车用铝内胆碳纤维全缠绕氢气瓶设计要点

国家“十一五”863计划将铝内胆碳纤维全缠绕气瓶做为未来车载储氢容器的研究方向;适当增加内胆壁厚,增长裂纹扩展“路程”,提高疲劳寿命;铝内胆设计承载比例不宜小于12％;根据内胆材料应力一应变曲线、内胆和纤维的力学性能确定内胆设计应力取值为σa=σbσsa／σsb并可计算出内胆设计壁厚;内胆封头型式以矢高为1．25R／2左右的椭球为宜;螺旋缠绕角从与瓶颈相切的最小缠绕角开始逐渐增大,避免纤维严重堆积、架空,有效利用极孔处堆积纤维的过剩强度,提高成层质量和强度利用率;碳纤维首层张力不宜超过65N／mm^2,首次递减量不宜超过上一层纤维张力的4．0％;纤维排列状态设计应充分考虑工艺的可行性,确保稳定、高质量地实现设计;通过自紧,内胆应至少获得不小于1．3％的应变,最小理论自紧压力可近似计算为PZ=kPba／A。     

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.     

Micromechanics analysis of progressive failure in cross-ply carbon fiber/epoxy composite under uniaxial loading

Three-dimensional micromechanics models were created for cross-ply carbon fiber/epoxy composite with a layer stacking-sequence arranged in [0/90]_s. Elasto-plastic finite element (FE) analysis was performed to study the effects of thermal residual stress and the stress redistribution as individual fiber fractures. The modified Rice and Tracey (RT) void growth model was used to predict the location of transverse matrix crack. The stress amplification factors (SAF) in intact fibers adjacent to a fractured fiber were calculated and compared with the planar array composite. The FE results show that small defects have already formed in curing process, and ply-delamination is likely to occur near the comer of free-edges. The transverse matrix crack was predicted to occur near the fiber fracture location in the models having little inter-fiber spacing.     

平纹编织CFRP制孔分层形成机制的热-力学理论建模及试验分析

碳纤维增强复合材料(Carbon fiber reinforced plastics, CFRP)在航空航天领域获得了广泛应用,但由于各向异性和层间连接较差等特点,钻削过程中极易出现分层缺陷,严重影响构件的使用性能。为分析钻削温度对平纹编织CFRP制孔缺陷的影响机制,基于弹性地基梁理论、黏聚力学模型和热力学理论,建立了新钻型钻削平纹编织CFRP制孔分层形成的理论模型。结果表明：当新钻型多刃尖(Ⅲ)钻削孔边缘的最表层材料时,钻削温度达到最大值,对最终分层的形成最为关键;钻削温度和制孔分层随着主轴转速的增大而逐渐降低,随着进给速度的增大而逐渐升高。当纤维角度(θ)在0°/90°/180°/270°附近时,层间分层的临界轴向力达到最大值,分层相对较大,当纤维角度(θ)在45°/135°/225°/315°附近时,临界轴向力最小,分层并非极大。因此,临界力的大小只能反映产生分层缺陷的难易程度,不能决定分层的最终形状和大小。考虑温度影响时的制孔分层形态预测与试验观测基本吻合,而不考虑温度影响下所获得的预测值总体上偏小。此外,平纹编织CFRP分层形状基本呈近似圆形。     

损伤识别在车用储氢容器模态试验中的应用

针对车用高压储氢容器的复合纤维缠绕结构在其使用过程中的安全问题,开展了体积为0.074m3车用纤维缠绕储氢容器的模态试验研究。根据完好容器、反复充装引起的桶身轻微损伤和疲劳破裂两种疲劳损伤状态容器的模态分析,探讨了基于模态参数进行损伤识别的可行性。研究表明,无论是轻微损伤还是疲劳破裂状态,局部的疲劳裂纹对损伤前后的频响函数有一定影响但并不敏感,无法基于频率响应函数判定损伤是否发生并确定损伤位置,但基于损伤前后振型比较可以实现损伤判定并预测损伤位置。该研究为确定车用储氢结构的在线损伤识别奠定了实践基础。     

