Combined High Temperature Aerothermal-Structural Physical Property Testing of Ceramic Matrix Composites

Abstract

The objective was to integrate a mechanical test apparatus into a wind tunnel flow field capable of generating controlled multi-directional stress/strain states in flat coupons exposed to appropriate chemical, thermal, and aerodynamic shear flow environments. Displacement control enables imposition of stress/strain fields (in the flat coupons) similar to those expected in complex flight component geometries. Control and measurement of these variables and the material response in a controlled environment enables assessment of material performance for hypersonic missile and re-entry vehicle flight trajectories. Requirements for the test apparatus were developed and the apparatus was designed. Unfortunately, closure of the proposed wind tunnel facility led to increased costs and imposed a major schedule slip. The program's contract was not extended and the test apparatus was not assembled.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 2008
Accession Number
ADA481825

Entities

People

  • David G. Drewry
  • Don E. King

Organizations

  • Johns Hopkins University

Tags

Communities of Interest

  • Air Platforms
  • Sensors
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Ceramic Matrix Composites
  • Composite Materials
  • Contracts
  • Flow
  • High Temperature
  • Laminates
  • Materials
  • Measurement
  • Mechanical Properties
  • Military Research
  • Physical Properties
  • Refractive Index
  • Shock Tubes
  • Silicon Carbide
  • Test And Evaluation
  • Wind Tunnels

Readers

  • Fluid Mechanics and Fluid Dynamics.
  • Materials Science
  • Structural Health Monitoring of Composite Structures.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow