Electric propulsion was evaluated for orbit insertion, satellite positioning and de-orbit applications on big (hundreds of kilograms) and little (tens of kilograms) low earth orbit communication satellite constellations. A simple, constant circumferential thrusting method was used. This technique eliminates the complex guidance and control required when shading of the solar arrays must be considered. Power for propulsion was assumed to come from the existing payload power. Since the low masses of these satellites enable multiple spacecraft per launch, the ability to add spacecraft to a given launch was used as a figure of merit. When compared to chemical propulsion ammonia resistojets, ion, Hall, and pulsed plasma thrusters allowed an additional spacecraft per launch Typical orbit insertion and de-orbit times were found to range from a few days to a few months.
Electric Propulsion for Low Earth Orbit Communication Satellites
1997
16 pages
Report
No indication
English
Unmanned Spacecraft , Common Carrier & Satellite , Electric propulsion , Communication satellites , Satellite constellations , Low earth orbits , Orbit insertion , Payloads , Spacecraft launching , Figure of merit , Chemical propulsion , Ammonia , Resistojet engines , Ion propulsion , Hall effect , Plasma engines , Satellite orientation , Time dependence , Launch vehicles , Positioning
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