薄弱环节对复合材料波纹梁吸能能力的影响

薄弱环节设置是复合材料吸能结构的关键技术,良好的设计可以使复合材料结构产生稳定的渐进压溃,从而吸收较多的能量.基于波纹梁准静态轴向压溃实验结果,运用MSC/DYTRAN有限元软件建立了三组不同尺寸的碳纤维-环氧树脂波纹梁的有限元模型,在数值模拟结果与实验结果基本吻合的基础上,分析了不同薄弱环节设置对复合材料波纹梁峰值载荷、吸能能力的影响,并进一步比较了不同薄弱环节设置的波纹梁在以6.5m/s的速度碰撞刚性地面时的能量吸能能力.     

复合材料吸能圆管在半圆凹槽触发机制下的斜向压溃失效行为

有效的触发机制能诱导并改善复合材料吸能结构的轴向渐进压溃行为,但仍无法解决汽车吸能结构在斜向冲击载荷下的失稳问题。为了提出新的设计来改善失稳行为,对复合材料吸能圆管在半圆凹槽触发机制下的斜向压溃行为和失效机制进行研究。建立引入半圆凹槽触发机制的圆管有限元模型,采用界面和层内非线性损伤演化模型来模拟其真实的压溃失效模式。通过对比模拟和实验对应的轴向压溃载荷、吸能和失效模式来验证圆管的准静态压溃模型。进而,预测斜向压溃角度(10°～50°)对圆管在半圆凹槽触发机制下压溃行为的影响,并详细揭示其轴向和斜向压溃失效机制及其区别。结果表明,压溃载荷、吸能及失效面积随角度增大而明显减小,不稳定的压溃过程使材料失效耗能不充分。圆管在轴向压溃下表现为渐进破坏,而在斜向压溃下以“渐进破坏”向“失稳破坏”过渡为特征,导致斜向压溃载荷与吸能曲线均存在一个过渡。本研究加深了对圆管在外部触发机制下斜向压溃失效机制的理解,为改善斜向压溃失稳行为提供了一定的设计依据。     

纤维铺层角度对复合材料薄壁圆管轴向压溃吸能特性影响研究

研究T700/3234复合材料薄壁圆管轴向压溃吸能特性受纤维铺层角度变化的影响规律。开展复合材料力学性能试验和薄壁圆管轴向准静态压溃试验。通过对比圆管轴向压溃峰值载荷及比吸能等指标的试验结果,验证建立的复合材料圆管有限元模型和分析方法。基于验证的有限元分析方法,探讨了复合材料纤维铺层角度的变化对薄壁圆管轴向压溃吸能特性的影响规律。结果表明,在准静态轴向压缩载荷下,随着纤维铺层角度的增大,比吸能先增大后减小;纤维角度为±45°时,初始峰值载荷最低,载荷效率最高,圆管易于进入渐进破坏吸能阶段。研究结果可为复合材料纤维铺层角度设计及复合材料薄壁结构有限元建模提供参考。     

直升机抗坠毁元件构形设计分析研究

为探究差异化的构形参数对复合材料波纹梁吸能性能影响,针对多种构形波纹梁,进行动态压溃试验,对试验现象分析及试验数据处理,给出了多种构形波纹梁的载荷-时间曲线和破坏模式。采用有限元软件ABAQUS模拟波纹梁的瞬态冲击过程,得到吸能特性参数比吸能(SEA)和平均载荷值等,并与试验结果对比,对比结果验证了数值模型的有效性。通过试验及数值分析结果讨论了波纹构形对波纹梁峰值载荷和吸能能力的影响,对不同构形波纹梁以及增加薄弱环节设计的吸能差异作出评估,为实际工程设计提供参考依据。结果表明,利用等截面剖面杆轴向压缩载荷作用下的临界应力方程将波纹梁梁高/波幅比、波长/波幅比设定在相应关系式时波纹梁结构表现出较为稳定的压溃过程,具有一定的应用价值;波纹腹板圆角R值除了对峰值载荷及平均载荷有影响,对波纹梁破坏模式改变也有一定关系,薄弱圆角r值能比较好的改善峰值载荷大小。     

具有褶皱薄弱段的正弦波纹梁吸能性能研究

薄弱环节的设置对波纹梁吸能性能的影响很大,好的薄弱环节可以降低波纹梁的冲击过载,从而降低结构传递给乘员的过载,并使波纹梁产生稳定的渐进压溃,以吸收更多的能量。提出了褶皱薄弱环节的概念,并对带有褶皱薄弱环节的波纹梁吸能性能进行了研究。对具有弧形薄弱段的波纹梁进行了有限元仿真,验证了仿真分析方法的正确性。在此基础上,建立了带有褶皱薄弱段的正弦波纹梁的有限元模型,对波纹梁几何参数对其吸能性能、坠毁冲击时的最大加速度的影响进行了研究。研究发现:褶皱薄弱环节能够有效降低波纹梁的最大冲击载荷,且对波纹梁吸能性能的影响不大。以上研究结果对波纹梁在吸能结构中的应用具有一定的指导意义。     

复合材料层合结构破坏机理及压溃吸能特性分析

针对纤维增强复合材料层合试验样件,对[90]_(16)和[0]_(16)试验样件分别进行拉伸、压缩试验,对[±45]_(4s)试验样件进行剪切试验,分析其破坏模式,通过SEM扫描电镜观察试验样件断口微观形貌,揭示其细观破坏机理。针对纤维增强复合材料层合薄壁结构,对[±45/0/0/90/0]_s圆管、[0/90]_(3s)圆管、[0/90]_(3s)方管和[±45]_(3s)方管进行准静态轴向压溃试验,分析其宏观破坏模式及吸能特性。结果表明:宏观破坏模式是多种细观破坏机理共同作用的结果,包含纤维断裂、基体变形与开裂、层间与层内裂纹扩展等;[±45/0/0/90/0]s圆管为横向剪切破坏模式,比吸能最大;[0/90]_(3s)圆管为层束弯曲失效模式,比吸能次之;[0/90]_(3s)方管为层束弯曲失效模式,比吸能第三大;[±45]_(3s)方管为局部屈曲失效模式,比吸能最小。不同铺层方式复合材料层合薄壁圆管和方管压溃破坏失效模式差异较大,比吸能差距也较大,通过合理设计可以改变复合材料层合薄壁结构破坏模式,改进其吸能特性。     

铺层顺序对复合材料薄壁圆管轴向压溃吸能特性的影响研究

采用仿真和试验相结合的方法探讨复合材料薄壁圆管在准静态轴向压缩载荷下的失效吸能特性和吸能机理。首先,建立复合材料薄壁圆管"层合壳"有限元模型,通过显式动力学方法求解其在准静态轴向载荷下的压溃失效力学行为。仿真与试验结果在圆管轴向压溃变形过程、初始峰值载荷、平均压溃载荷及比吸能等主要吸能参数上具有很好的一致性,验证了"层合壳"复合材料圆管有限元模型和建模方法的有效性。其次,采用解析模型与仿真分析方法分别对[0/90]_3s、[0/90/0₂/90₂]_s、[0₃/90₃]_s三种不同铺层顺序的复合材料圆管的屈曲载荷与吸能特性进行了对比,进一步分析了铺层顺序对圆管失效吸能特性的影响。研究表明,0°与90°铺层交替程度对复合材料圆管的吸能特性影响较大,保证纤维失效方式在结构宏观失效中占主导地位能够提高材料失效吸收能量。     

