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Kumar, Anil, Raghav, Sapna, Supale, Jayant Pandurang, Datar, Gajanan Shravan. (1405). Modeling and Experimental Validation of Carbon Fiber-Kevlar Honeycomb Core Sandwich Structure. نشریه هنرهای کاربردی, 13(1), 69-82. doi: 10.22075/macs.2025.36296.1782
Anil Kumar; Sapna Raghav; Jayant Pandurang Supale; Gajanan Shravan Datar. "Modeling and Experimental Validation of Carbon Fiber-Kevlar Honeycomb Core Sandwich Structure". نشریه هنرهای کاربردی, 13, 1, 1405, 69-82. doi: 10.22075/macs.2025.36296.1782
Kumar, Anil, Raghav, Sapna, Supale, Jayant Pandurang, Datar, Gajanan Shravan. (1405). 'Modeling and Experimental Validation of Carbon Fiber-Kevlar Honeycomb Core Sandwich Structure', نشریه هنرهای کاربردی, 13(1), pp. 69-82. doi: 10.22075/macs.2025.36296.1782
Kumar, Anil, Raghav, Sapna, Supale, Jayant Pandurang, Datar, Gajanan Shravan. Modeling and Experimental Validation of Carbon Fiber-Kevlar Honeycomb Core Sandwich Structure. نشریه هنرهای کاربردی, 1405; 13(1): 69-82. doi: 10.22075/macs.2025.36296.1782

Modeling and Experimental Validation of Carbon Fiber-Kevlar Honeycomb Core Sandwich Structure

Mechanics of Advanced Composite Structures
مقاله 6، دوره 13، شماره 1 - شماره پیاپی 27، تیر 2026، صفحه 69-82    اصل مقاله (689.51 K)
نوع مقاله: Research Article
شناسه دیجیتال (DOI): 10.22075/macs.2025.36296.1782
نویسندگان
Anil Kumar* 1؛ Sapna Raghav1؛ Jayant Pandurang Supale1؛ Gajanan Shravan Datar2
1G. B. Pant DSEU Okhla-I Campus, New Delhi,110020, India
2Government College of Engineering and Research, Avasari, Pune- 412406, India
تاریخ دریافت: 28 آذر 1403،  تاریخ بازنگری: 26 فروردین 1404،  تاریخ پذیرش: 06 تیر 1404 
چکیده
Composite sandwich structures are becoming more and more popular in the sports, automotive, and aerospace sectors because of their excellent strength-to-weight ratio. However, more research is required to fully understand their stiffness properties and the accuracy of predictive modeling. By simulating and examining two different sandwich structures made of Carbon fiber face sheets and Kevlar honeycomb core material represented as an equivalent solid, this study fills this gap. The Gibson and Ashby model has been adopted to find the equivalent orthotropic properties of the core because this model provides a balance between precision, computational efficiency, and suitability for honeycomb cores, guaranteeing accurate stiffness predictions and facilitating simple engineering design implementation. Experimental stiffness values of 529.74 N/mm and 479.98 N/mm for the two configurations are obtained by performing a “Three Point Bend Test” on the manufactured panels. With an accuracy deviation of about 0.84%, the numerical model predictions closely resemble the experimental findings, demonstrating the model’s dependability in representing the material’s static behavior. The sandwich structure demonstrates a stiffness of about 565 N/mm, suitable for high-load applications in aerospace and automotive sectors. Numerical modeling effectively validates the experimental results by accurately predicting the stiffness of Kevlar honeycomb core sandwich panels.
کلیدواژه‌ها
Numerical modeling؛ Composite sandwich؛ Kevlar® Honeycomb؛ Orthotropic properties؛ Stiffness
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