Nonlinear progressive damage model for composite laminates used for low-velocity impact

In order to effectively describe the progressively intralaminar and interlam- inar damage for composite laminates, a three dimensional progressive damage model for composite laminates to be used for low-velocity impact is presented. Being applied to three-dimensional （3D） solid elements and cohesive elements, the nonlinear damage model can be used to analyze the dynamic performance of composite structure and its failure be- havior. For the intralaminar damage, as a function of the energy release rate, the damage model in an exponential function can describe progressive development of the damage. For the interlaminar damage, the damage evolution is described by the framework of the continuum mechanics through cohesive elements. Coding the user subroutine VUMAT of the finite element software ABAQUS/Explicit, the model is applied to an example, i.e., carbon fiber reinforced epoxy composite laminates under low-velocity impact. It is shown that the prediction of damage and deformation agrees well with the experimental results.     

复合材料层合板冲击损伤近场动力学模型与分析

近场动力学(简称PD)理论通过域内积分建立物质基本运动方程。不同于传统理论中通过微分建立运动方程的方法,该理论对场函数没有连续性的要求,因而适合求解各类不连续问题。基于此,本文建立了正交各向异性单层板PD理论模型,进而引入单层板层间作用,发展了正交各向异性层合板PD模型及其损伤模型,并模拟了各向同性与各向异性层合板冲击损伤;通过对比分析,对模型的有效性进行了验证。     

复合材料冲击损伤及冲击后压缩强度的等效实验方法

简要论述了复合材料低速冲击及冲击后压缩的研究情况,比较了几种不同的冲击后的压缩实验方法,选取一种小尺寸试件方法,对复合材料低速冲击后的压缩行为进行研究,并将结果与有关文献进行了比较,实验结果与文献结果具有一致的变化规律。研究结果显示,对于材料研究,该方法可用来表征复合材料冲击后的压缩特性。使用该方法可以大大节省实验费用及周期。     

CONSTITUTIVE RELATION AND STIFFNESS DEGRADATION OF CRACKED ANISOTROPIC COMPOSITE LAMINATES(II)─DETERMINATION OF RESOLVED STIFFNESS AND INVESTIGATION OF STIFFNESS DEGRADATION

The study on properly degradation of damaged,.onlj,osile laminates is extendedto anisotropic laminates with matrix cracking. In (II) of the paper, a solution forpartitioned stiffness is given to complete the constitutive relations developed in (I) Thestiffness degradation in (θ_m/90_n)_s cracked laminates is calculated and the results arediscussed.     

层合板冲击损伤的PD率效应本构模型分析

从近场动力学(简称PD)理论的PMB材料模型出发,结合Kelvin-Voigt粘弹性固体模型,建立PD率效应本构模型。采用LAMMPS软件模拟了环氧树脂板、纤维增强复合材料单向层板和多向铺层层合板受冲击的情况。通过分析各板的冲击损伤,探索纤维对板的增强作用。同时,分析了不同冲击速度下层合板上下表面的损伤程度,初步探讨了从低速碰撞到高速冲击过程中复合材料层合板的破坏机理及规律。     

Optimum design of composite laminates

A new procedure for the optimum layup design of composite laminates is described in this paper. In this method the global optimum search and local relaxing constraints are adequately combined together. The design variables are divided and applied in separate processes. A 16-node hybrid semi-Loof element model is used in the global structure analysis. The iterative complex method is adopted in the optimization. The method is suitable for the minimum weight design of a laminate subjected to the strength and stiffness constraints under multiple loading. The numerical results demonstrate the high efficiency and reliability of the present method.The project was supported by National Natural Science Foundation of China     

含圆孔复合材料层板在拉伸载荷下损伤破坏过程的模拟

本文应用有限元法模拟受拉含孔夏合材料层板损伤起始、累积直至破坏的过程。在模拟中引入了作者早些时建立的包含基体开裂层非对称约束影响的损伤本构关系，以及裂纹密度与损伤区应力关系函数等。本文给出损伤累积模拟方法并编制了程序，用该程序可以获得层板加载过程中各层的损伤状态、计算其刚度衰减和应力重分布以及最终破坏载荷。给出了数值模拟算例并与现有研究结果进行了比较。     

