摘 要： 兼顾旋翼气弹耦合的计算精度及效率，建立了一套基于GEBT/VVPM/L-B全耦合旋翼气弹分析方法。结构上采用可有效考虑大变形的几何精确梁理论（Geometrically Exact Beam Theory，GEBT）建立桨叶动力学模型，并耦合粘性涡粒子方法（Viscous Vortex Particle Method，VVPM）以及L-B动态失速模型，有效捕捉尾迹粘性流动和畸变以及桨叶的非定常气动特性。在动力学模型迭代求解过程中，将响应以参数化形式写入气动求解模块，实现旋翼气弹全耦合求解。以UH-60A的c8534高速前飞状态为例，通过与试验值和CFD/CSD紧耦合计算结果对比，验证了气弹耦合方法的有效性。结果表明：相比于刚性旋翼，气弹全耦合求解模型可显著提高旋翼非定常气弹载荷的分析精度；相比于CFD/CSD耦合方法，在不影响计算精度的前提下，计算效率可提升54倍以上；前飞过程中桨叶的挥舞和扭转响应具有强非线性特性，在此状态下仍可有效预测旋翼气弹载荷，进一步验证了模型的鲁棒性。

Abstract: Considering the calculation accuracy and efficiency of rotor aeroelastic coupling analysis, the fully coupling aeroelastic method based on GEBT/VVPM/L-B is established. The dynamic model of blade is established by using the Geometrically Exact Beam Theory (GEBT), which can consider the large deformation effectively. 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 affecting the calculation accuracy apparently; The rotor aeroelastic loads can be effectively predicted in solving the strong nonlinear aeroelastic responses, which verifies the robustness of the model.