复合材料头盔壳体用超薄层合板冲击后的压缩性能

使用[0°/0°/0°]T、[45°/0°/45°]T两种铺层角度将碳纤维经面缎纹织物、碳纤维平纹织物预浸料、不同面密度芳纶纬编双轴向织物(MBWK)三种增强材料混杂铺层,制备出厚度为1.30 mm的复合材料头盔壳体用超薄层合板。测试分析了层板冲击后的压缩性能,用C扫描超声波检测仪测试了层合板冲击损伤图像,使用Image Pro Plus图像分析软件计算出不同冲击条件下的超薄层合板冲击损伤面积,研究了增强体结构类型、铺层角度对超薄复合材料层合板冲击后压缩性能的影响。结果表明,使用铺层角度为[45°/0°/45°]T的增强体结构可抑制层板沿纤维方向的冲击损伤裂纹的扩展,但是冲击点损伤破坏严重;纬编双轴向织物的面密度越大,则层板冲击后的凹坑深度越小。与其他铺层结构相比,当铺层角度为[0°/0°/0°]T时底层为碳纤维预浸料、中间层纬编双轴向织物面密度为630 g/m2、面层为碳纤维经面缎纹织物的复合材料超薄层板的冲击损伤面积与凹坑深度均最小,分别为225.28 mm2、0.16 mm,其剩余冲击后压缩强度达到最大值97.43 MPa,压缩强度保持率75.72%。这种结构,具有优异的冲击后压缩性能。     

三维织造层间增强的纤维棒复合材料细观结构模型及力学性能有限元模拟

针对复合材料层间增强的需求,提出了一种三维织造层间增强的纤维棒复合材料几何结构,建立了0°/90°、45°/135°及0°/90°/45°/135°3种织造方案下的复合材料单胞有限元模型,该模型能较为真实地反映织造物内纤维束与纤维棒的交织特征。通过施加周期性位移边界条件,利用该模型采用有限元方法得到了3种织造方案下复合材料的等效弹性性能参数,讨论了复合材料弹性性能与织造方案和纱线填充因子的关系,分析了在单向拉伸载荷下3种织造方案单胞的细观应力场分布,制作了实体模型,进行了相关实验。结果表明:单胞有限元模型的模拟结果与实验结果吻合较好,织造复合材料各弹性常数对纱线填充因子变化的敏感度不同,不同织造方案的复合材料具有不同的力学性能特征,其主要影响因素为纤维束在复合材料内部的排列方式。给出了3种织造模型单胞的应力场分布,为三维织造层间增强的纤维棒复合材料的结构优化提供了依据。     

双轴向衬纱纬编玄武岩纤维复合材料弯曲性能

经纬纱和针织纱分别选用不同线密度的高模高强玄武岩纤维,以不同衬纱方式编织出机织针织复合(CWK)织物和多层双轴向纬编(MBWK)织物,并以其作为增强体,采用真空辅助树脂传递模塑工艺制备了玄武岩纤维/乙烯复合材料.对两种复合材料0°、90°和45°方向的弯曲性能进行测试,分析比较了弯曲应力-应变特征曲线及纱线强度.结果表明:两种复合材料具有较好的弯曲性能,0°和90°方向的弯曲性能均优于各自45°方向的,弯曲应力-应变曲线均表现出一定的塑性破坏特征;MBWK织物增强复合材料0°和90°方向的弯曲性能又分别高于CWK织物增强复合材料0°和90°方向的弯曲性能;复合材料中经纱和纬纱的屈曲程度不同,致使MBWK织物增强复合材料的比模量和纱线强度均高于CWK织物增强复合材料,两种复合材料的弯曲性能受不同衬纱方式的影响,而两种复合材料试样的弯曲破坏形态相近.研究结果为双轴向衬纱纬编玄武岩纤维复合材料的应用提供了参考.     

