Manufacturing and testing of a CFRC sandwich cylinder with Kagome cores

Filament winding and twice co-curing processes were proposed to make a carbon fiber reinforced composite (CFRC) sandwich cylinder with Kagome cores. Axial compression was carried out to reveal the stiffness and load capacity of the fabricated sandwich cylinder. Compared with the stiffened cylinder with similar dimensions and mass, the sandwich cylinder is shown to be stiffer and stronger by several times. Restrained by the double skins, the buckling of lattice ribs is effectively suppressed, leading to the elimination of the dominant failure mode. Skin crippling and strength failure were observed in the testing to be the competing failure mechanisms of the lattice sandwich cylinder. The prediction based on the weakest link of these mechanisms only overestimates the testing load capacity by 30%. The novel sandwich structure shows the promise of lattice composites in upgrading the mechanical properties.     

A novel carbon fiber reinforced lattice truss sandwich cylinder: Fabrication and experiments

To get a strong, stiff and weight efficient cylindrical shell, a novel carbon fiber reinforced corrugated lattice truss-core sandwich cylinder (LTSC) was designed and fabricated. The core is made up of orthogonal corrugated trusses and manufactured by mould pressing method. The LTSC is fabricated by filament winding and co-curing method. The face sheets have layups of [0°/30°/−30°/−30°/30°/0°] to improve the fundamental frequency as it is controlled by the circumferential stiffness. In end-free vibration the fundamental frequency of the LTSC is 112.18 Hz, higher than the referenced quasi-isotropic Isogrid-core sandwich cylinder. Determined by the skin fracture, the compression strength of the LTSC is 328.03 kN, stronger than the referenced Isogrid-core sandwich cylinder failed at rib buckling and the post-failure deformation is ductile. According to the optimization scheme jointly constrained by the strength and the fundamental frequency, an ultra-light and strong cylinder with high fundamental frequency was successfully fabricated.     

An optimization of composite lattice cylinder using the approximate method

Recently, the approximate methods based on continuous models have been developed to perform structural analysis of composite lattice structures due to their relative simplicity and computational efficiency. This paper defines the modified effective stiffness considering the directionally dependent mechanical properties to an intersection of ribs and mode shape function of a composite lattice cylinder. It subsequently presents an approximate method based on the continuous model of conducting a buckling analysis of the composite lattice cylinder with various boundary conditions under uniform compression. This method considers the coupled buckling mode as well as the global and local buckling modes. The validity of the present method is verified by comparing the results of the finite element analysis. In addition, a parametric analysis is performed to investigate the effects of the design parameters on the critical load and buckling mode shape of the composite lattice cylinder based on the present method. Finally, we apply the present method to perform the optimization of a composite lattice cylinder for a high-speed vehicle to minimize the mass. Consequently, it is concluded that the present method is very suitable to optimization of composite lattice cylinders due to their relative simplicity and computational efficiency.     

Compression and bending performances of carbon fiber reinforced lattice-core sandwich composites

To restrict debonding, carbon fiber reinforced lattice-core sandwich composites with compliant skins were designed and manufactured. Compression behaviors of the lattice composites and sandwich columns with different skin thicknesses were tested. Bending performances of the sandwich panels were explored by three-point bending experiments. Two typical failure mechanisms of the lattice-core sandwich structures, delaminating and local buckling were revealed by the experiments. Failure criteria were suggested and gave consistent analytical predictions. For panels with stiff skins, delamination is the dominant failure style. Cell dimensions, fracture toughness of the adhesives and the strength of the sandwich skin decide the critical load capacity of the lattice-core sandwich structure. The mono-cell buckling and the succeeding local buckling are dominant for the sandwich structures with more compliant skin sheets. Debonding is restricted within one cell in bending and two cells in compression for lattice-core sandwich panels with compliant face sheets and softer lattice cores.     

