Computer Science
Scientific paper
Jun 1993
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1993jpmc.confqz...m&link_type=abstract
AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference and Exhibit, 29th, Monterey, CA, June 28-30, 1993, 12 p.
Computer Science
Cost Reduction, Orbit Transfer Vehicles, Solar Electric Propulsion, Solar Thermal Propulsion, Spacecraft Launching, Earth Orbital Environments, Inertial Upper Stage
Scientific paper
An assessment of the payload capabilities and costs of orbit transfer vehicles using solar electric and solar thermal propulsion systems was conducted to compare these systems under consistent assumptions and to estimate potential reductions in the costs of launching satellites to geosynchronous orbit. The types of propulsion evaluated were hydrogen arcjet, xenon ion, xenon stationary plasma, hydrogen resistojet, carbon-60 ion, and hydrogen solar thermal. Trip time was set at a maximum of 180 d. Planar and concentrator solar arrays ranging in specific power from 50 to 200 W/kg were considered. Except for the resistojet, each of the propulsion types potentially enables launching Atlas-IIAS-class payloads on a Delta II at a net reduction in launch cost. Solar thermal propulsion offers the largest cost reduction. Using a high-voltage concentrator array, advanced ion propulsion was found to have a power requirement and cost lower than arcjet propulsion, because it yields a lighter vehicle that can be put in a high initial orbit. Ion propulsion also could enable the Delta II to launch as much GEO payload mass as the Titan-IV/IUS, at 50 percent lower cost, and could enable the Atlas IIAS to launch nearly as much as the Titan-IV/Centaur, at 20 percent lower cost. Achieving these results depends on having solar arrays providing a mission-average specific power of 60-100 W/kg at a cost of $1M/kW or less.
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