Optimal reorientation of a multibody spacecraft through joint motion using averaging theory

The problem of reorienting a multibody spacecraft using appendage joint motion is addressed. Averaging theory shows that small periodic actuation of such appendages results in a secular change in the orientation of the multibody spacecraft. The secular variation is controllable through choice of control profiles. Using optimal control theory, an analytic control algorithm that minimizes the required control effort is developed for a four-link multibody system having zero angular momentum.