A procedure for automatically designing a liquid propellant rocket engine combustion chamber in an optimal fashion is outlined. The procedure is contained in a digital computer code, AUTOCOM. The code is applied to an existing engine, and design modifications are generated which provide a substantial potential payload improvement over the existing design. Computer time requirements for this payload improvement were small, approximately four minutes in the CDC 6600 computer.


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    Title :

    Optimizing a liquid propellant rocket engine with an automated combustor design code (AUTOCOM)


    Contributors:
    Hague, D. S. (author) / Reichel, R. H. (author) / Jones, R. T. (author) / Glatt, C. R. (author)

    Publication date :

    1972-12-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English