The Effect of Temperature Stresses on the Stability of a Sandwich Wing Panel

Abstract

A study was made of the stability of a sandwich wing panel compressed in one direction in the presence of different temperatures on the upper and lower carrying layers. It is considered that the hypothesis of straight-line normals is valid for the carrying layers. The general relations of the theory of elasticity are used for the core materials; however, it is assumed that the entire compression load is received by the carrying layers and that the core material up to the moment of bulging is free of stresses. The temperature stresses and strains in the core material are not taken into account in view of the small rigidity of the latter.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1961
Accession Number
AD0268053

Entities

People

  • V. P. Karnozhitskiy

Organizations

  • National Air and Space Intelligence Center

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Biharmonic Functions
  • Compression
  • Elastic Properties
  • Equations
  • Foreign Technology
  • Government Procurement
  • Governments
  • Materials
  • Modulus Of Elasticity
  • Poisson Ratio
  • Sandwich Panels
  • Shear Modulus
  • Thickness
  • Translations
  • Two Dimensional

Fields of Study

  • Engineering

Readers

  • Structural Dynamics.