Five firings of the Rocketdyne J-2 rocket engine were conducted in Test Cell J-4 of the Large Rocket Facility. The firings were accomplished during test period J4-1801-23 at pressure altitudes ranging from 105,500 to 113,000 ft at engine start to evaluate the effects of predicted Saturn S-II stage pre-fire conditions on J-2 engine start transients. Engine components were thermally conditioned to simulate the expected S-II interstage/engine thermal environment. Satisfactory engine operation was obtained. Accumulated firing duration was 56.3 sec.
Altitude Developmental Testing of the J-2 Rocket Engine in Propulsion Engine Test Cell (J-4) (Test J4-1801-23)
1968
111 pages
Report
Keine Angabe
Englisch
Rocket Engines & Motors , Liquid propellant rocket engines , Captive tests , High altitude , Fuel pumps , Pressure , Simulation , Engine starters , Liquid rocket propellants , Hydrogen , Oxygen , Thrust , Combustion chambers , Nozzle throats , Launch vehicles , Fuel injectors , Turbopumps , Gas generating systems , Propellant control , Pneumatic devices , Helium , Bypass valves , Electrical equipment , Control systems , Sequence switches , Altitude chambers , Checkout procedures , J-2 engines , Restart ignition , Restartable rocket engines , Saturn launch vehicles , Saturn 5 launch vehicles , S-1b stages , S-2 stages , S-4b stages