典型螺栓连接CFRP薄壁C型柱轴压失效行为:试验及数值模拟

为了研究典型螺栓连接碳纤维增强树脂复合材料(CFRP)薄壁C型柱的轴压失效模式及吸能特性,进行了5组不同铺层方式C型柱的准静态轴压试验,即[0/90]_4s、[±45]_4s、[±45/90₂/0₄]_s、[±45/90/0₂/90/0₂]_s、[90/±45/0]_2s,获得其失效形貌及载荷-位移曲线。采用Lavadèze单层壳单元模型、Puck-Yamada失效准则、层间胶粘单元及螺栓模型,建立C型柱层合壳模型进行轴压仿真,并与试验失效形貌、载荷-位移曲线及吸能特性评估指标进行对比分析。结果表明:0°、±45°、90°纤维可以显著影响C型柱轴压失效模式及吸能特性。在轴压载荷下,±45°纤维铺设C型柱发生局部屈曲失效模式,吸能特性差。±45°纤维铺设在外部,0°和90°纤维交替铺设在内部的C型柱,其轴压失效过程平稳,吸能特性好。与C型柱轴压试验结果相比,层合壳模型获得的整体变形和局部失效形貌吻合较好,载荷-位移曲线变化趋势和吸能特性评价指标基本一致。研究结果对CFRP薄壁C型柱吸能设计具有一定的指导意义。      

复合材料波纹板准静态轴压性能试验及数值模拟

以[+45/-45]_(4s)和[0/+45/-45/0]_(2s)碳纤维增强复合材料波纹板为研究对象,通过准静态轴压试验获得其失效形貌及载荷-位移曲线;通过CT扫描分析其破坏机理,基于吸能特性评价指标进一步研究其吸能特性。针对[0/+45/-45/0]_(2s)波纹板,建立考虑层间模型的多层壳模型进行轴压仿真,通过对比失效形貌、载荷-位移曲线及吸能特性评价指标来验证有限元模型。试验结果表明:[+45/-45]_(4s)波纹板出现整体失稳现象,材料利用率较低导致其吸能特性较差,且试验获得的比吸能的离散系数大于15%,试验重复性较差。[0/+45/-45/0]_(2s)波纹板为典型的层束张开失效模式,材料利用率较高导致其吸能特性较好,吸能特性评价指标的离散系数均小于15%,具有良好的轴压稳定性与可重复性。在±45°纤维铺层中增加0°纤维铺层,可改变其轴压失效模式,并显著提升其轴压吸能特性。仿真结果表明:多层壳模型能较好地复现[0/+45/-45/0]_(2s)波纹板轴压过程及层束张开失效模式;同时仿真获得的比吸能比试验均值高2.27%,能较好地复现[0/+45/-45/0]_(2s)波纹板轴压吸能特性,从而验证了多层壳模型。     

铺层方式对CFRP-铝合金单搭接胶接接头低速冲击损伤及剩余拉伸性能的影响

采用热压罐成型方法制备铺层方式为[+45/-45]_4s、[0/+45/-45/90]_2s和[0/90]_4s的碳纤维复合材料层合板,通过胶黏剂与铝合金板进行粘接获得异质材料单搭接胶接接头。利用落锤冲击试验机和万能电子试验机分别对三种接头进行低速冲击与冲击后静态拉伸测试,获得接头接触力-时间曲线和拉伸强度。通过CT扫描技术和数字图像相关(DIC)方法表征接头冲击损伤模式及表面应变演化过程,研究了铺层方式对接头抗冲击性能、冲击损伤模式以及剩余拉伸性能的影响。结果表明,复合材料铺层方式为[+45/-45]_4s时,接头在冲击载荷作用下具有较高的抗冲击性能,但胶层界面脱粘损伤较为严重。与胶层界面脱粘相比,接头剩余强度对层合板分层损伤更为敏感。相较于[+45/-45]_4s,[0/+45/-45/90]_2s和[0/90]_4s铺层方式接头的胶层界面脱粘范围与冲击后失效载荷退化程度较小,同时接头冲击后拉伸载荷主要集中于临近胶层的0°铺层且失效模式较为复杂...     

