سال انتشار: ۱۳۸۶

محل انتشار: هفتمین همایش انجمن هوافضای ایران

تعداد صفحات: ۶

نویسنده(ها):

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

چکیده:

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.