| STUDY ON THE TENSILE FATIGUE DAMAGE OF QUASI—ISOTROPIC COMPOSITE LAMINATES |
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| 作者姓名： | I.G.Kim I.S.Kim O.S.Kim YaragarraK.D.V.Prasad |
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| 作者单位： | I.G. Kim，I.S. Kim，O.S. Kim and Yaragarra K.D.V.Prasad Department of Aerospace Engineering，Chosun University，375 Seosuk-dong，Dong-gu，Gwangju，501-759，Korea Department，of Mechanical Engineering，Mokpo National University，61 Dorimri，Chunhke-myun，Muan-gun，Chonam，534-729，Korea Department of Mechanical Engineering，Yosu National University，San 96-1，Dunduck-dong. Yosu，Chon-nam，550-749，KoreaSchool of Mech. & Med. Engineering，Queensland University of Technology，2 George Street，GPO Box 2434，Brisbane. QLD 4001，Australia |
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| 基金项目： | BK(Brain Korea)21 of Ministry of Education, Korea. |
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| 摘 要： | Quasi-isotropic. laminates have isotropic elastic properties in all in-plane directions. Therefore, this kind of laminate is widely used for structural elements. The simplest stacking sequence of quasi-isotropic laminates is 0/-60/60]s. When the direction of applied axial load to 0/-60/60]s laminate is inclined at a 30-degree angle, we have the other quasi-isotropic laminate 30/-30/90]s under axial load. The failure mechanisms of these two laminates are, however, entirely different from each other because these two laminates have different distribution of the interlaminar stresses. It was confirmed by tensile fatigue tests that the 0/-60/60]s laminate does not show any visible fatigue damage, but the 30/-30/90]s laminate develops edge-delamination during cyclic loading. The analytical results were in good agreement with the experimental results.
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| 收稿时间： | 2002-04-24 |
STUDY ON THE TENSILE FATIGUE DAMAGE OF QUASI-ISOTROPIC COMPOSITE LAMINATES |
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| I.G.Kim
,I.S.Kim
,O.S.Kim
,YaragarraK.D.V.Prasad.STUDY ON THE TENSILE FATIGUE DAMAGE OF QUASI-ISOTROPIC COMPOSITE LAMINATES[J].Acta Metallurgica Sinica(English Letters),2003,16(1):1-7. |
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| Authors: | IGKim ISKim OSKim Yaragarra KDVPrasad |
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| Affiliation: | DepartmentofAerospaceEngineering,ChosunUniversity,375Seosuk－dong,Dong－gu,Gwangju,501－759,Korea |
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| Abstract: | Quasi-isotropic laminates have isotropic elastic properties in all in-plane directions. Therefore, this kind of laminate is widely used for structural elements. The simplest stacking sequence of quasi-isotropic laminates is 0/-60/60]s. When the direction of applied axial load to 0/-60/60]S laminate is inclined at a 30-degree angle, we have the other quasi-isotropic laminate 30/-30/90]s under axial load. The failure mechanisms of these two laminates are, however, entirely different from each other because these two laminates have different distribution of the interlaminar stresses. It was confirmed by tensile fatigue tests that the 0/-60/60]s laminate does not show any visible fatigue damage, but the 30/-30/90]s laminate develops edge-delamination during cyclic loading. The analytical results were in good agreement with the experimental results. |
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| Keywords: | composite material delamination fatigue fracture mechanics interlaminar stress |
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