编织Kevlar/Epoxy复合材料层合板在冲击荷载下的动态响应

通过编织Kevlar/Epoxy复合材料层合板的平头弹冲击实验,分析了结构在不同冲量下的变形失效模式以及结构的抗冲击性能。实验表明复合板的变形失效模式主要表现为:(1)弹性变形;(2)复合板表面嵌入失效及整体塑性大变形;(3)背面纤维拉伸断裂及分层失效。基于实验研究,运用LS-DYNA 971有限元程序对铺层数不同的复合板在冲击载荷作用下的动态响应过程进行了数值模拟,模拟结果与实验吻合较好,子弹作用区域边缘处首先发生近似圆形的嵌入失效,而在板背面发生近似正方形的破坏区域;计算中重点分析了铺层数对结构动力响应的影响,在一定冲量范围内,通过对铺层数的优化,能够有效地减小后面板挠度,提高结构的能量吸收效率,增强结构的抗冲击性能。     

基于深度学习和近场动力学的层合板冲击工况识别

在冲击荷载作用下复合材料会产生断裂和分层等损伤。基于损伤数据对冲击工况进行识别，对改善复合材料的设计和确保其安全使用具有重要意义。基于此，本文提出一种基于深度学习和近场动力学（PD）理论的层合板冲击工况识别方法。首先使用改进的表面修正系数PD理论建立复合材料层合板刚体冲击损伤演化分析PD模型，PD模型数值模拟结果结合噪声数据增强技术构建层合板的冲击工况数据库；基于深度学习-卷积神经网络（CNN），对不同工况下的冲击损伤演化数据进行训练，实现对未知冲击工况的识别。结果显示，对于钢球冲击速度和角度的识别准确率均高于90%。     

破片冲击作用下舰船复合材料结构损伤的近场动力学模拟

基于近场动力学方法,综合分析了破片的速度、层合板的铺层方式、加筋板的筋条尺寸和破片相对筋条的冲击位置对结构损伤模式和破片剩余速度的影响。结果显示：高速破片冲击作用下,层合板会发生侵彻和穿透现象,层合板的损伤模式以基体损伤为主,且随着破片冲击速度的增大,板上下表面的损伤区域呈现出一种先增大后减小的趋势;高速破片冲击作用下,层合的板损伤扩展方向和纤维铺设方向有关,对于纤维铺层方向相同的层合板,其上下表面的损伤扩展方向一般与纤维方向相同;加筋板通过增加少量质量可以获得比层合板更好的抗破片冲击性能,且加筋板的筋条尺寸和破片相对筋条的冲击位置对加筋板的损伤具有明显影响。

     

On the description of anisotropic damage in composite laminates

A general anisotropic damage theory of cracked laminates is formulated here. The deformation of composite laminates is composed of matrix elastic strains, pseudo-elastic damage strains due to cracking and permanent damage strains due to interlaminar slip. The surface of damage initiation is constructed according to the concept of linear elastic fracture mechanics for the virgin material. After the initial damage, a pesudo-elastic damage can be used to describe the damage behaviour if interlaminar slip is negligible. Damage evolution, load induced anisotropy and interlaminar intralaminar interaction for composite laminates are examined; the latter can perturb the normality structure of damage strain rate. Explicit expressions are given for pseudo-elastic (or secant) moduli of the damaging composite laminates, under a non-interacting assumption imposed on the cracks between different families.     

含冲击损伤高强中模碳纤维复合材料层压板压缩剩余强度分析与试验验证

论文以碳纤维复合材料层压板为研究对象,发展了一种模拟复合材料层压板冲击及冲击后压缩的一体化数值分析方法．基于Puck 失效准则和粘聚区模型描述层内损伤与层间损伤,分别采用基于断裂能的双线性型、函数型以及直接折减型等不同损伤折减方法构建了层内损伤预测与演化模型;建立了碳纤维复合材料冲击后压缩数值仿真模型,通过开展不同能量冲击后压缩试验,验证了所发展的数值分析方法的有效性;研究结果表明,采用Puck 失效准则和基于断裂能的双线性损伤演化模型预测冲击后压缩强度时具有较高精度．     

复合材料T型接头冰雹高速撞击损伤的数值模拟

利用高速空气炮进行了冰雹撞击复合材料T型接头的实验,研究了不同撞击速度下结构的损伤情况。同时,采用光滑质点流体动力学方法与黏聚区模型相结合的方法,对冰雹撞击复合材料T型接头进行了数值模拟。通过与实验结果的对比,验证了数值模拟模型的有效性。在此基础上,利用数值模型研究了影响复合材料T型接头冰雹撞击损伤的各种因素。计算结果表明：冰雹撞击对复合材料T型接头造成的损伤主要为分层损伤;冰雹的撞击速度、尺寸、入射角等,都对T型接头的损伤程度有很大影响;T型接头的分层面积与冰雹的撞击能量之间呈近似线性关系,分层面积随着撞击能量的增大而增大;冰雹的入射角越大,分层面积与撞击力峰值也越大。

