复合材料层合结构的铺层优化

本文采用最速下降法，对复合材料层合圆柱壳体受外压作用的铺层进行了优化。优化结果表明：在受外压作用下，层合圆柱壳体的铺层有最优化方案，且完全能在实际中实现。对于其他形状的结构和承受其他载荷的情况，只需改变指标函数即可用此方法获得优化铺层。     

脱层损伤对层合梁动态特性影响规律的研究

脱层损伤是层合复合材料常见的一种损伤.本文以单向机织物增强环氧树脂复合材料层合板为研究对象,研究了脱层损伤大小和脱层损伤位置对层合悬臂梁自振特性的影响规律.通过实验和数值模拟,得到了脱层损伤对层合粱自振特性影响的一些规律性认识,通过实验和数值分析结果的比较,也证实了本文采用的数值分析方法的正确性.     

复合材料层合板孔边应力场的有限元计算

纤维增强复合材料具有较高的比强度、比刚度和比模量,在航空航天领域得到越来越广泛的应用.层合板是当前复合材料在工程结构中应用的主要形式.对于含孔的层合板结构,由于材料的各向异性以及孔的影响,其应力分布比较复杂,采用数值解是较好的选择.本文基于层合板的可设计性特点,综合考虑铺层角度、铺层顺序等对层合结构的影响,设计出了一种二十四层对称层合板.以有限元方法为基础,借助ANSYS分析工具,对该层合板含孔结构的孔边应力重点分析,得出了不同铺层角度铺层中应力分布的云图和孔边应力分布曲线.本文结论对复合材料层合板优化设计和带孔层合结构的应力计算具有较好的参考价值.     

碳纤维复合材料曲梁冲击后四点弯曲强度及损伤失效模式研究

通过四点弯曲试验和落锤冲击试验,研究了复合材料层合曲梁冲击前后四点弯曲强度及其破坏模式。不仅通过超声C扫描分析了不同内径复合材料层合曲梁试件冲击后的损伤特征,而且分析了冲击损伤对层合曲梁强度及层间最大应力的影响;同时,通过数字散斑相关方法得到复合材料层合曲梁在四点弯曲载荷作用下的变形场以及失效模式。研究结果将为复合材料层合曲梁在飞行器结构中的应用提供有价值的实验依据。     

缝合复合材料层合板的层间细观应力分析

介绍了缝合复合材料代表体单元（RVE）的三维细观有限元分析模型,模型考虑了缝线的实际形状以及缝合对层合板面内纤维的影响。在分析中引入了保证胞单元边界面的应力和位移周期性连续的边界条件。着重分析了三种平均应力状态下不同角度铺层间层间应力的分布情况。研究结果表明：缝合复合材料单胞内部层间应力分布也是不均匀的;促使材料发生分层破坏的主要层间应力和外载荷有关。     

薄铺层层合复合材料研究进展

简要介绍了碳纤维薄层预浸料及其制备的层合复合材料,主要阐述碳纤维薄层预浸料的制备方法和薄铺层复合材料的力学性能特点。对国内外关于薄铺层复合材料与常规铺层复合材料的静态、韧性和疲劳等力学性能的研究进展进行了分析和总结,归纳了铺层厚度的减薄对层合复合材料力学性能的影响规律。最后对薄铺层复合材料的研究趋势和应用前景进行了展望。     

复合材料与表面处理技术(Ⅰ)

表面处理技术除了对各种零部件表面进行加工,满足不同的使用要求外,还是制备材料特别是复合材料的一种主要方法.介绍了复合材料的基本概念、分类及其特点.总结了采用表面处理技术制备复合材料的方法特别是层合复合材料的制备.     

基于ANSYS的复合材料层合板的拉伸失效模拟

基于ANSYS的APDL语言开发复合材料层合板的拉伸失效模块,实现有限元分析的参数化建模和累积失效分析.采用Solid64宴体单元建立复合材料层合板的三维模型,依据改进的三维Haisin失效准则对结构单元进行失效判断,并对失效单元进行刚度退化.当失效单元贯穿所有单层时,复合材料层合板结构彻底失效.通过对铺层方式为[0/45/-45/90]s复合材料层合板结构拉伸模拟,探讨其拉伸破坏形式,得到层合结构的最终拉伸强度,并把其拉伸强度与文献实验结果进行对比,得到的结果与实验一致.该方法简便直观,便于工程运用.     

