نوع مقاله : مقاله پژوهشی
نویسندگان
1 دانشکده مکانیک، دانشگاه تربیت ندرس.تهران ایران
2 عضو هیئت علمی، گروه مهندسی مکانیک، دانشگاه تربیت مدرس، تهران، ایران
3 مهندسی هوافضا، دانشکده مکانیک، دانشگاه تربیت مدرس، تهران، ایران
چکیده
کلیدواژه‌ها
موضوعات
عنوان مقاله [English]
نویسندگان [English]
Sandwich panels are widely used in aircraft structures, such as the surfaces of the wing, radome and engine cowling, due to their optimal energy absorption compared to their low weight. Nowadays, hybrid sandwich panels are used in the aviation industry due to their different mechanical properties. The structure of sandwich panels consists of two thin layers and a core, the core prevents the effect of out-of-plane shear loads on the surface sheets and supports them against buckling. In this paper, the energy absorption and strength of sandwich panels with 2024-T3 aluminum plate as the shell and 5052 aluminum honeycomb as its core are investigated under quasi-static punch loading using two punchers with flat and spherical cross sections, experimentally and numerically. For numerical analysis, the explicit solution method is used in Abaqus finite element software. Failure modes in this test are classified as wrinkling of the panel, separation of the adhesive layer between the panel and the core, tearing of the panel, crushing of the core of the sandwich panel outside the plate, bending of the core of the sandwich panel inside the plate, and tearing of the core of the sandwich panel. The results of numerical analysis are in good agreement with the results of experimental samples. The minimum amount of energy absorption of sandwich panel experimental samples in the punch penetration test is 21.42 joules and the maximum is 25.13 joules.
کلیدواژه‌ها [English]
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