灵敏航天器快速倾斜机动的MCMG参数和力矩估算

Estimation of MCMG parameters and torques for rapid slewing maneuver of agile spacecraft

该文研究灵敏航天器快速倾斜机动时微型控制力矩陀螺(MCMG)的参数估算问题。所得到的估算结果可供微型控制力矩陀螺群初步设计时选择设计参数。从航天器的动力学模型出发,给出了倾斜机动模式下MCMG最大框架角速度和输出力矩的估算方法。然后在给定机动任务的前提下,以某小卫星为例,对采用标准金字塔构型的微型控制力矩陀螺群的姿态控制系统进行了仿真验证。仿真结果显示出该估算方法的可行性。

The micro control moment gyro （MCMG） parameters were estimated for an agile spacecraft performing a rapid slewing maneuver to provide reference data for the MCMGs parameters in the primary design stage. The estimation algorithms for the MCMG＇s maximum angular rates and the output torques were based on the spacecraft dynamics during the slewing maneuver. The response of the attitude control system of a small spacecraft during slewing was simulated for MCMGs with a pyramid configuration. Simulation results show that the estimation algorithm gives reasonable results.