低速冲击下压电层合板的非线性动力响应与疲劳损伤寿命分析

基于损伤力学,考虑压电效应、几何非线性和损伤演化的影响,建立了集中载荷作用下压电层合板的非线性运动微分方程,考虑撞击物与压电层合板之间的弹性接触效应,确定了层合板所承受的冲击力.对此非线性动力问题,采用有限差分法进行求解,且引入损伤层合板单元模型,采用有限元方法模拟了冲击荷载作用下压电层合板的损伤演化.算例中,讨论了撞击物的冲击速度、压电材料以及损伤对压电层合板非线性动力响应的影响,以及周期冲击荷载下冲击速度和压电材料对压电层合板疲劳损伤寿命的影响.     

变形对非饱和土渗透系数影响规律模拟研究

对有、无缝合复合材料层合板的拉伸疲劳性能进行了试验研究,考察了0^\circ 缝合对复合材料光滑板拉伸疲劳损伤扩展规律的影响. 通过有限元素法分析了有、无缝合复 合材料层合板的应力状态分布情况,对缝合复合材料层合板的拉伸疲劳损伤及其扩展机理进 行了分析. 研究表明,缝合改变了复合材料层合板拉伸疲劳损伤起始与扩展的机理,针脚 附近的面内正应力\sigma_{x}与层间剪应力的集中对层合板拉伸疲劳损伤的 发生与扩展有着重要的作用,自由边界处的层间集中应力对缝合板的疲劳性能也有影响. 自 由边界处的层间集中应力是导致无缝合层合板疲劳损伤及其扩展的主要原因.     

含分层损伤复合材料层合板剩余压缩强度研究

准确预测含分层损伤层合板的剩余压缩强度,对复合材料具有十分重要 意义。本文基于层合板一阶剪切理论,建立了一种考虑复合材料多种损伤的含分层层合板刚度退化模型,通过数值算例分析了分层屈曲临界载荷与材料强度极限的关系以及刚度退化对含分层层合板前后屈曲行为的影响。     

考虑界面损伤层合梁板的层间应力分析

基于精确应力分析的广义六自由度板理论，应用变分原理和损伤力学中 的应变等效原理，考虑复合材料铺设层内和层间界面处的损伤效应，建立了具两种损伤模式 的复合材料层合板的三维非线性平衡微分方程，且运用有限差分法对考虑损伤简支层合梁板 的层间应力进行了求解.     

复合材料层合板壳非线性力学的研究进展

复合材料层合板壳是由多种组分材料组合而成.与单一材料的板壳结构相比,它无明确的材料主方向,各层间材料间断和不连续,具有明显的几何非线性和材料非线性等新的特点.其失效模式也远比单一材料的情况复杂,具有如基体开裂、脱胶、分层、分层裂纹偏转、多分层以及分层传播等多种模式.各国学者基于不同的考虑,提出了多种方法研究复合材料层合板壳的失效.首先,在简要介绍了层合板壳线性力学基本理论的基础上,重点回顾了层合板壳结构非线性力学几种基本理论发展的过程,主要阐述了经典大挠度非线性理论、一阶剪切变形理论、高阶剪切变形理论、锯齿理论、广义分层理论的理论体系及基本公式,并对几种理论之间的联系和差异进行了总结;其次,介绍了当前层合结构非线性领域的研究进展,综述了典型复合材料板壳结构的失效机理及优化设计、复合材料板壳结构在复杂环境下的破坏机理、复合材料板壳结构的物理非线性、含脱层纤维增强复合材料板壳结构的破坏机理等各研究热点的最新研究成果;最后,对该领域未来的研究方向进行了展望.     

