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In this paper, a novel adaptive three-dimensional finite-time guidance law is proposed to achieve the interception of maneuvering targets. The proposed guidance law considers terminal angle constraints and the coupled nonlinear dynamics of the three-dimensional missile-target interception scenario. Adaptive control technique and sliding mode control theory are applied to design the guidance law. More specifically, the designed adaptive law can ensure sliding mode manifold fast reach a predefined region and weaken the chattering phenomenon without the upper bounds of target maneuvers. Furthermore, the line-of-sight angle tracking errors and the line-of-sight angular rates can achieve finite-time convergence via the designed nonsingular fast terminal sliding mode controller. Therefore, the accurate interception of the missile against maneuvering targets can be achieved via the proposed guidance law. Numerical simulations show the effectiveness and superiority of the proposed guidance law.

A novel adaptive three-dimensional finite-time guidance law with terminal angle constraints for interception of maneuvering targets