Effect of fiber orientation on interfacial fracture toughness for adhesively bonded composite plates

In this study, interfacial fracture toughness was investigated experimentally and numerically in laminated composite plates with different fiber reinforcement angles bonded with adhesive. The composite plates are four-layered and the layer sequence is [0º/θ]_s. DCB test was applied to composite plates reinforced with epoxy resin matrix and unidirectional carbon fiber. The experimental sample model for the DCB test was made using the ANSYS finite element package program. In the numerical study, four layered composites were prepared in three dimensions. Under critical displacement value; mode I fracture toughness at the crack tip was calculated using VCC (virtual crack closure) technique. Numerical values consistent with experimental results have presented in graphical forms. At 60o and 75° the greatest fracture toughness was obtained. In addition, numerical results have shown that fiber orientation prevents the uniform distribution of stress on the interface crack tip and causes stress accumulation, especially at the edge of the plate.

     

Effects of cutting edge radius and fiber cutting angle on the cutting-induced surface damage in machining of unidirectional CFRP composite laminates

Carbon fiber reinforced polymer composite laminates are anisotropic, inhomogeneous, and mostly prepared in laminate form before undergoing the finishing operations. The edge trimming process is considered as one of the most common finishing operations in the industrial applications. However, the laminate surface is especially prone to damage in the chip formation process, and the most common damage mode is burrs. Burrs may increase cost and production time because of additional machining; they can also damage the surface integrity. Many studies have been done to address this problem, and techniques for reducing burr size in material removal process has been the focus of the research. Nonetheless, the combined effects of the cutting edge radius and the fiber cutting angle on the burr formation have seldom been conducted, which in turn restricts to find out the mechanism of burr formation. The purpose of the present paper is to study the particular mechanism that leads to burr formation in edge trimming of CFRP laminates and investigate the effects of fiber cutting angle and cutting edge radius on burr formation. The results indicate that the burrs are prone to form in the fiber cutting angle range of 0° < χ < 90° when a large cutting edge radius of the tool is used for both milling and drilling of CFRP composites.     

某碳纤维机载电子机架设计及仿真分析

树脂基碳纤维复合材料(Carbon Fiber Reinforced Polymer,CFRP)作为一种高性能复合材料,与金属材料相比,具有比强度和比模量高、减振性能好等特点,在机载电子设备中的应用越来越广泛。文中针对机载环境条件特点,设计了一种碳纤维复合材料电子机架,提出了一种碳纤维铺层设计方法,采用ANSYS软件进行了力学仿真分析,并利用ANSYS Composite PrepPost(ACP)工具基于蔡-吴失效准则计算了铺层失效系数,较好地验证了该设计方法。该设计方法对同类电子机架结构设计具有一定的指导意义。     

铺层结构对CFRP准各向同性板损伤破坏的影响

研究铺层结构对CFRP(Carbon fiber reinforced plastics)准各向同性板损伤破坏和最终失效强度的影响，对几种不同的CFRP层合板进行拉伸试验，观察其损伤形态，并测定最终抗拉强度。利用有限元程序对完整结构以及带裂纹结构进行数值分析，讨论铺层结构、应力的数值分析结果以及损伤破坏之间的对应关系。     

飞机复合材料蒙皮的优化设计

从工程实际出发,提出了一种针对连续纤维增强复合材料蒙皮的三级优化设计方案。能够从铺设角、铺层比例、铺层厚度、铺层块形状及位置以及铺层次序等多个方面给出层合板的设计参数。在设计过程中．加入了一系列与实际加工制造非常吻合的制造性约束,使复合材料层合板构件的优化设计结果具有非常好的可制造性。运用该方法对某型飞机复合材料机翼前缘蒙皮进行了优化设计,取得了良好的设计结果。     

