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.
ASJC Scopus subject areas
- Control and Systems Engineering
- Aerospace Engineering
- Space and Planetary Science
- Electrical and Electronic Engineering
- Applied Mathematics