Suboptimal Asymmetric Spacecraft Maneuvers Using Two Controls

摘要

Extensive literature exists for controlling the attitude motion of rigid and flexible spacecraft. For a fully functioning spacecraft, it is assumed that all actuators required for completing the control task are available. Many different control strategies have been proposed for handling the nominal three-axis control case. More specialized literature has considered off-nominal cases where actuator failures have occurred. For example, Tsiotras and Longuski have considered the case designing control strategies for handling situations in which sensor and actuator failures limit the control options available for carrying out the original mission objectives.