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应用科学学报 ›› 2007, Vol. 25 ›› Issue (1): 108-110.

• 论文 • 上一篇    

基于伪陀螺/磁强计/地球敏感器的微卫星姿态自适应确定方法

郁丰, 刘建业, 熊智, 段方   

  1. 南京航空航天大学导航研究中心, 江苏南京 210016
  • 收稿日期:2006-01-19 修回日期:2006-08-25 出版日期:2007-01-31 发布日期:2007-01-31
  • 作者简介:郁丰,博士生,研究方向:GPS与微小卫星导航技术,E-mail:yufeng@nuaa.edu.cn;刘建业,教授,博导,研究方向:惯性技术、卫星定位、组合导航系统,E-mail:lyac@nuaa.edu.cn

Adaptive Determination of Micro-satellite Attitude Using Pseudo Gyro, Magnetometer and Earth Sensor

YU Feng, LIU Jian-ye, XIONG Zhi, DUAN Fang   

  1. Navigation Research Center, Nanjing University of Aeronautics and Astronautics, Nangjing 210016, China
  • Received:2006-01-19 Revised:2006-08-25 Online:2007-01-31 Published:2007-01-31

PDF

95

被引次数

12

摘要：

以伪陀螺、磁强计与地球敏感器构成的姿态测量系统为基础,设计了自适应扩展卡尔曼滤波算法.对轨道倾角不同的两种卫星的定姿性能进行了仿真,结果表明,该方案的滚动与俯仰角精度达到0.05°,航向角优于0.4°,且随轨道倾角的减小而改善;当地球敏感器发生故障时,大倾角轨道的卫星滚动与俯仰角精度优于0.5°,航向精度约1°;同时自适应滤波方法能显著地提高姿态确定的性能.

关键词: 伪陀螺, 地球敏感器, 微卫星, 自适应卡尔曼滤波, 磁强计

Abstract:

Attitude determination is a key that affects the performance of a micro satellite platform.An adaptive extended Kalman filtering algorithm is presented in this paper for attitude determination consisting of a pseudo gyro, a magnetometer and an earth sensor.Attitude determination performance of a satellite on two orbits with different inclination is studied by simulation.The results indicate that roll and pitch accuracy is about 0.05ånd heading accuracy is better than 0.4°.The accuracy is improved as inclination decreases.When the earth sensor fails, roll and pitch accuracy of the satellite on the orbit with large inclination is better than 0.5°, and heading accuracy is about 1°.The adaptive Kalman filter can evidently enhance attitude determination performance.

Key words: pseudo gyro, magnetometer, earth sensor, micro satellite, adaptive Kalman filtering

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