弹性纳米粒子改性中温固化环氧树脂复合材料的研究

采用弹性纳米粒子改性3233中温固化阻燃环氧树脂,制备3233/EW250F玻璃纤维布预浸料,并测试树脂、预浸料和复合材料性能.结果表明,弹性纳米粒子不会降低复合材料的玻璃化转变温度,能提高自粘性树脂-3233树脂预浸料的滚筒剥离强度,有利于树脂预浸料的自粘性,树脂具有韧性,抗冲击性能好,其CCF300碳纤维复合材料冲...     

薄型碳纤维织物预浸料及其复合材料研究

采用国产1k T300级薄型碳纤维织物和中温固化高性能树脂制备预浸料。测试了该预浸料及其复合材料性能,并与国产3k T300级碳纤维织物预浸料及其复合材料性能进行对比。研究结果表明:国产1k T300级薄型碳纤维织物的复合材料性能与国产3k T300级碳纤维织物的复合材料性能相当;该薄型碳纤维织物复合材料的树脂体系是改性增韧环氧树脂,韧性好,适用于轻质夹层结构复合材料,具有较高滚筒剥离强度;同时,该轻质复合材料耐热性好,玻璃化转变温度能达到200℃。     

977-2/T300和M21/T800复合材料性能研究

探讨了增韧环氧树脂977-2与T300碳纤维、增韧环氧树脂M21与T800碳纤维形成的单向带预浸料、织物预浸料以及复合材料层压板的性能。研究结果表明:M21/T800预浸料属于T800级材料,M21/T800复合材料的常规力学性能在纤维控制的项目上,高于其他三种材料;树脂基体及界面的性能与T300材料的相当,材料的韧性和抗损伤能力比T300材料有较大程度的提高;M21/T300织物预浸料的韧性和抗损伤能力优于977-2A/T300预浸料。     

混杂纤维复合材料性能研究

对碳纤维织物、玻璃纤维织物和芳纶织物的性能进行测试,采用热熔法分别制备了一种增韧中温固化环氧碳纤维织物预浸料、玻璃纤维织物预浸料和芳纶织物预浸料。预浸料以单种预浸料铺层和不同纤维织物预浸料混合铺层方式铺贴组合,通过模压法成型复合材料层合板,进行性能测试并对比。结果表明,增韧中温固化环氧树脂的不同纤维织物预浸料混合铺层成型的层压板力学性能可以根据铺层设计优化,并不损失不同纤维铺层之间的界面性能。     

新型改性BMI／T300和BMI／T800复合材料性能

本文研究了新型改性BMI树脂与T300和T800）碳纤维形成的预浸料和复合材料层压板性能，并对二者进行了比较和分析，获得了具有良好力学性能的BML/T300和BML/T800复合材料体系。     

利用单方向碳纤维预浸料织物的复合材料及利用该复合材料的覆铜板层压板

正本发明涉及具有厚度薄、热膨胀系数低及热放出高等特性的复合材料的制造方法和通过该制造方法制造的复合材料及利用该复合材料的覆铜板层压板。根据本发明的利用单方向碳纤维预浸料织物的复合材料,利用通过包括如下步骤的方法制造的单方向碳纤维预浸料织物,该方法包括:制造单方向碳纤维预浸料的步骤;将制造的单方向碳纤维预浸料切断成一定宽幅的步骤;将切断成     

中温固化薄型环氧预浸料的综合性能研究

采用超声波扩展法制得薄型单向碳纤维,与自制的中温固化环氧树脂(EP)体系制得预浸料及复合材料,通过电镜分析、示差扫描量分析及凝胶时间、力学性能测试研究了预浸料纤维排布变化、预浸料及其复合材料的性能.结果 表明,预浸料纤维排列均匀、平直、紧密,无损伤.自制EP胶膜具有明显潜伏性和中温快速固化特征.薄型及常规碳纤维预浸料制...     

