玻璃纤维-铝合金层板的拉伸和疲劳性能研究

对单向和正交玻璃纤维-铝合金层板的拉伸和疲劳性能进行实验和分析,利用和修正了金属体积分数理论,对两种层板的拉伸性能进行验证.通过对两种层板裂纹扩展速率及裂纹扩展形貌的研究,得到两种层板的裂纹扩展速率方程, 并对玻璃纤维-铝合金层板的裂纹扩展机理进行分析.     

玻璃纤维-铝合金正交层板的拉伸性能研究

通过对两组具有不同铺层次序的玻璃纤维-铝合金正交层板进行拉伸实验,对比研究了铺层次序对材料拉伸力学行为的影响.载荷跌落前两组试件的拉伸力学性能和应力-应变曲线基本一致,说明玻璃纤维-铝合金正交层板的拉伸力学性能与纤维的铺层次序无关.提出了修正后的金属体积分数理论,准确预测了材料的弹性模量、屈服应力及拉伸强度.依据声发射数据和试件损伤失效形貌照片,分析了两组试件的拉伸损伤失效进程.结果表明,铺层次序的不同使得两组材料的损伤进程和破坏模式具有很大差异.最后,利用有限元方法对试件的拉伸力学行为进行了模拟分析,模拟结果与实验值吻合较好.     

复合材料层板开孔拉伸损伤分析

针对纤维增强复合材料层板开孔拉伸, 将复合材料层板的失效分为层内失效和层间失效, 建立了复合材料层板开孔拉伸损伤分析模型。该模型基于逐渐损伤分析, 对不同复合材料开孔层板进行了失效预测, 并与文献试验结果进行了对比, 破坏强度和失效模式均与文献试验结果非常吻合。结果表明本文中所建立的层板开孔拉伸损伤分析模型能够模拟含孔层合板拉伸过程中的损伤起始、 损伤扩展和最终破坏模式, 并最终预测含孔层合板拉伸失效模式和破坏强度。      

含分层损伤缝合复合材料层板的剩余压缩强度

基于渐进损伤方法,研究了含单脱层缝合复合材料层板在压缩载荷下的剩余强度。通过商用软件ABAQUS建立了含单脱层缝合复合材料层板剩余压缩强度计算模型,考虑了子层屈曲和分层扩展对剩余强度的影响。通过UMAT子程序实现了层板失效、层间失效和缝线失效的模拟。通过嵌入式杆单元结构模拟了缝线桥联作用及失效。采用Hashin准则及刚度折减法对纤维拉压、基体拉压失效进行了模拟。通过渐进损伤分析,揭示了缝合情况下含单脱层复合材料层板的失效机理,讨论了缝合参数对剩余压缩强度的影响。所预测的破坏模式和剩余强度结果与实验能较好地吻合。分析表明缝合可以明显提高含分层损伤复合材料层板的子层屈曲载荷,抑制分层扩展,并提高层板的剩余压缩强度。     

含雷击热-力耦合损伤复合材料层压板拉伸剩余强度预测

为了对含雷击热-力耦合损伤复合材料层压板的剩余强度进行预测,基于连续介质损伤力学法(CDM)和唯象分析法,建立了表征复合材料雷击热-力耦合损伤的刚度矩阵渐进损伤退化模型。基于该模型,通过ABAQUS有限元仿真软件,建立了含雷击热-力耦合损伤的复合材料层压板结构三维模型。结合UMAT子程序,完成了拉伸载荷下的剩余强度预测。结果表明:通过与试验对比,仿真结果与试验结果取得了良好的一致性。本文所建立模型,能够有效进行含雷击热-力耦合损伤复合材料层压板结构拉伸剩余强度预测。     

玻璃纤维/酚醛树脂复合材料热响应预报方法玻璃纤维/酚醛树脂复合材料热响应预报方法

为研究航空复合材料在火灾环境下的热响应,考虑材料热解过程,建立了复合材料热响应方程组,推导了显式有限差分格式,研究了玻璃纤维/酚醛树脂复合材料内部瞬态热响应与碳化规律。结果表明:建立的非线性热响应方程组与计算方法能够预测玻璃纤维/酚醛树脂复合材料的温度-时间历程,800 s时的受热表面温度达到了1048℃,背面温度为226℃,与实验值吻合较好;随着材料深度增加,材料达到热解温度所需的时间更长,材料密度下降速率随之降低,碳化过程变慢;热解反应区中不同深度位置的材料剩余质量分数在同一温度下略有不同,位置越深,剩余质量分数越小,碳化程度越高;随着时间推移,发生热解的材料比重增大,碳化范围逐步扩大,热解层厚度范围也逐渐扩大。      

