Eleven firings of the Rocketdyne J-2 rocket engine were conducted in Test Cell J-4 of the Large Rocket Facility. The firings were accomplished at pressure altitudes ranging from 85,000 to 109,000 ft at engine start to investigate (1) engine start transients for both S-IVB first burn and (2) 80-min orbital restart with the engine in a 230,000-lbf-thrust configuration. Engine components were thermally conditioned to temperatures representative of an S-IVB first burn or 80-min orbital restart. The total accumulated firing duration for the four test periods was 188.43 sec. Engine operation appeared to be satisfactory.
Altitude Developmental Testing of the J-2 Rocket Engine in Propulsion Engine Test Cell (J-4) (Tests J4-1801-24 Through 27)
1968
146 pages
Report
No indication
English
Rocket Engines & Motors , Liquid propellant rocket engines , Captive tests , Pressure , High altitude , Simulation , Engine starters , Thrust , Liquid rocket propellants , Oxygen , Hydrogen , Combustion chambers , Nozzle throats , Launch vehicles , Fuel injectors , Turbopumps , Centrifugal pumps , Gas generating systems , Pneumatic valves , Propellant control , Helium , Pneumatic devices , Diffusers , Altitude chambers , Data processing , Digital systems , J-2 engines , Restartable rocket engines , Restart ignition , Saturn launch vehicles , Saturn 4b stages , Saturn 5 launch vehicles