SST Technology Follow-on Program - Phase 2: Integrally Stiffened Panel Biaxial Compression Tests

Abstract

This report presents the results of a structural test program to verify the structural integrity of biaxial compression panels designed for use on the wing of the U.S. SST prototype airplane. The 28 test specimens are flat, integrally stiffened titanium panels. Four basic cross-section configurations were tested. Tests included uniaxial and biaxial compression with thermal effects from room temperature to 450 deg F.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1973
Accession Number
AD0913422

Entities

People

  • E. F. Nichols
  • J. E. Mooney

Organizations

  • Boeing Commercial Airplanes

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Actuators
  • Aircraft Industry
  • Aircrafts
  • Airframes
  • Airplanes
  • Assembly
  • Commercial Aircraft
  • Gages
  • Governments
  • Instrumentation
  • Manufacturing
  • Molecular Dynamics
  • Photographs
  • Steady State
  • Strain Gages
  • Supersonic Transport Aircraft
  • Titanium

Fields of Study

  • Physics

Readers

  • Mechanical Engineering/Mechanics of Materials.
  • Software Engineering
  • Structural Dynamics.