16MnR／0Cr18Ni9Ti复合钢板损伤与断裂过程的声发射特性试验

研究了16MnR／0Cr18Ni9复合钢板在承受拉伸载荷时的损伤与断裂行为。给出了损伤类型、阶段和恒载等关键声发射特性,发现了不同损伤类型表现出不同的声发射特性。损伤与断裂的不同阶段,可用声发射信号的几种关联图进行区分。     

声发射技术在三维编织复合材料测试中的应用研究

论述了声发射技术在三维编织复合材料拉伸过程损伤测试中的应用，结果表明，通过采集声发射参数可以描述复合材料在载荷情况下的内部变形的损伤机制。系统采用小波分析方法对声发射信号进行噪声处理，用频谱图描述复合材料的内部损伤变形特征，为复合材料的力学性能分析和材料复合工艺的改善提供理论基础。     

飞机复合材料拉伸过程损伤的声发射特性分析

利用声发射技术开展对拉伸载荷下飞机复合材料T型结构件的损伤发生过程研究,对复合材料试件拉伸载荷下损伤产生过程的机理进行了初步探讨。采用参数分析方法对拉伸试验采集到的声发射信号进行分析,得到该T型结构件拉伸过程中基体开裂、分层、纤维断裂至完全丧失承载能力时的声发射信号特征及其对应的载荷。结果表明,声发射技术能够准确预测复合材料T型结构件拉伸载荷下的损伤发生过程,可为该类结构件的检测提供参考。     

C/SiC复合材料拉伸过程的声发射研究

利用声发射（AE）技术对C／SiC复合材料试样拉伸试验过程进行动态监测。通过声发射多参数分析法对拉伸过程中的声发射累计能量和平均持续时间随载荷或时间的变化进行了综合分析；同时对拉伸过程中典型AE信号的频率特征进行了分析，揭示了C／SiC复合材料拉伸损伤的演化过程及规律，给出了材料拉伸损伤发展的不同阶段以及各阶段损伤类型。通过声发射累计能量随载荷变化的斜率突变定义了材料临界损伤强度。     

2D-C/SiC陶瓷基复合材料拉伸试验的声发射特性

对2D-C/SiC陶瓷基复合材料试样在室温条件下单调拉伸试验和循环拉伸试验的损伤声发射信号进行研究,利用无监督层次聚类分析方法对单调和循环拉伸试验的声发射信号进行损伤模式识别,得出了两种拉伸试验下试样都有相同的损伤分类。对每次单调加/卸载试验分别进行应力和声发射信号分析,得到了在循环加载区间和卸载区间试样的损伤情况。对比分析两种拉伸试验的声发射信号,得到两次试验中首次加载相同应力时,两个试样有同一种类的声发射损伤信号,从而说明循环加载对试样的主要损伤影响较小。     

复合材料拉伸过程的声发射特性研究

为了研究16MnR／0Cr18Ni9Ti复合材料断裂过程的声发射特性,可以利用声发射技术对16MnR／OCr18Ni9Ti复合材料试件的拉伸过程进行全程监测。研究表明,材料拉伸断裂过程中,声发射信号丰富明显,可测性良好,并且不同破坏阶段的声发射信号具有不同的特征。通过对不同拉伸阶段声发射信号的参数分析,可以了解材料不同变形阶段的声发射特性,并据此来分析材料损伤的发生、发展及演变过程。与传统的力学试验方法相比,声发射技术在研究复合材料断裂过程方面具有明显的优势。     

高温环境下钛合金拉伸损伤声发射试验

针对高温环境钛合金损伤在役监测需要,提出了采用声发射技术对其进行实时动态监测。通过模拟真实机匣内高温环境,对TA15钛合金进行高温拉伸损伤力学声发射监测试验。确定了钛合金为波导杆的材料,将焊接了波导杆的钛合金试件进行不同拉伸速率下的高温拉伸试验。试验结果表明,不同温度下TA15钛合金的力学性能呈现有规律的变化,声发射技术可以成功地监测和表征钛合金的损伤演变,计数能够明显地反映出高温下拉伸试验的不同力学阶段。     

T700／环氧复合材料拉伸损伤机理声发射实验研究

以声发射技术为手段,对T700／环氧复合材料试样进行了拉伸损伤实验,依据其损伤过程和声发射特性,发现在加载初期主要发生的是基体、界面的损伤;加载的后期微损伤发生的数量不多,但是损伤性质严重,其主要是碳纤维损伤;同时拉伸过程声发射信号存在峰值和”平静期”,且重复性很强。     

