斜纹编织碳纤维/环氧树脂复合材料II型分层性能及损伤演化表征

为研究编织复合材料在静载及疲劳载荷下的分层特性及损伤演化模式,对斜纹编织CF3052/3238A碳纤维/环氧树脂复合材料II型静开裂及疲劳开裂性能进行了测试。结果表明:斜纹编织CF3052/3238A碳纤维/环氧树脂复合材料裂纹扩展行为受纬向纤维影响存在周期性局部受阻现象,分层破坏模式除层间开裂外还存在纬向纤维脱粘;斜纹编织CF3052/3238A碳纤维/环氧树脂复合材料裂纹扩展速率符合Paris公式,不同加载控制模式下编织复合材料疲劳驱动力增长规律存在本质区别:恒幅疲劳载荷下斜纹编织复合材料疲劳驱动力呈抛物线型单调增长;而恒幅疲劳位移下复合材料疲劳驱动力随分层长度呈波峰型分布;采用基于载荷控制模式和位移控制模式下的疲劳驱动力模型,可对斜纹编织CF3052/3238A碳纤维/环氧树脂复合材料进行损伤演化表征,其表征效果良好,具有工程参考价值。      

3238A炭纤维织物复合材料力学性能研究

通过中温固化环氧树脂3238A分别增强炭纤维织物C305和G803,制作成为预浸料.两种预浸料在温度125℃,压力0.5MPa下经2h固化,成为层压板,3238A/C305与3238A/G803两种复会材料常规力学性能、高低温、湿热性能程疲劳性能进行比较.结果表明,3238A/C305复合材料性能略低.     

Al-7Si-0.3Mg铸造合金的旋转弯曲疲劳性能研究

研究了M-7Si-0.3Mg铸造铝合金的室温旋转弯曲疲劳性能。结果表明,A1-7Si-0.3Mg铸造铝合金在10~7次疲劳寿命下的极限应力为88 MPa;结合对疲劳试样断口的分析发现,在高应力低寿命区,A1-7Si-0.3Mg合金试样的表面划痕和缺陷造成了材料的表面破坏模式;而在低应力高寿命区,试样内部近表面区的铸造孔洞则是引起材料疲劳破坏的主要原因。使用Paris公式推导出孔洞尺寸和疲劳寿命之间的关系,并计算出不同应力水平条件下的临界孔洞尺寸。     

碳纳米管对碳纤维/环氧树脂复合材料力学性能的影响

为了探讨碳纳米管(CNTs)对碳纤维/环氧树脂复合材料(CF/ER复合材料)力学性能与疲劳寿命的影响,利用静态拉伸实验和拉-拉疲劳实验沿纤维方向对CF/ER复合材料和CNTs增强CF/ER复合材料(CNTs/CF/ER复合材料)进行了对比研究,同时利用X射线仪与扫描电镜对试样进行了观察.研究结果表明,CNTs的加入,虽然对CF/ER复合材料的拉伸力学性能影响不明显,但可以提高高周疲劳寿命约4倍,使各种实验应力水平下的裂纹密度降低9.5％以上,并可观察到试样中CNTs的拔出、破裂及桥联作用.由此可见,CNTs的加入可明显改善CF/ER复合材料的疲劳寿命.     

调质42CrMo钢的弯曲微动疲劳实验研究

针对循环软化材料调质42CrMo钢进行了常规弯曲疲劳实验和弯曲微动疲劳实验,分析了常规弯曲疲劳和弯曲微动疲劳之间的差异,并讨论了循环弯曲载荷对疲劳寿命的影响。通过分析不同弯曲载荷下弯曲微动疲劳试样断口的形貌和不同循环次数下微动损伤的情况,揭示调质42CrMo钢弯曲微动疲劳过程中的损伤特性。研究结果表明:同一循环载荷作用下,弯曲微动疲劳的寿命明显低于常规弯曲疲劳的寿命;随着循环弯曲载荷的增大,弯曲微动疲劳的寿命降低更明显;微动引起的局部接触疲劳和局部塑形变形促进了弯曲微动疲劳裂纹的萌生和进一步扩展。     

