The firings were accomplished at pressure altitudes ranging from 81, 000 to 107,000 ft at engine start. Basic test objectives were to evaluate the effect on the engine start transient of (1) different configuration gas generator oxidizer supply lines, (2) gaseous helium as a start tank pressurant, (3) start tank pressures ranging from 600 to 1000 psia, and (4) a simulated gas generator fuel poppet leak. Engine components were thermally ...
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