سال انتشار: ۱۳۹۱

محل انتشار: اولین کنفرانس بین المللی مواد پیشرفته

تعداد صفحات: ۴

نویسنده(ها):

A.R.N Oskouie – Emam Hossein , Faculty of Mech. Eng. ,Hakimiyeh , Tehran
M.R Mohammadi – Emam Hossein University, Faculty of Aero Space .Eng. ,Hakimiyeh , Tehran
A.H.R Mazyak – Emam Hossein University, Faculty of Aero Space .Eng. ,Hakimiyeh , Tehran
M.R.S Barzegar –

چکیده:

Nowadays, as is well known, optimized composite materials are employed in many constructions when high strength to weight ratio and increasing the section rigidity of the light weight structures and ease of manufacturing are required. In this paper, new optimization method of graphite-epoxy composite cylindrical shell, under thermo mechanical loading is done by MATLAB SOFTWARE coding in GENETIC algorithm method to decrease weight of structure in satisfactory limit. The completely mathematical method of composite layup is reached by using of approximately approach analysis of long shells and plates. The failure criterion of Composite materials is T-SaiHill. Final results of analysis forobtain the critical points of rocket shooting, are done by ABAQUS SOFTWARE