利用ABAQUS模拟裂纹.ppt

ABAQUS平台的扩展有限元方法模拟裂纹实现1.1 扩展有限元方法（XFEM）在ABAQUS上的实现ABAQUS中XFEM的实现，两个步骤最为关键：1、选择模型中可能出现的裂纹区域，将其单元设为具有扩展有限元性质的enrichment element.2、其次重要的是选择恰当的破坏准则，使单元在达到给定的条件破坏，裂纹扩展。

在ABAQUS中模拟裂纹扩展的操作中，需要注意的是：1、在Property模块，添加损伤演化参数、破坏法则、损伤稳定性参数2、在Interaction模块，主菜单Special中创建XFEM的enrichment element对于固定的裂纹模型，采用ABAQUS/STANDARD中使用奇异渐进函数。

针对移动的裂纹问题，在XFEM中，有一种方法基于traction-separation cohesive behavior，即使用虚拟节点连续片段法进行移动裂纹建模，ABAQUS/STANDAR D 中用于计算脆性或韧性材料的裂纹初始化和扩展过程的模拟。

另外一种cohesive segments method (粘性片段方法)可用于bulk material中的任意路径的裂纹初始化模拟扩展过程，由于裂纹扩展不依赖于单元边界，在XFEM中，裂纹每扩展一次需要通过一个完整单元，避免尖端应力奇异性。

除此之外，ABAQUS为拥护提供了自定义子程序，来满足不同建模的需要。

ABAQUS/STANDARD中的任意力学本构模型均可用来模拟扩展裂纹的力学特性。

由于XFEM采用的形函数在求解过程中，很容易造成逼近线性相关，极大的增加了收敛难度，到目前为止，能够实现扩展有限元的商业软件只有ABAQUS，但是ABAQUS为了减少求解难度，做了大量简化，因此用ABAQUS 扩展有限元模拟裂纹扩展时，有一些局限[16]：1.扩展单元内不能同时存在两条裂纹，所以ABAQUS不能模拟分叉裂纹；2.在裂纹扩展分析过程中，每一个增量步的裂纹转角不允许超过90度；3.自适应的网格是不被支持的；4.固定裂纹中，只有各向同性材料的裂纹尖端渐进场才被考虑。

ABAQUS中的断裂力学及裂纹分析总结（转自simwe）（1）做裂纹ABAQUS有几种常见方法。

最简单的是用debond命令, 定义*FRACTURE CRITERION, TYPE=XXX,参数。

***DEBOND, SLAVE=XXX, MASTER=XXX, time increment=XX0,1,……......time,0要想看到开裂特别注意需要在指定的开裂路径上定义一个*Nset，然后在*INITIAL CONDITIONS, TYPE=CONTACT中定义master, slave, 及指定的Nset这种方法用途其实较为有限。

（2）另一种方法，在interaction模块，special, 定义crack seam, 网格最好细化，用collapse element模拟singularity. 这种方法可以计算J积分，应力强度因子等常用的断裂力学参数.裂尖及奇异性定义:在interaction-special,先定义crack, 定义好裂尖及方向, 然后在singularity选择：midside node parameter: 输入0.25, 然后选Collapsed element side, duplicate nodes，8节点单元对应(1/r)+(1/r^1/2)奇异性。

这里midside node parameter选0.25对应裂尖collapse成1/4节点单元。

如果midside nodes不移动到1/4处, 则对应(1/r)奇异性, 适合perfect plasticity的情况.网格划分:裂尖网格划分有一些技巧需要注意，partition后先处理最外面的正方形，先在对角线和边上布点，记住要点constraint, 然后选第三个选项do not allow the number of elements to change不准seed变化，密度可以自己调整. 最里面靠近圆的正方形可以只在对角线上布点. 也可以进一步分割内圆及在圆周上布点. 里面裂尖周围的内圆选free mesh, element type选cps6或者cpe6，外面四边形选sweep mesh, element type选cps8或者cpe8, 记住把quad下那个缩减积分的勾去掉。

abaqus混凝土裂缝计算摘要：一、引言二、abaqus软件介绍三、abaqus混凝土裂缝计算方法1.材料模型的选择2.边界条件和加载设定3.后处理分析裂缝四、结论正文：一、引言随着我国基础设施建设的快速发展，混凝土结构的工程应用越来越广泛。

