The engineering aspects of automated prepreg layup: History,present and future

Highly consistent quality and cost-effective manufacture of advanced composites can be achieved through automation. It may therefore open up new markets and applications for composite products in aerospace, automotive, renewable energy, and consumer goods. Automated Tape Laying (ATL) and Automated Fibre Placement (AFP) are the two main technologies used to automate the layup of prepreg. The historical development and past research of both technologies is reviewed; with an emphasis on past issues in application and capability as well as their solution, including both thermoset and thermoplastic material layup. It is shown that past developments have moved away from simply emulating manual layup into the now unique layup procedures for ATL, and into the current AFP technology base. The state of the art for both technologies is discussed and current gaps in the understanding of both processes highlighted. From this, future research needs and developments are derived and discussed.     

嵌入式低温共固化高阻尼纤维/树脂基复合材料

通过正交试验新研制出一种可以与玻璃纤维/BA9913环氧树脂预浸料低温共固化的高阻尼黏弹性材料,提出使用四氢呋喃（THF）作为溶剂,将该高阻尼材料制成黏弹性材料溶液。采用双面刷涂工艺,将玻璃纤维/BA9913环氧树脂复合材料制成带阻尼薄膜的预浸料,按照设计的铺层根据热压罐固化工艺制成嵌入式低温共固化高阻尼复合材料试件。模态试验和层间剪切试验验证了本文所提出制作工艺和黏弹性材料组分的有效性,试件一阶模态损耗因子可达7.2%。为嵌入式低温共固化高阻尼复合材料的广泛使用奠定了基础。      

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。      

Coupled visco-mechanical and diffusion void growth modelling during composite curing

Most critical processing step during long fiber reinforced epoxy matrix composite laminate manufacturing is the polymerization stage. If not optimized, it gives birth to defects in the bulk material, such as voids. These defects are considered as possible sources of damage in the composite parts. The aim of this work is to model the evolution of void growth in thermoset composite laminates after ply collation (autoclave processes) or resin impregnation (RTM, LCM process). A coupled mechanical and diffusion model is presented to better predict the final void size at the end of polymerization. Amongst the parameter investigated, onset of pressure application and diffusive species concentration where found to have a major effect on void size evolution during curing process.     

Cure cycle optimization of composites by dielectric measurements

Cure cycle monitoring by dielectric loss factor was investigated for prepreg composites based on epoxy, epoxy-phenolic, polyimide and phenolic matrices. Dielectric loss measurements were carried out to establish optimal cure conditions for the various polymer composites with respect to testing rates, curing temperature and timing for pressure application. For each polymer composite studied, initial laboratory experiments were carried out in a temperature-programmable oven to determine the onset of polymer flow, the temperature range where resin viscosity is appropriate for pressure application and the duration of the cross-linking reaction. Subsequently, autoclave processing was conducted using similar conditions accompanied by in situ dielectric loss monitoring. Dielectric cure monitoring of room temperature aged, epoxy-based prepreg indicated that curing of aged prepregs is possible provided a flow region exists. Flexural properties of specimens prepared from composite laminates processed under optimized conditions substantiated the adequacy of in situ dielectric loss measurements for cure monitoring of prepreg composites.     

Influence of Layup and Curing on the Surface Accuracy in the Manufacturing of Carbon Fiber Reinforced Polymer (CFRP) Composite Space Mirrors

Carbon fiber reinforced polymer, CFRP, composite materials have been used to fabricate space mirror. Usually the composite space mirror can completely replicate the high-precision surface of mould by replication process, but the actual surface accuracy of replicated space mirror is always reduced, still needed further study. We emphatically studied the error caused by layup and curing on the surface accuracy of space mirror through comparative experiments and analyses, the layup and curing influence factors include curing temperature, cooling rate of curing, method of prepreg lay-up, and area weight of fiber. Focusing on the four factors, we analyzed the error influence rule and put forward corresponding control measures to improve the surface figure of space mirror. For comparative analysis, six CFRP composite mirrors were fabricated and surface profile of mirrors were measured. Four guiding control measures were described here. Curing process of composite space mirror is our next focus.     