石油钻杆材料G105在不同条件下的疲劳断裂

采用国产PQ-6型旋转弯曲疲劳试验机研究钻杆管体材料G105的弯曲疲劳性能以及H_2S腐蚀和缺口对试样弯曲疲劳性能的影响,利用金相显微镜和扫描电子显微镜对光滑试样断口、缺口试样断口以及H_2S腐蚀后试样断口进行微观形貌分析。结果表明:在光滑试样的疲劳极限载荷作用下,经过H_2S腐蚀后的光滑试样的疲劳寿命和缺口试样的疲劳寿命相当,材料的疲劳寿命都从106降低至104;缺口试样在缺口的高应力集中效应下,加快疲劳裂纹形核过程。H_2S腐蚀对钻杆疲劳性能影响的主要作用在于氢原子在材料内缺陷处聚集引起材料疲劳性能降低,缺口和H_2S腐蚀都会加快疲劳裂纹的扩展。材料疲劳断裂主要是因为试样在交变应力的作用下上产生滑移最后致使位错塞积而导致的。     

芳纶纤维对炭黑/丁苯橡胶复合材料疲劳行为的影响

使用短芳纶纤维（AF）增强炭黑/丁苯橡胶（CB/SBR）复合材料,研究AF对复合材料疲劳行为的影响。在应力控制条件下,少量AF的加入使缺口试样的疲劳寿命提高了25.5倍;疲劳使试样的储能模量（G'）降低,AF的加入使疲劳后试样的Payne效应降低,G₀'/G₁₀₀'值降低10.5%;复数模量随疲劳周期增加而降低,但少量纤维能使复合材料的复数模量保持在较高的水平,30 000周疲劳下AF-CB/SBR的复数模量仍为CB/SBR的1.73倍;疲劳后AF-CB/SBR复合材料的100%和300%定伸应力随疲劳变形量的增加而先增大后降低,断裂伸长率有所下降。试样疲劳后相对于拉伸变形量,纤维的增强作用产生滞后效应,相对界面滑脱能随疲劳应变幅度的增加而降低; SEM结果显示,疲劳后橡胶基体出现一定的剥离,纤维与橡胶界面受到损伤。     

残余压应力对45钢疲劳裂纹萌生寿命的影响

本文研究了４５钢不同缺口半径及经预压，喷丸处理后对试样弯曲疲劳裂纹萌生寿命的影响。研究结果表明：随着试样缺口根部半径的增大，试样的弯曲疲劳裂纹萌生寿命增加。     

高速列车制动盘SiCp／A356颗粒增强铝基复合材料的热疲劳性能研究

通过SiCp／A356颗粒增强复合材料切口试样在20℃-300℃循环下的热疲劳试验,获得热疲劳裂纹形成寿命与试样切口半径及厚度等几何尺寸的关系。采用热弹塑性有限元法模拟热疲劳试验中试样切口根部的应力．应变响应,进而揭示出残余应力形成机制。结合热疲劳试验的裂纹形成寿命与有限元模拟的应力．应变响应,建立起考虑平均应力影响的...     

复合材料高周弯曲疲劳试验与寿命预测

利用一阶弯曲共振现象,开展了复合材料悬臂梁高周弯曲疲劳试验。为了取代传统的金属疲劳理论,根据复合材料疲劳损伤渐进扩展的特点,发展了新的数值方法应用于复合材料的疲劳分析。研究局部疲劳损伤模型和周期跳跃技术,开发了复合材料悬臂梁高周弯曲疲劳的半解析法Matlab疲劳损伤分析程序;另一方面,通过开发UMAT子程序,实现了疲劳损伤模型和周期跳跃技术在商业有限元软件ABAQUS中的应用。分别使用半解析法和有限元法分析复合材料悬臂梁高周弯曲疲劳的损伤累积破坏过程,预测了其高周弯曲疲劳寿命,数值预测结果与试验结果较好吻合。     

An apparatus for quantitative fretting testing

The design and construction of an apparatus for performing quantitative fretting fatigue experiments is described. The device allows accurate measurement and control of normal contact force, tangential contact force, relative displacement between contacting surfaces and bulk fretting loads, as well as measurement of average friction coefficients. Its design is simple, and includes interchangeable fretting contact pads, allowing the use of various pad geometries without major adjustment. The device incorporates many points of adjustment for alignment and compliance, making it a robust frame for a wide variety of fretting fatigue conditions involving different materials. The capabilities of this device are also verified by results of fretting fatigue experiments conducted on a 7075-T6 aluminium alloy.     

