含预制裂纹L形梁柱试件动态断裂过程

针对含预制裂纹L形梁柱试件，为研究预制裂纹动态扩展的力学特征及其对梁柱试件破坏模式的影响，采用数字动态焦散线实验系统，对距节点核心区不同距离l处含有预制裂纹的试件进行落锤冲击实验，得到预制裂纹的扩展轨迹、速度、动态应力强度因子的变化规律。结果表明，l值增大，扩展裂纹在梁下边缘的贯通点与预制裂纹的夹角逐渐增大，曲裂程度变大。裂纹扩展速度随着l的增大振荡性增强，裂纹扩展平均速度逐渐降低。l值为2 mm时，裂尖表现为Ⅰ型断裂，l值增大，裂尖受到剪应力作用增强，Ⅰ型动态应力强度因子减小，Ⅱ型动态应力强度因子增大，断裂逐渐转变为Ⅰ-Ⅱ复合型。     

垂直裂缝在砂泥岩层理界面上拐折扩展特性研究

首先以大庆油田薄差油藏的砂泥岩储层力学参数为基础,根据相似原理,制备了砂泥岩相似材料试件。然后通过三点弯曲实验构建了Ⅰ型裂缝扩展,并采用数字散斑相关方法,获得了裂缝扩展过程中试件表面散斑场的变化规律。由此给出了界面位置处裂尖的应力奇异性阶数及应力强度因子,了解了材料强度差异对裂缝在界面扩展特性的影响。分析表明,当垂直裂缝从高强度材料一侧扩展时,界面的应力奇异性阶数大,界面的应力集中效应高,KⅡ/KⅠ比值小,裂缝拐折程度小,反之亦然。     

CTS试件中复合型疲劳裂纹扩展

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.     

基于有限元方法的航空发动机叶片应力强度因子计算

为研究叶片裂纹尖端的应力奇异性，以某型航空发动机压气机叶片为例，利用有限元方法研究了叶片裂纹尖端应力强度因子的计算方法，并研究了旋转叶片振动状态下裂尖应力强度因子随裂纹长度的变化规律。建立计算模型时，在裂纹尖端划分了三维奇异单元，在裂尖外围划分了过渡单元。计算结果表明：研究旋转叶片振动状态下的裂尖应力奇异性，仅利用I型应力强度因子就具有足够的精度；对于同一裂纹，绝大多数情况下叶盆面应力强度因子大于叶背面应力强度因子，故研究叶片应力强度因子时只需研究叶盆应力强度因子即可；随着裂纹扩展，叶盆面I型应力强度因子不断增大。本文的研究方法及结论为进一步研究叶片的裂纹扩展规律及损伤容限奠定了基础。     

可压缩粘弹性材料Ⅱ型动态扩展裂纹尖端场

为了研究粘性效应作用下的动态扩展裂纹尖端渐近场,建立了可压缩粘弹性材料II型动态扩展裂纹的力学模型,推导了可压缩材料Ⅱ型动态扩展裂纹的本构方程.在稳态蠕变阶段,弹性变形和粘性变形同时在裂纹尖端场中占主导地位,应力和应变具有相同的奇异量级r-1/(n-1).通过渐近分析求得了裂纹尖端应力、应变和位移分离变量形式的渐近解,并采用打靶法求得了裂纹尖端应力、应变和位移的数值结果,给出了应力、应变和位移随各种参数的变化曲线.数值计算表明,弹性变形部分的可压缩性对Ⅱ型裂尖应力场影响甚微,而对应变场和位移场影响较大.裂尖场主要受材料的蠕变指数n和马赫数M的控制.当泊松比ν =0.5时,可以退化为不可压缩粘弹性材料Ⅱ型动态扩展裂纹.     

爆炸载荷下板条边界斜裂纹的动态扩展行为

为了研究爆炸应力波作用下板条边界斜裂纹的动态扩展行为,首先分析了爆炸应力波在含边界斜裂纹板条中的传播,其次采用动态焦散线实验方法,进行了爆炸载荷下板条边界斜裂纹扩展规律的实验研究.研究结果表明,爆炸应力波作用下,板条试件边界斜裂纹的扩展过程中,裂纹扩展速度、扩展加速度和裂尖动态应力强度因子随时间波动变化,扩展速度最大值...     

