Abstract:

By analyzing the traditional star-tracking correction technology, this paper studies the star-tracking direct correction method which is based on star sensor dynamic separation initial displacement angles and main errors of inertial measure unit (IMU) in order to carry out automatic navigation and improve the hitting accuracy and quick reaction capability of near-earth flight vehicles. Through comprehensive application and improvement of the best correction factor method, this paper proposes the startracking comprehensive correction method which combines the two methods above-mentioned and the accelerometer dynamic error separation technology. The simulation results show that obvious effects can be achieved by using the star-tracking integrated correction method.