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بررسی آزمایشگاهی تأثیر فوم الاستومری بین لایه‌ای در الگوی خرابی پنل‌های چندلایه کامپوزیتی با لایه‌گذاری‌های مختلف | ||
| مکانیک هوافضا | ||
| مقاله 1، دوره 19، شماره 3 - شماره پیاپی 73، آذر 1402، صفحه 1-15 اصل مقاله (1.63 M) | ||
| نوع مقاله: مکانیک جامدات | ||
| نویسندگان | ||
| علیرضا نظری* 1؛ احسان بهمیاری2 | ||
| 1نویسنده مسئول: استادیار، گروه مهندسی عمران، دانشگاه فنی و حرفه ای، تهران، ایران. | ||
| 2استادیار، گروه مهندسی دریا، دانشکده مهندسی، دانشگاه خلیج فارس، بوشهر. | ||
| تاریخ دریافت: 18 دی 1401، تاریخ بازنگری: 10 بهمن 1401، تاریخ پذیرش: 06 اسفند 1401 | ||
| چکیده | ||
| دستیابی به روش‌هایی جهت بهبود رفتار خرابی ورق‌های چندلایه کامپوزیتی همواره موردتوجه محققین بوده است. در مقاله حاضر به‌منظور تأخیر در فروریزش چندلایه‌های کامپوزیتی به‌صورت ترد و ناگهانی، یک لایه فوم الاستومری بین ورق‌های کامپوزیتی از جنس شیشه-وینیل استر جاگذاری شده و تغییر الگوی خرابی و مقاومت نهایی ورق‌های ساندویچ شده با لایه‌گذاری‌های مختلف الیاف، نسبت به ورق‌های کامپوزیتی منفرد ملاحظه گردید. در لایه‌چینی‌های موردبررسی، ابتدا الگوی خرابی در انواع چندلایه‌ها با لایه‌چینی متفاوت شامل یک راستای قوی‌تر، لایه‌گذاری متعامد و لایه‌های بافته‌شده تحت بارگذاری متمرکز ملاحظه شده و تأثیر فوم بین‌لایه‌ای در تغییر الگوی تشکیل لولاهای گسیختگی در ورق‌ها و پارامترهای ظرفیت باربری و میزان انرژی جذب‌شده ملاحظه شد. سپس لایه‌ای از فوم الاستومری بین ورق‌های کامپوزیتی جاگذاری شد که توانست با توزیع تنش از ورق بالایی به ورق پایینی، باعث جذب انرژی قابل‌توجه در پنل‌ها قبل از فروریزش نهایی شده و تأخیر در رسیدن به لحظه گسیختگی کامل ایجاد کند. نتایج نشان داد که استفاده از فوم‌های الاستومری بین‌لایه‌ای باعث تغییر الگوی تشکیل لولاهای گسیختگی در پنل کامپوزیتی و نرم‌شدگی قابل‌توجه قبل از فروریزش نهایی می‌شود. این باعث افزایش جذب انرژی خصوصاً در مورد پنل‌های دارای سفتی خمشی کمتر تا حدود 115% می‌گردد که نتیجه رضایت‌بخشی است. | ||
تازه های تحقیق | ||
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| کلیدواژه‌ها | ||
| چندلایه‌های کامپوزیتی؛ فوم الاستومری بین لایه‌ای؛ الگوی خطوط شکست؛ جذب انرژی؛ کامپوزیت شیشه-وینیل استر | ||
| عنوان مقاله [English] | ||
| Experimental Study of the Impact of Interlayer Elastomeric Foam on Failure Pattern of Composite Laminated Panels with Various Layups | ||
| نویسندگان [English] | ||
| Ali Reza Nazari1؛ Ehsan Bahmyari2 | ||
| 1Corresponding author: Assistant Professor,, Department of Civil Engineering, Technical and Vocational University, Tehran, Iran. | ||
| 2Assistant Professor, Faculty of Engineering, Persian Gulf University, Bushehr, Iran. | ||
| چکیده [English] | ||
| Achieving methods to improve the failure behavior of composite multilayer plates has always been of interest to researchers. In this article, in order to delay the collapse of composite multilayers in a brittle and sudden manner, a layer of elastomeric foam is inserted between glass-vinyl ester composite plates and the change of the failure pattern and ultimate strength of sandwiched plates with different layering of fibers, compared to single composite plates, is observed. In the examined layers, firstly, the failure pattern was observed in different types of multilayers with different layering including a stronger alignment, orthogonal layering and woven layers under concentrated loading, and the effect of interlayer foam in changing the pattern of rupture hinges in the plates and parameters of bearing capacity and the amount of absorbed energy was observed. Then, a layer of elastomeric foam was placed between the composite plates, which was able to absorb significant energy in the panels before the final collapse by distributing the stress from the upper plate to the lower plate, and delayed the moment of complete rupture. The results showed that the use of interlayer elastomeric foams causes a change in the formation pattern of rupture hinges in the composite panel and significant softening before the final collapse. This increases energy absorption, especially in the case of panels with lower bending stiffness, up to about 115%, which is a satisfactory result. The objective for application of an elastomeric foam was omission of disadvantage by inflexible crushable foams. Although, the elastomeric foam supplied aa lower flexural modulus for the sandwich composite panels due to its lower shear rigidity, it could distribute stress concentration areas from the top to the bottom composite panels, to create a considerable fuselage to reach the ultimate strength via absorption of considerable energy. The results showed promising performance for failure response of elastomeric foam cored sandwich panels. Application of the interlayer elastomeric foam in the case of composite panels with lower stiffness showed larger enhancing effect. | ||
| کلیدواژه‌ها [English] | ||
| Composite laminates, Interlayer elastomeric foam, Failure lines pattern, Energy absorption, Glass/Vinyl ester composites | ||
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| مراجع | ||
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