国产PEEK为基体的复合材料成型工艺研究

本文论述了用热压法成型热塑性树脂PEEK和碳织物或玻璃织物复合材料的工艺研究,表明复合材料的质量与温度、压力和时间等条件有关。通过流变性能试验,计算表观流动活化能和在同样剪速下熔体相差40℃的粘度,考察了PEEK对温度的依存性。用超声C-扫描的结果表征工艺参数的变化,表明该方法有很好的选择性,较其他方法敏感。     

碳纤维增强热塑性树脂复合材料

扩大碳纤维复合材料的应用研究势在必行。特别是扩大碳纤维增强热塑性树脂复合材料(CFRTP)在民用工业中的应用尤为重要。如果说航天航空工业是碳纤维复合材料发展的推动力,那么民用工业则是它长期稳定发展的经济基础。换言之,宇航工业的用量毕竟有限,大量的市场仍需在潜力无限的民用工业中开拓。作为复合材料的基体树脂有两大类:一类是热固性树脂(TS),另一类是热塑性树脂(TP)。TP 为线型分子链,由两官能团     

连续碳纤维复合材料热压成型工艺条件优化研究

以连续碳纤维为增强体,以聚酰胺(PA)为基体,运用平板硫化机热压成型的方法制备连续碳纤维增强热塑性复合材料。对热压温度、热压压力、热压时间和保温时间等成型工艺参数进行考察,通过正交试验设计,研究热压成型工艺参数对复合材料力学性能的影响并分析各参数的影响程度,确定了较优的生产工艺条件,从而具备制得高性能碳纤维复合材料的热压成型工艺条件。     

碳纤维增强热塑性聚酰亚胺及其复合材料

采用双螺杆共混挤出法,在热塑性聚酰亚胺(TPI)树脂中添加碳纤维(CF)进行复合增强,实验研究了碳纤维种类、加入量及成型方法对复合材料力学性能的影响.结果表明:碳纤维的加入能显著提高材料的常温和高温力学强度,并与碳纤维种类有关;复合材料的拉伸和弯曲强度均随着碳纤维加入量的增大而升高;相对于模压成型方法,注塑成型可获得更高强度的复合材料.由扫描电镜(SEM)观察到的材料拉伸和弯曲断面的微结构形貌,初步探讨了碳纤维的增强机理.     

基于非正交本构模型的热塑性机织物预浸料宽温域赋形褶皱缺陷仿真方法

热塑性复合材料预制体的赋形质量直接影响结构件的制造质量。由于热塑性基体具有较高的熔融温度和黏度，赋形工艺温度设计不合理会导致褶皱等赋形缺陷，给热塑性复合材料结构高质量成型带来了挑战。现有的热塑性预浸料热成型研究主要基于连续介质力学、离散元、半离散元法，通过建立多机制耦合的本构模型分析热塑性预浸料的各向异性大变形行为，未充分考虑工艺调控对赋形宏观变形过程中褶皱缺陷的影响。发展了一种热塑性预浸料宽温域赋形褶皱缺陷仿真方法。通过表征热塑性机织物预浸料在不同温度、载荷下的力学性能，获取宽温域热塑性预浸料本构参数，基于非正交本构模型，提出了温度对热塑性预浸料赋形褶皱缺陷的作用规律，揭示了赋形过程中宽温域褶皱缺陷的变形机制，获得了赋形温度优化调控方案。研究结果表明：褶皱缺陷的萌生和演化过程由不同温度下的面内剪切和压缩变形行为共同影响，预浸料的褶皱缺陷变形程度随温度的增加而减弱，非正交本构模型的模拟结果与实验结果基本一致。     

制备工艺对单向连续碳纤维增强聚醚砜复合材料层间结合强度的影响

采用溶液浸渍和热压成型制备了以聚醚酚为基体的单向连续碳纤维增强复合材料,研究了不同树脂浓度和热压工艺参数下复合材料的层间剪切强度。结果表明:成型温度高的复合材料具有较高的层间剪切强度,适当延长保温时间能够大幅度提高复合材料的性能。扫描电镜和热重分析表明树脂基体与碳纤维之间结合紧密,不同树脂含量的复合材料在热压成型过程中,界面处有不同的作用机理。     

