Attitude Determination of Nano Satellite Based on Gyroscope, Sun Sensor and Magnetometer

被引：13
|
作者：
Ni, Shaobo [1 ,2 ]
Zhang, Cui [3 ]
机构：
[1] Beijing Inst Technol, Sch Aerosp Engn, Beijing 100081, Peoples R China
[2] Beijing Inst Technol, Beijing Aerosp Automat Control Inst, Beijing 1000854, Peoples R China
[3] Beihang Univ, Sch Instrumentat Sci & Optelect Engn, Beijing 100191, Peoples R China
来源：
CEIS 2011 | 2011年 / 15卷
关键词：
nano-satellite; Attitude determination; Optic gyroscope; Sun sensor; Magnetometer;
D O I：
10.1016/j.proeng.2011.08.177
中图分类号：
TP [自动化技术、计算机技术];
学科分类号：
0812 ;
摘要：
With the fast development of nano-satellite applications, higher requirements on the method and accuracy for determining attitude of Nano-satellite are presented. Aiming at the accuracy requirements of attitude determination of sun-oriented mode of the nano-satellite, an integrated attitude sensor is built with combining of gyroscope, magnetometer and sun sensor. Furthermore, the extended Kalman filter is used to fuse measurement data from gyroscope, magnetometer and sun sensor. A simulation model of attitude determination is built, and a few simulations are performed. The simulation results show that the accuracy of the integrated attitude determination sensor proposed in this paper can meet the accuracy requirement (0.05. Deg.) of nano-satellite attitude determination. (C) 2011 Published by Elsevier Ltd. Selection and/or peer-review under responsibility of [CEIS 2011]
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收藏
页数：5
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