Optimal nonlinear feedback control for spacecraft attitude maneuvers Academic Article uri icon

abstract

  • 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.

citation count

  • 59

publication date

  • January 1986