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.
JOURNAL OF GUIDANCE CONTROL AND DYNAMICS
author list (cited authors)
CARRINGTON, C. K., & JUNKINS, J. L.
complete list of authors
CARRINGTON, CK||JUNKINS, JL