玻璃纤维/环氧树脂复合材料热解特性研究

采用热重-差热分析仪研究玻璃纤维/环氧树脂复合材料在空气及氮气氛围下不同升温速率的热解特性规律。结果表明,在空气气氛下,热解分为两个阶段;氮气气氛下,热解只存在一个热分解阶段,与空气气氛相比热解初始分解温度较高,热解温度范围变窄,失重速率明显变大。在两种气氛下,玻璃纤维均不参与热解。随着升温速率的增加,热解反应各阶段的起始温度、终止温度、最大失重速率温度均向高温方向移动,热解温度范围大小都基本保持不变。氮气气氛下使用Kissinger法、FWO法和Starink法计算出玻璃纤维环氧树脂的平均表观活化能分别为106.42、123.09和119.48kJ/mol。复合材料活化能随转化率的增加而升高,表观活化能保持在一定数值范围内且数值相近,热解反应比较稳定,具有较低A值,表明其具有较强的热稳定性。     

碳纤维-玻璃纤维层内混杂单向增强环氧树脂复合材料拉伸性能

采用不同混杂比的碳纤维-玻璃纤维层内经向混编单轴向织物制备了混杂纤维增强环氧树脂复合材料, 研究了不同混杂结构和不同混杂比的碳纤维-玻璃纤维/环氧树脂复合材料拉伸性能的变化及破坏形式。0°拉伸结果表明:同种混杂织物的不同混杂结构中, 碳纤维相对集中的完全对齐结构强度最高, 不同混杂比织物的完全对齐结构强度相当;碳纤维-玻璃纤维/环氧树脂复合材料的模量遵循混合定律。90°拉伸结果表明:纤维与树脂间的界面结合强度为碳纤维/树脂>玻璃纤维/树脂, 碳纤维-玻璃纤维/环氧树脂复合材料的强度、模量与材料厚度方向上界面的不同形式(单一或交替界面、碳纤维或玻璃纤维的分布位置等)有关, 与碳纤维的含量基本无关。      

低温暴露对碳纤维/环氧树脂复合材料拉伸力学性能的影响

针对低温暴露对碳纤维/环氧树脂(CF/EP)复合材料力学性能影响进行研究,对低温0℃、?20℃、?40℃、?60℃暴露100 h、200 h、300 h、400 h、500 h后,对CF/EP的复合材料拉伸力学性能影响展开研究,利用SEM电镜扫描分析损伤机制,根据试验结果提出了一种预测CF/EP复合材料低温暴露后剩余强度的预测公式。试验结果表明,在长时间低温暴露后,CF/EP复合材料拉伸强度随低温暴露时间的增长呈现出先增后降的趋势;低温暴露时间低于300 h时,CF/EP复合材料拉伸强度随温度下降先增后降,暴露时间高于300 h后,拉伸强度随温度下降逐渐降低;CF/EP复合材料拉伸弹性模量随低温暴露时间的增长呈现逐渐上升趋势,温度越低,上升趋势越明显。SEM结果表明,低温暴露后,纤维与环氧树脂黏结程度增强,有利于荷载传递,CF/EP复合材料拉伸强度增大,破坏形貌上表现为纤维上包裹更多树脂;长时低温暴露后,由于纤维与基体收缩系数不同导致微裂纹产生,在受到荷载时裂纹进一步扩散,不利于荷载传递,使拉伸强度下降,破坏形貌上表现为纤维成束凝集,纤维束间距增大。基于初始试验,本文提出了一种基于初始试验的CF/EP复合材料低温暴露后剩余强度预测模型,试验与预测结果吻合较好,由于考虑了同种材料在不同低温和暴露时间耦合作用下的等效作用,可减少相同材料在不同低温与暴露时间下的试验次数,因此具备一定参考价值。      

Tensile behavior of glass/epoxy laminates at varying strain rates and temperatures

In the present work tensile tests at different strain rates and temperatures were performed in glass fiber reinforced polymer (GFRP). It is observed that such kind of composite presents an elasto–viscoplastic behavior – the rate dependency only occurs for loading levels above a given elasticity limit. Strain rate strongly affects the ultimate tensile strength (σ_u) and the modulus of elasticity is almost insensitive to it while temperature only influences the modulus. Analytical expressions to predict the modulus of elasticity and (σ_u) as a function of the temperature and strain rate are proposed and compared with experimental data showing a reasonable agreement.     

