Missile Controlled by Lift and Divert Thrusters Using Nonlinear Dynamic Sliding Manifolds

Abstract

A new approach to the design of a kinetic-kill longitudinal autopilot steering the missile trajectory by the combination of aerodynamic lift and divert thrusters (dual-thrusters control) and with its attitude oriented by attitude thrusters is presented. The proposed approach may increase the total divert acceleration capability by up to 100%, improving the end-game intercept accuracy, when such capability is required. The pitch plane autopilot design is based on second-order sliding mode control using a nonlinear dynamic sliding manifold technique. A robust high-accuracy tracking of the missile normal acceleration guidance command is achieved in the presence of considerable model uncertainties created by the interactions between the airflow and the thrusters jets. Results of the computer simulation demonstrate excellent, robust, high-accuracy tracking performance of the proposed design.