Downloads & Free Reading Options - Results

Eleven test periods involving a total of 14 J-2 rocket engine starts were accomplished in Propulsion Engine Test Cell (J-4) to verify the engine altitude ignition characteristics and performance in support of the Saturn IB and Saturn V flights. The test article consisted of a flight configuration J-2 rocket engine and a battleship S-IVB stage. Engine ignition characteristics were different from those predicted for altitude testing and provided an important insight into the J-2 engine transient operation for the Saturn IB and Saturn V flights. Transient gas generator outlet temperatures observed were consistently higher than engine acceptance test values. One test resulted in an engine safety cutoff because of an excessive transient gas generator outlet temperature. Combustion instability during engine ignition was observed for time durations ranging from 3 to 132 msec for ten of the firings and was similar to the instability recorded during the Saturn IB AS-201 through -203 flights. Excessive engine vibration resulted in an engine safety cutoff on one test. Engine side forces measured at altitude conditions were significantly less than those recorded during previous J-2 engine tests. Engine operation time accumulated during these tests was 145.8 sec.

No Abstract Available