Twenty-four firings and two fuel lead tests of the Rocketdyne J-2 rocket engine were conducted. This testing was in support of the J-2 engine application to the S-II stage of the Saturn V vehicle. The firings were accomplished at pressure altitudes ranging from 55,000 to 116,000 ft at engine start. The primary objective of these firings was to investigate fuel pump operation under conditions of lower than minimum engine model specification fuel pump net positive suction head and maximum thrust chamber fuel flow resistance utilizing an S-II stage center engine configuration fuel low pressure duct designed to simulate the fluid dynamic characteristics experienced during flight. Engine components were thermally conditioned to temperatures as expected during flight. Engine operation appeared to be satisfactory. The total accumulated firing duration for the six test periods was 190 sec. The total firing duration of this engine at AEDC through test period J4-1801-33 is 940 sec, resulting from 79 engine firings.
Altitude Developmental Testing of the J-2 Rocket Engine in Propulsion Engine Test Cell (J-4) (Tests J4-1801-28 Through J4-1801-33)
1968
306 pages
Report
Keine Angabe
Englisch
Rocket Engines & Motors , Liquid propellant rocket engines , Captive tests , High altitude , Booster rockets , Altitude chambers , Launch vehicles , Fuel pumps , Propellant control , Barometric pressure , Manned spacecraft , Pressure , Thrust , Temperature , Apollo , J-2 engines , Saturn launch vehicles , Saturn 5 launch vehicles , S-2 stages