NDLI: Characteristics of thermally-induced transverse cracks in graphite epoxy composite laminates

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Characteristics of thermally-induced transverse cracks in graphite epoxy composite laminates

Content Provider	NASA Technical Reports Server (NTRS)
Author	Adams, D. S. Herakovich, C. T. Bowles, D. E.
Copyright Year	1983
Description	The characteristics of thermally induced transverse cracks in T300/5208 graphite-epoxy cross-ply and quasi-isotropic laminates were investigated both experimentally and analytically. The formation of transverse cracks and the subsequent crack spacing present during cool down to -250 F (116K) and thermal cycling between 250 and -250 F (116 and 394K) was investigated. The state of stress in the vicinity of a transverse crack and the influence of transverse cracking on the laminate coefficient of thermal expansion (CTE) was predicted using a generalized plane strain finite element analysis and a modified shear lag analysis. A majority of the cross-ply laminates experienced transverse cracking during the initial cool down to -250 F whereas the quasi-isotropic laminates remained uncracked. The in situ transverse strength of the 90 degree layers was more than 1.9 times greater than the transverse strength of the unidirectional 90 degree material for all laminates investigated.
File Size	36731844
Page Count	135
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19830027838
Archival Resource Key	ark:/13960/t9g49j31v
Language	English
Publisher Date	1983-06-01
Access Restriction	Open
Subject Keyword	Composite Materials Finite Element Method Thermal Expansion Damage Assessment Cryogenic Cooling Failure Modes Graphite-epoxy Composites Stress Corrosion Cracking Prediction Analysis Techniques Crack Initiation Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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