摘要
In this paper, an optimal orbit design and control method for satellite clusters is presented and the method is applied to the four pico/nano-satellite system NetSat. Firstly, the relative motion based on relative eccentricity/inclination vectors is reviewed. Then, an optimal orbit design method for the cluster flight is developed, and the initial states of satellites in the cluster are derived using a graphical representation of the relative eccentricity/inclination vectors combined with a constrained nonlinear programming method. Next, a novel satellite cluster feedback control method is designed, and an optimal three-maneuver strategy is proposed, which could maintain the satellites in a bounded relative motion, satisfying the tight fuel consumption constraints and fuel balance for a long operational lifetime. Finally, the feasibility and effectiveness of the optimal orbit design and control for satellites cluster and its application to NetSat project are verified through numerical simulations.
| 源语言 | 英语 |
|---|---|
| 页（从-至） | 1559-1570 |
| 页数 | 12 |
| 期刊 | Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering |
| 卷 | 232 |
| 期 | 8 |
| DOI | |
| 出版状态 | 已出版 - 1 6月 2018 |