Propellant Fires in a Simulated Shipboard Compartments: Project HULVUL Phase III

Abstract

A multi-phase investigation was conducted to quantify the thermal insult produced by the burning of unspent solid rocket propellant in a missile hit scenario. The objectives of this multi-phase investigation were to; identify the thermal conditions produced in the compartment during the missile fuel burning stage, identify the likelihood for ignition of Class A materials in the space and bound the transition time for the ensuring compartment fire. This report summarizes the results of the third and final phase of this investigation.

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Document Details

Document Type
Technical Report
Publication Date
Aug 20, 1999
Accession Number
ADA367293

Entities

People

  • Frederic W. Williams
  • G. G. Back
  • J. L. Scheffey
  • R. L. Darwin

Organizations

  • United States Naval Research Laboratory

Tags

DTIC Thesaurus Topics

  • Burning Rate
  • Chemistry
  • Combustion
  • Data Acquisition
  • Equations
  • Fires
  • Flow Rate
  • Ignition
  • Load Cells
  • Materials
  • Materials Laboratories
  • Materials Science
  • Measurement
  • Propellants
  • Rocket Propellants
  • Solid Rocket Propellants
  • Temperature Gradients

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Computational Modeling and Simulation
  • Software Engineering

Technology Areas

  • Space
  • Space - Hall-Effect Thruster