基于非线性连续损伤的机床轴结构疲劳研究

运用MINER线性累积损伤理论对机床轴结构进行疲劳研究时,由于不能连续描述损伤与载荷之间的关系,在高周疲劳寿命预测过程中其计算结果不能令人满意。为此,基于CHABOCHE提出的单轴非线性连续累积损伤理论,通过对45钢进行疲劳试验获得了轴结构材料的S-N曲线,在对机床载荷谱简化处理的基础上,建立了适于机床轴结构寿命预测的多轴非线性连续损伤累积模型。实例计算证明,该模型能准确描述机床轴结构损伤累积过程,计算结果更符合工程实际。     

基于电阻法的金属材料损伤表征研究现状

电阻率对金属材料微观组织变化具有精确性和敏感性。近年来,随着微电阻测量精度的不断提高,基于电阻法的金属材料损伤表征研究开始大量出现。综述了不同金属材料试样在拉伸韧性损伤、高温时效损伤、高周疲劳损伤和蠕变损伤过程中弹性模量、拉伸强度、断裂韧性、硬度、时效时间和疲劳周次等参量与电阻参量的映射关系,探讨了损伤导致电阻变化的微观机理,指出了今后微电阻法的主要研究方向。     

基于累积损伤理论的ST12钢T型点焊件寿命研究

对低碳钢T型撕裂拉伸点焊试件分别进行低-高和高-低两级加载疲劳试验,并利用线性和非线性疲劳累积损伤理论进行寿命预测。对于低-高加载,非线性预测结果较线性稍好一些;对于高-低加载,由于高载下的"过载效应",线性预测结果与非线性预测结果都不太理想。针对高-低加载下的寿命预测误差,本文提出一种基于CHABOCHE修正模型的非线性疲劳累积损伤模型,分别考虑了两级应力幅以及疲劳塑性指数的影响。通过对比后发现,修正后的模型预测点焊寿命能力较原模型有所改善。     

基于固有耗散的FV520B钢高周疲劳性能研究

基于固有耗散理论和计算模型,对FV520B钢的高周疲劳性能进行了较为系统的实验研究.结果表明,随着施加的交变应力幅的增大,FV520B钢的固有耗散也不断增大.其变化规律的拐点对应于固有耗散产生机制的转变,从单纯地由材料微结构的可逆运动(位错线在强钉扎点之间的摆动)引起,到由材料微结构的可逆运动和不可逆运动(永久滑移的产生、强钉扎点的脱钉以及位错的增殖)共同引起.并且,固有耗散拐点的应力幅值就是导致材料疲劳损伤累积的临界应力幅值,即疲劳极限.另外,实验还表明,FV520B钢在等幅交变应力下具有相对稳定的损伤演化速率,且损伤演化速率由应力幅值决定,与加载次序无关;每一周加载造成的疲劳损伤也不受加载频率的影响.当FV520B钢在疲劳过程中累积的与微结构不可逆演化相关的固有耗散部分达到一个临界值时,材料即发生疲劳断裂,且这个临界值是一个与加载历史无关的材料常数.     

过盈配合对沉头铆钉无载孔疲劳寿命的影响分析

针对飞机结构中过盈配合对无载孔疲劳寿命的影响开展了研究,通过试验对比分析了普通铆接试验件和过盈量1%铆接试验件。结合有限元分析,采用多轴疲劳理论对不同过盈量的铆接紧固孔在疲劳载荷下的损伤参量进行研究,确定过盈量对疲劳损伤的影响规律。实验结果表明:过盈量为1%铆接紧固件可提高紧固孔的疲劳寿命15%左右;通过有限元分析,适当的过盈量可降低紧固孔的应力幅和应变幅,进而降低疲劳损伤参量。     

基于能量耗散的激光焊对接接头高周疲劳性能快速评估

基于红外热像法获得对接接头疲劳自热温升数据,建立激光焊对接接头能量耗散疲劳评估模型. 借助能量耗散模型,对Q310NQL2-Q345NQR2激光焊接头高周疲劳过程的疲劳性能进行了研究. 结果表明,随着应力幅值的增加,Q310NQL2-Q345NQR2激光焊接头的能量耗散随之增加,并在疲劳极限附近出现了拐点. 结合 RVE(representative volume element)模型分析,该拐点正是材料内部从单一的可逆微结构运动到同时包括可逆和不可逆的微结构运动的转折点. 其中不可逆微结构运动相应于引起材料损伤的非弹性耗散,当损伤累积到一定程度,其相应的非弹性能量耗散也存在阀值. 以此阀值作为疲劳寿命预测参量,建立高周疲劳激光焊对接接头疲劳寿命预测模型,实现S-N曲线的快速预测.     

Ti-55531合金的高周疲劳断口形貌分析

基于断口学理论、借助SEM分析技术,分析高强韧Ti-55531合金片层和双态组织在不同应力幅下的高周疲劳断口形貌特征,揭示应力幅和组织因素对该合金高周疲劳裂纹萌生的协同作用机制,阐明组织因素对合金疲劳裂纹扩展的影响规律。结果显示:应力幅大小对片层组织的疲劳裂纹萌生行为有显著影响,但对双态组织影响较小。在疲劳裂纹扩展前期,片层的裂纹扩展速率大于双态的;但在裂纹扩展中后期,双态的裂纹扩展速率反而更高。     

基于不同应力法的焊接构架纵向角接头疲劳累积损伤评估

在焊接构架结构应力计算整体有限元模型基础上,通过考虑接头角焊缝和1 mm焊趾虚拟缺口半径,对转臂定位座板与箱形侧梁下盖板的组焊纵向角接头进行逐步细化,构建热点应力和有效缺口应力计算局部模型.在动态疲劳试验载荷等效的9级载荷谱作用下,分别基于名义、热点及有效缺口三种不同应力参量,结合ⅡW建议的疲劳设计S-N曲线进行累积损伤计算.结果表明,有效缺口应力的累积损伤远高于名义和热点应力,极有可能引起评估结果过于保守.为充分发挥有效缺口应力法的优势,需要以更加符合结构实际的缺口几何数据和强度数据作为支撑.     

ST12汽车钢板拉剪点焊接头的疲劳强度

针对车身使用的ST12低碳钢板,利用生产线上焊接设备制备了电阻点焊接头拉剪疲劳试件.对点焊接头区域进行了金相组织观测,测量了焊点附近的维氏硬度值分布.在MTS材料疲劳试验机上进行了恒幅疲劳加载,得到了ST12低碳钢板的电阻点焊接头的S-N曲线.基于所得的S-N曲线进行了两级疲劳加载试验,对两级加载下的线性累积疲劳损伤进行了分析.累积损伤结果分析表明,ST12低碳钢板电阻点焊件在两级加载下存在加载次序效应,高-低加载次序下加载次序效应更为明显.     

一种基于能量耗散的对接接头疲劳寿命快速预测模型

通过引入ISV(internal state variable)本构模型中的α和β变量,建立了一种与对接接头高周疲劳滞弹性和非弹性行为相关的能量耗散模型,并定义了两个特征应力幅,即标志着可恢复滞弹性和不可恢复非弹性行为开始形成的关键应力幅σ_c0和σ_c1(疲劳极限);借助该能量耗散模型,研究了不同应力幅下的对接接头能量耗散响应情况,发现能量耗散在疲劳极限附近呈现从线性响应到非线性响应的过渡;在此基础上,考虑到当应力幅高于疲劳极限时,全寿命周期的能量耗散存在临界值,结合与损伤相关的非弹性耗散,研发了一种基于损伤累积的疲劳寿命预测模型,并对接头的疲劳寿命进行了快速预测.结果表明,经预测数据和试验数据拟合的中值S-N曲线一致程度较好,从而证明了模型可用于实现对接接头的疲劳寿命快速、精确预测.     

