热压罐零吸胶工艺树脂压力在线测试及其变化规律

针对碳纤维缎纹布/环氧914预浸料热压罐零吸胶工艺,采用热压成型过程树脂压力在线测试系统监测树脂压力的大小与分布,分析了真空、外加气压对树脂压力的作用规律,通过显微观察研究了真空及外加气压对孔隙缺陷的影响。实验结果表明,所采用的在线测试系统可以定量分析真空在铺层内的作用程度和树脂压力的变化;零吸胶工艺树脂承担了大部分外压且沿层板厚度及面内方向分布均匀;真空通过铺层内的气路通道排出夹杂空气,其作用程度受到树脂黏流状态和铺层密实程度的影响;不同压力条件下复合材料层板孔隙状况与树脂压力的测试结果相吻合。     

L形层板真空袋成型缺陷的实验研究

采用真空袋阳模成型法在不同条件下制备了90°的L形玻纤单向布/环氧树脂层板, 对层板不同位置处纤维密实和缺陷状况进行了研究, 考察了成型过程主要工艺条件对缺陷的影响规律。结果表明, 富树脂、 孔隙、 厚度分布不均和纤维屈曲变形是L形层板中主要的缺陷类型, 加压时机、 层板尺寸、 铺层方式以及边界条件对纤维密实和缺陷的形成都有重要的影响。对以上各种缺陷的产生机制进行了初步分析: 剪切流动的存在导致层板厚度分布不均匀而且出现富树脂区; 纤维的屈曲变形是由于轴向受压缩力; 本文实验条件下孔隙的主要来源是夹杂空气。研究结果对热压工艺中缺陷的预测与控制以及工艺参数的优化具有重要的指导意义。      

硅橡胶热膨胀工艺预浸料铺层内树脂压力变化规律

采用硅橡胶热膨胀工艺制备了碳纤维/双马树脂复合材料层板, 通过自行设计的成型模具及树脂压力在线测试系统测试并分析了成型过程中热胀压力和预浸料铺层内树脂压力的变化规律, 考察了工艺间隙和温度分布的影响, 并通过显微观察分析了不同工艺条件下层板的密实状况。结果表明: 采用树脂压力在线测试系统, 可实现热膨胀工艺预浸料铺层内树脂压力的测试; 工艺间隙和硅橡胶内的温度分布对树脂压力及硅橡胶的热胀压力有重要影响, 在零吸胶工艺条件下, 当工艺间隙设计合理时, 凝胶前热胀压力和树脂压力的变化趋势及变化程度基本一致, 固化层板纤维密实并且厚度均匀; 通过增加恒温平台减小硅橡胶内部温差, 可使热胀压力的增加速度减小。      

复合材料等厚层板热压成型中树脂流动过程数值模拟

树脂基复合材料热压成型过程中树脂流动在很大程度上决定着层板纤维含量、 孔隙含量以及层板尺寸 , 根据有效应力原理与达西渗流定律建立了描述复合材料等厚层板热压成型过程树脂流动与纤维密实的数学模型 , 采用有限单元方法实现了热压成型中纤维密实均匀状况的预报。分析了温度边界条件、 铺层方式对树脂流动过程的影响。结果表明: 温度边界条件对计算结果影响比较大 ; 铺层方式对层板厚度以及纤维体积分数分布规律影响非常大 ; 边界条件以及材料参数的准确性直接影响计算结果的可靠性。以 T700S/环氧 5228单向层板为例进行了实验验证 , 结果表明计算与实验结果的一致性非常好。      

