Study on Application of the Fiber-Optical Gyroscope for Satellite Attitude Control System

摘要

As a new kind of solid state inertial device, the fiber-optic gyroscope will be widely used for spacecrafts. In this paper, we study the arithmetic of satellite attitude determination and attitude control using fiber-optic gyroscopes. For improving the precision of satellite attitude control, the precision of attitude estimation must be improved, fiber-optic gyroscope can produce angle rate continuously, but it has drift error which will be increased with time and is influenced by environment easily. Star sensor has high precision for attitude detection and its error will not be increased with time, but it can not work continuously. So using merits of fiber-optic gyroscopes and star sensors, the precision of satellite attitude estimation will be increased. In theory, fiber-optic gyroscopes bias error can be corrected using star sensors. The detailed derivation of arithmetic is based on the model of satellite kinematics and characters of fiber-optic gyroscopes and star sensors. This paper presents a more accurate filter which develops methods for on-line tuning of the noise covariance matrices to build adaptive and robust Kalman filter. The simulation of this arithmetic is presented to show the filter performance. Not as traditional inertial devices ,the angular random walk is a key parameter for fiber-optic gyroscope. We use transition district manner to improve the strategy of satellite attitude control according to the character of fiber-optical gyroscopes output. The estimation shows that this strategy will debase the demand of attitude control system to fiber-optical gyroscopes.