Research of sun vector in the attitude estimation of interplanetary spacecraft

Xiao Hua Chang*, Ping Yuan Cui, Hu Tao Cui

*此作品的通讯作者

科研成果: 期刊稿件文章同行评审

摘要

In the interplanetary spacecraft attitude determination based on vector observation, the geometric relation between the reference vectors is an important factor which influences the accuracy of attitude estimation. This paper proposes an optimal algorithm using the Sun line-of-sight vector to improve the attitude estimation accuracy. With the introduction of the Sun vector, the attitude quaternion obtained from the star-tracker is converted into a pair of mutually perpendicular reference vectors perpendicular to the Sun vector. The normalized weights are calculated according to the accuracy of the sensors. Furthermore, the optimal attitude estimation in the least square sense is achieved with the quaternion estimation method. Finally, the practical data of the Deep Impact mission is used to demonstrate the presented algorithm. The estimation error of attitude angles are within 150μrad, which meets the requirements of the Deep Impact mission.

源语言英语
页(从-至)758-763
页数6
期刊Yuhang Xuebao/Journal of Astronautics
31
3
DOI
出版状态已出版 - 3月 2010

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