舰载飞机弹射动力学仿真与试验验证

目的获取舰载飞机弹射过程中冲击动载荷在结构上的响应规律,以及前起落架和与其连接的机体主传力结构的动响应特性。方法基于多体系统动力学理论,建立描述舰载机弹射过程的刚柔耦合多体系统动力学模型,对弹射过程进行仿真分析。同时开展地面模拟弹射冲击试验,通过仿真和试验对照,重点研究牵制载荷突卸瞬间结构的动态响应规律。结果仿真和试验得到结构传力路径各点的加速度和应力响应数据,试验测得机体结构加速度峰值达到255g,而同位置的应力峰值为85 MPa,仿真和试验数据的趋势一致。结论牵制载荷突卸形成的冲击动响应峰值沿着结构传力路径衰减。航向加速度和应力响应峰值随着牵制释放载荷的增加而增加。虽然瞬态加速度峰值达到较高水平,但是瞬态作用机体结构的应力峰值不高,不足以造成结构失效。结构设计应重点关注弹射冲击响应峰值和振动疲劳的影响。

Dynamic Simulation and Experimental Verification of Carrier-based Aircraft

In order to obtain the response law of dynamic load on the structure and the dynamic response characteristics of the front landing gear and the body structure connected with it during the shooting process of carrier-based aircraft, based on the multi-body system dynamics theory, this paper established a rigid-flexible coupling multi-body system dynamics model to describe the ejection process of the carrier-based aircraft fuselage. The ejection process was simulated and analyzed. Combined with the simulation ejection impact experiment, the dynamic response law of the structure at the moment of the traction load unloading was mainly studied. The acceleration and stress response data of each point in the force transmission path of the structure were obtained by simulation and experiment. The peak acceleration of the body structure measured by experiment reached 255g, while the peak stress at the same position was 85 MPa. The trend of simulation and experimental data were consistent. The results showed that the peak value of the impact dynamic response formed by the sudden unloading of the traction load attenuated along the force transmission path of the structure, and the peak value of heading acceleration response increased with the increase of traction release load at the moment of traction rod fracture. Although the peak value of transient acceleration reached a high level, the peak value of structural stress under transient action was not high enough to cause structural failure. The structural design should focus on the impact of the corresponding peak and vibration fatigue.