Facesheet debonding criteria for composite sandwich panels under in-plane compression

W. C. Kim, C. K.H. Dharan

Research output: Contribution to journalArticle

31 Citations (Scopus)

Abstract

A method for determining the critical debond size between the facesheet and the core in composite sandwich panels under in-plane compression is described. The approach uses fracture mechanics together with a buckling criterion for a debonded faceskin. The technique yields predictions for the critical in-plane compressive load for debond propagation as a function of core-to-faceskin debond size, faceskin thickness, lay-up, composite material properties, and honeycomb properties and geometry. A computer program, developed in this work, calculates the critical buckling load and facesheet deformed shape by solving an eigenvalue problem. The output predicts, for several cases, critical initial debond lengths comparable to those that have been observed on tests on sandwich panels.

Original languageEnglish
Pages (from-to)643-652
Number of pages10
JournalEngineering Fracture Mechanics
Volume42
Issue number4
DOIs
Publication statusPublished - 1992 Jul

Fingerprint

Debonding
Buckling
Compaction
Composite materials
Fracture mechanics
Computer program listings
Materials properties
Geometry

All Science Journal Classification (ASJC) codes

  • Materials Science(all)
  • Mechanics of Materials
  • Mechanical Engineering

Cite this

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Facesheet debonding criteria for composite sandwich panels under in-plane compression. / Kim, W. C.; Dharan, C. K.H.

In: Engineering Fracture Mechanics, Vol. 42, No. 4, 07.1992, p. 643-652.

Research output: Contribution to journalArticle

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