针对某舰载无人机拦阻着舰过程中的机体强度问题，以其中机身结构为主要研究对象，首次设计了包括中机身结构与前后机身、机翼假件以及拦阻钩等构件的地面拦阻模拟试验方案，并搭建了相应装置，采用地面试验和刚柔耦合仿真模拟2种方法，对拦阻着舰过程中拦阻力冲击下中机身结构的动态响应特性进行了全面分析。试验与仿真结果表明：中机身最大航向过载沿两条主传力路径自后机身到前机身方向衰减，下传递路径点的过载峰值明显大于上传递路径点的峰值；发现最大过载点位于拦阻接头处，应变危险点位于机腹梁前段处；中机身结构上各测点的试验和仿真过载误差均在5%以内，应变误差均在8%以内，验证了试验结果的有效性和刚柔耦合数值仿真方法的可行性。地面拦阻试验及数值仿真的联合分析可为舰载无人机机身结构强度设计提供重要参考，并为后续舰载无人机的拦阻着舰分析以及机身结构响应预测提供依据。
This paper aims at the airframe strength problem of a carrier-based UAV in the process of arresting and landing. With the fuselage structure as the main research object, a ground hindered simulation test plan is designed, including the fuselage structure, the fuselage and wings before and after false, and hindered hook component. The corresponding device is set up. Adopting the ground test and the coupled simulation, the dynamic response of the ship block resistance under the impact of the fuselage structure is analyzed. The test and simulation results show that the maximum longitudinal overload of the middle fuselage attenuates along the two main transmission paths from the rear fuselage to the front fuselage, and the peak load of the lower transmission path point is significantly higher than that of the upper transmission path point. It is found that the maximum overload point is at the arresting joint and the strain danger point is at the front section of the belly beam. The overload error of test and simulation at each measuring point on the medium fuselage structure is within 5% and the strain error is within 8%, which verify the validity of test results and the feasibility of the rigid-flexible coupling numerical simulation method. The joint analysis of ground arresting test and numerical simulation can provide important reference for the design of structural strength of carrier-based UAV, and provide basis for the subsequent analysis of arresting landing of carrier-based UAV and prediction of fuselage structural response.
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