基于刚柔耦合的卫星舱壳体平抛式分离仿真与试验研究

Simulation and tests for horizontal throwing separation of satellite cabin shell based on rigid-flexible coupling

针对卫星舱壳体分离过程中柔性效应带来的影响,基于柔性多体动力学方法,建立了复合材料卫星舱壳体平抛式分离的刚柔耦合动力学模型,采用推冲器的推力-位移关系实现了从地面试验到任意工况的推冲器推力等效,对柔性体模型和刚体模型进行了仿真及对比分析。结果表明:壳片弹性变形以2阶“呼吸运动”模态为主,吸收了约推冲器做功的15%,分离速度降低;分离面下角点处“呼吸运动”最为剧烈,半罩第一次向内“呼吸运动”时对内包络的影响最大;柔性效应还会影响推冲器推力作用的时间历程。进行卫星舱分离地面试验,采用高速摄影测量半罩运动情况,对比验证了仿真方法的正确性,仿真误差在13%以内。研究结果有助于确保分离方案的有效性,释放了卫星舱内包络空间的设计余量,为分离优化设计提供参考。

Here,aiming at influences of flexible effect on separation process of a satellite cabin shell,a rigid-flexible coupled dynamic model for horizontal throwing separation of a composite satellite cabin shell was established based on the flexible multi-body dynamic method.The thrust-displacement relationship of a thruster was used to realize the thrust equivalence of the thruster from ground tests to arbitrary conditions.Simulation and contrastive analysis for the flexible body model and the rigid body model were performed.The results showed that elastic deformation of the shell is dominated by the second-order“breathing motion”mode to absorb about 15%of work done by the thruster,and the separation speed decreases;the respiratory motion at the lower corner point of the separation surface is the most severe,and the influence of the first time inward breathing movement of the half hood on the inner envelope is the greatest;the flexibility effect can also affect the thrust action time history of the thruster.Satellite cabin separation ground tests were conducted.A high-speed photography was used to measure the half hood’s motion to contrastively verify the correctness of the simulation method.It was shown that the simulation error is less than 13%;the study results are helpful to ensure the effectiveness of the separation scheme,release the design margin of the satellite cabin inner envelope space,and provide a reference for separation optimization design.