胶合板拉伸过程中的声发射特征

针对传统的力学试验方法对胶合板破坏过程的表征不足,提出了用声发射检测技术全程监测胶合板拉伸破坏过程。试验表明,材料的损伤破坏具有阶段性,不同阶段的声发射信号特征有明显的区别。研究发现声发射特征参数能够表征材料受载过程中的损伤演化规律和损伤类型,能直观地反映材料的损伤特征。因此,声发射检测技术可作为材料测试、质量评定的有效手段,也是传统力学方法的有益补充。     

不同拉伸速度下的碳布/环氧树脂复合材料声发射评价

采用电子万能实验机控制,分别以1、2、5 mm/min的加载速度对碳布/环氧树脂复合材料进行拉伸,在拉伸过程中用声发射检测设备采集拉伸过程中产生的声发射信号,建立采集的声发射信号特征与时间、载荷的相关图,通过对相关图的分析,判断碳布/环氧树脂材料在拉伸过程中的损伤情况,并结合相关图分析不同拉伸速度对碳布/环氧树脂复合材料的影响,判定碳布/环氧树脂复合材料的临界失效载荷。结果表明:声发射检测可用于评价复合材料加载过程中的损伤情况,可将最大承载载荷的70%～80%作为碳布/环氧复合材料的失效参考载荷。     

碳纤维增强树脂基复合材料层压板冲击损伤模式的试验研究

针对两种典型的碳纤维增强树脂基复合材料（T300/5405和T700/5428）层压板进行不同能量水平的落锤冲击试验,通过对冲击后试样的外部损伤形态、内部损伤情况等的检测以及纤维/树脂微观界面剪切强度的检测,讨论了两种碳纤维复合材料层压板的冲击损伤模式。试验结果表明,当冲击载荷达到一定程度时:在T300/5405体系中,由于T300纤维拉伸强度相对较低,纤维所受作用率先达到破坏载荷,因而冲击损伤表现出以穿透性为主的破坏特征;在T700/5428体系中,由于T700纤维拉伸强度较高,尽管其微观界面剪切强度略高,但是由于冲击载荷未使纤维达到破坏载荷时已使T700/5428界面率先遭到破坏,因此表现出以分层为主的破坏特征。     

Experimental investigation of drilling damage and stitching effects on the mechanical behavior of carbon/epoxy composites

The main purpose of composite materials drilling is the need to put together different parts of a structure, in aeronautics for example. Machining generates damages which affect mechanical properties and have to be taken into account during manufacturing process. The objective of this study is to experimentally analyze the influence of drilling on a carbon/epoxy composite, to investigate the relationships among damages, cutting forces, mechanical properties of the drilled specimens and crack propagation. Stitching and a range of spindle speed and feed have been tested when drilling with a classic twist drill. The effect of each parameter has been assessed in terms of thrust force, moment (during machining) and defects, and then linked to mechanical test results. Experimental results have shown significant influences of feed and composite configuration on delamination. Furthermore, cyclic tensile tests have shown that reducing damage and using stitching help increasing tensile strength.     

碳/环氧复合材料拉伸损伤声发射Felicity效应研究

为研究碳/环氧复合材料的Felicity效应,制定了碳/环氧复合材料[0]单向板拉伸试验方案,结合试验数据探讨了复合材料的Felicity比值变化规律。结果表明,复合材料的Felicity比值随损伤程度的增加呈下降趋势,说明利用Felicity比值可以较有效地评定复合材料损伤程度。     

Multiscale modeling of failure in metal matrix composites

A multiscale approach to composite failure, in which detailed information on small-scale micromechanics is incorporated approximately yet accurately into larger-scale models capable of simulating extensive damage evolution and ultimate failure, is applied to the deformation and failure of a Ti–matrix composite. The composite is reinforced with SiC fibers under conditions of matrix yielding and interfacial sliding via Coulomb friction. Specifically, a fully three-dimensional finite element model is employed to investigate the load transfer from broken to unbroken fibers as a function of applied stress and interface friction coefficient. With a von Mises matrix yield criterion, constraint effects permit the matrix to carry some of the transferred load near the fiber break, a feature not captured in previous composite models. The single-break results for stress concentrations are then used as the discrete Green's functions for load transfer in the full composite, and the predicted load transfer around a seven-fiber-break cluster is shown in good agreement with finite element results. The Green's function model is then used to predict overall damage evolution and composite failure for an IMI-834 Ti/SCS-6 SiC system for various interface friction coefficients. The composite tensile strength is rather insensitive to the friction coefficient and, for values of μ comparable to those measured experimentally, the predicted tensile strength is in excellent agreement with the measured value. Analytic models for scaling of the tensile strength to very large sizes are then shown to agree well with strengths obtained from simulations. These results suggest that the hierarchical coupling approach used here may be useful for approaching a wide variety of damage and failure problems in fiber composites.     

