Potential failure mechanisms of bonded composite repairs for metal and concrete

The objective of the present paper is to clarify the potential failure mechanisms of composite repairs and thereby assist in the development of a certification methodology for both civil and aircraft structures. In this context it is shown that interlaminar failure, in the case of composite repairs to aircraft structures, and shear failure in the concrete, in the case of repairs to degraded concrete structures, can often drive the design process. This phenomena is highlighted by considering a range of recent failures associated with the repairs to civil structures, i.e. bridges, concrete structures and chimney's, etc., and also to aeronautical structural components.     

Analysis of thermally induced multistable composites

This paper models the non-linear flexural response of laminates that have piecewise variation of lay-up in the planform, using finite element analysis. Attention is focused on the effects that thermal stresses have on the potential multiple shapes of a composite structure. Unsymmetric laminates may possess more than a single equilibrium configuration, and during the cool-down the solution thus bifurcates at a critical temperature. In static analyses, numerical solutions are often coaxed to converge into one or the other branch of the solution. A methodology to overcome this problem is presented. Such modelling is necessary to allow application of multistable composite within morphing aircraft structures as multistable composites could provide a viable solution for the realisation of shape-adaptable structures.     

Postbuckling behavior of composite-stiffened-curved panels loaded in compression

In this paper, a methodology is developed for the design of a weight-efficient, composite, curved-stiffened panel, loaded in compression well beyond the initial buckling load. A stiffened fuselage panel is designed to satisfy typical design load criteria for the moderately loaded sections of a typical fighter aircraft. Several stiffened panels are fabricated. Some panels are tested to determine experimentally the static strength and the remaining panels are subjected first to severe fatigue loading and then tested statically to determine the effect of fatigue loading on the postbuckling strengh. The experimentally observed behavior is compared with analytical predictions. The weight efficiencies of buckled and unbuckled construction are also compared.     

加热压电纤维复合材料圆板的横向自由振动

基于经典薄板理论和极正交各向异性材料的本构理论,建立了加热压电纤维复合材料圆板的线性振动控制微分方程。采用打靶法分别获得了加热压电纤维复合材料圆板在周边固支和简支情况下,无量纲固有频率随温度和电场强度变化的关系曲线,并分析了压电纤维体积分数、刚度参数、电场强度和温度变化对压电纤维复合材料圆板无量纲固有频率的影响。结果表明,一定体积分数或者电场强度下,压电纤维复合材料圆板的无量纲固有频率都随温度的升高而单调下降;同一温度下,刚度参数越小,无量纲固有频率越低;电场强度越大,无量纲固有频率越高。     

纤维增强合成闸片摩擦磨损特性的试验研究

采用MM-1000型摩擦磨损试验机进行了纤维增强合成闸片和HZ408合成闸片与H300制动韫材料配副的制动摩擦试验，记录了制动过程中摩擦系数、磨损量与制动盘温度的变化情况，采用三维激光共焦扫描显微镜（CLSM）分析了磨损表面形貌．结果表明：制动初速度对纤维增强合成闸片的平均摩擦系数影响小于HZ408合成闸片，在高速制动工况下，纤维增强合成闸片的平均摩擦系数大于HZ408，耐磨性略低于HZ408合成闸片；在低速制动工况下，纤维增强合成闸片和HZ408合成闸片所引起的制动盘温升大致相同；在高速制动工况下前者引起的制动盘温升略高．     

Modelling of fibre pull-out in cracked fibre reinforced composites with linear elastic fracture mechanics

A method of finite element modelling the fracture mechanics of a fibre reinforced cement composite is presented. It embodies the use of beam elements with negative extensional stiffness. The method compares favourably with experimental work. Whilst fibre reinforced cement composites are used in this work, the techniques used are applicable to any type of fibre composite material.     

复合材料内多处横向冲击损伤的光纤图像检测

基于埋设在复合材料层板中的多方位多模光纤网络的特点,提出了检测层板内部发生多处横向冲击损伤的重构算法．根据光纤损伤图像检测系统获得的图像信号,可实时、定量、直观重构并显示出层板内部各处损伤的位置和各处的损伤程度．在复合材料多点冲击损伤检测试验中,屏幕显示的损伤图示与对半透明试件同时做反向照明检测的结果相一致,证实了重构结果的正确性     

The strain energy density ratio criterion for predicting cracking direction in composite materials

The strain energy density ratio criterion for predicting cracking direction incomposite materials is proposed.The Tsai-Hill criterion and Norris criterion ofcomposite materials are extended to predict the cracking direction in composites.Thethree criteria are used to analyse the crack propagation problem of the unidirectionalfibre composite sheet with various fibre directions.The predicted results are comparedwith those of the existing normal stress ratio criterion and strain energy densitycriterion.     