在混凝土结构中，裂缝是一个常见的问题，它不仅影响美观，还可能影响结构的性能和使用寿命。

因此，对混凝土裂缝进行准确预测和控制具有重要意义。

本文将介绍如何使用abaqus软件进行混凝土裂缝计算。

二、abaqus软件介绍Abaqus是一款强大的有限元分析软件，广泛应用于各种工程领域。

它具有丰富的材料模型库，可以为用户提供多种分析功能，包括线弹性分析、非线性分析、热力学分析等。

三、abaqus混凝土裂缝计算方法1.材料模型的选择在abaqus中，混凝土的材料模型通常选择为C3D8。

此外，还需要定义混凝土的强度、弹性模量、泊松比等参数。

对于钢筋，可以选择C3D20或C3D20R模型，并定义钢筋的强度、弹性模量等参数。

2.边界条件和加载设定在建立模型之后，需要设置模型的边界条件。

对于固定边界，可以设置固定约束；对于转动约束，可以设置旋转约束。

在设置加载条件时，应根据实际工况选择合适的加载类型，如位移加载、力加载等。

3.后处理分析裂缝在abaqus中，可以通过后处理工具对模型进行分析。

在后处理中，可以查看混凝土和钢筋的应力、应变分布，以及裂缝的产生和发展情况。

此外，还可以通过输出裂缝的分布图、最大宽度等参数，以便对裂缝进行进一步分析。

四、结论使用abaqus软件进行混凝土裂缝计算，可以为实际工程提供有效的分析手段。

通过对材料模型、边界条件和加载条件的设置，可以模拟混凝土结构在各种工况下的裂缝发展情况。

基于ABAQUS的裂纹扩展仿真软件及应用摘要：裂纹扩展仿真软件是材料力学领域中重要的工具之一。

本文介绍了一种基于ABAQUS的裂纹扩展仿真软件的开发和应用。

该软件结合ABAQUS的强大有限元分析功能和裂纹扩展理论，能够模拟裂纹在不同材料中的扩展过程，并可以用于评估裂纹扩展的速率、路径和影响因素等。

通过实例分析，展示了该软件在材料工程中的应用价值。

关键词：ABAQUS；裂纹扩展；仿真软件；应用1. 引言裂纹扩展是一种材料破坏的典型形式，对材料的强度、可靠性以及使用寿命有重要影响。

因此，对裂纹扩展的研究具有重要意义。

传统的实验方法虽然可以获得一些关于裂纹扩展的数据，但是实验周期长、成本高，不能满足大规模数据收集和分析的需求。

裂纹扩展仿真软件的开发就能够解决这一问题。

2. 基于ABAQUS的裂纹扩展仿真软件开发ABAQUS是一款功能强大的有限元分析软件，可以模拟材料的力学行为。

基于ABAQUS的裂纹扩展仿真软件利用ABAQUS的有限元方法，采用计算机辅助设计和数值计算方法，结合裂纹扩展理论，实现了裂纹扩展过程的模拟。

软件开发的核心是建立裂纹扩展模型。

首先，根据实际应用需求和研究目的，选取合适的材料模型，提取材料力学性质的参数。

然后，根据裂纹扩展行为的实际情况，选择适当的裂纹模型，并设计计算网格。

考虑到裂纹扩展过程中应力场的复杂性，需通过迭代计算得到裂纹尖端处的应力强度因子。

最后，计算得到裂纹扩展速率，并更新裂纹形貌。

3. 基于ABAQUS的裂纹扩展仿真软件应用基于ABAQUS的裂纹扩展仿真软件在材料工程领域中有着广泛的应用。

以下是一些典型的应用场景：3.1 裂纹扩展速率评估该软件可以模拟不同材料中的裂纹扩展过程，并可以根据计算结果评估裂纹扩展的速率。

通过对不同材料的裂纹扩展机制和速率的仿真，可以为材料的设计和改良提供参考。

3.2 裂纹扩展路径分析裂纹扩展仿真软件还能够模拟裂纹在材料中的传播路径。

对于复杂结构和材料，通过仿真软件可以预测裂纹传播的路径，并为结构强度和寿命分析提供依据。

ABAQUS XFEM Tutorial: 3D Edge Crack Written By: Matthew Jon Pais, University of Florida (2010)Website: Email: mpais@, matthewjpais@Creating the Uncracked Domain1. Open ABAQUS/CAE 6.9 or later.2. Double click on Parts. Enter name as Solid, Modeling Space is 3D, Type is Deformable, Base Feature is Solid and Approximate Size is 5. Click Continue.3. Use the rectangle tool to draw a square from (-2,-2) to (2,2). Click Done. Enter 4 for the depth. Click Ok.4. Double click on Materials. Enter name as Aluminum. Click on Mechanical, then Elasticity, then Elastic. Enter Young's modulus as 70 GPa and Poisson's ratio as 0.33. Click on Mechanical, then Damage for Traction Separation laws, then Maxps Damage. Enter a value of 500 MPa. From the Suboptions menu click on Damage Evolution. Enter Displacement at Failure as 1. Click Ok. Click Ok.5. Double click on Sections. Name as Main. Accept default settings by clicking Continue. Select Aluminum as material. Click Ok.6. Expand Parts then expand Solid. Double click on Section Assignments. Select the domain. Click Done. Accept default settings. Click Ok.7. Expand Solid. Double click on Mesh. From the top menu select Seed, then Edge By Number. Select the Domain. Click Done. Enter 21 as Number of elements along the edges. Hit Enter. Click Done.8. From the top menu select Mesh, then Controls. Select Hex, Structured. Click Ok. From the top menu select Mesh, then Part. Click Yes.9. Expand Assembly. Double click on Instances. Select Solid. Accept default settings by clicking Ok.Creating the Cracked Domain1. Double click on Parts. Enter name as Crack, Modeling Space is 3D, Type is Deformable, Base Feature is Shell, Type is Extrusion and Approximate Size is 5. Click Continue.2. Draw a line from (-2,0) to (-1,0). Click Done. Enter 4 for depth. Click Ok.3. Expand Assembly, then double click on Instances. Select Crack. Accept default settings by clicking Ok.4. Double click on Interactions. Click Cancel. From top menu click Special, then Crack, then Create. Name as EdgeCrack, Type is XFEM. Click Continue. Select the uncracked domain as the Crack Domain. On the menu which appears, Specify the Crack Location by clicking on the line signifying the crack. Click Ok.5. Double click on Interactions. Enter name as Growth. Select Initial Step and Types for Selected Step as XFEM Crack Growth. Click Continue. XFEM Crack should have EdgeCrack. Click Ok.Create the Boundary Conditions and Loads1. Double click on Steps. Enter Name as Loading. Accept default setting and click Continue. Accept default settings and click Ok.2. Double click on Loads. Enter name as TopPressure, Category is Mechanical, Type is Pressure. Click Continue. Select the top edge of the domain. Click Done. Enter -1 as Magnitude, other settings are default. Click Ok.3. Repeat step 2 for the bottom edge of the domain, entering the name as BottomPressure.4. Double click on BCs. Enter name as FixedBREdge, Step is Initial, Category is Mechanical, Types for Selected Step is Displacement/Rotation. Click on the bottom right edge through the thickness of the domain. Click Done. Set U1, U2 and UR3 to zero. Click Ok.5. Repeat step 4 for the top right corner of the domain. Enter name as RollerTRC. Set U1 and UR3 to zero.6. Expand Field Output Requests, double click on F-Output-1. Expand the Failure/Fracture options and check the box next to PHILSM, Level set value phi. Click Ok. This will allow you to view the level set function defining the crack.Solving the System of Equations1. Double click on Jobs. Enter name as EdgeCrack3D. Click Continue. Accept default settings by clicking Ok.2. Expand Jobs. Right click on EdgeCrack3D and click Submit.3. Right click on EdgeCrack3D, click Results to view results.。

