This paper presents performance predictions for LANTR nozzles and the system implications for their use in a manned Mars mission. The LANTR concept is rocket thrust augmentation by injecting Oxygen into the nozzle to combust the Hydrogen exhaust of a Nuclear Thermal Rocket. The performance predictions are based on three‐dimensional reacting flow simulations using VULCAN. These simulations explore a range of O2/H2 mixture ratios, injector configurations, and concepts. These performance predictions are used for a trade analysis within a system study for a manned Mars mission. Results indicate that the greatest benefit of LANTR will occur with In‐Situ Resource Utilization (ISRU). However, Hydrogen propellant volume reductions may allow greater margins for fitting tanks within the launch vehicle where packaging issues occur.


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    Title :

    3D Reacting Flow Analysis of LANTR Nozzles



    Conference:

    SPACE TECH.& APPLIC.INT.FORUM-STAIF 2006: 10th Conf Thermophys Applic Microgravity; 23rd Symp Space Nucl Pwr & Propulsion; 4th Conf Human/Robotic Tech & Nat'l Vision for Space Explor.; 4th Symp Space Coloniz.; 3rd Symp on New Frontiers & Future Concepts ; 2006 ; Albuquerque, New Mexico (USA)


    Published in:

    AIP Conference Proceedings ; 813 , 1 ; 858-869


    Publication date :

    2006-01-20


    Size :

    12 pages





    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English



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    LANTR Engine System Integration

    Bulman, Melvin / Borowski, S. | AIAA | 2004



    Numerical Study of Chemically Reacting Flow in Nozzles

    T. J. Vanoverbeke / J. Shuen | NTIS | 1989


    Simulated LOX-Augmented Nuclear Thermal Rocket (LANTR) Testing

    Bulman, M. J. / Neill, T. M. / American Institute of Aeronautics and Astronautics et al. | British Library Conference Proceedings | 2000