微动疲劳损伤失效分析

介绍了微动疲劳损伤失效的现象，影响因素，鉴别特征，并举例说明。     

Review of Advances in Quantitative Eddy Current Nondestructive Evaluation

A comprehensive review of advancements in eddy current (EC) modeling is presented. This paper contains three main sections: a general treatise of EC theory, the thin skin EC forward modeling, and the EC inverse problem. (1) The general treatise of eddy current theory begins with an exposition of the reciprocity formulas for evaluating probe impedance changes, which are derivable from first principles. Two versions of the reciprocity formulas, one with a surface integral and the other with a volume integral, are given. Any particular type of defect, as well as both one-port and two-port probes, can be treated. Second, a brief account of analytical and numerical methods for calculating the field distributions is presented. Third, theory of probe/material interactions with various defect types is described. (2) The paper then proceeds to the forward modeling section, which contains a detailed treatment of the eddy current forward problem for surface breaking cracks and EDM notches in the thin skin approximation. (3) The inverse problem section begins with a general review of commonly used inversion methods, exemplified by selected references from the literature, followed by more detailed examinations of EC inversions for surface breaking cracks and slots. The last part of this section is devoted to the inverse problem for layered structures. Although being a review in nature, the paper contains a number of new accounts for time-domain eddy current interactions. In particular, a modification is proposed to the reciprocity formula in order to take a better account of pulsed eddy current signals.     

A Procedure for Comprehensive Investigation of the Fretting-Fatigue Damage of Metals

A procedure for comprehensive investigation of the fretting-fatigue damage of metals and structural alloys is described. A specific feature of the procedure is the possibility to measure and monitor the main mechanical parameters of fretting fatigue using a personal computer for primary processing and accumulation of test data in real time. The procedure developed makes it possible to reduce considerably the experimental error and to increase the informativeness and efficiency of experiments. The magnitude of electric microcurrents in fretting pairs during testing is used as the parameter for the estimation of the level of damaging processes of nonmechanical nature.     

电涡流传感器阵列测试技术

针对采用扁平柔性电涡流传感器阵列实现大面积金属曲面部件位置实时监测,对电涡流传感器的阵列测试技术进行了研究.采用一种基于时分多路的电涡流阵列测试的方法,通过对传感器探头和测试电路的合理设计,使系统电路得到简化,减小阵列单元之间的串扰,提高传感器系统的测试性能,实现了电涡流传感器阵列的快速、高精度测量.     

18CrNiMo7-6合金钢的弯曲微动疲劳特性

对18CrNiMo7-6合金钢进行弯曲微动疲劳实验,建立弯曲微动疲劳S-N曲线,并对实验结果进行分析。结果表明:该合金钢的弯曲微动疲劳S-N曲线不同于中碳钢材料,也不同于常规弯曲疲劳,而是呈"ε"型曲线特征。随着弯曲疲劳应力的增加,微动运行区域由部分滑移区向混合区和滑移区转变,损伤区的磨损机制以剥层、磨粒磨损和氧化磨损为主。在混合区内,裂纹最易萌生和扩展,且裂纹均萌生于材料接触区次表面。受接触应力和弯曲疲劳应力影响,弯曲微动疲劳裂纹的萌生和扩展可分为三个阶段:初期,在接触应力控制下,裂纹萌生于次表面;随后,裂纹受接触应力和弯曲疲劳应力共同控制,转向更大角度方向扩展;最后,裂纹完全受弯曲疲劳应力控制而垂直于接触表面扩展,直至断裂失效。     

铝包带包裹高压输电线路导线的微动损伤

在自制的微动试验装置上对铝包带包裹钢芯铝绞导线（ACSR）进行微动试验研究。振幅1．0mm,2．0×107次微动循环后,研究内、外层铝股线及钢芯线的磨损状况,测定其抗拉强度,探讨铝包带包裹导线的微动损伤机制。结果表明：外层铝股线表面经受铝包带的刮擦以及磨粒磨损;内层铝股线微动磨损斑呈椭圆形,部分磨损斑下有疲劳裂纹;而钢芯线的损伤微弱,仅发生镀锌层的磨损、脱落。铝包带对导线有较好的保护作用,内外层铝股线的抗拉强度均高于未包裹导线的抗拉强度。     

材料的微动疲劳机理及防护措施的研究进展

论述了微动疲劳的概念及时其研究的必要性.对微动疲劳研究的4个主要部分即微动疲劳的机理研究、影响因素、寿命预测和防护方法的发展过程进行了论述,尤其对当前的研究现状及所取得的成果做了重点阐述,并说明了一些尚待研究的问题.从微动疲劳机理研究、研究方法和防护方法等几个方面概述了微动疲劳研究的发展趋势.     

