预应变法调整芳纶－铝层板的残余应力

采用预应变法能有效地调整芳纶-铝层板的层间残余应力[1]。本文分析了3/2铺层的芳纶-铝层板的残余应力与所施加的预应变的关系;并用腐蚀法测定了几种不同的预应变层板中铝层的残余应力;研究了施加预应变对层板的拉伸性能和疲劳性能的影响。     

预应变法调整芳纶－铝层板的残余应力

采用预应变法能有效地调整芳纶-铝层板的层间残余应力[1]。本文分析了3/2铺层的芳纶-铝层板的残余应力与所施加的预应变的关系;并用腐蚀法测定了几种不同的预应变层板中铝层的残余应力;研究了施加预应变对层板的拉伸性能和疲劳性能的影响。      

双频激振下带V形缺口轴的疲劳寿命研究

针对金属轴类零件在实际复杂工况下易产生应力集中而发生疲劳破坏的问题，利用双频激振系统，研究带V形缺口轴的疲劳寿命随缺口几何参数的变化规律。首先，提出了促进轴疲劳裂纹萌生的激振频率控制曲线，同时采用响应曲面法中的Box-Behnken设计法对V形缺口的夹角、圆角半径和深度进行三因素三水平的实验设计；其次，建立了疲劳寿命多元回归预测模型，并采用方差分析法对模型进行可靠性评价；最后，利用响应曲面和等高线图分析了缺口的夹角、圆角半径和深度对轴疲劳寿命的影响规律，并进行了预测模型的应用。研究结果表明：疲劳寿命预测值与实测值之间的误差在4.2%以内，预测精度较高，预测模型可靠；缺口几何参数对疲劳寿命从大到小的影响次序是缺口深度、缺口圆角半径、缺口夹角，以圆角半径和深度的交互作用对轴疲劳寿命的影响最为显著。研究结果可为金属轴类零件的抗疲劳设计提供重要参考。     

变幅载荷下纤维金属层板的疲劳与寿命预测

文章建立了纤维金属层板等幅疲劳载荷下的疲劳裂纹扩展速率与寿命预测模型。在此基础上对玻璃纤维-铝合金层板（GLARE）的疲劳裂纹扩展与分层扩展行为进行了试验研究,探讨了层板过载疲劳行为的机理,提出了纤维金属层板变幅载荷下疲劳寿命预测的等效裂纹闭合模型,并在GLARE层板上得到了验证。     

35CrMoA微动疲劳特性及其微结构研究

通过平面对平面的接触方式,研究35CrMoA微动疲劳特性及其微结构,通过透射电镜(TEM)观察并分析了微动疲劳过程中不同接触应力及不同循环周次时接触区位错的组态。结果表明,随着接触应力的增大,其寿命不断降低,但在不同接触应力区间内,疲劳寿命降低的趋势不同;随着微动疲劳周次增加,其位错密度逐渐增大并互缠结在一起,进一步演化为位错胞;在不同接触应力下,微动疲劳后期都形成了位错胞结构;微动疲劳表层发现有层错亚结构,并且微动接触区的表层容易形成驻留滑移带。     

微动疲劳裂纹萌生位置及形成方式研究

着重研究了微动桥足不同几何形状——方足(r=0mm)及带不同半径r(0.3mm、0.6mm、0.9mm)对微动区接触应力的影响,用不同的r值模拟微动桥足在微动疲劳中的磨损状况。采用ANSYS有限元分析软件详细计算了接触表面的应力分布和磨损区、粘着区、滑动区及张开区的大小,进而讨论裂纹的萌生位置,并建立了不同的r大小即磨损状况与裂纹萌生位置的关系。同时针对方足微动桥/平面试件的接触几何,计算了不同名义接触压力分布形式对接触面上应力分布的影响。此外,还对方足微动桥/平面试件接触几何进行了三维有限元分析,证明了萌生裂纹通常是以多源方式同时出现。计算结果与实验结果吻合很好。     

复合材料层板圆形分层的屈曲

本文设分层发生在距层板表面不远处,由此建立了子层屈曲分析的力学模型,利用Ragleigh-Ritz能量法及通过选择能够表征层板拉—剪和弯—扭耦合效应效应的位移函数,导出了子层屈曲的特征方程,给出了几种铺层角度下,圆形子层临界应变随分层半径R,基层泊松比的变化规律和单向子层临界应变随铺层角变化规律.     