复合材料变厚层板热压成型缺陷类型与成因实验研究

采用热压机工艺与热压罐工艺两种成型方法制备了玻璃纤维/环氧 648 变厚度层板 , 研究了两种工艺下缺陷的形成机制及铺层方式和变厚梯度对缺陷程度和分布的影响。结果表明 : 纤维分布不均、 富树脂、 分层是主要缺陷类型 , 其中纤维分布不均由树脂二维流动引起 , 并与纤维不连续区、 纤维层渗透特性以及外压的均匀性有关; 富树脂主要是纤维的不连续性造成的 ; 而分层缺陷与纤维分布和热膨胀各向异性紧密相关。研究结果对变厚度复合材料层板的缺陷消除和成型质量控制有重要的指导意义。      

T形加筋板热压罐成型过程压力分布与树脂流动实验研究

针对飞行器复合材料常用加筋板结构,采用胶接共固化整体工艺成型T形加筋板。采用自行建立的压力测试方法测试了 T形加筋板在热压罐成型过程的压力分布,通过吸胶量、筋条厚度的检测,分析了树脂在筋条内的流动形式,研究了树脂流动的影响因素及影响规律。结果表明：筋条不同部位明显存在压力分布不均,在压力差作用下树脂发生明显的面内流动,易产生富脂、厚度不均等缺陷,导致筋条拐角较厚,约是突缘和腹板厚度的1.1~1.4倍,模具组合方案、曲率半径、填充料含量明显影响树脂面内流动和纤维密实程度。     

L 形复合材料层板热压工艺密实变形过程的数值模拟

基于 Biot 固结原理和达西定律 , 建立了二维树脂流动与纤维密实模型 , 采用有限元方法实现了 L 形层板热压成型过程树脂压力分布、 层板变形的预测。通过对 AS4 炭纤维/环氧 350126 等厚层板厚度变化的模拟结果与实验数据的对比分析 , 证明了数学模型和有限元程序的可靠性。以阳模成型 90° 铺层 S22玻璃纤维/环氧 648L 形层板为例 , 对工艺过程层板厚度变化进行了分析。模拟结果表明 : 剪切模量对拐角以及拐角与平板过渡区域的变形影响较大 ; 平板长度对拐角区域变形影响较明显 , 对平板区的变形影响较小。采用热压罐制备了 90° 铺层S22玻璃纤维/环氧 648阳模成型 L 形层板 , 实验数据表明 , 固化后层板呈现拐角区厚、 平板区薄的厚度不均现象 , 并且平板长度对拐角区厚度变化影响较显著 , 这与数值预测结果具有较好的一致性。     

复合材料层板热压工艺参数的分析与优化

在热固性树脂基复合材料热压成型过程中,外加压力和加压时机是决定层板厚度、纤维含量以及孔隙含量的两个主要因素.基于复合材料热压成型过程树脂流动模型,采用遗传算法,根据固化层板纤维体积分数的要求,对单向和正交两种铺层形式的T700/5228和T700/5224层板加压时机进行了分析.以航空航天应用的典型纤维含量为准,对优化得到的加压时机以及不同工艺条件下固化层板内纤维分布特点进行了分析.结果表明,纤维、树脂种类相同,铺层方式不同,加压时机差别很大;纤维种类、铺层方式以及初始和优化目标相同的条件下,不同树脂体系,加压时刻树脂粘度基本相同;层板内纤维分布均匀性主要由纤维层压缩特性决定.采用本文建立优化方法,可以快速地得到满足目标纤维含量要求的加压时机,具有重要的学术价值和工程应用意义,有助于降低成本,缩短复合材料研制周期.     

基于树脂流动的变截面复合材料结构固化过程热-流-固多场强耦合数值仿真

在考虑树脂流动对固化温度场影响的基础上,将树脂流动引入经典热-化学模型,并在考虑了固化过程材料性能时变特性条件下,建立了复合材料热-流-固多场强耦合有限元模型。通过对比文献中未考虑树脂流动对温度场的影响,本文所建模型温度场较实际结果的最大温差更低,厚度密实精度更高,模型可靠性更好。基于所建热-流-固强耦合有限元模型,对变截面复合材料结构固化过程进行数值仿真。研究发现,变截面复合材料结构较厚区域存在明显温度场、固化度场及树脂流场分布梯度,纤维体积分数分布不均性较大,这与结构不同区域的厚度、固化过程温度传递滞后及局部树脂流动受固化效应不同步产生的影响有关。变截面复合材料结构厚度由3.52 mm增加至42.24 mm,截面最大温差由0.3℃增加到34.3℃,纤维体积分数分布不均匀性由0.1%增加到1.3%。     

