A Cooperative Guidance Law for Multiple Missiles with Impact Time and Terminal Angle Constraints

Abstract

To solve the problem of multiple missiles attacking a maneuverable target simultaneously, a novel finite-time cooperative guidance law with line-of-sight angle constraint is proposed based on sliding-mode control method. The multiple missiles cooperative guidance model is constructed based on in-plane missiles-target relative motion equations and the process of design including two stages. In the first stage, a distributed finite time cooperative guidance law in the line-of-sight direction is designed based on the adaptive super-twisting and integral sliding mode control theory. Secondly, the acceleration command on the normal direction of the line-of-sight is developed. Mathematical simulation of time cooperation of multiple missiles is carried out for maneuverable target to ensure the missile's line-of-sight angle converges to its desired value in finite time. The proposed guidance law guarantees the attacking of target, and the attack time cooperation of multiple missiles is realized as well.