拉伸和弯曲耦合层合梁应力分析

本文建立了拉伸和弯曲耦合层合梁的位移微分方程,导出了拉弯耦合层合梁正应力和层间剪应力的计算公式。分析了规则非对称正交层合梁的应力具有非对称特性。当规则非对称正交层合梁的铺层组数大于8时,其应力趋于对称分布。     

某电磁弹射无人机复合材料机翼结构优化设计与分析

无人机已经成为航空领域重要成员之一。在无人机初步设计阶段,为减轻其结构重量,采用复合材料设计。复合材料在比强度和比刚度以及抗振和加工制造等方面优于其他传统材料,在无人机结构中得到了广泛的应用。由于复合材料层合板在生产加工过程中具有可设计性,在复合材料中已经成为使用最多的一种结构形式。以某型号电磁弹射无人机机翼为研究对象,建立了复合材料机翼结构的有限元模型,将机翼的结构重量作为优化目标,以机翼翼尖挠度和复合材料失效因子为约束条件,应用工程优化软件对复合材料翼面结构进行自由尺寸优化,整个优化过程需同时满足机翼强度及刚度要求。最终自由尺寸优化结果表明,复合材料的铺层比例和厚度分布在优化后得到了重新设计,比较之前的结构方案,优化后的铺层设计能够有效降低机翼结构质量,实现减重的优化目标。     

碳纤维钛合金超混杂复合层板残余应力研究

基于复合材料经典层合理论,分别采用解析法、有限元法计算了2／1结构的碳纤维钛合金超混杂复合层板（T∥PEEK／Cf）0°方向残余应力,并利用应力释放法测定层板残余应力,计算结果与实验结果基本一致。结合解析法和有限元法讨论了加载预应力对层板残余应力分布的影响,当预应力为150MPa时,残余应力几乎为0MPa,有利于层板各项综合性能,为后期设计研制出具有最佳性能的层板提供了有价值的理论参考。     

Edge Stresses in Alumina/Zirconia Laminates

Using the technique of fluorescence piezospectroscopy, we determine the distribution of thermal residual stresses across the edges of three laminated alumina/zirconia composites. We develop a methodology for separating the measured stress state into microstresses that result from grain-to-grain thermal mismatch and macrostresses that result from lamination-induced thermal mismatch between individual plies. Comparison between the measured edge-stress distributions and those calculated based on a simple force-superposition model shows good agreement, indicating that the laminate system is well approximated as linear elastic. Given the experimental confirmation of significant edge stresses in multi-ply laminates, the possibility of failure initiating at composite edges must be considered in the design of surface-compressed laminate structures with the aim of mediating the detrimental effect of surface flaws.     

Stress analysis of the thermal barrier coating system near a cooling hole considering the free-edge effect

Due to the thermal mismatch between layers and the free-edge effect, interfacial peeling and shear stresses are generated locally around the edges of cooling holes in a thermal barrier coating (TBC)–film cooling system. These interfacial peeling and shear stresses may lead to modes I and II edge delamination, resulting in TBC spallation around the cooling hole. In this study, analytical and numerical models were built to study the stress and interfacial cracking behaviors of TBCs near the cooling hole. Analytical solutions for interfacial peeling moment and shear force at each layer were obtained to analyze the free-edge effect on the stress distributions in TBCs, and they were verified by the finite element calculations. The results showed that interfacial peeling moment and shear force were functions of the hole radius and thicknesses of top coat and oxide layer. The increase of interfacial peeling moment and shear force raised the likelihood of edge cracking around the hole. Derived by the local stresses, the interfacial cracks in TBCs initiated and propagated from the hole edge upon cooling.     

纤维分布不均匀的层压板表征与弯曲性能研究

基于MATLAB图像处理技术,本文开发了用于测定复合材料纤维分布状态的计算机图像处理程序。以T300/BMP316复合材料为对象,采用三点弯曲法研究了纤维分布均匀性对复合材料弯曲性能的影响,用有限元方法分析了纤维分布不均匀的复合材料弯曲变形时的应力分布,提出了运用抗弯系数R评价其性能。结果表明,基于MATLAB图象处理技术可快速准确地测定纤维增强复合材料的纤维密实指数,确定纤维的分布状态。纤维分布不均的T300/BMP316复合材料弯曲性能受纤维分布方式和载荷方向的影响极大,抗弯系数R反映了纤维分布与性能的关系。     

含孔损伤平面编织层合板固有频率研究

本文对一端固支舍圆形孔损伤平面编织层合板的固有动力特性进行了试验研究.基于MSC.Patran建立了含圆形孔和椭圆孔损伤平面编织层合板的有限元模型,研究了圆孔损伤和椭圆孔损伤的损伤尺寸对一端固支纤维双向层合板固有频率的影响规律.试验结果表明,有限元方法得到的舍圆孔损伤层合板固有频率与试验值吻合较好;圆形穿孔和长轴平行于试件长度方向椭圆形穿孔损伤对平面编织层合板各阶固有频率的影响规律相同;在椭圆穿孔损伤尺寸小于一定值或偏心率较小时,可用圆孔来估算椭圆形穿孔损伤和结构设计开孔对结构固有频率的影响.为开口复合材料结构件的设计以及含孔损伤复合材料结构件的维修设计提供依据.     

