太阳翼展开锁定最大冲击载荷修正方法

摘要

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.%太阳翼展开锁定过程产生的锁定冲击载荷是卫星设计的重要指标,太阳翼设计时一般通过地面试验或仿真对该载荷进行估计。文章提出一种对太阳翼展开锁定过程最大锁定冲击载荷的修正方法。此方法在试验或仿真得出的载荷-时间曲线的基础上,参考模态分析结果或载荷曲线的频率分布情况,按频段分解,调整相位后再进行叠加,得到修正后的可能最大载荷。利用此方法对地面试验冲击力矩结果进行修正,解决了同一工况下多次试验结果间相差较大的问题。利用此方法对空间仿真冲击力矩结果进行修正,解决了展开末速度相同但锁定载荷相差较大的问题,得到了具有工程参考性的太阳翼空间展开冲击力矩偏保守估计值。进一步应用该方法,对空间展开末速度与最大锁定冲击力矩之间的线性关系进行了验证。