NDLI: Fatigue of notched fiber composite laminates. part 1: analytical model

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Fatigue of notched fiber composite laminates. part 1: analytical model

Content Provider	NASA Technical Reports Server (NTRS)
Author	Huang, S. N. Kulkarni, S. V. Rosen, B. W. McLaughlin Jr., P. V.
Copyright Year	1975
Description	A description is given of a semi-empirical, deterministic analysis for prediction and correlation of fatigue crack growth, residual strength, and fatigue lifetime for fiber composite laminates containing notches (holes). The failure model used for the analysis is based upon composite heterogeneous behavior and experimentally observed failure modes under both static and fatigue loading. The analysis is consistent with the wearout philosophy. Axial cracking and transverse cracking failure modes are treated together in the analysis. Cracking off-axis is handled by making a modification to the axial cracking analysis. The analysis predicts notched laminate failure from unidirectional material fatique properties using constant strain laminate analysis techniques. For multidirectional laminates, it is necessary to know lamina fatique behavior under axial normal stress, transverse normal stress and axial shear stress. Examples of the analysis method are given.
File Size	4580603
Page Count	117
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19760008186
Archival Resource Key	ark:/13960/t9j43j969
Language	English
Publisher Date	1975-03-01
Access Restriction	Open
Subject Keyword	Composite Materials Fatigue Materials Notches Failure Modes Mechanical Properties Laminates Fibers Crack Propagation 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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