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Session: Poster session & drinks
Session starts: Tuesday 18 June, 18:00
Presentation starts: 18:09
Room: Room 1.1

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Rui Zhao ()
Chao An ()
Changchuan Xie ()

Abstract:
Large flexible aircraft represented by high-altitude long-endurance UAVs and flying wing UAVs have broad application prospects in many fields. Due to specific requirements for flight performance, such aircraft has large structural flexibility. Under the aerodynamic loads, large flexible aircraft will undergo large elastic deformation, which will bring geometric nonlinear aeroelastic problems. Tradtional linear aeroelastic analysis methods cannot meet the aeroelastic analysis requirements of large flexible aircraft. In this paper, we use the nonlinear substructure method to establish a reduced-order model of a large flexible aircraft and calculate the aeroelastic response. Meanwhile, discussion and variation of calculation results will be performed. Aiming at the large flexible aircraft components, the natural structural mode is used as the basis to establish a nonlinear structural reduced-order model, and regression analysis method is used to solve the nonlinear stiffness coefficients. On this basis, combined with the surface aerodynamics and three-dimensional surface spline interpolation methods, the geometric nonlinear aeroelastic analysis of the wing components is carried out. Compared with the aeroelastic analysis results based on the nonlinear finite element method, the deviation of the analysis results is small. The nonlinear structural reduced-order model can balance the solution efficiency, accuracy and structural application range. Aiming at the whole aircraft structure of large flexible aircraft, aircraft is separated into nonlinear wing components and linear fuselage components, and a hybrid interface modal synthesis method considering geometric non-linear factors in the domain is established based on substructure method. Combined with the nonlinear structural reduced order model of the wing, a low-order structure model of the whole aircraft is formed. On this basis, the static aeroelastic trim and rigid/elastic coupling stability analysis of large flexible aircraft are carried out. In this paper, the structural modeling method and geometric nonlinear aeroelastic analysis of the complex engineering model of large flexible aircraft are carried out, which verifies the applicability of the structural modeling method and aeroelastic analysis established in the complex engineering model, and shows its great advantages in computational efficiency. Key words：Large flexible aircraft, Aeroelasticity, Geometric nonlinearity, Reduced order modeling, Nonlinear substructure method, Modal synthesis method