复合材料胶接修补问题的试验研究和分析

用带中心裂纹的Ｌｙ１２ＣＺ铝合金板模拟飞机的损伤结构,对于不同的修补方式（单边和双边修补）,不同的补片材料（铝合金和复合材料）和几何尺寸以及脱胶等因素,进行了静强度和疲劳裂纹扩展试验． 实验表明． 胶结修补能明显地提高损伤结构的强度和疲劳寿命,同时实验还为修补实践的选材和几何参数的设计等提供了大量数据． 文中最后给出了修补结构疲劳裂纹的有限元计算估计,并与试验结果进行了比较和分析．     

复合材料层板构件气弹振动控制实验研究

飞机局部复合材料构件存在着因涡流作用诱发的弹性振动问题。本文首先研究了表面粘贴型压电元件对复合材料构件的传感和驱动原理;针对结构待控模态的要求,采用了D-准则优化确定同位压电传感/驱动器在构件中的布置方案;应用自适应振动前馈控制原理和方法,构造了闭环控制系统;分别利用正弦和方波信号激发气动声场,对玻纤/环氧圆筒构件进行激振和振动控制实验;结果表明：构件主要待控模态的振动得到了有效抑制,但也出现了高阶模态被激发的问题,导致结构辐射噪声上升。     

基于连续丝束剪切技术的变角度复合材料层合板的热屈曲分析

连续丝束剪切(Continuous Tow Shearing, CTS)铺放技术是一种新的变角度层合板制作技术，这种新技术能显著减少丝束铺放过程中产生的丝束重叠和间隙等缺陷，然而，采用CTS技术铺设时，层合板的厚度将随着纤维角度的变化而变化．本文基于一阶剪切变形理论并应用Chebyshev-Ritz法对这种变厚度的变角度复合材料层合板的热屈曲问题进行了研究．假设纤维方向角沿板的长度方向按照线性变化，获得了均匀温度变化时变厚度层合板的临界热屈曲荷载．通过与现有文献的比较验证了本文方法的正确性，并进一步讨论了纤维铺设技术、纤维方向角的变化以及边界条件的不同对变角度复合材料层合板的临界屈曲温度的影响．研究结果表明，在体积相同的情况下，采用CTS铺设较传统的自动丝束铺放(AFP)可以进一步提升变角度层合板的临界屈曲温度．本文的研究结果可为变角度复合材料的设计提供一定的参考．     

大飞机研制中的若干复合材料力学问题

简要介绍了先进复合材料在当代大型飞机结构中的应用状况，以及相关的力学问题，着重论 述了复合材料及结构的工艺力学、跨尺度材料/结构一体化设计问题和力学性能表征、高效复 合材料结构设计和力学分析、复合材料损伤容限与耐久性设计、大型飞机的安全监测和管理 系统等. 指出，从目前国际上以及我国复合材料在大型飞机结构上的应用趋势来看，我们需 要进一步发挥广大力学工作者与相关领域科研人员和工程师的协同作用，提高我国复合材料 基础研究和应用水平，使复合材料在提升我国研制的大飞机的先进性和竞争力方面发挥重要 的作用.     

民机复合材料结构冲击后压缩设计值的确定方法

冲击后压缩设计许用值是复合材料飞机结构设计的一个非常重要的参数。本文通过分析常用的目视检测方法和飞机结构冲击能量统计结果,从凹坑深度和冲击能量截止值两方面定义了目视勉强可见损伤;根据民机设计兼顾安全性和经济性的特点,作者提出压缩设计许用值中的目视勉强可见损伤应综合考虑,慎重确定。文章还研究了复合材料层压板的抗冲击性能,从工程应用角度给出了结构冲击后压缩设计许用值的确定要点,即用小试样的冲击后压缩试验结果推导的基准系数和环境系数,对元件乃至典型结构件的冲击后压缩试验结果进行修正。     

Direct simulation for concentrated fibre suspensions in transient and steady state shear flows

A numerical method to simulate fibre suspensions in transient and steady state shear flows for concentrated solutions is reported, which takes into account short-range hydrodynamic interaction via lubrication forces, contact forces and hydrodynamic forces. Fibres are assumed to have varying lengths as observed in industrial composites and this can be described with a fibre distribution length function. Stresses in the composite have been calculated from a constitutive equation or from an approximate expression for the effective stress of fibre suspensions. This simulation will assist in modelling of short fibre filled industrial composites. Our first results shown here qualitatively agree with experiments.     

