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。     

T300/648迭层板接头挤压疲劳损伤参数的选择与测定

本文对碳纤维增强复合材料迭层板(C.F.R.P)接头在不同环境条件下的挤压疲劳损伤扩展进行了实验研究.并根据“剩余强度,剩余刚度”理论和“疲劳模量”概念,讨论了接头的刚度下降和强度变化.由此提出了“损伤参数”D的定义和测量方法;并对损伤试件,进行了X射线检测分析,验证了累积损伤的扩展.     

金属损伤复合材料胶接修补结构力学试验研究

为评估金属损伤复合材料胶接修补结构的剩余强度和剩余寿命,进行了含腐蚀和疲劳损伤LY12CZ航空铝合金板碳/环氧复合材料补片胶接修复结构的力学性能试验,分析了在静拉伸和疲劳载荷作用下修补结构的破坏模式、失效机理。试验研究发现:复合材料胶接修补技术有效改善了腐蚀和疲劳损伤这两类损伤区域的受力状况,恢复了其载荷传递路线,其静拉伸失效形式为金属韧性断裂后胶层脱粘的分步渐进式破坏;与含损伤未修补试样相比,胶接修补大幅度提高了试件的剩余强度和剩余寿命恢复率,修补后铝合金试件承载能力增加了约25%,疲劳寿命增加至修补前的约4倍~5倍。     

基于Zig-Zag变形假定的复合材料夹层板的自由振动

针对复合材料夹层板的实际变形特征，基于Zig-Zag变形假定和Mindlin一阶剪切理论，建立了复合材料夹层板自由振动的有限元模型，在该模型中分别对上、下面板和芯体建立了三个独立坐标系，使三部分的转角独立，为具有厚夹芯和软夹芯的复合材料夹层板的动力分析提供了一种更为准确的有限元模型；在此基础上推导了相应的刚度阵和质量阵，并采用子空间迭代法求解。夹层板的固有频率。通过典型考题证明了本模型的有效性。文中最后还通过参数讨论，研究了具有不同长厚比的复合材料夹层板基频的变化规律。     

位移模式下PMI泡沫夹层结构疲劳损伤试验研究

论文选取磁悬浮列车车身所用的由铝面板与聚甲基苯丙酰亚胺(PMI)聚合物泡沫芯层所组成的轻质夹层复合材料为研究对象,对夹层结构在室温下进行静态强度测试和进行以位移为控制变量的疲劳损伤演化试验,探讨分析了PMI泡沫夹层结构在交变位移控制下的疲劳性能和破坏行为.给出了PMI泡沫夹层结构在静态载荷作用下的力学性能参数.参考静态试验结果加载适当的位移载荷进行疲劳试验,发现在位移控制模式下,夹层结构的疲劳损伤过程和破坏模式明显区别于载荷控制模式.当最大控制位移较小时破坏形式为面板与泡沫层脱离;位移较大时为面板断裂和泡沫芯层塌陷.通过引入载荷的变化作为损伤参量建立了位移控制模式下损伤演变公式,并对两种模式的破坏行为进行了较好的预测.     

铝面板厚度对Nomex蜂窝夹层结构冲击后弯曲性能影响的试验研究

通过低速冲击试验和四点弯曲试验,研究了铝面板厚度对Nomex蜂窝夹层结构抗冲击能力和剩余强度的影响。结果表明:在冲击荷载作用下,面板发生变形的区域大小随面板厚度增加而变大,当面板厚度大于0.5mm时,变形区域直径趋于稳定;无论试件是否受到过冲击,在弯曲载荷作用下,0.2mm厚面板发生芯格内屈曲失稳,而其他厚度面板均发生格间失稳;对无冲击损伤的结构,0.2mm厚面板弯曲强度显著低于其他厚度面板;对含冲击损伤的结构,0.2mm厚面板的剩余强度百分比最高。     

复合材料层合板的低速冲击损伤及其剩余压缩强度研究

本文采用理论和实验方法研究了复合材料层合板的低速冲地及其剩余压缩强度。文中利用有限元方法和能量转换原理计算了层合板受到低速冲击的受载最危险状态，以及此时的应力分布；并用Ｔｓａｉ－Ｗｕ张量准则判断损伤情况，对产生损伤的单元进行相应的刚度折减，且作重复计算直至不产生新的损伤为止；最后，对受冲击的层合板还进行剩余压缩强度计算。在实验中，采用激光全息无损检测法测量了层合板的冲击损伤，并对受冲击的层合板进行     

复合材料燃料贮箱渐进损伤分析与剩余强度预报

基于复合材料渐进失效准则和刚度降阶模型,建立了复合材料燃料贮箱性能演化的 表征模型和分析模型,借助有限元软件ABAQUS对内压作用下复合材料贮箱结构的渐进损伤过 程进行了分析,实现了复合材料贮箱结构剩余强度的预报,通过与文献数据的比较,验证了 该分析方法的有效性.     

