摘要
为保证太阳翼在轨展开锁定的可靠性,往往需要较大的展开驱动力矩、较高的力矩裕度;而为了减缓太阳翼展开锁定对SADA的冲击载荷,又需要较小的驱动力矩,较少的展开到位剩余能量。为解决两者之间的矛盾,采用了为太阳翼加装黏滞型阻尼器的方法,它既不降低展开锁定的可靠性,又能有效抑制冲击载荷。但须要注意的是,当阻尼系数过大时,由于地面展开试验存在不可避免的因素(如设备阻力、空气阻力等),太阳翼地面展开试验时可能发生无法完全展开的故障;因此,在选择阻尼器性能时,须要同时兼顾在轨展开和地面试验展开的可靠性。文章利用AD-AMS和Nastran/Patran软件联合建立了太阳翼在轨和地面试验展开的仿真模型,分别得到无阻尼器和不同阻尼系数下的太阳翼在轨和地面试验展开动力学分析结果;通过对仿真结果的分析比对,综合评估了黏滞型阻尼器对太阳翼在轨展开和地面试验展开的影响。
In order to ensure its deployment reliability, the solar array needs higher driven torque and margins. At the same time, reducing impact load on SADA needs lower driven torque and unwanted energy. Adopting viscous damper can solve this conflict, which will effectively reduce impact load and not decrease deployment reliability. But higher damping rate will cause deploy able test failure due to inherent factors （such as deployable device resistance, wind resistance, etc）during ground test. So, we need adopt appropriate damping rate to ensure deployment suc- cessful on ground as well in orbit. The deployment models of solar array in orbit as well as on ground are proposed by using ADAMS and Nastran/Patran software. The dynamic simulation re- sults are obtained both in no damping and in different damping rates. Finally, the evaluating re- sult of impact load descending level is summarized.
出处
《航天器工程》
2013年第1期54-59,共6页
Spacecraft Engineering
关键词
太阳翼
黏滞型阻尼器
展开
动力学仿真
solar array； viscous damper ； deployment ； dynamic simulation
