STRENGTH AND STRESS-STRAIN PROPERTIES OF RAPIDLY HEATED LAMINATED ABLATIVE MATERIALS

Abstract

It is shown that the mechanical properties of rocket nozzle liners and reentry vehicle ablation materials can be determined by tests in which a high temperature plasma arc is used as a heat source. The arc flow is used to heat slender specimens, and a pneumatically actuated loading frame is used to apply stress. This method of testing provides heating and loading in time periods typical of the rapid heating during rocket firing or reentry, on the order of 10 sec. Earlier investigations of similar ablative materials have used specimens heated and charred (degraded) slowly prior to the application of load. Strength and stress-strain properties in the warp direction were determined for carbon, graphite, and silica phenolic materials. The method appears promising for the determination of properties in various loading-laminate orientations and during thermal expansion, and for studies of heating and strain rate effects on strength at elevated temperatures.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1967
Accession Number
AD0660534

Entities

People

  • A. Ching
  • W. E. Welsh Jr.

Organizations

  • The Aerospace Corporation

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Ablation
  • Ablative Materials
  • Compressive Strength
  • Failure Mode And Effect Analysis
  • Graphitic Materials
  • Laminates
  • Materials
  • Materials Laboratories
  • Mechanical Properties
  • Mechanics
  • Orientation (Direction)
  • Shear Strength
  • Strain Rate
  • Stress Strain Relations
  • Stresses
  • Tensile Strength
  • Tensile Stress

Readers

  • Combustion and Flow Dynamics.
  • Reinforced Composite Materials