Solar electric propulsion (SEP) technology is currently being used for geostationary satellite station keeping to increase payload mass. Analyses show that advanced electric propulsion technologies can be used to obtain additional increases in payload mass by using these same technologies to perform part of the orbit transfer. In this work three electric propulsion technologies are examined at two power levels for an Atlas 2AS class spacecraft. The on-board chemical propulsion apogee engine fuel is reduced to allow the use of electric propulsion. A numerical optimizer is used to determine the chemical burns which will minimize the electric propulsion transfer time. Results show that for a 1550 kg Atlas 2AS class payload, increases in net mass (geostationary satellite mass less wet propulsion system mass) of 150 to 800 kg are possible using electric propulsion for station keeping, advanced chemical engines for part of the transfer, and electric propulsion for the remainder of the transfer. Trip times are between one and four months.
Advanced Propulsion for Geostationary Orbit Insertion and North-South Station Keeping
1995
18 pages
Report
Keine Angabe
Englisch
Spacecraft Trajectories & Flight Mechanics , Electric & Ion Propulsion , Arc jet engines , Geosynchronous orbits , Ion engines , Orbit insertion , Solar electric propulsion , Stationkeeping , Trajectory optimization , Transfer orbits , Chemical propulsion , Orbital maneuvers , Payloads , Synchronous platforms , Transit time
Advanced Propulsion for Geostationary Orbit Insertion and North-South Station Keeping
Online Contents | 1997
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