Impact damage and hygrothermal effects on fatigue bending strength of orthotropy composite laminates

This paper focuses on fracture mechanisms experimentally based on the scanning acoustic microscope (SAM) when subjected to impact damages, i. e., foreign object damages (FOD), and also on the influence of impact damages and hygrothermals on residual fatigue bending strength of CFRP laminates. Composite laminates used in the experiments are CF/Epoxy orthotropy laminated plates, [0₄/90₄]_s. A steel ball launched by an air gun impacts on CFRP laminates to generate impact damages. Bending fatigue tests are periodically interrupted for a nondestructive evaluation (NDE) measurement of the progressive damages to build the fracture mechanism based on impact damages, and three-point fatigue bending tests are carried out to investigate the influence of hygrothermals on the effect of the residual bending fatigue strength of CFRP laminates.     

Impact damages and residual bending strength of CFRP composite laminates subjected to impact loading

The purpose of this study is to confirm the decreasing in residual bending strength, and the failure mechanisms experimentally when CFRP composite laminates are subjected to foreign object damage (FOD). Composite laminates used in this test are CFRP orthotropic laminated plates, which are stacked with two-interfaces [0^o ₆/90^o ₆] _sym and four-interfaces [0^o ₃/90^o ₆/0^o ₃] _sym . When the specimen was subjected to transverse impact by a steel ball, the delamination area generated by the impact damage was observed by using the SAM (scanning acoustic microscope). Also, the fracture surfaces obtained by three-point bending test were observed by using the SEM (scanning electron microscope). Further, failure mechanisms were investigated based on the observed delamination areas and fracture surfaces.     

Interlaminar fracture toughness of CFRP laminates with silk fibers interleave

Interlaminar fracture toughness of CFRP laminates with silk fibers interleave was evaluated in this paper. Silk fibers were obtained from silkworm cocoon. Long silk fibers were wound around a bobbin and cut into specimen size. Resin films were bonded on both sides of a sheet of silk fibers. Silk fibers with resin films were put between [0₁₂] and [0₁₂] and cured by following the curing process. Evaluation of mode I and mode II interlaminar fracture toughness was accomplished by DCB and ENF test, respectively. Mode I interlaminar fracture toughness of CFRP laminates with silk fibers interleave was 59% higher than that of CFRP. Mode II interlaminar fracture toughness of CFRP laminates with silk fibers interleave was 44% higher than that of CFRP. It seems that CFRP laminates with silk fibers interleave will be useful to structures which need high interlaminar fracture toughness.     

Characterization of the residual mechanical properties of woven fabric reinforced composites after low-velocity impact

An investigation is undertaken to examine the residual mechanical properties of crowfoot-weave carbon/epoxy laminates subjected to a transverse central low-velocity impact load. It is found that the residual strength and stiffness of impacted laminates decrease with increasing impact damage area. Experimental data indicates that flexural stress constitutes the basis of a failure criterion that also describes damage severity, if localized damage at the region of impact is not serious. By formulating a simple model involving the motion of a rigid impactor, together with fundamental stress analysis of a transversely loaded plate, the effects of impactor mass, impact velocity, impactor tip radius, laminate thickness and lay-up on low-velocity impact damage are identified. Based on the experimental observations, it is found that the residual mechanical properties can be approximated by a linear relationship with a single damage severity parameter Q, where Q is a function of incident impact energy, impactor tip radius and laminate thickness. The theoretical results are verified by experimental data.     

Fatigue damage of quasi-isotropic composite laminates under tensile loading in different directions

The purpose of this work is to investigate fatigue damage of quasi-isotropic laminates under tensile loading in different directions. Low cycle fatigue tests of [0/−60/60]_s laminates and [30/−30/90]_s laminates were carried out. Material systems used are AS4/Epoxy and AS4/PEEK. The fatigue damage of [30/−30/90]_s is very different from that of [0/−60/60]_s. The experimental results are compared with the result obtained from the method for determining strain energy release rate components proposed by the authors. The analytical results were in good agreement with the experimental results. It is proved that the failure criterion based on the strain energy release rate is an appropriate approach to predict the initiation and growth of delaminations under cyclic loading.     

Bending fatigue strength of case-carburized helical gears with large helix angles up to 40 degrees

Case-carburizing of helical gears with large helix angles may form too large hardened layers near the tooth width end on the acute angle side (ACUTE-END), and adversely affect the bending fatigue strength. We investigated the bending fatigue strength of casecarburized helical gears with large helix angles up to approximately 40° through a bending fatigue test, hardness test, and residual stress measurement. We found that the case-carburizing formed large hardened layers near ACUTE-END, reduced the compressive residual stress near ACUTE-END, and restricted the improvement of the bending fatigue strength in a meshing state where tooth root stress became large near ACUTE-END. Based on the obtained bending fatigue limits, we revealed that ISO 6336-3:2006 overestimated the rate of increase of the permissible circumferential loads for helix angles exceeding approximately 30°, and ISO/DIS 6336-3:2018 underestimated this rate for helix angles near 30°.

     

Evaluation of material properties and internal damage within CFRP and CFRP/Al sandwich panels due to impact loading

In the present paper, damage development within Carbon fiber reinforced plastic (CFRP) laminates and CFRP/Aluminum (Al) honeycomb core sandwich panels by impact loading was evaluated, and change in material properties due to the damage development was investigated. Falling weight impact tests, 3-point bending tests and cross-sectional observation were carried out. As results, it is found that falling rate of bending elastic modulus due to internal damage in the laminate only is lower than that in the upper face-sheet of the sandwich panel, and that difference in the falling rate between them becomes maximum at the impact energy of 5.1 J. As a result of investigating the relationship between reduction in bending elastic modulus and internal damage development, the reduction is caused by delamination within CFRP laminates mainly. Since total length of cracks in CFRP/Al honeycomb core sandwich panels is smaller than that in the laminates only, the sandwich panels have high impact tolerance because of absorption of impact energy by damaging Al honeycomb core.     

A study on fatigue damage modeling using neural networks

Fatigue crack growth and life have been estimated based on established empirical equations. In this paper, an alternative method using artificial neural network (ANN) -based model developed to predict fatigue damages simultaneously. To learn and generalize the ANN, fatigue crack growth rate and life data were built up using in-plane bending fatigue test results. Single fracture mechanical parameter or nondestructive parameter can’t predict fatigue damage accurately but multiple fracture mechanical parameters or nondestructive parameters can. Existing fatigue damage modeling used this merit but limited real-time damage monitoring. Therefore, this study shows fatigue damage model using backpropagation neural networks on the basis of X-ray half breadth ratioB/B ₀ , fractal dimensionD _f and fracture mechanical parameters can estimate fatigue crack growth rateda/dN and cycle ratioN/N _f at the same time withinengineering limit error (5%).     

Wechselbiegeapparatur für die in situ-Untersuchung von Zerrüttungsvorgängen im Rasterelektronenmikroskop

An SEM stage (Fig. 1 and 2) is described which allows bending fatigue of metallic specimens in the vacuum of the specimen chamber. With the aid of inductive displacement pick-ups the angle of bending can be measured (Fig. 3) as well as the momentum of bending (Fig. 4). Thus the mechanical hysteresis can be registrated and the fatigue of the specimen can be controlled. Fig. 5 shows the geometry of the fatigue specimen, which has an electrolytically polished surface area of about 6 × 3 mm² on which the development of deformation topography can be studied during the fatigue experiment. The main advantages of the new fatigue apparatus are:

• 1 No interruption of cyclic straining is necessary for the investigation of the specimen surface.
• 2 The specimen is in vacuum during the complete experiment so that environmental influences are reduced.
• 3 The development of surface topography can be monitored continuously.
• 4 Differences of the topography (e. g. fatigue cracks) in the phase of tension and compression can be detected.

In the case of fatigue of polycrystalline metals, fatigue cracks often start at the surface of the specimen in slipbands produced by the cyclic straining. Fig. 6 shows typical fatigue slipbands with extrusions and intrusions for pure Al. A slipband crack in a later stage of fatigue is shown in Fig. 7. For the investigation of the distribution of fatigue cracks at the surface the possibility of watching the surface in different phases of bending is a great help. The cyclic crack opening – which depends on the crack depth – can be seen by eye on the TV-screen and can be recorded on video tape when the frequency of bending is about 1 cycle/s or can be photographed from the record display at very low frequencies of bending. Fig. 8 gives an example of the difference in crack opening in the phase of tension and compression of the specimen surface respectively.     

FDM 3D打印聚醚醚酮零件摩擦磨损特性研究

为研究3D打印各向异性对摩擦性能的影响,通过熔融沉积成型(FDM)制备了0°、45°、90°3种打印角度的聚醚醚酮(PEEK)试样,研究3种不同打印角度及载荷变化对PEEK试样摩擦学性能及磨损机制的影响。利用MFT-5000摩擦磨损试验机对PEEK材料进行室温水润滑下的往复滑动摩擦试验,用超景深显微镜观察磨损后表面形貌。试验结果表明：不同载荷下3种打印角度试样的摩擦因数由大到小依次为0°试样、90°试样、45°试样,磨损率由大到小依次为90°试样、45°试样、0°试样;随着载荷的增大,3种不同打印角度试样的摩擦因数均呈现下降趋势,磨损率则呈现上升趋势;PEEK磨损机制是黏着磨损以及疲劳磨损引起的表层脱落。     

