A first inclination vector associated with a first satellite (12) of the plurality of satellites is established. A second inclination vector associated with a second satellite (42) of the plurality of satellites is established. The first satellite and the second satellite are controlled, such that the first satellite and the second satellite are synchronized with a node.
Methods and apparatus for controlling a plurality of satellites using node-synchronous eccentricity control
Verfahren und Vorrichtung zur Steuerung einer Vielzahl von Satelliten mit knotensynchroner Exzentrizitätssteuerung
Procédés et appareil pour commander une pluralité de satellites au moyen de contrôle d'excentricité de noeuds synchrones
2019-03-20
Patent
Electronic Resource
English
IPC: | B64G Raumfahrt , COSMONAUTICS |
European Patent Office | 2016
|European Patent Office | 2015
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