摘要
介绍天宫一号目标飞行器采用的单框架控制力矩陀螺的总体结构、技术指标和验证试验.该单框架控制力矩陀螺的角动量为200Nms,最大可输出力矩为20Nm,响应带宽为2Hz,其中2个控制力矩陀螺高速转子已经进行了25000h的寿命试验.天宫一号目标飞行器姿态控制系统共采用了6个单框架控制力矩陀螺来输出姿态控制力矩,当1个或2个控制力矩陀螺失效时姿态控制系统仍能正常工作.
Development of 200Nms single gimbal control moment gyro(SGCMG) used in Tiangong-1 spacecraft,including overall structure,specification and verification test is presented in this paper.The SGCMG has 200Nms angular momentum,20Nm maximum output torque and 2Hz response bandwidth.The rotating mass assembly of two CMGs has been running for 25000 hours in the long-life test.The attitude control system of Tiangong-1 spacecraft uses six SGCMGs to provide the necessary attitude control torques.The system is redundant,and it can function if one or two CMGs failed in operation.
出处
《空间控制技术与应用》
2011年第6期14-18,46,共6页
Aerospace Control and Application
关键词
控制力矩陀螺
结构
姿态控制
control moment gyro
structure
attitude control