本文兼顾旋翼气弹耦合分析的计算精度和效率，发展了一种粘性涡粒子方法（Viscous Vortex Particle Method，VVPM）/几何精确梁理论（Geometrically Exact Beam Theory，GEBT）耦合的高效高精度气弹耦合分析方法。尾迹分析方面，采用VVPM方法模拟旋翼尾迹粘性流动，有效捕捉旋翼非周期非定常机动状态尾迹畸变运动，使尾迹可以远距离输运。气动力计算采用L-B动态失速模型，可有效模拟桨叶的动态失速等非定常气动特性。结构上基于三维有限转动理论建立精确的应变-位移关系，发展了GEBT方法建立旋翼桨叶的大位移和大转动变形下的非线性动力学方程。耦合基于VVPM方法的非定常气动模型和GEBT方法的非线性结构动力学方程。在悬停状态以及总距突增状态下，通过与旋翼拉力系数变化的试验结果对比，验证了耦合方法的有效性。以BO105旋翼为算例，分析了总距突增过程中桨叶的弹性变形规律及其对旋翼气动特性的影响。结果表明：旋翼在悬停状态下，随着桨叶总距的增大，桨叶弹性变形对旋翼气动力的影响逐渐减弱。在总距突增过程中，当初始总距较小时，弹性桨叶的拉力过冲现象比刚性桨叶更加严重，在较大初始总距下，由于桨距突增过程导致桨叶出现失速，桨叶低头力矩开始迅速增大，并且翼型拉力系数减小，从而使旋翼的拉力过冲现象开始减弱。通过旋翼尾迹流场分析发现，由于总距突增后尾迹的延迟脱落导致桨盘平面的诱导速度滞后，同时导致旋翼尾迹流场出现畸变，而旋翼的拉力过冲现象主要是诱导速度的滞后所导致。

The viscous vortex particle method (VVPM) and the geometrically exact beam theory (GEBT) coupling method was developed to efficiently analyze the aeroelasticity effect of the helicopter rotors. The VVPM method is employed to simulate viscous flows of rotor wake with high precision, which can effectively capture the wake distortion in non-periodic and unsteady maneuvering, so that the wake can be transported long distance. The L-B dynamic stall model is used in aerodynamic calculation, which can effectively simulate unsteady aerodynamic characteristics such as dynamic stall. In addition, the GEBT method is based on the three-dimensional finite rotation theory to establish an accurate strain-displacement relationship, and it can simulate the large displacements and rotations of the blade with high precision. In the hover and the collective pitch increases rapidly, the validity of the method is verified by comparing with the experimental results. Taking the BO105 helicopter as a case, the elastic deformation of the blade and its influence on the aerodynamic characteristics are analyzed. During the collective pitch increases rapidly, the results show that the elastic deformation of the blades has a significant impact on the aerodynamic forces when the collective pitch is small, while its influence diminishes at larger collective pitch. For instance, the overshoot phenomenon of the rotor’s thrust is more severe than that of the rigid blade when the initial collective pitch is small. Under larger initial collective pitch, the negative moment of the blades begins to increase rapidly due to the stall state of the blades during the collective pitch increases rapidly, which leads to the weakening of the rotor's thrust overshoot phenomenon. Tail wake analysis reveals that the collective pitch increasing rapidly causes distortion in the rotor wake, and the thrust overshoot phenomenon of the rotor is mainly due to the lag of the induced velocity.