Orbit design and control method for satellite clusters and its applications to NetSat project

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...

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Bibliographic Details
Published in:Proceedings of the Institution of Mechanical Engineers. Part G, Journal of aerospace engineering Journal of aerospace engineering, 2018-06, Vol.232 (8), p.1559-1570
Main Authors: Zhou, Liang, Luo, Jian-jun, Nogueira, Tiago, Schilling, Klaus
Format: Article
Language:English
Subjects:
Clusters
Computer simulation
Control
Eccentric orbits
Feedback control
Graphical representations
Inclination
Nanosatellites
Nonlinear programming
Orbits
Satellites
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Summary: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.
ISSN:0954-4100
2041-3025
DOI:10.1177/0954410017696109