海洋结构CFRP环向约束钢管混凝土柱在压弯扭荷载下的力学性能研究

为了研究CFRP环向约束钢管混凝土柱在压弯扭复合荷载下的力学性能,该文开展了4个CFRP环向约束钢管混凝土柱和2个钢管混凝土柱的拟静力试验,主要参数为CFRP层数和轴压比,得到了在弯扭、压弯扭两种荷载作用下柱的破坏模式和荷载-变形曲线。试验结果表明, CFRP环向约束钢管混凝土柱的破坏模式为弯型破坏,其破坏过程为:塑性铰区域钢管局部屈曲、CFRP形成环向裂纹,随后CFRP断裂、与钢管剥离,最后钢管局部屈曲部位开裂。轴力的存在会使得钢管更容易出现“象腿”破坏模式。在弯扭荷载下, CFRP环向约束对钢管混凝土的延性以及承载力提高不明显;在压弯扭荷载下, CFRP环向约束能有效提高钢管混凝土的延性及其耗能能力,减缓刚度退化,但对承载力的提高不明显。此外,增加CFRP层数能有效抑制钢管的局部屈曲,增强耗能能力。     

薄壁钢板组合截面PEC柱抗震性能的足尺试验研究

为了研究薄壁钢板组合截面PEC柱(强轴)在恒定竖向荷载下的抗震性能,通过了解国内外在PEC组合柱研究领域的现状,对3 个变化混凝土强度的薄壁钢板组合PEC柱足尺试件进行了恒定轴压下水平循环荷载试验.观测记录了各个试件受力阶段的外在混凝土裂缝与压溃和薄壁钢板组合截面翼缘钢板局部屈曲现象,得到了试件的荷载-位移滞回曲线.根据试验结果分析了试件的抗侧刚度、裂缝开展与破坏模式、试件的抗震延性与耗能等力学性能.结果表明:试验试件具有较高的承载能力和较好的延性与耗能性能;构件的破坏模式为薄壁钢板组合截面翼缘发生局部屈曲、柱脚混凝土压溃和拉结筋屈服甚至拉断.     

复合材料夹芯梁屈曲破坏模式及极限承载

为研究复合材料夹芯梁在轴压作用下的屈曲、后屈曲特性及承载能力,进行了试验研究与有限元仿真。首先,开展了系列复合材料夹芯梁屈曲特性试验,研究了铺层比例、梁长度、表层厚度及芯层厚度等因素对其屈曲、后屈曲破坏模式及极限承载的影响;然后,基于非线性屈曲理论,采用三维内聚力界面单元模拟面芯脱粘,并引入初始预变形及材料损伤准则对复合材料夹芯梁在轴压下的屈曲特性及极限承载进行仿真研究。结果显示:界面脱粘是屈曲破坏的重要模式;仿真计算的极限承载与试验结果相比,误差控制在10%以内。所得结论表明该方法可有效预报复合材料夹芯梁的后屈曲路径、破坏模式及极限承载。      

含孔复合材料点阵夹层结构数值计算方法及其影响因素

针对含孔复合材料点阵夹层结构在面内压缩载荷作用下的失效模式及其影响因素问题,通过实验对含孔复合材料点阵夹层结构失效模式进行了研究;基于3D Hashin准则和Chang-Chang刚度退化准则建立了含孔复合材料点阵夹层结构有限元渐进损伤失效分析模型,并将计算结果与实验结果进行了对比;基于有限元分析方法探讨了开孔形状、开孔率以及开孔位置对其极限承载力的影响。结果表明:当点阵夹层结构面板厚度较大时,含孔复合材料点阵夹层结构的主要失效模式为面板圧溃;通过对比有限元计算结果和实验结果,极限承载力的最大误差约为12%,失效位置与实验结果一致;当点阵夹层结构的对称面与载荷方向平行且孔的中心在对称面上时,面内压缩强度与开孔位置无关,主要受到开孔形状和开孔率的影响;当点阵夹层结构对称面与载荷方向垂直且孔的中心在对称面上时,边距大于一个胞元,面内压缩强度基本不变,边距小于一个胞元,面内压缩强度下降。     

