EVALUATION OF COLUMBIUM CARBIDE NOZZLES FOR SOLID PROPELLANT ROCKET MOTORS.

Abstract

Two replicate columbium carbide nozzles were designed and fabricated. They were tested at the Rocket Propulsion Laboratory in the 5,000 pound solid-propellant char motor. Although minor difficulties occurred at the attachment fitting because of a subsequent change in test vehicle, the performance of the refractory carbide material from a standpoint of thermal shock resistance was excellent. The erosion performance was also good. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1966
Accession Number
AD0376139

Entities

People

  • Eugene L. Olcott

Organizations

  • ARCO

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Classification
  • Combustion
  • Contracts
  • Fabrication
  • Guided Missiles
  • Heat Transfer
  • Materials
  • Materials Laboratories
  • Propellants
  • Propulsion Systems
  • Resistance
  • Rocket Engines
  • Rocket Propulsion
  • Security
  • Shock Resistance
  • Solid Propellants

Fields of Study

  • Physics

Readers

  • Powder metallurgy of Titanium alloys.
  • Psychological Intervention/Treatment for Stress, Anxiety, PTSD, and Related Emotional and Cognitive Health Symptoms.
  • Rocket Propulsion.