DocumentCode :
489736
Title :
On the Attitude Stabilization of a Rigid Spacecraft Using Two Control Torques
Author :
Krishnan, Hariharan ; McClamroch, Harris ; Reyhan, Mahmut
Author_Institution :
Department of Aerospace Engineering, University of Michigan, Ann Arbor, Michigan 48109.
fYear :
1992
fDate :
24-26 June 1992
Firstpage :
1990
Lastpage :
1995
Abstract :
The attitude stabilization problem of a rigid spacecraft using only two control torques is considered. The control torques are assumed to be generated by either gas jet actuators or momentum wheel actuators. In particular, we focus on the development of a control strategy for the following two problems which have not been considered elsewhere: the attitude stabilization of an axially symmetric spacecraft using control torques supplied by two pairs of gas jet actuators about axes spanning a two dimensional plane orthogonal to the axis of symmetry; the attitude stabilization of a spacecraft using control torques supplied by two momentum wheel actuators about axes spanning a two dimensional plane orthogonal to a principal axis. The complete dynamics of the spacecraft system fails to be controllable or even accessible in these cases. However, the spacecraft dynamics are strongly accessible and small time locally controllable in a restricted sease; but the restricted spacecraft dynamics cannot be asymptotically stabilized using any smooth C1 feedback. A nonsmooth feedback control strategy is developed for the restricted spacecraft dynamics which achieves an arbitrary reorientation of the spacecraft.
Keywords :
Attitude control; Control systems; Electrical capacitance tomography; Feedback; Meteorological radar; Nonlinear dynamical systems; Space vehicles; Tellurium; Torque control; Wheels;
fLanguage :
English
Publisher :
ieee
Conference_Titel :
American Control Conference, 1992
Conference_Location :
Chicago, IL, USA
Print_ISBN :
0-7803-0210-9
Type :
conf
Filename :
4792472
Link To Document :
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