SYMPOSIA PAPER Published: 01 January 1976
STP33380S

Structural Reliability Prediction Method Considering Crack Growth and Residual Strength

Source

An analysis method to estimate structural reliability based on crack growth and residual strength of aircraft structures is presented. The method is based on linear elastic fracture mechanics theory and allows for the variability of crack initiation and growth found in the experimental data of various metals. At a reference stress intensity factor, the central tendency and the variance values of material crack-growth parameters are determined. Combinations of these parameters are selected by Monte Carlo simulation techniques, and are used to describe the characteristically stochastic behavior of crack growth in a material. This description of material crack-growth behavior is then applied to the typical case of the built-up skin-stringer configuration of fail-safe type airplane structures to predict the number and size of cracks in a fleet at any time during its life. Thus, inspection routines may be established based on realistic fleet performance, to provide suitable levels of structural reliability for a fleet of airplanes during its operational lifetime.

Author Information

Varanasi, SR
Boeing Commercial Airplane Company, Seattle, Wash.
Whittaker, IC
Boeing Commercial Airplane Company, Seattle, Wash.
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Details
Developed by Committee: E08
Pages: 292–305
DOI: 10.1520/STP33380S
ISBN-EB: 978-0-8031-4672-3
ISBN-13: 978-0-8031-0344-3