A Novel Inertial/Celestial Integrated Navigation Method

As the navigation error caused by the sensor error of the inertial navigation cannot be modified by the traditional inertial/celestial integrated navigation system,a novel method which uses the measurements of celestial navigation system to modify the accelerator bias at the end of initial alignment and correct the gyro drift in close-loop during the navigation is proposed.The attitude,velocity and positioning precision are improved by this method.The simulation results show that this method is valid and efficient.