中国空间科学技术

›› 2013, Vol. 33 ›› Issue (1): 21-29.doi: 10.3780/j.issn.1000-758X.2013.01.004

• 研究探讨 • 上一篇    下一篇

单框架控制力矩陀螺构型分析与奇异可视化

魏孔明, 吴忠, 刘涛   

  1. （北京航空航天大学仪器科学与光电工程学院，北京100191）
  • 收稿日期:2012-03-01 修回日期:2012-04-07 出版日期:2013-02-25 发布日期:2013-02-25
  • 作者简介:魏孔明 1982年生，2007年获北京航空航天大学精密仪器及机械专业硕士学位，现为北京航空航天大学精密仪器及机械专业博士研究生。研究方向为航天器姿态控制。
  • 基金资助:

    国家自然科学基金（10772011），中央高校基本科研业务费专项资金（YWF-10-01-A22）资助项目

Configuration Analysis and Singularity Visualization of Single Gimbal Control Moment Gyroscopes

Wei Kongming,Wu Zhong,Liu Tao   

  1. (School of Instrumentation Science and Opto-electronics Engineering, Beijing 100191)
  • Received:2012-03-01 Revised:2012-04-07 Online:2013-02-25 Published:2013-02-25

PDF (PC)

1515

摘要： 在单框架控制力矩陀螺(SGCMG)系统构型的分析和评价指标中，构型效益和可控效益分别反映了构型角动量包络和奇点在空间中的分布，可在一定程度上反映构型的性能。然而，构型效益不够直观，而可控效益中包含了角动量包络大小的影响。为此，将构型效益归一化，并从可控效益中去除角动量包络的影响，定义了两个新的构型指标——角动量利用率和非奇异率，对构型进行分析和评价。在此基础上，为了直观反映不同构型对奇点分布的影响，引入奇异可视化方法对不同构型下的奇异角动量曲面分布情况进行了对比分析。分析结果表明，SGCMG个数和构型的对称性是影响构型指标和奇异角动量曲面分布的主要因素。

关键词: 控制力矩陀螺, 构型分析, 姿态控制, 航天器

Abstract: The configuration efficiency and controllable efficiency are important indices in  evaluating the configuration of a single gimbal control moment gyroscope (SGCMG) system. But the configuration efficiency is non-normalized, and the controllable efficiency depends on the magnitude of the angular momentum envelop. By normalizing the configuration efficiency and excluding the impact of the angular momentum envelop to the controllable efficiency, two improved indices, which are capacity ratio and nonsingular capacity ratio, were introduced. As the singularity of SGCMGs is complex and these scalar indices do not indicate the whole properties of the configuration, visualization techniques were used to compare the singular surfaces of different configurations. The analysis results show that the quality of the SGCMG and the symmetries of the configurations mainly affect the configuration indices and the complexity of the singular surface.

Key words: Control moment gyroscope, Configuration analysis, Attitude control, Spacecraft