Document Type

Article

Publication Date

Winter 1-1983

Abstract

We apply Floquet theory to the problem of designing a control system for a satellite in an unstable periodic orbit. Expansion about a periodic orbit produces a time periodic linear system, which is augmented by a time periodic control term. We show that this can be done such that a) the application of control produces only inertial accelerations, b) positive real Poincare exponents are shifted into the left half-plane, and c) the shift of the exponent is linear with control gain. We apply these developments to an unstable orbit near the Earth-Moon L3 point perturbed by the Sun. Finally, we show that the control theory can be extended to include first order perturbations about the periodic orbit without increase in control cost.

Comments

This material is declared a work of the U.S. Government and is not subject to copyright protection in the United States.

No digital edition of JAS volume 31 is known to be vended by Springer or another publisher.

Source Publication

Journal of the Astronautical Sciences

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