SYMPOSIA PAPER Published: 01 January 1992

Contribution of Individual Load Cycles to Crack Growth under Aircraft Spectrum Loading


Fatigue crack growth in airframe materials under a variety of aircraft wing load spectra is numerically analyzed using a simple crack closure based model. An integrated load/damage-exceedance diagram is used to graphically describe the load spectrum as well as crack growth damage distribution. Characteristic features of crack growth damage contribution from individual load cycles are associated with the nature of the load spectrum. The significance of fatigue crack closure and its impact on damage distribution are studied.

Author Information

Sunder, R
National Aeronautical Laboratory, Bangalore, India
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Developed by Committee: E08
Pages: 176–190
DOI: 10.1520/STP24159S
ISBN-EB: 978-0-8031-5185-7
ISBN-13: 978-0-8031-1423-4