Electric propulsion offers large fuel savings compared with chemical propulsion, at the expense of lower thrust levels and longer transfer times. In the case of orbit raising, typically for telecommunication satellites targeting a geostationary orbit, the priority is to minimize the transfer time, taking into account the eclipses which interrupt the energy supply required by the engine. In the case of orbit plane changes, typically for constellations of satellites in low Earth orbits, the priority is to minimize the transfer consumption by using the natural precession due to the Earth flattening. These problems are solved by optimal control approaches, using specific properties issued from the theoretical analysis.
Low‐Thrust Transfer
Space Trajectories ; 239-274
24.12.2024
36 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
low thrust , eclipse , Edelbaum , Pontryaguin , Hamiltonian , costate
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|Thrust Limited Coplanar Aeroassisted Orbital Transfer
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|Optimal, Low-Thrust, EarthMoon Orbit Transfer
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