中国空间科学技术

中国空间科学技术 ›› 2018, Vol. 38 ›› Issue (4): 20-26.doi: 10.16708/j.cnki.1000-758X.2018.0021

• 研究探讨 • 上一篇    下一篇

微小卫星轨道保持的混合切换控制方法

杨博１,∗ ，魏鲍杰１，魏延明２，苗峻1   

  1. 1. 北京航空航天大学宇航学院，北京 100191
    2. 北京控制工程研究所，北京 100190
  • 收稿日期:2017-12-20 修回日期:2018-01-18 接受日期:2018-05-15 出版日期:2018-08-25 发布日期:2018-06-11
  • 通讯作者: 杨博（1963-），女，副教授，yangbo@buaa.edu.cn，研究方向为航天器深空探测自主导航与制导、航天器天文自主导航技术、可重复运载器GNC关键技术

Hybrid switching control method for micro-satellite station keeping

YANG Bo1,*, WEI Baojie1, WEI Yanming2, MIAO Jun1   

  1. 1. School of Astronautics, Beihang University, Beijing 100191, China
    2. Beijing Institute of Control Engineering, Beijing 100190, China
  • Received:2017-12-20 Revised:2018-01-18 Accepted:2018-05-15 Published:2018-08-25 Online:2018-06-11

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摘要： 固体微推力器阵列作为一种新型推力装置用于微小卫星轨道保持具有精度高、无燃料泄漏、冲量可调等优点，但是微推力器推力不连续的特点，使得控制系统设计时与以往的连续系统有所不同。为了充分发挥微推力器高精度的特性，采用基于混合系统的切换控制思想，建立了微推力器混合切换系统控制模型。首先，根据固体微推力器的推力特点推导了卫星离散动力学模型；其次，以李雅普诺夫稳定性定律为基础，设计了混合系统脉冲切换控制律；最后，针对小卫星轨道控制进行了仿真验证。结果表明，基于混合系统建立的控制模型能准确反映微推力器的特点，轨道保持精度能达到0.2m，而且推力器消耗量满足卫星长时间在轨运行要求。

关键词: 微小卫星, 固体微推力器阵列, 混合切换系统, 轨道控制

Abstract:

Solid propellant micro-thruster array (SPMTA) as a new type of thrust device for micro-satellite station-keeping has the advantages of high accuracy, no fuel leakage and adjustable impulse. But the thrust of SPMTA is discontinuous, making the control system design different from the previous continuous system. To realize the full potential of SPMTA, a new control method for micro-satellite station-keeping was proposed based on the idea of switching control in hybrid system. First, the satellite discrete dynamic model was deduced according to the thrust characteristics of SPMTA. Then the hybrid switching control law was designed based on the Lyapunov stability theorem. Finally a numerical example of micro-satellite station-keeping was presented. Numerical simulation results indicate that the hybrid switching control method can accurately reflect the characteristics of SPMTA. The accuracy of station-keeping can reach 0.2 m and the consumption meets the satellite requirements of long time orbit operation.

Key words: micro-satellite, solid propellant micro-thrusterarray (SPMTA), hybrid switching system, orbit control