埋头紧固件椭圆形表面裂纹应力强度因子的三维有限元分析

采用裂端为 2 0节点奇异单元的三维有限元模型 ,对工程中常见的 90°、10 0°、12 0°埋头紧固件埋头部分与直杆部分相交处的表面裂纹 ,以及直圆杆表面裂纹的应力强度因子进行了计算分析。给出了圆直杆以及 90°、10 0°、12 0°埋头紧固件椭圆形表面裂纹的应力强度因子拟合公式。研究结果表明 ,本文的应力强度因子计算方法和计算结果是有效的。本文的工作可为埋头紧固件的损伤容限分析提供应力强度因子。     

Stress singularities in dissimilar orthotropic composites containing an interlaminar crack

The problem of an interlaminar crack in dissimilar orthotropic composite materials under in-plane and anti-plane loading conditions is investigated. In the analytical model, orthotropic half-spaces are assumed to be bound together by a matrix interlayer which represents the matrix-rich interlaminar region in the fiber-reinforced composite laminate. The crack is embedded within the interlayer. With the utilization of the stiffness matrix approach, a system of singular integral equations of the first kind is derived for the current mixed boundary value problem. Numerical results are obtained for the interlaminar crack in a [0°/90°] fibrous composite laminate subjected to three basic loadings in fracture mechanics. Under each applied loading, variations of major and coupling stress intensity factors with respect to relative crack size, crack location, and fiber volume fraction are illustrated.     

Multi-objective structural optimization of a HAWT composite blade based on ultimate limit state analysis

An extensively automated optimization procedure is presented for a horizontal axis wind turbine (HAWT) blade based on ultimate limit state analysis. Two composite materials named glass fiber reinforced plastic (GFRP) and carbon fiber reinforced plastic (CFRP) are applied with a multi-objective of blade cost and total mass. Laminate layer thickness, material type and orientation angle are tailored for the structural performance and subjected to three design constraints which are derived from analysis of ultimate strength, fatigue failure and critical deflection, respectively. Combining FEM analysis and an evolutionary algorithm, the proposed optimization process has dramatically reduced design cost and improved blade performance.     

Fatigue crack propagation behavior at a notch for needled C/SiC composite under tension-tension loading

Fatigue test of a needled C/SiC composite with a notch under tension-tension cyclic loading was completed, and the main fatigue crack propagation curve of the needled composite was obtained by the in situ observation of the fatigue process. By analyzing the influence of the failure number and distribution on the tensile loading subjected by 0° fiber bundles, the relationship between the main fatigue crack propagation and the distribution of 0° fiber bundles in the needled composite was established. By observing the fracture microstructure (especially the distribution of 0° fiber bundles) of the needled composite through scanning electron microscopy, the reasons for the varying fatigue resistance of different notched specimens were also explained. In addition, acoustic emission (AE) was also used to analyze the AE energy characteristics during the fatigue crack propagation process of the needled composite.

     

基于超声复解析信号的碳纤维层压复合材料检测方法研究

采用超声波检测碳纤维层压复合材料时,换能器将接收到层间产生的反射信号。为了有效利用层间反射信号表征碳纤维层压复合材料内部树脂及纤维铺层的几何状态,开展基于超声复解析信号的检测方法研究。介绍超声复解析信号的基本理论,阐述其相对原始A型信号的优势;定义用于成像的复解析信号表征参量,设计基于表征参量的检测成像算法,采用简化声学模型分析碳纤维层压复合材料微观结构超声响应对表征参量的影响;针对包含冲击损伤的碳纤维增强复合材料层压板开展阵列超声检测试验,试验结果表明基于超声复解析信号的检测成像方法可清晰观测出碳纤维层压复合材料微观结构内部的纤维铺层几何形态,基于原始A型信号的检测成像方法无法有效观测,超声复解析信号具有用于表征评价复合材料脱层、褶皱等缺陷的巨大潜力。     

