A 25 lb sub f hydrogen/oxygen thruster has been developed and proven as a viable candidate to meet the needs of the Space Station Program. Likewise, a 50 lb sub f hydrogen/oxygen thrust chamber has been developed and has demonstrated reliable, long-life expectancy at anticipated Space Station operating conditions. Both these thrust chambers were based on design criteria developed in previous thruster programs. Extensive thermal analysis and models were used to design the thrusters to achieve total impulse goals of 2 million lb sub f sec. Test data from each thruster are compared to the analytical predictions for the performance and heat transfer characteristics. Also, the results of thrust chamber life verification tests are presented.


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    Title :

    Proven, long-life hydrogen/oxygen thrust chambers for space station propulsion


    Contributors:


    Publication date :

    1986-08-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English






    Theoretical performance of hydrogen-oxygen rocket thrust chambers

    Sievers, Gilbert K. / Tomazic, William A. / Kinney, George R. | TIBKAT | 1961


    Theoretical performance of hydrogen oxygen rocket thrust chambers

    Sievers, Gilbert K. ;Tomazic, William A. ;Kinney, George R. | SLUB | 1962