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1.
分析和讨论3种典型载荷(单轴拉压、纯扭及90°非比例)情况下的5组损伤控制参数,提出了一种以临界面上最大剪切应力幅和最大法向应力的非线性组合作为损伤控制参数的多轴高周疲劳寿命预测模型,该模型考虑了平均应力对疲劳寿命的影响,比现有的疲劳预测模型具有更宽的金属材料适用范围.两种不同类型材料下的多轴非比例试验的预测结果表明,模型的预测结果与试验符合较好.  相似文献   

2.
CTS试件中复合型疲劳裂纹扩展   总被引:3,自引:0,他引:3  
马世骧  胡泓 《力学学报》2006,38(5):698-704
针对复合型循环载荷作用下的金属构件中的裂纹扩展问题进行了实验分析和理论建模. 首先 采用紧凑拉剪试件(CTS)和 Richard研制的复合型载荷加载装置,对承受复合型循环载荷的裂纹进行了实验研究. 实验选择了两种金属材料试件,分别承受3种形式的复合型循环载荷的作用,在裂纹尖端具 有相同的初始应力场强度的条件下考察复合型循环载荷对裂纹扩展规律的影响. 实验结果表明,疲劳裂纹的扩展速率与加载角度有关. 对于同样金属材料的试件,当裂尖处 初始应力场强度相等时,载荷越接近于II型,裂纹增长速率越快. 采用等效应力强度 因子(I型和II型应力强度因子的组合)、裂纹扩展速率及复合强度等参数,以实验数据为 基础,建立了一个疲劳裂纹扩展模型,用来预测裂纹在不同模式疲劳载荷作用下的扩展速率. 为验证其有效性,该模型被应用于钢制试件的数值模拟计算中. 实验结果与模拟计算曲线保 持一致,表明该模型可以用来估算带裂纹金属构件的寿命.  相似文献   

3.
16MnR钢循环蠕变-疲劳交互作用损伤力学模型   总被引:8,自引:0,他引:8  
应力控制模式下出现的循环蠕变现象,将和疲劳一起加速材料的损伤.在进行损伤评估的时候,需兼顾循环蠕变和疲劳的影响.在循环蠕变本构模型、延性耗散理论的基础上,建立循环蠕变疲劳交互作用损伤力学模型.进行16 MnR钢420℃下应力控制的脉动循环试验,选取一种新的损伤参量“等效模量”来描述循环蠕变和疲劳的综合作用,得到16 MnR钢420℃脉动循环时循环蠕变疲劳交互作用下的损伤演化估算表达式和寿命预测方法.通过试验验证,寿命预测结果与试验结果吻合较好.  相似文献   

4.
疲劳线性累积损伤理论的α值实验验证   总被引:3,自引:0,他引:3  
对疲劳累积损伤临界值进行了实验验证.首先进行了某构件三种随机载荷谱下的疲劳试验,测定了其谱载下的疲劳寿命T;再对载荷谱进行雨流计数,得到了各应力水平的循环次数n;利用疲劳性能Sα-Sm-N曲面,确定了构件在各应力水平单独作用下的疲劳寿命N;最后,根据 Miner公式,估算出各构件的疲劳累积损伤临界值(α值).根据分析结果推测:α值是一个均值为1的随机变量.  相似文献   

5.
高温合金材料循环相关热机械疲劳寿命预测   总被引:5,自引:0,他引:5  
在变温非线性运动强化规律所描述的高温合金材料热机械寿命应力-应变循环特性的基础上,讨论了应变控制的循环相关热机械疲劳寿命预测技术,所建模型采用了由应变以密度表示的损伤参数,并且引入了温度损伤系数,考虑了温度变化范围以及温度循环和应变循环相位关系对疲劳寿命的影响,在确定模型的一些参数,采用等温力学试验和疲劳试验的数据,为了把等温疲劳研究成果推广到变温疲劳分析领域,开辟了新的途径。  相似文献   

6.
为了定量评估含广布腐蚀损伤老龄化飞机结构的剩余强度, 采用等效裂纹方法将腐蚀坑沿垂 直于外界最大主应力方向进行投影处理, 使其转化为具有相同寿命的等效初始表面裂纹, 然 后采用参数化有限元方法,求解等效裂纹前沿的应力强度因子、裂纹扩展方向和裂纹扩展增量, 建立并应用应力强度因子变化历程, 采用循环接循环的损伤累积方法对含广布等效表面裂纹 在疲劳载荷作用下的寿命进行了预测. 预测结果为复杂环境中含广布腐蚀坑的飞机结构寿命 预测提供了参考.  相似文献   