Tribological behaviour of Si3N4 and Si3N4-%TiN based composites and multi-layer laminates

Si₃N₄-TiN based multi-layer laminates exhibit differences in residual stress between individual layers due to a variation of the thermal expansion coefficient between the layers. The residual stress distribution in these multi-layer laminates is known to improve the apparent macroscopic fracture toughness. In this work, the tribological behaviour of bulk, composites and multi-layers laminates are investigated. Si₃N₄ bulk, Si₃N₄ based composites with 10, 20 and 30 wt% TiN and different multi-layer laminates have been tested under dry conditions with reciprocal movement using a ball-on-block configuration. In particular, the influence of sliding directions with respect to the layer orientations has been investigated.The experimental results show that wear resistance increased with increasing TiN content in Si₃N₄-TiN composites. However, multi-layer laminates exhibit an up to three times higher apparent fracture toughness, but do not show an improvement of wear resistance compared to composites.     

高速列车S38C车轴外物致损模拟与疲劳性能研究

外物致损是造成高速列车车轴疲劳失效的典型因素之一。采用立体显微镜分析CRH2系列高速列车S38C车轴表面的损伤，借助轻型空气炮向取于S38C车轴表面的四点弯曲疲劳试样发射多种角度、速度的球形和正方形钨钢弹体，模拟外物致损。采用逐步加载法来确定损伤试样的疲劳强度，在场发射扫描电镜下观测损伤特征和疲劳断口形貌。结果表明，车轴表面的损伤大部分是刮擦，少部分是缺口。球形弹体垂直冲击损伤随着速度的增大变得逐渐恶劣，材料缺失和微裂纹分布在损伤边缘，底部出现绝热剪切带引发的裂纹；球形弹体斜冲击损伤出射区主要以形变和剪切作用下的掉块为主；方形弹体冲击损伤形态各异。不考虑损伤形成的工况，试样疲劳强度随着损伤深度的增加而降低，深度作为损伤评价参数具有可操作性，本研究为车轴外物致损检修标准的制定提供参考。     

层压复合材料剪切疲劳寿命预估

将Iosipescu剪切强度测试方法推广到剪切疲劳试验.以碳纤维/树脂基T300/QY8911复合材料层压板为研究对象,对三种多向铺层试件进行剪切疲劳试验.用一种疲劳损伤累积模型和自行开发的有限元/疲劳寿命分析程序预测被试多向层压板的剪切强度,模拟局部疲劳失效演变的过程,给出疲劳寿命和剩余强度预估结果,比较两种静强度准则(Tsai-Hill准则和Puck修正准则)对预估结果的影响.寿命预测结果与试验结果基本相符.     

Fracture toughness of CFRP laminated plates according to resin content

CFRP(carbon fiber reinforced plastic) has recently found wide use in different industries. The material, however, is very prone to damage from collision with foreign objects. This study aims at finding Ĵ-integral in mode II for CFRP laminated plates based on classical bar theory for dynamic conditions in consideration of inertia forces and eventually to finding dynamic inter-layer fracture toughness. Dynamic inter-layer fracture toughness was observed using an in-house ENF (End Notched Flexure) experimental facility using Split Hopkinson’s Bar (SHPB). Also the variation of the fracture toughness depending on different resin contents and fiber arrangement in the CFRP specimen ([0°3/90°3/0°6/90°3/0°3], [0°20], [0°5/90°10/0°5]) was observed. It was established that under both quasi-static and dynamic load conditions, the critical load and the inter-layer fracture toughness increased sharply following the extension of the resin content. Thus, it may be concluded that the resin content is the major factor determining the inter-layer fracture toughness in the CFRP laminated plate.     

Solid particle erosion of unidirectional carbon fibre reinforced polyetheretherketone composites

The solid particle erosion behaviour of unidirectional carbon fibre (CF) reinforced polyetheretherketone (PEEK) composites has been characterised. The erosion rates of these composites have been evaluated at different impingement angles (15–90°) and at three different fibre orientations (0, 45, and 90°). The particles used for the erosion measurements were steel balls with diameter of 300–500 μm and impact velocities of 45 and 85 m/s. The unidirectional CF reinforced PEEK composites showed semi-ductile erosion behaviour, with maximum erosion rate at 60° impingement angle. The fibre orientations had a significant influence on erosion rate. The morphology of eroded surfaces was examined by using scanning electron microscopy (SEM). Possible erosion mechanisms are discussed.     

