北京航空航天大学学报 ›› 2010, Vol. 36 ›› Issue (7): 767-770.

• 论文 • 上一篇    下一篇

基于气浮台的微小卫星姿态控制实时仿真

王新升1, 韩建斌1, 梁斌2, 李基勇2   

  1. 1. 北京航空航天大学 宇航学院, 北京 100191;
    2. 哈尔滨工业大学 空间智能系统研究所, 哈尔滨 153001
  • 收稿日期:2009-05-10 出版日期:2010-07-30 发布日期:2010-09-10
  • 作者简介:王新升(1973-),男,黑龙江伊春人,讲师,xswang@buaa.edu.cn.
  • 基金资助:

    国家863计划资助项目(2007AA704340,2007AA704115)

Micro-satellite attitude control real-time simulation based on mono-axis air-bearing table

Wang Xinsheng1, Han Jianbin1, Liang Bin2, Li Jiyong2   

  1. 1. School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;
    2. Space Intelligence System Institute, Harbin Institute of Technology, Harbin 153001, China
  • Received:2009-05-10 Online:2010-07-30 Published:2010-09-10

摘要: 针对某在研卫星项目任务需求,以单轴气浮台为仿真平台,对单刚体微小卫星的姿态控制问题进行了气浮台实时仿真研究.介绍了微小卫星仿真气浮台系统的硬件组成,论述了仿真系统软件实现的机制,分析了姿态控制系统的基本原理.根据任务要求,对微小卫星三轴正常姿态稳定控制,大角度机动姿态控制模式进行了仿真实验.实验结果表明姿态控制系统的控制精度能够满足任务要求,从而验证了姿态控制系统方案的正确性和可行性.

Abstract: Micro-satellite attitude control real-time simulation was studied based on the mono-axis air-bearing table, which was supported by a micro-satellite project. The hardware structure of the micro-satellite air-bearing table was introduced and the software architecture for the simulation system was described; Real micro-satellite attitude control system was analyzed. According to the mission requirements, the real-time simulation focused on the micro-satellite three-axis attitude stable controlling and the large angle attitude maneuver problem. The simulation results show that the micro-satellite attitude control scheme is implemented and the control precision is satisfied to meet the mission requirements. The feasibility and reliability of the micro-satellite attitude control scheme is also verified.

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