Low-energy electron beam cured tape placement for out-of-autoclave fabrication of advanced polymer composites

The autoclave curing process for advanced polymer composites is labor and capital intensive, with the curing cost increasing dramatically by the growth in part size. In order to develop an out-of-autoclave (OOA) fabrication process for advanced polymer composites, a new process integrating automated tape placement with low-energy electron beam radiation curing was explored, by which in situ layer-wise curing of advanced composites can be achieved with the tape placement process. The irradiation process was optimized to get a homogenous curing, by tuning the electron beam dose-depth distribution in the prepreg material. Besides, the curing characteristics of the prepreg material by the low-energy electron beam irradiation was investigated and effect of exposure dose and post curing on curing degree, glass transition temperature (Tg) and interlaminar shear strength (ILSS) were characterized experimentally.     

An approach in modeling the temperature effect in thermo-stamping of woven composites

Made with high-strength continuous fibers, textile composites are of increasing interest in automotive and aerospace industries due to their high-strength/weight performance as compared to sheet metals. Nevertheless, significant reduction in manufacturing cost is required to use textile composites for mass production applications. Highly efficient thermo-stamping operations possess the potential to substantially reduce fabrication time and cost compared to the much slower autoclave forming process. In this paper, thermo-forming of woven fabric-reinforced thermo-plastic composites is simulated using a non-orthogonal material model. The temperature effect is taken into account by modifying the equivalent material properties for the composite sheet based on the contact status between the tooling and the blank. The approach is exemplified on the hemispherical thermo-stamping of a plain weave composite sheet.     

先进树脂基复合材料制造技术进展

国内先进树脂基复合材料制造技术经过30多年的发展, 已初步形成以热熔预浸料制造、 热压罐和树脂传递模塑(RTM)成型技术为代表的先进树脂基复合材料制造技术体系, 所制备的先进树脂基复合材料已在航空领域得到大量应用。本文中主要介绍国内先进树脂基复合材料热压罐成型技术、 RTM成型技术和自动铺放技术的最新进展以及先进树脂基复合材料制造过程模拟与优化技术, 讨论了国内先进树脂基复合材料制造技术的主要发展方向。     

Effects of Processing Parameters on the Forming Quality of C-Shaped Thermosetting Composite Laminates in Hot Diaphragm Forming Process

In this study, the effects of processing temperature and vacuum applying rate on the forming quality of C-shaped carbon fiber reinforced epoxy resin matrix composite laminates during hot diaphragm forming process were investigated. C-shaped prepreg preforms were produced using a home-made hot diaphragm forming equipment. The thickness variations of the preforms and the manufacturing defects after diaphragm forming process, including fiber wrinkling and voids, were evaluated to understand the forming mechanism. Furthermore, both interlaminar slipping friction and compaction behavior of the prepreg stacks were experimentally analyzed for showing the importance of the processing parameters. In addition, autoclave processing was used to cure the C-shaped preforms to investigate the changes of the defects before and after cure process. The results show that the C-shaped prepreg preforms with good forming quality can be achieved through increasing processing temperature and reducing vacuum applying rate, which obviously promote prepreg interlaminar slipping process. The process temperature and forming rate in hot diaphragm forming process strongly influence prepreg interply frictional force, and the maximum interlaminar frictional force can be taken as a key parameter for processing parameter optimization. Autoclave process is effective in eliminating voids in the preforms and can alleviate fiber wrinkles to a certain extent.     

