Test and Evaluation of Refractory Nozzle Materials for Application to the High Altitude Supersonic Target Missile.

Abstract

Six high temperature nozzle throat materials were tested to evaluate their performance in a highly oxidizing rocket exhaust environment. Four nozzles were designed and fabricated with a throat inside diameter of approximately 1.47 inches. The materials tested in this configuration were pyrolytic graphite washers (edge-oriented), co-deposited silicon carbide/pyrolytic graphite (SiC/PG) coated on an ATJ graphite substrate, JTA composite graphitic material, and co-deposited Hafnium carbide/zirconium carbide/pyrolytic graphite (HfC/PG and ZrC/PG) washers. The best performance was demonstrated by the SiC/PG with an erosion rate of about 2 mils per second over a 35-second duration test. The remaining two nozzle materials, zirconium diboride (ZrB2) and pyrolytic graphite coated carbitex, were tested in a 2.55-inch nominal diameter throat nozzle. (Modified author abstract)

Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1973
Accession Number
AD0762533

Entities

People

  • Phil S. Martin

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Carbides
  • Ceramic Materials
  • Composite Materials
  • Graphitic Materials
  • High Altitude
  • High Temperature
  • Materials
  • Rocket Exhaust
  • Silicon Carbide
  • Test And Evaluation

Readers

  • Combustion science or combustion engineering.
  • Fluid Dynamics.
  • Powder metallurgy of Titanium alloys.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow