混杂复合材料非对称铺层结构性能研究EI北大核心

混杂复合材料是两种或两种以上不同基体或增强材料组成的复合材料。混杂复合材料因选用了不同的材料,在性能上常有互补性。通过研究典型基体材料和典型增强材料组成的混杂复合材料,和混杂复合材料的非对称铺层特性,形成混杂复合材料非对称铺层制件。在单一材料性能基础上,主要研究典型混杂复合材料的性能,混杂复合材料非对称铺层结构的性能。     

面内线性变化载荷作用复合材料层合板的振动与屈曲优化

采用广义微分求积（GDQ）法开展了不同边界条件下承受面内线性变化载荷作用复合材料层合板振动与屈曲的分析与优化。针对GDQ法求解面内线性变化载荷工况复合材料层合板屈曲问题存在计算振荡、不收敛现象,提出载荷扰动策略实现了GDQ法对复合材料层合板屈曲问题的稳定高效求解。基于基础圆频率和临界屈曲载荷系数的归一化指标,分析了铺层角度对复合材料层合板综合性能的影响,并结合直接搜索模拟退火算法开展了复合材料层合板的铺层顺序优化。结果表明:铺层角度变化对屈曲性能的影响明显强于频率特性;面内线性变化载荷中,以弯曲载荷作用下复合材料层合板的优化综合性能受边界条件变化的影响最小,而优化铺层角度受边界条件变化的影响最大。研究结果为复杂载荷作用下复合材料层合板的设计提供了参考。      

纤维混杂铺层对无伞空投箱抗冲击性的影响

目的 对无伞空投箱所用的碳纤维、玻璃纤维、芳纶纤维/环氧树脂体系纤维混杂铺层的复合材料层合板进行研究,以在低成本下提高实现效果。方法 复合材料层合板分为10层,采用层间混杂结构,通过改变混杂比、铺层角度及铺层顺序,设计148种铺层方案,利用ANSYS–APDL软件分析3种参数变量对层合板拉伸性能及抗弯性能的影响。结果 沿主要受力方向铺设纤维,碳纤维层在外侧、玻璃纤维层集中在中心,且玻璃纤维层体积分数为40%时,材料具有最高的性价比。结论 针对混杂纤维复合材料层合板,通过调整混杂比得出碳/玻璃混杂纤维复合材料性能较好,通过调整铺层角度得出纤维铺设角度越接近受力方向其性能效果越好,通过调整铺层顺序得出不同混杂比、铺层角度下的最佳性能结构。     

双稳定矩形非对称复合材料层板的跳变研究

对双稳定矩形非对称复合材料层合板两种稳定构型的跳变行为进行了实验和数值研究。通过实验测得中心加载下层合板两种稳定构型跳变的临界载荷, 建立了两种稳定构型的非线性有限元分析模型, 成功预报了层合板固化后的两种稳定构型, 并进一步预报了两种稳定构型的跳变临界载荷, 预报结果与实验结果吻合良好。实验和有限元模拟结果表明, 中心加载下矩形非对称层合板两种构型的临界载荷相差较大, 并且跳变的过程有所差异。      

CF/GF混杂增强环氧树脂复合材料的高载动态黏弹特性

采用高载动态热机械分析仪EPLEXOR500对T300/S-2混杂纤维增强环氧树脂复合材料的动态黏弹特性进行了分析, 考察了静态载荷、 动态载荷对其储能模量、 损耗模量和损耗角正切的影响, 并研究和对比了不同载荷水平下混杂比以及混杂方式对动态黏弹性参数的影响规律。结果表明: 不同混杂比复合材料的储能模量均随动态载荷的增大而降低, 随静态载荷的增大而增大, 损耗模量和损耗角正切则随两种载荷的增大而降低。高载荷下混杂复合材料的储能模量仍较好地符合"复合梁理论"。动载扫描模式下, 损耗角正切随混杂比的变化基本符合"混合定律", 夹芯混杂复合材料的储能模量远高于层间混杂复合材料, 且损耗角正切也比层间混杂时大; 但在静载扫描模式下则是层间混杂复合材料的损耗角正切更大。      