TC4钛合金的多轴高周疲劳损伤及强度退化研究

不同工况下TC4(Ti-6Al-4V)钛合金疲劳累积损伤及强度退化存在较大差别。为了充分表征载荷参数的影响,基于Chaboche损伤模型以及改进的多轴疲劳损伤准则,提出新的强度退化模型,开展了TC4钛合金的多轴高周疲劳(HCF)寿命预测和强度退化评估。首先,开展TC4合金在一系列加载路径下的多轴比例和非比例疲劳试验。将Chaboche非线性损伤准则和临界平面法与提出的损伤控制参数相结合,描述了TC4合金的非线性疲劳损伤计算和寿命预测。其次,进一步建立了基于累积损伤的非线性强度退化模型,并证明了该模型在不同载荷工况下均可以获得更高的精度。实验结果表明,由于考虑载荷参数的影响,提出的TC4钛合金疲劳寿命与强度退化预测结果精度远高于其他的预测模型。     

Fatigue behavior of aluminum stiffened plate subjected to random vibration loading

Vibration tests were carried out on three types of stiffened aluminum plates with fully clamped boundaries under random base excitation. During the test, the response of the specimens was monitored using strain gauges. Based on the strain history, the accumulation of fatigue damage of the stiffened plates was estimated by means of the rainflow cycle counting technique and the Miner linear damage accumulation model in the time domain. Utilizing the change of natural frequencies, a nonlinear model was fitted for predicting the fatigue damage of plate and then the foregone failure criterion of 5% reduction in natural frequency is improved. The influence of section and spacing of the stiffeners on the vibration fatigue behavior of the aluminum plate was investigated. The results show that the fatigue life of aluminum plate increases with adding either T or L section riveted stiffeners. With the same cross-sectional area of stiffener, the T section stiffened plate shows longer fatigue life than L section stiffened plate. Meanwhile, the vibration fatigue life also shows great sensitivity to the spacing between the stiffeners.     

Fatigue Life Prediction of Metallic Materials Based on the Combined Nonlinear Ultrasonic Parameter

The fatigue life prediction of metallic materials is always a tough problem that needs to be solved in the mechanical engineering field because it is very important for the secure service of mechanical components. In this paper, a combined nonlinear ultrasonic parameter based on the collinear wave mixing technique is applied for fatigue life prediction of a metallic material. Sweep experiments are first conducted to explore the influence of driving frequency on the interaction of two driving signals and the fatigue damage of specimens, and the amplitudes of sidebands at the difference frequency and sum frequency are tracked when the driving frequency changes. Then, collinear wave mixing tests are carried out on a pair of cylindrically notched specimens with different fatigue damage to explore the relationship between the fatigue damage and the relative nonlinear parameters. The experimental results show when the fatigue degree is below 65% the relative nonlinear parameter increases quickly, and the growth rate is approximately 130%. If the fatigue degree is above 65%, the increase in the relative nonlinear parameter is slow, which has a close relationship with the microstructure evolution of specimens. A combined nonlinear ultrasonic parameter is proposed to highlight the relationship of the relative nonlinear parameter and fatigue degree of specimens; the fatigue life prediction model is built based on the relationship, and the prediction error is below 3%, which is below the prediction error based on the relative nonlinear parameters at the difference and sum frequencies. Therefore, the combined nonlinear ultrasonic parameter using the collinear wave mixing method can effectively estimate the fatigue degree of specimens, which provides a fast and convenient method for fatigue life prediction.     

Low cycle fatigue behavior of zirconium–titanium–steel composite plate

The low cycle fatigue behavior of zirconium–titanium–steel composite plate under symmetrical and asymmetric stress control was studied. The effects of mean stress and stress amplitude on cyclic deformation, ratcheting effect and damage mechanism were discussed in detail. The results show that under symmetric stress control, the forward ratcheting deformation is observed. Under asymmetric stress control, the ratcheting strain increases rapidly with mean stress and stress amplitude increasing. Under high stress amplitude, the influence of mean stress is more significant. In addition, by studying the variation of strain energy density, it is found that the stress amplitude mainly promotes the fatigue damage, while the mean stress leads to the ratcheting damage. In addition, fracto- graphic observation shows that the crack initiates in the brittle metal compound at the interface, and the steel has higher resistance to crack propagation. Finally, the accuracy of life prediction model considering ratcheting effect is discussed in detail, and a high-precision life prediction model directly based on mean stress and stress amplitude is proposed.     