微动工况对疲劳裂纹扩展影响的数值模拟研究

文章研究了不同微动工况对疲劳裂纹扩展的影响,在Hypermesh中建立带有预置裂纹的有限元模型,把单元和节点信息导入Matlab,利用向量式有限元法研究薄板在恒定拉载荷、恒定压载荷、拉压载荷和交变载荷作用时的裂纹扩展规律。研究表明,恒定拉载荷和交变载荷作用下,裂纹开口形状和程度大致相同;裂纹在恒定压载荷作用下发生交错;在拉载荷作用时裂纹开口幅度达到最大值,拉压载荷作用下裂纹扩展开口幅度最小,其次,在交变载荷下裂纹扩展速度最快,拉载荷和压载荷作用下裂纹扩展最慢。     

Carbon Fiber Reinforced Smart Laminates with Embedded SMA Actuators—Part I: Embedding Techniques and Interface Analysis

Up to now one of the main limits for a large use of shape memory alloys (SMA)-based smart composite structures in the aerospace industry is the lack of useful numerical tools for design. Moreover, technological aspects still need a more detailed investigation. This paper shows how to overcome issues regarding embedding of NiTiNOL wires in carbon fibre/epoxy laminates. A crucial aspect of those structures is related to the load transfer capabilities between the SMA actuators and the host material during their activation. Embedding techniques developed for taking into account problems like thermal and electrical compatibility between actuators and host material and passive/active invasivity are reported in this paper. Simple smart laminates with several actuators were manufactured, tested, and deeply analyzed. In order to characterize the interface in the real operative conditions, pull-out tests were conducted on NiTiNOL wires embedded in composite fiber laminates. The results were compared to standard experiments on wires embedded in pure epoxy resin blocks.     

制孔分层损伤对CF/PEEK复合材料拉伸性能和表面应变分布的影响

目的 研究钻削制孔表面分层损伤与拉伸载荷下开孔碳纤维增强聚醚醚酮（CF/PEEK）复合材料表面应变分布的相关性。方法 通过对CF/PEEK复合材料层合板进行钻削制孔实验,分析不同进给速度对钻削温度、钻削轴向力、制孔出口表面分层和孔壁表面损伤的影响。采用数字图像相关技术（DIC）和力学实验相结合的方法,研究分层损伤程度对开孔CF/PEEK复合材料层合板拉伸性能和表面应变分布的影响。使用扫描电镜观测开孔试件的断裂形貌,分析开孔试件受拉伸载荷时的破坏模式。结果 随着进给速度的增加,钻削温度降低,钻削轴向力提高,出口表面分层和孔壁损伤程度加剧。随着分层损伤程度的增加,层合板的拉伸强度呈现出降低的趋势,试件的拉伸强度从558.4 MPa降低到525.63 MPa,降低了5.87%。在中应力和高应力状态下,试件x方向的最大负应变随着分层损伤程度的增加而增加。在高应力状态下,试件y方向的最大正应变随着分层损伤程度的增加而增加。试件的断裂方式主要是基体开裂、分层和纤维撕裂,断口有纤维脱落和纤维拔出,垂直于载荷方向的纤维破坏模式为剥离破坏,与载荷方向一致的纤维破坏模式为拉伸破坏。结论 钻削制孔表面分层损...     

SiC纤维表面去碳处理对PIP-SiCf/SiC复合材料力学性能以及界面影响

采用强度测试、SEM、HRTEM等分析测试手段对纤维表面去碳前后SiC纤维强度、复合材料力学性能、纤维表面形貌、复合材料断口形貌以及复合材料界面特征进行分析表征.结果表明,去碳处理后,纤维表面的固有缺陷暴露出来,纤维强度下降约15%,但由其制备的复合材料强度下降只有原纤维制备复合材料的1/6;复合材料断口非常平整,纤维...     

Mechanistic study of stress corrosion cracking of carbon steel in ethanol

Mechanistic study of stress corrosion cracking of carbon steel in fuel‐grade ethanol was made using slow strain rate testing and constant tensile load testing at yield strength stress level of the steels. Characterization of the fracture surface was made using SEM and SEM–EDS. Selective dissolution of ferrite from pearlite phase was observed. Crack initiation took place preferably from pearlite phase. Corroded zones consisting of crystallographic pits were found from fracture surfaces.