Lunar lander and return propulsion system trade study

Details Lunar lander and return propulsion system trade study Lunar lander and return propulsion system trade study

Aug 1993

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1993stin...9416496h&link_type=abstract

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Computer Science

Performance

Liquid Rocket Propellants, Lunar Landing, Lunar Launch, Lunar Spacecraft, Propulsion System Configurations, Propulsion System Performance, Spacecraft Design, Spacecraft Reliability, Tradeoffs, Lunar Programs, Mission Planning, Modularity, Spacecraft Modules, Systems Engineering

Scientific paper

This trade study was initiated at NASA/JSC in May 1992 to develop and evaluate main propulsion system alternatives to the reference First Lunar Outpost (FLO) lander and return-stage transportation system concept. Thirteen alternative configurations were developed to explore the impacts of various combinations of return stage propellants, using either pressure or pump-fed propulsion systems and various staging options. Besides two-stage vehicle concepts, the merits of single-stage and stage-and-a-half options were also assessed in combination with high-performance liquid oxygen and liquid hydrogen propellants. Configurations using an integrated modular cryogenic engine were developed to assess potential improvements in packaging efficiency, mass performance, and system reliability compared to non-modular cryogenic designs. The selection process to evaluate the various designs was the analytic hierarchy process. The trade study showed that a pressure-fed MMH/N2O4 return stage and RL10-based lander stage is the best option for a 1999 launch. While results of this study are tailored to FLO needs, the design date, criteria, and selection methodology are applicable to the design of other crewed lunar landing and return vehicles.

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