反对称铺设复合材料层合板非线性后屈曲分析

基于层合板壳理论，考虑反对称铺设层合板的拉弯耦合效应和后屈曲过程中的非线性几何变形，推导了由应力函数和挠度表示的复合材料层合板的后屈曲控制方程。引入无量纲参数对控制方程和边界条件进行无量纲化，以消除材料参数及几何尺寸对分析结果的影响。采用摄动法将无量纲的非线性控制方程及边界条件展开成一系列非齐次线性摄动方程组，分析各阶摄动方程的通解与特解的构造，并逐次求解，建立了反对称铺设复合材料层合板受单向均布压力作用的临界屈曲荷载及后屈曲平衡路径的理论解。进而运用ABAQUS软件对复合材料层合板在面内压缩载荷作用下的屈曲和后屈曲进行有限元分析，结果表明理论解与ABAQUS结果十分接近，验证了理论解的正确性。在此基础上进一步讨论了铺设角度、铺设层数和拉弯耦合效应等对层合板后屈曲性能的影响。研究发现层合板的屈曲载荷受铺设角度与层数的影响较为显著，而拉弯耦合效应使板的屈后强度大大降低。     

具有分层损伤的不同加筋形式复合材料层合板的后屈曲性态研究

基于板的一阶剪切理论和V on-K arm an大挠度理论,分别推导了复合材料层合板和层合梁的几何非线性有限元列式,提出了含嵌入分层的复合材料加筋层合板在受压缩载荷作用下的后屈曲有限元分析方法,对在板厚方向具有不同分层位置的加筋板结构进行了有限元数值分析,研究了不同的加筋方式及筋的分布对具有分层损伤的复合材料加筋层合板的后屈曲性态的影响,所得结果对确定在压缩载荷作用下含损伤复合材料加筋层合板的剩余承载能力具有参考价值。     

含多个分层复合材料层合板后屈曲性态研究

基于Mindlin假定下的大变形板／壳理论，采用参考面单元和虚拟杆单元相结合的非线性有限元方法，建立了分析含多个穿透分层损伤层合板后屈曲行为的有限元计算模型，并给出了考虑接触后非线性屈曲方程的迭代算法，从而研究考虑层间接触效应的多分层层合板的后屈曲性态。文中着重讨论了分层的深度、数目和尺寸对含多分层合板后屈曲性态的影响。大量数值分析结果证明了该模型的有效性，并且得到了一些对层合板结构设计和对含分层损伤层合板评估有益的结论。     

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.     

缝合复合材料层合板拉伸疲劳损伤及其机理

对有、无缝合复合材料层合板的拉伸疲劳性能进行了试验研究,考察了0^\circ缝合对复合材料光滑板拉伸疲劳损伤扩展规律的影响. 通过有限元素法分析了有、无缝合复合材料层合板的应力状态分布情况,对缝合复合材料层合板的拉伸疲劳损伤及其扩展机理进行了分析. 研究表明,缝合改变了复合材料层合板拉伸疲劳损伤起始与扩展的机理,针脚附近的面内正应力\sigma_{x}与层间剪应力的集中对层合板拉伸疲劳损伤的发生与扩展有着重要的作用,自由边界处的层间集中应力对缝合板的疲劳性能也有影响. 自由边界处的层间集中应力是导致无缝合层合板疲劳损伤及其扩展的主要原因.      

INVESTIGATION ON STABILITY OF PZT/EPOXY PIEZOCOMPOSITE WITH PRESSURE AND TEMPERATURE

With the universal test machine and temperature test chamber, the effect of pressure and temperature on the behavior of 1-3 and 1-3-2 piezocomposites prepared with PZT/epoxy in our lab has been investigated through electrical impedance and dielectric analysis. The permittivity, resonant frequency and dielectric loss of the composites have been measured under vertical stress and temperature, and the variety of the material properties under pressure and temperature could also be obtained. The pressure and temperature stability of the composites have been assessed through experiments. The data of these two types of composites indicated that the stability of 1-342 composite with pressure was better than that of 1-3 composite, and two composites have almost the same dielectric stability with temperature. However, 1-3-2 composite showed slower frequency variation than 1-3 composite.     

PTFE/Al含能复合物的本构关系

室温下,利用万能材料试验机和分离式霍普金森压杆获得了PTFE/Al含能复合物在应变率10-3~103s-1范围内的压缩应力应变曲线。通过对不同应变率下力学性能的分析,初步建立了材料基于Johnson-Cook塑性模型的压缩本构方程,考虑了材料的应变硬化效应和应变率效应。利用该方程进行的PTFE/Al弹丸侵彻钢靶板的数值模拟结果与实际情况较符合,验证了该方程的可靠性和合理性,对PTFE/Al材料的实际应用也具有一定的指导作用。     

