Integrated guidance method considering radar seeker feedforward

Aiming at a large maneuvering target, air-to-air missile radar seeker tracking error will increase and guidance accuracy will decline. A new radar seeker feedforward intergated guidance technology is proposed based on the maneuvering target. In order to accelerate the seeker's response speed and reduce the tracking error, a line-of-sight(LOS) angular rate feedforward loop is designed to compensate the radar seeker angle tracking system. Based on the LOS coordinate system, the radar seeker intergated guidance algorithm uses the Kalman filter to estimate both LOS angular rate and target acceleration. Then compensate estimated LOS angular rate commend to the seeker tracking system and compensate estimated target acceleration to the optimal guidance law. Simulation results show that the radar seeker intergated guidance algorithm can estimate LOS angular rate and target acceleration at the same time.