| 200Nms单框架控制力矩陀螺研制 |
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| 引用本文： | 魏大忠,张激扬,武登云,李刚.200Nms单框架控制力矩陀螺研制[J].空间控制技术与应用,2011,37(6):14-18,46. |
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| 作者姓名： | 魏大忠 张激扬 武登云 李刚 |
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| 作者单位： | 北京控制工程研究所,北京100190;空间智能控制技术重点实验室,北京100190 |
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| 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.
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| 关 键 词： | 控制力矩陀螺 结构 姿态控制 |
Development of a 200Nms Single Gimbal Control Moment Gyro |
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| WEI Dazhong
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ZHANG Jiyang
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WU Dengyun
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LI Gang.Development of a 200Nms Single Gimbal Control Moment Gyro[J].Aerospace Contrd and Application,2011,37(6):14-18,46. |
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| Authors: | WEI Dazhong ZHANG Jiyang WU Dengyun LI Gang |
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| Institution: | WEI Dazhong1,2,ZHANG Jiyang1,WU Dengyun1,LI Gang1,2(1.Beijing Institute of Control Engineering,Beijing 100190,China,2.Science and Technology on Space Intelligent Control Laboratory,China) |
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| Abstract: | 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... |
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| Keywords: | control moment gyro structure attitude control |
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