بررسی اثر آلیاژ حافظ شکل بر کمانش و پس‌کمانش پانل کامپوزیتی در جریان مافوق‌صوت با گرمایش حرارتی

در کار حاضر، اثر آلیاژهای هوشمند حافظ شکل بر کمانش و پس‌کمانش حرارتی پانل کامپوزیتی مونوکلینیک و تک‌جهته مورد بررسی قرار می‌گیرد. فشار آیرودینامیکی وارد شده بر سیستم با استفاده از روش تئوری پیستون مدلسازی و همچنین اثر گرمایش حرارتی برای جریان‌های مافوق صوت از روش دمای مرجع تخمین زده می‌شود. رفتار پانل به صورت غیرخطی، با تغییر شکل‌های بزرگ و بر اساس تئوری فون‌کارمن مدل‌سازی می‌گردد. نتایج بدست آمده نشان می‌دهد آلیاژ حافظ‌شکل می‌تواند دمای بحرانی کمانش حرارتی را افزایش دهد. در این مقاله، تاثیر چینش لایه‌های کامپوزیتی در بالا بردن دمای کمانش حرارتی نیز مورد مطالعه قرار می‌گیرد. نتایج بدست آمده نشان می‌دهد به واسطه‌ی استفاده از آلیاژ حافظ شکل، مقدار خیز پس‌کمانش حرارتی تا حدود زیادی کاسته می‌شود و در اختلاف دماهای بالاتر، میزان کاهش خیز پانل، افزایش می‌یابد.

investigation of the effect of shape memory alloy on buckling and post-buckling of composite panels in supersonic flow with thermal heating

in the present work, the effect of smart shape-memory alloys on thermal buckling and post-buckling of monoclinic and unidirectional composite panels has been investigated. the aerodynamic pressure applied to the system was modeled using the piston theory method. the effect of thermal heating for ultrasonic flows was also estimated from the reference temperature method. the panel is modeled nonlinearly with large deformations based on van karmen’s theory. the obtained results show that the shape-memory alloy was able to increase the critical temperature of thermal buckling. the effect of the arrangement of composite layers on increasing the thermal buckling temperature was also studied. the results show that the amount of thermal deflection is greatly reduced due to the use of this alloy. also, in the higher temperature differences, the rate of reduction of the panel increases.in this work, the effects of thermal stress on buckling and thermal buckling in a rectangular composite panel with hinge-hinge boundary conditions were investigated. also, the effect of shape retention alloy in controlling these two phenomena has been studied. the shape memory alloy wire was placed in martensitic mode to apply a compressive force to the panel to control the heating and aerodynamic forces after changing the phase to austenite. the governing equations of the system were extracted through the layer theory method to show the effects of in-plane displacements better.investigations on the effect of different layers (symmetry effects and arrangement angle of composite sheets) were performed to investigate thermal buckling. according to the obtained results, the layer arrangement of plates (0.90 / 0.90), (-45.45), (30/60), and (0.90 / 90.0), respectively, had the greatest effect on raising the critical temperature of thermal buckling in dimensional ratios equal to or greater than one. this shows that the symmetry of the arrangements has a greater effect than the angle of the arrangements. examining the buckling diagrams for the effect of a shape memory alloy, it can be concluded that by placing this alloy in the composite panel, in addition to raising the buckling temperature, this alloy has a greater effect on displacement control by increasing the temperature after the critical buckling temperature.