A Model for Predicting the Overload Effects on Fatigue Crack Growth Behavior AIAA-2003-1523

Manjunatha, C and Parida, B (2003) A Model for Predicting the Overload Effects on Fatigue Crack Growth Behavior AIAA-2003-1523. In: 44th AIAA/ASME/ASCE/AHS Structures, Structural Dynamics, and Materials Confere, 7-10 April 2003, Norfolk, Virginia.

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    Abstract

    An analytical model using crack driving force13; parameter, K * was developed to account for the13; overload interaction effects on fatigue crack growth13; behavior. Crack growth acceleration and retardation13; were modeled using residual stress intensity concept.13; Fatigue crack growth behavior was predicted using this13; model for SE(T) specimen made from an aircraft grade13; D16 (2024-T3 equivalent) aluminum alloy, subjected to13; (a) constant amplitude load, (b) constant amplitude13; load, interspersed with single tensile overloads at13; certain intervals of crack length. Fatigue crack growth13; tests were performed under the above load sequences13; and the experimental crack growth results were13; compared with those obtained from the proposed13; model. All the fatigue tests were performed in a servo-hydraulic13; test machine and the crack length was13; measured by traveling microscope/ cellulose acetate13; replication method. A fairly good correlation was13; obtained between the experimental and predicted crack13; growth curves under the applied loading sequence.13;

    Item Type: Conference or Workshop Item (Paper)
    Uncontrolled Keywords: Aluminium Alloys;Fatigue Cracks;Critical Loading;Crack Propogration;Damage Tolerance;Tensile Stressmathematical 13; Modelsstress Intensity Factors13;
    Subjects: AERONAUTICS > Aeronautics (General)
    Division/Department: Structural Integrity Division, Structural Integrity Division
    Depositing User: Mr. N A
    Date Deposited: 02 Feb 2006
    Last Modified: 24 May 2010 09:40
    URI: http://nal-ir.nal.res.in/id/eprint/1030

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