Terminal Guidance Law Design for Compound Control Missile Based on Time-Delay Control Theory

This paper proposes a new terminal guidance law based on zeroing line of sight rate using time delay control theory and back-stepping method. Firstly, the plane guidance model of the compound control missile is established accounting for dynamic characteristics of double actuator, where the unknown interferences such as target maneuver, time-varying relative velocity and parameter perturbation, constitute the system unmatched uncertain parts. Secondly, the guidance law is proposed by introducing the time delay control theory into the solution of terminal guidance, estimating target maneuver and accurate compensation of subsystems at each layer. Then the closed-loop stability of the whole system is demonstrated by giving the basis of parameter selection in the second half of this paper. Finally, the simulation analysis is carried out under the scenario of air targets with large maneuvering. The guidance law can independently estimate target maneuverability, verifying the correctness and effectiveness of combating unknown interfere systems.