双轴向衬纱纬编玄武岩纤维复合材料弯曲性能

经纬纱和针织纱分别选用不同线密度的高模高强玄武岩纤维, 以不同衬纱方式编织出机织针织复合(CWK)织物和多层双轴向纬编(MBWK)织物, 并以其作为增强体, 采用真空辅助树脂传递模塑工艺制备了玄武岩纤维/乙烯复合材料。对两种复合材料0°、 90°和45°方向的弯曲性能进行测试, 分析比较了弯曲应力-应变特征曲线及纱线强度。结果表明: 两种复合材料具有较好的弯曲性能, 0°和90°方向的弯曲性能均优于各自45°方向的, 弯曲应力-应变曲线均表现出一定的塑性破坏特征; MBWK织物增强复合材料0°和90°方向的弯曲性能又分别高于CWK织物增强复合材料0°和90°方向的弯曲性能; 复合材料中经纱和纬纱的屈曲程度不同, 致使MBWK织物增强复合材料的比模量和纱线强度均高于CWK织物增强复合材料, 两种复合材料的弯曲性能受不同衬纱方式的影响, 而两种复合材料试样的弯曲破坏形态相近。研究结果为双轴向衬纱纬编玄武岩纤维复合材料的应用提供了参考。     

UHMWPE防弹复合材料正交试验设计与分析EI北大核心CSCD

铺层结构和成型工艺是影响超高分子量聚乙烯(ultra-high molecular weight Polyethylene,UHMWPE)纤维复合材料弹道防护性能的重要因素。为评估各因素对UHMWPE纤维复合材料防弹性能的影响程度,基于正交试验设计建立了铺层角度以及包括温度、压强、时间三个热压成型工艺条件下的4因素3水平正交表并进行了9组弹道极限试验。通过对试验结果进行极差和方差分析表明,各试验因素对弹道防护影响程度由大到小依次为铺层角度、成型时间、成型压强和成型温度。此外,研究发现:[(0°/90°)_(2)]_(2n)和[(-45°/45°)_(2)]_(2n)铺层复合材料弹道冲击吸能体现为多破坏模式协同耗能,而[(0°/90°)_(2)/(-45°/45°)_(2)]n准各向铺层复合材料的弹道冲击吸能体现为单一破坏模式耗能;综合考虑防弹性能和成本确定的最优组合为成型温度120℃、压强25 MPa、时间20 min,铺层角度[(0°/90°)_(2)]_(2n)。     

对位芳香族聚酰胺纤维/环氧树脂复合材料防弹性能及其破坏机制

为研究对位芳香族聚酰胺纤维/环氧树脂（Epoxy resin,EP）复合材料的防弹性能及其破坏机制,采用铅芯弹侵彻复合材料靶片。以对位芳香族聚酰胺纤维作增强纤维,EP作基体树脂,纳米SiO₂和聚乙烯醇缩丁醛（Polyvinyl butyral,PVB）作增韧剂,通过热压工艺制备单向（Unidirectional,UD）结构的对位芳香族聚酰胺纤维/EP复合材料靶片。研究单片纤维面密度、UD片材结构、射击角度和树脂改性对靶片防弹性能的影响;观察弹击实验后靶片的破坏形貌,分析靶片的破坏机制。研究结果表明:对位芳香族聚酰胺纤维/EP复合材料具有优异的防弹性能,随着单层纤维面密度的增大,靶片的防弹性能呈现整体上升、局部上下波动的变化趋势;铺层方式为0°/90°/0°/90°的四层单UD片材（4UD）结构的防弹性能优于铺层方式为0°/90°的两层单UD片材（2UD）结构;角度射击时,靶片的穿透比率更大,背衬凹陷深度（Back face signature,BFS）比率更小;PVB增韧改性EP提升了靶片的防弹性能;纤维拉伸变形破坏、片材分层和基体树脂碎裂是复合材料靶片主要的吸能方式。      

表面带金属层的复合材料层合板低速冲击数值模拟

使用Abaqus/Explicit建立表面带金属层的复合材料层合板和复合材料裸板低速冲击有限元模型,与已有文献对比验证结果的可靠性,研究结果对复合抗弹结构有很好的借鉴和参考价值.采用Johnson-Cook本构关系模拟铝合金和钛合金层的力学行为,选用Hashin准则对复合材料层内损伤进行失效判断,用二次应力准则来模拟粘结层Cohesive单元的层间失效.结果表明,相同铺层与冲击能量下,表面带铝合金层合板对内部纤维的保护性能优于表面带钛合金层合板,表面带钛合金层合板的抗冲击性能优于复合材料裸板;[§/0°/90°/0°/90°/0°]s铺层层合板的抗冲击性能优于[§/-45°/90°/0°/45°/-45°]s铺层层合板的抗冲击性能;在子弹刚冲破层合板与子弹完全离开层合板阶段,表面带铝合金层合板对子弹动能吸收率最大.     