碳纤维/Kevlar纤维混杂复合材料的研究进展

纤维混杂复合材料作为一种先进的复合材料,受到国内外众多研究者的青睐。介绍了纤维混杂复合材料的发展,并描述了纤维的混杂方式。着重概述了碳纤维/Kevlar纤维混杂复合材料在拉伸性能,冲击性能,压缩性能,摩擦性能,吸湿性能,阻尼性能,热性能方面的研究进展。简要探讨了纤维走向、铺层方式、混杂比等对其性能的影响。     

包装箱用混杂纤维复合材料的设计

目的 研究混杂纤维复合材料在静载荷作用和拉-拉疲劳载荷条件下的力学性能及其在包装箱等领域的应用。方法 采用树脂转移模塑成型工艺制备5种包装箱用混杂纤维复合材料,并对试样进行拉伸性能和拉-拉疲劳性能测试。结果 纯C试样的拉伸强度高于C/G层内和C/G层间试样;在相同的铺层和织布方式下,C/G层内试样的拉伸强度高于C/G层间试样;纯G试样的塑性明显优于C/G层内和C/G层间试样,C/G层内试样的断裂伸长率高于C/G层间试样;C/G层内试样具有混杂正效应,可保证在具有较高强度的同时具备良好塑性。玻璃纤维在提高复合材料料板疲劳寿命上的作用要高于芳纶纤维,前者的刚度退化会低于后者,且碳纤维和玻璃纤维的层内混杂方式要优于层间混杂,层间混杂在复合材料抵抗疲劳损伤时具有正混杂效应。     

湿热环境下玻/碳纤维混杂复合材料梁阻尼特性的细观力学分析

基于复合材料细观力学,利用能量耗散原理及宏观应变能法建立了湿热环境下玻/碳纤维混杂复合材料层合梁的阻尼预测模型。利用MATLAB软件编写了湿热环境下玻/碳纤维混杂复合材料损耗因子的计算程序,研究了纤维铺设角度、体积分数、铺层顺序以及湿热效应对玻/碳纤维混杂复合材料层合梁阻尼性能的影响规律。结果表明：湿热环境导致材料产生湿热应变是影响阻尼特性的主要机理;玻/碳纤维混杂复合材料层合梁的损耗因子均随温度及吸水浓度的增大而增大,且温度的影响远大于吸水浓度的影响;纤维体积分数越高,受湿热影响程度越大;铺层角度对损耗因子影响远高于湿热、混杂方式、纤维体积分数的影响。     

纤维/镁合金混杂层合板低速冲击响应及损伤模拟

为了研究新型纤维增强镁合金混杂层合板在低速冲击下的力学响应,分别对由玻璃纤维、碳纤维和二者混杂增强的AZ31B镁合金层合板在不同冲击能量下的落锤低速冲击试验进行了数值模拟。基于镁合金各向异性塑性本构和指数关系界面脱粘内聚力本构模型,同时纤维复合材料层采用三维Hashin失效准则且引入刚度折减,编写了复合材料层板损伤的VUMAT子程序,并将该子程序嵌入ABAQUS/Explicit中实现对层合板冲击过程的模拟。研究了该纤维层合板在不同冲击能量下的动态冲击响应以及脱粘与损伤演化规律,分析了冲击载荷、形变和能量吸收随时间的变化规律。模拟结果表明:在冲击能较小时,首先在冲击背面出现基体开裂,随着冲击能的增加,层合板受冲击面出现由无明显损伤到出现基体开裂和纤维断裂的现象;与单一碳纤维增强的镁合金层合板复合材料相比,单一玻璃纤维增强的镁合金层合板在冲击载荷作用时能够吸收更多的能量,碳纤维层内混杂合适的玻璃纤维铺层能够提高碳纤维增强镁合金层合板的抗冲击性能。     