摩擦材料在无围压和加围压条件下的形变比较

研究铜基粉末冶金摩擦材料在无围压和加围压条件下的动态力学特性及其形变特征。试验在Hopkinson压杆上完成,通过试验发现,材料在无围压、应变率低于1000-1s时,有应变率强化效应;在更高应变率下,材料有损伤软化效应。微观分析可以看到试件上大量的平行滑移裂纹导致了材料破坏,形变是滑移伴随少量的孪晶;裂缝中有大量的碳纤维组织,这些纤维状组织对裂纹的扩展起抑制作用。而材料在加围压下的性能得到了很大的改善,同一应变率下最大应力、屈服极限和动态杨氏模量均有提高。在高应变率时,无论是加围压还是无围压,破碎的硬质颗粒都是长条状的。由此得出推论,球状、细化的硬质颗粒,可提高基体的强度。     

Size effect of lattice material and minimum weight design

The size effects of microstructure of lattice materials on structural analysis and minimum weight design are studied with extented multiscale finite element method（EMsFEM） in the paper. With the same volume of base material and configuration, the structural displacement and maximum axial stress of micro-rod of lattice structures with different sizes of microstructure are analyzed and compared.It is pointed out that different from the traditional mathematical homogenization method, EMsFEM is suitable for analyzing the structures which is constituted with lattice materials and composed of quantities of finite-sized micro-rods.The minimum weight design of structures composed of lattice material is studied with downscaling calculation of EMsFEM under stress constraints of micro-rods. The optimal design results show that the weight of the structure increases with the decrease of the size of basic sub-unit cells. The paper presents a new approach for analysis and optimization of lattice materials in complex engineering constructions.     

Experimental simulation of matrix cracking and debonding in a model brittle matrix composite

A model composite material system was designed to simulate typical damage mechanisms in unidirectional fiber reinforced brittle matrix composites. Experiments were performed at low to high quasistatic, macroscopic loading rates . At all loading rates reversal of the transverse strain was observed and was correlated to matrix cracking and debonding. The optical method of coherent gradient sensing (CGS) was used to obtain qualitative information regarding the stress fields and to observe the progression of damage. It was found that the sequence of damage formation (damage path) depended on the macroscopic loading rate. At lower loading rates periodic matrix cracks developed; minimal debonding of the reinforcement-matrix interface occurred only much later in the experiment. At higher loading rates extensive debonding followed propagation of the initial matrix crack, and periodic cracking was not observed. Several features of the material response of the model material system were also observed in a previously studied unidirectional ceramic matrix composite.     

平面应变状态下不可压缩幂硬化蠕变材料中刚性片状夹杂的奇异场和局部解

本文采用Williams特征展开方法结合Lee伪应力函数方法得到了平面应变状态下不可压缩幂硬化蠕变材料中刚性片状夹杂物的奇异场和局部解.研究发现,夹杂物尖端的应力奇性为r~(-m/2),与幂硬化指数m有关;而应变奇性为r~(-1/2),与幂硬化指数无关.本文通过选择积分路径给出了近尖的局部解,并用显函数的形式给出了近尖应力和位移的角变化.     

Damage evolution of ductile material under impact loading

Nucleation, growth and coalescence of micro-voids result in the fracture of materials. Most mathematical models neglect nucleation and introduce initial damage, assuming it as a material constant. However, the original damage, which is formed during material working, is a material constant. The initial damage is a model parameter and depends on the load. Apparently, the predictability of such a model is poor.This paper made comparison and analysis of the four classical void growth models and showed their similarities. At the beginning of damage evolution, all the models follow a linear relationship in the form , where c is the size of micro voids and k is a parameter which relates the material and loading condition. With the concept of statistical micro-damage and the assumption of uniform void radius for new voids, a damage evolution equation was deduced based on the above void growth model. With this equation the effects of nucleation and growth at the beginning of the damage stage on the whole process of damage evolution can be calculated. The transition time from the nucleation dominant phase to the growth dominant phase can be determined. When the transition time is applied to the damage failure model of ductile material proposed by Johnson, the initial damage (f₀), a model parameter in the original model, can also be determined. The results of the derived damage evolution equation agree well with the previous research results.     