UHMWPE波纹结构复合材料抗压及抗冲击性能研究

以超高分子量聚乙烯(UHMWPE)UD布为原料,采用模压成型工艺制备UHMWPE波纹结构复合材料。研究不同工艺下复合材料的界面强度、结合载荷-位移曲线及试样的损伤模式,分析不同铺层方式对试样压缩和冲击性能的影响。结果表明,UHMWPE波纹板吸能的主要方式是整体结构屈曲变形,[0°/90°]铺层数量的增多能够提高波纹板的整体承载能力,通过波纹板内部加入[45°/-45°]铺层可增加波纹板的吸能能力。     

不同铺层方式下连续玻璃纤维/聚丙烯复合材料波纹夹芯板的力学性能

制备了多种铺层方式的连续玻璃纤维/聚丙烯（GF/PP）复合材料波纹夹芯板,并研究了GF/PP复合材料波纹夹芯板的平压性能和弯曲性能。结果显示:面板相同时,增加芯板厚度可大大增加夹芯板整体的平压性能;芯板相同时,面板的铺层方式对夹芯板的平压性能有一定影响,且面板含有0°和90°铺层的波纹夹芯板具有最高的平压模量,为59.55 MPa,而单纯增加面板厚度对提升波纹夹芯板的平压性能影响不大;面板铺层方式对弯曲性能具有较大影响,面板为0°铺层的波纹夹芯板具有最高的横向弯曲模量,为783.66 MPa,面板为90°铺层的波纹夹芯板具有最高的纵向弯曲模量,为732.09 MPa;面板为单向铺层（0°或90°铺层）时,会使夹芯板另一方向（纵向或横向）的弯曲性能形成短板。      

复合材料汽车轮毂的成型工艺及性能研究

研究了不同冲击方向下复合材料的冲击力学性能,设计不同纤维布料裁剪方式并分析原材料的使用率,设计易于铺层操作以及产品脱模的三片式模具,优化热压罐成型工艺,并进行了车轮冲击测试。结果表明,冲击测试时的冲击方向对复合材料的冲击性能有较大影响,相较于垂直于铺层方向的冲击性能,冲击方向平行于铺层方向的复合材料冲击性能更高,产品铺层中应根据冲击工况进行优化铺层设计;采用合适的裁剪结构设计提高了操作便利性,并且使材料利用率达到83.8%,大大节约了材料成本;采用优化热压罐成型工艺制备的复合材料轮毂在冲击静载荷为600 kg的13°冲击测试中未出现断裂情况,满足汽车车轮冲击测试的装车要求。     

碳纤维增强聚酰亚胺树脂基复合材料MT300/KH420高温力学性能(I)——拉伸和层间剪切性能

研究了碳纤维增强聚酰亚胺树脂基复合材料MT300/KH420的高温力学性能, 重点揭示了MT300/KH420的[0°]₇、[0°]₁₄ 和[±45°/0°/90°/+45°/0°₂]_s层合板在常温~500 ℃的拉伸和层间剪切性能的变化规律。结果表明:在350 ℃以内,[0°]₇层合板拉伸强度随温度升高有所提高, 拉伸模量几乎不变, 在420 ℃时拉伸强度和模量均出现明显下降, 在500 ℃时分别保持在65%和83%以上, 表现出优异的高温拉伸性能。MT300/KH420的[0°]₁₄层合板层间剪切强度在常温~420 ℃随温度升高不断降低至52.8%, 在高温下呈现出黏弹效应, 且在420 ℃时最为明显。相比于单向层合板, [±45°/0°/90°/+45°/0°₂]_s多向层合板高温力学性能较为稳定, 且由纤维控制的纵向试件力学性能受温度影响较小。      

各向异性复合材料开孔板拉伸强度预测及模型验证

基于有限断裂力学方法建立了一种预测多向复合材料开孔板拉伸强度的通用和半经验模型。该模型同时采用基于应力形式的失效准则和基于能量形式的失效准则预测失效。模型仅需铺层弹性常数、无缺口层合板的强度以及0°铺层的断裂韧性等参数。基于线弹性断裂力学建立了多向复合材料层合板的断裂韧性与0°铺层断裂韧性之间的关系, 进而预测了任意铺层复合材料开孔板发生纤维主导拉伸失效时的强度。将模型预测结果与开孔板拉伸强度的试验数据进行了对比验证, 预测误差最大为9.7%, 与点应力和平均应力等方法的对比表明, 该模型的预测精度高于传统的特征长度方法。      

