Optimal nonlinear feedback control for spacecraft attitude maneuvers
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Polynomial feedback controls for large-angle, nonlinear spacecraft attitude maneuvers are developed. A fivebody configuration consisting of an asymmetric spacecraft and four reaction wheels is considered. Attention is restricted to the momentum transfer class of internal control torques; this, in conjunction with the choice of Euler parameters as attitude coordinates, permits several important order reduction simplifications. Three numerical examples are included to illustrate applications of the concepts presented. © 1985 American Institute of Aeronautics and Astronautics, Inc.
author list (cited authors)
Carrington, C. K., & Junkins, J. L.