旋翼高效/高精度气弹全耦合分析方法

doi:10.7527/S1000-6893.2025.32161

Abstract

Abstract:

To balance calculation accuracy and efficiency of rotor aeroelastic coupling analysis， a fully coupling aeroelastic method based on GEBT/VVPM/L-B is established. Structurally， the dynamic model of blade is established by using the Geometrically Exact Beam Theory （GEBT）， which effectively consider the large deformation. The Viscous Vortex Particle Method （VVPM） and the L-B dynamic stall model are coupled to consider the viscous flow， the distortion of the wake and the unsteady aerodynamics of the airfoil. In each iterative step， the aeroelastic response is inserted into the aerodynamic computation module in a parametric form to realize the full coupling strategy. The c8534 flight of UH-60A is introduced for verification， and the effectiveness of the aeroelastic coupling method is verified by comparing with the experiment and the CFD/CSD tight coupling result. The results show that the proposed method can improve the computational accuracy significantly relative to the rigid rotor model. Compared with the CFD/CSD coupling method， the calculation efficiency can be improved by more than 54 times without apparently affecting the calculation accuracy. The rotor aeroelastic loads can be effectively predicted in solving the strong nonlinear aeroelastic responses， which verifies the robustness of the model.

Key words: viscous vortex particle method, geometrically exact beam theory, aeroelastic full coupling, structural loads, aeroelastic response

CLC Number:

V215.34

Xin WANG, Xiayang ZHANG, Lixiong ZHENG, Jinwu XIANG. High-efficiency and high-precision aeroelastic full coupling method of rotor[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(S1): 732161.

Figures/Tables 11

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参数	数值
桨叶片数	4
桨叶弦长/m	0.527
桨叶半径/m	8.178
实度	0.082 6
桨叶负扭/（°）	-8
挥舞较外伸量/m	0.381
桨尖后掠角度/（°）	20
旋翼转速/（r·min^-1）	258

High-efficiency and high-precision aeroelastic full coupling method of rotor

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Figures/Tables 11

References 34

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[1]	Xin WANG, Xiayang ZHANG, Qijun ZHAO, Jinwu XIANG. Aeroelastic loads of rotor during collective pitch ramp increase in hovering state based on VVPM/GEBT coupling method [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(16): 231628-231628.
[2]	Yufeng BAI, Qitong ZOU, Rui HUANG, Haojie LIU, Yuguo RAN. Aeroelastic control of flexible wing with flying-wing configuration and wind tunnel tests [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(14): 331452-331452.
[3]	TAN Jianfeng. Influence of helicopter rotor on tail rotor unsteady aerodynamic loads [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(10): 3228-3240.
[4]	TAN Jianfeng, WANG Haowen, WU Chao, LIN Changliang. Rotor/Empennage Unsteady Aerodynamic Interaction with Unsteady Panel/Viscous Vortex Particle Hybrid Method [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2014, 35(3): 643-656.