Chinese Space Science and Technology ›› 2018, Vol. 38 ›› Issue (2): 16-23.doi: 10.16708/j.cnki.1000-758X.2018.0017

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Attitude determination algorithmfor micro-satellite based on Gauss-Newton and UKF

KANG Guohua1,*, FAN Kai1, ZHOU Qiongfeng1, LIANG Ertao2   

  1. 1. Research Center of Microsatellites, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
    2. Shanghai Institute of Satellite Engineering, Shanghai 201109, China
  • Received:2017-02-17 Accepted:2018-01-15 Online:2018-03-25 Published:2020-02-12

Abstract: To improve the attitude determination accuracy of miniature low-cost attitude sensor, a micro-satellite attitude determination algorithm combining Gauss-Newton iterative algorithmandunscented 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 gyrodata as the observed data, using the attitude quaternions and the angularvelocity of theinertial systemas 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.

Key words: micro-satellite, attitude determination, Gauss-Newton determination algorithm, unscented Kalman filter