纤维铝合金胶接层板残余应力分布

本文采用准三维有限元方法,计算对称铺设混杂复合层板在固化时产生的残余应力,给出了芳纶纤维/树脂-铝合金层板,在自由状态和施加预应力情况下的残余应力计算值,以及不同温度变化下残余应力计算值。本文还给出铝合金-玻璃纤维/树脂-芳纶纤维/树脂层板,在自由状态下固化时的残余应力值。某些计算结果与应变片包埋法实验测得的层板残余应力值十分吻合,表明了计算方法的正确性。用准三维有限元分析残余应力的方法,为设计和制造出满足最佳力学性能要求的层板提供了有价值的参考。     

碳纤维复合材料的微波反射特性研究

研究了各种铺层（０°、０°／９０°、±３０°、±４５°、±６０°）方式碳纤维复合材料（ＣＦＲＰ）的皮反射特性。结果表明,单向纤维铺层ＣＦＲＰ的反射率与纤维方向及层板厚度有关;交叉铺层ＣＦＲＰ的反射率很大,但比金属略小,喷涂了防雷击层的单向纤维铺层ＣＦＲＰ,电性能基本上各向员性;喷涂了防雷击层的０°、±４５°、０°／９０°ＣＦＲＰ的反射率比喷涂前有所降低。     

复合材料压缩实验时应力分布的有限元计算

碳纤维增强树脂基复合材料（简称ＣＦＲＰ）薄板压缩实验时有三种不同的加载形式。本文对这三种加载形式进行了研究和分析，并有限元素法计算了这三种加载形式在１－３面内的压应力和层剪应力的分布? ?     

HA-Ti生物功能梯度材料微观组织及热应力缓和特性

本文用粉末冶金法制备了ＨＡ－Ｔｉ系生物ＦＧＭ,并测定了ＨＡ－Ｔｉ复合体材料的弹性模量和热膨胀系数．应用经典叠层板理论和热弹性力学理论分析了ＨＡ－Ｔｉ系ＮＦＧＮ双层板和ＨＡ－Ｔｉ系ＦＧＭ的制备残余热应力和热应变．结果表明,ＨＡ－Ｔｉ系生物ＦＧＭ呈现出宏观不均匀性与微观连续性的组织特征．ＨＡ－Ｔｉ系复合体材料的弹性模量在Ｔｉ－ＨＡ８０达到谷值,并受到气孔率的影响．其热膨胀系数随着ＨＡ含量和测试温度的升高而增大．残余热应力和残余热应变强烈依赖于组成分布,ＦＧＭ由于组成梯度化减小了成分变化幅度,其最大残余拉应力只有ＨＡ／Ｔｉ直接叠合体（ＮＦＧＭ）的１／３,具有显著缓和热应力的功能.     

颗粒/铜基复合镀层的摩擦学性能研究

研究了复合电沉积法制备的αＡｌ２Ｏ３／Ｃｕ、ＴｉＣ／Ｃｕ和ＴｉＣ＆ＣａＦ２／Ｃｕ复合材料的摩擦学性能及磨损机理。实验结果表明,颗粒的含量对磨损率表显著的影响,并且ＴｉＣ＆ＣａＦ２／Ｃｕ是一种很好的减摩、耐磨材料。另外,显微照片显示,磨粒磨损和粘着磨损在磨损过程中主导地位。     

Fe-Ti-C系燃烧合成反应的热力学分析

利用相图计算技术（ＣＡＬＰＨＡＤ）对Ｆｅ－Ｔｉ－Ｃ燃烧合成反应体系进行热力学分析,着重研究Ｆｅ含量和Ｃ／Ｔｉ原子比对体系绝热燃烧温度Ｔ_ａｄ和平衡相组成的影响．研究结果表明,Ｆｅ含量对 Ｆｅ－Ｔｉ－Ｃ三元系的平衡相组成影响不大,但对绝热燃烧温度的影响非常大．当保持Ｃ／Ｔｉ原子比接近１．０时,不管Ｆｅ含量如何变化;在２９８Ｋ下均会得到理想的平衡相组织ＴｉＣ＋Ｆｅ 随Ｆｅ含量增加,体系的绝热燃烧温度大致呈线性降低．Ｆｅ－Ｔｉ－Ｃ体系发生ＳＨＳ反应的热力学条件之一（Ｔ_ａｄ＞１８００Ｋ）是Ｆｅ＜５５ｗｔ％．而 Ｃ／Ｔｉ原子比对绝热燃烧温度的影响比较小,但对平衡相组成影响非常大,主要表现在两个方面：①石墨相的析出温度不同．随Ｃ／Ｔｉ原子比降低,析出温度也随之降低．②在各温区石墨相的含量不同．当 Ｃ／Ｔｉ在１．０～１．４变化时,石墨相含量在低温区由１％提高到１６％．     