Damage tolerance in graphite-epoxy composite: Comprehensive monitoring method

A failure model is proposed to calculate the minimum expected lifetime of a graphite-epoxy structure under cyclic loading conditions. The theoretical approach is based on the statistical theory of strength and the mechanical redistribution of stresses between piles of a damaged laminate. The use of the acoustic emission technique has permitted the development of internal damage to be monitored during cyclic loading of unidirectional laminates. The experimental results indicate that the composite can withstand greater damage at low level cyclic loading than observed during monotonic loading to failure. The theoretical modeling under development aims at predicting this behavior.     

Improving energy dissipation and damage resistance of CFRP laminates using alumina nanoparticles

ABSTRACT

In this paper, the effect of a toughened epoxy matrix on the damage evolution, energy dissipation, and permanent indentation of composite laminates under out-of-plane (transverse) loading is presented experimentally. The epoxy matrix was toughened by 3% alumina nanoparticles with sizes less than 200?nm. A quasi-static indentation test was exploited to characterise the damage modes and evaluate the dissipation of energy of the composite laminate. The dissipated energy was evaluated as the enclosed area between the loading and unloading curves, while the damage resistance was expressed as the number of delaminations and their size. The results showed that epoxy toughened by alumina nanoparticles, showed an improvement in the damage threshold load by 27.3% and higher ultimate load under indentation. Regarding the damage resistance, the toughened laminates showed lower number of delaminated interfaces and lower projected delamination area than untoughened laminates. This is due to the localised damage under the indenter, the matrix cracks at low indentation energy and fibre breakages occur at high indentation energy.     

Time-dependent response of aramid-epoxy-aluminum sheet,ARALL, laminates

Selected results of an ongoing investigation aimed at characterizing the timedependent response of an aramid-epoxy-aluminum sheet laminate and its constitutents at 121°C are outlined in this paper. This laminate is a recently developed hybrid composite developed by the Aluminum Company of America, marketed under the ARALL-4 tradename. The paper addresses the time-dependent response of the above hybrid composite under creep loading. It is illustrated that ARALL-4 laminates may exhibit substantial creep effects at stress levels below the proportional limit. The creep response is a nonlinear function of time and the applied stress level and is primarily due to the creep characteristics of the aluminum layers. An analytical model based on the assumptions of the classical lamination theory developed to model the time-dependent response of these laminates under creep and thermal loading is shown to yield good correlation with the experimental data. It is also illustrated that the residual state of stress can influence the extent of creep. This offers the possibility of minimizing the creep effects by altering the state of residual stress with mechanical prestraining.     

Fatigue strength estimation of adhesively bonded tongue and groove joint of thick woven composite sandwich structures using genetic algorithm approach

In the present work, the fatigue behavior of tongue and groove joints bonded by a toughened epoxy adhesive was investigated. Axial cyclic tests were performed by different design configuration conditions and the effects of design parameters were evaluated. The bonding strength of adhesives under fatigue loading is influenced by many factors such as, the length of bondline, adhesive thickness, traverse pre-stress on near the free edges of bond line and material of the joining parts. Since all these factors affect the fatigue strength of the adhesively joined parts, the effects of these parameters need to be investigated. The present paper describes the use of the stochastic search process that is the basis of a Genetic Algorithm, in developing fatigue strength estimation of adhesively bonded thick woven E-glass/vinyl ester laminates. Non-linear estimation models were developed using genetic algorithm. Developed models are validated with experimental data. Genetic Algorithm Fatigue Strength Estimation Model for Tongue and Groove Joints was developed to estimate the fatigue strength of the adhesively bonded joint. The strongest adhesively bonded joints can be achieved by selecting optimum design parameters obtained from the models. The logarithmic number of cycles was increased 2.46 times by selecting aluminum EN AW 5083 insert instead of composite insert materials. The joint fatigue strength was significantly improved by selecting appropriate design parameter values.     

The effect of cyclic loading on residual stresses and strains in a bonded joint

The mechanical performance of a structural bonded joint is mainly dependent on the interlaminar stresses and strains, the high concentration of which is close to the free edges of the adhesive. Under cyclic loading these stresses and strains are expected to be intensified and to accumulate. The present study deals with the distribution of the residual stresses and strains along the interlaminar adhesive layer under cyclic loading and how it is affected by geometrical edge conditions. A numerical non-linear finite element method was applied, the adhesive layer being regarded as an elasto-plastic bi-linear material with kinematic hardening (Bauschinger effect) which accounts for cyclic plasticity. Findings indicate that lateral normal residual strains in the edge of the adhesive layer are the major component which increases significantly with cycling and are probably responsible for failure initiation and propagation. It was also found that a significant reduction of stress concentration at the adhesive edge may be achieved by a modification of the free-edge geometry of both the adhesive and the adherend phases.