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

摘要

As an important sensor in the navigation systems, star sensors and the gyro play important roles in spacecraft atti-tude determination system. Complex environmental factors are the main sources of error in attitude determination. The error in-fluence 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 im-proves the spacecraft attitude determination accuracy. Simula-tion results indicate that when the stars sensor optical axis vec-tors overlap the reference coordinate axis of the gyro in the same benchmark, the attitude determination accuracy improves.