建立了旋翼多体系统气动弹性模型并给出了一种适合于该模型响应计算的数值计算方法。采用柔性多体系统动力学方法建立旋翼气动弹性模型,利用驱动约束显著简化约束方程形式,集成大变形桨叶模型,准确考虑变形的非线性,适合于对采用柔性结构的先进旋翼进行气动弹性分析。基于Broyden法改进隐式积分法积分一步中非线性方程的求解,避免求取切线矩阵和矩阵求逆运算,保持隐式积分法具有较好稳定性的同时提高计算效率,解决了旋翼多体系统气动弹性力学方程隐式表达且具有较强非线性和较高刚性比造成的响应计算困难。通过模型旋翼桨叶响应计算验证了结构模型与气动弹性响应求解方法。采用建立的气动弹性模型计算悬停和前飞状态旋翼气动弹性稳定性,与试验结果对比验证了模型的正确性。研究了不同的稳定性计算方法、桨叶结构模型和入流模型等对悬停和前飞稳定性计算的影响,结果表明本文所采用的结构、气动模型及气动弹性稳定性计算方法提高了气动弹性稳定性分析精度。 Aeroelastic model of a rotorcraft multi-body system is established and a numerical calculation method suitable for the response calculation of the model is given. A flexible multibody system dynamics method is used to establish the rotor aeroelastic model. The driving constraint is used to simplify the constrained equation form. The large deformation blade model is integrated to accurately consider the deformation nonlinearity. It is suitable for the aeroelastic analysis of the advanced rotor with flexible structure . Based on Broyden’s method, the nonlinear equation of implicit integration method is improved, avoiding the tangent matrix and matrix inversion operation, keeping the stability of implicit integration method and improving the computational efficiency, and solving the multi-body system of rotor It is difficult to calculate the response caused by implicit expression of aeroelasticity equation with strong nonlinearity and higher stiffness ratio. The structural model and the method of solving the aeroelastic response are verified by the model rotor blade response calculation. The aeroelastic model was used to calculate the aeroelastic stability of the hovering and forward flying rotor. The comparison with the experimental results verified the correctness of the model. The effects of different stability calculation methods, blade structure model and inflow model on the stability calculation of hovering and forward flight are studied. The results show that the structure, aerodynamic model and aeroelastic stability calculation method used in this paper improve the aeroelasticity Stability analysis accuracy.