航天器工程2011，Vol.20Issue(6)：55-62,8.
太阳翼展开锁定最大冲击载荷修正方法
Method of Modifying Maximum Impact Load on Solar Array Deployment and Locking Process
陈天智 1王晛 1柴洪友1
作者信息
- 1. 北京空间飞行器总体设计部,北京100094
- 折叠
摘要
Abstract
Impact Load caused by solar array deployment and locking is an important consideration in the design of satellite.Generally,ground test or simulation is used to estimate the load.A modifier method is proposed based on load-time curve of solar array locking impact load acquired by test or simulation.Consulting results of modal analysis or frequency distributing of load curve,we disassemble the impact load into several subsections.Then,the maximum impact load can be gained by adjusting the phase of each subsection and reassembling the modified subsections.By this method,the impact torque in the solar array ground deployment test is modified and the issue that the testing results are quite different under the same exterior condition is resolved.By this method,impact torque in the space simulation is also modified,and the issue that the loads are quite different under the same deployment angular velocity is also resolved,and a conservative solar array space impact load is obtained for engineering reference.Furthermore,the linearity between terminal angular velocity and impact torque is testified.关键词
太阳翼/展开锁定/冲击/试验Key words
solar array/deployment and locking/impact/experiment分类
航空航天引用本文复制引用
陈天智,王晛,柴洪友..太阳翼展开锁定最大冲击载荷修正方法[J].航天器工程,2011,20(6):55-62,8.
