本文以有限條元法探討方形複合層板在中性面上含有離層且離層跨越整個長度方向時，離層對顫振邊界的影響。以線性結構理論、半穩定空氣動力學理論以及一致運動模型作為分析的基礎。文中探討層板於不同長寬比時離層長度、離層位置、疊層順序以及纖維角度對顫振邊界的影響。結果顯示離層長度、離層位置、疊層順序、長寬比以及纖維角度皆會影響其顫振邊界。以對稱Cross-ply層板而言，疊層順序的改變對於顫振邊界的影響，比離層長度及離層位置的影響要來的大。至於對稱Angle-ply層板，則由於纖維角度可任意改變，當離層發生時，層板的顫振行為隨纖維角度的改變而有較據烈的影響，尤其是在寬形層板的部份。

The effect of delamination on the flutter boundary of a delaminated rectangular plate was investigated by Finite Strip Method. Linear structural theory, quasi-steady supersonic aerodynamic theory and a moving together model were empolyed for the analysis. The effects of delamination length, delamination location, stacking sequence, fiber orientation and aspect ratio on the flutter boundary of the composite laminates were studied. Results show that the above mentioned factors have considerable effect on the flutter boundary of the laminates. For symmetric cross-ply laminate, the effect of stacking sequence on the flutter boundary is more profound than that of the delamination length and the delamination location. For symmetric angle-ply laminate, because of the fiber angle can change arbitrarily, the behavior of flutter boundary is more complex due to the change of the fiber orientation, especially in the part of the wide shape laminate.

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