The effect of the measurement frequency on the elastic anisotropy of fibre laminates

Static tests and ultrasonic measurements (2.25 MHz) have been carried out on a series of composite laminates of glass fibres in a polypropylene matrix. A range of angle ply laminates were prepared for this study, with laminate angles θ of ±0, 10, 20, 30 and 40^∘. The high frequency measurements were made using the ultrasonic immersion technique, which allows the determination of a complete set of the elastic constants of a material. The relationship between the ultrasonically determined elastic constants of the angle ply laminates was found to be in excellent agreement with theoretical predictions, as previously validated for carbon fibre/epoxy angle ply laminates. A comparison between the ultrasonic and statically measured values was made for two of the angle ply laminates (θ = 0 and 20^∘). It was found that the static values were lower than those measured at ultrasonic frequency, particularly those constants that were more matrix dominated (for example the transverse moduli of the laminates). Measurements on a pure polypropylene sample at both testing frequencies confirmed that the change in matrix properties with frequency was the cause of this difference. The change in properties with test frequency is likely to be much larger in this system than in other composite materials because the glass transition temperature of polypropylene is close to ambient temperature. Dynamic mechanical tests (1 Hz) were carried out on a sample of pure polypropylene to assess this effect. We also give an appropriate method of estimating the dependence of glass transition temperature on frequency. The results for polypropylene are compared with those for other commonly used polymer matrix materials: epoxy resin, nylon and polyetheretherketone (PEEK): DMTA measurements were also made on these samples. The effect of test frequency on matrix properties, for the glass/PP laminates, was further investigated by examining the relationship of the Poisson's ratios with laminate angle using a mixture of ultrasonic experiments and theoretical predictions. Previously we have shown that the degree of anisotropy between the reinforcing fibre and the matrix phase is paramount in determining whether the material will show a negative Poisson's ratio at a critical laminate angle. The ultrasonic measurements carried out in this study on the glass/PP laminates showed a minimum in one of the Poisson's ratio at a laminate angle of 32°, but the value did not become negative. However, theoretical predictions showed that for a static frequency measurement (1 Hz), where the matrix is softer and hence the anisotropy of each laminate ply is higher, the laminate will show a negative Poisson's ratio with a minimum at a laminate angle of around 28°.     

Improvements in mechanical properties of a carbon fiber epoxy composite using nanotube science and technology

Carbon fiber reinforced epoxy composite laminates, with strategically incorporated fluorine functionalized carbon nanotubes (f-CNTs) at 0.2, 0.3 and 0.5 weight percent (wt.%), are studied for improvements in tensile strength and stiffness and durability under both tension–tension (R = +0.1) and tension–compression (R = −0.1) cyclic loadings, and then compared to the neat (0.0 wt.% CNTs) composite laminate material. To develop the nanocomposite laminates, a spraying technology was used to deposit nanotubes on both sides of each four-harness satin weave carbon fiber fabric piece for the 12 ply laminate lay up. For these experimental studies the carbon fiber reinforced epoxy laminates were fabricated using a heated vacuum assisted resin transfer molding (H-VARTM®) method followed by a 2 soak curing cycle. The f-CNTs toughened the epoxy resin-fiber interfaces to mitigate the evolution of fiber/fabric-matrix interfacial cracking and delamination under both static and cyclic loadings. As a consequence, significant improvements in the mechanical properties of tensile strength, stiffness and resistance to failure due to cyclic loadings resulted for this carbon fiber reinforced epoxy composite laminate.     

Evaluation of the interfacial properties of polypropylene composite laminates,reinforced with paper sheets

Laminates, composed of different papers and polypropylene (PP), were fabricated by a manual stacking and hot pressing. The laminates were characterized by mechanical testing and the results were compared to glass fiber reinforced PP. Furthermore, a detailed evaluation of the interfacial properties and the paper structures was carried out by means of data modeling via rule of mixtures (ROM), as well as electron microscope (SEM) analysis. For investigating the influence of the laminate’s composition on the water adsorption behavior, water diffusion coefficients were determined. As a result, laminates with a tensile modulus up to 6 GPa and a tensile strength of 80 MPa were obtained. The property changes of the papers upon processing were successfully modeled, revealing a significant increase of the paper’s mechanical properties after fiber embedding. In general, the obtained results indicate a high potential of paper as a suitable reinforcement material for low to middle strained applications.     

