A new three-dimensional adaptive sliding mode guidance law for maneuvering target with actuator fault and terminal angle constraints

Abstract

In this paper, an adaptive terminal sliding mode guidance law is designed to intercept the maneuvering target with terminal line of sight angle constraints in three-dimensional space, and the actuator failure is considered. First, the relative kinematics model of three-dimensional space missile target considering fault is established. Then, the guidance law is designed by using the nonsingular fast terminal sliding mode method, which makes the tracking error and rate converge in finite time; Aiming at the problem of uncertain disturbance and fault in the model, the adaptive method is used to evaluate online. Finally, the Lyapunov stability theorem is used to prove that the missile target system is closed-loop stable under the proposed guidance law. Simulation results verify the performance of the proposed guidance law.