宇航学报

宇航学报 ›› 2011, Vol. 32 ›› Issue (7): 1462-1470.doi: 10.3873/j.issn.1000-1328.2011.07.005

• 制导、导航与控制 • 上一篇    下一篇

基于鲁棒H∞滤波的追踪卫星相对导航算法研究

孙兆伟1, 邓泓1, 刘皓2, 仲惟超1   

  1. (1.哈尔滨工业大学卫星技术研究所, 哈尔滨 150001;  2. 哈尔滨工业大学控制科学与工程系, 哈尔滨 150001)
  • 收稿日期:2010-06-17 修回日期:2010-09-18 出版日期:2011-07-15 发布日期:2011-07-27
  • 基金资助:
    收稿日期：20100617;
    \ 修回日期：20100918

Relative Navigation Algorithm for Chaser Satellite Based on Robust H∞ Filtering

SUN Zhao-wei1, DENG Hong1, LIU Hao2, ZHONG Wei-chao1   

  1. (1. Research Center of Satellite Technology, Harbin Institute of Technology, Harbin 150001, China;
    2. Department of Control Science and Engineering, Harbin Institute of Technology, Harbin 150001, China)
  • Received:2010-06-17 Revised:2010-09-18 Online:2011-07-15 Published:2011-07-27

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摘要： 针对追踪卫星存在轨道机动的情况，在模型存在不确定参数和非高斯噪声输入时，研究了基于鲁棒H∞滤波理论的相对导航算法。该算法采用线性不等式技术，根据Lyapunov稳定性原理推导出具有范数有界不确定参数离散系统的鲁棒H∞滤波器存在的充要条件，并将滤波器的设计转化为一个凸优化的求解问题。将该算法应用到追踪卫星导航中，仿真结果表明该算法在大轨道机动下有效且能消除模型不确定性和非高斯噪声对系统造成的不利影响。

关键词: 轨道机动, 不确定性, 非高斯噪声, 相对导航, 鲁棒滤波

Abstract:

Under the condition of the chaser satellite with orbit maneuvering, a relative navigation algorithm based on robust H∞ filtering theory is researched, considering parametric uncertainties and non\|Gaussian noise inputs. By means of the linear matrix inequality technique, the necessary and sufficient condition of the robust H∞ filtering for discrete system with norm\|bounded uncertainties is derived. The filter design is transformed into a convex optimization problem in terms of linear matrix inequality. Finally, the numerical simulation results show that the algorithm is effective in the presence of large orbit maneuver can eliminate unfavorable effects of parametric uncertainties and non\|Gaussian noise inputs, and it is applied to the relative navigation of chaser satellite.


Key words: Orbit maneuver, Uncertainty, Non-Gaussian noise, Relative navigation, Robust filtering

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