to achieving high aerodynamic efficiency while mitigating the structural penalties associated with large-aspect-ratio wings. By reducing wing root bending moments and suppressing severe geometric nonlinearities, such configurations preserve the operational flexibility of individual units. However, the introduction of inter-vehicle constraints fundamentally alters the flight dynamics, leading to coupled motion modes that may cause dynamic instability and necessitate active stabilization. Most existing studies on multi-body combined UAVs are based on rigid-body flight dynamics models, which neglect structural flexibility and aeroelastic effects. This limitation becomes critical for high-aspect-ratio configurations, where elastic deformation, aerodynamic load redistribution, and control interactions are strongly coupled. To address this gap, this study investigates the aeroelastic response and stability augmentation of a wing-tip-hinged two-body composite UAV by explicitly accounting for structural flexibility and unsteady aerodynamics. The structural dynamics of the composite UAV are formulated using the floating frame of reference method combined with modal coordinates, allowing the decomposition of motion into large rigid-body displacements and small elastic deformations. The wing-tip hinge is modeled as a single-degree-of-freedom rotational constraint permitting relative roll motion between adjacent UAVs. Constraint equations are incorporated using the Lagrange multiplier method, resulting in a unified set of flexible multi-body equations of motion. Aerodynamic forces are computed using strip theory, with unsteady aerodynamic loads evaluated through induced velocity state variables and spanwise corrections applied to account for the unique boundary conditions of wing-tip-connec
0206
R. Zhao¹, X. Li, Comac Bejing Aircraft Technology Research Institute, CN; C. An¹, Y.-B. Zhou¹, Y. Yang¹
¹School of Aeronautic Science and Engineering, Beihang University, CN
This work develops an efficient nonlinear aeroelastic framework for large flexible wings using a reduced-order structural model and UVLM aerodynamics. It captures complex dynamic paths to chaos, showing that higher angles of attack reduce instability speeds and shorten the transition to chaos—key insights for flight safety.
0268
N. M. Leonard Garrido¹, M. Hickman¹, M. Amoozgar¹, M. Jabbal¹
¹Faculty of Engineering, University of Nottingham, GB
Modern eVTOL aviation has shifted small aircraft design to urban applications, increasing the likelihood of these aircraft interacting larger gusts. Due to this, understanding the gust response and the potential interactions between propellers an wings are critical to the design of the aircraft. Currently there is little research into the gust loads of wings with distributed propellers. The aim of this project is to investigate the influence of wing mounted propellers on the wing gust response.
0271
C. Ma¹, S. He¹
¹Northwestern Polytechnical University, CN
Transonic aeroelastic phenomena threaten aircraft safety. We build a POD-based structural-parametric aerodynamic ROM that delivers unsteady generalized aerodynamic forces in a unified POD space at low cost. This enables rapid flutter prediction across varying structural parameters via a coupled POD-coordinate aeroelastic model and eigenvalue analysis, validated on AGARD 445.6 and its counterparts.
0298
M Moradkhani, DE; J Rashid Jafari, TR; T Farsadi, TR; D Asadi, GB; H Haddad Khodaparst, GB
This work presents a geometry-based structural optimization of an aircraft engine pylon to reduce stress concentrations without mass or material changes. Finite element analyses with consistent aerodynamic loading show significant reductions in peak stress and strain, improving load transfer efficiency and structural durability with direct relevance to lightweight aircraft design.
0307
M. Valasek¹, J. Zavrel¹, V. Bauma¹, T. Vampola¹, G. Frulla, Politecnico di Torino, IT; M. Ritter, DLR, DE; A. Schirrer, Technical University Vienna, AT
¹Czech Technical University in Prague, CZ
The paper describes new mechanism that combines requirements of wing morphing and aeroelastic control. Morphing requires weak structure that can be easily deformed. Aeroelastic control requires stiff structure with suitable bandwidth where servo can provide aeroelastic stability. The considered morphing involves wing trailing edge with clear aerodynamic benefit. Aeroelastic control is included.