含半穿透损伤层合板挖补修理后的拉伸性能

对含半穿透损伤层板挖补修理后的拉伸性能进行了试验研究, 结果表明修理试件的拉伸强度和破坏模式随挖补斜度的变化出现显著差异。对修理试件的拉伸性能进行了有限元模拟, 计算得到的极限强度和破坏模式与试验结果吻合良好。数值模型计算结果表明, 挖补斜度是修理试件最重要的设计参数, 其对试件的极限强度、 破坏模式及修理/未修理子层间界面损伤均有显著影响。研究结论可以为含半穿透损伤层板的挖补修理设计提供理论指导。     

含半穿透损伤层合板挖补修理后的拉伸性能

对含半穿透损伤层板挖补修理后的拉伸性能进行了试验研究,结果表明修理试件的拉伸强度和破坏模式随挖补斜度的变化出现显著差异.对修理试件的拉伸性能进行了有限元模拟,计算得到的极限强度和破坏模式与试验结果吻合良好.数值模型计算结果表明,挖补斜度是修理试件最重要的设计参数,其对试件的极限强度、破坏模式及修理/未修理子层间界面损伤均有显著影响.研究结论可以为含半穿透损伤层板的挖补修理设计提供理论指导.     

Mechanical and thermal behavior of non-crimp glass fiber reinforced layered clay/epoxy nanocomposites

Mechanical and thermal properties of non-crimp glass fiber reinforced clay/epoxy nanocomposites were investigated. Clay/epoxy nanocomposite systems were prepared to use as the matrix material for composite laminates. X-ray diffraction results obtained from natural and modified clays indicated that intergallery spacing of the layered clay increases with surface treatment. Tensile tests indicated that clay loading has minor effect on the tensile properties. Flexural properties of laminates were improved by clay addition due to the improved interface between glass fibers and epoxy. Differential scanning calorimetry (DSC) results showed that the modified clay particles affected the glass transition temperatures (T_g) of the nanocomposites. Incorporation of surface treated clay particles increased the dynamic mechanical properties of nanocomposite laminates. It was found that the flame resistance of composites was improved significantly by clay addition into the epoxy matrix.     

A continuum damage model for glass/epoxy laminates in tension

The present work is concerned with the study of the damage behaviour of a composite material based on glass fibre reinforced polymer (GFRP). The main goal is to predict the rupture force using model equations that combine enough mathematical simplicity to allow their usage in engineering problems with the capability of describing a complex nonlinear mechanical behaviour. A model for tensile developed within the framework of Continuum Damage Mechanics that accounts for the effect of the load rate and temperature of the system is proposed and analyzed. The predicted values of tensile stress for different values of the load rate and temperature are compared with experimental data, showing a good agreement.     

Interlaminar shear behavior of unidirectional glass fiber (U)/random glass fiber (R)/epoxy hybrid and non-hybrid composite laminates

The interlaminar shear behavior of unidirectional glass fiber (U)/random glass fiber (R)/epoxy hybrid composites was studied with short beam shear bending test. Random glass fiber (R)/epoxy means chopped fiber composite having short discontinuous fiber randomly dispersed in epoxy matrix. The effect of stacking sequence and unidirectional glass fiber relative volume fraction (V_fU/V_fT) on the interlaminar shear strength (ILSS) of the manufactured composites has been investigated experimentally and theoretically. The laminates were fabricated by hand lay-up technique with 5 plies. Two non-hybrid composite laminates [R]₅ and [U]₅ were fabricated using the same fabrication technique for the comparison purpose. The average thickness of the manufactured laminates is 5.5 ± 0.2 mm and the total fiber volume fraction (V_fT) is 37%. Failure modes of all specimens were investigated. Experimental results indicated that the ILSS of [U]₅ is higher than those of hybrid and [R]₅ composite. Hybrid composites have higher ILSS than that of random composites. The stacking sequence and (V_fU/V_fT) ratio have a detectable effect on ILSS of the investigated composites.     

