关键词: 巡航导弹, 最优制导律, 航向误差, 时间增益

Abstract: Aiming at the problem of multi constraint precise strike of cruise missile in its terminal flight, a new guidance law under impact angle and impact time constraints is proposed independent of time to go prediction. The relative motion relationship between the missile and the target in the heading plane is deduced, and an impact time constrained guidance law based on additional heading angle is designed. By designing and optimizing the time gain coefficient, the additional heading angle is adjusted to make the actual flight time converge to the expected time quickly. On this basis, a guidance law with the impact angle and impact time constrained is obtained by combining the angle constrained and time constrained guidance laws. The guidance law does not depend on the time to go prediction, and then realizes the adaptive trajectory adjustment under multiple constraints in the heading plane. The trajectory convergence condition is obtained by solving the closed loop trajectory analysis of the biased guidance law, and the explicit convergence condition satisfying the impact angle and time constrained guidance law is given. Finally, it is verified by the mathematical simulation that the proposed multi constraint guidance law can meet the impact time and impact angle constraints and has fast convergence.

Key words: Cruise missile, Optimal guidance law, Heading error, Time gain