When an inertial navigation system regains avalid aiding navigation signal after a long-term outage,normal state feedback correction in the Kalman Filter will cause a large instantaneous jump in the navigation parameters which mayseverely affect flight control stability.In this paper,we present a partial state feedback correctionmethodin the Kalman Filter to smooth the navigation parameters to solve this problem.The idea is to partially correct the navigation state in several steps according to the requirement of the guidance and control system.The simplicity of this method lies in the fact that no additionalchanges of the filter parametersare needed in the algo-rithm.The capability of residual monitoring and fault detection is the same with normal state feedback correction in the Kalman filter.Comparative simulation results show the effectiveness of the proposed method.