Fatigue crack propagation under spectrum loading

Sunder, R (1986) Fatigue crack propagation under spectrum loading. Journal of Aeronautical Society of India, 38 (3). pp. 153-160.

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This project involved the development of a method to predict the fatigue crack propagation process in thin-walled aircraft structural components under flight-by-flight loading. Extensive experimental test results provided the input for software development. They yielded evidence pointing to the complex nature of crack growth under spectrum loading and also provided the basis for procedures adopted for life prediction. A simple engineering method is proposed for estimating fatigue crack propagation life under random loading. Predictions are based on test data obtained under constant amplitude loading. Prediction accuracy favorably compares with that of available techniques. Computation time is extremely small, enabling the use of desktop computers for life predictions.

Item Type: Article
Uncontrolled Keywords: Crack propagation;Fracture mechanics;Fatigue cracking; Aeronautics;Aircraft components;Accuracy;Computer programs; Fatigue life;Aging aircraft;Aircraft;Computation;Aircraft structures;Crack closure;Crack propagation;Fatigue tests; Metal fatigue;Aerodynamic loads;Aluminium alloys;Cyclic loads
Subjects: ENGINEERING > Structural Mechanics
AERONAUTICS > Aeronautics (General)
Depositing User: Mr. Ravikumar R
Date Deposited: 07 Nov 2006
Last Modified: 24 May 2010 04:23
URI: http://nal-ir.nal.res.in/id/eprint/3321

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