Abstract
The deformation relief was revealed to be formed and evolved on the surface of a cladding layer of a D16AT aluminum alloy under random cyclic loading. The surface saturation, roughness, and microplastic deformation are found to be quantitative estimates of the deformation relief and damage levels. Experimental deformation relief characteristics-load cycle number relations are similar and can be employed for predicting the fatigue crack initiation in aircraft structure elements.
Full Text 
Sign-in/Register to access full text options
Sign-in/Register to access full text options 
Published version (
Free)
Free) 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call
