Satellite Launcher on-off Controller for Attitude Tracking and Decoupling

摘要

A study about an on-off satellite launcher control law design for attitude tracking and decoupling was carried out. The study considered a linear decoupled and a linear coupled model of the vehicle to obtain the controller gains. A comparisonbetween the performance given by each design was performed The stability analysis of both designs was also carried out using the describing function technique and the circle criterion. Finally the robustness of the design based on the coupled model wasassessed with respect to uncertainties on the control forces and on the inertial parameters. It was assumed the vehicle flying a ballistic phase outside the atmosphere.