北京航空航天大学学报 ›› 2010, Vol. 36 ›› Issue (12): 1417-1421.

• 论文 • 上一篇    下一篇

某型航天器推力矢量控制伺服机构的设计理论

陆豪1, 李运华1, 朱成林2   

  1. 1. 北京航空航天大学 自动化科学与电气工程学院, 北京 100191;
    2. 中国航天科技集团公司 第1研究院18所, 北京 100076
  • 收稿日期:2009-12-02 出版日期:2010-12-30 发布日期:2010-12-30
  • 作者简介:陆 豪(1973-),男,山东东平人,博士生,luhaocasc@sina.com.
  • 基金资助:

    国防科工委"十一五"预研资助项目

Design theory of thrust vector control servo mechanism for a type of spacecraft

Lu Hao1, Li Yunhua1, Zhu Chenglin2   

  1. 1. School of Automation Science and Electrical Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;
    2. The 18th Institute of 1st Academe in China Aerospace Science & Technology Group Corporation, Beijing 100076, China
  • Received:2009-12-02 Online:2010-12-30 Published:2010-12-30

摘要: 针对某型航天器对伺服机构的要求,设计了推力矢量控制伺服机构.通过比较液压、气动和电动3种类型伺服机构的特点,选择了电动伺服机构.研究了包括机电作动器设计、驱动控制技术和冗余技术等电动伺服机构的3项关键技术.建立了双冗余电动伺服机构的二自由度动力学模型,对其动态性能进行了仿真研究.理论分析和仿真结果证明:电动伺服机构的方案设计合理可行,不仅满足航天器高可靠性、良好维护性等基本要求,而且满足控制系统的动态性能指标要求.

Abstract: Addressing the requirements of servo mechanism applied in a certain type of spacecraft, one servo mechanism for thrust vector control was designed. By comparing hydraulic servo mechanism,pneumatic servo mechanism and electric servo mechanism, their characteristics were obtained and the electric servo mechanism was selected. The key techniques of electric servo mechanism were researched, including the design of electromechanical actuators, drive and control technology and redundancy technology. The two-degree of freedom dynamics model of electric servo mechanism with two redundancies was established and its dynamic characteristics were simulated. Theory analysis and simulation results show that the scheme of electric servo mechanism is practical and logical. The electric servo mechanism not only meets the basic demands of the spacecraft, such as high reliability and good maintainability, but also satisfies the requirements of dynamic performance targets for controlling system.

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