【摘要】：復(fù)合材料在船舶、汽車和航空航天等工業(yè)領(lǐng)域得到了廣泛的應(yīng)用,而織物復(fù)合材料因其比強度高、材料可設(shè)計性好、熱膨脹系數(shù)小等諸多優(yōu)勢,越來越多的引起科研工作者和工程技術(shù)人員的重視。本文以復(fù)合材料織物單向板的疲勞試驗為基礎(chǔ),探究織物層合板的疲勞性能,發(fā)展出一套適用于織物復(fù)合材料層合板疲勞累積損傷失效分析的壽命預(yù)測方法。首先,將單向纖維增強復(fù)合材料層合板疲勞累積損傷壽命預(yù)測理論加以推廣,應(yīng)用于織物復(fù)合材料層合板,引入強度、剛度退化公式和擴展的Hashin疲勞失效準(zhǔn)則,建立織物復(fù)合材料層合板疲勞累積損傷壽命預(yù)測方法。其次,開展??16?0,90???、??16??45???織物單向?qū)雍习鍦?zhǔn)靜態(tài)拉伸試驗,分析其拉伸和剪切強度值;之后進行拉-拉疲勞試驗,得到織物單向板的應(yīng)力-壽命曲線,分析其疲勞破壞形式;利用數(shù)學(xué)軟件擬合得到織物層合板各主方向的強度和剛度退化公式。再次,基于本文推廣得到的織物復(fù)合材料層合板疲勞累積損傷壽命預(yù)測方法,利用FORTRAN語言編寫有限元軟件ABAQUS的UMAT材料子程序,實現(xiàn)對含孔、不對稱鋪層織物層合板進行應(yīng)力分析、疲勞損傷失效模式判斷、材料性能逐漸退化、材料性能突然退化以及疲勞壽命預(yù)測的分析過程。最后,開展含孔織物層合板的拉-拉疲勞試驗,對本文數(shù)值模擬所得結(jié)果進行驗證,驗證本文推廣得到的復(fù)合材料織物層合板疲勞壽命預(yù)測方法的適用性與可靠性。
[Abstract]:Composite materials have been widely used in ship, automobile, aerospace and other industrial fields. Fabric composites have attracted more and more attention of scientific researchers and engineers because of their high specific strength, good material design, low thermal expansion coefficient and so on. In this paper, based on the fatigue test of composite fabric unidirectional plate, the fatigue properties of fabric laminated plate are studied, and a set of life prediction method suitable for fatigue cumulative damage failure analysis of fabric composite laminated plate is developed. Firstly, the fatigue cumulative damage life prediction theory of unidirectional fiber reinforced composite laminates is extended and applied to fabric composite laminates. The strength and stiffness degradation formula and the extended Hashin fatigue failure criterion are introduced to establish the fatigue cumulative damage life prediction method of fabric composite laminates. Secondly, carry out 16 / 090, 16 / 45? The quasi-static tensile test of fabric unidirectional laminated plate is carried out, and the tensile and shear strength values are analyzed. Then the tensile-tensile fatigue test is carried out to obtain the stress-life curve of fabric unidirectional plate and its fatigue failure form. The degradation formulas of strength and stiffness in each main direction of fabric laminated plate are obtained by mathematical software fitting. Thirdly, based on the fatigue cumulative damage life prediction method of fabric composite laminates extended in this paper, the UMAT material subprogram of finite element software ABAQUS is compiled by FORTRAN language to realize the analysis process of stress analysis, fatigue damage failure mode judgment, gradual degradation of material properties, sudden degradation of material properties and fatigue life prediction of laminate laminates with holes and asymmetrical laminate. Finally, the tensile fatigue test of porous fabric laminates is carried out, and the numerical simulation results are verified to verify the applicability and reliability of the fatigue life prediction method of composite fabric laminates extended in this paper.
【學(xué)位授予單位】：哈爾濱工業(yè)大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2015
【分類號】：TB33

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本文編號：2507402