علوم و فناوری کامپوزیت

تحلیل استاتیکی و دینامیکی تیر جدار نازک کامپوزیتی با الیاف خمیده

نوع مقاله : مقاله پژوهشی

نویسندگان

1 استادیار، مهندسی مکانیک، دانشگاه فنی و مهندسی گلپایگان، گلپایگان، ایران

2 استاد، مهندسی هوافضا، دانشگاه صنعتی شریف، تهران، ایران

10.22068/jstc.2018.91728.1463

چکیده

در این تحقیق تحلیل استاتیکی و دینامیکی بال هواپیما ساخته شده از مواد مرکب، به روش تحلیلی بررسی می‌شود. بال به صورت تیر جدار نازک یکسرگیردار با سـطح مقطـع بـسته‌ و دارای لایه‌چینی سـختی محیطـی نامتقـارن CAS، مدلسازی شده است. در مدل تیر اثرات غیرکلاسیک مثل تنش برشی، قید واپیچش، مدل پیچشی غیریکنواخت و غیر ایزوتروپ بودن ماده در نظر گرفته می‌شود. معادلات حاکم با استفاده از اصل هامیلتون توسعه یافته به دست می‌آیند و بر اساس روش گالرکین توسعه یافته حل می‌شوند. نتایج حاصل از آنالیز از تطابق خوبی با داده‌های تجربی و نتایج تحلیل عددی برخوردار است. در این مقاله برای اولین بار اثرات تغییرات خطی و پیوسته زاویه الیاف در طول تیر جدار نازک کامپوزیتی که منجر به سفتی متغیر در سازه می‌شود، مورد بررسی و تحلیل قرار می‌گیرد. برای این منظور از دو تعریف مسیر با تغییرات خطی زاویه الیاف و مسیر با انحنای ثابت استفاده می‌شود. بر مبنای نتایج تحلیل، فرکانس طبیعی و کوپلینگ خمش-پیچش وابسته به زاویه الیاف می‌باشد و استفاده از الیاف خمیده با تغییر پیوسته زاویه الیاف در طول تیر، امکان استفاده بهینه از خواص کامپوزیت و افزایش فضای طراحی نسبت به بال معمولی با الیاف مستقیم را فراهم می‌کند.

کلیدواژه‌ها

موضوعات

عنوان مقاله [English]

Static and dynamic analysis of composite thin walled beam with curvilinear fiber

نویسندگان [English]

  • Zahra Zamani Miandashti 1
  • Hasan Haddadpour 2

1 School of Mechanical Engineering, Golpayegan University of Technology, Golpayegan, Iran

2 School of Aerospace Engineering, Sharif University of Technology, Tehran, Iran

چکیده [English]

In this study, the static and dynamic analysis of composite wing is investigated using analytical method. The wing is modeled as a cantilevered thin walled beam with a single-cell closed cross section and the circumferentially asymmetric stiffness (CAS) configuration. The non-classical effects such as transverse shear, warping restraint, rotary inertia, nonuniform torsional model and material anisotropy are considered in the beam model. The governing equations were derived by means of the extended Hamilton’s principle and are solved based on the extended Galerkin’s method. From the validation process, the obtained results are in good agreement with the numerical results and experimental data. In this paper, a linear spanwise variation of the fiber orientation along the thin-walled beam span resulting in a variable-stiffness structure is investigated for the first time. Therefore, two fiber path definitions will be used with linear fiber orientation variation and with constant curvature of the fiber path. Numerical results indicate that eigenfrequencies and bending-torsion couplings depend on fiber angle, resulting improvements of wings with curvilinear fiber over conventional, straight ones through the variation of fiber angle along the beam span and increase of the design space.

کلیدواژه‌ها [English]

  • Thin walled composite beam
  • Aircraft wing
  • Curvilinear fiber
  • Non-classical effect
مراجع
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علوم و فناوری کامپوزیت
دوره 6، شماره 1
خرداد 1398
صفحه 79-88
فایل ها
هم رسانی
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