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.
Assurance of service life of MIRA 150a variable thrust rocket engine
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 3 , n 7
1966
5 pages
Article (Journal)
English
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