7.
疲劳寿命估算的能量法及其实验研究   总被引:6,自引:0,他引:6  
根据疲劳损伤滞后能等效原理,导出了缺口件与光滑件的当量应力关系,通过Neuber公式和饱和应力应变关系,可确定当量应力取值;采用定量方程随机化方程,建立了γ-p-ε-N曲线(置信度-可靠度-应变-寿命曲线)公式及其实验测试方式;根据疲劳累积损伤理论和γ-p-ε-N曲线公式,得到了随机载荷谱作用下构件疲劳寿命估算公式;最后,实验验证了复杂实测载荷谱作用下,LY12CZ铝合金含孔试样的疲劳寿命估算结果  相似文献   

8.
疲劳是力学上的一个分支.主要是研究材料和构件在承受交变循环载荷作用下的强度、应力状态与寿命关系问题.材料在循环加载下,某部可发生损伤递增过程.经一定的应力或应变循环后,损伤累积可使材料产生裂纹,进一步扩展后可完全断裂.这种情况叫作疲劳破坏.疲劳问题是一个涉面很广的学术课题.据统计, ...  相似文献   

9.
从疲劳过程中材料显微组织结构的变化特征、疲劳损伤的非线性效应等方面进行分析与论证,提出了不存在一般意义上的“等效损伤状态”的观点,采用高-低和低-高两组循环载荷下的损伤累积试验,对传统意义上的“等效损伤状态”下的剩余寿命试验进行了验证。  相似文献   

10.
基于能量耗散法,推导出了复合材料厚壁圆筒的疲劳损伤和疲劳寿命函数;在此基础上,采用有限元软件 ABAQUS 建立复合材料圆筒模型,进行了模拟周期内压载荷作用下的疲劳仿真计算,得到了随着循环数的增加,疲劳损伤变量不断增大和材料性能不断退化的损伤规律。以同样的方法和载荷边界条件计算了全金属圆筒疲劳损伤的起始和演化。对比结果表明:相同循环次数作用下,后者的裂纹扩展长度和张开位移更大;随着循环次数的增加,后者的疲劳破坏比前者更剧烈,更难预测。  相似文献   

11.
大开口复合材料层合板强度破坏研究   总被引:5,自引:2,他引:3  
陈建霖  励争  储鹏程 《力学学报》2016,48(6):1326-1333
复合材料层合板的各向异性及非均质,使得复合材料层合板内部的破坏形式非常复杂.在复合材料结构的设计中,为满足制造及使用功能上的需求,在复合材料层合板承力结构件上不可避免地需要设计各种开口.然而,含大开口复合材料层合板的强度破坏问题变得更为复杂,使得现有的强度理论面临新的挑战.针对碳纤维增强复合材料大开口层合板受单向拉伸载荷作用下的强度破坏问题进行了数值分析和实验研究.首先,根据Hashin准则和刚度退化模型,对含不同圆形开口尺寸的[0]_(10)单向铺层、[0/90]_5和[±45]_5正交铺层的层合板,进行了单向拉伸载荷作用下渐进失效的数值模拟分析,获得了对应结构的极限载荷和破坏模式.在此基础上,采用数字图像相关方法,进行复合材料大开口层合板强度破坏的实验研究.研究结果表明,大开口复合材料层合板在单向拉伸加载下主要呈现脆性破坏形式,破坏起始位置处于应力集中区.此外,破坏强度和失效模式与复合材料铺层方式和开口尺寸大小密切相关.其中[±45]_5铺层的开口层合板承载能力最弱,分层破坏最严重.开口尺寸越大,结构的极限载荷值越低.同实验测试结果相比,数值模拟对复合材料层合板的损伤失效分析略显不足,往往很难全面分析复合材料层合板破坏失效过程中的各种因素的影响.  相似文献   