料浆对熔渗工艺制备碳纤维织物增强碳化硅复合材料的影响

针对航空发动机热端部件复杂结构存在的陶瓷基复合材料成型难度大的问题,以碳纤维织物为增强体,以有无添加粉体的两种树脂料浆为研究对象,开展料浆-熔渗工艺制备碳纤维织物增强碳化硅复合材料技术研究,探索两种料浆的注浆成型及熔渗工艺适应性,并对获得的复合材料基本性能进行表征.结果显示:有无添加粉体的两种料浆的黏度适中,在注浆工艺温度下具有3～5h以上的注浆工艺窗口,通过注浆成型工艺均可获得少孔隙、质量均匀的树脂基复合材料;无粉体和有粉体的料桨固化物在900℃炭化后,孔隙率分别为39.6％和31.3％,残炭率分别为24％和76％,平均孔径分别为0.068μm和0.069μm,能够满足熔渗工艺的要求;采用添加粉体的料浆制备的碳纤维织物增强碳化硅复合材料具有更低的气孔率(3.54％)和更高的弯曲强度(162 MPa),满足航空发动机静止部件的应用要求.     

PET缝编碳纤维织物冷等离子体处理对RTM成型浸润性的影响

RTM工艺成型过程中树脂对纤维增强体的浸润是重要的一环,浸润不好将导致RTM成型复合材料中产生缺陷,这将降低复合材料的界面性能。本文作者采用冷等离子体技术对PET缝编碳纤维织物进行表面处理,并采用AFM对处理前后的碳纤维表面形貌进行了分析。实验结果表明:冷等离子体处理可以使碳纤维表面活性提高,从而改善RTM工艺成型过程树脂对PET缝编碳纤维织物的浸润性,进而改善RTM成型复合材料的界面性能。     

新型热塑性复合材料细观力学与宏观性能的研究

碳纤维增强杂萘联苯聚醚酮(CF/PPEK)和碳纤维增强杂萘联苯聚醚砜(CF/PPES)是一种新型高性能热塑性复合材料,制备方法和力学性能的研究是使其得到广泛应用的基础.本工作研究了两种复合材料的预浸热压成型工艺,对制备的单向复合材料进行了力学性能实验研究,并基于复合材料细观结构周期性假设,建立了一种细观力学模型.该模型建立起了宏、细观场量的联系,实验及理论计算结果表明该模型能够较好的预测此种复合材料的宏观弹性性能.     

碳纤维编织复合材料冲压成形实验与仿真分析

编织复合材料成形由双曲率曲面构成的复杂结构件时,会导致复杂的纤维重新排布和重新取向,从而影响最终成形件的力学性能。基于纤维增强连续介质力学理论,作者以前提出了一种简单实用的超弹性模型来描述编织复合材料在成形过程中的非线性各向异性力学行为。利用冲压工艺为树脂传递模塑法提供碳纤维编织复合材料预成形件,研究了碳纤维编织复合材料在冲压成形带有双曲率曲面的结构件时的纤维重新排布和重新取向。碳纤维编织布被剪成纱线分别与模具矩形边成0和45°两种样式。利用所提出的模型对实验进行模拟并与实验结果进行对比发现,预测的纤维局部剪切角和边界纤维缩进量与实验结果吻合很好。这一研究对编织复合材料成形的数值预测与结构设计有着重要的意义。     

Intra/inter-ply shear behaviors of continuous fiber reinforced thermoplastic composites in thermoforming processes

The thermoforming of continuous fiber reinforced thermoplastic (CFRTP) composite panels generally involves significant in-plane shear deformation. In the present work, the in-plane shear behavior of woven thermoplastic composites (Carbon/Polyphenylene Sulfide) over a range of processing temperatures is studied by bias-test experiments at different velocities. The experimental data of force versus displacement and force versus shear strain are presented for different extension velocities and temperatures. A thermo-visco-elastic model for numerical simulations of woven thermoplastic composite forming is proposed considering the influences of temperature and of strain rate. We applied a large displacement three-dimensional cohesive element with eight nodes which has been used for crack analysis in fracture mechanics by other authors, to investigate the inter-ply shear mechanism of woven thermoplastic composites. Applying three-dimensional cohesive elements, multi-plies forming simulations are performed to show inter-ply slip behaviors at different temperatures. The proposed models can be useful to predict from the properties of reinforcement and resin the intra/inter-ply shear behaviors of woven thermoplastic composites at high temperatures if experimental characterization of composite laminate behaviors is difficult to conduct.     

