Control for motors such as are employed in ballistic missiles and space vehicles proposed and three systems presented; fundamental equations of burning rate and mass rate of flow from which control system will be derived; design offers increase in specific impulse at cold temperature, decrease in specific impulse at hot temperature, and increase in specific impulse with decreasing atmospheric pressure (increasing altitude). (See also SAE -- Paper n 59T for meeting Mar 31-Apr 3 1959 23 p)


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    Titel :

    Thrust magnitude control of solid-propellant rocket motors by mechanical means


    Weitere Titelangaben:

    SAE -- J


    Beteiligte:
    Gates, J.S. (Autor:in) / Pinto, S.L. (Autor:in)


    Erscheinungsdatum :

    1959


    Format / Umfang :

    4 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch




    Thrust magnitude control of solid-propellant rocket motors by mechanical means

    Gates, J.S. / Pinto, S.L. | Engineering Index Backfile | 1959


    THRUST MAGNITUDE CONTROL OF SOLID-PROPELLANT ROCKET MOTORS BY MECHANICAL MEANS

    GATES, J. S. / PINTO, S. L. | SAE Technical Papers | 1959




    Prediction of thrust losses occurring in solid-propellant rocket motors

    DAINES, W. / MAYBERRY, J. / LUND, R.K. et al. | AIAA | 1974