Application of Reliability Analysis to Aircraft Structures Subject to Fatigue Crack Growth and Periodic Structural Inspection.

摘要

A method of simulating crack growth has been investigated. The proposed model,which is based on linear elastic fracture mechanics theory,allows for the variability in crack growth behavior found in the experimental data of various materials. Given a reference stress intensity factor range and central tendency values for the crack growth rate and the exponent of the stress intensity factor excursions of a material in a specified configuration,Monte Carlo simulation is used to select various combinations of parameters. These are then used to generate fatigue cracks,on the assumption that crack growth rate is a power function of the stress intensity factor range. The residual strength of the cracked structure is considered to be a decreasing function of the induced crack length. The probability of crack detection also depends on the generated crack and is assumed to improve with increasing crack length. However,this improved detection probability is modified by the probability that the crack location is not the one being inspected. (Modified author abstract)