12.
智能可变形结构能感知周围环境的变化并做出适当的反应,其主要原理是利用智能材料层产生应变以达到驱动主体结构发生变形。含有智能材料压电纤维MFC的双稳态复合材料层合板可以通过智能驱动实时调整主体结构的形状,实现稳态构型之间的跳变。本文对中心点固支的MFC压电智能驱动双稳态复合材料层合板的稳态构型、跳变规律及其影响因素进行了系统地研究。研究内容主要包括:含MFC的双稳态层合板的稳态构型、分叉行为和驱动跳变分析。利用理论模型分析了层合板的长宽比、厚度尺寸、铺层方式和MFC粘贴位置对双稳态板分叉行为的影响,并预测了双稳态层合板的临界尺寸以及驱动跳变的临界电压。双稳态板的跳变是一个大变形的非线性行为,实现和控制跳变行为的研究是其应用的基础。本文的研究结果为新型压电材料驱动双稳态板的结构设计提供了一定的理论参考。  相似文献   

13.
The fatigue properties of graphite/epoxy (Gr/Ep) T300/5208 composite laminates of 16 plies with a central circular hole subjected to tension-tension (T-T) constant-stress amplitudes at room temperature and low humidity have been fully investigated. Studied are four types of notched laminates which are classified as unidirectional, off-axis, orthotropic shear and quasi-isotropic. Some of them were precracked to initiate and guide the crack growth transversely. Our work is experimental and the analysis is based on a semiempirical approach. We have experimentally measured S-N curves, failure surfaces, crack lengths and their corresponding growth directions, delamination areas and transverse delamination lengths for the above series of composites. The fatigue failure mechanism was observed and expressed schematically. To analyze the experimental results, we have categorized the S-N curves by three common equations. The effective transverse crack length of quasi-isotropic laminates was found to be independent of the applied stress. For simplicity, it was modeled by a power law of applied cycles. It was also found that the delamination area could be expressed by a power law of applied cycles. Hence, the so-called modified Paris law, i.e., the power law of cycles, proposed here has been verified as satisfactorily acceptable.  相似文献   

14.
Effects of stress ratio on fatigue life of carbon-carbon composites   总被引:1,自引:0,他引:1  
Cyclic loading causes cumulative damage and therefore degrades the inelastic properties of composite materials. Present work investigates the damage development under tension-tension fatique, and the effect of stress ratio on the fatigue life of carbon-carbon (C/C) composites at room temperature at a frequency of 3 Hz. The fatigue damage has been identified through ultrasonic non-destructive technique, optical microscopy and scanning electron microscopy.From the S-N curve it has been observed that the endurance strength of C/C composite is quite high; approximately 85% of the ultimate tensile strength. The fatigue life of C/C composites has also been observed to increase with the stress ratio. Matrix cracks, filament splitting within the yarns, complete delamination and the nucleation of the interfacial flaws have been identified as the failure mechanisms during the fatigue tests. On the other hand, the failure modes during the static test were found to be complete fiber fracture accompanied by partial delamination. A statistical fatigue life distribution for carbon-carbon composites has also been presented in this paper.  相似文献   

15.
焊趾表面裂纹的形态发展曲线与疲劳寿命预测   总被引:4,自引:0,他引:4  
以作者建立的焊地椭圆表面裂纹应力强度因子数据库以及复杂应力场中焊践半随圆表面裂纹前缘应力强度因子分布计算的基本模式法为基础上,给出了复杂应力场中焊践表面表纹在疲劳扩展过程中形态变化规律及寿命的工程分析方法。  相似文献   

16.
A two-dimensional model has been developed for thermal stresses, elastic strains, creep strains, and creep energy density at the interfaces of short and long trilayer assemblies under both plane stress and plane strain conditions. Both linear (viscous) and non-linear creep constitutive behavior under static and cyclic thermal loading can be modeled for all layers. Interfacial stresses and strains are approximated using a combination of exact elasticity solutions and elementary strength of materials theories. Partial differential equations are linearized through a simple finite difference discretization procedure. The approach is mathematically straightforward and can be extended to include plastic behavior and problems involving external loads and a variety of geometries. The model can provide input data for thermal fatigue life prediction in solder or adhesive joints. For a typical solder joint, it is demonstrated that the predicted cyclic stress–strain hysteresis shows shakedown and a rapid stabilization of the creep energy dissipation per cycle in agreement with the predictions of finite element analysis.  相似文献   

