Study of the method for the spacecraft autonomous celestial navigation based on the Kalman filter

The high positioning precision can be obtained by the autonomous navigation method based on indirectly sensing horizon by stellar atmospheric refraction. Because of the finite space-time resolving power of the stratosphere density model, large instantaneous error will occur in the horizon sensed by this method In this case, the performance of the navigation filter will degrade, even diverge. In this paper the Fuzzy Inference System (FIS) is applied to the autonomous celestial navigation to resolve this problem. The navigation filter can obtain the adaptive ability when the observation is exceptional. The results of the computer simulation demonstrate the validity of this method.