321不锈钢疲劳早期损伤的涡流评估

采用涡流阵列系统对321不锈钢疲劳早期损伤进行了检测与评估。整个疲劳过程中涡流幅值的变化分为快速增长、稳定和加速增长三个阶段。第一阶段的涡流幅值与循环周次对数之间有近似线性关系。在裂纹萌生寿命内,疲劳损伤区的大小与循环周次无关。对不同循环周次下321不锈钢试样的微结构分析表明疲劳早期涡流幅值变化的主要来源是材料内部位错的增殖和运动,而不是马氏体相转变。     

Quantitative Fractography for Improved Probability of Detection (POD) Analysis of Bolt Hole Eddy Current

Fatigue cracks are prone to develop around the fasteners found in multilayer aluminum structures such as ageing aircraft. The determination of their probability of detection (POD) using eddy current techniques is critical for risk assessments used in evaluating serviceability. Normally, a large number of samples of both fatigue cracks and electric discharge machined notches are required for such a study. In this study, the use of quantitative fractography (QF) to efficiently gather POD data for bolt hole eddy current is demonstrated. The technique can be readily automated, significantly reducing man-hour requirements. The method is applied to mid-bore cracks, grown without starter notches, in order to simulate naturally occurring fatigue cracks. POD of the mid-bore cracks is examined using a probit analysis. An a _90/95 is the probability that 90% of the cracks of size a or larger will be detected 95% of the time. An a _90/95 of 0.34 mm was obtained for mid-bore crack depth. This value is consistent with skin depth considerations at the 1.6 MHz inspection frequency. An examination of the POD based on crack length found that it was related to that of depth according to the average length-to-depth aspect ratio of 2 to 1.     

Eddy Current Probability of Detection for Mid-Bore and Corner Cracks in Bolt Holes of Service Material

Fatigue cracks are prone to develop around fasteners found in multilayer aluminum structures on aging aircraft. Probability of detection (POD) studies using eddy current techniques within the bolt holes contribute to risk assessments used in evaluating the serviceability of these aircraft. Signal response to corner and mid-bore cracks by eddy current testing using standard split-D differential probes has been examined for in-service material from the horizontal stabilizer of a Hercules aircraft. Results are compared to data obtained from laboratory samples with drilled holes. Based on a logistic regression analysis, the results show no significant difference for a_90/95 (90% of the cracks of size a will be detected 95% of the time) for mid-bore crack length of 0.60 mm in this study compared to 0.62 mm in earlier work on drilled holes. However, there was a substantial loss of sensitivity for corner cracks. In this study on in-service material, the a_90/95 for corner cracks was 0.82 mm compared to 0.31 mm obtained from drilled holes. Decrease in sensitivity was attributed to damage at the hole’s corners of the in-service material, including rounding, folded metal, and burrs. Hole damage also significantly increased the risk of a false call.     

Nondestructive Evaluation of Fiberglass Reinforced Plastic Subjected to Combined Localized Heat Damage and Fatigue Damage Using Acoustic Emission

The effect of fatigue damage to unidirectional fiberglass composite specimens with prior contact heat damage was investigated. After damaging the specimens by contacting them to a hot tip at 360°C, the specimens were subjected to fatigue loading at cyclic stress amplitude corresponding to 65% of the specimens' ultimate tensile strength. The fatigue experiments was halted after 3,000 cycles. The specimens were then subjected to tensile tests while monitoring their acoustic emission (AE) activity. In addition, acoustic emission activities of undamaged and contact heat-damaged specimens were monitored during tensile tests for comparison with specimens with combined fatigue and heat damage. AE activities of all specimens can be categorized into three regions: an early rise in activity, a relatively dormant period in activity, and a high exponential activity before failure. The early rise in activity did not appear on the specimens with combined contact heat and fatigue damage. For undamaged and contact heat-damaged specimens, the period of the dormant activity was independent of the contact heat duration of less than 15 minutes. However, the period was a function of the contact heat duration for combined contact heat and fatigue damaged specimens. Analyzing event duration distribution identified micro-mechanisms of the damage growth upon tensile loading. AE-stress delay concept was used to predict the state of the damage in the composite. A correlation between stress delay parameter and damage parameter was obtained for all of the specimens. Fatigue life of contact heat damaged specimen was also studied. It was found that localized heat damage reduced the fatigue life significantly. Loss of matrix to transfer the load to the fibers uniformly was believed to be responsible for the reduction in the fatigue life.     

