Development efforts in the United States have demonstrated the viability and performance potential of NTP systems. For example, Project Rover (1955 - 1973) completed 22 high power rocket reactor tests. Peak performances included operating at an average hydrogen exhaust temperature of 2550 K and a peak fuel power density of 5200 MW/m3 (Pewee test), operating at a thrust of 930 kN (Phoebus-2A test), and operating for 62.7 minutes on a single burn (NRXA6 test).1 Results from Project Rover indicated that an NTP system with a high thrust-toweight ratio and a specific impulse greater than 900 s would be feasible. Binary and ternary carbide fuels may have the potential for providing even higher specific impulses.


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    Title :

    A Nuclear Cryogenic Propulsion Stage for Near-Term Space Missions



    Conference:

    AIAA Space 2013


    Publication date :

    2013-09-10


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English




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