基于Zinoviev理论的含孔复合材料层合板三维有限元渐进失效分析

建立了含孔复合材料层合板的三维有限元模型,以二维Zinovie理论为基础,结合改进的三维Hashin准则,对二维Zinoviev理论进行了简化和拓展,提出了适用于三维模型的刚度退化方案,完成了对层合板的渐进失效分析。从纤维失效、基体失效、分层失效三个方面讨论了层合板在拉伸载荷作用下的失效过程,并预测了层合板的拉伸极限强度及破坏模式。数值模拟结果与试验基本吻合,验证了所提出退化模型的正确性。     

三维机织空芯结构复合材料的研究

众所周知，二维织物增强的复合材料有层间强度差的问题，为从根本上提高其损伤害限和可靠性，就需要提高材料厚度方向的整体性，三维机织空芯预制件应运而生。本文通过大量理论研究与织造实践，论述了三维机织空芯织物的整体织造技术、结构设计及复合工艺，为批量化生产奠定了基础。     

玻璃纤维复合材料层合板冲击后的压缩强度

对不同厚度的二维编织环氧玻璃纤维层合板进行落锤冲击试验及冲击后压缩破坏试验,以研究低速冲击对复合材料层合板剩余压缩强度(CAI)的影响。用透光描影及热揭层方法对冲击损伤形式进行描述。讨论了损伤宽度、损伤面积与冲击能量及剩余压缩强度、模量间的关系,并建立有限元模型,采用开口等效及软化夹杂等分析方法对材料的冲击后压缩强度值进行估算。     

2.5维机织复合材料疲劳寿命预测

对2.5维机织复合材料进行了静力分析,在受拉伸载荷的情况下将其视为经纱层和纬纱层组合而成的层合板。以单向板疲劳寿命预测为基础,考虑到疲劳加载过程中刚度退化导致的应力重新分配,采用Miner理论对其拉-拉疲劳寿命进行预测,且对该方法进行了试验验证,为预测2.5维机织复合材料的疲劳寿命提供了一种途径。     

有拧紧力矩复合材料单钉接头疲劳寿命预测

通过对有拧紧力矩复合材料单钉接头疲劳加载过程应力分析及材料三维疲劳失效准则损伤判定,并结合建立的疲劳加载材料退化模型、材料性能退化方法及复合材料接头最终失效判据,建立了基于三维累积损伤分析的层合板接头疲劳载荷作用下寿命预测方法。最后,对拉-拉疲劳载荷作用下有拧紧力矩层合板接头的疲劳寿命及破坏模式进行了模拟分析,并与试验结果进行了对比,结果表明,建立的寿命预测方法能够很好地预测有拧紧力矩复合材料单钉接头的寿命以及破坏模式。     

三维机织空芯昨全材料的研究

众所周知，二维织物增强的复合材料有层间强度差的问题，为从根本上提高其损伤容限和可行性，就需要最度方向的整体性，三维机织空芯预制件应运而生。本文通过大量理论研究与织造实践，论述了三维机织空芯织物的整体织造技术、结构设计及复合工艺，为批量化生产奠定了基础。     

碳纤维复合材料铆胶连接强度研究

采用有限元分析比较了碳纤维复合材料层合板之间铆胶连接的主要承力方式，并对铆胶连接方式做了静力拉伸试验、盐雾试验与疲劳试验，结果表明：金属-层合板铆胶连接的拉剪强度总是高于层合板-层合板铆胶连接拉剪强度；金属-层合板铆胶连接的拉剪强度高于层合板-层合板的拉剪强度12.6%；盐雾试验结果与静力拉伸试验结果倾向性一致，整体来说层合板-层合板铆胶连接受盐雾条件影响较小；疲劳试验结果证明铆胶连接不易发生疲劳损坏。     

碳纤维复合材料低温下螺栓连接疲劳研究

本文主要围绕碳纤维复合材料(CFRP)与2024Al的连接件,研究低温环境下螺栓连接的拉-拉疲劳问题。首先进行不同环境下的拉伸实验,从中获得最大静力载荷,并通过静载破坏曲线探究不同温度下异质材料连接层合板接头的损伤过程,通过观察不同温度下的拉伸破坏现象,对比复合材料层合板纤维分层与撕裂程度,以此为依据研究低温环境对异质材料螺栓连接疲劳的影响,选用不同温度分组的层合板接头分别在各自85%、80%、75%的最大静载条件下进行常温与低温疲劳实验,实验结果拟合常温与低温下的S-N曲线。结果表明,在其他实验条件相同时,低温环境下层合板接头拉伸破坏强度相比于常温环境增强。分析疲劳曲线得出低温环境下层合板接头受疲劳载荷能力更强。     

