Test and Evaluation of a Passively Cooled Thrust Chamber for Fluorinated Propellants

Abstract

A 3,000-pound thrust composite graphite thrust chamber was made by coating a Carbitex shell with pyrolytic graphite. Stress analysis was made to assist in the design of the optimum combination of pyrolytic graphite and Carbitex. The thrust chamber was test fired with ClF3/BAlO14 at a chamber pressure of 300 psia. Total firing duration was 300 seconds, including one single firing of 150 seconds and multiple hot starts. The overall performance of the thrust chamber was excellent. This composite graphite structure appears capable of providing thrust chambers for even more severe chamber pressures and firing durations with negligible erosion.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1969
Accession Number
AD0506114

Entities

People

  • John G. Campbell

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Adapters
  • Air Force
  • Assembly
  • Combustion
  • Combustion Chambers
  • Composite Materials
  • Elastic Properties
  • Fabrication
  • Government Procurement
  • Governments
  • Insulation
  • Materials
  • Propellants
  • Rocket Propulsion
  • Stress Analysis
  • Test And Evaluation
  • Thrust Chambers

Fields of Study

  • Physics

Readers

  • Reinforced Composite Materials
  • Rocket Propulsion.