Flight Support Testing of the J-2 Rocket Engine in Propulsion Engine Test Cell (J-4) (Tests J4-1901-03 through J4-1901-06)

Abstract

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.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1968
Accession Number
AD0844885

Entities

People

  • N. R. Vetter

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Cells
  • Combustion
  • Combustion Chambers
  • Data Acquisition
  • Engine Components
  • Engines
  • Flow Rate
  • Fuel Injection
  • Fuel Injectors
  • Fuel Systems
  • Fuel Tanks
  • Ignition
  • Measurement
  • Recording Systems
  • Rocket Engines
  • Rockets

Fields of Study

  • Physics

Readers

  • Aviation Science / Aeronautics.
  • Rocket Propulsion.
  • Unmanned Aerial System (UAS) Autonomous Capabilities and Mission Reconnaissance.