周边固支缝合复合材料层板的小波配置精细积分法

建立了缝合复合材料面内纤维弯曲几何描述模型,将拟Shannon小波配置法和缝合单层板的刚度矩阵应用到缝合层合板的Hamilton正则方程中,构造了缝合板平面方向离散、而厚度方向解析的Hamilton正则方程,然后用精细积分法求解。用拟Shannon尺度函数表示的近似解很适于求解固支边界问题。数值算例结果表明,小波配置精细积分法在缝合复合材料层板位移、应力分析方面,较低网格密度下即可获得较精确的结果。从而为缝合层合板静力学问题分析提供了一种方法。     

单轴拉伸状态下橡胶隔振器的疲劳寿命预测研究

针对橡胶隔振器疲劳寿命预测问题,基于哑铃型橡胶材料试片的疲劳寿命试验数据,建立橡胶隔振器的疲劳寿命预测模型,进而提出橡胶隔振器疲劳寿命预测的研究方案。设计了一哑铃型橡胶试片进行拉伸疲劳试验,实测其疲劳寿命数据并以最小二乘法拟合了该试片疲劳寿命的幂函数预测模型。再通过有限元方法计算了橡胶隔振器的三种常见的疲劳寿命评价参数：对数主应变、柯西主应力和应变能密度,最后将橡胶隔振器的疲劳寿命预测值与实测值进行比对。结果发现：当疲劳失效标准静为刚度降级25%时,三种疲劳寿命评价参数均能较好地拟合成幂函数疲劳寿命预测模型,对数主应变的预测值较为接近实测值、应变能密度参数的预测值约为实测值2倍左右、柯西主应力预测寿命的可靠性验证系数均接近5,且三种疲劳损伤评价参数的疲劳寿命拟合曲线形状均较为相似。     

考虑应变路径的多轴低周疲劳寿命预测模型

通过分析材料在多轴非比例加载下产生附加强化的机理,该文以拉扭薄壁管试件为研究对象,分析了临界平面上的应变状态,并在此基础上以塑性应变能为控制参数定义表征多轴低周疲劳寿命对应变路径依赖性的非比例度。基于多轴疲劳临界损伤面原理,应用von-Mises 准则和本文定义的应变路径非比例度参数建立起能反映应变路径对非比例附加强化影响的多轴低周疲劳寿命预测模型。利用该模型预测08X18H10T 不锈钢、Ti-6Al-4V合金、S460N 钢和2.25Cr-1Mo 钢这4 种材料的多轴疲劳寿命,并与试验值进行比较。结果表明:该模型的预测结果与试验结果吻合良好,能同时适用于比例与非比例加载,预测精度较高,便于工程应用。     

Mode III interlaminar fracture characterization of composite materials

An experimental project was undertaken to develop two interlaminar Mode III tearing test methods. The first was a split cantilever beam test. A laminate, containing a starter crack, was bonded between aluminum bars. The ends of the bars were then loaded in opposite directions, parallel to the plane of the crack and normal to the beam length. Stable crack growth was achieved in carbon fiber material. Unidirectional carbon fiber composites showed Mode III critical strain energy release rates in the range 1·1–1·3 kJ/m². The effects of laminate thickness, beam depth, and data reduction method were investigated. In addition, testing was conducted on angle-ply laminates. Unsuccessful tests were conducted on a tougher matrix thermoplastic composite.An edge delamination specimen was also investigated. [15° _i/ – 15° _i]_S angle-ply laminates were fabricated with four implanted edge starter cracks. Both tension and compression tests were conducted. Difficulties in interpreting the results are discussed. The split cantilever beam and edge delamination results are compared.     

