OPERATING CHARACTERISTICS OF THE APOLLO LM DESCENT ENGINE WITH HELIUM INGESTION AND PROPELLANT DEPLETION IN A SIMULATED SPACE ENVIRONMENT
Abstract
An Apollo Lunar Module Descent Engine (LMDE) was tested under a simulated thermal radiation and pressure space environment in Propulsion Engine Test Cell (J-2A) to investigate (1) engine ignition characteristics at 10- percent throttle, while ingesting various trapped volumes of helium (the flight vehicle propellant tank pressurant), and (2) engine operating and shutdown characteristics while injecting various flow rates of helium into the propellant feed lines. Fifteen firings were conducted during two test periods. The first test period consisted of seven firings; four were checkout and baseline performance tests, and three were helium ingestion propellant depletion tests. Eight firings were conducted during the second test period; seven were helium ingestion propellant depletion tests. Helium volumes equivalent to over 9 ft of propellant feed line were ingested during the starts, and helium flow rates equivalent to more than 40 percent of the total volumetric flow of each propellant were injected into the feed lines during engine operation with insignificant engine damage.
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1967
- Accession Number
- AD0822318
Entities
People
- J. A. German
- K. L. Farrow
- T. M. Gernstein
Organizations
- Arnold Engineering Development Complex