Dynamic Sliding Mode Autopilot for an Aerospace Launch Vehicle

Tracking of guidance commands with unmatched disturbances is considered for a linear time-varying aerospace launch vehicle during the atmospheric flight in sliding mode control theory. Dynamics of aerospace launch vehicle is rendered into a regular form and a practical application of dynamic sliding manifold is employed to circumvent restrictive performance of conventional sliding manifolds in accommodating unmatched perturbations. Results of simulations are presented to demonstrate the performance, robustness, and stability of the considered autopilot.