碳纤维复合材料低温热导率分析计算模型

探讨了碳纤维复合材料（ＣＦＲＰ）低温传热机理及低温热导率的一般规律和影响因素；在分析讨论的基础上，建立了ＣＦＲＰ低温热导率的计算模型，并将计算结果与测试结果进行了比对。为设计、推算ＣＦＲＰ材料的低温热导率提供了一种简便、较准确的手段。     

纤维－金属胶结层板的桥接应力与应力强度因子研究EI

在国内外首次建立了纤维－金属结层板（ＦＲＭＬｓ）裂纹桥接应力分布的计算模型，本模型考虑了分层形状与尺寸、分层前沿胶黏剂的剪切变形、层板的残余温度应力以及有限板宽等因素的影响。在正确计算裂纹桥接应力的基础上，用权函数方法得到了纤维－金属胶结层板在桥接机理下的应力强度因子。     

纤维－金属胶结层板的桥接应力与应力强度因子研究

在国内外首次建立了纤维－金属结层板（ＦＲＭＬｓ）裂纹桥接应力分布的计算模型，本模型考虑了分层形状与尺寸、分层前沿胶黏剂的剪切变形、层板的残余温度应力以及有限板宽等因素的影响。在正确计算裂纹桥接应力的基础上，用权函数方法得到了纤维－金属胶结层板在桥接机理下的应力强度因子。     

玻璃纤维-铝合金层板(GLARE)的残余应力

对确定纤维金属层板残余应力的几种方法的基本原理进行了介绍，用Ｘ光衍射法，解析法和腐蚀去层法确定了玻璃纤维－铝合金层板（ＧＬＡＲＥ）的残余应力，对以上几种测试方法的优缺点进行了分析，提出了确定纤维金属层板残余应力的建议。     

Evaluation of impact damage mechanism of multi-axial stitched CFRP laminate

This study focuses on multi-axial stitched fabric, which is a thick, high performance reinforcement for large-scale composite structures. The effects of impact damage on multi-axial stitched CFRP laminates molded by vacuum-assisted resin transfer molding (VARTM) method were evaluated. Impact damage within material was evaluated by ultrasonic scanning device and optical cross-sectional observations. Probed images obtained by both non-destructive and destructive methods were compared, and internal damage distributions of multi-axial stitched CFRP laminates were clarified. In addition, residual compressive strength and fatigue property of impact-damaged CFRP laminates were evaluated by in situ damage growth monitoring using the thermo-elastic stress analyzer (TESA). Three-dimensional damage distribution of impacted CFRP laminate was obtained from ultrasonic C-scan images and cross-sectional photographs. Damage progress behavior was observed on a destructive and non-destructive basis by post-impact fatigue (PIF) test.     

碳纤维增强银粉改性树脂复合材料的雷击损伤效应

针对碳纤维增强树脂(CFRP)复合材料中树脂电阻大,在雷电流作用下会产生大量焦耳热造成雷击损伤的短板,探索通过增强基体的导电性来解决这一问题。为实现对CFRP复合材料的改性,在其环氧树脂浆料中加入了以Ag粉为主的导电填料,使改性CFRP复合材料层合板沿厚度方向的电导率提高217.30倍。采用不同峰值的单一雷电流D分量分别对改性及未改性CFRP复合材料层合板试件进行雷击损伤实验,通过损伤区域超声C扫描图像、试件残余温度场和仿真热解损伤的对比,分析基体改性对CFRP复合材料雷击损伤的防护机制。结果表明:通过Ag粉改性能有效提高CFRP复合材料层合板的电导率,且在厚度方向上的改性效果最佳;在峰值电流分别为20 kA、40 kA和60 kA的条件下,改性CFRP复合材料层合板的损伤面积分别下降87.28%、77.82%和88.59%,损伤深度分别增加147.06%、130.65%和119.72%;以损伤体积为最终指标,则Ag粉改性基体能有效降低CFRP复合材料的雷击损伤,其防护机制是通过减少雷电流作用下的高温区域面积和升温幅度来降低热解和爆炸冲击实现。      

