A method for transferring a spacecraft (10), such as an artificial satellite, from an initial elliptical orbit (30) to a final geostationary orbit (50), the spacecraft taking at least one intermediate elliptical orbit (40) propelled by electric propulsion means (12, 13), the method includes: when the spacecraft is in an intermediate orbit, a nominal thrust step (410) in which the propulsion means generate nominal thrust while the spacecraft is on at least part of a first orbital arc (41) passing through the apogee A of the intermediate orbit, and a minimum thrust step (420), in which the propulsion means are partly stopped or slowed while the spacecraft is on at least part (43) of a second orbital arc (42) passing through the perigee P of the intermediate orbit, the two orbital arcs being complementary.
PROCÉDÉ D'OPTIMISATION DU TRANSFERT D'ORBITE D'UN ENGIN SPATIAL À PROPULSION ÉLECTRIQUE ET SATELLITE METTANT EN OEUVRE LEDIT PROCÉDÉ
METHOD FOR OPTIMISING THE ORBITAL TRANSFER OF AN ELECTRICALLY PROPELLED SPACECRAFT, AND SATELLITE USING SAID METHOD
VERFAHREN ZUR OPTIMIERUNG DES ORBITALEN TRANSFERS EINES ELEKTRISCH ANGETRIEBENEN RAUMFAHRZEUGS UND DAS VERFAHREN VERWENDENDER SATELLIT
2024-03-13
Patent
Elektronische Ressource
Französisch
IPC: | B64G Raumfahrt , COSMONAUTICS |
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