The conceptual design of a nuclear rocket based on the vapor core reactor is presented. The Nuclear Vapor Thermal Rocket (NVTR) offers the potential for a specific impulse of 1000 to 1200 s at thrust‐to‐weight ratios of 1 to 2. The design is based on NERVA geometry and systems with the solid fuel replaced by uranium tetrafluoride (UF4) vapor. The closed‐loop core does not rely on hydrodynamic confinement of the fuel. The hydrogen propellant is separated from the UF4 fuel gas by graphite structure. The hydrogen is maintained at high pressure (∼100 atm), and exits the core at 3,100 K to 3,500 K. Zirconium carbide and hafnium carbide coatings are used to protect the hot graphite from the hydrogen. The core is surrounded by beryllium oxide reflector. The nuclear reactor core has been integrated into a 75 klb engine design using an expander cycle and dual turbopumps. The NVTR offers the potential for an incremental technology development pathway to high performance gas core reactors. Since the fuel is readily available, it also offers advantages in the initial cost of development, as it will not require major expenditures for fuel development.


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    Titel :

    Nuclear vapor thermal reactor propulsion technology


    Beteiligte:
    Maya, Isaac (Autor:in) / Diaz, Nils J. (Autor:in) / Dugan, Edward T. (Autor:in) / Watanabe, Yoichi (Autor:in) / McClanahan, James A. (Autor:in) / Wen‐Hsiung Tu (Autor:in) / Carman, Robert L. (Autor:in) / El-Genk, Mohamed S. (Herausgeber:in) / Hoover, Mark D. (Herausgeber:in)

    Kongress:

    10th SymposiumùSpace Nuclear Power and Propulsion ; 1993 ; Albuquerque, NM, USA


    Erschienen in:

    AIP Conference Proceedings ; 271 , 3 ; 1583-1590


    Erscheinungsdatum :

    20.01.1993


    Format / Umfang :

    8 pages





    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




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