基于耦合算法的三维复杂结构冲击动力学特性

光滑粒子流体动力学-有限元耦合算法（SPH-FEM）较好地结合了SPH和FEM的优势,近年来逐渐被引入冲击动力学相关问题研究中。然而早期的研究对象多为单一材料的简单结构,所取得的研究成果距离实际工程应用仍有一定差距。为此,在总结前人工作的基础上,对SPH-FEM耦合算法进行适当改进,通过引入复合材料损伤模型,对复合材料蒙皮结构飞行器舱段结构进行建模计算,分析其在爆炸冲击激励下的冲击动力学特性。将数值计算结果与试验结果进行对比分析,验证该算法和模型的有效性和准确性,初步实现SPH-FEM的工程实际应用。最后总结了复合材料蒙皮结构飞行器在爆炸冲击激励下的一系列结构动态响应规律,以期为航天飞行器结构设计与防护提供参考。     

复合材料修补结构腐蚀扩展特性实验研究

为了研究腐蚀环境对复合材料修补结构疲劳特性的影响,开展以某型飞机加速环境谱为基础的预腐蚀试验,并采用递进式的试验方法分别完成对未修补未腐蚀、修补但未腐蚀、又修补又腐蚀的试样疲劳裂纹扩展试验。利用试验数据计算了复合材料修补构型、腐蚀环境对裂纹尖端应力强度因子影响的修正系数,并确定了通过试验验证的修补结构疲劳裂纹扩展修正模型。该模型预测腐蚀环境下修补结构的疲劳寿命与试验值一致。试验数据和预测模型可为海军飞机复合材料修补结构的损伤容限设计提供参考。     

平尾翼型后加载对飞机配平的影响研究

利用MGAERO 软件对搭配不同尾翼模型的某典型布局客机翼身组合体流场进行了计算,研究了平尾翼型后加载对全机配平的影响. 分析表明,采用后加载设计的平尾翼型在配平时升力和阻力损失较小,配合其他手段可以提高全机升阻比,进而改善全机配平后的气动性能. 这一结论从流场计算的角度揭示了客机平尾翼型采用后加载设计这一发展趋势的重要原因.     

Composite patch reinforcement of cracked aircraft upper longeron: analysis and specimen simulation

The use of composite patches on cracked portions of metallic aircraft structures is an accepted means of improving fatigue life and attaining high structural efficiency. As more and more advanced composite materials are beng developed, the wider use of the repair technology is anticipated even for the reinforcement of primary aircraft structure. The objective of this work is to illustrate how the composite patch repair technology can be successfully applied to restore the structural integrity of cracked components.The Phosphoric Acid Anodize (PAA) surface treatment on aluminum when applied in conjunction with the AVI13/HV998 adhesive were essential for achieving the appropriate patch bonding strength. Such a process was done without immersing the component into the PAA tank; dismantling the component from the aircraft was not necessary. Boron/epoxy and carbon/epoxy patches were applied at room temperature to the 7075-T6511 cracked specimens and tested under fatigue simulating the load spectrum for the upper longeron attached to the access door of the electronic equipment bay. Considerable improvement in the fatigue life was observed after the repair. Equivalent flight test hours were increased from approximately two thousand hours at which the component fractured completely when not repired to twelve thousand hours when the repair was made with only a small amount of crack growth. A six times increase fatigue life is obtained. The laboratory developed technique has been applied to several in-service aircraft which have now been flown for more than 700 h without detection of crack growth.     

Asymptotic study of geometrically non-linear elastic strip with regular system of fibres

Two-dimensional composite material consisting of linear elastic fibres embedded in a non-linear elastic strip has been studied. That inhomogeneous medium models a mechanical behaviour of a rubber-like textile reinforced with threads distributed in parallel. The analytical solution relating the displacement field to fibre width, fibre distance, fibre length and fibre and matrix elastic moduli has been derived. To this end we used a special perturbation and homogenization technique. Anlustrative example is also provided.     

含铝纤维复合炸药的能量输出和力学强度

通过空中爆炸实验,研究了铝纤维对爆炸能量输出的影响,结果表明:wAl=0.20的TNT/Al,冲击 波压力峰值为TNT 的1.19倍,TNT 当量为TNT 的1.29倍;wAl=0.20的RDX/Al,冲击波压力峰值为 RDX的1.20倍,爆热为TNT的1.64倍,是RDX的1.31倍。通过抗压实验,研究了铝纤维对炸药力学强度 的影响,结果表明,铝纤维能增强TNT炸药的力学强度,破坏应力为6.8MPa,应变为0.043。铝纤维对炸药 能量和力学强度的双重增强特性,可以为现代高性能炸药设计提供参考。