Design of An Optimal Midcourse Guidance Law for the Guidance Handover of the Ship-to-Air Missile

For the case of ship-to-air missile intercepting the low target,the relative motion model between the missile and the target was firstly established at the midcourse guidance segment.Considering the velocity charac teristics of the ship-to-air missile,the solution model of the prediction encounter point was presented based on the radio information of the guidance platform,and the dynamic constraint condition at the end of the mid course guidance was determined.Based on the solution model of the interception point,an optimal midcourse guidance law was designed by applying the concept of the pseudo control variable and the theory of optimal con trol.The simulation results validated the correctness and effectiveness of the solution model of the interception point and the designed optimal midcourse guidance law.