A Blended Autopilot for Dual Control Missile Using Generalized Predictive and Adaptive Terminal Sliding Mode Control

Abstract

A blended autopilot algorithm is developed using generalized predictive control and adaptive non-singular terminal sliding mode control, for dual control missile steered by combination of aerodynamic fins and reaction jets. The blended algorithm considers the reaction jets control design prior due to its inherent control error, and then treats the aerodynamic fin control on the basis of the reaction jets control results. The generalized predictive control method is applied to the reaction jets control, which could make the missile achieve desired performance with a small number of consumed reaction jets. Then a novel adaptive non-singular terminal sliding mode control method is proposed for the aerodynamic control system design, to meet the requirements of robustness and fast response for the control of the missile. The unknown bound of the uncertainties and disturbances is estimated adaptively in the control, which makes the control with better robustness. Using the Lyapunov stability theory, the finite time convergence in both reaching and sliding phases is achieved. Finally, the simulations are conducted on the nonlinear longitudinal missile model with uncertainties and disturbances, and the simulation results demonstrate the effectiveness of the blended autopilot algorithm.