Integrated Guidance and Control Design for Orbit Injection Phase of Launch Vehicle

Abstract

AbstractThis study develops a modified integrated guidance and control (IGC) design for the orbit injection phase of a launch vehicle. Firstly, a coupled full-stage position and attitude dynamic model of a launch vehicle is firstly formulated. Secondly, dynamic surface control (DSC) technique is introduced, based on the nonlinear IGC scheme, to achieve the orbit injection mission, with saturation issues in view of the thrust magnitude and swing constraints of the main engines being considered. Besides, the control scheme utilizes a finite-time extended state observer (ESO) to handle various uncertainties in the system. Furthermore, the stability analysis of the closed-loop system is given by using the Lyapunov theory. Finally, numerical simulation is set to verify the proposed IGC method has satisfactory control accuracy and robust performance for the orbit-injection control under various uncertainties.KeywordsLaunch vehicleOrbit injectionIntegrated guidance and controlFinite-time extended state observer design