碳纤维/环氧树脂复合材料-铝合金层合板深拉成型特性

碳纤维增强树脂复合材料（Carbon fiber reinforced plastic,CFRP）因其轻质高强的特点,越来越多地应用到汽车轻量化设计和制造中。为研究CFRP板件及CFRP-Al层合板深拉成型影响因素,加速CFRP零部件产业化进程,本文通过DSC测试分析了CFRP预浸料的固化放热过程,以此为依据,用热压罐制备了不同后固化温度下成型的CFRP板材及单向、编织两种预浸带铺层的CFRP-Al层合板,用Inspekt table 100材料试验机对上述两种板材分别做了深拉试验。考虑到提高制备效率,用打磨、打磨+涂覆硅烷偶联剂、阳极氧化+涂覆硅烷偶联剂三种方式对铝合金板进行表面处理,不经热压罐固化成型,直接和正交对称铺层的单向预浸带一起在Inspekt table 100材料试验机的环境箱中混合温深拉,固化成形。并通过金相显微镜、SEM进行显微组织观察,验证后固化温度、深拉环境温度、预浸带的种类对CFRP板材及CFRP-Al层合板深拉成型性能的影响及铝合金板表面处理方式对CFRP叠层预浸带、铝合金板材混合温深拉成型性能的影响。结果表明,适当降低后固化温度、提高深拉环境温度有利于板材二次深拉成型。编织预浸带较单向预浸带能更好地承受压力,深拉成型质量更优。阳极氧化+涂覆硅烷偶联剂的表面处理方式一方面能在铝合金板材表面形成致密、均匀的微孔,另一方面硅烷偶联剂能很好地促进铝合金板材和CFRP的界面结合,有利于深拉成型。      

Characterization of fatigue damage in long fiber epoxy composite laminates

A study of damage characterization of a GFRC laminate is presented here. Forty fatigue tests were executed and S–N curves traced. Two parameters were chosen to monitor damage evolution during each test: stiffness and dissipated energy per cycle. Moreover, the presence of three zones in graphs of processed data can be observed and it is evident that the most important structural transformations take place only in the very final part of life. Adopting a continuum mechanics approach, the degradation through the whole life in composite is evaluated and it is shown that the two parameters are strictly related to damage state of composite material. A method for predicting the remaining life in a GFRC is here proposed.     

不同环境下宽径比对碳纤维增强环氧树脂复合材料开孔层压板压缩失效的影响

复合材料结构强度的参数影响研究是结构设计的必要内容,然而还缺乏在不同湿热环境条件下结构尺寸对其强度的影响研究。采用数值和试验方法研究了宽径比（W/D）对不同湿度、温度时T800/X850碳纤维增强环氧树脂复合材料（CF/EP）开孔层压板压缩强度的影响。设计了参数影响研究试件,通过试验获得了不同湿热条件下的开孔层压板压缩失效结果;并利用现有的考虑湿热影响的复合材料渐进损伤方法,建立了湿热及几何参数影响的渐进损伤模型,通过将预测结果与试验结果对比验证了模型正确性。进一步结合试验和数值分析,揭示了不同湿热条件下几何参数的影响规律。研究表明:湿热环境对T800/X850 CF/EP开孔板的压缩失效载荷影响显著,相比于室温干态（RTD）,室温湿态（RTW）和高温湿态（ETW）压缩失效载荷分别下降了7.75%和14.68%; RTW和RTD失效形式接近,ETW失效形式不同且失效面积更大; RTW和RTD时压缩失效强度随W/D的增大而增大,增大速度相似,ETW增大速度比前两者慢。      

Residual strength distribution of impacted glass/epoxy laminates with embedded shape memory alloy at low temperature

This paper evaluated the strength reduction and probabilistic behaviors of the residual flexural strength for impacted glass/epoxy laminates with embedded shape memory alloy (SMA) wires at various temperatures. A series of impact tests were performed on base (glass/epoxy laminates without SMA wires) and SMA laminates (glass/epoxy laminates with embedded SMA wires) at temperatures of 293 K, 263 K and 233 K. Three point flexural tests were then carried out so as to investigate the post-impact strength at the aforementioned temperatures. Strength reduction behavior of impacted laminates could be described by Caprino’s residual strength prediction model. A probabilistic model was developed in order to estimate the variation in residual strength of the impacted laminates with temperature. As the temperature decreased, the variation in residual strength increased due to the embrittlement of the constituent materials of the laminates at lower temperatures. When compared to the base laminates, the SMA laminates exhibited a higher variation in residual strength, especially at lower temperatures.