不同湿热条件下碳纤维/环氧复合材料湿热性能实验研究

对比研究了环氧5228A树脂及碳纤维/环氧5228A树脂复合材料层合板在3种湿热环境(水煮、70℃水浸,70℃85%相对湿度)下的湿热性能,考察了湿热条件对复合材料层间剪切性能的影响规律,并从吸湿特性、物理化学特性、树脂力学性能、湿应力等方面分析了不同湿热环境下复合材料性能衰减的机制。研究表明,碳纤维/高温固化环氧树脂复合材料层间剪切性能主要是由吸湿率决定,相同吸湿率不同湿热条件下性能的下降幅度基本相同;3种湿热条件下该树脂及其复合材料未发生化学反应、微裂纹等不可逆变化,复合材料层合板湿热老化机制主要是吸入水分后基体增塑和树脂、纤维湿应变不一致导致的湿应力对复合材料性能的负面作用。     

Microscopic damage behavior in carbon fiber reinforced plastic laminates for a high accuracy antenna in a satellite under cyclic thermal loading

For a high accuracy antenna in next radio astronomy satellite, a candidate material is carbon fiber reinforced plastics (CFRP), because negative longitudinal coefficient of thermal expansion (CTE) for unidirectional CFRP enables a laminate with 0 CTE through appropriate laminate design. This enables high structural accuracy under large temperature fluctuation like space. On the other hand, when the laminate is subjected to thermal cycles, cyclic thermal stress occurs and causes microscopic damages. In this study, we characterized damage progress in CFRP laminates and resultant variation in mechanical properties under cyclic thermal loading. Three types of matrices, such as polycyanate ester, polyimide and epoxy resin were used to prepare CFRP laminates. Specimens were subjected to thermal cycles from ?197°C to 120°C. The test was periodically stopped for surface observation and flexural loading. Transverse cracks in 90° plies accumulated with thermal cycles, whereas flexural modulus remained constant. We also numerically evaluated temperature gradient and resultant thermal stress distribution during cooling by finite element analysis. The result indicates higher transverse stress appeared in the surface of the specimen and saturated to constant value which corresponded with the value calculated based on classical lamination theory.     

Fabrication of Microchanneled Composites by Novel Selective Polymer Degradation

In this research a new low-cost, highly compatible method is proposed and demonstrated to create microchannels within carbon fiber reinforced polymeric (CFRP) composite laminates that caused a lower mechanical loss due to their presence. In it, microchannels were created within the CFRP composite laminate by selective degradation of the specially selected polymer, whose solid preforms were placed at specific locations within dry fabric layers during composite manufacturing by resin infusion. Interlaminar shear (ILSS) and three-point-bend flexural tests were carried out on CFRP composite laminates with and without microchannels of different diameters to assess their effect on structural strength. The results showed that inclusion of microchannels within the CFRP composite laminates decreased their ILSS and flexural strength, which decreased steadily with the increase in channel diameter. The mechanism for these observed results was found to be the creation of resin-rich areas, microchannels and lessened fiber content by the addition of microchannels. These mechanical testing results were compared with the results of CFRP composite laminates with microchannels, inserted by hollow glass tubes (HGTs), and it was found that the new applied strategy was quite effective in introducing microchannels within CFRP composite laminates with reduced mechanical loss and provided more space for additional functionalities.     

高温环境下碳纤维增强树脂复合材料的层间力学性能老化行为与失效预测

为了研究碳纤维增强树脂(CFRP)复合材料层间力学性能在高温环境中的老化失效行为,设计了CFRP复合材料层间拉伸和层间剪切实验,在高温(80℃)环境中进行0(未老化)、 120 h、 240 h、 360 h、 480 h、 600 h和720 h的老化测试,分析CFRP层间失效强度和失效形式随老化时间的变化规律,得到随高温老化的二次应力准则响应面。建立CFRP复合材料层间力学性能预测模型,得到不同老化衰减系数下的退化模型,并通过CFRP复合材料层间仿真模型进行了验证。结果表明:随着高温老化时间的增加,层间拉伸和层间剪切强度总体上都发生了一定程度的退化,层间拉伸时更容易发生碳纤维丝剥离,层间剪切发生局部的树脂剥离,纤维之间的分层更加明显,高温老化使树脂与纤维丝的界面结合力显著下降。通过CFRP复合材料层间力学性能随高温老化的二次应力准则,计算不同老化时间后的内聚力模型参数,预测CFRP复合材料在高温老化条件下的层间强度,发现仿真与实验误差小于10%,说明了CFRP复合材料层间失效预测模型的准确性。     

