Computer Science – Performance
Scientific paper
May 1994
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1994jspro..31..458p&link_type=abstract
Journal of Spacecraft and Rockets (ISSN 0022-4650), vol. 31, no. 3, p. 458-465
Computer Science
Performance
1
Chemical Propulsion, Cost Reduction, Liquid Propellant Rocket Engines, Liquid Rocket Propellants, Lunar Logistics, Payloads, Space Transportation, Spacecraft Propulsion, Liquid Hydrogen, Liquid Oxygen, Metal Propellants, Methane, Methylhydrazine, Nitrogen Tetroxide, Propulsion System Configurations, Propulsion System Performance
Scientific paper
To provide the transportation of lunar base elements to the moon, large high-energy propulsion systems will be required. Advanced propulsion systems for lunar missions can provide significant launch mass reductions and payload increases. These mass reductions and added payload masses can be translated into significant launch cost savings for the lunar base missions. The masses in low Earth orbit (LEO) were compared for several propulsion systems: nitrogen tetroxide/monomethyl hydrazine (NTO/MMH), oxygen/methane (O2/CH4), oxygen/hydrogen (O2/H2), and metallized O2/H2/Al propellants. Also, the payload mass increases enabled with O2/H2 and O2/H2/Al systems were addressed. In addition, many system design issues involving the engine thrust levels, engine commonality between the transfer vehicle and the excursion vehicle, and the number of launches to place the lunar mission vehicles into LEO will be discussed. Analyses of small lunar missions launched from a single STS-C flight are also presented.
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