Material Performance of Carbon Phenolic Ablators and Pyrolytic Graphite Coatings in Nozzles Subjected to Multiple Pulse Duty Cycles

Abstract

Measurements and analysis of the thermal and ablative response of five multiple pulse duty cycle rocket nozzles were performed. Nozzles were fired on a solid propellant simulator with a test stream composition, designated ANB-3066, which contained 16 percent aluminum. Nominal chamber pressure for each of the various firing pulses was 750 psia. Material temperature histories were recorded at several locations in each nozzle. Post-test measurements of surface recession, char penetration, and density versus depth, as well as thermocouple data are used for comparison with one and two-dimensional heat conduction and material ablation calculations.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1971
Accession Number
AD0738622

Entities

People

  • Andrew J Murphy
  • Duane L. Baker
  • Mitchell R. Wool

Tags

Communities of Interest

  • Energy and Power Technologies
  • Weapons Technologies

DTIC Thesaurus Topics

  • Ablative Materials
  • Aging (Materials)
  • Air Force
  • Boundary Layer
  • Chemical Reactions
  • Chemistry
  • Composite Materials
  • Crystal Structure
  • Graphitic Materials
  • Heat Transfer
  • Material Degradation Processes
  • Materials Processing
  • Materials Science
  • Rocket Engines
  • Thermal Conductivity
  • Thermodynamics
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Reinforced Composite Materials
  • Rocket Propulsion.