Filters for manufacturability in design optimization of variable stiffness composites

In the design optimization of variable stiffness composites, manufacturing constraints imposed by the automated fiber placement technology must be considered. In the present paper, two filters are proposed to address this issue, and they are incorporated into the Shepard interpolation-based design optimization framework developed in our previous studies. The fiber angle arrangement of a composite is represented by a continuous function that interpolates fiber angles at scattered design points. Two filters are appointed for each design point to deal with two typical manufacturing constraints, i.e., fiber curvature and gap/overlap. At each design point, the sensitivity is first filtered in a rectangular region around this point, and by this means the fiber curvature is controlled; then in another rectangular region around this design point, the filtered sensitivities are averaged, and the result is used to update the corresponding design variable. Several numerical examples are investigated, and the results show that the proposed method is effective.     

基于能量等效的2.5维机织复合材料刚度预测

提出了用能量等效原理预测2.5维机织复合材料经向拉伸的弹性模量的方法。以2.5维机织复合材料受经向拉伸载荷时经纱的变形为基础,分析了受经向拉伸载荷时2.5维机织复合材料中经纱、纬纱和填充树脂的变形能,利用各组分材料的变形能之和与整体复合材料的变形能相等的原理,推导出2.5维机织复合材料的经向拉伸弹性模量的计算方法。与试验数据对比发现,本文方法对经纬向拉伸弹性模量的预测结果比采用组分材料力学性能体积平均加权的方法更加精确。结果验证了本文方法的合理性,表明本文的计算公式对纬向拉伸时同样适用,并且本文方法所需要的基础参数更容易获得。     

缝合复合材料层合板面内拉伸强度的分析

提出了缝合复合材料层合板抗拉强度的微观分析方法,建立了针脚处纤维局部弯曲的几何模型。使用最大应力准则和强度破坏指标相结合的方法,根据主承力层的失效得到层合板的抗拉强度。计算结果表明,理论预测值与试验结果吻合良好,证实了该模型的正确性和可靠性。     

Fatigue life prediction model of 2.5D woven composites at various temperatures

As one of the new structural layout in the family of woven composites, 2.5D Woven Composites(2.5D-WC) have recently attracted an increasing interest owing to its excellent properties, i.e. high specific strength and fatigue resistance, in the aerospace and automobile industry. Indepth understanding of the fatigue behavior of this material at un-ambient temperatures is critical for the engineering applications, especially in aero-engine field. Here, fatigue behavior of 2.5D-WC at different temperatures was numerically investigated based on the unit cell approach. Firstly, the unit cell model of 2.5D-WC was established using ANSYS software. Subsequently, the temperature-dependent fatigue life prediction model was built up. Finally, the fatigue lives alongside the damage evolution processes of 2.5D-WC at ambient temperature(20 ℃) and unambient temperature(180 ℃) were analyzed. The results show that numerical results are in good agreement with the relevant experimental results at 20 and 180 ℃. Fatigue behavior of 2.5D-WC is also sensitive to temperature, which is partially attributed to the mechanical properties of resin and the change of inclination angle of warp yarns. We hope that the proposed fatigue life prediction model and the findings could further promote the engineering application of 2.5D-WC, especially in aero-engine field.     

三维角联锁机织复合材料剪切性能有限元分析

使用三维绘图软件Pro/E 5.0构建出一种三层角联锁机织复合材料的细观结构模型,借助有限元软件ANSYS对复合材料在剪切力作用下纤维与树脂的应力、应变分布进行数值模拟,并借此分析该复合材料在剪切作用下的力学行为,并预测复合材料破坏模式。结果表明:复合材料在剪切力作用下发生沿剪切力方向程度较均匀的剪切变形;纤维相对于树脂承受更多剪切力作用,产生更大应力,但发生相对较小的应变;纤维中轴向与剪切力方向平行的经纱相对轴向垂直于剪切力的纬纱表现出更大的应力和应变。     

