Mission requirements of engine, designed for use on vernier engine propulsion subsystem of Surveyor spacecraft, dictate throttleability, multistart capability, and durability specifications; streak test, developed for determining effect of injector combustion pattern on thrust-chamber durability, consists of employing substitute erodable nozzle throat in test chamber to register injector signature during prolonged static firing; quantitative accept/reject criteria employed in MIRA 150A acceptance streak test are defined and correlation of acceptance test results with thrust-chamber service life is shown.


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    Title :

    Assurance of service life of MIRA 150a variable thrust rocket engine


    Additional title:

    J Spacecraft Rockets


    Contributors:
    Shieber, H. (author) / Rupert, R.C. (author)

    Published in:

    Publication date :

    1966


    Size :

    5 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :