COMBUSTION TERMINATION SYSTEM FOR 120-INCH-DIAMETER SOLID ROCKET MOTOR (TITAN III-C).

Abstract

As a result of these tests, it was established that solid propellant motors cast with PBAN (polybutadiene acrylonitrile) propellant could be extinguished by injecting a liquid into the compustion chamber. The mechanism controlling the extinguishment of PBAN was determined to be heat transfer. For this reson, water, with its high specific heat, proved to be the most effective injectant, and the necessity of contacting all burning surfaces by the injectant was established. Radial slots in the propellant charge downstream of the injector were found to be particularly difficult to contact with injectant and were therefore subject to reignition. For this reason, a reliable system for extinguishing the Titan III-C was not developed.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1966
Accession Number
AD0804269

Entities

People

  • F. B. Nielsen

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Assembly
  • Burning Rate
  • Combustion
  • Combustion Chambers
  • Combustion Products
  • Heat Capacity
  • Heat Transfer
  • Igniters
  • Ignition
  • Materials Laboratories
  • Materials Processing
  • Measurement
  • Rocket Engines
  • Solid Propellants
  • Standards
  • Steady State

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Rocket Propulsion.