含冲击损伤复合材料层板及加筋壁板剩余强度研究

应用含刚度折减的椭圆形弹性核模拟了层板的损伤问题,研究了复合材料层板及加筋壁板冲击后的剩余强度问题。利用含椭圆核各向异性杂交应力有限单元对损伤层板进行了应力分析,采用基于特征曲线概念的点应力判据预测了含损伤层板、加筋壁板的剩余强度;基于Abaqus用户子程序uel实现了该方法在工程中的应用,并讨论各种参数对剩余强度的影响。研究结果表明此方法是有效的。     

正交复合材料面层夹层板非线性理论及应用

针对复合材料面层夹层板的构造和变形特点，考虑横向剪应力在面层和芯层粘结处的连续条件，应用Ｈａｍｉｌｔｏｎ原理建立了基于五个未知函数的正交铺设复合材料面层夹层板的非线性精化理论。对静力学问题，控制方程化简为由四个基本未知函数表述。文中还分析了简支正交铺设复合材料面层夹层板的非线性弯曲，给出了载荷—挠度特征关系和板中应力的分布状况。数值计算表明，夹层板面层和芯层粘结处的层间剪应力在工程设计中是十分重要的。     

Optimum design of laminated composite foam-filled sandwich plates subjected to strength constraint

Optimum design of laminated composite sandwich plates with both continuous (core thickness) and discrete (layer group fiber angles and thicknesses) design variables subjected to strength constraint is studied via a two-level optimization technique. The strength of a sandwich plate is determined in a failure analysis using the Tsai–Wu failure criterion and the finite element method which is formulated on the basis of the layerwise linear displacement theory. In the first level optimization of the design process, the discrete design variables are temporarily treated as continuous variables and the corresponding minimum weight of the sandwich plate is evaluated subject to the strength constraint using a constrained multi-start global optimization method. In the second level optimization, the optimal solution obtained in the first level optimization is used in the branch and bound method for solving a discrete optimization problem to determine the optimal design parameters and the final weight of the plate. Failure test of laminated composite foam-filled sandwich plates with different lamination arrangements are performed to validate the proposed optimal design method. A number of examples of the design of laminated composite foam-filled sandwich plates are given to demonstrate the feasibility and applications of the proposed method.     

含分层损伤复合材料层合板的压缩强度研究

给出了基于一阶剪切变形理论的含分层损伤层合板有限元分析模型,将含分层损伤层合板在压缩载荷作用下的强度破坏分析和屈曲破坏分析统一起来。先区分其破坏形式,然后再进行具体破坏分析,在屈曲特性分析中考虑了铺层强度破坏引起的刚度折减的影响,数值结果表明,该文给出的方法和结论对含分层损伤复合材料层合板的设计更具参考价值。     

Flat ended projectile penetrating ultra-high strength concrete plate target

Reactive powder concrete (RPC), a composite that has been developed in recent years, is a special mixture that is cured to have a higher compressive strength than that of concrete (about 200 MPa). Adding a few steel fibers can markedly increase its mechanical properties, such as tensile and bending strength, impact resistance and toughness. Hence, RPC is highly promising for use in the containment structures of nuclear power plants and in the protection of military facilities. This study evaluates the resistance of ultra-high strength concrete targets by high-velocity impact experiments. Test variables include the impact velocity and the amount of steel fibers added. The experimental results reveal that RPC plates, because of their higher compressive strength, are more fragile than normal concrete (NC) plates. However, adding a small amount of steel fibers significantly improved the impact resistance of the target plates. Moreover, a numerical simulation based on the nonlinear finite element code LS-DYNA was performed. The results of the numerical simulation have a good agreement with the experimental data and can be used for further research.     

ON RESIDUAL COMPRESSIVE STRENGTH PREDICTION OF COMPOSITE SANDWICH PANELS AFTER LOW-VELOCITY IMPACT DAMAGE

This paper introduces a nonlinear finite element analysis on damage propagation behavior of composite sandwich panels under in-plane uniaxial quasi-static compression after a low velocity impact. The major damage modes due to the impact, including the residual indentation on the impacted facesheet, the initially crushed core under the impacted area, and the delamination are incorporated into the model. A consequential core crushing mechanism is incorporated into the analysis by using an element deactivation technique. Damage propagation behavior, which corresponds to those observed in sandwich compression after impact (SCAI) tests, has been successfully captured in the numerical simulation. The critical far field stress corresponding to the onset of damage propagation at specified critical locations near the damage zone are captured successfully. They show a good correlation with experimental data. These values can be used to effectively predict the residual compressive strength of low-velocity impact damaged composite sandwich panels.     

