ADVANCED COMPOSITE CARBIDE NOZZLES.

Abstract

The purpose of this program is to develop two thermal-shock-resistant composite carbide systems that can be reliably used with high-flame-temperature solid rocket propellants. These are a micro-composite of monocarbide (tantalum, hafnium) and a tantalum-carbide-coated, tantalum carbide/graphite hypereutectic. During the report period, ambient-temperature physical-property screening tests have been completed on six candidate micro-composite compositions. Elevated temperature mechanical and thermal property testing has been partly completed on one of the two micro-composite compositions selected as a candidate rocket nozzle material. Scale-up has been initiated in a newly developed hot-press and fusion casting furnace facility for fabricating the tantalum carbide/graphite hypereutectic composites. (Author)

Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1967
Accession Number
AD0817208

Entities

People

  • L. M. Swope
  • P. N. Dangel
  • R. P. Radtke

Organizations

  • Aerojet Rocketdyne Holdings

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Carbides
  • Composite Materials
  • Gas Turbine Nozzles
  • Graphitic Materials
  • Materials
  • Nozzles
  • Physical Properties
  • Propellants
  • Rocket Nozzles
  • Rocket Propellants
  • Solid Rocket Propellants
  • Tantalum
  • Tantalum Carbides
  • Thermal Properties
  • Thermal Shock

Fields of Study

  • Materials science

Readers

  • Rocket Propulsion.
  • Software Engineering
  • Thin Film Deposition Science.