可收卷复合材料层板大变形弯曲性能研究

该文研究了玻璃纤维编织复合材料制成的可收卷层板在大变形条件下的弯曲静力性能和疲劳性能。通过弯曲静力试验得到了试验件在大变形条件下的应变和位移的关系;通过有限元模拟静力试验并与试验结果对照,确定了疲劳试验的载荷;研究了在大变形条件下不同铺层层板的弯曲疲劳寿命及失效模式和相同铺层层板的疲劳寿命曲线。结果表明:复合材料层板在大变形弯曲时具有明显的非线性行为,且(±45°)铺层层板弯曲疲劳性能明显优于(0°/90°)铺层层板;在最小应变和最大应变比不变的情况下,相同铺层层板的弯曲最大应变和对数疲劳寿命之间存在线性关系。     

Feasibility on fiber orientation detection of unidirectional CFRP composite laminates using one-sided pitch–catch ultrasonic technique

It is important to assess fiber orientation, material properties and part defect because strength and stiffness of composites depend on fiber orientation of CFRP (carbon fiber reinforced plastics). A one-sided pitch–catch setup was used in the detection and evaluation of ultrasonic wave behavior and fiber orientation in the unidirectional CFRP composite laminates. Two Rayleigh wave transducers were joined head-to-head and used in the pitch–catch mode on the surface of the composites. The pitch–catch signal was found to be more sensitive than normal incidence backwall echo of longitudinal wave to subtle flaw conditions in the composite. Especially, one-sided ultrasonic measurement was made with using a Rayleigh wave transducers and the Rayleigh ultrasonic waves were extensively characterized in the CFRP composite laminates. Also, a conventional scanner was used in an immersion tank for extracting fiber orientation information in the unidirectional laminate. Therefore, it is thought that the proposed method is useful to evaluate integrity of CFRP laminates.     

模压工艺对玻璃纤维增强聚丙烯复合材料层合板力学性能的影响

利用热模压工艺制备玻璃纤维增强聚丙烯（GF/PP）复合材料层合板,通过差示扫描量热（DSC）法试验分析,确定相变参数,运用ANSYS有限元分析,将复合材料热力学参数与温度的非线性关系定义到材料特性中,研究模压成型过程中温度场变化情况,为模压成型工艺制度的确立提供理论指导和依据。以压缩强度、层间剪切强度和冲击韧性作为力学性能评价指标,采用响应曲面法探讨和分析制备工艺对GF/PP复合材料层合板力学性能的影响,得到最优模压工艺制备参数,获得最高复合材料层合板力学性能,为GF/PP复合材料自动铺放奠定铺放工艺基础。试验结果表明:模压加热工艺参数对复合材料层合板力学性能的影响度（从大到小）依次为:热压温度、热压时间、热压压力。较优的模压加热工艺参数为:热压温度228℃、热压时间6 min、热压压力1.1 MPa,在此工艺条件下制备的GF/PP复合材料层合板,层间剪切强度为31.12 MPa,压缩强度为100.96 MPa,冲击韧性为2.27 kJ/cm2。      

Compression properties of z-pinned composite laminates

The effect of z-pinning on the in-plane compression properties and failure mechanisms of polymer laminates is experimentally studied in this paper. The reduction to the compression modulus, strength and fatigue performance of carbon/epoxy laminates with increasing volume content and diameter of pins is determined. The elastic modulus decreases at a quasi-linear rate with increasing pin content and pin diameter. Softening is caused by fiber waviness around the pins and reduced fiber volume content due to volumetric swelling of the laminate from the pins. A simple model is presented for calculating the compression modulus of pinned laminates that considers the softening effects of fiber waviness and fiber dilution. The compression strength and fatigue life also decrease with increasing volume content and diameter of the pins. The strength and fatigue properties are reduced by fiber kinking caused by fiber waviness around the pins and the reduced fiber content caused by swelling. The deterioration to the compression properties is also dependent on the fiber lay-up pattern of the laminate, with the magnitude of the loss in properties increasing with the percentage of 0° (load bearing) fibers in the laminate. The paper gives suggestions for minimizing the loss to the compression properties to laminates due to pinning.