Five firings of the Rocketdyne J-2 rocket engine (S/N J-2047) were conducted in Test Cell J-4 of the Large Rocket Facility. These firings were accomplished during test period J4-1801-16 at pressure altitudes of approximately 100,000 ft at engine start to investigate S-II/S-V (1) fuel pump operation during the start transient at lower than minimum model specification inlet pressure, (2) thrust chamber pressure buildup rate with low starting energy, and (3) gas generator and augmented spark igniter temperature transients with warmest and coldest expected thrust chamber temperatures as predicted from the AS-501 countdown demonstration. Engine operation was satisfactory for all firings. The accumulated firing duration was 46.2 sec. (Author)
Altitude Developmental Testing of the J-2 Rocket Engine in Propulsion Engine Test Cell (J-4) (Test J4-1801-16)
1968
107 pages
Report
Keine Angabe
Englisch
Rocket Engines & Motors , Laboratory & Test Facility Design & Operation , Liquid propellant rocket engines , Fuel pumps , Captive tests , Combustion chambers , Turbopumps , Bypass valves , Pneumatic valves , Hydrogen , Helium , Liquid rocket oxidizers , Fuel injectors , Fuel tanks , Fuel systems , Checkout procedures , Spark ignition , Temperature , Pressure , Altitude , Thrust , Performance(Engineering) , Bleed systems , Gas generating systems , Launch vehicles , Liquid rocket propellants , J-2 engines , Liquid oxygen , Saturn 5 launch vehicles , Saturn 1b launch vehicles , S-2 stages