A Multi-constraint Guidance Law for Cruise Missile Independent of Time-to-go Prediction

This paper presents a new impact time and angle control guidance law independent of time-to-go prediction for cruise missile. The relative motion relationship in heading plane is deduced. An impact time control guidance law based on additional heading angle is designed. Through the time gain coefficient design and optimization, the additional heading angle adjustment is implemented, and the actual flight time can quickly converge to the expected impact time. Accordingly, an impact time and angle control guidance law is presented. The guidance law is independent of the time-to-go prediction and realizes the adaptive trajectory adjustment under multiple constraints in 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 time and angle control guidance law is given. Finally, the mathematical simulations show that the presented multi-constraint guidance law can meet the impact time and impact angle constraints.