›› 2013, Vol. 33 ›› Issue (1): 7-14.doi: 10.3780/j.issn.1000-758X.2013.01.002

• 研究探讨 • 上一篇    下一篇

零动量卫星轮控系统可重构性设计研究

顾朋1,2, 王大轶1,2, 刘成瑞1,2   

  1. (1 北京控制工程研究所,北京 100190)(2 空间智能控制技术重点实验室,北京 100190)
  • 收稿日期:2012-07-18 修回日期:2012-09-18 出版日期:2013-02-25 发布日期:2013-02-25
  • 作者简介:顾朋 1988年生,2010年毕业于安徽大学测控技术与仪器专业,现为北京控制工程研究所硕士研究生。研究方向为导航,制导与控制。

Research on Momentum Wheel Reconfiguration Design of Zero-momentum Satellite

Gu Peng1,2,Wang Dayi1,2,Liu Chengrui1,2   

  1. (1 Beijing Institute of Control Engineering, Beijing 100190) (2 National Key Laboratory of Science and Technology on Space Intelligent Control, Beijing 100190)
  • Received:2012-07-18 Revised:2012-09-18 Online:2013-02-25 Published:2013-02-25

摘要: 针对卫星姿态控制系统设计中常见的动量轮配置问题,总结了星上常用的5种轮控系统构型,首先对各种构型从角动量包络、干扰力矩下动量轮的饱和情况、系统功耗和可靠性等方面进行了可重构性分析和比较,在此基础上提炼了动量轮可重构性设计准则,可为轮控系统的设计提供参考依据。

关键词: 动量轮, 配置, 角动量包络, 可靠性, 可重构性, 姿态控制, 航天器

Abstract: The selection of momentum wheel configuration in satellite attitude control system design was investigated. Five different orientations of momentum wheel system were summarized. The design criteria of momentum wheel reconfiguration, the saturation of the momentum wheel under disturbance torque, energy consumption and reliability in different orientations were proposed by comparing the angular momentum envelope. The proposed method could be applied to the design of momentum wheel control system.

Key words: Momentum wheel, Configuration, Angular momentum envelop, Reliability, Reconfiguration, Attitude control, Spacecraft