基于损伤力学的粉末高温合金FGH96疲劳寿命预测

以粉末高温合金FGH96为研究对象,提出采用损伤力学理论来建立寿命预测模型。对于不同夹杂物特征,粉末高温合金裂纹萌生有不同的表征参量,其数值变化为裂纹萌生的寿命预测提供思路。对粉末高温合金寿命预测的研究现状进行分析,然后利用损伤演变方程建立寿命预测模型;使用有限元软件（ANSYS）分别模拟夹杂物的不同位置、不同尺寸以及不同形状对裂纹萌生的影响,得到相应的损伤参量分布云图。将得到的损伤参量代入计算模型,得到疲劳寿命计算结果,与实验结果进行对比,证明疲劳寿命预测模型的有效性。结果表明:损伤参量Y能较好地表征材料的低周疲劳损伤;在不同的实验条件（温度、应变范围和应变比）下,所建立的粉末合金FGH96疲劳寿命预测模型都能较好地反映夹杂物对粉末高温合金疲劳寿命的影响。     

基于连续损伤力学的高低周复合疲劳损伤

基于连续损伤力学(CDM)的经典损伤理论和不可逆热力学原理，分别对高周和低周疲劳载荷下的损伤演化模型进行了研究，进而推导出一个新的高低周复合疲劳损伤模型；将该模型编写为UMAT耦合到ABAQUS有限元分析软件中，实现了对缺口材料高低周复合疲劳损伤的模拟及裂纹萌生位置和萌生寿命的预测；同时研究了不同的高低周循环比对裂纹萌生寿命的影响.结果表明,裂纹容易在缺口根部应力集中处萌生；该模型考虑了高低周循环的交互作用，模拟计算结果更符合实际情况；同时通过研究发现高的循环比会使裂纹的萌生加速.     

航空发动机液压管路疲劳寿命预测模型研究

为较为准确地评估航空发动机液压管路的疲劳寿命,提出一种疲劳寿命预测模型。该模型重点计算一个循环周期内载荷对液压管路造成的损伤,在此基础上,建立液压管路危险点处的应力与疲劳寿命之间的解析关系式。将该模型用于某型航空发动机外部液压管路疲劳寿命的计算,并将该理论计算结果与有限元仿真结果进行对比,验证了该疲劳寿命预测模型的有效性。     

基于混合硬化模型的Ti-6Al-4V低周疲劳损伤分析

以连续损伤力学(CDM)为基础,根据Ti-6Al-4V钛合金应变疲劳试验结果,改进了Krajcinovic和Lemaitre提出的损伤本构模型,并拟合确定了损伤模型参数;将该损伤本构模型编写为USDFLD子程序并耦合到ABAQUS有限元软件中. 使用Chaboche非线性随动强化和非线性各向同性硬化的混合硬化模型来描述Ti-6Al-4V钛合金的弹塑性行为,并拟合确定了混合硬化模型参数. 模拟了材料在不同应变幅下的低周疲劳损伤演化. 结果表明,损伤模型预测寿命和试验寿命吻合较好,对比试验和模拟结果可以发现,损伤模型预测寿命的平均误差为3.878%.     

Grain size based low cycle fatigue life prediction model for nickel-based superalloy

Nickel-based superalloys are easy to produce low cycle fatigue (LCF) damage when they are subjected to high temperature and mechanical stresses. Fatigue life prediction of nickel-based superalloys is of great importance for their reliable practical application. To investigate the effects of total strain and grain size on LCF behavior, the high temperature LCF tests were carried out for a nickel-based superalloy. The results show that the fatigue lives decreased with the increase of strain amplitude and grain size. A new LCF life prediction model was established considering the effect of grain size on fatigue life. Error analyses indicate that the prediction accuracy of the new LCF life model is higher than those of Manson-Coffin relationship and Ostergren energy method.