Analysis of expendable electric orbit transfer vehicles

Details Analysis of expendable electric orbit transfer vehicles Analysis of expendable electric orbit transfer vehicles

Jul 1990

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1990iep..confr....s&link_type=abstract

AIAA, DGLR, and JSASS, International Electric Propulsion Conference, 21st, Orlando, FL, July 18-20, 1990. 12 p.

Physics

Electric Propulsion, Geosynchronous Orbits, Orbit Transfer Vehicles, Payload Transfer, Titan Launch Vehicles, Earth Orbits, Expendable Stages (Spacecraft), Mission Planning, Payload Mass Ratio, Time Measurement

Scientific paper

This analysis estimated the Low Earth Orbit (LEO) to Geostationary Orbit (GEO) transfer times for various payloads and electric propulsion systems using the Titan IV launch vehicle. The results indicate that, based on current and projected technology, a minimum payload requirement of 5,800 (kg) delivered to GEO off a Titan IV, expendable EOTVs have limited value for supporting USAF heavy payload orbit transfer missions in less than 100 days. However, if trip time is permitted to increase beyond 100 days, the benefits realized by using electric propulsion are significant.

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