A model for predicting the overload effects on fatigue crack growth behavior

Manjunatha, CM and Parida, BK (2003) A model for predicting the overload effects on fatigue crack growth behavior. In: 44th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 7-10 Apr 2003.

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Abstract

An analytical model using crack driving force parameter, amp;Delta;K* was developed to account for the overload interaction effects on fatigue crack growth behavior. Crack growth acceleration and retardation were modeled using residual stress intensity concept. Fatigue crack growth behavior was predicted using this model for SE(T) specimen made from an aircraft grade D16 (2024-T3 equivalent) aluminum alloy, subjected to (a) constant amplitude load, (b) constant amplitude load, interspersed with single tensile overloads at certain intervals of crack length. Fatigue crack growth tests were performed under the above load sequences and the experimental crack growth results were compared with those obtained from the proposed model. All the fatigue tests were performed in a servo-hydraulic test machine and the crack length was measured by traveling microscope/cellulose acetate replication method. A fairly good correlation was obtained between the experimental and predicted crack growth curves under the applied loading sequence.13;

Item Type: Conference or Workshop Item (Paper)
Uncontrolled Keywords: Aerospace engineering;Aircraft parts and equipment13; ;Cracks;Crack propagation;Mathematical models13; ;Residual stresses;Aluminum alloys;Fatigue testing;Microscopes
Subjects: ENGINEERING > Structural Mechanics
Division/Department: Structural Integrity Division, Structural Integrity Division
Depositing User: MS Jayashree S
Date Deposited: 20 Apr 2007
Last Modified: 24 May 2010 09:55
URI: http://nal-ir.nal.res.in/id/eprint/4147

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