Compressive response of a sandwich plate containing a cracked diamond-celled lattice

The compressive strength is determined for a sandwich plate containing a centre-cracked core made from an elastic–brittle, diamond-celled lattice. It is assumed that the lattice fails when the major component of principal stress anywhere in the lattice attains the compressive or tensile strength of the solid, or when local buckling intervenes. First, analytical and numerical predictions are given for the unnotched strength of the core and for the compressive fracture toughness of the lattice K_IC. Second, finite element simulations and analytical models are reported for the fracture response of the sandwich plate with cracked core. The active failure mechanism in the cracked core is sensitive to core height, crack length, lattice geometry and material choice; this is illustrated by means of material-property charts.     

One-dimensional response of sandwich plates to underwater shock loading

The one-dimensional shock response of sandwich plates is investigated for the case of identical face sheets separated by a compressible foam core. The dynamic response of the sandwich plates is analysed for front face impulsive loading, and the effect of strain hardening of the core material is determined. For realistic ratios of core mass to face sheet mass, it is found that the strain hardening capacity of the core has a negligible effect upon the average through-thickness compressive strain developed within the core. Consequently, it suffices to model the core as an ideally plastic-locking solid. The one-dimensional response of sandwich plates subjected to an underwater pressure pulse is investigated by both a lumped parameter model and a finite element (FE) model. Unlike the monolithic plate case, cavitation does not occur at the fluid-structure interface, and the sandwich plates remain loaded by fluid until the end of the core compression phase. The momentum transmitted to the sandwich plate increases with increasing core strength, suggesting that weak sandwich cores may enhance the underwater shock resistance of sandwich plates.     

BENDING RESPONSES OF AN EXPONENTIALLY GRADED SIMPLY-SUPPORTED ELASTIC/VISCOELASTIC/ELASTIC SANDWICH PLATE

The bending response for exponentially graded composite (EGC) sandwich plates is investigated.The three-layer elastic/viscoelastic/elastic sandwich plate is studied by using the sinusoidal shear deformation plate theory as well as other familiar theories.Four types of sandwich plates are considered taking into account the symmetry of the plate and the thickness of each layer.The effective moduli and Illyushin’s approximation methods are used to solve the equations governing the bending of simply-supported EGC fiber-reinforced viscoelastic sandwich plates.Then numerical results for deflections and stresses are presented and the effects due to time parameter,aspect ratio,side-to-thickness ratio and constitutive parameter are investigated.     

腐蚀环境下复合材料修补件力学特性研究

采用复合材料补片胶接修补含裂纹LY12CZ铝合金板,开展了试验室大气环境和加速预腐蚀环境下复合材料修补件静强度拉伸和疲劳裂纹扩展对比试验研究.结果表明,复合材料补片均能显著提高损伤结构的拉伸强度和疲劳寿命,且短周期的预腐蚀环境对修补件两种力学特性的影响可以忽略不计.同时,基于Paris公式和Rose分析模型,建立了常规环境和预腐蚀环境下疲劳裂纹扩展寿命预测模型,通过与试验结果的对比证明了该模型的工程有效性.     

多孔金属夹层板在冲击载荷作用下的动态响应

借助两种有限元软件ABAQUS和LS_DYNA, 模拟和分析了两种厚度不同的泡沫铝合金夹层板(三明治板)、方孔蜂窝形夹层板和波纹形夹层板在冲击载荷下的动态响应. 4种夹层板的单位面积密度相同,冲击载荷分别用泡沫铝子弹与不锈钢子弹模拟. 讨论了泡沫金属夹层板和格构式夹层板在不同冲击载荷作用下的变形机制,重点在于对夹层板的吸能特性及板内各部分吸能变化规律的探讨.研究结果表明: 在泡沫子弹冲击下,夹层板主要是通过自身变形来消耗子弹动能,并转化为自身内能. 厚度为22\,mm的泡沫金属夹层板吸收能量最多,底面变形最小,是结构性能最优的夹层板;在刚性子弹高速冲击穿透过程中,格构式夹层板的吸能性能比单位面积密度相同的泡沫金属夹层板的吸能性能更好. 波纹形夹层板的能量吸收能力在4种板中最高.      

In-plane properties of composite laminates with through-thickness pin reinforcement

Laminated fibre-reinforced composites can be reinforced by through-thickness pins to reduce their susceptibility to delamination. However, the presence of the pins creates resin pockets and disrupts the alignment of the fibres, and may thereby lead to a degradation of the in-plane strength of the composite. Experiments and numerical simulations show that the presence of through-thickness reinforcing pins decreases the tensile strength of the composite by 27%, and the compressive strength of the composite by at least 30%. It is also shown that the pattern in which the pins are inserted has a strong influence on the compressive strength. A pin pattern is identified in order to minimise fibre alignment disruption and thereby maximise the compressive strength.