Nuclear rockets for terrestrial and space missions

The dual electric-nuclear rocket system combines a nuclear rocket for high thrust phases of manned interplanetary space missions with a cluster of electric engines powered by the same reactor for high-specific-impulse, low-thrust phases. For a seven-man fast Mars mission, the dual electric-nuclear engine can reduce the space vehicle gross weight in initial earth orbit to between 40 and 60% of that for an all-nuclear engine. The nuclear reactor is designed to operate in both open-cycle and closed-cycle systems. During open-cycle high-thrust phases, hydrogen propellant is heated as it flows through the reactor core passages and then exhausts through a nozzle to give J sp of about 833 sec. These open-cycle, high-thrust phases are used for orbital escape or orbital capture. In the closed-cycle phases, the reactor, operating at reduced power, heats a circulating fluid that drives a turbogenerator. The generator, in turn, powers a cluster of MHD accelerators, providing low thrust at an J sp of 4900 sec. These lowthrust phases are used for shortening trip times in what otherwise would be the coast periods of the nuclear rocket mission.

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Nuclear Space Vehicles Using Pebble Bed Reactors

Levoy¹,

Newgard²

1960

SAE Technical Paper Series

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Nuclear rockets for terrestrial and space missions

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Nuclear Rocket Engine Controls in an Orbital Transfer Role

Nuclear Rocket Engine Controls in an Orbital Transfer Role

Dual Electric-Nuclear Engine

Nuclear Space Vehicles Using Pebble Bed Reactors

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