新型针刺炭布C/C复合材料的结构与性能

采用炭布与预氧丝网胎交替叠层针刺成预制体,经ＣＶＩ与ＨＰＩＣ相结合的致密工艺及石墨化处理制取高密度（１．８０ｇ／ｃｍ＾３～１．８５ｇ／ｃｍ＾３）Ｃ／Ｃ复合材料。所及材料的微观结构,力学、热学和烧蚀性能均达到国际同类刹车盘Ｃ／Ｃ材料的先进水平,是一种有广阔应用前景的烧蚀分离燃气舵材料。     

化学气相沉积碳／碳复合材料性能研究

分析了化学气相沉积碳／碳（Ｃ／Ｃ）复合材料的刹车力矩和刹车速度的关系曲线及影响因素，结果表明，刹车力矩一刹车速度曲线上的初始力矩峰值随着摩擦界面温度的升高而增大，提高材料的石墨化度、改变刹车盘的结构、降低刹车比压的施加速度都可以降低初始力矩峰值，改善Ｃ／Ｃ材料的摩擦性能．Ｃ／Ｃ复合材料具有良好的自润滑性能，其磨损率仅为１．２×１０－３ｍｍ／次．它们具有较高的机械性能和热物理性能，完全可以满足飞机刹车的要求．     

碳／碳复合飞机刹车材料的现状及展望

论述了碳／碳复合刹车材料的优点制备方法及发展现状，并展望了Ｃ／Ｃ复合飞机杀车材料的未来。     

CLLVD法制备2D C／C复合材料

化学液气相沉积法是快速低成本制备Ｃ／Ｃ复合材料的一种新型工艺。通过离该工业快速制备Ｃ／Ｃ复合材料的根本原因,并以１．５ｍｍ／ｈ的速度制备了炭布局叠２ＤＣ／Ｃ复合材料,同时对该材料进行了力学性能测试和金相分析。实验结果表明材料优越,说明该工艺是制务Ｃ／Ｃ复合材料的理想工艺。     

碳纤维复合材料刹车片的发展及应用前景

本文介绍了刹车片材料发展的历程,基于密度低、制动性好等优越性的碳纤维复合材料刹车片的开发,以及碳纤维复合材料刹车片在汽车、列车、飞机产业的应用现状和应用前景。     

基体改性C／C复合材料在高温下的氧化规律

对基体改性Ｃ／Ｃ复合材料在高温下的氧化规律进行了探讨,分析限基体改性Ｃ／Ｃ复合材料在恒温下的氧化失重与氧化时间的变化关系,结果表明,这种关系可分为三个阶段：（１）失重率为０－６０５的线性阶段;（２）失重率为６０－８０％的指数阶段;（３）失重率为８０－１００％的线性阶段,其次又分析了基体改性Ｃ／Ｃ复合材料在恒定时间下的氧化失重与氧化温度的变化关系,结果表明,这种关系也可分为三个阶段;（１＇）室温－失     

C/C复合材料层间裂纹扩展研究

作为一种耐高温高性能复合材料,Ｃ／Ｃ复合材料具优异的高温力学性能,但是材料本身的脆性是其弱点之一,其中,对于二维碳碳复合材料而言,层间裂纹扩展是其主要损伤机理,本文针对Ⅰ型和Ⅱ型层间裂纹扩展进行实验研究,深入分析了不同密度及加入填充剂填充的二维碳／碳复合材料的层间裂纹扩展方式,测试了Ⅰ型和Ⅱ型层间裂纹扩展能,发现裂纹扩展能随密度的增大而增大,加入石墨粉或热解炭粉可以有效提高材料的裂纹扩展能．     

核聚变用C／陶复合材料的研制

某些Ｃ／陶复合材料，已在国外新一代核聚变托卡马克装置上试用，本文用热压法研制了Ｃ／Ｂ４Ｃ，Ｃ／ＴｉＣ及Ｃ／Ｂ４Ｃ／Ｔｉ／Ｓｉ三种Ｃ／陶复合材料，并描述了不同的原料配比对材料常规性能的影响，本文还介绍了新介绍的几种典型复合材料，对离子化学溅射腐蚀的影响效应。     

