Sunder, R (1992) Contribution of individual load cycles to crack growth under aircraft spectrum loading. In: Proceedings of the Symposium, 24 Apr 1990, California, USA.Full text not available from this repository.
A simple crack closure based model is used to analyze fatigue crack growth in airframe materials under a variety of aircraft wing load spectra. The load spectrum and crack growth damage distribution are graphically described by an integrated range /damage-exceedance (RDE) diagram for nondimensionalized representation of load and associated crack growth damage exceedance. The RDA diagram can be used to study the effect of truncation, load omission, and variation in other spectrum variables.
|Item Type:||Conference or Workshop Item (Paper)|
|Uncontrolled Keywords:||Airframe materials;Crack closure;Crack propagation; Cumulative damage;Cyclic loads;Fatigue (Materials);Crack initiation;Digital simulation;Random loads;Residual stress; Stress intensity factors|
|Subjects:||CHEMISTRY AND MATERIALS > Metals and Metallic Materials|
|Division/Department:||Structural Integrity Division|
|Depositing User:||M/S ICAST NAL|
|Date Deposited:||01 Apr 2008|
|Last Modified:||24 May 2010 09:55|
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