A friction model for thermostamping commingled glass–polypropylene woven fabrics

The effects of processing parameters on the friction coefficient between commingled glass–polypropylene plain-weave fabric composites (Twintex^®) and the steel tool during thermostamping processes were investigated. The investigation focused on the effects of fabric velocity, normal force and resin viscosity under conditions similar to those in thermostamping processes. The effect of resin viscosity on the resulting friction coefficient was evaluated through changes in tool temperature and initial fabric temperature. The results from these experiments could be related to trends predicted by Stribeck-curve theory. Based on the effects of those parameters and the Stribeck-curve theory, an empirical friction model was developed and incorporated into ABAQUS as a user-defined friction subroutine. This paper describes the development of that friction model for use in finite element models of the thermostamping process. It also discusses the results of a parametric study conducted using the friction model with a finite element model of the thermostamping process. These results show the importance of properly accounting for changes in friction at the metal–fabric interface in numerical simulations of the thermostamping process.     

碳纤维增强聚醚醚酮复合材料研究进展

近年来,碳纤维增强热塑性复合材料（CFRTP）,尤其是碳纤维/聚醚醚酮（CF/PEEK）复合材料以其优异的综合性能受到了大量关注。高性能碳纤维/聚醚醚酮复合材料具有强度大、韧性好、使用温度高等诸多优点,在航空航天、机械、电气、汽车工业和生物工程等领域得到了广泛的应用。针对近年的研究热点,对碳纤维/聚醚醚酮复合材料在界面性能、力学性能、生物相容性、成型工艺、失效机理等方面的研究进展进行了综述,为材料的制备技术研究及产业化应用奠定基础。      

考虑双拉耦合的复合材料编织物各向异性超弹性本构模型

为了准确描述复合材料编织物的各向异性力学特性,首先,基于纤维增强复合材料连续介质力学理论提出了一种考虑纤维双拉耦合的复合材料编织物各向异性超弹性本构模型,该模型中单位体积的应变能被解耦为便于参数识别的纤维拉伸变形能、双拉耦合引起的挤压变形能和纤维间角度变化产生的剪切变形能;然后,给出了模型参数的确定方法,并通过拟合单轴拉伸、双轴拉伸和镜框剪切实验数据得到了本构模型参数;最后,利用该模型对双轴拉伸和镜框剪切实验进行了数值仿真,并将模拟结果与实验结果对比分析。结果表明:提出的本构模型适用于表征复合材料编织物在成型过程中由于大变形引起的非线性各向异性力学行为。所得结论表明提出的本构模型具有简单、实用的优点,且材料参数容易确定,可为复合材料编织物成型的数值模拟和工艺优化奠定理论基础。      

碳纤维织物力学性能和冲压成形实验研究

在实际成形过程中,碳纤维复合材料往往处于复杂的应力状态,开展近于真实载荷环境下的力学试验分析,能够更准确地认识实际应用中材料的成形性能和变形机理.为获得碳纤维织物的基本力学特性,设计了平纹碳纤维织物拉伸试样及成形试样,进行了单轴拉伸、双轴拉伸、镜框剪切试验和方盒冲压成形实验研究,对比了不同双拉比及纱线取向对力学性能及成形性能的影响.研究结果表明:碳纤维织物具有高度的非线性、各向异性和双拉耦合特性,即经纬向纤维的力学性能会相互影响;剪切变形是成形过程中的主要变形模式,当剪切角达到临界锁死角时,织物发生起皱现象;同种织物不同纱线取向试样表现出不同的成形性能,因此可以根据零件几何形状选择合适纤维取向的织物,从而减少缺陷,优化成形零件的力学性能.研究结果为后续建立碳纤维织物本构模型和成形仿真奠定了基础.     

Design of an apparatus for measuring tool/fabric and fabric/fabric friction of woven-fabric composites during the thermostamping process

The thermostamping of prepreg woven fabrics shows promise as a low-cost high-volume manufacturing process for composite parts. One concern associated with the process is the unwanted formation of defects in the form of fabric wrinkling. This wrinkling can be prevented during the thermostamping process by inducing in-plane forces through the use of one or more metal binder rings. However, if the in-plane forces are too low, then the fabric may wrinkle as the fabric conforms to the shape of the punch, and conversely, if the in-plane forces are too high, then the yarns in the fabric can separate and the fabric may tear and yarns can break. The in-plane forces are a result of the friction between the fabric and the metal binder rings. As the fabric slides over the surfaces of the punch and die, further friction is induced between the metal tooling and the fabric part. In addition, most composite parts consist of multiple layers, and therefore as the fabric is drawn into the die adjacent layers of fabric may slide relative to one another. Thus, the friction at the tool/fabric interface and the interlaminar friction must be understood and quantified to predict part quality as a function of the processing parameters. In this paper, the design and implementation of a load-control test apparatus used to measure the friction between the tool and the fabric and between adjacent layers of fabric during a composite forming process is presented.     

