تحلیل رفتار آیروالاستیک صفحه کامپوزیتی نازک با استفاده از تئوری پیستون، با اثر نقص هندسی کلی و محلی

نوع مقاله : مقاله پژوهشی

نویسندگان

1 دانشکده مهندسی مکانیک، دانشگاه تربیت مدرس، تهران، ایران

2 دانشکده مهندسی مکانیک، دانشگاه صنعتی مالک اشتر، تهران، ایران

چکیده

تحلیل آیروالاستیسیته صفحه مواد مرکب نازک تحت اثر نقص هندسی و بارهای خارجی، حائز اهمیت می‌باشد. در این پژوهش اثر نوع و تعداد لایه‌ها، زاویه الیاف و بار مکانیکی داخل صفحه در ترکیب با نقص هندسی به عنوان یک ترکیب جدید در مباحث آیروالاستیسیته مورد بررسی قرار گرفته است. با استفاده از اصل کار مجازی، روابط حاکم براساس تئوری صفحه نازک کرشهف تعیین شده است. سپس با استفاده از روش مودهای فرضی در تئوری باقی‌مانده وزنی گالرکین، معادلات دیفرانسیلی جزئی به معادلات دیفرانسیلی معمولی تبدیل شده است. بعد از بی‌بعد سازی، روابط نهایی با استفاده از روش عددی رانج-کوتا حل شده و نتایج حوزه زمانی برای تعیین رفتار فلاتر و پسا فلاتر صفحه استخراج شده است. نتایج تحلیل نشان داد که نقص هندسی با تولید بار غیر یکنواخت و نامتقارن، نوع لایه‌چینی، تعداد لایه‌ها و بارهای مکانیکی در جابجایی مرز فلاتر صفحه موثر است. اثر نقص هندسی محلی در تعیین مرز فلاتر لزوما ناپایدار کننده نیست، بلکه در مواردی بسته به اندازه و مکان نقص، امکان افزایش پایداری در مرز فلاتر صفحه را نیز دارد. به علاوه رفتار دینامیکی صفحه تحت اثر نقص هندسی محلی با اشکال و ابعاد مختلف، بسیار متنوع‌ و متفاوت با نوع نقص کلی (شکل مود اول) یا پوسته با انحنای کوچک است.

کلیدواژه‌ها

موضوعات

عنوان مقاله [English]

Aeroelastic analysis of a thin composite plate, with the effect of general and local geometric defects

نویسندگان [English]

  • Hamid moosazadeh 1
  • Mohammad Mahdi Mohammadi 2
1 tarbiat modares univercity of technology
2 Faculty of Mechanic - Malek Ashtar University of Technology- Tehran- Iran
چکیده [English]

In this study, the effect of laminate type and number of layers, fiber angle and modulus of elasticity in combination with the effect of global and local geometric defects has been investigated as a new combination in the field of aeroelasticity. Using the principle of virtual work, by directly integrating the problem-solving boundary, the governing equations are determined based on Kirchhoff thin-plate theory. Then, using the assumption mode method in Galerkin's theory, the partial differential equations are converted to ordinary nonlinear differential equations. The final nonlinear equations are solved using the Runge–Kutta numerical method and the time domain results are extracted to determine the flutter and post-flutter behavior of the plate. The results of the analysis showed that the geometric defect with non-uniform and asymmetric load production, the type of layering, the number of layers and mechanical loads are effective on the plane flutter boundary. The effect of local geometric defects in determining the flutter border is not necessarily destabilizing, but in some cases, depending on the size and location of the defect, it is also possible to increase the stability of the plane flutter boundary. In addition, the dynamic behavior of the plate under the effect of local geometric defects with different shapes and dimensions is very diverse and different from the of general defect (first mode shape) or shell with small curvature.

کلیدواژه‌ها [English]

  • Thin orthotropic composite plate
  • aeroelastic analysis
  • specific heat coefficient
  • post-flutter behavior
  • geometric defects

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نشریه مهندسی مکانیک امیرکبیر
دوره 55، شماره 2
اردیبهشت 1402
صفحه 235-256

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