Flight Support Testing of the J-2 Rocket Engine in Propulsion Engine Test Cell (J-4) (Tests J4-1901-09 through J4-1901-11)
Abstract
The firings were accomplished at pressure altitudes ranging from 81, 000 to 107,000 ft at engine start. Basic test objectives were to evaluate the effect on the engine start transient of (1) different configuration gas generator oxidizer supply lines, (2) gaseous helium as a start tank pressurant, (3) start tank pressures ranging from 600 to 1000 psia, and (4) a simulated gas generator fuel poppet leak. Engine components were thermally conditioned to temperatures representative of S-IVB engine/interstage environment for a first burn, 80-min restart, or 6-hr restart. The total accumulated firing duration for the three test periods was 181.6 sec.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1969
- Accession Number
- AD0847382
Entities
People
- H. J. Counts Jr.
Organizations
- Arnold Engineering Development Complex