Flight Support Testing of the J-2 Rocket Engine in Propulsion Engine Test Cell (J-4) (Tests J4-1901-03 through J4-1901-06)
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
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This testing was in support of the J-2 engine application to ths S-2 and S-4B stages of the Saturn 5 vehicle. The firings were accomplished at pressure altitudes between 78,000 and 110,000 ft at engine start. The primary objective of these firings was to evaluate engine start transients under various combinations of starting conditions with start tank energy being the major variable. The total accumulated firing duration for these four test periods was 223.2 sec.
- Combustion and Ignition
- Liquid Propellant Rocket Engines
- Ground Support Systems and Facilities for Space Vehicles