Fatigue crack propagation under spectrum loading

Sunder, R (1985) Fatigue crack propagation under spectrum loading. Technical Report. National Aeronautical Laboratory, Bangalore, India.

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Abstract

This project involved 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 favourably compares with that of available techniques. Computation time is extremely small, enabling the use of desktop computer for life predictions.

Item Type: Proj.Doc/Technical Report (Technical Report)
Uncontrolled Keywords: Aircraft structure;Crack propagation;Fatigue (materials);Random loads;Stress analysis;Amplitudes;Life (Durability);Prediction analysis;Structural analysis
Subjects: ENGINEERING > Structural Mechanics
Division/Department: Materials Science Division
Depositing User: M/S ICAST NAL
Date Deposited: 23 Apr 2008
Last Modified: 24 May 2010 09:55
URI: http://nal-ir.nal.res.in/id/eprint/4287

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