Design of Integrated Guidance and Control Law with LOS Rate Estimate Based on UKF

Abstract

The traditional way to design a guidance and control system of a missile is to form subsystems separately, with disadvantages of lack of cooperation between subsystems. A homing missile with a strapdown seeker was discussed, and an integrated guidance and control (IGC) model in vertical plane has been formulated. A scheme of IGC law based on sliding mode control (SMC), using the line of sight (LOS) rate estimated by Unscented Kalman Filter (UKF) from the strapdown seeker was proposed. In addition, to verify the effectiveness of the IGC law based on SMC with LOS rate estimation by UKF algorithm, a numerical simulation by MATLAB was made. The simulation results demonstrated that the flight attitude was in stability and the missile was able to hit the target with a small miss distance.