声发射技术在疲劳裂纹监测中的应用

主要介绍了声发射技术在金属结构试件疲劳试验中的应用,对带孔金属铝板的疲劳裂纹萌生的声发射监测进行了研究,并且对采集到的声发射信号进行了处理与分析。声发射监测技术可以实现结构疲劳裂纹萌生的早期实时监控和扩展趋势的判断。     

基于声发射技术的接触疲劳失效检测应用与研究

接触疲劳是齿轮、轴承等长期承受交变载荷的重要旋转零部件的主要失效形式。采用声发射技术对接触疲劳失效过程进行监测,对损伤程度进行检测以及揭示接触疲劳失效机理具有重要的意义。随着声发射技术不断发展及先进声发射信号处理技术的出现,其在接触疲劳失效检测中的研究也越来越深入。文章回顾了声发射技术的发展现状,综述了声发射技术应用于块体零件和涂层零件的接触疲劳失效检测的研究进展与存在的问题,探讨了进一步研究的方向和解决问题的思路。     

某型飞机主起落架支柱外筒头部枢轴疲劳损伤的声发射监测

某型飞机全尺寸机体疲劳试验过程中的无损检测和声发射(AE)监测对该型飞机疲劳定寿、确定修理周期及未来改进型疲劳细节设计起着十分关键的作用。起落架地面载荷试验是疲劳试验的重要组成部分,需要声发射监测的区域包括起落架梁和上、下枢轴等关键部位。针对试验过程的强冲击和强噪声干扰,作者利用声发射信号参数的趋势分析、基于时域和频域的滤波技术、相关分析方法和基于空间的滤波技术,实现了对这些目标的实时监测并成功地监测出上、下枢轴磨损等故障。     

飞机关键零部件疲劳损伤的声发射实时监测

某型飞机的水平尾翼试验过程是在强冲击、高振动背景噪声下进行的。对处于不可接近位置的关键零部件（半轴）的疲劳损伤实施了声发射监测。基于对模拟测试信号的分析,提出信号数据的预处理原则,提高了数据的信噪比。声发射信号特征参数的趋势分析和关联分析方法,充分反映了关键零部件的疲劳损伤过程,采用声发射实时监测飞机关键零部件的疲劳损伤是可行的。     

活塞杆疲劳裂纹声发射监测的实验研究

介绍声发射技术用于活塞杆疲劳裂纹的监测研究,分析声发射信号与活塞杆疲劳裂纹扩展过程的关系。通过实验结果表明,采用声发射技术可以对活塞杆疲劳裂纹进行监测,证明声发射技术在活塞杆监测上的可行性。     

某型飞机飞行载荷疲劳试验过程中的声发射监测

介绍了某型飞机全尺寸机体飞行载荷疲劳试验过程中对关键部件(包括不可接近部件)疲劳损伤的声发射(AE)实时监测技术。在强冲击、高振动背景下,利用基于时间、空间、幅度或能量滤波等多种信号处理方式,对预处理后的AE信号以趋势分析为主,多参数分析综合验证,另辅以其它方法(包括波形分析),对一些关键部位的健康状态进行AE实时在线监测。成功预报了机翼对接区域某螺栓孔夹层裂纹的萌生,为保证机体飞行载荷疲劳试验顺利进行起到了重要作用。     

基于超声相控阵的耐候钢接头疲劳裂纹动态监测

借助超声相控阵技术对耐候钢对接接头开展疲劳失效过程动态监测. 基于超声波探头的信号特征,研究其扇形扫描反射过程,建立实时扫查方案, 并对10 mm厚的耐候钢对接接头实施实时监测.结果表明,当疲劳寿命为5 × 104次时,相控阵检测到多个裂纹从对接接头焊趾部位萌生,并沿着板厚扩展,当疲劳寿命超过3.5 × 105次时,裂纹开始快速扩展. 与疲劳试验断口对比发现,基于相控阵检测得到的裂纹尺寸与试验结果基本一致,验证了相控阵裂纹动态检测的准确性. 根据裂纹深度a、裂纹长度2c与循环次数N关系,明确了裂纹动态演化行为,并获得中厚板耐候钢对接接头表面裂纹的扩展演化规律.     