采用薄膜传感器的树脂基复合材料热压罐工艺密实压力测试方法

针对树脂基复合材料层板热压罐成型工艺,采用薄膜压力传感器建立了密实压力在线测试系统,用于监测成型过程中复合材料所受密实压力的大小和分布。研究了密实压力测试系统在热压罐工艺条件下的适用性,在此基础上以该系统为测试手段,研究了热压罐工艺下L形碳纤维/环氧树脂复合材料层板的密实压力变化规律及模具形式的影响。结果表明: 所建立的密实压力测试系统具有较高的准确性和动态响应性,能够测试高温条件及曲面位置的密实压力,满足复合材料热压罐成型过程中密实压力的在线测试要求; L形复合材料层板成型过程中拐角区与平板区的密实压力随热压罐压力增大而增加,但增加速度和最终大小不同,阳模成型时拐角区密实压力高于平板区,阴模成型时拐角区密实压力小于平板区和外加压力,表明曲面结构与平板结构的密实行为具有差异性。     

Influence of fabric structure and thickness on the ballistic impact behavior of Ultrahigh molecular weight polyethylene composite laminate

This paper presents the influence of fabric structure and thickness on the ballistic impact behavior of Ultrahigh molecular weight polyethylene (UHMWPE) composite laminate. UHMWPE composite laminates, reinforced by three kinds of fabric structures, unidirectional prepreg, 2D plain-woven and 3D single-ply orthogonal woven fabrics, were fabricated via hot pressing curing process. Through a series of standard ballistic tests, we demonstrated that unidirectional composite laminates exhibit higher ballistic impact velocity and absorbed energy capacity compared to others. A bi-linear relationship was found between the ballistic limit velocity and specimen thickness. Furthermore, the dominant failure mechanisms of unidirectional composite laminates were identified to be plugging and hole friction for thin laminates, whereas delamination, fiber tension and bulging for thick ones.     

Numerical and Experimental Study on the Effect of Lay-Up Type and Structural Elements on Thickness Uniformity of L-Shaped Laminates

Based on the two-dimensional resin flow and fiber compaction model developed by our group, we studied the cured laminate thickness uniformity of the L-shaped CF/BMI resin laminates and the effects of lay-up type and structural elements on it. Both the simulated and experimental data showed that the quasi-isotropic laminate thickness was more uniform than that of the [90°]_n laminates and the cured thickness of laminates molded by rigid convex tool was more uniform than that molded by the rigid concave tool. Lay-up type has a great influence on the cured laminate thickness uniformity. For the quasi-isotropic laminates, the structural elements, such as curvature radius, flat part length, and the number of plies, did not have much influence on the cured laminate thickness uniformity in the studied scope. For the [90°]_n laminates, the corner radius has a larger effect on the corner consolidation in comparison with the flat part length and the number of plies. According to the simulated results, resin pressure and consolidation time were largely affected by the lay-up type, due to the different permeability and compressibility. The rich resin defect was observed in the metallographic photos of the corner region of the [90°]_n laminates fabricated with the rigid concave tool, which demonstrated that the resin flow in the laminates played an important rule and validated the numerical prediction. Good agreement between the simulated results and experimental data demonstrated the reliability and universality of the numerical simulation method. These results are greatly helpful for the control of defects in angle-bended laminates and the optimization of cure cycle in autoclave process.     

