Abstract
In aircraft structure maintenance, when we remove edge cracks of some structures, such as aircraft skin, or frame edges, the removal depth and radius affect the stress intensity factor of the crack tip, thereby affecting the service life of the structure. In this paper, we use the finite element method to calculate the crack stress intensity factor of the finite width plate and compare it with the engineering analysis method, which proves the effectiveness of the finite element method. We further research the influence of the crack stress intensity factor with different edge damage depths and radii of the finite width plate, which will provide a reference for aircraft structure edge damage tolerance analysis in engineering.
Sign-in/Register to access full text options 
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
