Abstract:

Aiming at the characteristics of intermediate-long-range ballistic missiles, the system equations, namely quaternion kinematics equation, gyro measuring model and satellite sensor measuring model, etc., are established on the basis of analyzing the revised measurement scheme of SINS/CNS combined navigation. The UKF algorithm is applied to the environment of the powered phase shutdown point, so that the output value of missile’s attitude achieves a high accuracy by on-line estimating the value of gyro drifts. Simulation results show that the UKF algorithm possesses a higher accuracy compared with EKF, QUEST, MLS and inertia iterative algorithms.