A low pressure nuclear thermal rocket (LPNTR) is configured to meet the requirements of a nuclear stage for manned Mars exploration. Safety, reliability and performance are given equal consideration in selecting the stage configuration. Preliminary trade studies are conducted to size the engine thrust and determine the thrust chamber pressure. A weight breakdown and mechanical configuration for the selected LPNTR concept are defined. A seven engine stage configuration is selected which gives a two engine out capability and eliminates the need for engine gimbaling. The stage can be ground assembled and launched as a unit including tankage for trans Earth injection and Earth orbital capture. The tankage is configured to eliminate the need for an inert shield. The small engine will be cheaper to develop than a single engine providing full thrust, and will be compatible with stages for Earth orbital, Lunar and deep space missions. Mission analyses are presented with engine operation in a high thrust mode and in a dual range high thrust-low thrust mode. Mass savings over a reference NERVA stage are projected to be 45--55% for the high thrust operating mode and 50--60% for the dual range mode. Potential exists for further increases in performance by optimizing the thrust chamber/nozzle design. 6 refs., 10 figs., 5 tabs.


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    Title :

    Preliminary stage configuration for a low pressure nuclear thermal rocket (LPNTR)


    Contributors:

    Publication date :

    1990


    Size :

    18 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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