超声载荷下TC4钛合金的疲劳寿命分析

通过计算裂纹尖端应力强度因子及疲劳裂纹扩展速率da/d N,由C.Paris模型推导出安全寿命Nf,由Bathias公式计算"哑铃"状钛合金试样的裂纹扩展寿命。通过理论计算和有限元分析超声疲劳"哑铃"状试样,得出应力最大位置。利用有限元仿真和实验数据分析TC4钛合金疲劳寿命。在20 k Hz的超声疲劳试验中,试样的断口位置表明:TC4钛合金材料内部缺陷是试样萌生裂纹使断裂位置偏离最大应力处的主要原因。并得出疲劳裂纹萌生阶段寿命决定"哑铃"状试样的疲劳寿命。     

不同释放程度下下肢动脉支架的疲劳强度及寿命预测

目的 探究释放程度和支架结构对支架疲劳寿命的影响。方法 利用有限元法分析3款镍钛合金下肢动脉支架（Complete SE、E–luminexx–B和Pulsar–35）在脉动载荷作用下的力学性能,基于疲劳应变理论评估支架的疲劳强度,使用Fe–safe和Abaqus软件预测支架在不同释放程度（80%、85%、90%）下的疲劳寿命及安全性。应用Origin软件对支架应力与疲劳寿命进行拟合。结果 支架在释放尺度为80%～90%下的疲劳强度均满足10年疲劳寿命的要求。3种支架释放程度为90%时,疲劳强度大,寿命长;释放程度为80%时,疲劳强度、寿命及安全系数小。相同释放程度下,偏置型波峰结构支架变形后的交变应变及弹性应力值最大,支架寿命及安全系数最小;对称型波峰结构支架CE的寿命及安全系数小于EB。通过LangevinMod函数拟合PR支架疲劳寿命,拟合优度R2>0.99。结论 随着释放程度的增大,3款支架疲劳强度、寿命及安全系数呈增大趋势。在相同释放程度下,支撑单元对称型波峰结构支架疲劳强度、寿命及安全系数比偏置型波峰结构支架大,减小对称型波峰结构支架的连接体宽度有利于提高支架寿命。     

血管内支架的疲劳强度的有限元模拟分析

为了揭示支架支撑体长度、宽度及圆弧曲率半径对其疲劳强度的影响规律,利用有限元法对不同结构参数的9种血管内支架进行动静态模拟分析,并用Goodman线图评价了支架的疲劳强度。结果显示,静态扩张过程中,随着支撑体长度或圆弧曲率半径的增加,支架所需的最大等效应力有减少的趋势,而随着支撑体宽度的增加,支架所需的最大等效应力有增加的趋势。动态加载过程中,支撑体长度、支撑体宽度及圆弧曲率半径均与疲劳安全系数成反比,其中支撑体宽度对疲劳安全系数的影响要比圆弧曲率半径和支撑体长度的影响较明显。关于支架疲劳强度的有限元分析结果,为支架的优化设计提供科学的理论依据。     

浅谈港口机械结构疲劳寿命预测技术

分析了疲劳寿命预测技术对于港口机械在结构设计以及安全运行上的重要性,介绍了几种主要的疲劳寿命分析方法,并构建了一种适用于港口机械的结构疲劳寿命预测系统,以期为港口机械结构的安全可靠性提供保障。     

非比例载荷下缺口件疲劳寿命预测

针对Mod.9Cr-1Mo铁素体钢缺口件进行了一系列非比例载荷低周疲劳试验,采用直流电位差法测量裂纹萌生寿命,比较了缺口半径和应变路径对疲劳裂纹萌生寿命的影响。结果表明,缺口件裂纹萌生寿命占总寿命的比例与材料类型、应变路径相关,更与缺口半径尺寸直接相关。同一路径下,随着缺口半径增加,裂纹萌生寿命所占比例增大。采用Neuber律进行缺口局部应力-应变损伤的计算,结合Smith-Watson-Topper (SWT)模型和Kandil-Brown-Miller (KBM)模型进行疲劳寿命预测。结果表明,除单轴路径和比例路径外,SWT模型得到的预测结果偏于不安全;KBM模型除对单轴预测偏于保守外,其他预测值较好,总体预测结果位于2倍分散带内。     

机翼构件不同载荷谱下的寿命反推

对飞机机翼构件在不同截荷谱下的宏、微观断裂特征进行了观察与分析，并结合载荷谱中的应力变化特点，对A飞机和B飞机翼构件在不同载荷谱下的裂纹扩展寿命进行反推。结果表明，载荷谱中不同的应力变化在失效构件断口上反映出不同的宏、微观断裂特征，采用断口定量分析技术可反推构件的疲劳寿命，并依此反推构件疲劳裂纹形核的先后顺序。     

