سال انتشار: ۱۳۸۶
محل انتشار: هفتمین همایش انجمن هوافضای ایران
تعداد صفحات: ۶
H Hosseini-Toudeshky – Aerospace Engineering Department & Centre of Excellence in Computational Aerospace Engineering Amirkabir University of Technology, Associated Professor,
M Jalalvand – MSc Student
B Mohammadi – PhD Student
In this paper delamination phenomena in the laminates are analyzed using interface element. The interface elements are imposed with three different constitutive laws and the laminates are under monotonic quasi-static loading condition. For this purpose, a finite element code has been developed using twenty-node brick elements for the body and sixteen-node interface element for delamination modeling. Several examples containing an interface element with direct loading to produce mode-I and mixed-mode fracture conditions and also modeling of some benchmark fracture mechanics examples are presented. The obtained results are compared with the available numerical results in the literatures.