沥青炭基体C/C复合材料单向层间剪切性能及破坏机理

以沥青四氢呋喃溶液、沥青四氢呋喃溶液 20％焦炭粉(质量分数)和酚醛树脂四氢呋喃溶液 60％焦炭(质量分数)为预浸料预浸炭纤维，模压制成初坯体，然后再浸渍沥青-炭化，制备了3种单向纤维增强炭／炭(C／C)复合材料试祥。对试祥的密度、开孔率、层间剪切强度和显微结构进行了测试和观察，探讨了剪切破坏的机理。结果表明：C／C复合材料的层间剪切强度随密度的增大和孔隙度的降低而提高，高温处理虽可使致密度得到进一步增大，但层间剪切强度则由于基体炭的软化，以及基体炭与纤维(或焦炭粉颗粒)界面的变化而显著降低；由于微裂纹和孔洞的存在，剪切裂纹前沿应力集中被释放，可阻止裂纹继续扩展，载荷的继续增大导致新裂纹的生成并扩展，所以C／C复合材料的三点弯曲剪切破坏呈多裂纹复合剪切模式。     

芳纶/聚合物基复合材料层间剪切性能研究

按照国内外现行试验方法进行芳纶复合材料层间剪切性能测试,发现试样仅出现大弯曲变形,没有出现层间分层失效模式,推断现有方法无法正确表征和测试芳纶纤维增强聚合物基复合材料的层间剪切强度。通过基于界面元原理的复合材料层合板试验数值仿真,优化了试样的厚度和试验跨厚比。按照优化参数试验,试样出现了层间分层的正确失效模式,获得了真实的层间剪切强度,并与仿真结果吻合较好。由此,建议修订现有试验方法或建立专门的芳纶复合材料层合板层间剪切强度标准试验方法。     

C/C-SiC复合材料的制备及其层间剪切强度分析

采用先驱体浸渍裂解结合液硅渗透的方法制备C/C-SiC复合材料。通过X射线衍射和扫描电镜分析了材料的成分和微结构,采用压缩双切口试样法分别在室温和1600℃下测试其层间剪切强度,分析了微观剪切破坏机理。结果表明:碳纤维表面的热解碳(PyC)与液硅反应生成一层SiC,保护纤维不受残余Si的损伤。树脂碳和液硅反应生成的SiC填充了多孔C/C的孔隙。材料的高温层间剪切强度是室温下的2倍左右。室温下基体存在残余热应力,界面结合强度低,材料属于脆性断裂,高温下基体残余热应力得到释放,界面结合强度增大,基体裂纹部分闭合,该复合材料可承受更大的剪切应力。     

C/C-Cu复合材料的烧蚀性能及烧蚀机理

采用真空熔渗技术制备新型C/C-Cu复合材料。采用氧-乙炔焰测试不同时间下C/C-Cu复合材料的抗烧蚀性能,利用XRD、SEM分析材料烧蚀后的物相组成及组织形貌,对C/C-Cu复合材料的烧蚀机理进行研究。结果表明:烧蚀时间对材料的烧蚀率有显著影响,随着时间的延长,材料的质量烧蚀率和线烧蚀率均呈上升趋势;烧蚀后复合材料表面生成氧化物相TiO2和Cu2O,原来的TiC相被TiO2相替代;C/C-Cu复合材料的烧蚀性能优于C/C复合材料的烧蚀性能;C/C-Cu复合材料的氧-乙炔焰烧蚀机制为热氧化烧蚀、热物理烧蚀(升华)和机械冲刷的综合作用。     

