接头局部增强的复合材料层合板螺栓连接试验与数值模拟

采用真空辅助成型工艺（VARI）制备了四种局部增强的复合材料层合板螺栓连接试件，通过试验及数值模拟对其力学性能进行了研究。数值研究中将复合材料层合板连接件的拉伸作为一个准静态问题，运用ABAQUS的显示分析算法及所编写用户材料子程序VUMAT对连接件进行了三维渐进失效模拟，同时在有限元模型中采用内聚力单元模拟了层合板与所设增强层的界面分层失效。数值计算结果与试验结果取得了较好的一致，验证了本文中数值方法的有效性。研究结果表明，不同的局部增强方案对复合材料螺栓连接性能的影响较大，设置[0/90/0/90]_S铺层的内置纤维增强层能显著提高层合板的螺栓连接性能。     

一种改进的内聚力损伤模型在复合材料层合板低速冲击损伤模拟中的应用

针对传统内聚力损伤模型(CZM)无法考虑层内裂纹对界面分层影响的缺点,提出了一种改进的适用于复合材料层合板低速冲击损伤模拟的CZM。通过对界面单元内聚力本构模型中的损伤起始准则进行修正,考虑了界面层相邻铺层内基体、纤维的损伤状态及应力分布对层间强度和分层扩展的影响。基于ABAQUS用户子程序VUMAT,结合本文模型及层合板失效判据,建立了模拟复合材料层合板在低速冲击作用下的渐进损伤过程的有限元模型,计算了不同铺层角度和材料属性的层合板在低速冲击作用下的损伤状态。通过数值模拟与试验结果的对比,验证了本文方法的精度及合理性。     

确定金属型铸造界面传热系数方法的研究

铸造凝固过程数值模拟中通常用界面传热系数表示热阻的影响,在诸多影响模拟精度的因素中,该系数起主导作用。为提高模拟精度,以ANSYS软件为平台,在测温试验的基础上,考虑铸件与铸型的不同接触位置以及不同界面传热系数对模拟结果的影响,采用0.618黄金分割法选取了该系数;应用最小二乘法建立起界面传热系数与时间关系的数学模型,并对金属型铸造凝固过程的温度场进行了模拟,将模拟结果与试验结果做了对比分析,得到了合理的温度分布。研究的结果为获得精确的界面传热系数提供了一种研究方法。     

充冷过程中冷板内特性研究

针对机械冷板冷藏车冷板充冷时间长的问题,根据热量守恒原理建立了冷板内共晶冰冻结过程的数学模型,并对影响冷板充冷过程的关键因素进行了讨论,用准静态方法对蒸发盘管外共晶冰的形成过程进行了数值计算.计算结果表明,随着盘管周围共晶冰厚度的增加,共晶冰冻结缓慢;降低蒸发温度,减少冷板外热负荷,可以明显减少共晶冰的冻结时间;冻结过程中,冷板内的逐时蓄冷量基本不变.     

高层建筑周围定常风场的数值模拟

通过对高层建筑周围定常风场的数值模拟与原型试验结果的比较，分析了在进行数值模拟时，入口边界条件和湍流模型等因素对计算结果的影响。模拟结果表明，入口边界条件和湍流模型均对模拟结果具有较大影响。其中，入口边界条件中速度分布对计算结果的影响大于湍流强度分布对计算结果的影响，而RNGk-s湍流模型的计算精度优于标准κ-ε湍流模型。     

高性能计算平台在铜铁薄板热轧复合数值模拟中的应用

基于高性能计算平台,利用ABAQUS有限元软件首次对Cu/Fe/Cu薄板进行了热轧复合模拟.应用高性能计算平台不仅大大地提高了计算效率,而且还提高了计算精度.通过模拟仿真,获得了轧制复合过程的应力应变场和温度场变化,对热轧过程有更清晰的认识；通过与实验对比,数值模拟与实验结果吻合良好,复合板各层厚度变化误差在5％左右,可对原始板料的厚度提供参考,同时对工艺的制定提供良好的理论指导.     

