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A Method for Calculating Strain Energy Release Rates in Preliminary Design of Composite Skin/Stringer Debonding Under Multi-Axial LoadingThree simple procedures were developed to determine strain energy release rates, G, in composite skin/stringer specimens for various combinations of unaxial and biaxial (in-plane/out-of-plane) loading conditions. These procedures may be used for parametric design studies in such a way that only a few finite element computations will be necessary for a study of many load combinations. The results were compared with mixed mode strain energy release rates calculated directly from nonlinear two-dimensional plane-strain finite element analyses using the virtual crack closure technique. The first procedure involved solving three unknown parameters needed to determine the energy release rates. Good agreement was obtained when the external loads were used in the expression derived. This superposition technique was only applicable if the structure exhibits a linear load/deflection behavior. Consequently, a second technique was derived which was applicable in the case of nonlinear load/deformation behavior. The technique involved calculating six unknown parameters from a set of six simultaneous linear equations with data from six nonlinear analyses to determine the energy release rates. This procedure was not time efficient, and hence, less appealing. A third procedure was developed to calculate mixed mode energy release rates as a function of delamination lengths. This procedure required only one nonlinear finite element analysis of the specimen with a single delamination length to obtain a reference solution for the energy release rates and the scale factors. The delamination was extended in three separate linear models of the local area in the vicinity of the delamination subjected to unit loads to obtain the distribution of G with delamination lengths. This set of sub-problems was Although additional modeling effort is required to create the sub- models, this local technique is efficient for parametric studies.
Document ID
19990078564
Acquisition Source
Langley Research Center
Document Type
Reprint (Version printed in journal)
Authors
Krueger, Ronald
(NASA Langley Research Center Hampton, VA United States)
Minguet, Pierre J.
(Boeing Co. Philadelphia, PA United States)
OBrien, T. Kevin
(Army Research Lab. Hampton, VA United States)
Date Acquired
September 6, 2013
Publication Date
July 1, 1999
Subject Category
Composite Materials
Report/Patent Number
NAS 1.15:209365
NASA/TM-1999-209365
ARL-TR-2012
L-17872
Report Number: NAS 1.15:209365
Report Number: NASA/TM-1999-209365
Report Number: ARL-TR-2012
Report Number: L-17872
Meeting Information
Meeting: Composites Structures: Theory and Practice
Location: Seattle, WA
Country: United States
Start Date: May 17, 1999
End Date: May 18, 1999
Sponsors: American Society for Testing and Materials
Funding Number(s)
PROJECT: RTOP 581-10-21-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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