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)


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