在複材結構的使用上，最常發生類似脫層的行為，進一步拓展會造成結構的破壞，因此在評估複材脫層的損壞程度上，便有相關的判據來幫助了解結構較易發生危險的位置。
本文之研究內容，主要利用層間應力破壞判據，脫層彎矩判據及脫層應力強度因子起裂判據此三項破壞準則來幫助分析直昇機尾桿構件，並且針對裂縫尖端部分之網格化做一番探討及研究。在構件分析上，先藉由有限元素分析，利用子模型方法，去取得整體構件受力之後的應力場及位移場分佈情況，再經計算程式之數值計算，取得破壞參數，進而由相關破裂判據去觀察分析資料，評估結構較易產生脫層起裂的疊層位置。
藉由本文中三種破壞判據的相互驗證所獲得的分析結果，可用來幫助在此構件的脫層分析，提供一設計上的參考方針，以期能有效減低構件損壞行為的發生，增強構件的強度及使用率。

One of the most encountered problems in the using of composite structures is delamination whose extension will make the structure break. So in judging the level of damage, there are have some criteria helping us to understand the dangerous locations in the structure.
In the article, three different fracture criteria are used to study the delamination fracture. The basic parameters of these criteria are interlaminar stresses, respectively, delamination moments and delamination stress intensity factors. By using these criteria, we hope to predict the most probable delamination location of the helicopter tail structure. In analysis, first using the finite element method to get the stress and displacement fields in the whole structure and the local delamination fields, and then evaluating the related fracture parameters by programs. Finally, we can use the fracture criteria to judge the delamination onset. From the analysis data, we try to estimate the delamination locations of the tail part. It is hopeful that our results can be used as a reference data for the helicopter design.

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