A Space Shuttle liquid oxygen/hydrogen reaction control system design analysis has been performed. The system concept considered eliminates propellant conditioning equipment and delivers the propellants to the engines in a liquid rather than a gaseous state. This paper provides system design analyses results and compares various means of implementing the concept on the basis of weight, technology requirements, and operational considerations. Additionally, weight comparisons are made between cryogenic oxygen/hydrogen system requirements. These comparisons show that the liquid oxygen/hydrogen system concept could effect marked weight reductions in the Space Shuttle orbiter total impulse range.


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    Title :

    Cryogenic liquid O2/H2 reaction control systems for Space Shuttle.


    Contributors:
    Kelly, P. J. (author) / Mckee, H. B. (author) / Patten, T. C. (author)

    Conference:

    Joint Propulsion Specialist Conference ; 1972 ; New Orleans, LA, US


    Publication date :

    1972-11-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :