| Summary: | 碩士 === 國立中山大學 === 機械工程研究所 === 86 === The interlaminar stresses of composite laminates have been paid attention for a long time . They are greatly influenced by fibrous direction , different stacking sequence , thickness of laminate , and notched problem . Until right now , it still hasn(t had any regulation of the relation between stacking sequence and interlaminar stresses to obey . Hence , in this paper , the numerical analysis with statistical induction will be applied to yield a part of conclusions for the parameters of stacking sequences and the laminate thickness .This paper we try to seek for the solution by numerical analysis of finite element method . Further , the failure of laminate due to delamination is the main topic in the study of interlaminar stresses . Thus , the interlaminar stress distribution of unnothed and notched case , along the free edges or around the central hole focuses our efforts . Then , we can tell the delamination interface and failure initiation site . After a series of analytical discussion , it is found that the interline of thin laminates and thick laminates is located between 32-ply laminates and 64-ply laminates . Obviously , the mechanical performance about laminate interfaces in thick laminates is better than that in thin laminates . On the other hand , (zz and (yz are the principal stresses to cause delamination inside the laminate . And the distribution of interlaminar stresses is very complex while the laminates contain [+45(/-45(]-layers . Finally , the result of stacking sequence and interlaminar stress distribution will be described detailedly in section 6-2 .
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