基于组合单元的层压复合材料三维应力分析

为了分析层压复合材料层间特性,推导了将刚性元-弹簧元相结合的离散型界面单元的刚度矩阵。建立了层压板的准三维模型,即将Mindlin板单元应用于层压板的各子层,层间作用则利用上述界面单元来模拟。通过弯曲板元计算子层面内应力,通过界面单元的弹簧力确定层间应力。对受面内拉伸的多向层压板条进行了应力分析,与使用商业软件三维实体模型计算得到的层间和面内应力对比,结果表明准三维模型的计算结果合理。这种新型界面单元的优点是可用来表征层间损伤,并且能通过对弹簧刚度的消减来模拟分层损伤的演变。     

中厚板矫直过程中中性层偏移动态研究

研究中性层偏移对矫直力的影响,以提高矫直力精度。通过对矫直件三维弹塑性变形进行分析,提出中性层偏移理论,利用数值模拟和实验讨论中性层偏移的动态变化规律,说明中性层偏移是影响矫直力精度的重要因素之一,并验证了理论推导公式与数值计算结果之间的误差,为建立更为准确的矫直力模型提供理论基础和数据。     

多层抗爆结构冲击响应无网格MPM法分析

在两层钢板中间夹衬泡沫铝等多孔材料构成多层复合结构被应用于抗爆、抗冲击的结构设计中,能够有效地降低冲击载荷对结构的破坏作用。为了研究多层复合结构的抗爆机理和变形破坏过程,使用材料非线性本构模型和无网格物质点法对在高速冲击载荷作用下各层材料的弹塑性大变形进行数值模拟。MPM法利用了欧拉法和拉格朗日法两者的优点,不仅与网格无关,也避免了有限元法中网格畸变,而且在对涉及多物质分界面的问题计算时,因MPM法的耦合条件自动满足,不需要考虑材料界面的变形和破坏,为计算多层抗爆结构的冲击响应建立了一个有效的无网格法数值模拟平台。     

长厚比对正六边形铝蜂窝夹层板等效板模型动力学计算精度的影响

为提高正六边形铝蜂窝夹层板的数值计算精度,研究了长厚比对其等效板模型动力学计算精度的影响。针对芯层均匀壁厚的正六边形铝蜂窝夹层板,首先研究了它的等效板模型,包括Reissner理论模型、蜂窝板理论模型和层合板低阶剪切理论模型;然后,将等效板模型与精细化模型相同模态振型的模态频率进行比较,分析了长厚比对等效板模型动力学计算精度的影响。结果表明:芯层均质化后模型模态频率的计算误差很小;层合板低阶剪切理论模型是计算精度较高的等效板模型;Reissner理论模型在长厚比为7.37时计算精度最低,蜂窝板理论模型对厚板的计算精度比薄板低,层合板低阶剪切理论模型对厚板的计算精度比薄板高。      

Simulation of delamination–migration and core crushing in a CFRP sandwich structure

Following the onset of damage caused by an impact load on a composite laminate structure, delaminations often form propagating outwards from the point of impact and in some cases can migrate via matrix cracks between plies as they grow. The goal of the present study is to develop an accurate finite element modeling technique for simulation of the delamination–migration phenomena in laminate impact damage processes. An experiment was devised where, under a quasi-static indentation load, an embedded delamination in the facesheet of a laminate sandwich specimen migrates via a transverse matrix crack and then continues to grow on a new ply interface. Using data from this test for validation purposes, several finite element damage simulation methods were investigated. Comparing the experimental results with those of the different models reveals certain modeling features that are important to include in a numerical simulation of delamination–migration and some that may be neglected.     

