Five firings of the 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 104,000 to 112,000 ft at engine start to evaluate engine starting characteristics at the minimum main oxidizer valve sequence ramp limit and reduced fuel pump net positive suction head. These firings were in support of the S-2 vehicle application for Saturn flights. Engine components were thermally conditioned to predicted values for the S-2 interstage/engine environment. Satisfactory engine operation was obtained. The accumulated firing duration was 56.22 sec.
Altitude Developmental Testing of the J-2 Rocket Engine in Propulsion Engine Test Cell (J-4)(Test J4-1801-20)
1968
127 pages
Report
No indication
English
Rocket Engines & Motors , Space Launch Vehicles & Support Equipment , Combustion & Ignition , Launch vehicles , Liquid propellant rocket engines , Captive tests , Simulation , High altitude , Interior ballistics , Propellant control , Rocket igniters , Ignition , Fuel injection , Fuel pumps , Environmental tests , Altitude chambers , Valves , Performance(Engineering) , Manned spacecraft , Space capsules , Liquid rocket oxidizers , Turbopumps , Thrust , Liquid rocket propellants , Second-stage motors , Third stage engines , J-2 engines , Saturn launch vehicles , Saturn 5 launch vehicles , S-2 stages , Apollo , Saturn 1b launch vehicles , S-4b stages