基于abaqus的压电材料裂缝数值模拟摘要:压电材料为横观各向同性材料，有5个独立的弹性常数、3个独立的压电常数，2个独立的介电常数。

不同于各向同性材料，压电材料需要在建模时指明材料方向。

用abaqus建立4cm4cm的压电材料模型，中心有一个微小裂纹，利用mcci方法计算出在荷载作用下裂纹尖端的应变能释放率，与解析解相比较，发现结果吻合良好。

关键词：压电材料、常数、数据处理引言随着有限元法的发展，绝大多数工程问题都可以通过其得到令人满意的解答，abaqus作为通用有限元软件，强大的求解器能够很好的处理各种非线性问题。

压电材料是受到压力作用时会在两端面间出现电压的晶体材料。

1880年，由法国物理学家P.居里和J.居里兄弟发现。

把重物放在石英晶体上，晶体某些表面会产生电荷，电荷量与压力成比例。

这一现象被称为压电效应。

随即，居里兄弟又发现了逆压电效应，即在外电场作用下压电体会产生形变。

利用压电材料的这些特性可实现机械振动（声波）和交流电的互相转换。

因而压电材料广泛用于传感器元件中，例如地震传感器，力、速度和加速度的测量元件以及电声传感器等。

这类材料被广泛运用，举一个很生活化的例子，打火机的火花即运用此技术。

压电材料本构关系压电材料的本构方程有基于应力和基于应变两种形式，其在垂直于极化方向的平面上是各项同性的。

Yang[1]的文献中基于应力给出本构方程如下：其中为电位移分量，为压电常数，为介电常数，场强分量。

上述方程是以z轴方向为极化方向。

本文的计算模型以y轴为极化方向，所以需要调整各系数矩阵中参数的位置。

调整之后如下mcci计算应变能释放率Rybicki[2]文献中介绍了MCCI方法，利用裂纹尖端区域的节点力以及节点位移可以很方便的计算出应变能释放率。

I型裂纹的应变能释放率给出如下：应力强度因子与能量释放率的关系无限大板I型中心裂纹的应力强度因子解析解表达式为：，首先计算出应力强度因子，再根据其与应变能释放率的关系即可得压电材料无限大板中心裂纹的应变能释放率解析解，Z.Suo[4]文献中详细推导了两者之间的关系，现直接给出结果如下：其中，为Irwin矩阵，由材料的弹性参数，压电参数以及介电常数通过复变函数求解得到。