Spacing and failure mechanism of edge fracture in two-layered materials

The phenomenon of edge fractures is analyzed using a fracturing process approach. Such fractures often initiated from the free surface of layered materials, and often terminate at the interface that divides the fractured layer and the matrix layer, or continue to expand along the interface, or create a peel-crack. To understand better the pattern of fractures with different spacing and the fracture mechanism, a double-layer elastic model with the same material properties with a fractured overlying layer subjected to uniaxial tension is simulated firstly. The stress distribution between two adjacent fractures is periodically distributed as a function of the ratio of the fracture spacing to the thickness of the fractured layer (S/t ratio), and homogeneous and heterogeneous material properties are considered in the simulation. The simulation results show that both the stress distribution and the critical value of fracture spacing to layer thickness ratio are affected by material heterogeneity; the S/t ratio of heterogeneous material is much smaller and it is much easier to crack compared with the homogeneous materials. In particular, the fracture saturation mechanism is analyzed by stress state change. Then a numerical simulation is carried out to reveal the fracturing process from micro-fracture formation, propagation, coalescence, nucleation, fracture infilling, fracture saturation, termination, to interface delamination. A fitting curve of the relationship between strain and spacing to layer thickness radio is obtained. It is found that infilling fractures may grow near the bottom or the free surface of the fractured layer by coalescence of micro-fractures and flaws. We also find that fracture spacing in the case of interface delamination is greater than that without interface delamination. A study of stress transition between the two layers on fracture spacing in the fracture process is also carried out, with a focus on stress transfer mode.     

2.5D机织复合材料压缩性能实验与数值模拟

为了研究2.5D机织复合材料的压缩损伤和失效机制,验证双尺度渐进损伤有限元数值模拟方法的有效性,对这类复合材料分别沿经纱方向和纬纱方向进行了准静态压缩实验,获得了其相应的应力-应变曲线,并测定了材料的初始弹性模量和极限强度。在此基础上,利用双尺度渐进损伤有限元数值方法模拟分析了材料的压缩应力-应变响应和损伤演化行为,取得了与实验吻合较好的模拟结果。结果表明:2.5D机织复合材料在纬向压缩下的主要失效模式是纬纱的轴向压溃与断裂,可获得相对较高的压缩强度;但在经向压缩下,经纱因弯曲会承受附加弯矩作用,从而对周围基体造成挤压,故在经纱轴向断裂之前容易出现经纱之间基体的压溃和纱线之间的分层开裂,使强度降低,不利于发挥纤维的承载优势。     

Meso-Scale Damage Simulation of 3D Braided Composites under Quasi-Static Axial Tension

The microstructure of 3D braided composites is composed of three phases: braiding yarn, matrix and interface. In this paper, a representative unit-cell (RUC) model including these three phases is established. Coupling with the periodical boundary condition, the damage behavior of 3D braided composites under quasi-static axial tension is simulated by using finite element method based on this RUC model. An anisotropic damage model based on Murakami damage theory is proposed to predict the damage evolution of yarns and matrix; a damage-friction combination interface constitutive model is adopted to predict the interface debonding behavior. A user material subroutine (VUMAT) involving these damage models is developed and implemented in the finite element software ABAQUS/Explicit. The whole process of damage evolution of 3D braided composites under quasi-static axial tension with typical braiding angles is simulated, and the damage mechanisms are revealed in detail in the simulation process. The tensile strength properties of the braided composites are predicted from the calculated stress-strain curves. Numerical results agree with the available experiment data and thus validates the proposed damage analysis model. The effects of certain material parameters on the predicted stress-strain responses are also discussed by numerical parameter study.     

