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 microcomposite of monocarbide (tantalum and hafnium) and a tantalum-carbide-coated, tantalum carbide/graphite hypereutectic. During this reporting period, the characterization of ambient and elevated temperature properties has been completed on both the microcomposite and TaC-C hypereutectic composite systems. Thermal shock resistance and chemical corrosion evaluation tests have been completed on both composite systems. Testing was conducted in a hyperthermal environmental simulator using subscale inserts. The fusion casting of 4.2-in.-dia TaC-C hypereutectic billets are presently in progress for fabricating full-scale nozzle inserts. (Author)

Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1968
Accession Number
AD0831198

Entities

People

  • L. M. Swope
  • R. P. Radtke

Organizations

  • Aerojet Rocketdyne Holdings

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Carbides
  • Composite Materials
  • Graphitic Materials
  • Material Degradation Processes
  • Materials
  • Propellants
  • Resistance
  • Rocket Propellants
  • Shock
  • Shock Resistance
  • Solid Rocket Propellants
  • Tantalum
  • Tantalum Carbides
  • Thermal Shock

Readers

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