Altitude Developmental Testing of the J-2S Rocket Engine in Rocket Development Test Cell (J-4) (Tests J4-1001-06, -07, -11, and -15)
Abstract
Eleven firings of the Rocketdyne J-2S rocket engine were conducted. These firings were accomplished at pressure altitudes ranging from 80,000 to 108,000 ft at engine start signal. The major objectives for these tests were to verify stable idle-mode operation, confirm that oxidizer injection temperatures were not excessive during transition from main-stage to post-main-stage idle- mode operation, evaluate main-stage performance, and determine the rate at which thrust chamber temperature increased during pre-main-stage idle mode. A full- face oxidizer flow injector configuration was utilized during this series of tests for the distribution of oxidizer during idle-mode operation. Brief durations (<20 sec) of stable idle-mode operation (chamber pressure oscillations < + or - psi) were achieved. Oxidizer injection temperatures exhibited only insignificant increases (<10F) during transition to post-main-stage idle-mode operation. The maximum rate at which the thrust chamber temperature increased during idle-mode operation with high oxidizer (45-psia) and low fuel (27-psia) pump inlet conditions with 6F/sec. Three firings which simulated orbital restart conditions were prematurely terminated during transition to main stage by the vibration safety cutoff system. Liquid fuel was present at the injector at the dome prime when the excessive vibrations were first recorded.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1970
- Accession Number
- AD0874400
Entities
People
- C. E. Pillow
Organizations
- Arnold Engineering Development Complex