發(fā)布時(shí)間：2018-06-25 13:16

  本文選題：碳纖維復(fù)合材料層合板 + 漸進(jìn)失效分析方法��； 參考：《浙江大學(xué)》2015年碩士論文

【摘要】：碳纖維增強(qiáng)復(fù)合材料由碳纖維增強(qiáng)體和樹脂基體組成,它具有一系列優(yōu)異性能,如高強(qiáng)度、可設(shè)計(jì)性強(qiáng)、低密度、低熱膨脹系數(shù)等,是先進(jìn)材料領(lǐng)域重點(diǎn)開發(fā)、研究的一種結(jié)構(gòu)材料,具有良好的應(yīng)用前景。然而,復(fù)合材料失效機(jī)理通常非常復(fù)雜,對(duì)強(qiáng)度、剛度、損傷容限以及剩余壽命的評(píng)估和預(yù)測(cè)提出了較大挑戰(zhàn)。目前,國(guó)內(nèi)外在復(fù)合材料漸進(jìn)失效領(lǐng)域已經(jīng)開展了諸多研究,然而通常實(shí)際應(yīng)用中的復(fù)合材料幾何形狀和失效機(jī)理復(fù)雜,經(jīng)常導(dǎo)致應(yīng)力集中和局部化問(wèn)題,根本特征是剛度退化帶來(lái)的應(yīng)變軟化問(wèn)題,這使得運(yùn)用常規(guī)有限元分析結(jié)構(gòu)力學(xué)性能失去客觀性,數(shù)值求解失去意義。這是因?yàn)榫植炕瘑?wèn)題自然引入了尺度比例而連續(xù)介質(zhì)力學(xué)缺乏尺度比例參數(shù)。目前國(guó)內(nèi)外在復(fù)合材料局部化問(wèn)題的研究非常少。本文基于非局部積分理論和連續(xù)損傷力學(xué)理論,針對(duì)碳纖維復(fù)合材料層合板結(jié)構(gòu),基于ABAQUS有限元軟件發(fā)展了有限元數(shù)值計(jì)算技術(shù),開展了非局部漸進(jìn)失效分析,深入研究了含中心開孔復(fù)合材料層合板的漸進(jìn)失效機(jī)理和強(qiáng)度。取得的研究進(jìn)展如下：(1)建立了復(fù)合材料層合板漸進(jìn)失效分析預(yù)測(cè)理論模型,確定了以等效應(yīng)變作為判斷纖維和基體失效的參量,推導(dǎo)了針對(duì)纖維斷裂和基體開裂損傷變量的破壞進(jìn)化律及一致切線模量,為復(fù)合材料的強(qiáng)度預(yù)測(cè)提供理論支撐。(2)基于非局部積分理論,將控制應(yīng)變軟化的內(nèi)變量-等效應(yīng)變進(jìn)行非局部平均處理,從而在模型中引入針對(duì)纖維和基體的兩個(gè)尺度比例參數(shù),最后針對(duì)隱式有限元求解問(wèn)題,推導(dǎo)了各向異性非局部一致切線模量,為解決復(fù)合材料應(yīng)變局部化問(wèn)題提供了理論基礎(chǔ)。(3)運(yùn)用ABAQUS-UEL(用戶自定義單元子程序模塊),UMAT(用戶自定義材料子程序模塊),USDFLD(用戶場(chǎng)變量子程序模塊)和UEXTERNALDB(用戶外部數(shù)據(jù)接口應(yīng)用子程序模塊),開展數(shù)值編程,實(shí)現(xiàn)了提出的非局部漸進(jìn)失效模型,從而形成了復(fù)合材料非局部漸進(jìn)失效分析數(shù)值計(jì)算技術(shù)。(4)針對(duì)含中心圓孔復(fù)合材料層合板結(jié)構(gòu),運(yùn)用上述提出的非局部漸進(jìn)失效理論模型,開展了非局部有限元分析,與試驗(yàn)結(jié)果進(jìn)行比較,探討了開孔半徑、鋪層方式、網(wǎng)格尺寸和非局部尺度比例參數(shù)對(duì)復(fù)合材料層合板漸進(jìn)失效特性和強(qiáng)度、剛度的影響規(guī)律。
[Abstract]:Carbon fiber reinforced composites are composed of carbon fiber reinforcements and resin matrix. It has a series of excellent properties, such as high strength, high designability, low density, low thermal expansion coefficient and so on. A kind of structural material studied in this paper has a good prospect of application. However, the failure mechanism of composite materials is usually very complex, which poses a great challenge to the evaluation and prediction of strength, stiffness, damage tolerance and residual life. At present, many researches have been carried out in the field of progressive failure of composite materials at home and abroad. However, the geometric shape and failure mechanism of composite materials in practical applications are often complicated, which often lead to the problem of stress concentration and localization. The fundamental characteristic is the strain softening problem caused by stiffness degradation, which makes the use of conventional finite element analysis of the mechanical properties of the structure lose objectivity, and the numerical solution is meaningless. This is because the localization problem naturally introduces the scale and the continuum mechanics lacks the scale parameter. At present, there are few researches on localization of composite materials at home and abroad. Based on the nonlocal integral theory and the theory of continuous damage mechanics, the finite element numerical calculation technology is developed based on Abaqus finite element software for carbon fiber composite laminated plate structure, and the nonlocal progressive failure analysis is carried out. The progressive failure mechanism and strength of composite laminates with central holes were studied. The research progress is as follows: (1) A theoretical model of progressive failure analysis and prediction of composite laminates is established, and the equivalent strain is used as the parameter to judge the failure of fiber and matrix. The damage evolution law and uniform tangent modulus for fiber fracture and matrix cracking damage variables are derived, which provide theoretical support for the strength prediction of composites. (2) based on the nonlocal integral theory, The internal variable, equivalent strain, which controls strain softening, is treated with non-local average, and two scale proportional parameters for fiber and matrix are introduced into the model. Finally, the implicit finite element method is used to solve the problem. The anisotropic nonlocal uniform tangent modulus is derived. It provides a theoretical basis for solving the strain localization problem of composite materials. (3) using AbaquUS-UEL (user-defined unit subroutine module) UMAT (user-defined material subroutine module) USDFLD (user field variable subroutine module) and UEXTERNALDB (user external data) Interface application subroutine module), carry out numerical programming, The proposed nonlocal progressive failure model is realized, and the numerical calculation technique for nonlocal progressive failure analysis of composite materials is formed. (4) for the composite laminated plate structure with a central circular hole, the above proposed nonlocal progressive failure theory model is used. The non-local finite element analysis was carried out and compared with the experimental results. The effects of the opening radius, layering mode, mesh size and non-local scale ratio parameters on the progressive failure characteristics, strength and stiffness of composite laminates were discussed.
【學(xué)位授予單位】：浙江大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2015
【分類號(hào)】：TB33

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本文編號(hào)：2066070