Abstract
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.
| Original language | English |
|---|---|
| Pages (from-to) | 1559-1570 |
| Number of pages | 12 |
| Journal | Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering |
| Volume | 232 |
| Issue number | 8 |
| DOIs | |
| State | Published - 1 Jun 2018 |
Keywords
- formation flying
- fuel balance
- fuel consumption
- NetSat project
- Orbit design and control
- relative eccentricity/inclination vectors
- satellite clusters