IMPROVEMENT OF THE USEFULNESS OF PYROLYTIC GRAPHITE IN ROCKET MOTOR APPLICATIONS

Abstract

Research was continued in 3 phases consisting of deposition process studies, mechanical design analysis, and preparation and motor test firing of pyrolytic graphite coated nozzle inserts. The deposition process studies showed that pyrolytic graphite coatings can be prepared in the temperature range from 1300 to 1700 C; coatings prepared below 1500 C are very coarse grained. Calculation of the residual thermal stresses formed in the coated bodies during the deposition process was continued. Motor firing tests in a 6500 F propellant showed that the coating was lost in 9 sec from the first test piece fired as a result of excessive motor pressure. A second test piece displayed a very good erosion rate of 0.48 mil/sec in a firing at normal high pressure. This erosion rate is superior to any other graphitic material tested to date.

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Document Details

Document Type
Technical Report
Publication Date
Dec 15, 1961
Accession Number
AD0268652

Entities

People

  • E. F. Ford
  • E. L. Olcott
  • J. D. Batchelor
  • R. K. White
  • S. W. Mccormick

Organizations

  • ARCO

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Composite Materials
  • Fabrication
  • Gas Flow
  • Geometry
  • Graphitic Materials
  • High Pressure
  • Low Temperature
  • Materials
  • Materials Processing
  • Microstructure
  • Nozzles
  • Propellants
  • Rocket Engines
  • Rockets
  • Stress Strain Relations
  • Stresses
  • Thermal Stresses

Readers

  • Rocket Propulsion.
  • Surface Engineering/Surface Coating Technology.