含内埋矩形脱层板屈曲分析的传递函数方法

研究了含任意内埋矩形脱层复合材料层合板的屈曲问题。采用一种基于Mindlin一阶剪切理论的条形传递函数方法,将含内埋矩形脱层的复合材料层合板分成含脱层和不含脱层的两种矩形超级单元,然后由各超级单元之间连接结点处的位移连续和力平衡条件得到脱层板屈曲的特征方程,进而得到脱层板的屈曲载荷和屈曲模态。进行参数分析发现,脱层大小、深度、位置以及脱层板的边界条件和复合材料铺层方向对脱层板屈曲载荷的影响较显著。     

Thermal Response and Stability Characteristics of Bistable Composite Laminates by Considering Temperature Dependent Material Properties and Resin Layers

In this study, the stability characteristics and thermal response of a bistable composite plate with different asymmetric composition were considered. The non-linear finite element method (FEM) was utilized to determine the response of the laminate. Attention was focused on the temperature dependency of laminate mechanical properties, especially on the thermal expansion coefficients of the composite graphite-epoxy plate. Also the effect of including the resin layers on the stability characteristics of the laminate was investigated. The effect of the temperature on the laminate cured configurations in the range of 25°C to 180°C and ?60°C to 40°C was examined. The results indicate that the coefficient of thermal expansions has a major effect on the cured shapes. Next, optical microscopy was used to characterize the laminate composition and for the first time the effect of including the resin layers on the actuation loads that causes snapping behavior between two stable shapes was studied. The results obtained from the finite element simulations were compared with experimental results and a good correlation was obtained. Finally, the stability characteristics of a tapered composite panel were investigated for using in a sample winglet as a candidate application of bistable structures.     

Optimisation of blended bistable laminates for a morphing flap

Multistable composites offer significant deformations in stable shapes, and, this makes them interesting for morphing applications. Moreover, bistable laminates can be manufactured to have variable angle tows (VATs) in a ply using a tow-steering technique to ensure continuity of fibres over the planform of the laminates and, in doing so, may impart additional structural strength due to load path continuity along-with the prospect of easier integration with the major structure by blending lay-ups across components. The use of ant colony systems as an optimisation concept has been implemented, incorporating the feedback from the finite element analysis to identify blended VAT (equivalent) bistable laminate for a morphing flap application. Proof-of-concept is demonstrated by manufacture of VAT (equivalent) laminates. Presented research findings highlight the potential of blended bistable laminates, developed through optimisation based design methodology, for morphing applications.     

Local buckling loads of sandwich panels made with laminated faces

The paper is devoted to assessing the optimal arrangements of hybrid laminated faces of sandwich panels in order to maximize local buckling loads corresponding to the wrinkling of compressed faces. The analysis is carried out by modelling compressed faces as thin unsymmetric laminates resting on elastic two-parameter foundations. The First-order Shear Deformation Theory, in conjunction with the Rayleigh-Ritz method, has been used to evaluate buckling loads of simply supported flat laminates subjected to in-plane biaxial compression and shear forces. A numerical investigation is intended to support evidence for the influence of laminate parameters (fibre orientation, geometrical dimensions) and foundation parameters (modulus of subgrade reaction and shear modulus); obtained results are reported and discussed in the paper.     

Notched strength of woven fabric composites with moulded-in holes

The feasibility of enhancing damage tolerance and durability of fibre composites through the design of microstructure has been examined using three woven fabric-reinforced composite systems (carbon, Kevlar and carbon-Kevlar in epoxy matrix). Enhancement in notched strength has been demonstrated by comparing the performance of composites with drilled and moulded-in circular holes. Specimens with moulded-in holes exhibited failure strengths which were 2.7–38.3% higher than those of drilled specimens. Furthermore, for certain lay-ups of Kevlar and carbon-Kevlar hybrid laminates, the presence of moulded-in holes did not reduce the unnotched laminate strength; indeed a strength enhancement of 0.4–22.1% was observed. Comparisons of experimental data with existing notched strength theories are made and directions for future research are indicated.     