基于应变能耗散的复合材料层合板面内缺口强度分析CDM模型

基于伴随能量释放的渐进损伤演化思想,建立了复合材料层合板面内失效分析的连续介质损伤力学（CDM）分析模型,该模型包含损伤表征、损伤起始判定和损伤演化法则3个方面。基于CDM模型,通过引入损伤状态变量表征损伤,建立了平面应力状态下的材料损伤本构模型。采用损伤参量 f_E改写Hashin准则,以判定损伤的起始。损伤演化由特征长度内的应变能释放密度控制,建立了损伤状态变量关于等效应变的渐进损伤演化法则。模型中还同时考虑了面内剪切非线性和网格敏感性,并进行了对比分析。对含缺口的[90/0/±45]_3s和[（±θ）₄]_s 2类典型复合材料层合板的面内拉伸失效进行了分析,结果表明,本文中的模型能有效预测复合材料层合板的面内拉伸强度。     

复合材料开孔层板压缩渐进损伤试验

为研究碳纤维增强树脂基复合材料开孔层板在压缩加载过程中的损伤起始、演化方式和损伤特点,采用微距拍摄、逐级加载超声C扫描、X光扫描和扫描电子显微镜观测4种观测手段对国产CCF300/5228A[45/0/-45/90]4s、[452/02/-452/902]2s、[454/04/-454/904]s3种铺层方式的开孔层板进行了压缩试验研究。对压缩载荷作用下开孔层板的损伤起始和损伤演化进行了观察和对比。对试验中观测到的纤维微屈曲、纤维挤出、孔边开裂和分层扩展等现象之间的关系进行了分析和说明。试验结果表明:压缩载荷下45°和90°铺层相邻位置为层板易分层位置,含45°和90°铺层相邻位置的开孔层板渐进损伤过程较为明显:开孔层板在压缩载荷下较早出现损伤,损伤的起始和演化缓解了孔边应力集中,促使压缩应变能在孔边逐步释放,推迟开孔层板压缩破坏的发生,提高层板压缩承载能力。研究结果可为材料结构损伤容限设计提供依据。     

Damage detection of surface cracks in composite laminates using modal analysis and strain energy method

This paper presents an approach to detect surface cracks in various composite laminates. Carbon/epoxy composite AS4/PEEK was used to fabricate laminated plates, [0]₁₆, [90]₁₆, [(0/90)₄]_S and [±45/0/90]_2S. Surface crack damage was created on one side of the plate using a laser cutting machine. Modal analysis was performed to obtain the mode shapes from both experimental and finite element analysis results. The mode shapes were then used to calculate strain energy using the differential quadrature method (DQM). Consequently, the strain energies of laminated plates before and after damaged were used to define a damage index which successfully identified the surface crack location.     

Matrix cracking behavior of K3B/IM7 composite laminates subject to static and fatigue loading

The matrix cracking behavior of a new high-performance thermoplastic composite material, K3B/IM7, was systematically investigated. Laminates in various grouped thickness and ply stacking sequences, [0₂/90₂/0₂], [0₂/90₄/0₂], and a quasi-isotropic laminate [+45/0/−45/90]_s were tested under static and tension–tension fatigue loading. Depending on the stacking sequence of the laminates and the type of loading, various matrix cracking behavior were found. Under static loading, the matrix cracks were mainly close to the specimen edges. A few cracks were found to penetrate the specimen width, even when the load was large enough to break the specimen. However, under fatigue cyclic load, the edge initiated cracks propagated fully across the specimen width. Combined with the fatigue Paris Rule and considering the ply thickness and stacking sequence, the energy release rate method was applied to predict the relations between the loading strain amplitude and fatigue cycles for matrix cracking failure.     

变刚度碳纤维/环氧树脂复合材料薄壁圆管轴向压溃响应与破坏机制

通过控制缠绕线型改变轴管纤维角度,制备了一种轴向刚度渐变、压溃稳定的碳纤维增强树脂基复合材料(CFRP)变刚度薄壁圆管。对变刚度、[±45°]_n以及[90°]_n三类CFRP缠绕轴管进行轴向准静态压缩测试,结合数字图像相关技术(DIC)及有限元结果,对比三类结构压溃初始应变模式、损伤演化与应力状态结果,研究了变刚度结构的压溃响应与破坏机制。结果表明:不同纤维角度CFRP轴管因轴向刚度不同,压溃的初始破坏与损伤演化过程相异,三类结构产生不同的压溃响应与破坏模式。变刚度区连续变化的大角度纤维能有效地引发分层和“开花式”混合破坏,缓慢释放应变能,使变刚度CFRP轴管吸能效果明显优于其他两类结构。其峰值载荷为66.97 kN,压溃效率为50.8%,比吸能为10.1 kJ/kg,相对于[±45°]_n结构比吸能提升156.35%,压溃效率提升518.76%,相对于[90°]_n结构比吸能提升16.9%,压溃效率降低27.3%。      

