Installation Error Calibration Method of Stellar/inertial Integrated Navigation System for Star Tracker with Narrow Field of View

As the star tracker with a narrow field of view cannot perform the attitude determination independently, the installation matrix between the star tracker and the inertial measurement units cannot be estimated directly. To solve this problem, a calibration method based on the observation of the dot product error of two-star vectors is proposed. It utilizes high-precision relative attitude information of the gyroscope units, which is suitable for engineering practice. Numerical simulations and ground experiments are conducted to validate the feasibility of the calibration method. It is proved that the proposed method can control the calibration error of the x-axis and y-axis in the order of arcseconds when the installation angle errors are less than 0.2°.