Ti/CFRP超混杂层板的研究与应用展望

Ti/CFRP超混杂层板具有高比强度、高损伤容限及优异的疲劳性能,是航空航天领域的重要选材对象之一。界面性能决定了层板综合力学性能的好坏,是Ti/CFRP层板目前的研究热点。首先综述了钛和钛合金不同表面处理工艺;然后介绍了Ti/CFRP层板力学性能试验及理论预报的研究现状;最后通过分析Ti/CFRP层板航空航天领域的现有应用情况,展望了Ti/CFRP层板未来潜在的应用方向。     

Assessment of two quasi-static approaches to mimic repeated impact response and damage behaviour of CFRP laminates

Full impact damage tolerance assessment requires the ability to properly mimic the repeated impact response and damage behaviour of composite materials using quasi-static approximations. To this aim, this paper reports an experimental investigation evaluating two quasi-static methods for mimicking repeated impact response and damage behaviour of Carbon Fibre Reinforced Polymer (CFRP) composite laminates. In this study, an 8.45-J single impact was repeated 225 times and mimicked with 225 times 6.51-J quasi-static (energy equivalent) indentations and with 225 quasi-static (force equivalent) indentations following the recorded impact peak force variation. Results show that the loading rate and the inertial effect are the two major factors affecting the responses of the composite laminates under out-of-plane concentrated loading. Both the energy- and force-equivalent quasi-static indentations failed to reproduce the impact responses greatly associated with high loading rate and inertial effect. The force-equivalent quasi-static indentations were performed in a semi-automatic way and induced damage states more similar to those of the repeated impacts than those of the energy-equivalent quasi-static indentations, whereas the latter can be better automated and has better reproducibility compared to that of the repeated impact responses, as it is less dependent on high loading rate and inertial effect.     

Experimental and numerical investigation of mechanical behavior of plain woven CFRP composites subjected to three-point bending

The mechanical behavior of plain woven Carbon Fiber-Reinforced Polymer (CFRP) composites under Three-Point Bending (TPB) is investigated via experimental and numerical approaches. Multiscale models, including microscale, mesoscale and macroscale models, have been developed to characterize the TPB strength and damages. Thereinto, Representative Volume Elements (RVEs) of the microscale and mesoscale structures are established to determine the effective properties of carbon-fiber yarn and CFRP composites, respectively. Aimed at accurately and efficiently predicting the TPB behavior, an Equivalent Cross-Ply Laminate (ECPL) cell is proposed to simplify the inherent woven architecture, and the effective properties of the subcell are computed using a local homogenization approach. The macroscale model of the TPB specimen is constructed by a topology structure of ECPL cells to predict the mechanical behavior. The TPB experiments have been performed to validate the multiscale models. Both the experimental and numerical results reveal that delamination mainly appears in the top and bottom interfaces of the CFRP laminates. And matrix cracking and delamination are identified as the significant damage modes during the TPB process. Finally, the quasi-static and dynamic behaviors of plain woven composites are discussed by comparing the results of Low-Velocity Impact (LVI) and TPB simulations.     

拉伸载荷下正交三向机织复合材料接头失效多尺度渐进损伤分析

针对机械打孔三维机织复合材料耳片接头的单轴拉伸破坏性能，采用多尺度分析方法研究孔边纱线破坏过程。结果表明，正交三向（ORT）机织复合材料接头孔边的连续的经纱出现大量的纵向损伤；纬纱单元出现大量横向损伤，损伤沿着孔边45°方向逐渐扩展，纬纱发生剪切失效，最终接头的损伤形式为剪切破坏。数值模拟和试验结果的误差为1.14％，验证了多尺度有限元仿真方法的正确性。孔边细观区域的纱线损伤从孔边扩展到边接头边缘。孔边纱线的分布位置不同，纱线的破坏形式虽不一样，但是不影响破坏的扩展趋势。     

芳纶纤维表面改性及在EPDM 中的分散性

分别采用超声波法和物理机械法对芳纶纤维进行表面改性,研究了两种处理方法对其表面形貌、

分散性以及EPDM 复合材料性能的影响。结果表明:超声法和机械法使芳纶纤维表面形成差别较大的形貌特

征;其中芳纶经机械处理后呈现良好的分散性,其复合材料的拉伸强度和烧蚀深度分别为11. 3 MPa 和1. 2 mm

(10 phr),优于超声波法处理的结果。