Advanced composite sandwich structure design for energy absorption applications: Blast protection and crashworthiness

This paper describes an experimental investigation on the response of composite sandwich structures with tubular inserts to quasi-static compression. The performance parameters, namely the peak load, absorbed crash energy, specific energy absorption; average crushing load and crush force efficiency were evaluated. The composite sandwich specimens were fabricated from glass fiber, polystyrene foam and epoxy resin. The primary mode of failure observed was progressive crushing with the composites exhibiting high energy absorption capabilities and high crushes force efficiency. The mechanism of progressive crushing of the sandwich structures and its relation to the energy absorption capabilities was deliberated. Furthermore, a statistical analysis was performed to investigate the effects of the design variables and also to determine if there were interactions between these variables. Such information is vital in the design of polymer composite sandwich structures as energy absorbers.     

An investigation of graphite PEEK composite under compression with a centrally located circular discontinuity

The failure characteristic of graphite polyetheretherketone (Gr/PEEK) under compression with a centrally located circular discontinuity was investigated through experimentation and a nonlinear ply-by-ply finite element technique. The stacking sequence of the laminates investigated were: [0 °₁₆], [90 °₁₆], [±45 °]_4S [0 °/90 °]_4S, and [0 °/ ± 45 0°/90 °]_2S. In the experimentation, [90 °]₁₆, [0 °/90 °]_4S, and [0 °/ ±45 °/90 °]_2S laminates, as well as three of the [0 °]₁₆, failed due to a crack that was normal to the loading direction and initiated from the edge of the hole progressing to the outer edges of the specimen. The [±45 °]_4S specimens failed to support the load due to an internal crack that originated from the hole's edge and then traveled at an angle of about 42% to the direction of loading. The finite element method used to analytically model the failure of Gr/PEEK accurately modeled the response of the specimens tested experimentally.     

Role of matrix resin in delamination onset and growth in composite laminates

The effect of the matrix resin on the onset and growth of delamination in composite laminates has been investigated in this work. Two kinds of graphite/epoxy composite materials (T300/648-BF₃/MEA and T300/634-DDS) with quite different matrix properties have been used. The study was done on two different layups, [(±30)₃/90₂]_s and [(±45)₂/O₂/90₂]_s. Out-of-plane moiré interferometry and diiodomethane-enhanced X-radiography were used to detect delamination. A strength criterion for the onset of delaminatoin is proposed and an assessment made of the effect of matrix properties on delamination onset. A modified energy release rate model is presented for characterization of delamination growth emphasis being placed on assessing the behavior of delamination resistance curves and delamination growth rate. The results indicate that enhancement of matrix strength and ductility increases the critical loads for delamination onset and delamination resistance in the composite laminates under static loading, and significantly reduces the delamination growth rate under cyclic loading.     

Measurement of the static compressive strength of carbon-fibre/epoxy laminates

This paper describes an experimental study of the compressive failure of T800/924C carbon-fibre/efoxy composite laminates. Undirectional laminates loaded parallel to the fibres have compressive strengths that are 70% of the tensile strength and fail by fibre-microbuckling. During microbuckling the fibre debonds from the matrix, and the fibres break in bending. Multidirectional [(±45/0₂)₃]_sm laminates were also tested in compression, and the critical failure mechanism observed was microbuckling of the 0° plies. The failure strain was almost the same as for the undirectional laminate, The failure strain was almost the same as for the unidirectional laminate, which indicated that the ±45° plies have no significant influence on the failure strength of the 0° plies.