Analysis of a Deep Single Edge Notch Crack in a PlateThis example demonstrates the use of the "deep crack" capability in ZENCRACK with both sides of the crack modelled. In this type of analysis, in addition to inserting crack-blocks into the mesh, ZENCRACK separates other standard elements to form parts of the crack face.The example consists of a simple mesh of a square plate under prescribed end loading (displacement boundary condition). The full plate is modelled even though the geometry and loading is symmetric. A schematic of the geometry and loading is shown in Figure QA16-1.Figure QA16-1 - Square plate with single edge notchF.E. Mesh for the Uncracked ComponentThe finite element model for the uncracked component is shown in Figure QA16-2. The mesh consists of a 4x4x1 grid of elements. The crack is to be inserted by replacing elements 7 and 11. The nodes used to define crack orientation for each of these elements are shown in Figure QA16-3.To extend the crack faces outside the crack-blocks, it is required that elements 8 and 12 are split.ABAQUS Input Deck for the Uncracked ComponentThe ABAQUS input deck for the uncracked component is given in listing 1. The following points should be noted :1.PropertiesThe material property name ZCRMAT has been used toallow ZENCRACK to extract Young’s modulus andPoisson ratio from the uncracked mesh.ZENCRACK Input and OutputThe ZENCRACK input file is shown in listing 2. The analysis output file is shown in listing 3.The following points are specific to the "deep crack" definition :Input record 3 : 2 2 2 0.25 1 0 1Item 7, ISPLIT, is set to 1 to indicate that one split set is to be defined.Input record 3c : 1This indicates that there is 1 element pair in the split set.Input record 3d : 8 12This indicates that elements 8 and 12 are to be split.Figure QA16-2 - Uncracked mesh - element numbersFigure QA16-3 - Uncracked mesh - element 7 and 11 Nodes for crack front orientationFigure QA16-4 - Cracked meshFigure QA16-5 - Cracked mesh - displaced plotFigure QA16-6 - Cracked mesh - "lower left" region - displaced plot LISTING 1File: a16uc01.inpDescription: ABAQUS input file for uncracked component*HEADINGQA16 - 4x4x1 mesh*PREPRINT,ECHO=NO,HISTORY=NO,MODEL=NO*RESTART,WRITE*ELEMENT,TYPE=C3D20,ELSET=EALL1 12 7 6 26 27 32 31 126 127 128 129 130 131 132133 134 135 136 1372 23 8 7 27 28 33 32 384 376 385 127 386 380 387131 135 381 383 1363 34 9 8 28 29 34 33 373 374 375 376 377 378 379380 381 382 371 3834 45 10 9 29 30 35 34 388 389 365 374 390 391 368378 382 392 372 3715 26 27 32 31 51 52 57 56 130 131 132 133 302 213 224303 402 403 404 4056 27 28 33 32 52 53 58 57 386 380 387 131 211 203 212213 403 419 421 4047 28 29 34 33 53 54 59 58 377 378 379 380 200 201 202203 419 420 417 4218 29 30 35 34 54 55 60 59 390 391 368 378 219 220 192201 420 422 418 4179 51 52 57 56 76 77 82 81 302 213 224 303 238 216 227239 304 217 218 23010 52 53 58 57 77 78 83 82 211 203 212 213 214 207 215216 217 208 210 21811 53 54 59 58 78 79 84 83 200 201 202 203 204 205 206207 208 209 198 21012 54 55 60 59 79 80 85 84 219 220 192 201 221 222 195205 209 223 199 19813 76 77 82 81 101 102 107 106 238 216 227 239 240 241 242243 244 245 246 24714 77 78 83 82 102 103 108 107 214 207 215 216 294 290 295241 245 291 293 24615 78 79 84 83 103 104 109 108 204 205 206 207 287 288 289290 291 292 285 29316 79 80 85 84 104 105 110 109 221 222 195 205 296 297 282288 292 298 286 285*NODE1 0.0000 0.0000 0.00002 2.5000 0.0000 0.00003 5.0000 0.0000 0.00004 7.5000 0.0000 0.00005 10.0000 0.0000 0.00006 0.0000 2.5000 0.00007 2.5000 2.5000 0.00008 5.0000 2.5000 0.00009 7.5000 2.5000 0.000010 10.0000 2.5000 0.000026 0.0000 0.0000 2.500027 2.5000 0.0000 2.500028 5.0000 0.0000 2.500029 7.5000 0.0000 2.500030 10.0000 0.0000 2.500031 