多级三角形格栅夹芯板力学分析

为了提高点阵复合材料结构的轻质高强力学特征,尤其提高其抗屈曲性能,设计了一种新型的多级三角形格栅夹芯板结构。根据等效连续介质力学方法提出了多级三角形格栅夹芯板的等效计算理论,预测了拉伸主导型多级三角形格栅夹芯板结构的等效弹性模量以及等效抗弯刚度。分析了侧压条件下多级三角形格栅夹芯板的弹性屈曲载荷和强度破坏模式。在理论模型的基础上绘制了侧压条件下多级三角形格栅夹芯板结构的失效模式图,指出了结构破坏模式与多级三角形格栅夹芯板尺寸之间的对应关系。研究表明:具有工字型截面的多级三角形格栅夹芯板结构相比于传统矩形截面格栅结构具有更高的抗弯刚度和弹性屈曲载荷,是一种性能更加优越的轻质高强点阵结构。      

Mechanical Behavior of CFRP Lattice Core Sandwich Bolted Corner Joints

The lattice core sandwich structures have drawn more attention for the integration of load capacity and multifunctional applications. However, the connection of carbon fibers reinforced polymer composite (CFRP) lattice core sandwich structure hinders its application. In this paper, a typical connection of two lattice core sandwich panels, named as corner joint or L-joint, was investigated by experiment and finite element method (FEM). The mechanical behavior and failure mode of the corner joints were discussed. The results showed that the main deformation pattern and failure mode of the lattice core sandwich bolted corner joints structure were the deformation of metal connector and indentation of the face sheet in the bolt holes. The metal connectors played an important role in bolted corner joints structure. In order to save the calculation resource, a continuum model of pyramid lattice core was used to replace the exact structure. The computation results were consistent with experiment, and the maximum error was 19%. The FEM demonstrated the deflection process of the bolted corner joints structure visually. So the simplified FEM can be used for further analysis of the bolted corner joints structure in engineering.     

轴向运动黏弹性夹层板的多模态耦合横向振动

基于薄板小挠度理论和Kelvin-Voigt黏弹性本构方程, 建立了轴向运动黏弹性夹层板横向振动控制方程, 研究了其横向振动特性。采用一阶和二阶Galerkin截断得到夹层板横向振动的特征方程, 讨论了两种夹心层所占总厚度比率下轴向运动速度对其横向振动特性的影响。研究表明: 在未超过临界速度前, 无论一阶还是二阶截断, 在定性描述系统特征上二者相同, 但一阶截断不适合描述轴向运动速度超过临界速度的情形; 对四边简支黏弹性夹层板, 临界速度和发生耦合模态颤振的速度随着夹心层比率的减少逐渐增大。     

新型卷边钢板组合截面PEC柱(强轴)滞回性能试验研究

为进一步改善现行薄壁钢板组合截面PEC柱构件双向不等刚度和翼缘局部屈曲过于集中等力学性能缺陷,该文提出了采用翼缘钢板卷边的新型卷边钢板组合截面PEC柱类型。以拉结板条间距作为基本参数,对4个按新型卷边钢板组合截面强轴布置的足尺试件进行了恒定竖向荷载下的水平低周反复荷载试验,观察了试验过程中PEC柱卷边钢板组合截面翼缘钢板局部屈曲和混凝土部分裂缝开展与压溃发展过程,得到了试件的荷载-位移滞回曲线。根据试验结果分析了PEC柱的承载力、抗侧刚度、耗能与延性、变形模式与破坏模态等力学性能。结果表明:试验卷边PEC柱试件充分发挥了薄板局部屈曲后性能,具有优越的变形与耗能能力;构件的破坏模式为柱脚部位卷边钢板组合截面翼缘局部屈曲部位不断扩展和伴随混凝土大面积压溃。     

