Flame Temperatures and Internal Pressures of Pyrotechnic Igniters Used in Liquid Propellant Gun Firings

Abstract

Flame temperatures and internal pressures of various pyrotechnic igniters used in past NOS-365 bulk loaded liquid propellant gun (BLPG) firings were measured. The flame temperatures were measured using a modified line reversal method. The igniters were a radial venting type of primer and were selected for further study since these igniters, using the proper igniter element and booster charge, have yielded pressure time reproducibility firings superior to many of the earlier gun firings with NOS-365. The igniters consisted of either a T9E6 electric ignition element or an electric match element and a booster charge. The latter offered marginal ignition when fired in a BLPG. The former igniters provided adequate ignition and consisted of, in one case, a large M30 single perforated grain containing several strands of eimite and, in the other case, a Unique flake propellant. Average maximum measured flame temperatures were, respectively, 3060 K and 3280 K. The M30 plus eimite igniter gave a broader temperature curve than the unique propellant. The pressure time curves revealed similar general characteristics as the temperature time curves, although more structure was evident with the temperature curves.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1982
Accession Number
ADA114042

Entities

People

  • Douglas Taylor
  • Guenter Klingenberg
  • Irvin C. Stobie
  • John D. Knapton

Organizations

  • Ballistic Research Laboratory

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Cameras
  • Chemistry
  • Combustion
  • Electric Igniters
  • Electric Ignition
  • Igniters
  • Ignition
  • Ignition Systems
  • Internal Pressure
  • Jet Propulsion
  • Liquid Propellant Guns
  • Liquid Propellants
  • Measurement
  • Ordnance Laboratories
  • Photomultiplier Tubes
  • Physics
  • Physics Laboratories

Fields of Study

  • Physics

Readers

  • Rocket Propulsion.