0.0000 2.5000 2.500032 2.5000 2.5000 2.500033 5.0000 2.5000 2.500034 7.5000 2.5000 2.500035 10.0000 2.5000 2.500051 0.0000 0.0000 5.000052 2.5000 0.0000 5.000053 5.0000 0.0000 5.000054 7.5000 0.0000 5.000055 10.0000 0.0000 5.000056 0.0000 2.5000 5.000057 2.5000 2.5000 5.000058 5.0000 2.5000 5.000059 7.5000 2.5000 5.000060 10.0000 2.5000 5.000076 0.0000 0.0000 7.500077 2.5000 0.0000 7.500078 5.0000 0.0000 7.500079 7.5000 0.0000 7.500080 10.0000 0.0000 7.500081 0.0000 2.5000 7.500082 2.5000 2.5000 7.500083 5.0000 2.5000 7.500084 7.5000 2.5000 7.500085 10.0000 2.5000 7.5000 101 0.0000 0.0000 10.0000 102 2.5000 0.0000 10.0000 103 5.0000 0.0000 10.0000 104 7.5000 0.0000 10.0000 105 10.0000 0.0000 10.0000 106 0.0000 2.5000 10.0000 107 2.5000 2.5000 10.0000 108 5.0000 2.5000 10.0000 109 7.5000 2.5000 10.0000 110 10.0000 2.5000 10.0000 126 1.2500 0.0000 0.0000 127 2.5000 1.2500 0.0000 128 1.2500 2.5000 0.0000129 0.0000 1.2500 0.0000 130 1.2500 0.0000 2.5000 131 2.5000 1.2500 2.5000 132 1.2500 2.5000 2.5000 133 0.0000 1.2500 2.5000 134 0.0000 0.0000 1.2500 135 2.5000 0.0000 1.2500 136 2.5000 2.5000 1.2500 137 0.0000 2.5000 1.2500 192 8.7500 2.5000 5.0000 195 8.7500 2.5000 7.5000 198 7.5000 2.5000 6.2500 199 10.0000 2.5000 6.2500 200 6.2500 0.0000 5.0000 201 7.5000 1.2500 5.0000 202 6.2500 2.5000 5.0000 203 5.0000 1.2500 5.0000 204 6.2500 0.0000 7.5000 205 7.5000 1.2500 7.5000 206 6.2500 2.5000 7.5000 207 5.0000 1.2500 7.5000 208 5.0000 0.0000 6.2500 209 7.5000 0.0000 6.2500 210 5.0000 2.5000 6.2500 211 3.7500 0.0000 5.0000 212 3.7500 2.5000 5.0000 213 2.5000 1.2500 5.0000 214 3.7500 0.0000 7.5000 215 3.7500 2.5000 7.5000 216 2.5000 1.2500 7.5000 217 2.5000 0.0000 6.2500 218 2.5000 2.5000 6.2500 219 8.7500 0.0000 5.0000 220 10.0000 1.2500 5.0000 221 8.7500 0.0000 7.5000 222 10.0000 1.2500 7.5000 223 10.0000 0.0000 6.2500 224 1.2500 2.5000 5.0000 227 1.2500 2.5000 7.5000 230 0.0000 2.5000 6.2500 238 1.2500 0.0000 7.5000 239 0.0000 1.2500 7.5000 240 1.2500 0.0000 10.0000 241 2.5000 1.2500 10.0000 242 1.2500 2.5000 10.0000243 0.0000 1.2500 10.0000 244 0.0000 0.0000 8.7500 245 2.5000 0.0000 8.7500 246 2.5000 2.5000 8.7500 247 0.0000 2.5000 8.7500 282 8.7500 2.5000 10.0000 285 7.5000 2.5000 8.7500 286 10.0000 2.5000 8.7500 287 6.2500 0.0000 10.0000 288 7.5000 1.2500 10.0000 289 6.2500 2.5000 10.0000 290 5.0000 1.2500 10.0000 291 5.0000 0.0000 8.7500 292 7.5000 0.0000 8.7500 293 5.0000 2.5000 8.7500 294 3.7500 0.0000 10.0000 295 3.7500 2.5000 10.0000 296 8.7500 0.0000 10.0000 297 10.0000 1.2500 10.0000 298 10.0000 0.0000 8.7500 302 1.2500 0.0000 5.0000 303 0.0000 1.2500 5.0000 304 0.0000 0.0000 6.2500 365 8.7500 2.5000 0.0000 368 8.7500 2.5000 2.5000 371 7.5000 2.5000 1.2500 372 10.0000 2.5000 1.2500 373 6.2500 0.0000 0.0000 374 7.5000 1.2500 0.0000 375 6.2500 2.5000 0.0000 376 5.0000 1.2500 0.0000 377 6.2500 0.0000 2.5000 378 7.5000 1.2500 2.5000 379 6.2500 2.5000 2.5000 380 5.0000 1.2500 2.5000 381 5.0000 0.0000 1.2500 382 7.5000 0.0000 1.2500 383 5.0000 2.5000 1.2500 384 3.7500 0.0000 0.0000 385 3.7500 2.5000 0.0000 386 3.7500 0.0000 2.5000 387 3.7500 2.5000 2.5000 388 8.7500 0.0000 0.0000 389 10.0000 1.2500 0.0000 390 8.7500 0.0000 2.5000391 10.0000 1.2500 2.5000392 10.0000 0.0000 1.2500402 0.0000 0.0000 3.7500403 2.5000 0.0000 3.7500404 2.5000 2.5000 3.7500405 0.0000 2.5000 3.7500417 7.5000 2.5000 3.7500418 10.0000 2.5000 3.7500419 5.0000 0.0000 3.7500420 7.5000 0.0000 3.7500421 5.0000 2.5000 3.7500422 10.0000 0.0000 3.7500*NSET,NSET=BASE1 2 3 4 5 6 7 8 9 10 126 127 128 129 365 373374 375 376 384 385 388 389*NSET,NSET=TOP101 102 103 104 105 106 107 108 109 110 240 241 242 243 282 287288 289 290 294 295 296 297*NSET,NSET=FIX151 56*NSET,NSET=FIX251*NSET,NSET=NOUTBASETOPFIX1FIX2*ELSET,ELSET=EOUT1*MATERIAL,NAME=ZCRMAT*ELASTIC200000,0.3*SOLID