One approach being considered for transporting large space structures from low Earth orbit (LEO) to geosynchronous equatorial orbit (GEO) is the use of low thrust chemical propulsion systems. A variety of chemical rocket engine cycles evaluated for this application for oxygen/hydrogen and oxygen/hydrocarbon propellants (oxygen/methane and oxygen/RF-1) are discussed. These cycles include conventional propellant turbine drives, turboalternator/electric motor pump drive, and fuel cell/electric motor pump drive as well as pressure fed engines. Thrust chamber cooling analysis results are presented for regenerative/radiation and film/radiation cooling.
LEO-to-GEO low thrust chemical propulsion
1980-03-01
Conference paper
No indication
English
Low-thrust chemical propulsion
NTRS | 1980
|Low-Thrust Chemical Orbit Transfer Propulsion
NTIS | 1979
|Low-thrust chemical orbit transfer propulsion
AIAA | 1979
|Low-thrust chemical orbit transfer propulsion
NTRS | 1979
|Low-thrust chemical orbit transfer propulsion
NTRS | 1979
|