17.
Uniaxial ratcheting and fatigue failure of tempered 42CrMo steel were observed by the tests under the uniaxial stress-controlled cyclic loading with non-zero mean stress [G.Z. Kang, Y.J. Liu, Mater. Sci. Eng. A 472 (2008) 258–268]. Based on the obtained experimental results, the evolution features of whole-life ratcheting behavior and low-cycle fatigue (LCF) damage of the material were discussed first. Then, in the framework of unified visco-plasticity and continuum damage mechanics, a damage-coupled visco-plastic cyclic constitutive model was proposed to simulate the whole-life ratcheting and predict the fatigue failure life of the material presented in the uniaxial stress cycling with non-zero mean stress. In the proposed model, the damage was divided into two parts, i.e., elastic damage and plastic damage, which were described by the evolution equations with the same form but different constants, since the maximum applied stresses in most of loading cases were lower than the nominal yielding strength of the material. The ratcheting of the material was still described by employing a nonlinear kinematic hardening rule based on the Abdel-Karim–Ohno combined kinematic hardening model [M. Abdel Karim, N. Ohno, Int. J. Plast. 16 (2000) 225–240] but extended by considering the effect of damage. The maximum strain criterion combined with an elastic damage threshold was employed to determine the failure life of the material caused by two different failure modes, i.e., fatigue failure (caused by low-cycle fatigue due to plastic shakedown) and ductile failure (caused by large ratcheting strain). The simulated whole-life ratcheting behavior and predicted failure life of tempered 42CrMo steel are in a fairly good agreement with the experimental ones.  相似文献   

18.
The investigation on fatigue lives of reinforced concrete (RC) structures strength- ened with fiber laminate under random loading is important for the repairing or the strengthening of bridges and the safety of the traffic. In this paper, two methods are developed for predicting the fatigue lives of RC structures strengthened with carbon fiber [aminate (CFL) under random loading based on a residual life and a residual strength model. To discuss the efficiency of the model, 12 RC beams strengthened with CFL are tested under random loading by the MTS810 testing system. The predicted residual strength approximately agrees with test results.  相似文献   

19.
In a previous paper by Davidson, Eisenstadt and Reiner, it was noted that, as the diameter ratio of an open-end, thick-walled cylinder approached unity, the stress state due to internal pressure approaches that of uniaxial tension. It was, therefore, proposed that the fatigue life of a cyclically pressurized thick-walled cylinder might be predicted from the results of axialtension fatigue tests. In this paper, the results of the thick-walled-cylinder fatigue tests, reported in Ref. 2, extrapolated to a diameter ratio of unity, are compared with the results of axial-tension fatigue tests on the same material. The effect of oil in contact with the surface of the axial fatigue specimens and that of varying the cyclic speed from 1800 cpm to 200 cpm are investigated. Rotating beam fatigue test results for the same material are also reported. The results of the axial-tension fatigue tests do not agree with the extrapolated thick-walled cylinder results in the range of fatigue lives from 104 to 106 cycles with the cylinder results showing the shorter lives. For less than 104 cycles, the results converge. No effect of cyclic speed or of oil in contact with the surface was found. The results of the rotating-beam tests generally lie between the axial-tension and extrapolated cylinder results.  相似文献   

20.
The influence of ply-stacking sequence and ply orientation on the magnitude of lamination residual stresses in graphite/polyimide angle-ply laminates was investigated. The effect of stacking sequence was investigated with laminates of [02/±45]s, [±45/02]s, [0/+45/0/?45]s and [+45/02/?45]s layup. The effect of ply orientation was evaluated with additional specimens of [02/±15]s and [02/902]s layup. Thermal strains were measured using embedded-gage techniques. Residual strains were determined by comparing thermal strains in the angle-ply laminates with those of a unidirectional laminate. The ply-stacking sequence did not have an influence on the magnitude of residual strains. The highest residual strains occur in the [02/902]s laminate and the lowest, approximately one-fourth in magnitude, occur in the [02/±15]s laminate. The maximum residual strains in the [02/±45]s group are slightly lower than those in the [02/902]s laminate. Residual stress computations show that, at room temperature, the transverse-to-the-fibers stresses in all plies, except those of the [02/±15]s laminate, exceed the transverse tensile strength of the unidirectional material.  相似文献   

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