玻璃纤维二维平纹编织复合材料高温弯曲力学行为研究

对玻璃纤维2维平纹编织复合材料在6个不同温度下的弯曲性能进行了实验测试,研究了温度对编织复合材料层合板的载荷-挠度曲线、弯曲强度、弯曲模量和失效模式的影响。结果表明:在三点弯曲载荷作用下,2维编织复合材料层合板跨中发生了局部纤维束屈曲失效和基体的开裂与分层失效。温度对玻璃纤维复合材料的力学性能和失效形式产生了重要影响。在高温环境中玻璃纤维2维平纹编织复合材料的弯曲力学性能迅速下降,当试验温度从20℃升高至115℃时,层合板的弯曲强度和模量分别下降了91%和66%。随着温度的升高,2维编织复合材料层合板的弯曲失效变形行为也发生了转变,逐渐由脆性破坏转变为塑性变形失效。     

应用ANSYS的复合材料层合板静强度预测

复合材料层合板的静强度预测对于层合板设计和应用都具有重要的意义。为了提高预测的有效性,减少实验成本,在基于单层板理论的逐渐累积损伤的静强度预测方法的基础上,提出了用于二维机织复合材料静强度的预测方法。首先,以ANSYS有限元分析软件作为平台,利用其自带的APDL参数化语言建立有限元模型,并将铺层方式设定为[(0,90)/(±45)/(0,90)/(±45)/(0,90)]s,然后经过ANSYS软件的计算,得到最终的预测结果,最后制作该铺层方式的复合材料层合板并作拉伸实验,得到其实验强度,通过对比预测结果和实验结果验证了该预测方法的有效性。     

Review of the Mechanical Properties of a 3D Woven Composite and Its Applications

Owing to their complex structural characteristics, 3D woven composites display different mechanical properties and failure modes from traditional composite laminates. The relations between the weaving geometry and main mechanical properties of composites are obtained by studying the internal structures of 3D woven textile. This paper reviews the research on the mechanical behavior such as tension, compression, shear, flexural, and impact properties, and analytical models of 3D woven polymer matrix composites mainly in four major inner structures and discusses the development of mechanical properties and applications of 3D woven fabrics and suggests further studies on aero industry.     

三维碳纤维机织物增强PMR型聚酰亚胺复合材料的成型与性能研究

使用PMR型聚酰亚胺预聚物溶液和三维碳纤维机织物预制件制作了三维机织物增强PMR型聚酰亚胺复合材料。通过对制备的PMR型聚酰亚胺预聚物的红外特征光谱(FT-IR)的分析和熔融流变性能的测试,设计优化了一种"两步浸渍热压法"制作三维机织物增强PMR型聚酰亚胺基复合材料,对复合材料的内部结构、热性能以及力学性能进行了表征与测试。     

微波固化成型三维中空复合材料结构的力学性能

为了改善三维中空复合材料结构微波固化成型的固化均匀性,提出了添加外部导热附加模具和内部微波吸收剂两种不同的方法。通过试验研究了附加模具的材料、厚度以及微波吸收剂种类和含量对三维中空复合材料结构力学性能的影响。结果表明,结构的平压失效模式包括芯柱失稳和压溃,剪切失效模式为芯材剪切失效和界面脱粘,短梁弯曲的失效模式为面板/芯材界面的脱粘后屈曲破坏。相比于未添加附加模具,AlN和Al_2O_3陶瓷均可以提高结构的力学性能,但AlN的增强效果更显著。AlN模具厚度的增加不利于结构的力学性能,模具厚度从0.5 mm增加到1.5 mm时,结构的平压、剪切和芯材剪切强度均随之降低。微波吸收剂的添加均可提高中空结构的力学性能,其中剪切和芯材剪切强度随着石墨含量的增加而增加,平压强度随着石墨含量的增加先增加后降低,而Fe_3O_4含量变化则对结构力学性能的影响不显著。     

三维机织复合材料力学性能分析与研究

通过对三维机织复合材料几何细观结构的研究,分析了三维机织复合材料的力学性能,采用椭圆形纤维束截面假设并结合实际的纱线形态建立了一种新的三维机织复合材料力学模型,对三维机织复合材料的拉伸、压缩和层间剪切强度进行了理论分析,并与实验结果进行了对比,验证了力学模型的正确性。     

三维织物构件的力学性能探讨

探讨了用芳纶织制的三维机织物结构,并对该三维织物构成的简支梁进行力学性能测试,证明45°方向和90°方向接结纱共存的织物组成的简支梁的力学性能优于仅含90°方向接结纱的织物组成的简支梁。     

