In the present paper, an aircraft control surface flight cycle is predicted considering corner flaws and through crack under transport wing standard load using the NASGRO model available in AFGROW software. The effect of corner flaws length, depth of countersunk, panel thickness, axial load to pin load, composite patch, and disbond factor on the normalized stress intensity factor, critical flight cycle, and repeat inspection interval are investigated. The typical numerical prediction of the critical flight cycle is validated with analytical estimation and published experimental results, and shows excellent agreement.
Numerical Estimation of Flight Cycle and Repeat Inspection Interval
Journal of Aircraft ; 53 , 3 ; 790-799
2016-03-10
10 pages
Article (Journal)
Electronic Resource
English
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