单框架控制力矩陀螺部分失效时的空间站姿态机动方法  

Space station attitude maneuver method considering partial fault of single gimbal control moment gyroscopes

作　　者：赵乾[1] 唐国金[1] 

机构地区：[1]国防科技大学航天科学与工程学院,湖南长沙410073

出　　处：《国防科技大学学报》2015年第6期54-60,共7页Journal of National University of Defense Technology

基　　金：国家自然科学基金资助项目(11272346);国家973计划资助项目(2013CB733100)

摘　　要：对金字塔构型单框架控制力矩陀螺(SGCMG)的失效特性进行分析。结合SGCMG部分失效的特点,构建运用Legendre伪谱法的重规划姿态机动路径求解方法。考虑SGCMG失效情况的不可预测性,设计自适应操纵律,该操纵律可以根据指令力矩与输出力矩的偏差对SGCMG的失效情况进行诊断,从而调节操纵律的内部参数,实现失效情况操纵律的自适应调节。仿真结果表明,采用姿态机动路径重规划算法与自适应操纵律,在控制力矩陀螺部分失效的情况下,仍可以实现空间站的大角度姿态机动。姿态机动方法可以有效应对空间站大角度姿态机动过程中可能出现的SGCMG部分失效情况,从而提高空间站姿态机动任务的安全性与可靠性。The fault character of pyramid configuration single gimbal control moment gyroscopes （SGCMG） was analyzed. The calculation approach solving the replanned attitude maneuver path was proposed based on the Legendre pseudo spectral method. Considering the unpredictability of the SGCMG fault, an adaptive steering law was designed. Using this steering law, the fault state of SGCMG was detected and the parameters of the steering law was self-tuned. The simulation results reveal that, the large angle attitude maneuver can be accomplished by using the path replanned method and the adaptive steering law, when the SGCMG encounter partial fault. The proposed method can cope with the partial fault state of the SGCMG during attitude maneuver effectively, thus improving the security and reliability of the space station attitude maneuver mission.

关 键 词：姿态机动 控制力矩陀螺 路径规划 操纵律 

分 类 号：V421.4[航空宇航科学与技术—飞行器设计]