稀土改性剂处理对芳纶／环氧复合材料层间剪切强度的影响

分别采用稀土改性剂（RES）和环氧氯丙烷（ECP）接枝改性方法对F-12芳纶纤维表面进行改性处理，探讨了RES浓度对于芳纶／环氧复合材料层问剪切强度（ILSS）的影响，初步分析了RES对于F-12芳纶纤维表面作用的机理，应用SEM对复合材料层问剪切断口进行分析，并考察了稀土改性剂处理对于纤维强度的影响。实验结果表明：采用RES进行表面改性处理，稀土元素通过配位化学反应，能够提高芳纶纤维表面活性基团的浓度，从而提高芳纶纤维和环氧树脂基体的界面结合力；当稀十元素含量（ω,％）为0．5时，复合材料的层问剪切强度最好；稀土改性剂处理对于纤维本身的强度几乎没有影响。     

B4C/Al复合材料力学性能及其断裂机理的研究

对无压浸渗法制备的B4C/Al复合材料进行了力学性能测试。结果表明,B4C/Al复合材料的抗弯强度和断裂韧性与单一B4C材料相比有显著提高。B4C/Al复合材料的抗弯强度及断裂韧性分别比单一B4C提高了18.39%和75.27%,但其硬度降低。B4C/Al复合材料经扫描电镜和背散射仪分析后发现,无压浸渗法制备的B4C/Al复合材料中没有大尺寸的显微缺陷,组织分布比较均匀、致密;B4C以连续的骨架结构存在,而渗入的铝相也以连续基体的形式存在;单一B4C存在较多的穿晶断裂,而B4C/Al复合材料的断裂方式主要以沿晶断裂为主,这是B4C/Al复合材料断裂韧性提高的主要原因。     

混杂C/C复合材料的烧蚀性能

利用等离子体火炬为高温热源,研究了混杂C/C复合材料的烧蚀性能.结果表明:随着烧蚀区域从火焰中心到边缘的变化,材料的烧蚀特性从中心区域的以热力学烧蚀为主向靠近边缘区域的以热化学烧蚀为主过渡;碳基体和碳纤维的抗热力学烧蚀性能相当,而碳纤维的抗热化学烧蚀特性则明显优于碳基体.     

不同基体炭C/C复合材料的摩擦磨损性能

以炭纤维针刺毡为预制体,采用化学气相沉积法(CVI)和结合液相浸渍树脂或沥青法制备了热解炭为粗糙层与光滑层结构的准三维C/C复合材料,并研究了这些材料在0.6 MPa的模拟刹车压力下的摩擦磨损性能与磨损机理.研究表明:基体炭为粗糙层热解炭与树脂炭的C/C复合材料摩擦表面能形成较厚且连续的自润滑摩擦膜,摩擦稳定性最好,摩擦因数适中,氧化磨损小,磨损机理主要为膜的部分脱落、氧化磨损与相对较小的磨粒磨损;基体炭为光滑层热解炭与树脂炭或沥青炭的C/C复合材料摩擦表面形成的摩擦膜较薄且不连续,摩擦稳定性差,摩擦磨损较大,磨损机制主要为膜的部分脱落、磨粒磨损与更严重的氧化磨损;随着密度的升高,C/C复合材料摩擦稳定性增加,摩擦因数增加,磨损降低;基体炭为单一沥青炭的C/C复合材料,由于没有热解炭对纤维的保护,纤维断裂多,线性磨损尤其大,磨损机理主要为大量的磨粒磨损与氧化磨损.     

炭/炭复合材料热膨胀性能的研究

利用热膨胀仪测定了炭/炭复合材料从室温到1300℃的热膨胀系数,研究了热处理温度、炭纤维取向和环境温度对炭/炭复合材料热膨胀性能的影响。结果表明由于热解炭是以层状的方式围绕炭纤维生长,所以其热膨胀各向异性,垂直于纤维方向的热膨胀大于平行于纤维方向的热膨胀。随着热处理温度的升高,炭/炭复合材料中具有乱层石墨结构的晶体有序度增加,石墨化度增大,石墨片层间的范德华作用力增强,热膨胀系数减小。随着环境温度的升高热膨胀系数先增大后减小,在1200℃有最大值。     

