太阳帆板故障模式展开动力学仿真

Dynamics Simulation of Deployment of Solar Panels in Fault Modes

基于ADAMS软件,对柔性太阳帆板展开与锁定过程进行了动力学仿真分析,详细地研究了太阳帆板展开与锁定过程对航天器本体姿态运动的影响,并且重点研究了两种典型故障模式下太阳帆板展开与锁定过程对航天器本体姿态运动的影响,一种故障模式为一侧两块太阳帆板故障,另一侧太阳帆板正常展开;另一种故障模式为有一块太阳帆板展开机构故障,由同步机构协调展开。给出了航天器本体姿态运动以及太阳帆板展开过程动力学特性等仿真结果,并初步提出了故障模式下的动力学辅助展开策略的建议,对航天器姿态控制系统的设计以及地面试验提供了参考和依据。

Dynamics simulation of the process of the flexible solar panel deployment was made using ADAMS. The effects of the spacecraft attitude motion undergone the flexible solar panels deployment and locking were analyzed and the effects of the spacecraft attitude motion undergone the flexible solar panels deployment and locking in two typical fault modes were studied, one is the panels on one side are fault and the panels on the other side deploy normally; the other is one panel drive is fault and deployed using the synchronizer. The simulation provided the result about the attitude motion of the spacecraft and the dynamics characteristic of the panels. And some advices of assistant deployment for fau# modes were given, which has some reference meaning to engineering design of spacecraft attitude control system and ground text.