Structure optimization for multi-FOV star sensors

Star sensors are significant attitude determination instruments in a spacecraft. Multi-FOV star sensors have advantages compared with conventional single FOV star sensors, and becomes an important development trend with a better accuracy and reliability. In order to realize the best measurement results, structure optimization for multi-FOV star sensor is the first problem in the design and application. The structure optimization for multi-FOV star sensor was researched. Firstly, the measurement model of multi-FOV star sensors was established. Then choosing the trace of the covariance matrix of quaternion errors as criterion, some factors influencing the accuracy of QUEST attitude determination algorithm, especially the angular distance between star vectors and star sensor, were studied. Finally simulation experiments on multi-FOV star sensors with different structures were carried out. The results show that multi-FOV star sensors have better accuracy with the increase of the angles between optical axes of FOVs, and realize the highest precision when the optical axes are orthogonal.