高温老化后嵌入式共固化阻尼复合材料结构的阻尼性能

在综合研究双马来酰亚胺树脂基碳纤维预浸料(T700/QY260)和AFLAS氟橡胶的力学性能、阻尼性能和耐高温性能基础上,通过试验的方法提出一种能够耐260℃超高温度的黏弹性阻尼材料。利用四氢呋喃溶液将该黏弹性阻尼材料制成阻尼胶浆溶液,结合双面刷涂和热压罐工艺制备出嵌入式共固化阻尼复合材料试件,利用自由振动衰减实验方法对该试件分别做常温、230℃*96 H、260℃*96 H老化实验处理后相对阻尼系数的测定,得到不同温度老化处理后的嵌入式共固化阻尼复合材料的相对阻尼系数与阻尼材料厚度的关系,证明了所制备的嵌入式共固化阻尼复合材料具有优异耐超高温性能和稳定的阻尼性能。     

复合材料结构固化温度场精化模拟

以往的复合材料固化过程模拟,大多只是在简单外部条件下,或者针对厚尺寸复合材料构件进行的厚度方向的温度场模拟,而与实际复合材料的固化过程有一定的偏差。本文在考虑辅助材料、模具以及罐内强迫对流换热现象的情况下,建立了复合材料热压罐工艺固化温度场的精化模拟方法。在此基础上,针对常用航空复合材料结构以及材料体系,进行了相应的固化温度场模拟,并对结果进行了分析。     

Optimization of Parts Placement in Autoclave Processing of Composites

The main processing variable in autoclave production, besides pressure and time, is fluid temperature. The different geometry of tools and composite laminates and the fluid dynamic characteristics of each autoclave batch lead to temperature changes in the composites, during heating, soaking and cooling, not easily predicted. The soak time at maximum temperature is considered one of the most critical constraints. This time is computed for the entire autoclave batch when the last composite laminate reaches the specified cure temperature. In this work a completely different approach is presented. Areduction of cure time is achieved identifying a rule for the position of different tools inside the autoclave. An optimization model is derived by defining an objective function in terms of penalty coefficients associated to different tools and different positions into the autoclave. Test cases of the behaviour of autoclave batches have been simulated leading to significant predicted cure time reductions.     

Building Block Approach’ for Structural Analysis of Thermoplastic Composite Components for Automotive Applications

Advanced thermoplastic prepreg composite materials stand out with regard to their ability to allow complex designs with high specific strength and stiffness. This makes them an excellent choice for lightweight automotive components to reduce mass and increase fuel efficiency, while maintaining the functionality of traditional thermosetting prepreg (and mechanical characteristics) and with a production cycle time and recyclability suited to mass production manufacturing. Currently, the aerospace and automotive sectors struggle to carry out accurate Finite Elements (FE) component analyses and in some cases are unable to validate the obtained results. In this study, structural Finite Elements Analysis (FEA) has been done on a thermoplastic fiber reinforced component designed and manufactured through an integrated injection molding process, which consists in thermoforming the prepreg laminate and overmolding the other parts. This process is usually referred to as hybrid molding, and has the provision to reinforce the zones subjected to additional stresses with thermoformed themoplastic prepreg as required and overmolded with a shortfiber thermoplastic resin in single process. This paper aims to establish an accurate predictive model on a rational basis and an innovative methodology for the structural analysis of thermoplastic composite components by comparison with the experimental tests results.     

纤维增强热塑性树脂预浸料的制备工艺及研究进展

热塑性复合材料因冲击韧性高、环境适应性强、可回收利用等优点,被广泛应用于汽车制造、航空航天、国防军工等领域。但因热塑性树脂加热熔融后较高的黏度使其很难与纤维充分浸渍。预浸料作为制造复合材料的中间材料,现阶段制备工艺已相对成熟,预浸料中纤维已被树脂浸润,因此通过预浸料制备的复合材料孔隙率较低。本文介绍了现阶段常用的热塑性预浸料制备方法及各自的优缺点,包括溶液浸渍法、熔融浸渍法、粉末浸渍法、薄膜叠层法、纤维混杂法以及反应链增长浸渍法。阐述了热塑性树脂熔体浸润纤维的浸渍机理,对浸渍机理的部分研究成果进行了概括。概述了浸渍温度、浸渍压力和牵引速率对预浸带性能的影响。最后指出了国内预浸料生产中存在的主要问题,未来可采用多学科结合、纤维树脂改性、对浸渍过程进行计算机模拟等方法促进热塑性预浸带的产业化发展。     

