High Chamber Pressure Blast Tube and Nozzle Material Evaluation. Volume 1

Abstract

The objectives were to evaluate the effects of propellant corrosivity and blast tube contraction ratio on candidate nozzle materials in high chamber pressure rocket motor environments (3,000 and 3,500 psia). A total of 16 lightweight aft closures and nozzles were designed, fabricated, and test fired. High velocity blast tubes with contraction ratios of 2.0 and 1.3, respectively, were used on all nozzles. The effects of propellant flame temperature and corrosivity were evaluated by testing with both 18% and 5% aluminized, 88% solids loaded CTPB propellants. The effects of both cylindrical and keyhole port grain configurations also were evaluated. Conventional state-of-the-art phenolic, elastomeric, graphite materials were used.

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Document Details

Document Type
Technical Report
Publication Date
Jun 17, 1974
Accession Number
AD0780531

Entities

People

  • Wendell A. Stephen

Tags

Communities of Interest

  • Human Systems
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Carbon Carbon Composites
  • Chemical Synthesis
  • Chemistry
  • Composite Materials
  • Fabrication
  • Fluid Dynamics
  • Graphitic Materials
  • Heat Transfer
  • High Pressure
  • Mach Number
  • Materials Laboratories
  • Materials Processing
  • Materials Science
  • Propellants
  • Rocket Engines
  • Test And Evaluation

Fields of Study

  • Physics

Readers

  • Metallurgy
  • Rocket Propulsion.