超静超稳卫星碰振动力学建模

针对分离式卫星载荷模块(PM)受到扰动时可能与服务模块(SM)发生碰撞的问题，综合音圈电机反电动势(back-EMF)和柔性线缆动力学的效应，基于牛顿欧拉法建立了分离式卫星(DFP)载荷模块动力学模型。基于Hertz接触理论，推导了分离式卫星碰撞过程中连续接触力模型，并分析了碰撞过程中产生的接触力对载荷模块指向精度和指向稳定度的影响。数值仿真结果表明，碰撞使得载荷模块指向精度和指向稳定度下降5个数量级，碰撞后载荷模块可再次恢复到超静超稳工作状态，恢复时间超过1400 s。本文建立的碰撞模型对研究分离式卫星碰撞规避和碰撞控制具有重要意义。

Vibro Impact Modeling for Disturbance Free Payload Satellite

Since the payload module (PM) and support module (SM) of a disturbance-free payload (DFP) fly in close proximity formation, the two modules may have a high probability collision. Synthesizing the influence of the back-electromotive-force (back-EMF) and the flexible cable, the dynamics model of the DFP is established using the Newton Euler method. The contact force model is derived using the Hertz contact theory, and the influence of the contact force on the pointing accuracy and pointing stability of the payload module is analyzed. The numerical simulation results show that the collision reduces the pointing accuracy and pointing stability of the payload module by 5 orders of magnitude. The payload module can recover to the ultra-quiet and ultra-stable working state after the collision, but the recovery time exceeds 1400 s. The collision model in this paper is of great significance for studying the collision avoidance and collision control of DFP.