SECTION,ELSET=EALL,MATERIAL=ZCRMAT*BOUNDARYFIX1,1FIX2,2*STEP*STATIC*BOUNDARYTOP,3,3,0.01BASE,3,3,-0.01*EL PRINT,ELSET=EOUT*NODE PRINT,NSET=NOUT,TOTAL=YESRF*END STEPLISTING 2File: a16c05.zcrDescription: Input file for analysis of the initial configuration## ZENCRACK Q.A. Example #16## Uncracked mesh:a16uc01.inp# Job id:a16c05r0 1 0 3 2 0 02 2 2 0.25 1 0 1st111x5.sup7 54 53st111x5.sup11 59 5818 120.5 0.50.5 0.510 11LISTING 3File: a16c05r.repDescription: Output file for analysis of the initial configuration***************************************************************************** ** ZENCRACK is proprietary software of: ** ** ZENTECH INTERNATIONAL LTD., ** 103 Mytchett Road, ** Mytchett, ** Camberley, ** Surrey, ** GU16 6ES, ** GREAT BRITAIN ** Tel. (+44) 1252 376388 ** Fax. (+44) 1252 376389 ***********************.uk ** Web ** ****************************************************************************** ** The following system has been licensed: ** ** Program : ZENCRACK ** Version : 6.0 ** Release date : 09-NOV-1998 ** License type : Commercial ** Interface to : MARC & ABAQUS **** This system is licensed to: ** ** Company : Zentech International Limited ** Address : 103 Mytchett Road ** Camberley ** Surrey GU16 6ES ** U.K. ** Phone : +44 1252 376388 ** Fax : +44 1252 376389 ** Computer : PC ** ******************************************************************************** .zcr input file for analysis : ** E:\zencrack\qa16\a16c05 ** ** Date of analysis (D-M-Y) : 21-11-1998 ** Start time (H-M-S) : 15:18:40 ** *****************************************************************************INPUT RECORD 1***************UNCRACKED MESH : a16uc01.inp JOBNAME IS : E:\zencrack\qa16\a16c05rINPUT RECORD 2***************NUMBER OF DEBUG MODULES = 0WARNING FLAG = 1DISTORTION FLAG = 0F.E. CODE FLAG = 3RUN TYPE = 2READ RESTART = 0WRITE RESTART = 0PROGRAM WILL NOT STOP IF A WARNING IS ISSUEDELEMENT DISTORTION PARAMETERS WILL NOT BE CALCULATEDF.E. ANALYSIS USING ABAQUS 5.4 OR LATERNO DATA WILL BE READ FROM A RESTART FILENO DATA WILL BE WRITTEN TO RESTART FILESRUN TYPE 2 INDICATES :- ANALYSIS OF THE INITIAL CRACK ONLY OR FULL CRACK GROWTH ANALYSIS- EACH FE ANALYSIS SHOULD BE LINEAR ELASTIC- LOADING IS PROPORTIONAL(i.e. ENERGY RELEASE RATES CAN BE PROCESSED FROM ONLY THE FIRSTANALYSIS INCREMENT)INPUT RECORD 3***************NUMBER OF CRACK-BLOCKS TO BE INCLUDED = 2FLAG FOR INTERMEDIATE STEP DURING MAPPING OF CRACK-BLOCKS INTO THEMESHICONFO = 2 FLAGS TWO STAGE MAPPING OF CRACK-BLOCKS INTO THE MESHFLAG FOR COLLAPSED ELEMENT MODIFICATION AFTER MAPPINGIFIXER = 2 FLAGS LOCAL MODIFICATION OF CRACK FRONT ELEMENTS AFTERMAPPING"QUARTER POINT NODE" PARAMETER. VALID RANGE IS 0.25 TO 0.5,WITH 0.25 FOR QUARTER-POINT NODES AND 0.5 FOR MIDSIDE NODES.VALUE READ FOR QPR IS 0.2500VALUE USED FOR QUARTER POINT PARAMETER IS 0.2500FLAG FOR GENERATING EXTRA CRACK FRONT ELEMENT SETSICFSET HAS BEEN SET TO 1 - EXTRA ELEMENT SETS WILL BE GENERATED. SETSARE :CFACEn FOR ELEMENTS ON THE FACE(S) OF CRACK FRONT nCFRONTn FOR CRACK FRONT ELEMENTS OF CRACK FRONT nFLAG FOR GENERATING EXTRA CRACK RELATED NODE SETSINDSET HAS NOT BEEN SET TO 1,2 OR 12 - NO EXTRA NODE SETS WILL BEGENERATEDNUMBER OF SETS OF ELEMENTS TO BE SPLIT FOR CRACK FACES OF DEEP CRACKS= 1BIAS FACTOR NOT RELEVANT - ICONFO NOT SET TO 3USING DEFAULT VALUE FOR CONMIDF : 0.90000***WARNINGVALUE OF QUARTER POINT NODE PARAMETER HAS BEEN RESET TO 0.26TO AVOID POSSIBLE NUMERICAL PROBLEMS (INSIDE OUT ELEMENTS) WHENEXACTLY 0.25 IS USED.MINIMUM VALUE ALLOWED WITHOUT RESETTING IS 0.252.USE -0.25 TO FORCE A VALUE OF EXACTLY 0.25.CRACK-BLOCK NUMBER 1READ FROM FILE p:\009-zencrack\temptest\install\crack\st111x5.sup THIS CRACK-BLOCK REPLACES ORIGINAL ELEMENT 7CRACK PLANE IN MESH