| Article ID | Journal | Published Year | Pages | File Type |
|---|---|---|---|---|
| 721542 | IFAC Proceedings Volumes | 2007 | 6 Pages |
Abstract
The problem of orbit control for spacecraft on elliptical orbits is analysed and an approach to the design of optimal constant gain controllers for the periodic dynamics of relative motion is proposed. In particular, it is shown how the proposed approach can guarantee closed loop stability and optimal performance both in the case of circular and elliptical orbits.
Related Topics
Physical Sciences and Engineering
Engineering
Computational Mechanics