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。     

一种处理载荷累积频次分布的方法

针对载荷累积频次分布,提出了一种确定某个应力水平下累积频次的方法,与其它已有方法进行误差对比分析,可看出本方法能大大提高精度。在疲劳试验中,可应用于形成载荷程序块,使疲劳寿命的预测列加精确。     

316L不锈钢的高温疲劳蠕变行为和寿命预测

进行316L不锈钢在单级和两级载荷作用下的高温疲劳蠕变试验,研究了载荷历程效应对材料行为的影响.在已有统一的疲劳蠕变损伤演化模型基础上,得到了316L高温单级载荷作用下非线性损伤演化曲线.同时,建立了一种耦合载荷历程效应的多级疲劳蠕变载荷作用下的材料破坏准则.基于该破坏准则,结合材料的非线性损伤模型对316L不锈钢高温两级载荷作用下的疲劳蠕变寿命进行了预测,预测结果与试验数据符合得比较好.     

多轴载荷下缺口件的疲劳寿命估算方法

提出了一种多轴载荷下缺口件的疲劳寿命估算方法。该方法基于临界平面理论,计算出缺口件各部位的多轴疲劳损伤参数,以损伤参数最大的部位为缺口件的多轴疲劳危险点。根据临界距离思想,提出了热点法和线法的临界距离的计算方法,采用热点法和线法考虑缺口件疲劳危险点附近损伤梯度的影响,以临界距离修正的损伤参数计算多轴载荷下缺口件的疲劳寿命。采用SAE1045钢缺口件的多轴疲劳试验对该文提出的寿命估算方法进行评估和验证,结果表明：该文所建立的寿命预测方法具有较好的预测能力,预测结果大部分分布在试验结果的3倍分散带之内。     

复合材料层合板低速冲击后压-压疲劳试验研究及寿命预报

进行了复合材料层合板低速冲击和冲击后压-压疲劳试验。在疲劳试验过程中详细测量了损伤扩展情况,获得了损伤扩展规律。将冲击损伤等效为一圆形开孔,应用含椭圆形夹杂的杂交应力单元分析含圆孔有限大板的应力分布,采用特征曲线和点应力判据相结合的方式并通过引入损伤扩展规律建立了含低速冲击损伤复合材料层板压-压疲劳寿命预测模型。通过与试验数据的对比,证明了该模型的有效性。同时,该模型还可预报在疲劳载荷下含冲击损伤层板的剩余压缩强度。     

FATIGUE LIMIT AND FATIGUE LIFE PREDICTION IN HIGH STRENGTH COLD DRAWN EUTECTOID STEEL WIRES

Abstract— Both the fatigue limit and the fatigue life of a structural member are highly dependent upon its surface condition and on the microcrack growth rate. A model based on linear elastic fracture mechanics has been developed which involves both parameters and predicts with good accuracy the available experimental results. The factors that must be modified in order to improve the fatigue behaviour of cold drawn eutectoid steel wires are indicated.     

FRACTURE MECHANICS APPROACH FOR PREDICTION OF FATIGUE LIFE OF HIGH STRENGTH STEEL COMPONENTS

Abstract— A fatigue life estimation procedure based on a fracture mechanics approach is analytically developed for components made of a 4140 grade high strength steel. The maximum allowable flaw sizes for both static and cyclic loads are computed. For different stress levels and shapes of the defects, initially-existing, allowable defect size versus number of operating cycles, as well as the thickness versus tolerable defect sizes curves, are presented. The maximum allowable operating cycles of components for non-destructively detectable minimum defects are also estimated. From these estimations, a more realistic prediction of the safe service life of components is possible.     

FATIGUE LIFE PREDICTION FOR GAUSSIAN RANDOM LOADS AT THE DESIGN STAGE

Fatigue life prediction under variable amplitude loading normally involves a two stage process of cycle counting and damage summation. This paper shows that for certain classes of strain history, predictions can be made directly from a knowledge only of the power spectral density of the strain history and conventional fatigue strength data.     