VARI工艺成型纤维增强树脂复合材料层合板厚度和纤维体积分数的影响因素

分析了影响真空辅助成型技术（VARI）工艺成型复合材料的纤维体积分数和厚度均匀性的关键因素,即VARI成型工艺的树脂流动控制形式、纤维预制体状态、织物状态、树脂黏度,通过试验分析了各因素对VARI成型复合材料厚度和纤维体积分数的影响。试验结果表明,采用HFVI（high fiber-volume vacuum infusion）工艺、BA9914树脂及真空处理后的U3160单向机织物成型的纤维增强树脂复合材料层合板,其纤维体积分数和厚度均匀性能够接近预浸料/热压罐成型的复合材料制件的水平。     

A homogenization procedure for the numerical analysis of woven fabric composites

The paper presents a procedure for the numerical evaluation of the mechanical properties of woven fabric laminates. Woven fabrics usually present orthogonal interlaced yarns (warp and weft) and distribution of the fibers in the yarns and of the yarns in the composite may be considered regular. This allows us to apply the homogenization theory for periodic media both to the yarn and to the fabric. Three-dimensional finite element models are used in two steps to predict both the stiffness and the strength of woven fabric laminates. The model includes all the important parameters that influence the mechanical behavior: the lamina thickness, the yarn orientation, the fiber volume fraction and the mechanical characteristics of the components. The capabilities of the numerical model were verified studying the elastic behavior of a woven fabric laminate available in the literature and the ultimate strength of a glass fabric laminate experimentally investigated. The procedure, that can be implemented into commercial finite element codes, appears to be an efficient tool for the design of textile composites.     

超高分子量聚乙烯纤维/水性聚氨酯复合材料层压板抗软钢芯弹侵彻性能及其损伤机制

选用碳纳米粒子(CNPs)原位改性和未改性的超高分子量聚乙烯(UHMWPE)纤维作为增强纤维,水性聚氨酯(WPU)作为树脂基体,采用缠绕-复合-热压工艺制备单向(UD)正交结构的UHMWPE纤维/WPU复合材料层压板。基于X射线计算机断层扫描(CT)技术,研究UHMWPE纤维/WPU复合材料层压板在7.62 mm×39 mm软钢芯弹以弹速为(720±10) m/s侵彻下的弹道响应。结果表明,UHMWPE纤维的CNPs原位改性提高了CNPs-UHMWPE纤维/WPU复合材料层压板抗单发侵彻性能,但会降低其抗多发打击的能力。对于未被穿透的层压板,其被侵彻过程可分为三个阶段,依次为剪切冲塞、断裂破坏和剩余子层的塑性变形,且每个阶段的厚度比依次为11.51%、44.40%和44.09%;层压板的分层响应主要发生在第二阶段,并集中在弹着点附近;每发弹丸侵彻导致层压板的破坏区域包含在以弹着点为圆心、直径约为70 mm的圆内。      

Performance of stitched/unstitched woven carbon/epoxy composites under high velocity impact loading

In this paper, response of stitched/unstitched woven fabric carbon/epoxy composite laminates subjected to high velocity impact loading is discussed. Aerospace grade plain and satin weave carbon fabrics were used to manufacture the laminate using a toughened SC-15 epoxy resin system with an affordable vacuum assisted resin infusion molding process. For fabrication of stitched laminates, a 3-cord Kevlar thread was used to stitch the fabric preform in lock stitch fashion in an orthogonal grid of size 12.7 and 25.4 mm with 6 mm stitch spacing. Unstitched laminates used in the study were made of 7, 17 and 37 layers whereas the stitched laminates were made of 7 and 17 layers. Four laminates of each type were subjected to high velocity impact loading at different velocity to determine the ballistic limit. The ensuing damage was characterized through ultrasonic NDE. Results of the study indicate that the damage was well contained within the stitch grid incase of stitched laminates. However, ballistic limit was higher for the unstitched laminates. Ballistic limit increased with the increase in the thickness of the laminate. Further, satin weave laminates exhibited higher ballistic limits in most of the cases.