柔性航天器姿控执行机构微振动集中隔离与分散隔离对比研究

Comparison of concentrated and distributed isolations of micro vibrations in flexible spacecraft attitude actuators

姿控执行机构高速旋转诱发的微振动会降低柔性航天器姿态稳定度。为实现高稳指向,文章研究了姿控执行机构的集中隔振与分散隔振技术。首先建立包含隔振器的柔性航天器姿态动力学模型;然后仿真研究航天器在作大角度机动和稳定控制两种工况下,姿控执行机构的两种隔振方案的性能,并进行了对比分析。研究结果表明:航天器进行大角度机动时,对于高刚度隔振器,两种隔振均具有稳定性,并且指向控制性能相似;对于低刚度隔振器,集中隔振较分散隔振容易失稳;在稳定控制工况下,对于高刚度隔振器和低刚度隔振器,两种隔振性能基本一致。

The attitude stability of flexible spacecrafts is reduced because of micro vibrations resulting from rotating attitude control actuators. In this paper, the concentrated vibration isolation and the distributed vibration isolation are studied in the context of high stability pointing. At first, the attitude dynamics model for the flexible spacecraft containing vibration isolators is established. Then, the performances of the passive concentrated vibration isolation and the distributed vibration isolation for the attitude actuators are compared by using the simulation method. It is indicated that by using high-stiffness isolators, the concentrated vibration isolation has a similar performance as the distributed vibration isolation in the satellite maneuvering processes. Using the low-stiffness isolators, the concentrated vibration isolation loses stability more easily than the distributed vibration isolation. The concentrated and distributed vibration isolations have similar performances for attitude stabilizing with both the high-stiffness or the low-stiffness isolators.