Attitude determination algorithm for micro-satellite based on Gauss-Newton and UKF

被引：0
|
作者：
Kang Guohua [1 ]
Fan Kai [1 ]
Zhou Qiongfeng [1 ]
Liang Ertao [2 ]
机构：
[1] Nanjing Univ Aeronaut & Astronaut, Res Ctr Microsatellites, Nanjing 210016, Peoples R China
[2] Shanghai Inst Satellite Engn, Shanghai 201109, Peoples R China
来源：
CHINESE SPACE SCIENCE AND TECHNOLOGY | 2018年 / 38卷 / 02期
关键词：
micro-satellite; attitude determination; Gauss-Newton determination algorithm; unscented Kalman filter;
D O I：
10.16708/j.cnki.1000-758X.2018.0017
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
To improve the attitude determination accuracy of miniature low-cost attitude sensor, a micro-satellite attitude determination algorithm combining Gauss-Newton iterative algorithm and unscented Kalman filter (UKF) was designed based on the attitude sensor configuration of magnetometer/solar sensor/gyroscope. Firstly, the Gauss-Newton algorithm was used to fuse the data of magnetometer and solar sensor,and the optimal quaternion was obtained. Secondly,UKF was performed using the optimal quaternion combined with gyro data as the observed data, using the attitude quaternions and the angular velocity of the inertial system as the state variables, and the observed dimension was reduced and the observation equation was transformed into a linear equation by this method. As a result, the computational complexity is significantly reduced and the influence of measurement error on attitude determination accuracy is overcomed.
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收藏
页码：16 / 23
页数：8
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