Title :
Output feedback stabilization of flexible spacecraft
Author_Institution :
Dipartimento di Ingegneria Elettrica, Univ. di l´´Aquila, Italy
Abstract :
In this work a dynamic controller is derived for a spacecraft with flexible appendages. The control aim is to perform large angle maneuver. The actuators are reaction-wheels and the measured variables are the parameters describing the attitude and the angular velocity of the reaction wheels. Simulations show the feasibility of a control scheme based on such a controller
Keywords :
aerospace control; attitude control; control system synthesis; feedback; flexible structures; kinematics; nonlinear control systems; space vehicles; stability; angular velocity; attitude; dynamic controller; flexible appendages; flexible spacecraft; large angle maneuver; output feedback stabilization; reaction-wheels; Actuators; Angular velocity; Angular velocity control; Control systems; Equations; Nonlinear dynamical systems; Output feedback; Space vehicles; Velocity measurement; Wheels;
Conference_Titel :
Decision and Control, 1996., Proceedings of the 35th IEEE Conference on
Conference_Location :
Kobe
Print_ISBN :
0-7803-3590-2
DOI :
10.1109/CDC.1996.574364
