飞行器为了缩减储运空间，广泛采用折叠舵面构型。针对含非线性连接的折叠舵动力学系统，基于Mindlin板方程对舵面结构进行建模，采用三阶活塞理论推导了非定常气动力模型，运用Newmark方法和牛顿法迭代法求解了含非线性边界的舵面位移时域响应，采用频域法和时域法对飞行器折叠舵面的气动弹性稳定性和位移响应进行分析，讨论了折叠机构非线性类型和模型参数对气动弹性行为的影响。研究结果表明：建立舵面模型的固有频率和非定常响应结果与商业有限元结果的偏差小于2.2%，具有较好的一致性，验证了结构动力学模型的正确性；对于多项式非线性连接刚度，在临界速度条件下表现为收敛趋势；对于间隙非线性和双线性连接刚度，在临界速度条件下表现为渐发散趋势，在0.5°间隙条件下，双线性刚度的振动幅值显著小于间隙刚度的幅值，说明在间隙折叠机构内预置扭簧能够显著降低振动响应；对于非对称混合非线性刚度，在临界速度条件下表现为渐发散趋势。该方法对飞行器流固耦合问题研究以及飞行条件下含非线性连接的折叠舵面振动响应评估具有一定指导作用。

To reduce the storage and transportation space， folding fin configurations are widely used in aircraft. For dynamic systems of folding fin with nonlinear connections， the fin is modeled based on the Mindlin plate theory， and unsteady aerodynamic is simulated by third-order piston theory. The Newmark method and Newton method are used to solve time domain displacement response of the fin with non-linear boundaries. The aeroelastic stability and displacement response of the folding fin of the aircraft are analyzed using the frequency domain and time domain methods. The influence of nonlinear types and parameters of folding mechanisms on aeroelastic behavior is discussed. The results show that the difference of natural frequency and unsteady response results of the established model， and that from the commercial finite element results is less than 2.2%， indicating a good consistency and verifying the correctness of the structural dynamics model. For polynomial nonlinear connection stiffness， it exhibits a convergence trend under critical velocity conditions； for freeplay nonlinearity and bilinear connection stiffness， there is a gradual divergence trend under critical speed conditions. At a 0.5° freeplay condition， the vibration amplitude of bilinear stiffness is significantly smaller than that of freeplay stiffness， indicating that pre-installing torsion springs in freeplay folding mechanisms can significantly reduce vibration response； for asymmetric mixed nonlinear stiffness， this model exhibits a gradually divergent trend under critical velocity conditions. This method has certain guiding significance for the research of fluid structure coupling problems in aircraft and the evaluation of vibration response of folding fin with nonlinear connections under flight conditions.