高密度预制体制备炭/炭复合材料的弯曲力学性能与断裂机制

以丙烯作为碳源,氮气作为载气,采用初始密度为0.94g/cm3三维正交PAN基12K炭纤维预制体,利用自制的快速CVI炉制备基体热解炭结构为带状结构的C/C复合材料。力学性能测试结果表明,材料的弯曲断裂特征与制备过程中受到的高温热处理次数有关。从载荷-位移曲线来看,当C/C复合材料经过两次热处理时,C/C复合材料呈明显假塑性断裂特征。当C/C复合材料经过三次热处理时,载荷-位移曲线趋于稳定平滑,抗弯强度降低。从C/C复合材料断面的SEM图可以观察到材料断裂可以分为层间断裂和层内断裂,而层内断裂又因热解炭填充密度变化呈明显的分区断裂。由于热解炭和纤维含量在C/C复合材料中分布的差异,材料在不同的区域表现出不同的断裂特征,从而使得材料具备良好的弯曲强度同时具有一定的韧性特征。     

载气对CVI C/C材料密度和热解炭结构分布的影响

采用定向流动热梯度CVI工艺,以丙烯作炭源气,以针刺炭纤维整体毡作预制体分别研究了加氢气和氮气作载气对C/C复合材料密度和热解炭结构分布的影响。结果表明,载气对热梯度CVI C/C材料密度和热解炭结构沿径向分布的均匀性有重要影响。当其它工艺条件相同时,经过400 h的沉积,采用N2作载气时所得炭盘的平均体密度为1.54 g/cm3,炭盘密度沿径向分布的偏差Δρ为0.24 g/cm3,在炭盘的外侧易形成SL结构热解炭;而采用H2作载气时,可以得到平均体密度为1.67 g/cm3、热解炭结构分布高度均匀的全RL结构PyC基C/C复合材料,且炭盘密度沿径向分布的偏差Δρ仅为0.11 g/cm3,密度分布均匀性提高一倍以上。不管是采用N2还是H2作载气,炭盘的密度沿周向分布都十分均匀(Δρ≤0.02 g/cm3),且炭盘的较低密度部位均位于中间偏内侧。     

多孔体制备工艺对C/C-SiC复合材料弯曲性能的影响

以针刺整体炭毡为坯体,采用CVD和树脂浸渍／炭化混合法增密制备了4种C／C多孔体,然后熔硅浸渗C／C多孔体制备了C／C-SiC复合材料;研究了不同炭涂层、高温热处理对C／C-SiC复合材料弯曲强度和断裂方式的影响。结果表明：热解炭涂层可减少制备过程中炭纤维的损伤,具有适中的界面结合强度,使复合材料的弯曲强度达到161．5MPa,表现出良好的“假塑性”;适当选择高温热处理工艺可制备弯曲性能较高,具有一定“假塑性”的C／C-SiC复合材料。     

温压-原位反应法制备C/C-SiC材料的压缩性能及其破坏机理

以短炭纤维、炭粉、Si粉、树脂和粘结剂为原料,采用温压-原位反应法（WC-ISR）制备C/C-SiC制动材料,研究该材料的压缩性能及其破坏机理。结果表明：C/C-SiC制动材料的纵向压缩强度可达118.2 MPa,纵向压缩破坏表现为韧性断裂,以对角剪切破坏方式为主;横向压缩强度可达86.9 MPa,横向压缩破坏主要表现为脆性断裂,以多层复合剪切破坏方式为主。C/C-SiC制动材料的压缩性能分别随炭纤维和SiC含量的增加而增大,且炭纤维含量的影响更加显著;但随基体炭含量的增加而降低。     

Fracture mechanism of 2D-C/C composites with pure smooth laminar pyrocarbon matrix under flexural loading

