摘要
研究了应用单框架控制力矩陀螺(SGCMG)作为姿态控制执行机构,在部分陀螺失效时,灵敏航天器姿态机动的控制问题。对金字塔构型(PC)陀螺群中一只陀螺失效产生的构型变化进行了分析,研究了部分陀螺失效对陀螺群角动量包络及输出力矩的影响,基于最优化理论和坐标变换方法提出了一种利用失效后最大角动量包络提供较大输出力矩的策略。在给定飞行任务的前提下,以某小卫星为例,针对给定的姿态机动任务进行了仿真验证,结果表明使用所设计的方法,小卫星在失效情况下也可以完成姿态机动任务,验证了该方法的可行性和有效性。
Attitude stabilization and attitude maneuvers of agile small spacecraft were studied using SGCMG as the attitude control actuator during the failure of some of the control moment gyros （CMGs）. This study analyzed the effects of configurable variations and the effects on the angular momentum envelope and output torque caused by one SGCMG failure of pyramid configuration （PC）. An optimization and coordinate conversion method was designed to utilize the maximum workspace after CMG failure to generate larger torques. Simulations of the responses of the attitude control system of a small spacecraft during slewing show that the small spacecraft can change its attitude to carry out its mission in case of failure, with the design method giving reasonable results.
出处
《清华大学学报（自然科学版）》
EI
CAS
CSCD
北大核心
2010年第2期307-311,共5页
Journal of Tsinghua University(Science and Technology)
基金
国家自然科学基金资助项目(10872029)
北京市优秀人才培养资助计划(20071D1600300398)
北京理工大学优秀青年教师资助计划(2007Y0202)
关键词
微型控制力矩陀螺
失效l角动量包络
力矩输出
micro control moment gyro （MCMG）
failure
angular momentum envelope
output torque
