【摘要】：碳纖維復(fù)合材料以其高比強(qiáng)度、比模量,性能可設(shè)計(jì)、易于整體成形等諸多優(yōu)點(diǎn)被廣泛應(yīng)用于軍事、民用等領(lǐng)域,如在航天火箭、飛機(jī)、導(dǎo)彈、風(fēng)電葉片等制造中作為結(jié)構(gòu)材料、功能材料或結(jié)構(gòu)與功能集成材料,并且呈逐漸從簡(jiǎn)單零部件、次承力部件向大型復(fù)雜結(jié)構(gòu)件、主承力結(jié)構(gòu)件轉(zhuǎn)化的趨勢(shì)�？辜羟心芰Σ钍菑�(fù)合材料的主要缺點(diǎn),特別是層合結(jié)構(gòu),所以對(duì)復(fù)合材料材料在剪切力作用下?lián)p傷模式的無(wú)損檢測(cè)顯得尤為重要。復(fù)合材料層間性能取決于基體性能,層間材料性能僅為纖維方向的幾十分之一,分層損傷破壞是復(fù)合材料最主要的破壞形式。因此,本文對(duì)碳纖維復(fù)合材料分層損傷過(guò)程進(jìn)行了研究分析。本文建立一個(gè)碳纖維復(fù)合材料開孔層合板面內(nèi)損傷模型來(lái)模擬此材料在面內(nèi)剪切力作用下的損傷失效形式。利用ABAQUS的子程序功能,二次開發(fā)了復(fù)合材料橫向初始損傷準(zhǔn)則,在纖維方向由纖維主導(dǎo)的損傷采用Hashin準(zhǔn)則,基體主導(dǎo)的損傷采用Puck作用面準(zhǔn)則。對(duì)[0°/90°]14、[45°/-45°]14兩種鋪層方式的T700碳纖維復(fù)合材料開孔層合板面內(nèi)剪切過(guò)程進(jìn)行了有限元分析,研究分析了剪切過(guò)程中出現(xiàn)的損傷失效形式以及損傷演化過(guò)程。對(duì)[0°/90°]14、[45°/-45°]14兩種鋪層T700碳纖維復(fù)合材料開孔層合板剪切損傷進(jìn)行聲發(fā)射監(jiān)測(cè)實(shí)驗(yàn)研究,并利用光柵光纖技術(shù)測(cè)量實(shí)驗(yàn)過(guò)程中試件的應(yīng)變過(guò)程,研究了各損傷破壞過(guò)程中的聲發(fā)射特性,建立了損傷失效形式與聲發(fā)射信號(hào)間的聯(lián)系。并通過(guò)實(shí)驗(yàn)載荷、應(yīng)變曲線以及損傷形貌的分析與有限元分析結(jié)果進(jìn)行比較,分析結(jié)果和實(shí)驗(yàn)結(jié)果能夠得到互相驗(yàn)證。利用K-means聚類方法對(duì)碳纖維復(fù)合材料面內(nèi)剪切過(guò)程的聲發(fā)射信號(hào)進(jìn)行了聚類分析,選取計(jì)數(shù)和持續(xù)時(shí)間作為特征參數(shù),分析了T700碳纖維復(fù)合材料剪切過(guò)程聲發(fā)射信號(hào)的模式識(shí)別,為聲發(fā)射監(jiān)測(cè)預(yù)報(bào)碳纖維復(fù)合材料損傷失效提供了實(shí)驗(yàn)依據(jù)。
[Abstract]:Carbon fiber composites have been widely used in military, civil and other fields because of their high specific strength, specific modulus, performance design, easy overall forming and many other advantages, such as space rockets, aircraft, missiles and so on. Wind turbine blades are used as structural materials, functional materials or structural and functional integration materials, and show a trend of gradual transformation from simple parts, secondary bearing components to large complex structural parts and main bearing structural parts. The poor shear resistance of composites is the main disadvantage of composites, especially the laminated structure, so it is particularly important to nondestructive testing of damage modes of composites under shear force. The interlaminar properties of composites depend on the properties of matrix. The properties of interlaminar materials are only one tenth of the fiber direction. Delamination damage is the most important failure form of composites. Therefore, the delamination damage process of carbon fiber composites was studied and analyzed in this paper. In this paper, an in-plane damage model of carbon fiber composite porous laminated plate is established to simulate the damage failure mode of the material under in-plane shear force. Based on the subroutine function of ABAQUS, the transverse initial damage criterion of composites is developed. The Hashin criterion is used for the damage dominated by fiber in the fiber direction, and the Puck action surface criterion is used for the damage dominated by matrix. The in-plane shear process of [0 擄/ 90 擄] 14 and [45 擄/-45 擄] 14 laminated T700 carbon fiber composites was analyzed by finite element method. The damage failure form and damage evolution process in shear process are studied and analyzed. The shear damage of [0 擄/ 90 擄] 14 and [45 擄/-45 擄] 14 laminated T700 carbon fiber composites was studied by acoustic emission monitoring experiment, and the strain process of the specimen was measured by grating fiber technique. The acoustic emission characteristics of each damage process are studied, and the relationship between the damage failure form and the acoustic emission signal is established. The results of experimental load, strain curve and damage morphology are compared with those of finite element analysis, and the analysis results and experimental results can be verified by each other. The acoustic emission signals of carbon fiber composites during in-plane shear process were analyzed by K-means clustering method, and the counting and duration were selected as the characteristic parameters. The pattern recognition of acoustic emission signal in shear process of T700 carbon fiber composites is analyzed, which provides an experimental basis for acoustic emission monitoring and prediction of damage failure of carbon fiber composites.
【學(xué)位授予單位】：東北石油大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2017
【分類號(hào)】：TB332;TQ342.742
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本文編號(hào)：2475189