基于刚柔耦合动力学理论，在充分考虑空间各干扰力矩、柔性太阳翼惯性力矩、以及轴承附加阻力矩等作用基础上，建立了相应动力学仿真模型，针对目标飞行器驱动机构开展了各工况下的驱动力矩设计工作。仿真计算比较了“部分耦合”与“全耦合”两种算法计算结果间的差异，给出了该驱动机构“驱动力矩”及“止动力矩”设计指标，并据此进行了电机、谐波减速器等的选型工作。%Based on theory of rigid- flexible coupling dynamics, with fully consideration about disturbed moment in space, inertia moment of flexible solar arrays, and friction moment of bearing＇the dynamics simulation model is established, and the design of drive moment on the target spacecraft in orbit is carried out accordingly. The difference of results between ＂partial coupling＂ and ＂full coupling＂ analysis method is pointed out through dynamics simulation. The detailed design results of ＂drive moment＂ and ＂counteract moment＂ are given, and the suited electric motor, harmonic wave retarder are chosen consequently. The limitation of experience formula is remedied with the ＂full coupling＂ method mentioned in this paper which has been widely used in drive mechanism design of transport spacecraft and space station, etc.
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