Effect of delamination failure in crashworthiness analysis of hybrid composite box structures

In the present paper the effects of delamination failure of hybrid composite box structures on their crashworthy behaviour will be studied and also their performance will be compared with non-hybrid ones. The combination of twill-weave and unidirectional CFRP composite materials are used to laminate the composite boxes. Delamination study in Mode-I and Mode-II with the same lay-ups was carried out to investigate the effect of delamination crack growth on energy absorption of hybrid composite box structures. The end-loaded split (ELS) and double-cantilever beam (DCB) standard test methods were chosen for delamination studies. In all hybrid composite boxes the lamina bending crushing mode was observed. Regarding the delamination study of hybrid DCB and ELS the variation of the specific energy absorption (SEA) versus summation of G_IC and G_IIC were plotted to combine the effect of Mode-I and Mode-II interlaminar fracture toughness on the SEA. From this relationship it was found the hybrid laminate designs which showed higher fracture toughness in Mode-I and Mode-II delamination tests, will absorb more energy as a hybrid composite box in crushing process. The crushing process of hybrid composite boxes was also simulated by finite element software LS-DYNA and the results were verified with the relevant experimental result.     

Buckling characteristics and layup optimization of long laminated composite cylindrical shells subjected to combined loads using lamination parameters

The buckling characteristics and layup optimization of long laminated composite cylindrical shells subjected to combined loads of axial compression and torsion are examined on the basis of Flügge’s theory. In the buckling analysis of long laminated composite cylindrical shells, 12 lamination parameters are introduced and used as design variables for layup optimization. Applying a variational approach, the feasible region in the design space of the 12 lamination parameters is numerically obtained. The buckling characteristics are discussed in the design space of the 12 lamination parameters. In the layup optimization, the optimum lamination parameters for maximizing the buckling loads and the laminate configurations for realizing the optimum lamination parameters are determined by mathematical programming methods. It is found that in case of combined loads of axial compression and torsion, the optimum laminate configurations are unsymmetric.     

Inperfection sensitivity of laminated cylindrical shells in torsion and axial compression

The imperfection sensitivity of thin cylindrical shells, made out of fiberreinforced composite material and subjected to either uniform axial compression or torsion, and the effects upon it of certain parameters, are investigated. The sensitivity is established through plots of critical loads (limit point loads) versus imperfection amplitude. The larger the drop in critical load value with increasing amplitude, the greater the sensitivity. Results are presented for four- and six-ply laminates with simply supported boundaries and various stacking sequences. These sequences lead to symmetric, antisymmetric and asymmetric configurations with respect to the laminate midsurface. The material for all configurations is boron/epoxy. The parametric studies include primarily the effect of lamina stacking and length-to-radius ratio on the critical loads. Among the important findings are that (a) laminated cylindrical shells are more imperfection sensitive under axial compression than under torsion, (b) the imperfection sensitivity decreases as the length-to-radius ratio increases and (c) lamina stacking has a pronounced effect on the imperfection sensitivity of the laminated shell.     

Combined tension and bending testing of tapered composite laminates

A simple beam element used at Bell Helicopter was incorporated in the Computational Mechanics Testbed (COMET) finite element code at the Langley Research Center (LaRC) to analyze the responce of tappered laminates typical of flexbeams in composite rotor hubs. This beam element incorporated the influence of membrane loads on the flexural response of the tapered laminate configurations modeled and tested in a combined axial tension and bending (ATB) hydraulic load frame designed and built at LaRC. The moments generated from the finite element model were used in a tapered laminated plate theory analysis to estimate axial stresses on the surface of the tapered laminates due to combined bending and tension loads. Surfaces strains were calculated and compared to surface strains measured using strain gages mounted along the laminate length. The strain distributions correlated reasonably well with the analysis. The analysis was then used to examine the surface strain distribution in a non-linear tapered laminate where a similarly good correlation was obtained. Results indicate that simple finite element beam models may be used to identify tapered laminate configurations best suited for simulating the response of a composite flexbeam in a full scale rotor hub.The U.S. Government right to retain a non-exclusive, royalty-free license in and to any copyright is acknowledged.