Solar powered electric propulsion orbit transfer vehicle design and operational effectiveness

Details Solar powered electric propulsion orbit transfer vehicle design and operational effectiveness Solar powered electric propulsion orbit transfer vehicle design and operational effectiveness

Jan 1986

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1986aiaa.meetx....m&link_type=abstract

AIAA, Aerospace Sciences Meeting, 24th, Reno, NV, Jan. 6-9, 1986. 12 p.

Computer Science

Cost Analysis, Design To Cost, Orbit Transfer Vehicles, Solar Electric Propulsion, Spacecraft Propulsion, Concentrators, Gallium Arsenides, Solar Arrays, Solar Cells

Scientific paper

The feasibility and cost effectiveness for using solar powered electric propulsion orbit transfer vehicles (EOTV) to move Block 3 NAVSTAR Global Positioning System (GPS) satellites from LEO to a 10,900 nm orbit were determined. The electric propulsion systems considered were present and 1990's technology ion engines using mercury, xenon or argon for a propellant. A systems cost model which combines payload, power sources, trajectory, and earth-to-LEO launch parameters with algorithms characterizing the electric propulsion system was used. The least costly systems which had a triptime equal to or less than 90 days were determined. These systems were then compared with the PAM D-II, Centaur-G, and IUS in terms of total deployment costs for 28 GPS satellites launched at a rate of four per year for seven years. The study found that a reusable EOTV with 12 mercury ion engines powered by gallium arsenide concentrator arrays could perform the mission for 57 percent of the cost of the cheapest chemical system.

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