Experimental study of the disintegration of an instantaneously heated medium and the resulting impulse at energy concentrations less than the heat of evaporation

An experiment using the radiation from a Q-switched laser was carried out to confirm the phenomenon of detachment of the surface layer of a material when it is rapidly heated at energy concentrations less than the heat of evaporation Q [1]. The disintegration of the material was recorded by high-speed photography. Measurements were made of the impulse I for different energy concentrations, and it was shown that the dependence of I on the supplied energy E was in good agreement with the theoretical calculations reported in [1]. It is shown that by determining the pressure impulse produced during the disintegration of the rapidly heated material it is possible to investigate its thermodynamic properties at densities approaching the normal value. The detachment of the surface layer of the material under instantaneous heating at energy densities less than the heat of evaporation was described in [1], where an estimate was made of the resulting pressure impulse. The results described in [1] show that when an energy E_r is liberated in the surface layer of thickness x_r or mass m_r in a time τ < t_g, where t_g=x_r/ c is the characteristic time for gas-dynamic processes and c is the velocity of sound in the medium, the pressure produced in the layer is p°=(γ - l)E_r/x_r. Interaction between rarefaction waves propagating from the boundaries of the heated layer results in the appearance of negative stresses. When these stresses exceed the dynamic strength of the material, detachment of the surface layer may take place. The pressure impulse produced during the surface-layer detachment in the case of a uniformly heated layer is given by

$$I = \frac{{(\gamma - 1)E_r }}{{2\sqrt {c_0 ^2 + \gamma (\gamma - 1)E_r /m_r } }}, (0.1)$$     

Analysis of a permeable interface crack in elastic dielectric/piezoelectric bimaterials

A permeable interface crack between elastic dielectric material and piezoelectric material is studied based on the extended Stroh’s formalism. Motivated by strong engineering demands to design new composite materials, the authors perform numerical analysis of interface crack tip singularities and the crack tip energy release rates for 35 types of dissimilar bimaterials, respectively, which are constructed by five kinds of elastic dielectric materials: Epoxy, Polymer, Al₂O₃, SiC, and Si₃N₄ and seven kinds of practical piezoelectric ceramics: PZT-4, BaTiO₃, PZT-5H, PZT-6B, PZT-7A, P-7, and PZT-PIC 151, respectively. The elastic dielectric material with much smaller permittivity than commercial piezoelectric ceramics is treated as a special transversely isotropic piezoelectric material with extremely small piezoelectricity. The present investigation shows that the structure of the singular field near the permeable interface crack tip consists of three singularities: and , which is quite different from that in the impermeable interface crack. It can be concluded that different far field loading cases have significant influence on the near-tip fracture behaviors of the permeable interface crack. Based on the present theoretical treatment and numerical analysis, the electric field induced crack growth is well explained, which provides a better understanding of the failure mechanism induced from interface crack growth in elastic dielectric/piezoelectric bimaterials. The project supported by the National Natural Science Foundation of China (10572110), Doctor Foundation of the Chinese Education Ministry and Doctorate Foundation of Xi’an Jiaotong University. The English text was polished by Yunming Chen.     

Analysis of frequency-domain vibration response of thin plate attached with viscoelastic free layer damping

To predict the vibration response of viscoelastic composite structure, two key issues need to be conducted, one is introducing the constitutive model of viscoelastic material into the analysis model and the other is describing the real damping behavior of viscoelastic composite structure. The emphasis of this study is to obtain the effects of frequency dependence on the vibration response of viscoelastic composite structure and the method of introducing two kinds of damping (viscoelastic material damping and remaining equivalent viscous damping). Vibration response analysis in frequency domain was investigated for viscoelastically damped plate. A cantilever plate attached with the ZN_1 viscoelastic free layer damping (FLD) was chosen to demonstrate the developed method. Frequency-domain response of the composite plate were solved and the obtained results were compared with the experimental values for the purpose of assessing the rationality of the proposed method. In addition, in order to obtain the effects of viscoelastic material parameters on vibration response of viscoelastic composite structure, a detailed parametric analysis was performed. This study shows that the frequency dependent characteristic of viscoelastic material has significant influence on the vibration response in the resonant region and acceptable results can be achieved in the non-resonant region if frequency dependent parameters are substituted by average values of the viscoelastic parameters reasonably in the analysis process.