Experimental and Numerical Simulation Analysis of Typical Carbon Woven Fabric/Epoxy Laminates Subjected to Lightning Strike

To clarify the evolution of damage for typical carbon woven fabric/epoxy laminates exposed to lightning strike, artificial lightning testing on carbon woven fabric/epoxy laminates were conducted, damage was assessed using visual inspection and damage peeling approaches. Relationships between damage size and action integral were also elucidated. Results showed that damage appearance of carbon woven fabric/epoxy laminate presents circular distribution, and center of the circle located at the lightning attachment point approximately, there exist no damage projected area dislocations for different layers, visual damage territory represents maximum damage scope; visible damage can be categorized into five modes: resin ablation, fiber fracture and sublimation, delamination, ablation scallops and block-shaped ply-lift; delamination damage due to resin pyrolysis and internal pressure exist obvious distinguish; project area of total damage is linear with action integral for the same type specimens, that of resin ablation damage is linear with action integral, but no correlation with specimen type, for all specimens, damage depth is linear with logarithm of action integral. The coupled thermal–electrical model constructed is capable to simulate the ablation damage for carbon woven fabric/epoxy laminates exposed to simulated lightning current through experimental verification.     

Fractographical analysis on the mode II delamination in woven carbon fiber reinforced epoxy composites

Mode II delamination phenomena of woven fabric carbon/epoxy composites were investigated by scanning electron microscopy. End notch flexural (ENF) test was used to examine the mode II delamination. Woven fabric composites showed two peculiar crack propagation patterns due to the complexity of woven geometry. In warp yarn region, crack propagated with forming a shear band and breaking the fiber/matrix interface. In fill yarn region, however, no shear band was observed. Considering these crack patterns, matrix shear property and fiber/matrix interfacial strength played an important role in enhancing the delamination properties of woven fabric carbon/epoxy composites. Due to the woven geometry, matrix rich positions, which are interstitial and undulated region, were formed in woven carbon/epoxy composite. In these regions, matrix fracture and complex crack path were mainly observed.     

Numerical and Experimental Investigations on Deep Drawing of G1151 Carbon Fiber Woven Composites

This study proposes to simulate the deep drawing on carbon woven composites in order to reduce the manufacturing cost and waste of composite material during the stamping process, The multi-scale anisotropic approach of woven composite was used to develop a finite element model for simulating the orientation of fibers accurately and predicting the deformation of composite during mechanical tests and forming process. The proposed experimental investigation for bias test and hemispherical deep drawing process is investigated in the G1151 Interlock. The mechanical properties of carbon fiber have great influence on the deformation of carbon fiber composites. In this study, shear angle–displacement curves and shear load–shear angle curves were obtained from a bias extension test. Deep drawing experiments and simulation were conducted, and the shear load–displacement curves under different forming depths and shear angle–displacement curves were obtained. The results showed that the compression and shear between fibers bundles were the main deformation mechanism of carbon fiber woven composite, as well as the maximum shear angle for the composites with G1151 woven fiber was 58°. In addition, during the drawing process, it has been found that the forming depth has a significant influence on the drawing force. It increases rapidly with the increasing of forming depth. In this approach the suitable forming depth deep drawing of the sheet carbon fiber woven composite was approximately 45 mm.     

Characterization of the tool/fabric and fabric/fabric friction for woven-fabric composites during the thermostamping process

The dynamic coefficients of friction for Twintex® commingled glass-polypropylene balanced plain-weave and unbalanced twill-weave fabrics at the tool/fabric and fabric/fabric interfaces during the composite thermostamping process are characterized. The effects of fabric velocity and pressure on the coefficients of friction under conditions similar to those during the thermostamping process are studied. A phenomenological friction model accounting for pressure and velocity dependence is developed based on the experimental results and implemented into the commercial finite element codes ABAQUS/Explicit and LS-DYNA via user-defined subroutines. The mechanical behavior of the fabric is modeled using a mesoscopic approach. The friction subroutines are validated with a finite element model of the experimental friction test. The forming of a hemispherical dome is simulated using ABAQUS and LS-DYNA. Punch forces and yarn stresses are compared between variable friction and constant friction models, and the simulation results justify the necessity for a variable friction model to accurately predict part quality.