A level set model for simulating fatigue-driven delamination in composites

This paper proposes a level set model for simulating delamination propagation in composites under high-cycle fatigue loading. For quasi-static loading conditions, interface elements with a cohesive law are widely used for the simulation of delamination. However, basic concepts from fatigue analysis such as the notion that the crack growth rate is a function of energy release rate cannot be embedded in existing cohesive laws. Therefore, we propose a model in which the cohesive zone is eliminated from the computation while maintaining the flexibility that the crack shape is not bound to element edges. The model is able to predict the delamination growth rate and its front shape accurately. To demonstrate the validity of the model, several tests under different fracture modes are conducted and the results are compared with experimental data, analytical solutions and results from cohesive zone analysis.     

Delamination buckling growth in laminated composites using layerwise-interface element

In this paper, a numerical investigation on the buckling of composite laminates containing delamination, under in-plane compressive loads, is presented. For this purpose, delamination propagation is modeled using the softening behavior of interface elements. The full layerwise plate theory is applied for approximating the displacement field of laminates and the interface elements are considered as a numerical layer between any two adjacent layers where the delamination is expected to propagate. A non-linear computer code was developed to handle the numerical procedure of delamination buckling growth in composite laminates using layerwise-interface elements. The load/displacement behavior and the contours of embedded and through-the-width delamination propagation for composite laminates are presented. It is shown that delamination growth can be well predicted using this layerwise-interface elements with decohesive law.     

Intersonic delamination in curved thick composite laminates under quasi-static loading

Dynamic delamination in curved composite laminates is investigated experimentally and numerically. The laminate is 12-ply graphite/epoxy woven fabric L-shaped laminate subject to quasi-static loading perpendicular to one arm. Delamination initiation and propagation are observed using high speed camera and load–displacement data is recorded. The quasi-static shear loading initiates delamination at the curved region which propagates faster than the shear wave speed of the material, leading to intersonic delamination in the arms. In the numerical part, the experiments are simulated with finite element analysis and a bilinear cohesive zone model. Cohesive interface elements are used between all plies with the interface properties obtained from tests. The simulations predict a single delamination initiating at the corner under pure mode-I stress field propagating to the arms under pure mode-II stress field. The crack tip speeds transition from sub-Rayleigh to intersonic in conjunction with mode change. In addition to intersonic mode-II delamination, shear Mach waves emanating from the crack tips in the arms are observed. The simulations and experiments are found to be in good agreement at the macro-scale, in terms of load-displacement behavior and failure load, and at the meso-scale, in terms of delamination initiation location and crack propagation speeds. Finally, a mode dependent crack tip definition is proposed and observation of vibrations during delamination is presented. This paper presents the first conclusive evidence of intersonic delamination in composite laminates triggered under quasi-static loading.     

An Experimental Method for Dynamic Delamination Analysis of Composite Materials by Impact Bending

An improved experimental method for characterizing dynamic delamination growth in composite structures has been developed and verified using high speed photography and explicit finite element simulation. The method is based on a three-point bending device. End notch flexure carbon fiber composite beam specimens were subjected to both quasi-static and impact rates of Mode II loading. The experimental results showed no significant strain rate dependency of the delamination fracture toughness. This important result complements the scarce and conflicting data available in the literature, and serves as a reference for calibration of numerical modeling strategies.     

Deformation and failure modelling of high strength adhesives for crash simulation

The deformation and failure mechanisms of toughened high strength adhesives used in the automotive industry are very complex and require advanced numerical models for crashworthiness simulation. The theoretical background of two new modelling approaches for thin adhesive layers is presented: firstly, a simplified elastic damaging node-to-element tied interface model approach for convenient and efficient modelling, and secondly a detailed modelling approach for improved accuracy using an elasto-viscoplastic solid element representation of the adhesive layer. The material model parameters required for both approaches are determined by a comprehensive set of experiments, including quasi-static and dynamic adhesive coupon testing, fracture toughness testing, and quasi-static tension/shear (and combined) testing of thin adhesive layers. A more complex adhesively joined assembly of two aluminium extrusions subjected to quasi-static (QS) and dynamic loading serves as the final validation example for both modelling approaches. Good agreement of experiments and numerical predictions was observed for both modelling approaches.