     

Modeling vibration behavior of delaminated composite laminates using meshfree method in Hamilton system

Free vibration analysis of composite laminates with delaminations is performed based on a three-dimensional semi-analytical model established by introducing the local radial point interpolation method (LRPIM) into a Hamilton system. The governing equation is derived with a transfer matrix technique and a spring layer model based on a local weak-form equivalent to the modified Hellinger-Reissner variational principle. Main superiority of the present model is that the scale of the governing equation involves only the so-called state variables at the top and bottom surfaces, and is insensitive to the thickness and the layer number of the composite laminates. Several numerical examples for analyzing the vibration frequencies and mode shapes of delaminated composite beams and plates are given to validate the model. The results are in good agreement with the pre-existing results.     

复合材料层板疲劳损伤加载次序效应研究

从能量耗散的角度出发，建立了一种以有效循环滞回能为基础的非线性疲劳损伤累积法则，并从理论和实验两方面证明了该法则能够正确反映载荷次序效应     

Damage analysis and dynamic response of elasto-plastic laminated composite shallow spherical shell under low velocity impact

Based on the elasto-plastic mechanics, the damage analysis and dynamic response of an elasto-plastic laminated composite shallow spherical shell under low velocity impact are carried out in this paper. Firstly, a yielding criterion related to spherical tensor of stress is proposed to model the mixed hardening orthotropic material, and accordingly an incremental elasto-plastic damage constitutive relation for the laminated shallow spherical shell is founded when a strain-based Hashin failure criterion is applied to assess the damage initiation and propagation. Secondly, using the presented constitutive relations and the classical nonlinear shell theory, a series of incremental nonlinear motion equations of orthotropic moderately thick laminated shallow spherical shell are obtained. The questions are solved by using the orthogonal collocation point method, Newmark method and iterative method synthetically. Finally, a modified elasto-plastic contact law is developed to determine the normal contact force and the effect of damage, geometrical parameters, elasto-plastic contact and boundary conditions on the contact force and the dynamic response of the structure under low velocity impact are investigated.     

3-D numerical study on the bending of symmetric composite laminates

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含切口损伤复合材料层合板拉伸失效行为研究

对含有不同切口损伤的复合材料层合板试件进行了拉伸试验,采用电阻应变计同步测量切口损伤前缘区域随载荷的变化,测定含切口损伤层合板的剩余强度,并讨论了损伤长度和损伤角度对剩余强度的影响规律.建立含切口损伤复合材料层合板有限元模型,分析了含切口损伤复合材料层合板的拉伸失效行为,计算了含切口损伤复合材料层合板的剩余强度,确定了剩余强度与切口损伤状态的关系.计算结果与试验结果具有较好的一致性.     

含孔复合材料层合板静拉伸三维逐渐损伤分析

针对面内静拉伸纤维增强复合材料含中孔层合板，发展了参数化三维逐渐损伤模型. 该模型 可以模拟含中孔层合板损伤起始、发展及最终结构破坏整个过程，并能较好地预测含中孔层 合板的破坏模式和破坏强度. 采用所发展的模型和有限元三维逐渐损伤分析技术即应力分 析、失效判定准则及损伤过程中材料性能退化等，对其他文献所提供的9种不同类型含中孔层合板进行了损伤扩展分析及强度预测，同时对层合板的损伤基本机理、类型及其相互关联作用进行了探讨，计算结果与文献实验结果非常吻合.     

Low-velocity impact of sandwich composite plates

In this paper we investigate impact and compression after impact properties of plain weave carbon fiber sandwich composites. Impact tests were conducted on different sample types to obtain information about absorbed energy and maximum impact force. The different samples consisted of foam-filled and hollow honeycomb cores with four-layer carbon fiber facesheets on one or both sides. The impact and compression after impact data provided valuable information to allow for comparisons between the different sample types. Also, the compression after impact tests were conducted in order to determine the reduction in compressive strength when comparing impacted to non-impacted samples. In conclusion, a two-degrees-of-freedom spring/mass model was compared to experimental results. The comparison helped illustrate the limitations of current impact theory. This paper was presented, in part, at a symposium honoring Dr Christian P. Burger, Novel Applications of Experimental Methods in Mechanics, held at the 2003 SEM Annual Conference and Exposition on Experimental and Applied Mechanics, June 2–4, 2003, Charlotte, North Carolina.