Partial Integrated Missile Guidance and Control with Finite Time Convergence

A novel method of adaptive nonsingular terminal sliding mode control is proposed for a class of nonlinear systems subject to disturbances and uncertainties. The obtained results are applied to integrated guidance and control design for a missile. Using the Lyapunov stability theory, it is shown that the finite time convergence in both reaching and sliding phase is achieved by virtue of a terminal sliding surface and a switching controller that avoids singularity. With the assumption that the disturbances and uncertainties are bounded and the bounds are unknown, the adaptive method is incorporated with the controller design, which makes the proposed adaptive nonsingular terminal sliding mode control with better robustness. Due to the inherent property of time-scale separation between the translational and rotational dynamics, partial integrated guidance and control with a two-loop controller structure is designed for a missile based on the proposed adaptive nonsingular terminal sliding mode control. The outer loop, which generates directly the commanded pitch rate is constructed, and then the inner loop is designed to track the outer loop command. Finally, simulations are conducted on the nonlinear longitudinal missile model and results demonstrate the effectiveness of adaptive nonsingular terminal sliding mode control.