不同韧性金属扩展裂纹尖端Gao—Hwang奇异场的实验研究

用云纹法和光学空间滤波技术,测量了六种不同应变硬化指数(n)的铝和铜金属材料双边裂纹,单向拉伸试件的扩展裂纹尖端三维位移场.利用试验得到的位移场,分析了位移奇异性,并与G-H 理论解进行了比较.由试验的位移场数据确定了理论解中两个待定常数A 和ε_■,给出了Ⅰ型、平面应力、幂硬化材料,扩展裂纹尖端奇异场的比较形式.在理论与试验位移场相差±10%的误差范围内,确定了试验的G-H 奇异场主导区范围、形状,并对结果进行了分析.试验表明:扩展裂纹尖端存在[ln(A/r)]~■奇异主导区.在本试验应变硬化指数为n=3.5→14的六种材料范围内,这个主导区形状由蝶形发展到扁圆或圆形.G-H 奇异主导区的尺寸和形状与材料、试件几何尺寸、外载形式有关.在G-H 场内部存在着三维变形区,裂纹尖端断裂过程区在此三维变形区内.随着外载荷不断增加,裂尖三维变形区内将出现典型的韧性损伤现象:首先在晶界或二相夹杂处,出现孔洞,然后孔洞逐渐长大,汇合,导致宏观裂纹扩展.载荷比较低时,在G-H 场外边还将有弹性场存在,随着载荷增加,G-H 场也在向外扩大.     

冲击载荷下含空孔三点弯曲梁的动态断裂行为

为得到圆孔缺陷对运动裂纹扩展过程的影响规律,采用动态焦散线实验方法进行模型实验,研究了冲击载荷下含空孔三点弯曲梁的动态断裂行为。研究结果表明:空孔对裂纹扩展有极大的阻碍作用,在一定范围内,空孔直径越大,阻碍作用越明显。裂纹扩展到空孔附近时,扩展速度会下降。裂纹在空孔上部再次起裂后,最大扩展速度远远大于裂纹与空孔贯通前的最大扩展速度。裂纹扩展至空孔附近时,裂纹尖端动态应力强度因子KdⅠ和KdⅡ均会下降。裂纹在空孔上部再次起裂后,裂尖的应力强度因子KdⅠ和KdⅡ均大于裂纹与空孔贯通前裂尖的KdⅠ和KdⅡ。在整个扩展过程中,裂纹尖端的动态应力强度因子KdⅡ远小于KdⅠ,说明KdⅠ在裂纹扩展过程中起主要作用。     

I型裂纹尖端约束应力区模型及其解析解

考虑了I型裂纹尖端损伤区域内三种不同的约束应力分布形式,即右三角分布形式(情况A)、均匀分布形式(情况B)、左三角分布形式(情况C),并采用复变函数方法求得了应力强度因子与裂纹张开位移的解析解;在此基础上,通过数值计算得到了应力强度因子和裂纹张开位移随约束应力区长度、约束应力大小以及分布形式的变化规律。研究结果表明:随裂尖材料损伤程度的增加,裂尖损伤区内约束应力减小,应力强度因子和裂纹张开位移增大;约束应力的分布形式对应力强度因子和裂纹张开位移有显著影响;相对于其他区域,约束应力对裂纹尖端区域裂纹张开位移的影响较大。然而,对于裂尖损伤区域的形成与作用荷载、材料性质、构件几何尺寸之间的关系,还需要进行更为深入的研究。     

基于三维数字图像相关的低周疲劳试验研究

为研究三点弯曲试件在低周疲劳载荷作用下,裂纹萌生、扩展与循环周期间的关系以及裂纹区域位移与应变场的变化规律,由万能试验机及数字循环加载控制系统对三点弯曲试件施加循环周期载荷。两组CCD和试验机同步采集记录系列交变载荷作用下试件裂纹周边区域的数字散斑图像及载荷,应用三维数字图像相关(Digital image correlation,DIC)技术计算裂纹尖端区域的位移及应变场。通过对裂尖区域位移、主应变等的分析,获得裂纹扩展长度与扩展率等的变化规律。     

Evaluation Using Digital Image Correlation of Stress Intensity Factors in an Aerospace Panel

