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
16.07.2015
Patent
Elektronische Ressource
Englisch
IPC: | B64G Raumfahrt , COSMONAUTICS |
Europäisches Patentamt | 2019
|Europäisches Patentamt | 2016
|