摘要
根据天宫一号目标飞行器的特点及交会对接任务需求,天宫一号目标飞行器选择单框架控制力矩陀螺作为姿态控制执行机构,这是控制力矩陀螺首次在国内航天器上应用.阐述了单框架控制力矩陀螺在天宫一号目标飞行器姿态控制上的应用,主要包括四个方面:构形选择、操纵律设计、角动量卸载、故障诊断与重构.天宫一号目标飞行器控制力矩陀螺系统采用五棱锥构形,其操纵律设计为带零运动的伪逆操纵律,控制力矩陀螺系统具备故障诊断和重构功能.
According to the characteristics of Tiangong-1 spacecraft and the demand for rendezvous and docking mission,the single-gambal control moment gyro is used as the attitude control actuator of Tiangong-1 spacecraft.This is the first application of control moment gyro in the domestic spacecraft.The application of the control moment gyro in Tiangong-1 spacecraft is presented in this paper,which mainly includes 4 aspects:configuration,steering law,angular momentum unloading and fault diagnosis and reconfiguration.The configuration adopted by the control moment gyro system of Tiangong-1 spacecraft is the pentagonal pyramid configuration.The pseudo inverse steering law with zero motion is adopted.The fault diagnosis and reconfiguration is designed for the control moment gyro system.
出处
《空间控制技术与应用》
2011年第6期52-59,共8页
Aerospace Control and Application