脉冲磁场激励下圆柱导体内瞬态涡流场的快速计算

建立了脉冲磁场激励下圆柱导体内瞬态涡流场的理论模型。实现了瞬态涡流场的快速计算。通过实例表明上述圆柱导体内瞬态涡流场的快速计算方法有效。     

飞机结构腐蚀检测中的脉冲涡流无损检测技术

对脉冲涡流无损检测技术的工作原理进行了分析，建立了脉冲涡流的检测系统对加工的模拟飞机多层结构的试件进行了测试，提取其时域瞬态感应信号的峰值和过零时间作为特征量，对出现在飞机多层结构第二层中的腐蚀缺陷进行了定量检测，试验结果和理论分析相一致，证明了脉冲涡流检测方法的有效性，由于其具有快速和定量化的优点，因而在飞机结构的腐蚀检测中具有广阔的应用前景．     

单向帘线/橡胶复合材料的疲劳损伤模型与疲劳寿命预报

将不可逆热力学和损伤力学应用于橡胶复合材料的疲劳研究，在大量试验工作的基础上，选择适当的热力学势函数，建立了橡胶复合材料的损伤演变方程和橡胶复合材料的疲劳寿命预报方程。应用本模型对单向橡胶复合材料的疲劳寿命进行了预报，发现理论预测值与试验结果比较符合。     

结构风振的概率疲劳累积损伤

本文通过考虑脉动风压的随机过程性,利用风荷载的规范标定方法和结构疲劳试验结果,从结构风振随机反应分析着手,提出了基于疲劳累积损伤机制的抗风结构疲劳可靠性和寿命估计的分析方法,并通过一典型单自由度结构说明了此方法的应用。     

The Strategy of Widespread Fatigue Damage in FMP System

As is known,widespread fatigue damage ( WFD) is a common phenomenon of aging aircraft being a negative impact on safety and reliability. The current FAR 25. 571( b) requires that"An LOV ( Limit of Validity) must be established,during which it is demonstrated that widespread fatigue damage will not occur in the aircraft structures". The FAA issued AC 91-82A in August 2011 providing guidance on developing and implementing a Fatigue Management Program ( FMP) system to address in-service issues for metallic fatigue critical structures. This action brings new challenges to aircraft manufacturers in China. This paper introduces the problem of widespread fatigue damage including the MSD( multiple site damage) and MED( multiple element damage) and the differences between them and the steps to establish the LOV / ELOV( Extended limit of validity) . Authors in this paper is also proposing some management indicators to control WFD during the design phase and maintenance. Developing and implementing the management indicators to address WFD which are involved in the FMP system may provide guidance on the estimation and management to address WFD for present and future aircraft. Finally,some suggestions are put forward to provide the theoretical basis for large civil aircraft design and airworthiness.     

疲劳累积损伤对发动机缸盖再制造的影响

通过对新、旧发动机缸盖取样进行疲劳试验,对比了其SN曲线,结果发现：应力幅较大时,新、旧缸盖材料的疲劳寿命相差明显;应力幅较小时,新、旧缸盖材料的疲劳寿命相差不大,表明旧发动机缸盖材料的损伤程度随着应力幅的增加而增大。因此当发动机经过再制造后,有可能因为累积损伤的原因存在安全隐患。     

Time-Frequency Analysis of Pulsed Eddy Current Signals

Detection and measurement of the material loss due to corrosion in aircraft fuselage lap splices are of great importance to life management of ageing aircraft. Pulsed eddy current (PEC) techniques have shown the potential to fully characterise these structures. However, variations in the probe lift-off, the interlayer gaps and material thinning produce similar PEC signals, making signal interpretation very difficult. This paper describes time-frequency analysis algorithms applied to pulsed-eddy current signals from lap-joint specimens containing simulated flaws. The effect of probe lift-off, interlayer gap, and material thinning on PEC signals is examined in three-dimensional space (amplitude-time-frequency). This study shows that the time-frequency analysis of PEC signals provides specific visual patterns that can be related to the interlayer gap, lift-off, and material loss.     

基于脉冲涡流检测技术的缺陷定量检测研究

对飞机多层结构中出现的缺陷进行定量检测具有重要意义.文章将脉冲涡流检测技术应用其中,设计并实现了一套完整的脉冲涡流检测系统.在对检测信号进行分析处理的基础上,提取峰值、峰值时间、过零时间等时域特征量,实现对缺陷的定量检测,并通过进一步的实验加以验证.     

Acousto-elastic Measurement of the Fatigue Damage in Waspaloy

It has long been speculated that second-order effects should prove an effective measure of a material's fatigue and damage state. One such second-order effect is the acousto-elastic effect. In a series of experiments on the nickel-based superalloy waspaloy, the change in the acousto-elastic coefficient of Rayleigh waves was monitored as the material was fatigued. Our results demonstrate the possibility of using this variation as a mean of measuring fatigue in waspaloy. They also show that waspaloy demonstrates a significantly different acousto-elastic behavior than that expected from a metal. This fact enhances the sensitivity of the technique in this material. It is interpreted as being due to load transfer between the two major phases found in waspaloy, the matrix phase (γ) and the strengthening phase (γ′).