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

By Charles Pettit

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Extra resources for An impartial review of the rise and progress of the controversy between the parties known by the names of the Federalists, & Republicans. : Containing an investigation of the radical cause of division ; and of some of the subordinate or auxiliary causes w

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ENGINE 2 Pc, INJECTOR TEMPERATURE, AND OXIDIZER SUPPLY TEMPERATURE VERSUS TEST TIME I 120 A 1 E Y w iw loo 240 Y, G! 534; JUNE 11, 1968 PHASE IV SATURN V APS MODULE MODULE LOADED 5 DAYS PRIOR TO I I I , ENGlNk 3 INJECTOR WALL TEMPERATURE 160 / 0 A LL 0, w 120 I OXIDIZER INLET TEMPERATURE I PL 2 a t- W n 5 TEMPERATURE I f START SEQUENCE 3 1 BEGIN HEATING I E N k N E 4 FIRED FOR 330 SEC START SEQUENCE 2 I L- 4 MINUTE HOLD TO CHANGE F- TAPE 80 f- 40 0 2000 4000 h 8000 10 000 I 12 000 1 14 000 16 000 CUTOFF 18000 ELAPSED TEST TIME (SEC) h3 W FIGURE 12.

Low chamber pressure. After investigating the anomalies and performing a series of tests to verify the assumed causes of the problems, it was concluded that the high propellant temperature and low chamber p r e s s u r e anomalies warranted remedial action to preclude possible future mission problems. The testing at MSFC verified that the 501 flight APS gradual chamber pressure decay and oscillations, noted in the latter portion of the mission, were a direct result of the high propellant temperature.

However, the nominal Pc values were restored after two or three pulses. It was noted that the engine temperatures "soaked outf' at higher values during these hold periods. The dense portion of the firing cycle was begun at 10 900 seconds, followed by the beginning of heating of the oxidizer control module at 12 000 seconds. P c decay began at this point ( 12 000 seconds) and continued throughout the remainder of the duty cycle. The P c decay is best illustrated in Figures 10, 11, and 12, which contain curves of engine Pc , engine injector wall temperature , oxidizer inlet temperature, and oxidizer control module ( PCM) inlet temperature versus test time f o r a typical test.

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