A review of multiaxial fatigue of weldments: experimental results, design code and critical plane approaches

A survey of biaxial (bending or tension and torsion) constant amplitude fatigue of welded connections is presented. Re-analysis of 233 experimental results from eight different studies has been performed based on hot spot stresses and three potential damage parameters: maximum principal stress range; maximum shear stress range; and a modified critical plane model for welds. Of the three methods, the critical plane model was most successful in resolving the data to a single S – N line. The design curve for all toe failures based on the critical plane model was FAT 97 with a slope of 3. By excluding butt welds and including only fillet welds that failed at the weld toe, the design curve was increased to FAT 114 with a slope of 3. However, observed scatter was 70–100% larger than that observed in uniaxial loaded specimens analysed using the hot spot approach.     

On the estimation of the material fatigue properties required to perform the multiaxial fatigue assessment

To accurately perform the fatigue assessment of engineering components subjected to in‐service multiaxial fatigue loading, the adopted design criterion must properly be calibrated, the used information usually being the fatigue strength under both pure uniaxial and pure torsional fatigue loading. Because of the complex fatigue response of metallic materials to multiaxial loading paths, the only reliable way to generate the necessary pieces of calibration information is by running appropriate experiments. Unfortunately, because of a lack of both time and resources, very often, structural engineers are requested to perform the multiaxial fatigue assessment by guessing the necessary fatigue properties. In this complex scenario, initially, the available empirical rules suitable for estimating fatigue strength under both pure axial and pure torsional fatigue loading are reviewed in detail. Subsequently, several experimental results taken from the literature and generated by testing metallic materials under a variety of proportional and non‐proportional multiaxial loading paths are used to investigate the way such empirical rules affect the accuracy in estimating fatigue strength, the damage extent being evaluated according to the modified Wöhler curve method. Such a systematic validation exercise allowed us to prove that under proportional loading (with both zero and non‐zero mean stresses), an adequate margin of safety can be reached even when the necessary calibration information is directly estimated from the material ultimate tensile strength. On the contrary, in the presence of non‐proportional loading, the use of the empirical rules reviewed in the present paper can result, under particular circumstances, in a non‐conservative fatigue design.     

几种常用的金属材料疲劳极限试验方法

金属疲劳试验用于测定金属材料的许用疲劳应力,绘制材料的疲劳曲线,进而在交变应力下测定金属材料的疲劳极限。疲劳研究的试验方法有很多,该文根据有关国家标准和现有文献资料对一些常用疲劳试验方法进行了综述,包括单点疲劳试验法、升降法疲劳试验、高频振动疲劳试验法、超声波法疲劳试验、红外热像技术疲劳试验方法,并对每种疲劳试验方法的试验目的、适用条件、试验试样、所需仪器、具体步骤和数据处理进行了介绍。     

Experimental multiaxial fatigue tests realized with newly developed geometry specimens

In the literature there are many experimental results of multiaxial fatigue testing, usually generated by the combination of two or more cyclical loads. The cases in which samples are randomly stressed are rarer. Moreover, to generate particular stress states, the use of specific machinery for fatigue tests is usually required. For these reasons, the authors have created a particular geometry of specimens, which, when solicited by a single input of a random type, guarantees the creation of specific multiaxial stress states without using complex and costly instruments. The experimental tests were finally used for the validation of the multiaxial reduction method developed and currently utilized in the authors' design phase, though potentially used to verify all the other methodologies present in the literature.     

