DEVELOPMENT OF REFRACTORY COMPOSITE MATERIALS SYSTEMS FOR SOLID PROPELLANT ROCKET MOTORS.

Abstract

Difficulties encountered in deposition of metals from metal halide vapor dissociation were primarily caused by the vapor transport system and the difficulty in attaining a leak proof system. Efforts to circumvent and eliminate these difficulties showed extremely promising results. Depositions of Ta showed conclusively that the method is applicable for obtaining fine grained adherent coatings of TaC. The most successful carbide formations by direct union were those of Ta, Mo and V. Excellent coatings of TaC were obtained when thin Mo coatings were used as an intermediate layer. Hard, adherent, Mo2C coatings were produced at all temperatures above 3400 F. Coatings of VC, identified by X-ray diffraction, were produced at a temperature of 3400 F. The compounding of chemically bonded THO2 and Mo wire-chemically bonded ZrO2 composites was shown to be feasible. (Author)

Document Details

Document Type
Technical Report
Publication Date
Jul 20, 1961
Accession Number
AD0269975

Entities

People

  • H. Leggett
  • R. J. Urode

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Absorbers (Materials)
  • Advanced Materials
  • Composite Materials
  • Diffraction
  • Dissociation
  • Energetic Materials
  • Engineered Materials
  • Materials
  • Propellants
  • Rocket Engines
  • Rockets
  • Solid Propellants
  • X Rays
  • X-Ray Diffraction

Readers

  • Educational Psychology
  • Materials Science and Engineering.
  • Surface Engineering/Surface Coating Technology.