ADVANCED COMPOSITE CARBIDE NOZZLES

Abstract

The purpose of this program was to develop two thermal-shock- resistant composite carbide systems that could be reliably used with high-flame temperature solid rocket propellants. The selected systems were: (1) a microcomposite consisting of a tantalum/hafnium monocarbide and tantalum/hafnium alloy, and (2) a tantalum-carbide coated, tantalum carbide/graphite hypereutectic. Fabrication procedures were developed, and ambient and elevated temperature properties were characterized for both the microcomposite and TaC/C hypereutectic systems. The composites were evaluated for thermal shock and chemical corrosion resistance in a hyperthermal environmental simulator using subscale inserts. Scale-up of the fusion casting of the TaC/C hypereutectic composite to produce 4.2-in.-dia by 3.0-in.-long billets was demonstrated. Two solid propellant motor firings using 6500F propellant were conducted on nozzles containing TaC/C hypereutectic throat inserts.

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1968
Accession Number
AD0841194

Entities

People

  • L. M. Swope
  • R. P. Radtke

Organizations

  • Aerojet Rocketdyne Holdings

Tags

Communities of Interest

  • Advanced Electronics
  • Weapons Technologies

DTIC Thesaurus Topics

  • Chemistry
  • Composite Materials
  • Corrosion Resistance
  • Fabrication
  • Fungi
  • Material Degradation Processes
  • Materials
  • Materials Laboratories
  • Materials Processing
  • Materials Science
  • Materials Testing
  • Measurement
  • Mechanical Working
  • Mechanics
  • Rocket Engines
  • Solid Propellants
  • Stress Strain Relations

Fields of Study

  • Materials science

Readers

  • Powder metallurgy of Titanium alloys.
  • Rocket Propulsion.
  • Surface Engineering/Surface Coating Technology.