飞机主承力构件疲劳裂纹萌生和扩展的声发射评价

讨论了利用声发射(AE)监测飞机关键部位疲劳裂纹形成和扩展的意义、可行性以及应当注意的问题.提出利用多参数识别和相关技术从高背景噪声中获取裂纹扩展所产生的声发射信号,并曾在疲劳试验过程中多次成功预报了飞机一些主承力构件的疲劳裂纹萌生和扩展.     

铝合金疲劳裂纹扩展声发射监测

采用声发射(acoustic emission,AE)技术对7N01铝合金单边缺口三点弯曲试样不同应力比、不同峰值载荷下疲劳裂纹扩展过程中声发射信号进行了监测,建立了裂纹扩展速率、声发射计数(count)与应力强度因子之间的关系.结果表明,大部分的声发射信号主要产生于疲劳循环载荷的低应力阶段,这主要是低应力阶段的声发射活动主要与裂纹尖端的塑性变形和裂纹闭合现象有关,声发射计数与应力强度因子之间呈指数增长的关系.基于所建立的声发射计数率与裂纹扩展速率的关系,可以预测疲劳损伤结构的剩余寿命.     

某型飞机起落架收放试验过程中疲劳损伤的声发射监测

介绍了飞机起落架收放试验过程中其附属零部件疲劳损伤的声发射实时监测。在强冲击振动背景噪声下，采用声发射信号参数的趋势分析和相关分析方法，实现了对于多目标、动态对象的实时监测并成功地监测出作动筒泄漏故障和铰链磨损故障。所用方法具有简单、直观、快速和实时性好的特点，可供后续的全机疲劳试验过程中声发射信号处理或类似高背景噪声环境下的声发射监测技术提供借鉴。     

An arrayed uniform eddy current probe design for crack monitoring and sizing of surface breaking cracks with the aid of a computational inversion technique

This study demonstrates that eddy current testing can be an effective method for monitoring the growth of surface breaking cracks with the aid of computational inversion techniques. A uniform eddy current probe with 23 arrayed detectors was designed, and pseudo monitoring tests were carried out to measure signals due to six mechanical fatigue cracks introduced into type 316L austenitic stainless steel plates. In the test the position of the probe was fixed to simulate monitoring. The depths of the cracks were evaluated using a computational inversion method developed on the basis of k-nearest neighbor algorithm. The depths of the mechanical fatigue cracks whose actual depths were 1.1, 2.1, 3.1, 5.5, 6.7, and 8.5 mm were evaluated to be 0.9, 1.9, 3.8, 4.3, 7.0, and 5.7 mm, respectively. Additional simulations were conducted to demonstrate the stability of the method.     

防喷器壳体材料疲劳试验的声发射信号分析

根据新防喷器声发射检测遇到的数据难分析、难评定等问题,针对防喷器壳体材料进行多种疲劳试验,在试验过程中全程采集声发射信号数据。通过对比不同的试验数据,分析出防喷器壳体材料中缺陷扩展和典型干扰的信号特征,以及材料在疲劳过程中声发射信号特征的变化趋势。并且把这些分析结果应用到新防喷器的检测中,检测证明整个分析非常正确。     

On-line monitoring of fatigue cracks using ultrasonic surface waves

During the last decade many techniques were developed to detect fatigue cracks, and estimate their location and size. Unfortunately, most of the currently available nondestructive testing methods are off-line: the operational (or fatigue) loading and the inspection are considered as two distinct stages. Mostly, the loading should be released before inspection can take place, and sometimes the device under test even has to be disassembled. In this article, an experimental methodology based on ultrasonic surface waves will be developed to continuously inspect a structure during its operation. The proposed method uses spectral information of transmitted surface waves at several working points of the operational load. Simple statistical indicators of the transmitted wave energy during loading are introduced in order to be able to monitor the structural health on-line. As a validation experiment, a propagating fatigue crack in a sinusoidally loaded beam will be considered. In addition, a comparison with an off-line method is made, showing that the on-line method is also much more sensitive.     

