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An impartial review of the rise and progress of the by Charles Pettit

By Charles Pettit

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The purpose of the hold w a s to simulate KSC prelaunch groundhold conditions. A certain degree of GHe saturation in the propellants would be expected during the hold. In one test the module was loaded and the duty cycle conducted the day of the test to minimize the GHe saturation to determine the effect, if any, of saturated propellants on the Pc decay phenomenon. The test data revealed a significant decay in engine Pc with increase in propellant and engine temperature. However, for the initial 12 000 seconds of the tests, there was little variation in the nominal Pc operating levels.

From the low of 81 psia the Pc began to increase again and stabilize at 94 psia after 4 t e s t s in a 14 day period. A 10-second steady state run was then conducted and the Pc returned t o the nominal value of 99 psia after I. 5 seconds burn time. 32 MAROTTA MODEL MV 563 K VALVE - 3/8 IN. NOTE: OXIDIZER SYSTEM SHOWN FOR ENGINE SETUP. FUEL SYSTEM IDENTICAL. 150 LB THRUST TRW ENGINE TRW INJECTOR +I 3 , TO FACILITY BLEED LINE GHeSUPPLY I 10 MICRON NOMINAL FILTER VENT VALVE I - 1/2 IN. I 26 GALLON RUN TANK 1/2 IN.

FACILITY SCHEMATIC FOR TRW ENGINE "SEA LEVEL" TESTS AND INJECTOR FLOW TESTS TO SCRUBBER TRW Injector Flow Testing The particulate matter discovered in the oxidizer injector feed tubes in engine 585 prompted a series of injector flow tests. The injector was removed from a TRW engine previously fired at MSFC in APS module performance testing, and special connectors were fabricated to mate the injector oxidizer inlet fitting to the facility oxidizer supply line. The engine valves were replaced by a single facility solenoid valve to eliminate the engine valves variable.

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