Using natural gas as carbon source, 2D needle felt as preform, 2D-C/C composites were prepared by thermal gradient chemical vapor infiltration. Their microstructures were observed under polarized light microscope (PLM) and scanning electron microscope (SEM), and the flexural behaviors before and after heat-treatment were studied with a universal mechanical testing machine. The fracture mechanism of the composites was discussed in detail. The results show that, carbon matrix exhibits pure smooth laminar (SL) characteristic including numerous wrinkled layered structures and some inter-laminar micro-cracks. With the decreasing density, the strength of the composites decreases and the toughness increases slightly; after 2500 °C heat-treatment, the inter-laminar micro-cracks in matrix increase, the strength decreases, and the toughness obviously increases. The fracture mode of the composites changes from brittle to pseudo-plastic characteristic due to more crack deflections in SL matrix.     

Numerical simulation on thermal expansion coefficient of 3D braided C/C composites简

To effectively get the thermal expansion coefficient(CTE) of three-dimensional(3D) braided C/C composites and study the variations, a VC?? program with graphical user interfaces was obtained, based on the yarn unit model and numerical analysis. With the limited basic properties of carbon fibers and carbon matrix, CTE of 3D braided C/C composites is obtained at 85 °C. The deviation between the simulated and experimental axial CTE of 3D braided C/C composites is no more than 11 %. The effects of different parameters(including the braiding angle of 3D braided preform, the fiber volume fraction and the porosity of 3D braided C/C composites, and the elastic modulus, Poisson's ratio and CTEs of carbon fibers and carbon matrix) were analyzed with the program. The results show that the axial CTE of C/C composites decreases with the increase of the braiding angle, the fiber volume fraction, and the porosity of 3D braided C/C composites. The transverse elastic modulus of carbon fibers has the greatest effect on the axial CTE among the studied mechanical parameters, followed by the elastic modulus and Poisson's ratio of carbon matrix.     

Microstructure and mechanical properties of 3D fine-woven punctured C/C composites with PyC/SiC/TaC interphases

The 3D fine-woven punctured C/C-(P_yC/SiC/TaC) composites, composed of P_yC/SiC/TaC interphases and pyrocarbon (PyC) matrix, were synthesized by isothermal chemical vapor infiltration (ICVI) methods. The alternating layers and the structure of these composites were examined by polarized light microscopy (PLM), X-ray diffractometry (XRD) and scanning electron microscopy (SEM). It is found that the P_yC matrix has rough laminar (RL) structure, the TaC layer has NaCl-type cubic structure, and the SiC layer has few wurtzite type 10H-SiC besides β-SiC structure. The effects of fiber coating and the bulk density on the tensile and flexural properties of composites along X or Y and Z direction were investigated. It is shown that fiber coated 3D woven punctured C/C composites have good tensile and flexural strength, and the maximum of flexural strength is 375 MPa in X or Y direction at density of 1.89 g/cm³, which is about three times higher than that of samples without TaC/SiC fiber coating. The flexural strength and bending strength increase with increasing the density of the composites. The analysis of fracture surfaces reveals that fibers and fiber bundles are pulled out in composites, indicating that the composite exhibits a non-linear failure behavior through propagation and deflection of the cracks.     

Effect of fiber characteristics on fracture behavior of C_f/SiC composites

Cf/SiC composites were prepared by precursor pyrolysis-hot pressing, and the effect of fiber characteristics on the fracture behavior of the composites was investigated. Because the heat treatment temperature of fiber T300 (below 1500℃) was much lower than that of fiber M40JB (over 2000℃), fiber T300 had lower degree of graphitization and consisted of more impurities compared with fiber M40JB, suggesting that T300 exhibits higher chemical activity. As a result, the composite with T300 showed a brittle fracture behavior, which is mainly ascribed to a strongly bonded fiber/matrix interface as well as the degradation of fibers during the preparation of the composite. However, the composite with M40JB exhibits a tough fracture behavior, which is primarily attributed to a weakly bonded fiber/matrix interface and higher strength retention of the fibers.