涂层刀具高速铣削碳纤维复合材料的铣削力研究

由于碳纤维复合材料(CFRP)的各向异性,纤维的铺层方向对其整体性能有重要的影响。本文采用斜角自由切削方法对具有12种不同纤维方向的T800、T700和T300碳纤维复合材料的切削力进行了试验研究,得出了CFRP单向层合板在不同基体类型和不同纤维方向下切削力的变化规律,并分析了纤维结构对切削力的影响机理。结果表明:基体类型对切削力的影响均匀稳定,无方向性;纤维方向对切削力的影响具有显著的方向性,对切削力影响的强弱关系为F_XF_ZF_Y。     

切向加载下螺栓连接复合板的失效分析*

极限载荷和孔周应力是导致螺栓连接复合板失效的主要因素。基于Hashin失效准则和有限元模型建立螺栓连接复合板的渐进损伤有限元模型,通过位移载荷响应讨论预紧力、界面摩擦因数和孔隙变化对极限载荷的影响,分析不同铺层角下孔周应力分布规律。结果表明：随预紧力增大,螺栓连接复合板极限载荷先增大后减小,随摩擦因数增大,螺栓连接复合板极限载荷逐渐增大;不同孔隙下准线性阶段位移载荷响应基本一致,孔隙对极限载荷的影响主要体现在滑移阶段及剪切变形阶段;孔隙增大会减小螺栓与螺孔间的有效接触面积,影响螺栓连接的压力分布和强度;纤维铺层方向与应力分量同向时可有效减少外载荷导致的该方向应力分量的变化,且主应力分量皆在承压区域达到其最小值;应力分量方向与纤维铺层方向相同且该方向无外载荷作用时,应力分量随着角度从承压区到非承压区递增变化。     

铺层参数对复合材料电池箱盖模态和稳定性的影响

为满足汽车在运动过程中电池箱壳体振动小和噪声低的要求,现以某款新能源汽车电池箱盖的玻璃纤维复合材料铺层设计为研究对象,通过有限元分析软件对电池箱盖纤维铺层方案进行模态及强度分析,探究复合材料铺层结构对电池箱盖固有频率和稳定性的影响。分析结果表明:当铺层厚度和铺层顺序保持不变时,增加±45°纤维铺层比例,电池箱盖的固有频率和稳定性能显著提高;保持铺层厚度和铺层比例不变时,铺层顺序对电池箱盖模态的影响效果不明显,但对最大应力值有很大的影响,0°纤维铺层角度在最外侧电池箱盖受到的最大应力远低于±45°;随着纤维铺层厚度的增加,电池箱盖的固有频率和稳定性能不断提高。     

风载荷下机载复合材料天线罩强度有限元分析

机载天线罩对重量要求高,需要承受较大的风载荷,多采用复合材料以满足要求,因此需要对天线罩进行强度校核。文中针对某机载天线罩首先进行风载荷的计算流体动力学（Computational Fluid Dynamics, CFD）有限元仿真,然后利用ANSYS ACP进行复合材料结构铺层设计,进一步通过流固耦合方法在计算风压工况的条件下对天线罩强度进行分析,最后通过许用应力、变形情况以及复合材料多失效准则校核对天线罩结构设计安全性做出判断。该机载天线罩在要求的风载荷条件下满足使用要求。     

Impact collapse characteristics of CF/Epoxy composite tubes for light-weights

This paper investigates the collapse characteristics of CF/Epoxy composite tubes subjected to axial loads as changing interlaminar number and outer ply orientation angle. The tubes are aften used for automobiles, aerospace vehicles, trains, ships, and elevators. We have performed static and dynamic impact collapse tests by a way of building impact test machine with vertical air-compression. It is fanad that CF/Epoxy tube of the 6 interlaminar number (C-type) with 90° outer orientation angle and trigger absorbed more energy than the other tubes (A, B and D types). Also collapse mode depended upon outer orientation angle of CF/Epoxy tubes and loading type as well ; typical collapse modes of CF/Epoxy tubes are wedged, splayed and fragmentcl.