高精度碳纤维增强树脂复合材料夹层天线面板热变形影响参数仿真与实验

为满足亚毫米波、太赫兹波段等高频天线反射面的应用需求,采用附加树脂修型技术制得1米级、面形精度优于10 μm均方差(RMS)的碳纤维增强树脂(CFRP)复合材料天线面板。主要开展了针对高精度CFRP复合材料面板在极端低温环境下的热变形机制研究。根据基础材料性能测试数据,建立面板的有限元仿真模型,预测大温差工况下多结构参数面板的热变形残差,分析了影响面板热变形特性的主要因素。比较了铝蜂窝和碳管阵列夹芯两种面板结构热变形特性的差异。结果表明,碳管夹芯结构面板具备更高的比刚度和热稳定性。通过仿真结构优化给出了面板的结构设计参数,并重新试制了原型面板。采用基于高精度数字摄影测量的实验方法,对铝蜂窝和碳管阵列两种夹芯结构原型面板在低温环境下的热变形误差进行了测量,通过分析实验与仿真结果的误差来源,讨论了有限元预测方法的可行性,给出了针对高精度CFRP复合材料面板设计及工艺方法的指导意见。      

含纤维波纹缺陷复合材料层合板的损伤分析

纤维波纹是复合材料层合板制备过程中的一种常见缺陷,会导致其刚度和强度显著下降,有效地预测含波纹缺陷复合材料层合板的失效强度具有显著的意义。基于此,本文采用解析的方式分别构造了纤维波纹呈正弦起伏与余弦起伏状的复合材料层合板模型。利用该模型,以Tsai-Wu准则作为失效判据,研究了一种含纤维波纹的碳纤维/环氧树脂复合材料层合板在受压情况下的损伤演化过程,得到了碳纤维/环氧树脂复合材料层合板的初始损伤强度。与有限元方法计算得到的损伤位置和损伤强度非常吻合,验证了本文算法的正确性。另外,相比于有限元方法,本文所述计算方法具有模型构造简单、计算效率高等优点,便于快速分析和确定含纤维波纹缺陷复合材料层合板的损伤位置与损伤强度。      

基于锥形量热法的典型碳纤维/环氧复合材料燃烧特性

采用锥形量热仪实验研究环氧树脂基体、T300碳纤维/环氧复合材料及T300碳纤维/环氧-泡沫层合板(上下层为T300碳纤维/环氧复合材料,中间层为4mm厚的Divinycell H60泡沫芯材)在不同火灾环境下的燃烧性能。对比分析其点燃时间、热释放速率、总烟气释放量和CO生成速率等燃烧特性参数的变化规律。利用SEM测试T300碳纤维/环氧复合材料燃烧前、后表面形貌图像和环氧树脂基体和T300碳纤维/环氧复合材料燃烧形成炭层的形貌图像,分析碳纤维在碳纤维/环氧复合材料热解、燃烧过程中的影响作用。结果表明,随热辐射强度的增加,三种实验样品的平均点燃时间均缩短,热释放速率峰值和300s内热释放速率均值均增大,峰值出现时间提前,燃烧后残余率均降低。碳纤维对环氧树脂热解和燃烧起到抑制作用,其点燃、放热及达到热释放速率峰值的时间延后,T300碳纤维/环氧-泡沫层合板中泡沫芯材的燃点较低,使其平均点燃时间、热释放速率峰值出现时间及CO开始释放时间提前。T300碳纤维/环氧复合材料和T300碳纤维/环氧-泡沫层合板燃烧后均出现明显的分层现象,力学性能丧失,整体结构被破坏。碳纤维的存在能够有效抑制碳纤维/环氧复合材料的热解及燃烧,并能有效抑制在燃烧过程中产生融滴、喷溅和大量黑烟。     

Monitoring LCM Process by FBG Sensor Under Birefringence

Abstract: Optical fibre Bragg gratings (FBG) provide accurate and non‐intrusive strain and temperature local measurements. FBG sensors can be embedded into fibrous preforms to monitor the flow and the cure of the resin and deliver real‐time information on the ongoing process. The paper concentrates on the utilisation of the strain‐induced birefringence of the FBG to derive information on the effective stress–strain state of the composite at the end of the process cycle (Vacher 2004, Optical fiber sensors to monitor the processing and the mechanical characterization of composites. PhD thesis). During the cooling phase, the reflection spectrum from the FBG splits into two peaks because of the birefringence of the glass fibre owing to the residual stress. The paper shows that this effect can be utilised to estimate the residual stress and strain in composites manufactured by Liquid Composite Moulding technologies. The birefringence effect arising from the cooling of a [0₆,90₃]_S CFRP laminate is first characterised, and then the determination of the strains along the principal axes inside the laminate is completed by modelling the local stress–strain state because of the interaction of the optical fibre and its environment within the framework of orthotropic thermo‐elasticity and the Classical Laminated Plate Theory.