风电叶片用国产碳纤维预浸料工艺性能和力学性能研究

应用碳纤维制备风电叶片结构件是大型风电叶片制作技术的一个发展方向。为推动国产碳纤维的发展应用,给出了风电叶片对碳纤维预浸料的技术要求,研究了国产碳纤维预浸料和进口碳纤维预浸料的力学性能和工艺性能,通过对比分析发现,面密度低的国产碳纤维预浸料力学性能高于进口碳纤维预浸料,但面密度≥600g/m2的国内碳纤维预浸料的工艺性能较差,需要进一步改进。     

连续碳纤维增强聚醚醚酮复合材料的制备及力学性能

采用自主研发的连续碳纤维/聚醚醚酮热熔法预浸料(HC2110),通过热压成型工艺制备了复合材料层合板。测试了复合材料的力学性能,表征了微观形貌和破坏模式。预浸料热性能测试表明,HC2110预浸料较国外材料(TC1200)的耐热性及成型工艺性较优。微观形貌分析表明,复合材料层合板中纤维分布均匀性对0°拉伸性能影响较小;而纤维和树脂的界面结合较差是导致90°拉伸强度明显偏低的主要原因。     

直升机尾梁用碳／环氧复合材料的性能

介绍了一种适用于制造直升机主承力构件－尾梁的改性环氧树脂／T300碳纤维预浸料及其复合材料的工艺性能和主要力学性能。     

Thermo‐mechanical behavior of stretch‐broken carbon fiber and thermoplastic resin composites during manufacturing

Stretch‐broken fiber reinforcements and thermoplastic resin commingled prepregs are interesting for manufacturing composite parts in aeronautic and automobile industries. With these materials it is possible to produce composite parts with complex geometries, and high curvatures. On the other hand the length of the fibers leads to mechanical properties of the final composite that are close to those of the composite with continuous fibers. This paper analyzes the thermo‐mechanical properties of Stretch Broken Carbon Fiber (SBCF) / PPS and PEEK commingled prepregs during manufacturing. Tensile and in‐plane shear tests at different temperatures are analyzed. The experiments are realized in an isothermal oven. The range of temperature is those of the part during a thermoforming process. The experimental data allow to analyze the differences on the tensile and in‐plane shear behaviors at different temperatures between thermoplastic prepregs with continuous fibers and thermoplastic prepregs with stretch‐broken fibers. Forming simulations show that wrinkling can be avoided with SBCF prepregs while these wrinkles develop during continuous fibers prepreg forming. POLYM. COMPOS., 36:694–703, 2015. © 2014 Society of Plastics Engineers     

Processing and properties of solution impregnated carbon fiber reinforced polyethersulfone composites

Carbon fiber reinforced polymer composites are attractive because of their high stiffness and strength‐to‐weight ratios. In order to fully utilize the stiffness and strength of the reinforcement fiber, it is necessary to bring the polymer matrix and the reinforcement fiber together with homogeneous wetting. In this paper, a solution processing technique and the mechanical properties of carbon fiber reinforced polyethersulfone composites were investigated. The polymer was dissolved in cyclopentanone and fed onto a continuous carbon fiber tow using a drum winder. The solution‐processed composite prepregs were then layed up and compression molded into unidirectional composite panels for evaluation. The composite samples showed uniform fiber distribution and reasonably good wetting. The longitudinal flexural modulus was as high as 137 GPa, and longitudinal flexural strength 1400 MPa. In addition, the effects of polymer grade and processing conditions on the mechanical properties of the composites were discussed. It is suggested that the transverse properties and interlaminar fracture toughness could benefit from higher polymer matrix molecular weight. A careful design in the spatial distribution of the molecular weight would be necessary for practical applications.     

碳纤维改性HA/PMMA生物复合材料力学性能的研究

采用原位合成与溶液共混相结合的方法,制备了短切碳纤维增强纳米羟基磷灰石(HA)/聚甲基丙烯酸甲酯(PMMA)生物复合材料。研究了碳纤维的含量和长度对HA/PMMA复合材料结构和力学性能的影响。采用万能材料试验机和扫描电子显微镜对复合材料的力学性能及断面的微观形貌进行了测试和表征。结果表明:碳纤维在HA/PMMA复合材料中分布均匀,有效提高了复合材料的力学性能;碳纤维含量为4%时,复合材料的拉伸强度、弯曲强度、压缩强度和弹性模量等均达到最大值;复合材料的断裂伸长率随碳纤维含量的增加而减小;当碳纤维含量一定时,随其长度的增加,复合材料的拉伸强度、弯曲强度和弹性模量均增加,但断裂伸长率降低。     

Erosion Behavior of C/SiC Composites in Atomic Oxygen

A T300 carbon fiber and a SiC‐coated C/SiC composite made from the same fiber were studied in atomic oxygen environment. The carbon fiber shows significant degradation while the erosion rate of SiC‐coating of C/SiC is about 50 times lower. Evidence shows that Si is preferentially etched from the SiC surface. And XPS information showed that amorphous carbon and diamond‐like carbonare periodically generated on the tested composite surface. Statistical analysis shows that the C/SiC specimens have no significant change in flexural properties after 1‐year fluence AO treatment.     