Off-axis fatigue cracking behaviour in notched fibre metal laminates

The off‐axis fatigue cracking behaviour of notched fibre metal laminates under constant amplitude loading conditions was investigated experimentally and numerically. It was found that the off‐axis fatigue crack initiation life decreased as the off‐axis angles increased. This indicated that the off‐axis laminates raised the applied stress level in the aluminium (Al) layer and subsequently resulted in earlier cracking in the Al layer. The off‐axis fatigue crack initiation lives of notched fibre metal laminates were predicted using lamination theory and an energy‐based critical plane fatigue damage analysis from the literature. After a crack initiated in the Al layer, it was observed that the crack path angles of the off‐axis specimens were neither perpendicular to the fibre nor to the loading direction. A finite‐element model was established for predicting the crack path angles.     

玻璃纤维-Al 混杂复合层板的疲劳裂缝扩展行为

本文研究了一种新型结构复合材料玻璃纤维-Al 混杂复合层板(Glass Aluminum Laminates,GLALL)在不同外载荷作用下的疲劳裂缝扩展行为,以及疲劳破坏规律。试验发现,由于未断高强度纤维对裂缝的桥接作用降低了裂缝尖端的有效应力场强度因子,GLALL 的疲劳裂缝扩展速率远低于单一Al 合金。伴随 Al 合金层内疲劳裂缝的扩展,GLALL 疲劳裂缝附近区域会产生脱层破坏,脱层区宽度随外加载荷增大而增大。脱层区宽度越小,纤维对疲劳裂缝的桥接作用越强。     

轻合金自冲铆微动磨损及疲劳性能研究

选择4组轻合金自冲铆进行疲劳实验,用扫描电子显微镜和能谱仪对其断口进行微动磨损机理分析,并系统地研究了接头疲劳寿命和失效形式的影响因素。结果表明,下板与钉腿区的微动磨损是导致下板沿纽扣断裂和铆钉断裂的主要原因,两板间的微动磨损是导致上板靠钉头断裂的主要原因;微动磨屑主要成分为金属板材氧化物,并对微动磨损起缓冲作用。增加板厚可提高接头疲劳寿命,且疲劳载荷较大时寿命提高更为显著;增加板强可提高接头疲劳寿命,且寿命提高程度受疲劳载荷影响较小。增加板厚使失效形式从上板断裂变为下板断裂,增加板强使失效形式从板材断裂变为铆钉断裂。     

Delamination growth mechanisms in woven glass fiber reinforced polymer composites under Mode II fatigue loading at cryogenic temperatures

The purpose of this research is to characterize the cryogenic delamination growth behavior in woven glass fiber reinforced polymer (GFRP) composite laminates subjected to Mode II fatigue loading. Mode II fatigue delamination tests were performed at room temperature, liquid nitrogen temperature (77 K) and liquid helium temperature (4 K) using the four-point bend end-notched flexure (4ENF) test method, and the delamination growth rate data for the woven GFRP laminates were obtained. The energy release rate range was determined by the finite element method. Microscopic examinations of the specimen sections and fracture surfaces were also carried out. The present results are discussed to obtain an understanding of the fatigue delamination growth mechanisms in the woven GFRP laminates under Mode II loading at cryogenic temperatures.     

Mode III fatigue delamination growth of glass fiber reinforced polymer woven laminates at cryogenic temperatures

This paper investigates the cryogenic fatigue delamination behavior of glass fiber reinforced polymer woven laminates under Mode III loading. Fatigue delamination tests were conducted using split cantilever beam specimens at room temperature, liquid nitrogen temperature (77 K) and liquid helium temperature (4 K). A finite element analysis was also employed to calculate the energy release rate. The temperature dependence of the fatigue delamination growth rate vs. energy release rate range is discussed. Fracture surfaces were examined by scanning electron microscopy to identify the delamination mechanisms under fatigue loading. The important conclusion we reach is that the Mode III fatigue delamination growth rates of woven laminates at cryogenic temperatures are lower than that at room temperature.     