添加预氧化纤维（OXI－PAN）的C／C复合材料的摩擦和磨损性能

添加预氧化纤维（ＯＸＩ－ＰＡＮ）的Ｃ／Ｃ复合材料的摩擦和磨损性能ＪｉｎＹｏｎｇＬｅｅ等（南朝鲜）前言Ｇ／Ｇ复合材料在１０００℃以上的高温下具有良好的摩擦／磨损性能，低的热膨胀系数、适当的热容及高的强度，因而使得这种材料可以用作飞机、赛车、高速火车、军...     

用圆形和C形碳纤维增强的C／C复合材料

用圆形和Ｃ形碳纤维增强的Ｃ／Ｃ复合材料Ｙ．Ｊ．Ｃｈｏｉ等（南朝鲜）前言纤维－基体界面强度对复合材料的性能有强烈的影响（１２），可以通过表面处理增强化学结合力或增加表面积来提高界面结合力。很少有报道通过增大表面积的方法来提高纤维和基体间的结合力。在以前...     

Effects of Anti-Oxidant Migration on Friction and Wear of C/C Aircraft Brakes

The surfaces of carbon-carbon (C/C) aircraft brakes are usually coated with anti-oxidant to protect them from oxidation. These surfaces do not include the friction surfaces since it is known that when anti-oxidant get onto the friction surface, the friction coefficient decreases. The anti-oxidant migration (AOM), however, happens during processing, heat treatment and application. In this study, phosphorus based anti-oxidants inhibited 3-D C/C aircraft brake system was investigated. The effects of their migration on friction and wear in the 3-D C/C brakes were revealed by sub-scale dynamometer tests and microscopic analysis. Dynamometer results showed that when AOM occurred, both landing and taxi coefficients decreased in humid environment and the wear was slightly lowered. Microscopic study showed that under high humidity conditions there was no formation of the friction film.     

碳/碳复合飞机刹车材料低能摩擦性能研究

研究了碳/碳(简称C/C)复合飞机刹车材料在低能载条件下的摩擦磨损性能,分析了刹车力矩与刹车速度之间关系曲线,探讨了C/C复合材料因能载变化出现摩擦系数最大值的根本原因.结果表明:随着刹车比压增加,摩擦系数最大值下降;低能条件下C/C复合材料摩擦面较粗糙,磨损率约为正常能载下的两倍.     

碳／碳复合材料在航空领域的应用研究现状

介绍了碳／碳复合材料在飞机刹车装置及航空发动机热端部件方面应用，研究的国内外状况，论述了目前研究中存在的总是及今后的研究发展方向。     

Fatigue characteristics of metal impregnated C/C composites with slots for load transfer

An experimental investigation is performed on the quasi-static and cyclic behavior of metal impregnated composites such as Cu–C/C and Si–C/C with a slot together with C/C for comparison. They are expected to be applied to an aircraft brake system. Composites tested are based on a preformed yarn method and their fatigue strength and related characteristics are obtained. Damage mechanisms are discussed and it is concluded that effects of microscopic debonding are quite important to the fatigue response of the present specimen and that the debonding makes the failure mode shift from crack propagation in static loading to bearing in cyclic loading.     

民航飞机刹车装置选材研究EI

通过对90年代国外民航飞机刹车装置选材分析,论述了飞机国产刹车装置选材的依据原则。根据刹车装置零部件选材的试验研究及多年的生产应用实践证明,国产刹车装置的设计选材达到了中国民用航空局CCAR CTSO-C26c《航空机轮和机轮刹车装置》技术标准规定,符合美国联邦航空局FAA TSO-C26c Aircraft Wheels and Wheel Brake Assembles技术标准规定。     

Design,Fabrication, and Application of Thermostructural Composites (TSC) like C/C,C/SiC,and SiC/SiC Composites

The French company Snecma Moteurs is a leading producer of high‐performance composites for operation under high mechanical stress and at high temperature, such as in jet engines, aircraft brake disks, or even rocket propulsion systems. The author presents the different families and generations of carbon‐carbon and ceramic‐matrix composites developed by Snecma, and discusses their manufacture and characteristics.     

