本文選題：復(fù)合材料層合板 + 三維漸進損傷��； 參考：《鄭州大學(xué)》2015年碩士論文

【摘要】：先進復(fù)合材料因其優(yōu)良的特性,諸如良好的比強度和比剛度、良好的耐腐蝕性能和良好的抗疲勞能力等,在航空航天工業(yè)中得到了廣泛的應(yīng)用。隨著設(shè)計方法的不斷完善和制造工藝的日益改善,復(fù)合材料的性能得到了大幅度提高,并在成本方面開始與傳統(tǒng)的金屬材料相競爭。鑒于此種情況,復(fù)合材料結(jié)構(gòu)修理和損傷探測技術(shù)已成為復(fù)合材料技術(shù)研究的重要方向。本文主要研究了飛機復(fù)合材料貼片修補設(shè)計的分析方法。首先,本文建立了復(fù)合材料層合板漸進損傷分析的三維有限元模型。借助有限元軟件ANSYS的二次開發(fā)語言(APDL),編寫三維Hashin準(zhǔn)則作為失效判斷準(zhǔn)則,分別考慮了基體開裂、基體纖維剪切、分層和纖維斷裂四種單元破壞形式,退化準(zhǔn)則采用固定的材料剛度折減系數(shù)。有限元計算結(jié)果與試驗數(shù)據(jù)相吻合,驗證了本文建立的復(fù)合材料三維漸進損傷模型的有效性。其次,本文分別建立了基于連續(xù)介質(zhì)損傷力學(xué)和最大剪應(yīng)力理論的膠層有限元模型。假設(shè)膠層含各向同性損傷,分別采用兩種膠層模型進行有分析計算,通過比較計算結(jié)果和試驗數(shù)據(jù)的吻合程度,確定兩種模型均有較高的可靠性,本文采用膠層基于連續(xù)介質(zhì)損傷力學(xué)的貼片修補模型。第三,分析了復(fù)合材料貼片修理模型在均布拉伸載荷下的應(yīng)力分布情況,總結(jié)得到貼片修補模型的高應(yīng)力集中區(qū)域。第四,建立基于三維漸進損傷理論的復(fù)合材料貼片修補模型,分析了補片半徑不同時模型的極限載荷和失效擴展情況,總結(jié)得到三種貼片修補結(jié)構(gòu)的整體失效模式,并分析其產(chǎn)生的原因。同時,分析了補片厚度、補片形狀和補片材料對模型修補效果的影響,確定修補效率最高的補片厚度、補片形狀及補片材料等參數(shù)。最后,考慮膠層的參數(shù)(膠層厚度、膠粘劑種類)對貼片修補模型極限載荷和失效擴展情況的影響,確定修補效果最佳的膠層參數(shù)。
[Abstract]:Advanced composite materials have been widely used in aerospace industry because of their excellent properties, such as good specific strength and stiffness, good corrosion resistance and fatigue resistance. With the continuous improvement of design method and manufacturing process, the properties of composite materials have been greatly improved, and the cost of the composites has begun to compete with the traditional metal materials. In view of this situation, composite structure repair and damage detection technology has become an important research direction of composite technology. This paper mainly studies the analysis method of aircraft composite patch repair design. Firstly, a three-dimensional finite element model for progressive damage analysis of composite laminated plates is established. With the help of the secondary development language of finite element software ANSYS, three dimensional Hashin criterion is compiled as the failure judgment criterion. The failure modes of matrix cracking, matrix fiber shear, delamination and fiber fracture are considered, respectively. The degradation criterion adopts a fixed material stiffness reduction coefficient. The results of finite element method are in agreement with the experimental data, which verifies the validity of the 3D progressive damage model of composite materials established in this paper. Secondly, the finite element model of rubber layer based on the theory of continuum damage mechanics and maximum shear stress is established in this paper. Assuming that the rubber layer contains isotropic damage, two kinds of rubber layer models are used to carry out the analysis and calculation respectively. By comparing the calculated results with the experimental data, it is determined that the two models have high reliability. In this paper, a patch repair model based on continuum damage mechanics is used. Thirdly, the stress distribution of the composite patch repair model under uniform tensile load is analyzed, and the high stress concentration region of the patch repair model is obtained. Fourthly, a composite patch repair model based on 3D progressive damage theory is established, and the ultimate load and failure expansion of the model with different radius are analyzed, and the overall failure modes of three kinds of patch repair structures are summarized. The causes of its occurrence are analyzed. At the same time, the effects of patch thickness, patch shape and patch material on the effect of model repair were analyzed, and the parameters such as patch thickness, patch shape and patch material, which had the highest repair efficiency, were determined. Finally, considering the influence of the rubber layer parameters (thickness of adhesive layer, adhesive type) on the ultimate load and failure expansion of the patch repair model, the parameters of the best repair effect are determined.
【學(xué)位授予單位】：鄭州大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2015
【分類號】：TB33

【參考文獻】

相關(guān)期刊論文 前1條

1 孫晶晶;張曉晶;宮占峰;汪海;;復(fù)合材料帽型筋條脫粘的失效機理分析[J];航空學(xué)報;2013年07期

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本文編號：1859921