DEFINED BY CORNER NODES 54 53CRACK-BLOCK NUMBER 2READ FROM FILE p:\009-zencrack\temptest\install\crack\st111x5.sup THIS CRACK-BLOCK REPLACES ORIGINAL ELEMENT 11CRACK PLANE IN MESH DEFINED BY CORNER NODES 59 58SETS FOR SPLITTING ELEMENTS ON DEEP CRACK FACES1 PAIR OF ELEMENTS DEFINED FOR SET 1ELEMENT PAIR FOR THIS SET IS :8 & 12INPUT RECORD 4***************CRACK-BLOCK NUMBER 1RATIO OF CRACK LENGTH TO CRACK-BLOCK EDGE 1 LENGTH IS .50000E+00RATIO OF CRACK LENGTH TO CRACK-BLOCK EDGE 2 LENGTH IS .50000E+00RING SIZE NOT RELEVANT - ICONFO NOT SET TO 3CRACK-BLOCK NUMBER 2RATIO OF CRACK LENGTH TO CRACK-BLOCK EDGE 1 LENGTH IS .50000E+00RATIO OF CRACK LENGTH TO CRACK-BLOCK EDGE 2 LENGTH IS .50000E+00RING SIZE NOT RELEVANT - ICONFO NOT SET TO 3INPUT RECORD 5***************VALUE OF IPROG = 1NO USER SUBROUTINE REQUIREDINPUT RECORD 6***************NO FATIGUE CRACK GROWTH PREDICTIONS ARE REQUESTEDINPUT RECORD 10***************FACTORS ON APPLIED LOAD TO GIVE CYCLIC LOAD RANGEFACTOR TO GIVE MINIMUM LOAD = 0.00000E+00FACTOR TO GIVE MAXIMUM LOAD = 0.10000E+01INPUT RECORD 12***************FLAG FOR ABAQUS CONTOUR SELECTION FOR PROCESSINGNUCONT = 1 : USE CONTOUR 1 TO CALCULATE GmaxABAQUS CONTOUR INTEGRAL OPTIONJITYPE = 0 : *CONTOUR INTEGRAL OPTION SPECIFIES J-INTEGRALCALCULATIONSJVCE = 0 : *CONTOUR INTEGRAL WILL SPECIFY CRACK EXTENSIONDIRECTIONSNUMBER OF CONTOURS TO BE EVALUATED BY ABAQUSNCONT IS SET TO THE DEFAULT VALUE - 3 CONTOURS*NORMAL AT ENDS OF CRACK FRONTSJSNORM = 0 : *NORMAL AT ENDS OF CRACKS WILL BE USED***WARNINGUSE OF CONTOUR 1 VALUES IS NOT RECOMMENDEDYOU SHOULD COMPARE CONTOUR 1 VALUES WITH RESULTS FOR HIGHER CONTOURSFINAL INPUT RECORD******************ELEMENT DISTORTION PARAMETERS WILL NOT BE CALCULATED (IDIST=0 ON CARD2)--------------------------------------------------------------------------------END OF READ FROM .ZCR FILE--------------------------------------------------------------------------------***INFORMATION : WARNINGS WHILE READING .ZCR INPUT DATA2 warning messages generated while reading .ZCR data***INFORMATION : MATERIAL PROPERTY DATAZCRMAT material property defined on *MATERIAL input :*MATERIAL,NAME=ZCRMAT*ELASTICYoungs modulus= 0.200000E+06 Poisson ratio= 0.30000Temperature= 0.00***INFORMATION : CRACK FRONT DEFINITIONCrack front 1 Side 1 Side 2C.B. Element C.B. Element1 72 11***INFORMATION : NODES FOR SPLIT SET 1ORIGINAL NODE NODE ON OPPOSITE FACE INITIAL COORDINATES (X,Y,Z)54 1633 0.75000E+01 0.00000E+000.50000E+0155 1634 0.10000E+02 0.00000E+000.50000E+0159 1635 0.75000E+01 0.25000E+010.50000E+0160 1636 0.10000E+02 0.25000E+010.50000E+01192 1637 0.87500E+01 0.25000E+010.50000E+01201 1638 0.75000E+01 0.12500E+010.50000E+01219 1639 0.87500E+01 0.00000E+000.50000E+01220 1640 0.10000E+02 0.12500E+010.50000E+01***INFORMATION : CRACK FRONT NODE LISTSCrack front number 1472 541 588 636 673 724 777 816 861908 973***INFORMATION : CONTOURS AND Gmax EVALUATION FOR EACH CRACK FRONTCrack front 1 has 3 contours : Gmax evaluated using contour 1***INFORMATION : ANALYSIS DESCRIPTIONSingle finite element analysis (IRUN=2) with no fatigue crack growth--------------------------------------------------------------------------------ZENCRACK 6.0 : Zentech International Ltd. Date of analysis :21-11-1998Licensed to : Zentech International LimitedLicense type : CommercialInput ref. : E:\zencrack\qa16\a16c05 Output ref. : E:\zencrack\qa16\a16c05r --------------------------------------------------------------------------------RESULTS FOR FINITE ELEMENT ANALYSIS NUMBER 1--------------------------------------------------------------------------------NEW MESH WRITTEN.SYSTEM TIME IS (H,M,S) 15:18:47ELAPSED TIME IS (H,M,S) 0: 0: 7J-INTEGRAL VALUES FROM ABAQUS OUTPUT FILE, SET 1**************************************************ANALYSIS