The fracture behavior of a crack propagating in a large (4.8 m × 1.4 m) aircraft panel was investigated quantitatively by experiment for the first time using digital image correlation. Mixed mode (I+II) stress intensity factors were evaluated using a methodology, which combined digital image correlation with the multi-point over-deterministic method to fit displacement field equations to the experimental data from around a crack tip. More than 800 images were taken during a 10-minute time period as the fracture of the panel occurred under monotonic loading. It was observed that the crack propagated through the skin of the panel at a relatively low speed, with an average crack tip velocity of 0.014 mm/s, and changed its propagation direction at particular points due to the reinforcement of the structure. In the later stages of the test, substantial shear lips were observed indicating a state of plane stress as would be expected in a thin, wide panel and the size of the plastic zone increased substantially. The value of the mode I stress intensity factor obtained from the measured displacement fields initially increased linearly to around 50 MPa√m (K_Ic = 37 MPa√m) and afterwards non-linearly reaching 300 to 400 MPa√m for crack extensions of the order of 100 mm. It is proposed that these high values of stress intensity factor do not represent an unrealistically high material fracture toughness but rather are indicative of the high resistance to crack growth of the structural assemblage of ribs, stringers and hole reinforcements in the panel which allow the skin to sustain a strain level that would otherwise cause unstable crack growth. Digital image correlation is demonstrated to be particularly powerful in elucidating this structural behavior.     

Study of a Crack at a Fastener Hole by Digital Image Correlation

In this work the efficacy of using digital image correlation to determine stress intensity factors for a crack emanating from a fastener hole has been investigated. To this end a fatigue crack was grown in pure mode I from a 50 mm diameter hole in an Al 7010 alloy plate test-piece. This crack was then loaded elastically under several combinations of mixed mode (I + II) displacements. In each case, images of the sample surface before and after the deformation were recorded using a high resolution digital camera. The surface preparation consisted only of scratching the surface lightly with silicon carbide abrasive paper. The crack location and resulting displacements were then calculated using digital image correlation. The analytical displacement fields for a traction free crack under arbitrary loading conditions based on the Muskhelishvili’s complex function approach were fitted to the experimentally measured displacement fields and the mixed mode stress intensity factor was determined in each case. Good agreement with the nominal applied values was obtained. The uncertainty of the crack tip position has a major influence on the accuracy of the stress intensity factors and so the Sobel edge finding filter was successfully applied to experimental displacement fields to establish precisely the crack tip location. This paper was presented at the 2007 SEM Congress held in Springfield, Massachusetts, USA     

Experimental analysis of crack tip fields in rubber materials under large deformation

A three-nested-deformation model is proposed to describe crack-tip fields in rubber-like materials with large deformation.The model is inspired by the distribution of the measured in-plane and out-of-plane deformation.The inplane displacement of crack-tip fields under both Mode I and mixed-mode(Mode I-II) fracture conditions is measured by using the digital Moire’ method.The deformation characteristics and experimental sector division mode are investigated by comparing the measured displacement fields under different fracture modes.The out-of-plane displacement field near the crack tip is measured using the three-dimensional digital speckle correlation method.     

一种基于SHTB的Ⅱ型动态断裂实验技术

冲击剪切载荷作用下动态断裂韧性的测定是材料力学性能和断裂行为研究中重要组成部分.为了测定材料的Ⅱ型动态断裂韧性,许多学者采用不同的试样与实验方法进行了实验,但限于实验条件,裂纹断裂模式往往是I+Ⅱ复合型,而不是纯Ⅱ型,因而不能准确测得材料的Ⅱ型动态断裂韧性.鉴于此,本文基于分离式霍普金森拉杆(split Hopkinson tension bar,SHTB)实验技术,提出一种改进的紧凑拉伸剪切(modified compact tension shear,MCTS)试样,通过夹具对MCTS试样施加约束,从而保证试样按照纯Ⅱ型模式断裂.采用实验-数值方法对MCTS试样动态加载过程进行分析,将实验测得的波形输入有限元软件ANSYS-LSDYNA,得到了裂纹尖端应力强度因子-时间曲线,并与紧凑拉伸剪切(compact tension shear,CTS)试样进行了对比.同时采用数字图像相关法进行了实验,验证了有限元分析结果.结果表明,MCTS试样在整个加载过程中K_I K_Ⅱ,裂纹没有张开;而CTS试样在同样的加载过程中K_IK_Ⅱ,出现裂纹张开现象.这说明MCTS试样能够准确地测定材料的Ⅱ型动态断裂韧性,为材料动态力学测试提供了一种有效的实验技术.     