转子裂纹检测与寿命预测技术研究

现代的抗疲劳设计法——损伤容限设计使零件在出现疲劳裂纹后通过严格的检修、剩余寿命计算和断裂控制仍能安全使用 ,使充分利用零件的剩余强度成为可能。对损伤容限设计的关键技术——初始缺陷或服役中出现的疲劳裂纹检测和疲劳剩余寿命预测技术进行了研究。成功地研制了一套性能优良的交流电位表面裂纹监测系统 ,分辨率为 0 .1 mm,测量精度达到± 2 % ,测量范围为 0～ 1 0 0 mm;开发出一套微机平台上的基于断裂力学的 (含表面裂纹 )转子剩余寿命计算程序 ,为分析裂纹扩展形态和概率断裂力学方法估算剩余寿命提供了快速计算途径。有较强的工程实用性和良好的市场开发前景。     

CFL增强RC梁抗弯疲劳强度的实验研究

疲劳强度是进行结构抗疲劳设计的重要力学参量。通过对5组24条碳纤维薄板(CFL)增强RC梁进行三点弯曲常幅疲劳试验,得到了增强梁的容许疲劳寿命和极限疲劳寿命S-N曲线及其相应的表达式,并推定其容许疲劳强度和极限疲劳强度分别为其极限承载力的62%和68%。还给出了新的疲劳寿命曲线的表达形式:载荷做功的功率H与增强梁的疲劳寿命N的关系曲线(H-N曲线),并由此推定了增强梁的容许疲劳强度和极限疲劳强度所对应的功率值。     

BIMODAL CONCEPT OF HIGH-CYCLE FATIGUE LIFE PREDICTION FOR CONSTANT AND VARIABLE AMPLITUDE FATIGUE

A bimodal concept for the prediction of the high-cycle fatigue life of structural details subjected to constant- or variable-amplitude loading is considered in this paper. The total fatigue life was separated into two phases: crack initiation and crack propagation. The portion of life spent in crack initiation was estimated by using S–N data obtained on smooth specimens. A fracture mechanics concept was used to calculate the portion of life spent in crack propagation, and the S–N curve, including the fatigue limit of a structural detail, was determined by using material properties and the geometry of the detail. The bimodal concept was applied to a welded stiffener and the results are compared with experimental data reported in the literature.     

FATIGUE LIFE PREDICTION OF NOTCHED COMPOSITE COMPONENTS

Abstract— The local stress/strain approach has been used to predict the fatigue lives of notched composite components. The method was based on a microstress analysis and the application of a multiaxial fatigue parameter incorporating the alternating strain components on the critical plane. This parameter was able to correlate the fatigue lives obtained under a variety of multiaxial loading and geometrical configurations, enabling a generalized fatigue life curve to be determined on the basis of limited experimental data.
The ability of the multiaxial fatigue parameter to relate the fatigue behaviour of composites was illustrated by predicting the locations of crack initiation sites in a unidirectional silicon carbide fibre reinforced titanium plate containing a circular hole tested under constant amplitude cyclic loading. The same approach was also successfully employed to predict the fatigue lives of graphite reinforced epoxy composite tubes with circular holes tested under several combinations of cyclic tension and torsion.     

LIFE PREDICTION BY SIMULATION OF CRACK GROWTH IN NOTCHED COMPONENTS WITH DIFFERENT MICROSTRUCTURES AND UNDER MULTIAXIAL FATIGUE

A modelling procedure was developed which is applicable to crack growth in notched components subjected to multiaxial fatigue for materials with different microstructures. An algorithm for crack growth, in a microstructure that was modelled as hexagons, was established as a competition between growth by crack linkages during the crack initiation and propagation stages and the propagation of a dominant crack as a single crack. Analytical results simulated by using the developed model were compared with experimental results from fatigue tests which had been conducted using notched specimens of pure copper, carbon steel and two kinds of titanium alloy. Cracking morphology, which was experimentally observed to depend on the microstructure and the loading mode, was well simulated using the present model. The fatigue failure life of a notched specimen was statistically estimated by a Monte Carlo procedure based on the model. The simulated life with a statistical scatter-band almost coincided with the experimental data.     

FATIGUE CRACK INITIATION LIFE PREDICTION IN HIGH STRENGTH STRUCTURAL STEEL WELDED JOINTS

The local approach method is used to calculate the fatigue crack initiation/early crack growth lives (N_i) in high strength structural steel weldments. Weld-toe geometries, welding residual stresses and HAZ (heat affected zone) cyclic mechanical properties are taken into account in the N_i estimation procedure. Fatigue crack initiation lives are calculated from either a Basquin type or a Manson-Collin type equation. The local (HAZ) stress and strain amplitudes and the local mean stress are determined from an analysis based on the Neuber rule and the Molski-Glinka energy approach. The accuracy of the different methods is evaluated and discussed. Finally the previous methods are used with HAZ cyclic mechanical properties estimated from hardness measurements.