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)


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

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


    Additional title:

    SAE -- J


    Contributors:
    Gates, J.S. (author) / Pinto, S.L. (author)


    Publication date :

    1959


    Size :

    4 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




    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