三点弯曲试样动态应力强度因子计算研究

利用Hopkinson压杆对三点弯曲试样进行冲击加载,采集了垂直裂纹面距裂尖2mm和与裂纹面成60°距裂尖5mm处的应变信号。根据裂尖附近测试的应变信号计算试样的动态应力强度因子,并与有限元计算结果进行比较,结果表明由于裂尖有一段疲劳裂纹区,通过裂尖附近应变信号来计算动态应力强度因子时,如果裂尖位置确定不准及粘贴应变片位置不够准确对计算结果将带来很大影响。因此利用应变片法计算动态应力强度因子时,为了获得更准确的计算结果,在实验后应对试件裂纹面进行分析测量,重新确定裂尖位置,必要时需对应变片至裂尖距离进行修正后再计算动态应力强度因子值。     

复合材料断裂力学参量的实验测定

本文采用三维云纹干涉仪同步测量含裂纹复合材料弯曲板的面内位移场及离面位移场，并对离面位移场云纹图进行计算机自动采集和处理，编制了云纹数字图像处理软件。文中推导了正交异性复合材料弯曲问题的离面位移场表达式，得到了弯曲板裂纹尖端位移w与应力场强度因子K1的关系式。通过实测位移，结合裂尖位移场推导出应力强度因子K1值。     

APPLICATION OF THE DIGITAL MOIRE METHOD IN FRACTURE ANALYSIS OF A CRACKED RUBBER SHEET

This paper deals with the mode I crack problem of a cracked rubber sheet under plane stress condition using the delicate digital moire technique. Through the four step phase-shifting method of automated fringe analysis, the displacement fields in the Cartesian coordinate system are given. By the coordinate-transform equation, the radial and circular displacement distributions in the polar coordinate system are obtained. The displacement isoline distributions and displacement vector distributions near the crack tip are discussed. The strain isoline distributions near the crack tip are also analyzed in this paper. Finally, the distribution rules for the mechanical fields near the crack tip are discussed with the sector division method.     

扩展数字图像相关方法中裂尖位移函数的表征研究

探寻适用于扩展数字图像相关方法(X-DIC)的裂纹尖端位移函数,对于提高该方法在裂尖测试精度方面具有重要意义。本文基于断裂力学裂纹尖端位移场函数,进行主导项影响分析,并探究裂尖位移函数中各项及其组合项对位移场表征的贡献程度及对测试精度的影响。通过对I型、II型及混合型裂纹进行测试,发现各项及其组合项在不同裂纹类型测试中的影响有着较大区别,从而得出在X-DIC测试计算中影响裂尖位移场表征的主导项。最后,应用上述研究成果对某航空超硬铝合金的单边裂纹进行拉伸测试。     

基于DIC的爆炸加载下脆性材料裂纹扩展规律的试验研究

通过数字图像相关法（DIC），应用PMMA对爆炸加载条件下脆性材料的裂纹扩展规律进行了试验研究。基于对称性试验模型，实现了裂纹尖端位置和应变场信息的同步记录。以此为基础，通过对比分析获知，主应变场应变值最大点不能作为裂纹尖端的判断依据。并以动态裂纹扩展速度为参量，应用断裂动力学和最小二乘牛顿迭代法，计算出了考虑惯性效应的Ⅰ-Ⅱ混合型裂纹的应力强度因子:K_Ⅰ和K_Ⅱ值会随着裂纹扩展方向改变而发生突变；K_Ⅰ最大值为2.63 MPa·m1/2，最小值为0.89 MPa·m1/2；其整体变化趋势表明，爆炸加载条件下脆性材料裂纹扩展随能量积聚和释放呈循环阶梯式递减发展。     

Observation of Stress Field Around an Oscillating Crack Tip in a Quenched Thin Glass Plate

The variation of stress field around an oscillating crack tip in a quenched thin glass plate is observed using instantaneous phase-stepping photoelasticity. The successive images around the propagating crack are recorded by a CCD camera that is equipped with a pixelated micro-retarder array. Then, the phase maps of the principal stress difference and the principal direction are easily obtained even though the photoelastic fringes cannot be visualized. The path of the crack growth as well as the stress intensity factors and the crack tip constraint are obtained from these phase distributions. Results show that the mode I stress intensity factor and the crack tip constraint vary remarkably with the crack growth. In addition, the results show that the mode-II stress intensity factor exists even though the crack propagates smoothly.