A first inclination vector associated with a first satellite of the plurality of satellites is established. A second inclination vector associated with a second satellite 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
2015-07-16
Patent
Electronic Resource
English
IPC: | B64G Raumfahrt , COSMONAUTICS |
European Patent Office | 2019
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