Effect of Lamina Thickness of Prepreg on the Surface Accuracy of Carbon Fiber Composite Space Mirrors

Composite space mirror can completely replicate the high-precision surface of mould by replication process, but the actual surface accuracy of the replication composite mirror always decreases. Lamina thickness of prepreg affects the layers and layup sequence of composite space mirror, and which would affect surface accuracy of space mirror. In our research, two groups of contrasting cases through finite element analyses (FEA) and comparative experiments were studied; the effect of different lamina thicknesses of prepreg and corresponding lay-up sequences was focused as well. We describe a special analysis model, validated process and result analysis. The simulated and measured surface figures both get the same conclusion. Reducing lamina thickness of prepreg used in replicating composite space mirror is propitious to optimal design of layup sequence for fabricating composite mirror, and could improve its surface accuracy.     

A composite cost model for the aeronautical industry: Methodology and case study

This paper presents a novel composite production cost estimation model. The strength of the model is its modular construction, allowing for easy implementation of different production methods and case studies. The cost model is exemplified by evaluating the costs of a generic aeronautical wing, consisting of skin, stiffeners and rib feet. Several common aeronautical manufacturing methods are studied. For studied structure, hand layup is the most cost-effective method for annual volumes of less than 150 structures per year. For higher production volumes automatic tape layup (ATL) followed by hot drape forming (HDF) is the most cost-effective choice.     

热压釜成型工艺工时估算的理论模型

大部分复合材料新产品的制造成本取决于早期设计阶段,因此应用一个统一的成本估算模型来估算制造成本对设计者来说具有重要的指导作用。针对先进复合材料制造工艺,总结了两种制造工艺时间的估算近似方法:幂定律近似和一级速度反应模型(一阶模型)近似。以热压釜成型工艺生产板材作为实验,应用最小二乘法将所得数据进行幂定律拟合和一阶模型拟合,结果表明,两种方法拟合结果非常一致。一阶模型具有物理可解释性,因此对新的设计和改进工艺,应用一阶模型比较理想。     

PEEK基体热塑性树脂基复合材料的研究

介绍了热塑性树脂基复合材料用ＰＥＥＫ树脂的性能，静电粉末法制备热塑性树脂预浸料的设备和工艺，用该工艺制备的预浸料规格和性能以及ＡＳ４Ｃ单向织物／ＰＥＥＫ复合材料的力学性能，韧性，耐环境性能，同时还介绍了将这种材料用于宇航工业而进行的基础研究工作。     

The effect of thermal cycles on the mechanical properties of fiber–metal laminates

The effect of thermal-shock cycles on the mechanical properties of fiber–metal laminates (FMLs) has been evaluated. FML plates were composed by two AA2024 Al sheets (1.6 mm thick) and one composite ply formed by two layers of unidirectional glass fiber epoxy prepreg and two layers of epoxy adhesive tape of glass fiber reinforced epoxy adhesive. The set was manufactured by hand layup and typical vacuum bag technique. The curing cycle was in autoclave at 125 ± 5 °C for 90 min and an autoclave pressure of 400 kPa. FML coupons taken from the manufactured plate were submitted to temperature variations between −50 and +80 °C, with a fast transition between these temperatures. Tensile and interlaminar shear strength were evaluated on samples after 1000 and 2000 cycles, and compared to nonexposed samples. 2000 Cycles corresponds to typical C Check interval for commercial aircraft maintenance programs. It was observed that the thermal-shock cycles did not result in significant microstructural changes on the FML, particularly on the composite ply. Similarly, no appreciable effect on the mechanical properties of FML was observed by the thermal-shock cycles.