Effects of micro-stresses from machining and shot-peening processes on fatigue life

An investigation of the effects of tensile machining and compressive shot-peening residual stresses on fatigue life is presented. The paper is focused on fatigue life modelling using the finite element method (FEM). A representative broached notched specimen under three-point bending is modelled as a 2D plane stress geometry using the FEM. Inconel 718 mechanical and fatigue material properties at 600°C are used. Machining and shot-peening residual stresses are mapped to the macro FE models using mathematical algorithms around the notched area of the specimen and their influence on the fatigue life experiencing high cycle fatigue (HCF) and low cycle fatigue (LCF) is investigated. The results show that the compressive shot-peening residual stresses significantly increase the life at HCF compared to the LCF.     

Study on burr occurrence and surface integrity during slot milling of multidirectional and plain woven CFRPs

Machining carbon fiber reinforced composite (CFRP) is often accompanied with cutting edge defects and surface damage including interlayer delamination, cavities and debonding of fiber-matrix. A detailed understanding of the effect of fiber configuration and cutting parameters on cutting force, burr occurrence/formation and surface integrity is necessary. In this paper, experimental data is presented relating to fiber burrs on entry surface, cutting force, surface roughness and workpiece integrity when slot milling CFRP laminates with varying fiber configurations (0°/90°, 45°/135° and plain woven) at different cutting speed (60 and 120 m/min) and feed rate (0.05 and 0.1 mm/rev). Lateral cutting force is recorded down to 56 N and highly dependent on fiber orientation. The length (up to ~?5.6 mm) and amount of fiber burrs are highly related to fiber orientation and fiber cutting angle. Surface roughness Ra down to ~?1.4 μm was recorded when milling type 2 (45°/135°) and type 3 (plain woven) laminates. Various surface defects predominantly occurred due to different cutting conditions and fiber configurations, which are mainly located in the layers with fibers orientated at 45°/135°. The occurrence and propagation of fiber burrs and surface cavities were also investigated based on different fiber fracture mechanisms.     

利用超声成像分析不同复合材料层压结构冲击损伤行为

复合材料各向异性和吸能的特点,在受到外来冲击作用时容易产生损伤,呈现表里迥然不同的损伤行为和分布规律。为研究不同复合材料层压结构的冲击损伤行为,设计制备树脂传递模型工艺(Resin transfer molding, RTM)缝合和预浸料复合材料层压结构两种不同成型工艺的试样,通过冲击试验模拟复合材料在外力作用下产生的冲击损伤,采用超声反射法,通过点聚焦换能器对试样进行超声B扫描成像,揭示两种复合材料层压结构试样内部断面损伤行为及其扩展规律。试验结果表明,冲击引起的试样内部损伤比表面损伤要大得多;随着冲击能量在试样内部传递,会在不同深度铺层产生新的损伤,而且损伤分布并不仅沿层间界面扩展;冲击点附近和远离冲击点附近的内部损伤具有明显不同的分布规律;RTM缝编与预浸料复合材料结构呈现明显不同的损伤行为,其中RTM缝合复合材料结构中的纵向缝线,对冲击损伤在试样内部沿层间的扩展有显然的阻止作用。研究结果对更好地理解复合材料的损伤行为、寻找新的改进复合材料层压结构损伤行为的机制有非常重要的指导意义和帮助。     

CF/PEEK复合材料自阻电热-原位膜混合加热固化方法

碳纤维增强聚醚醚酮树脂基(CF/PEEK)复合材料密度小、韧性强、疲劳强度高,且可循环使用,但PEEK树脂熔融温度高(>340℃)、熔融黏度大(>1000 Pa·s)、熔融-烧蚀工艺温度窗口小,零件固化难度大。提出一种CF/PEEK树脂基复合材料自阻电热-原位膜混合加热固化方法,结合有限元仿真,引入组合原位膜自适应地辅助加热制件。有限元仿真和实验研究结果证明了该方法的有效性：加热过程中相较纯自阻电热加热方法,制件温度均匀性提高了75%,结晶度提高了16.2%,实现了CF/PEEK树脂基复合材料的高效、均匀加热固化。     

Wear and rolling contact fatigue of PEEK and PEEK composites

Wear and rolling contact fatigue were investigated on unfilled PEEK and on three PEEK short fiber reinforced composites. For this aim, roller-shaped specimens were subjected to rolling contact tests at different contact pressure levels. Wear rate-pv product and contact pressure-life diagrams were obtained, depending on material hardness. Microscopic observations of rolling contact surfaces and sections of the rollers highlighted damages at two different scales, surface and bulk, leading independently to wear and rolling contact fatigue. These damages were also of different typology for unfilled PEEK and composites: micro-pitting and deep transversal cracks occurred on unfilled PEEK rollers, while delamination and spalling phenomena where found on composite rollers.