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Sliding mode control of a launch vehicle during its atmospheric flight phaseis studied in the presence of unmatched disturbances. Linear time-varyingdynamics of the aerospace vehicle is converted into a systematic formula andthen dynamic sliding manifold as an advanced method is used in order toovercome the limited capability of conventional sliding manifolds in minimizingthe undesired effects of unmatched perturbations on the control system. At theend, simulation results are evaluated and the performance of two approaches arecompared in terms of stability and robustness of the autopilot.

Unmatched Perturbation Accommodation for an Aerospace Launch Vehicle Autopilot Using Dynamic Sliding Manifolds