高速冲击载荷作用下钎焊蜂窝夹层板动态响应

目的 以钎焊高温合金蜂窝夹层板为研究对象,分析其在弹丸高速冲击作用下的力学性能。方法 采用轻气炮冲击加载试验结合有限元模拟,对蜂窝夹层板开展不同冲击强度下的动态响应和失效研究。开展含高速冲击损伤的蜂窝夹层板侧压试验,研究损伤模式对剩余强度的影响。结果 冲击强度对夹层板的失效过程和失效模式有着明显的影响,当冲击条件不足以使得迎弹面发生侵彻时,夹层板失效为表面压痕损伤;随着冲击强度的提高,出现不同程度的局部芯层压缩;当冲击强度大于临界值时,迎/背弹面陆续被侵彻,夹层板出现侵入损伤及贯穿损伤。结论 高速冲击损伤使得蜂窝夹层板的侧压失效模式,由理想塑性屈曲转变为局部失稳,侧压极限载荷大幅降低。     

复合材料褶皱夹芯结构的制备及压缩性能研究

目的 探究复合材料褶皱芯子的一次性成型工艺,并研究浸胶量对褶皱夹芯结构压缩性能的影响。方法 以V型褶皱夹芯结构为研究对象,首先采用真空吸附成型工艺制备V型复合材料褶皱芯子,然后通过黏接工艺将碳纤维复合材料层合板与褶皱芯子进行复合,得到复合材料褶皱夹芯结构,最后通过实验测试,研究该结构在压缩载荷作用下的力学性能和失效模式,以及不同浸胶量对其压缩性能的影响。结果 采用真空吸附成型工艺能够一次性制备出褶皱芯子,其成型精度有待提高;由压缩实验可知,褶皱夹芯结构先从壁面开始失效,后逐步扩散至棱线处,最终导致芯子的整体失效;由压缩实验测试结果可知,浸胶量(质量分数)为11%、17%、22%的褶皱夹芯结构的破坏载荷分别为362.853、420.521、471.389 N。结论 采用真空吸附成型工艺可一次性成型出褶皱芯子,其制备效率较高,但存在成型尺寸精度不高问题,后续需要进一步改进;在一定范围内,复合材料褶皱夹芯结构的压缩破坏载荷与芯子的浸胶量近似成正比例线性关系。     

结构参数对树脂基纤维编织复合材料折叠夹芯结构力学性能的影响

折叠夹芯结构是一种新型的复合材料夹芯结构,其结构参数对力学性能有重要的影响。文中以碳纤维和Kevlar平纹编织预浸料为芯材原料,采用热压工艺,制备了复合材料折叠夹芯结构试样。通过压缩试验得到不同条件下折叠夹芯结构在静态压缩载荷作用下的力-位移变化曲线。构建了复合材料折叠夹芯结构有限元模型,对不同结构参数复合材料折叠夹芯的力学性能进行了数值模拟分析,并将模拟结果与实验结果进行对比验证了模型的可靠性。实验及数值模拟的分析结果表明,随着芯材厚度的增加,折叠夹芯层的压缩强度呈线性增加,其破坏形式由假塑性变形逐渐向脆性破坏转化;面板对夹芯层的约束作用能够极大地提高压缩模量和强度,而且上下面板对压缩性能曲线有着不同的影响;折叠夹芯单元的高度、长度、折叠夹角等参数对其力学性能具有不同程度的影响。     

陶瓷棒填充点阵金属夹层结构的制备及抗侵彻实验

为提高轻量化复合装甲的抗侵彻能力,提出了内部填充陶瓷棒并由混杂短切玻璃纤维的环氧树脂封装的点阵金属夹层防护结构。首先,通过弹道冲击实验研究了陶瓷棒填充点阵金属夹层防护结构的抗弹丸侵彻能力;然后,结合失效模式和吸能效率,综合分析了该夹层防护结构的抗侵彻机制。结果表明:陶瓷棒填充点阵金属夹层防护结构的主要失效模式包括点阵金属结构和混杂填充材料的拉伸断裂、陶瓷棒的破裂、面板和背板的局部剪切破坏以及背板的总体弯曲变形。在球形弹丸侵彻过程中,由于点阵金属结构的塑性大变形和剪切扩孔、陶瓷棒和环氧树脂的断裂破坏以及面板的宏观弯曲变形,防护结构的抗侵彻能力得到大幅提高。研究结果可为新型轻质复合装甲的防护设计提供一定参考。      

