Preferred gimbal angles for single gimbal control moment gyros Academic Article uri icon


  • This paper deals with torque command generation using single gimbal control moment gyros. The angular momentum and torque envelopes are assumed to be known a priori. A method based on back integration of the gyro torque equation from desired final conditions is used to determine a family of initial gimbal angles that avoid singularities. Each member of this family is defined as a preferred initial gimbal angle set. The pseudoinverse steering law is used during the numerical integrations. This procedure is demonstrated by means of numerical examples that include attitude control and momentum management of the Space Station Freedom. A feedback control scheme based on “null motion” is also developed to position the gimbals at preferred angles. © 1990 American Institute of Aeronautics and Astronautics, Inc., All rights reserved.

altmetric score

  • 3

author list (cited authors)

  • Vadali, S. R., Oh, H., & Walker, S. R.

citation count

  • 112

publication date

  • November 1990