Using electric propulsion to deliver materials to lunar orbit for the development and construction of a lunar base was investigated. Because the mass of the base and its life-cycle resupply mass are large, high specific impulse propulsion systems may significantly reduce the transportation system mass and cost. Three electric propulsion technologies (arcjet, ion, and magnetoplasmadynamic (MPD) propulsion) were compared with oxygen/hydrogen propulsion for a lunar base development scenario. Detailed estimates of the orbital transfer vehicles' (OTV's) masses and their propellant masses are presented. The fleet sizes for the chemical and electric propulsion systems are estimated. Ion and MPD propulsion systems enable significant launch mass savings over O2/H2 propulsion. Because of the longer trip time required for the low-thrust OTV's, more of them are required to perform the mission model. By offloading the lunar cargo from the manned O2/H2 OTV missions onto the electric propulsion OTV's, a significant reduction of the low Earth orbit (LEO) launch mass is possible over the 19-year base development period.
Electric Propulsion for Lunar Exploration and Lunar Base Development
1992
11 pages
Report
Keine Angabe
Englisch
Electric & Ion Propulsion , Extraterrestrial Exploration , Electric propulsion , Lunar bases , Lunar flight , Space transportation , Hydrogen oxygen engines , Lunar spacecraft , Propulsion system performance , Cargo , Costs , High impulse , Ion propulsion , Manned spacecraft , Orbit transfer vehicles , Plasma propulsion , Propulsion system configurations , Specific impulse
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