The development of low cost, highly reusable rocket thrusters is essential for fulfilling NASA's commitment of providing economical space access. Results obtained from a recent sub-scale, high performance rocket thruster development and test program applied to a Rocket Based Combined Cycle engine have demonstrated rocket versatility and durability in over 678 tests at chamber pressures between 190 and 1930 psia using gaseous oxygen and gaseous hydrogen.


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    Title :

    Durability Demonstration of Small High Performance Rocket Thrusters for RLV Applications


    Contributors:

    Conference:

    Joint Propulsion ; 1999 ; Los Angeles, CA, United States


    Publication date :

    1999-06-07


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English





    Durability Demonstration of Small High Performance Rocket Thrusters for RLV Applications

    Neill, T. M. / Gladstone, J. D. / American Institute of Aeronautics and Astronautics| Society of Automotive Engineers| American Society of Mechanical Engineers| American Society for Engineering Education | British Library Conference Proceedings | 1999


    Micro-Rocket Impulsive Thrusters

    L. H. Caveny / M. Summerfield | NTIS | 1971



    Development and Testing of New, HAN-Based Monopropellants in Small Rocket Thrusters

    Meinhardt, D. / Brewster, G. / Christofferson, S. et al. | British Library Conference Proceedings | 1998