Tensile Properties of Ceramic Matrix Fiber Composites

The mechanical properties of various 2D ceramic matrix fiber composites were characterized by tension testing, using the gripping and alignment techniques development in this work. The woven fabric composites used for the test had the basic combinations of Al₂O₃ Fabric/Al₂O₃, SiC fabric/SiC, and SiC minofilament uniweave fabric/SiC. Tension testing was performed with strain gauge and acoustic emission instrumentation to identify the first-matrix cracking stress and assure a valid alignment. The peak tensile stresses of these laminate composites were about one-third of the flexural strengts. The SiC monofilament uniweave fabric (14 vol%)/SiC composites showed a relatively high peak stress of 370 MPa in tension testing.     

机织/针织混合铺层对复合材料力学性能的影响

为使纺织复合材料同时具有机织结构复合材料和针织结构复合材料的综合力学性能,通过混合铺层方式制备机织/针织混合结构复合材料。以芳纶机织平纹织物和针织罗纹织物为增强体,以环氧树脂为基体,调整复合材料中增强体的铺层顺序,利用真空辅助成型技术制备四层层压机织/针织混合结构复合材料。通过对复合材料拉伸性能、弯曲性能和冲击性能的测试,分析混合铺层和铺层顺序对芳纶环氧树脂复合材料力学性能的影响。结果表明,混合铺层和铺层顺序对芳纶环氧树脂复合材料的弯曲强度和冲击强度有较大影响,特别是对罗纹结构复合材料纬向弯曲强度和冲击强度的改善。当采用相同铺层方式,罗纹织物为受力面时,机织/针织混合结构复合材料具有较大弯曲强度和冲击强度。     

Energy absorptions and failure modes of 3D orthogonal hybrid woven composite struck by flat‐ended rod

Three‐dimensional (3D) orthogonal woven composite has high stiffness, strength, and energy absorption capacity along X, Y, and Z directions because there are no crimps in yarn. This paper presents mechanical behaviors and energy absorptions of the 3D orthogonal hybrid woven composite under transverse impact and quasi‐static loading by flat‐ended rod. The failure load and energy absorption of the composite increase with the increase in loading rate. The damage morphology of the composite coupon manifests the compression failure in the front side and tension failure in rear side. There are no delaminations in the composite coupons for both quasi‐static and impact loading for the existence of Z‐yarn in fabric structure. This phenomenon manifests the potential application of the 3D orthogonal woven composite to impact resistance areas. POLYM. COMPOS., 27: 410–416, 2006. © 2006 Society of Plastics Engineers     

三维机织热塑性复合材料的拉伸性能测试与分析

本研究对三维机织热塑性复合材料的拉伸力学性能进行了测试,分析了三维机织热塑性复合材料预型件的结构(纱线的直径、三维机织物的结构)、预型件的预拉伸工艺(经纱和接结经的伸直程度)、复合成型工艺(成型压力)对复合材料的力学性能的影响.     

Drape behavior of 3D woven glass‐epoxy composites

This article deals with the drapability of 3D woven glass fabrics for composite applications. The study focuses on forming a 3D fabric over the mold, the result is a preform, which generally is then injected with a polymer matrix by so called Liquid Composite Molding (LCM) technique. When draping pre–impregnated composites, the fabric is embedded in the epoxy resin as matrix material. Various drape models for dry and pre‐impregnated fabrics have been proposed in the work. Solidworks and ANSYS are the software used for modeling and simulation of 3D woven fabric composites. Given the linear density (tex) and density of E‐glass fiber, the radius of the yarn was calculated. So far the cross section of yarn is assumed to be perfectly circular in shape, keeping the perimeter of yarn constant the circular cross section was deformed into a race track shape which is a much more practical and realistic shape of a yarn cross section. After calculating all the required dimensions, all the three 3D woven structures namely angle interlock, warp interlock and orthogonal were developed in solidworks. All the parameters like total number of warp and weft yarn per unit distance and thickness of the fabric were kept constant in all three structures. The analysis is based on first principles and the parameters of yarn and fabric construction. Results obtained through simulation are reported. These are validated with experimental composite samples. The model used to predict drapability of 3D woven glass‐epoxy composite gives good results. Orthogonal structure proves to be the best as far as resistance to deformation is concerned. However, if a relatively more flexible and formable prepreg is desired, it is advisable to use angle interlock or warp interlock structures. Warp interlock 3D structure proves most beneficial for draping on a mold. POLYM. COMPOS., 37:472–480, 2016. © 2014 Society of Plastics Engineers