Integrated Design and Accuracy Analysis of Star Sensor and Gyro on the Same Benchmark for Satellite Attitude Determination System

被引：14
作者：
Hou, Bowen [1 ]
He, Zhangming [1 ,2 ]
Zhou, Haiyin [1 ,2 ]
Wang, Jiongqi [1 ]
机构：
[1] Natl Univ Def Technol, Coll Liberal Arts & Sci, Changsha 410072, Hunan, Peoples R China
[2] China Acad Space Technol, Beijing Inst Control Engn, Beijing 100080, Peoples R China
来源：
IEEE-CAA JOURNAL OF AUTOMATICA SINICA | 2019年 / 6卷 / 04期
关键词：
Accuracy analysis; attitude determination; gyro; integrated design; same benchmark; star sensor;
D O I：
10.1109/JAS.2019.1911600
中图分类号：
TP [自动化技术、计算机技术];
学科分类号：
0812 ;
摘要：
As an important sensor in the navigation systems, star sensors and the gyro play important roles in spacecraft attitude determination system. Complex environmental factors are the main sources of error in attitude determination. The error influence of different benchmarks and the disintegration mode between the star sensor and the gyro is analyzed in theory. The integrated design of the star sensor and the gyro on the same benchmark can effectively avoid the error influence and improves the spacecraft attitude determination accuracy. Simulation results indicate that when the stars sensor optical axis vectors overlap the reference coordinate axis of the gyro in the same benchmark, the attitude determination accuracy improves.
引用
收藏
页码：1074 / 1080
页数：7
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