By Charles Pettit
Read Online or Download 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 PDF
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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
Example text
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. TO 3 FT. DIAMETER ALTITUDE CELL PREVALVE FLOWMETER TO APS MODULE w w FIGURE 13. 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.
Slow chamber pressure decay of ullage engine 3. Chamber p r e s s u r e oscillations 4. Chamber pressure decay 5. 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.
Thus, a need f o r additional thermal isolation of the propellant feed system is needed. The solution, implemented by MDC, is the addition of: ( 1) new radiation shields i n the propellant manifold area inside of the module, ( 2 ) fiberglass covers over the servicing disconnects located externally on the aft end of the module to shield them from direct solar heating, and ( 3 ) new brackets that attach the propellant lines to the primary structure which will serve as thermal insulators to prevent conduction of heat from the structure into the propellant lines.