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Residual strength predictions with crack buckling

Content Provider	NASA Technical Reports Server (NTRS)
Author	Gullerud, A. S. Hampton, R. W. Dawicke, D. S. Dodds Jr., R. H.
Copyright Year	1999
Description	Fracture tests were conducted on middle crack tension, M(T), and compact tension, C(T), specimens of varying widths, constructed from 0.063 inch thick sheets of 2024-T3 aluminum alloy. Guide plates were used to restrict out-of-plane displacements in about half of the tests. Analyses using the three-dimensional, elastic-plastic finite element code WARP3D simulated the tests with and without guide plates using a critical CTOA fracture criterion. The experimental results indicate that crack buckling reduced the failure loads by up to 40%. Using a critical CTOA value of 5.5 deg., the WARP3D analyses predicted the failure loads for the tests with guide plates within +/- 10% of the experimentally measured values. For the M(T) tests without guide plates, the WARP3D analyses predicted the failure loads for the 12 and 24 inch tests within 10%, while over predicting the failure loads for the 40 inch wide tests by about 20%.
File Size	615502
Page Count	10
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19990028738
Archival Resource Key	ark:/13960/t9576c369
Language	English
Publisher Date	1999-01-01
Access Restriction	Open
Subject Keyword	Structural Mechanics Crack Tips Metal Sheets Aluminum Alloys Computerized Simulation Residual Strength Load Tests Finite Element Method Crack Opening Displacement Failure Analysis Predictions Mathematical Models Cracking Fracturing Applications Programs Computers Buckling Aircraft Structures Structural Analysis Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Article

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