飞机刹车用长寿命高摩擦特性炭/炭复合材料制备技术(英文)

以针刺炭纤维准三向结构整体毡为预制体,经丙烯气体狭缝定向流的"外热内冷"、"内热外冷"径向热梯度CVI工艺致密技术,优化组合的热解炭/树脂炭双元炭基体技术,通过调控高温处理技术等三大关键技术制备了A320系列飞机炭刹车盘材料。与现用的A320系列飞机进口炭刹车盘进行了地面台架对比试验和装机应用。结果表明:自主开发的炭刹车盘其设计着陆能量和超载着陆能量的摩擦特性与国外相当,但在高能载(RTO)刹车时,其摩擦系数提高了21%～48%,静摩擦系数提高了28%;装机应用寿命平均达到2700次以上,比国外产品寿命提高了23%,凸现出长使用寿命和高摩擦特性的特色。     

Preparation, Properties and Application of C/C-SiC Composites Fabricated by Warm Compacted-in situ Reaction

Carbon fibre reinforced carbon and SiC dual matrices composites (C/C-SiC) show superior tribological properties, high thermal shock resistance and good abrasive resistance, and they are promising candidates for advanced brake and clutch systems. The microstructure, mechanical properties, friction and wear properties, and application of the C/C-SiC composites fabricated by warm compacted-in situ reaction were introduced. The results indicated that the composites were composed of 50-60 wt pct carbon, 2-10 wt pct residual silicon and 30-40 wt pct silicon carbide. The C/C-SiC brake composites exhibited good mechanical properties. The value of flexural strength and compressive strength could reach 160 and 112 MPa, respectively. The impact strength was about 2.5 kJ·m^-2. The C/C-SiC brake composites showed excellent tribological performance, including high coefficient of friction (0.38), good abrasive resistance (1.10 μm/cycle) and brake steadily on dry condition. The tribological properties on wet condition could be mostly maintained. The silicon carbide matrix in C/C-SiC brake composites improved the wear resistance, and the graphite played the lubrication function, and right volume content of graphite was helpful to forming friction film to reduce the wear rate. These results showed that C/C-SiC composites fabricated by warm compacted-in situ reaction had excellent properties for use as brake materials.     

C/C刹车盘快速致密化工艺及其性能

为了缩短C/C刹车盘制备周期并提高其性能,介绍了一种制备C/C飞机刹车盘的快速致密化工艺,即采用天然气与丙烷气的混合气体为炭源气体的等温压差CVI法。与常规致密化工艺（丙烯气为炭源气体的等温压差CVI法）相比,C/C刹车盘的CVI(Chemical vapor infiltration) 时间缩短了一半,其导热性能提高5%以上,拉伸、压缩、弯曲与剪切性能提高10%以上,摩擦磨损性能提高20%以上。      

高性能C/SiC刹车材料及其优化设计

对比分析了 C/ C和 C/ SiC刹车材料的力学性能和摩擦磨损性能。结果表明 , C/ SiC刹车材料的力学性能比 C/ C的高 , 而且 C/ SiC刹车材料克服了 C/ C静态摩擦系数低和湿态摩擦性能严重衰减的不足 , 说明 C/ SiC刹车材料是一种新型高性能刹车材料。以 C/ C复合材料为基础 , 在深入分析机轮刹车盘服役环境特点的基础上探讨了 C/ SiC刹车材料的力学性能、 热物理性能、 摩擦磨损性能、 复合材料结构和制造工艺等方面的优化设计途径和方法 , 为实现材料微结构2力学性能2摩擦磨损性能的协同设计与制造奠定基础。