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تاثیر موقعیت و شکل حفره بر بار کمانش محوری پانل استوانه ای کامپوزیتی | ||
| نشریه مهندسی مکانیک امیرکبیر | ||
| مقاله 16، دوره 52، شماره 10، دی 1399، صفحه 2879-2898 اصل مقاله (2.38 M) | ||
| نوع مقاله: مقاله پژوهشی | ||
| شناسه دیجیتال (DOI): 10.22060/mej.2019.16042.6259 | ||
| نویسندگان | ||
| داود پورویس* 1؛ امین خواجه دزفولی2؛ شاپور مرادی3 | ||
| 1گروه عمران، دانشکده مهندسی، دانشگاه شهید چمران اهواز، اهواز، ایران | ||
| 2گروه مهندسی عمران، دانشکده مهندسی، دانشگاه شهید چمران اهواز، اهواز، ایران | ||
| 3گروه مهندسی مکانیک، دانشکده مهندسی، دانشگاه شهید چمران اهواز، اهواز، ایران | ||
| چکیده | ||
| در این مقاله تاثیر موقعیت و شکل حفره بر بارکمانش پانل استوانه‌ای کامپوزیتی تحت اثر فشار محوری بررسی شده است. به این منظور، پانل استوانه‌ای کامپوزیتی دارای حفره با شکل دلخواه با کمک روش نوار محدود شبیه‌سازی شده و با حل مسئله مقدار ویژه، بار کمانش آن تحت اثر فشار محوری محاسبه شده است. به منظور بررسی صحت نتایج بدست آمده از روش نوار محدود، مقایسه‌ای میان نتایج روش نوار محدود، نتایج روش اجزای محدود و نتایح حاصل از روش تحلیلی صورت گرفته است. با درنظر گرفتن پنج نوع حفره با شکل‌های مختلف در چهار محل مختلف از پانل استوانه‌ای، بار کمانش پانل استوانه‌ای دارای لایه‌بندی‌های مختلف، انحناهای متفاوت و شرایط تکیه‌گاهی مختلف محاسبه گردید. در میان همه موقعیت‌های حفره، موقعیت حفره مرکزی در مجموع بیشترین بار بحرانی را با روند صعودی در مقابل افزایش انحنای پانل ارائه می‌کند. بدترین عملکرد مربوط به حفره با خروج از مرکزیت عمود بر راستای بارگذاری می‌باشد. حفره بیضی با قطر کوچک در راستای بارگذاری بیشترین مقاومت کمانش و حفره با قطر بزرگ در راستای بارگذاری دارای کمترین مقاومت کمانشی بوده‌اند. از میان لایه‌بندی‌های مختلف، آرایش شبه‌همسانگرد برای تمامی اشکال و موقعیت‌های حفره حداکثر بار بحرانی محوری را ارائه می‌کند. | ||
| کلیدواژه‌ها | ||
| شکل حفره؛ موفعیت حفره؛ بار کمانش؛ پانل استوانه ای کامپوزیتی؛ روش نوار محدود | ||
| عنوان مقاله [English] | ||
| Effects of Position and Shape of Cutout on the Axial Buckling Load of Composite Cylindrical Panel | ||
| نویسندگان [English] | ||
| Davood Poorveis1؛ Amin Khajehdezfuly2؛ Shapour Moradi3 | ||
| 1Department of Civil Engineering, Faculty of Engineering, Shahid Chamran University of Ahvaz, Ahvaz, Iran | ||
| 2Department of Civil Engineering, Faculty of Engineering, Shahid Chamran University of Ahvaz, Ahvaz, Iran | ||
| 3Department of Mechanical Engineering, Faculty of Engineering, Shahid Chamran University of Ahvaz, Ahvaz, Iran | ||
| چکیده [English] | ||
| In this paper, the effects of position and shape of cutout on the buckling load of composite cylindrical panel under compressive load are investigated. The laminated cylindrical panel with an arbitrary cutout shape is simulated by the spline finite strip method. The first-order shear deformation theory is considered in this study. Using a linear buckling analysis, an eigenvalue problem is solved to obtain the buckling load of the panel under the compressive axial load. A comparison between the results obtained from the finite strip, finite element, and analytical methods was made to show the validity of the results obtained in this study. Several case studies are presented to investigate the effects of some parameters such as shape and position of cutout, central angle of panel, ply sequence of the composite layers, and boundary condition of the panel on its buckling load. The results show that the position and shape of cutout have considerable effects on the buckling load of the panel. The buckling load of the panel reaches its minimum when the cutout center has eccentricity from the loading direction. The results also show that the buckling load with quasi-isotropic configuration is greater than those of cross[1]ply and angle-ply. | ||
| کلیدواژه‌ها [English] | ||
| Cutout position, Cutout shape, Buckling load, Cylindrical composite panel, Finite strip method | ||
| مراجع | ||
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