Manjunatha, CM and Parida, BK (2004) Prediction of Fatigue Crack Growth After Single Overload in an Aluminum Alloy. AIAA Journal, 42 (8). pp. 1536-1542. ISSN 0001-1452Full text not available from this repository.
An analytical method using crack driving force parameter K was developed to account for the single overload interaction effects on the constant amplitude fatigue crack growth behavior in D16 (2024-T3 equivalent) aluminum alloy. Crack growth acceleration and retardation were accounted for by using residual stress intensity concept. Fatigue crack growth behavior was predicted using this method for a thin SE(T)specimen subjected to 1) constant amplitude load and 2) constant amplitude load interspersed with single tensile overloads at certain intervals of crack length. Fatigue crack growth tests were performed13; with these load sequences, and the experimental crack growth results obtained were compared with predictions made by use of the proposed analytical method. All of the fatigue crack growth tests were performed in a vohydraulic test machine. Crack length was measured by the traveling microscope/cellulose acetate replication method. A fairly good correlation was obtained between the experimental and13; predicted fatigue crack growth curves under the applied loading sequence.
|Item Type:||Journal Article|
|Uncontrolled Keywords:||Fatigue crack growth;analytical method using crack driving force parameter|
|Subjects:||AERONAUTICS > Aeronautics (General)|
|Division/Department:||Structural Integrity Division, Structural Integrity Division|
|Depositing User:||Ms Indrani V|
|Date Deposited:||14 Nov 2005|
|Last Modified:||24 May 2010 09:39|
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