舰载飞机拦阻着舰过程中，载荷大、加速度大、距离短、时间短，且受航母运动、气 流扰动等条件影响，存在复杂的强非线性多学科动力学耦合问题． 文中对某型号舰载无人 机建立了舰载飞机 －拦阻钩简耦多体动力学模型，根据等质量小车实验数据提出一种施 加拦阻载荷的方法，同时考虑气动载荷的作用，利用 ADAMS 动力学仿真软件对舰载机拦 阻着舰进行刚柔耦合多体动力学仿真分析，得到了拦阻过程中飞机迅速作低头运动随后 保持相对平稳的姿态变化规律、机身纵向过载沿机身从后向前先急剧减少再缓慢增加的 传递路径，以及机身应力和应变在与起落架、拦阻钩接位置处较大而其它位置处较小的分 布规律． 仿真结果表明，这种仿真方法能够高效模拟强非线性复杂载荷耦合下的舰载机着 舰过程，为舰载机拦阻着舰全过程研究及机身结构设计提供参考． 

 In the process of arresting the landing of a carrier-based aircraft， the load and the acceleration are large， but the distance and the time are short，and they are affected by the conditions of aircraft carrier movement and airflow disturbance． There is a complex strong nonlinear multidisciplinary dynamics coupling problem． This paper establishes the UAV aircraft arresting hooksimple coupled multi-body dynamics model of a certain type of aircraft according to the experimental data obtained from the quality of the car to put forward a method of applying arresting loads by taking into consideration the effect of aerodynamic load，and by using the dynamic simulation software ADAMS for carrier-based aircraft landing on the basis of the rigid flexible coupling multi-body dynamics simulation analysis． In the process of arresting，the UAV aircraft posture changed quickly into a bow movement，and then maintained a relatively stable，body vertical acceleration along the fuselage from rear to front which first decreased sharply and then increased slowly． The distribution law of the stress and strain on the fuselage was that the landing gear and the arresting hook position were larger than that of others． The simulation results showed that the method can effectively simulate the landing process of a carrier-based aircraft with strong nonlinear complex loads，which can provide a reference for the whole process of carrier-based aircraft arresting， landing and the design of fuselage structure．