Nuclear (NERVA) solid-core propulsion systems are compared to advanced cryogenic (F2/H2 and O2/H2) chemical propulsion systems for an orbit-to-orbit vehicle operating in the earth-moon space. The orbit-to-orbit vehicle is assumed to use propellants delivered by a reusable earth-to-orbit shuttle (EOS). High-velocity-increment missions (lunar and geostationary orbit) are emphasized. Optimum operating regimes for reusable and expendable chemical and nuclear systems are indicated. (Author)
Comparison of Chemical and Nuclear Propulsion for Lunar and Cislunar Transportation Systems
1970
29 pages
Report
Keine Angabe
Englisch
Combustion, Engines, & Propellants , Astronautics , Space propulsion , Rendezvous spacecraft , Costs , Lunar trajectories , Spacecraft nuclear propulsion , Cryogenic propellants , Velocity , Specific impulse , Manned spacecraft , Cargo , Mission profiles , Transfer trajectories , Parking orbit trajectories , Cost effectiveness , Space shuttles , OOS(Orbit to Orbit Shuttles) , Orbit to orbit shuttles , EOS(Earth to Orbit Shuttles) , Earth to orbit shuttles , Nerva engines , Cislunar , Incremental velocity
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