5231树脂体系/碳纤维复合材料力学性能研究

着重研究了5231／T300复合材料的常规力学性能和高温下的力学性能,并与5222／T300复合材料的相应性能进行了对比,试验表明,前者在抗压缩模量和抗剪切性能方面比后者略低,其他力学性能基本相当,耐高温性能良好,另外,5231碳布预浸料可与铝蜂窝直接共固化,抗滚筒剥离强度较高,该复合材料可应用于飞机的结构件上。     

零吸胶工艺复合材料层板成型质量与预浸料特性关联分析

针对3种国外产碳纤维/环氧预浸料,测试表征了预浸料的工艺特性,并采用热压罐零吸胶工艺制备了复合材料层板,考察了工艺条件对层板厚度和内部缺陷的影响,分析了成型质量与预浸料特性之间的关联性,进一步研究了层板弯曲性能、层间剪切性能对成型质量变化的敏感性。实验结果表明,由于零吸胶工艺树脂流动受到很大限制,预浸料树脂含量不均容易造成所成型层板厚度不均、表面不平整,另外,预浸料树脂流动性小的体系在层间容易出现明显富树脂现象;零吸胶工艺夹杂空气主要在真空作用下通过铺层内的通道排出,因此预浸料气体渗透率和成型封装方式对孔隙缺陷有重要影响;实验范围内,工艺条件的改变没有显著影响所成型层板的短梁剪切性能和弯曲性能。研究结果对于预浸料选择和国产高性能预浸料的开发具有重要参考价值。     

Mechanical characterization and fractography of glass fiber/polyamide (PA6) composites

The mechanical properties of the glass fiber reinforced Polyamide (PA6) composites made by prepreg tapes and commingled yarns were studied by in‐plane compression, short‐beam shear, and flexural tests. The composites were fabricated with different fiber volume contents (prepregs—47%, 55%, 60%, and commingled—48%, 48%, 49%, respectively) by using vacuum consolidation technique. To evaluate laminate quality in terms of fiber wet‐out at filament level, homogeneity of fiber/matrix distribution, and matrix/fiber bonding standard microscopic methods like optical microscopy and scanning electron microscopy (SEM) were used. Both commingled and prepreg glass fiber/PA6 composites (with V_f ∼ 48%) give mechanical properties such as compression strength (530–570 MPa), inter‐laminar shear strength (70–80 MPa), and transverse strength (80–90 MPa). By increasing small percentage in the fiber content show significant rise in compression strength, slight decrease in the ILSS and transverse strengths, whereas semipreg give very poor properties with the slight increase in fiber content. Overall comparison of mechanical properties indicates commingled glass fiber/PA6 composite shows much better performance compared with prepregs due to uniform distribution of fiber and matrix, better melt‐impregnation while processing, perfect alignment of glass fibers in the composite. This study proves again that the presence of voids and poor interface bonding between matrix/fiber leads to decrease in the mechanical properties. Fractographic characterization of post‐failure surfaces reveals information about the cause and sequence of failure. POLYM. COMPOS., 36:834–853, 2015. © 2014 Society of Plastics Engineers     

大丝束碳纤维复合材料力学性能研究

本文研究了大丝束碳纤维(48K)复合材料的常规力学性能及耐湿热性能，并与小丝束碳纤维(T300．3K)复合材料进行了对比，研究结果可为大丝束复合材料在航空器的次承力件或非承力件的应用提供技术基础。     

Thermoforming of advanced thermoplastic composites. I: Single curvature parts

Thermoforming has been studied for a single curvature part made from various advanced thermoplastic matrix composite prepregs. For parts with acceptable shape conformity, preheating of the composite laminates to a processing temperature of 350 to 400°C is necessary prior to forming with molds maintained at 200°C. However, only PEEK/carbon fiber prepreg tapes yielded parts with acceptable microstructural integrity and a matrix crystallinity level of about 30 percent. Amorphous matrix based PXM 8505/T500 fabric prepregs also result in lamination and void free parts, but fiber matrix distribution in this case was rather poor. Parts thermoformed from other prepreg laminates contained voids and/or were delaminated, thereby indicating the need for higher mold temperature and forming pressure than that afforded by the present study, in which a standard lab-scale thermoforming machine was used.