轴压圆柱钢薄壳稳定设计综述

轴压圆柱薄壳广泛应用于土木工程中的各类钢壳结构,包括筒仓、塔桅、烟囱及容器等。轴压圆柱壳的屈曲问题一直是壳体稳定研究中最为活跃的课题之一。本文全面总结轴压圆柱壳稳定设计方面的研究成果及设计准则。首先简要回顾轴压圆柱壳的弹性经典解及初始缺陷敏感性的经典研究,接着对实际结构中的初始缺陷与制作过程的关系以及焊接残余应力对屈曲强度影响的近期研究进展进行了总结。然后,在简单介绍欧洲钢结构协会规程对轴压圆柱壳稳定设计有关规定的基础上,详细说明了新的欧洲钢壳设计规范所给出的设计准则及相应的研究背景。     

飞机典型薄壁复合材料夹层结构整体屈曲

为了研究飞机机身无筋无框复合材料典型薄壁夹层结构在型号上应用的可行性,本文采用解析方法、有限元方法和试验方法对蜂窝夹层复合材料结构的面内压缩和剪切整体屈曲开展系统研究。基于经典层合板理论和工程解析方法推导蜂窝夹层复合材料的压缩和剪切屈曲载荷随试验件尺寸的变化规律。依据某型飞机机身典型结构分别设计压缩和剪切试验件尺寸大小、边界条件和加载方式。利用有限元商用软件ABAQUS对试验设计建立虚拟试验分析,对比验证解析方法和有限元方法的一致性。最后通过真实试验方法确定解析方法和有限元方法的有效性,并验证典型薄壁夹层结构的承载能力和破坏模式。结果显示,压缩试验结果失效模式与理论预测一致,故3种方法得到的结构整体失稳载荷相近,验证了理论方法的有效性;剪切试验结果发生局部破坏,故试验结果偏低,但有限元方法与解析方法所得结果一致,解析方法相对保守。     

Failure analysis of adhesive surface damage in sandwich plates under compressed loads

Abstract

Failures of honeycomb sandwich plates are analyzed using experiments and three-dimensional (3D) finite element simulations to understand the failure mechanism. Meanwhile, correlations of the critical load and various physical parameters (e.g., height and thickness of the core) are investigated. The results demonstrated that the core height and skin thickness have significant effects on the compressed load buckling of the honeycomb sandwich plates, the core density is a sub-critical sensitive factor, while wall thickness and spacing of the cell, and the sandwich modulus have negligible effects. Cracking on the adhesive surface is the dominant factor to reduce the buckling critical load of the laminated plate, which leads to failures of sandwich plates. The ultimate failure of the sandwich panel is attributed to severe deformations that lead to local cracking of the entire cemented adhesive surface. Due to the bonding of the adhesive surface defects, the actual loads related to the core height are large enough to cause compressions with local buckling. Hence, the actual loads cannot reflect the performance of the sandwich panels. It is recommended to use panels with appropriate thicknesses below the sandwich and moderate grid density in the design.     

锈损冷弯薄壁卷边槽钢短柱受压承载力试验研究

为研究锈损对冷弯薄壁型钢短柱受压承载性能的影响,设计加工了6个轴压及6个绕强轴偏心受压短柱试件,首先通过拉伸试验,分析了材料力学性能与锈蚀程度间的关系,然后对试件进行承载力试验,分析其破坏模式、极限承载力及变形特征等特性,结果表明:锈损钢材的屈服、抗拉强度、弹性模量及伸长率均随锈蚀程度的增加呈线性下降趋势。锈损未使短柱试件的最终破坏模式发生变化,但随着偏心距的增大,试件由腹板局部屈曲变为以畸变屈曲为主的耦合破坏模式;在相同锈蚀率条件下,轴压试件的极限承载能力较偏压试件退化更明显。采用ABAQUS有限元软件对试件进行数值模拟,计算结果表明其能够较好的预测试件承载力及屈曲行为。