Stiffness and fracture analysis of laminated composites with off-axis ply matrix cracking

Matrix cracks parallel to the fibres in the off-axis plies is the first intralaminar damage mode observed in laminated composites subjected to static or fatigue in-plane tensile loading. They reduce laminate stiffness and strength and trigger development of other damage modes, such as delaminations. This paper is concerned with theoretical modelling of unbalanced symmetric laminates with off-axis ply cracks. Closed-form analytical expressions are derived for Mode I, Mode II and the total strain energy release rates associated with off-axis ply cracking in [0/θ]_s laminates. Stiffness reduction due to matrix cracking is also predicted analytically using the Equivalent Constraint Model (ECM) of the damaged laminate. Dependence of the degraded stiffness properties and strain energy release rates on the crack density and ply orientation angle is examined for glass/epoxy and carbon/epoxy laminates. Suitability of a mixed mode fracture criterion to predict the cracking onset strain is also discussed.     

The impact properties and damage tolerance and of bi-directionally reinforced fiber metal laminates

Fiber metal laminates are an advanced hybrid materials system being evaluated as a damage tolerance and light weight solution for future aircraft primary structures. This paper investigates the impact properties and damage tolerance of glass fiber reinforced aluminum laminates with cross-ply glass prepreg layers. A systematic low velocity impact testing program based on instrumented drop weight was conducted, and the characteristic impact energies, the damage area, and the permanent deflection of laminates are used to evaluate the impact performance and damage resistance. The post-impact residual tensile strength under various damage states ranging from the plastic dent, barely visible impact damage (BVID), clearly visible impact damage (CVID) up to the complete perforation was also measured and compared. Additionally, the post-impact fatigue behavior with different damage states was also explored. The results showed that both GLARE 4 and GLARE 5 laminates have better impact properties than those of 2024-T3 monolithic aluminum alloy. GLARE laminates had a longer service life than aluminum under fatigue loading after impact, and they did not show a sudden and catastrophic failure after the fatigue crack was initiated. The damage initiation, damage progression and failure modes under impact and fatigue loading were characterized and identified with microscopy, X-ray radiography, and by deply technique.     

A Review of Critical Plane Orientations in Multiaxial Fatigue Failure Criteria of Metallic Materials

The paper presents a review of multiaxial fatigue failure criteria based on the critical plane concept. The criteria have been divided into three groups, according to the fatigue damage parameter used in the criterion, i.e. (i) stress, (ii) strain and (iii) strain energy density criteria. Each criterion was described mainly by the critical plane orientation. Multiaxial fatigue criteria based on the critical plane concept usually apply different loading parameters in the critical plane whose orientation is determined by (a) only shear loading parameters (crack Mode II or III), (b) only normal loading parameters (crack Mode I) or sometimes (c) mixed loading parameters (mixed crack Mode). There are also criteria based on few critical plane orientations and criteria based on critical plane orientations determined by a weighted averaging process of rotating principal stress axes.     

A new unidirectional carbon fiber prepreg using physically modified epoxy matrix with cellulose nano fibers and spread tows

A new unidirectional carbon fiber prepreg was successfully developed, whose epoxy matrix was physically modified with cellulose nano fibers (CNF). Two different types of prepreg were fabricated using regular carbon fiber (CF) and spread CF tows to identify the effect of prepreg thickness on the mechanical performance including fatigue of quasi isotropic laminates using these prepregs while the thickness of each layer was kept the same (120 μm). The effect of CNF modification of epoxy matrix on the fatigue life is quite significant if thin prepregs were used. It increases greater than 10 times than the fatigue lives of laminates fabricated by regular CF tows/unmodified EP or regular CF tows/modified EP. Uniformly dispersed CNF in the epoxy matrix increases the interfacial strength between CF and matrix.