Launch Vehicle Control Design Using Sliding Mode Control Toolbox

Abstract

In this work, the problem of “Launch vehicle” (LV) in an ascent mode is considered. The use of Sliding Mode Control (SMC) Aero toolbox based on the relative degree approach for an LV dynamics reduces the complexity of the control paradigm. The emphasis on the SMC Aero toolbox and their library classifications based on the various criteria are discussed. Conventional l-SMC algorithm from the SMC Aero toolbox is employed for the LV robust, accurate and precise attitude controller design in the presence of the flexible modes, actuator dynamics, and bounded perturbations. The efficacy of the LV attitude control design using the SMC Aero toolbox is illustrated via numerical simulations.