正交性複合材料翼翅之超音速顫振有限元素法分析

本研究之目的在發展－有限元素法程式以分析正交性複合材料翼翅於超音速飛行之顫振行爲，顫振乃飛行體翼翅承受過大之氣動力負荷，導致結構振動自原來之穩定收斂變爲發散。爲驗證此有限元素法之準確性，本研究亦推導出一根部固定之正交性複合材料矩形薄板翼翅的顫振理論解析式。本報告發展之顫振有限元素法程式可應用於超音速複合材料翼翅之顫振問題解析。經本有限元素法程式分析顯示欲提高翼翅之顫振速度除了提高翼翅之結構自然振頻外，同時應避免相鄰之兩個自然振頻接近。

關鍵字

氣彈學；顫振；正交性複合材料；有限元素法

並列摘要

A finite element program has been developed for evaluating the flutter phenomenon of a supersonic, orthotropic composite laminated wing. Flutter is concerning with the dynamic instability of aeroelasticity, which is the study of the effect of aerodynamic forces on an elastic flight vehicle. In order to verify the accuracy of this algorithm, an analytical solution for a rectangular orthotropic wing with built-in at the root has been developed. This developed finite element program can be used to analysis the wing flutter problem of a supersonic flight vehicle. The results of this study indicate that in order to avoid the occurrence of the wing flutter, not only a stiffer structure should be used, but also that any two neighboring natural frequencies of the wing structure should be separated enough to eliminate the coupled effect between these vibration modes.

並列關鍵字

aeroelasticity ； flutter ； supersonic wing ； finite element method

國際替代計量

正交性複合材料翼翅之超音速顫振有限元素法分析

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