DocumentCode
307212
Title
Output feedback stabilization of flexible spacecraft
Author
Gennaro, S. Di
Author_Institution
Dipartimento di Ingegneria Elettrica, Univ. di l´´Aquila, Italy
Volume
1
fYear
1996
fDate
11-13 Dec 1996
Firstpage
497
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;
fLanguage
English
Publisher
ieee
Conference_Titel
Decision and Control, 1996., Proceedings of the 35th IEEE Conference on
Conference_Location
Kobe
ISSN
0191-2216
Print_ISBN
0-7803-3590-2
Type
conf
DOI
10.1109/CDC.1996.574364
Filename
574364
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