Fatigue damage of medium carbon steel under sequential application of axial and torsional loading

Fatigue tests were conducted on S45C steel under fully reversed strain control conditions with axial/torsional ( at ) and torsional/axial ( ta ) loading sequences. The linear damage value (n₁/N₁+n₂/N₂) was found to depend on the sequence of loading mode ( at or ta ), sequence of strain amplitude (low/high or high/low) and life fraction spent in the first loading. In general, at loading yields larger damage values than ta loading and the low–high sequence of equivalent strain leads to larger damage values than the high–low sequence. The material exhibits cyclic softening under axial cyclic strain. Cyclic hardening occurs in the torsion part of ta loading, which elevates the axial stress in the subsequent loading, causing more damage than in pure axial fatigue at the same strain amplitude. Fatigue life is predicted based on the linear damage rule, the double linear damage rule, the damage curve approach and the plastic work model of Morrow. Results show that overly conservative lives are obtained by these models for at loading while overestimation of life is more likely for ta loading. A modified damage curve method is proposed to account for the load sequence effect, for which predicted lives are found to lie in the factor‐2 scatter band from experimental lives.     

A computerized procedure for long-life fatigue assessment under complex multiaxial loading

A computerized procedure is presented and evaluated for application examples of long-life fatigue analyses of metallic materials under complex multiaxial loading. The method is based on the stress invariants and uses the minimum circumscribed ellipse approach for evaluating the effective shear stress amplitude under complex multiaxial loading. The applicability of the procedure for handling non-proportional loading is examined through typical examples such as combined normal/shear stresses and combined bi-axial normal stresses with complex stress time histories. The effects of phase shift angles, frequency ratios and waveforms on fatigue endurance were re-analysed and compared with available experimental results from the literature. The comparison shows that the presented procedure based on stress invariants is a potential conservative engineering approach, very suitable for fast fatigue evaluation in the integrated computer aided fatigue design.     

On the life-controlling microstructural fatigue mechanisms in ductile metals and alloys in the gigacycle regime

The high-cycle fatigue (HCF) behaviour of ductile metals and alloys, and the life-controlling microstructural fatigue mechanisms known from HCF are reviewed critically with respect to their possible role in the gigacycle or ultra-high-cycle fatigue (UHCF) regime. Arguments are presented to support the hypothesis that, at the very low amplitudes of the UHCF regime, fatigue crack initiation, resulting from cyclic strain localization, and slow early Stage I fatigue crack propagation are the life-controlling mechanisms and that these processes can essentially be described in terms of the microstructurally irreversible portion of the cumulative cyclic plastic strain. Emphasis is placed on the important role of the so-called slip irreversibility which decreases as the amplitude becomes lower and lower. Finally, the Manson–Coffin law is reformulated for very low amplitudes in terms of microstructurally relevant parameters, and a fatigue life diagram is developed, based on these preceding microstructural considerations. Important features of this diagram are: (i) the plastic strain fatigue limit in the HCF regime which is related to the threshold for cyclic strain localization in persistent slip bands; and (ii) the transition from this plastic strain fatigue limit to a threshold of negligible slip irreversibility at still lower amplitudes in the UHCF regime.     

金属材料疲劳试验与数据处理方法

疲劳是金属材料机械构件常见的一种失效形式,疲劳试验方法与数据处理方法一直是研究学者们关注的热点。该文从疲劳寿命和规定寿命下的疲劳强度两个方面介绍了疲劳试验和数据处理方法的主要研究成果,并说明了几种典型的疲劳寿命试验方法与疲劳寿命概率分布参数的统计方法,以及规定寿命下的疲劳强度试验方法与规定寿命下的疲劳强度概率分布参数的统计方法;并通过算例,对比了不同方法之间的差异。     

Fatigue damage discrepancies,the intrinsic fatigue damage map locus and the multiple stages of the similitude concept

The work demonstrates how the theory of the fatigue damage map (FDM) can be used in order to define a closed form locus where fatigue crack growth can be sought. The Intrinsic FDM Locus depending only on readily material properties represents a tool able to accurately predict crack growth of polycrystals. If the Locus is expressed in terms of a surface plot after triangulation of the data, it concludes into visualization of the potential for multiple similitude stages. The stages are defined as a function of the maximum far field stress and ΔK. Multiple similitude stages are found to dominate the short and near threshold area (Stage I growth) and represent direct result of the effect of polycrystalline behaviour to flow resistance. The work concludes that interrogation of the points defining the Intrinsic FDM Locus and related to the three thresholds can provide potential characteristics in the quest for an ideal damage tolerance material.