Cold hole expansion effect on the fatigue crack growth in welds of a 6061-T6 aluminum alloy

Compact test specimens were extracted from a 6061-T6 aluminum alloy welded plate with a thickness of 9 mm to analyze the cold hole expansion effect on fatigue crack growth tests conducted in mode I cyclic loading. At R = 0.1, a sharp crack in base metal, weld metal and heat affected zone was propagated from 17 to 24 mm. The fatigue crack growth at 24 mm (α = a/W = 0.3) was delayed by drilling a hole at the crack tip and applying a cold hole expansion of 4.1%. The residual stress fields due to cold hole expansion were determined with the finite element method. The fatigue crack growth testing was continued up to a crack length of 35 mm (α ∼ 0.43) at the same R, and crack opening displacements of the post-expansion crack were also determined with the finite element method. The results were expressed in terms of crack length versus number of cycles, as well as, fatigue crack growth rate as a function of applied and effective stress intensity factor range. The cold hole expansion contributed to delay the fatigue crack growth in base metal, and to a lesser extent in the weld metal and heat affected zone. A crack closure effect was determined by means of load versus crack opening displacement curves of the post-expansion crack, which was, completely or partially closed, in welded zones with compressive residual stress fields. The fracture surfaces of each welded zone were analyzed to elucidate the crack nucleation zone and its relation with the residual stress field. In all cases the crack was initiated at the surface of the specimen where the residual stresses were positive.     

某型飞机疲劳试验过程中关键结构的AE监测

介绍了某型飞机疲劳试验过程中的关键结构的声发射检测技术。根据监测的实时性要求,采用参数趋势分析,辅以幅值滤波和空间滤波技术对信号进行实时处理,特别是在空间滤波技术中,采用损伤区域内事件数占总事件数的比例来分析裂纹的发展状况,并以相关参数的变化趋势进行论证,取得了满意结果。成功预报了右外翼三墙处某螺栓孔裂纹的萌生,为试验的顺利进行起到了重要保障。     

开缝衬套挤压工艺影响TA15孔疲劳增益研究

采用对比疲劳试验方法,研究了相对挤压量、终铰参量、衬套开缝放置角度等工艺参数和特征对开缝衬套挤压TA15钛合金连接孔疲劳增益的影响。结果表明,开缝衬套挤压技术可有效提高TA15钛合金孔结构疲劳强度,延长其疲劳寿命；相对挤压量越大,孔挤压疲劳增益越大,但是TA15钛合金对挤压量非常敏感,微小的相对挤压量波动会导致显著的疲劳增益波动；在完全去除开缝衬套在孔壁遗留的材料凸脊前提下,0.190 mm和0.065 mm两种单边终铰参量对TA15孔结构挤压疲劳增益有明显影响,0.190 mm单边铰削量时挤压疲劳增益更大,而非终铰参量越小越好；在s_max=400 MPa,R=0.1疲劳载荷条件下,衬套开缝与试样最窄截面平行放置,仍能够获得明显的疲劳增益,但相对于与试样与最窄截面呈90°放置,疲劳增益会略有下降,建议在实际孔挤压操作中,衬套开缝尽量避开最窄截面放置。     

Effect of welding parameters on mechanical and microstructural properties of AA6056 joints produced by Friction Stir Welding

The effect of processing parameters on mechanical and microstructural properties of AA6056 joints produced by Friction Stir Welding was analysed in the present study. Different samples obtained by employing rotating speeds of 500, 800 and 1000 rpm and welding speeds of 40, 56 and 80 mm/min were produced. The mechanical properties of the joints were evaluated by means of microhardness (HV) and tensile tests at room temperature. Fatigue tests on the welds were carried out by using a resonant electro-mechanical testing machine under constant loading control up to 250 Hz sine wave loading. The low cycle (LCF) and high cycle (HCF) fatigue tests were conducted in the axial total stress-amplitude control mode with R = σ_min/σ_max = 0.1, for all the welding and rotating speeds used in the present study. It was observed that the specimens welded at 56 mm/min showed the best behaviour in the low cycle regime. The microstructural evolution of the material was analysed by optical observations of the welds cross sections.