USED ABAQUS VERSION 5.8-1CRACK SET NODE CONTOUR 1 CONTOUR 2 CONTOUR 31 1 1 0.16840E+01 0.16330E+01 0.16450E+011 12 0.19440E+01 0.19600E+01 0.19550E+011 1 3 0.20310E+01 0.19690E+01 0.19740E+011 1 4 0.19990E+01 0.20210E+01 0.20200E+011 1 5 0.21040E+01 0.20360E+01 0.20370E+011 1 6 0.20210E+01 0.20440E+01 0.20430E+011 1 7 0.21030E+01 0.20360E+01 0.20370E+011 1 8 0.19990E+01 0.20210E+01 0.20200E+011 1 9 0.20300E+01 0.19690E+01 0.19740E+011 1 10 0.19450E+01 0.19600E+01 0.19550E+011 1 11 0.16830E+01 0.16340E+01 0.16450E+011 2 1 0.25790E+01 0.25020E+01 0.25200E+011 2 2 0.29790E+01 0.30030E+01 0.29950E+011 2 3 0.31110E+01 0.30170E+01 0.30240E+011 2 4 0.30620E+01 0.30960E+01 0.30950E+011 2 5 0.32230E+01 0.31200E+01 0.31210E+011 2 6 0.30970E+01 0.31310E+01 0.31300E+011 2 7 0.32220E+01 0.31200E+01 0.31210E+011 2 8 0.30630E+01 0.30960E+01 0.30950E+011 2 9 0.31100E+01 0.30170E+01 0.30240E+011 2 10 0.29800E+01 0.30030E+01 0.29950E+011 2 11 0.25790E+01 0.25030E+01 0.25210E+011 3 1 0.31630E+01 0.30700E+01 0.30910E+011 32 0.36550E+01 0.36840E+01 0.36740E+011 3 3 0.38150E+01 0.37000E+01 0.37100E+011 3 4 0.37570E+01 0.37980E+01 0.37970E+011 3 5 0.39530E+01 0.38270E+01 0.38280E+01 1 3 6 0.37990E+01 0.38410E+01 0.38390E+01 1 3 7 0.39530E+01 0.38270E+01 0.38280E+01 1 3 8 0.37570E+01 0.37980E+01 0.37970E+01 1 3 9 0.38150E+01 0.37010E+01 0.37100E+01 1 3 10 0.36550E+01 0.36840E+01 0.36740E+01 1 3 11 0.31630E+01 0.30710E+01 0.30920E+01 1 4 1 0.33650E+01 0.32670E+01 0.32900E+01 1 42 0.38900E+01 0.39200E+01 0.39100E+01 1 43 0.40600E+01 0.39380E+01 0.39480E+01 14 4 0.39980E+01 0.40420E+01 0.40410E+01 1 45 0.42060E+01 0.40720E+01 0.40740E+01 1 46 0.40430E+01 0.40870E+01 0.40860E+01 1 47 0.42060E+01 0.40720E+01 0.40740E+01 1 48 0.39980E+01 0.40420E+01 0.40410E+01 1 49 0.40600E+01 0.39380E+01 0.39480E+01 1 4 10 0.38900E+01 0.39200E+01 0.39100E+01 1 4 11 0.33660E+01 0.32680E+01 0.32910E+01 1 5 1 0.31620E+01 0.30700E+01 0.30910E+01 1 5 2 0.36550E+01 0.36840E+01 0.36740E+01 1 5 3 0.38150E+01 0.37000E+01 0.37100E+01 1 5 4 0.37570E+01 0.37980E+01 0.37970E+01 1 5 5 0.39520E+01 0.38270E+01 0.38280E+01 1 5 6 0.38000E+01 0.38410E+01 0.38390E+01 1 5 7 0.39520E+01 0.38270E+01 0.38280E+01 1 5 8 0.37570E+01 0.37980E+01 0.37970E+01 1 5 9 0.38150E+01 0.37010E+01 0.37100E+01 1 5 10 0.36550E+01 0.36840E+01 0.36740E+01 1 5 11 0.31630E+01 0.30710E+01 0.30920E+01 1 6 1 0.25770E+01 0.25020E+01 0.25200E+01 1 6 2 0.29800E+01 0.30030E+01 0.29950E+01 1 6 3 0.31100E+01 0.30170E+01 0.30240E+01 1 6 4 0.30630E+01 0.30960E+01 0.30950E+01 1 6 5 0.32220E+01 0.31200E+01 0.31210E+01 1 6 6 0.30980E+01 0.31310E+01 0.31300E+01 1 6 7 0.32220E+01 0.31200E+01 0.31210E+01 1 6 8 0.30620E+01 0.30960E+01 0.30950E+01 1 6 9 0.31100E+01 0.30170E+01 0.30240E+01 1 6 10 0.29800E+01 0.30030E+01 0.29950E+01 1 6 11 0.25790E+01 0.25030E+01 0.25210E+01 1 7 1 0.16810E+01 0.16330E+01 0.16450E+01 1 7 2 0.19450E+01 0.19600E+01 0.19550E+01 1 7 3 0.20290E+01 0.19690E+01 0.19740E+01 1 7 4 0.19990E+01 0.20210E+01 0.20200E+01 1 7 5 0.21020E+01 0.20360E+01 0.20370E+011 7 6 0.20220E+01 0.20430E+01 0.20430E+011 7 7 0.21030E+01 0.20360E+01 0.20370E+011 7 8 0.19990E+01 0.20210E+01 0.20200E+011 7 9 0.20300E+01 0.19690E+01 0.19740E+011 7 10 0.19450E+01 0.19600E+01 0.19550E+011 7 11 0.16830E+01 0.16340E+01 0.16450E+01DATA FOR CRACK FRONT 1***********************ENERGY RELEASE RATE SET 1 ALONG CRACK FRONT 1 - from contour 1 N G-LOCAL NX NY NZ1 0.16840E+01 -0.50000E+00 0.00000E+00 0.86603E+002 0.20310E+01 -0.50000E+00 0.00000E+00 0.86603E+003 0.21040E+01 -0.50000E+00 0.00000E+00 0.86603E+004 0.21030E+01 -0.50000E+00 0.95367E-06 0.86603E+005 0.20300E+01 -0.50000E+00 -0.95370E-06 0.86603E+006 0.16830E+01 -0.50000E+00 0.00000E+00 0.86603E+00ENERGY RELEASE RATE SET 2 ALONG CRACK FRONT 1 - from contour 1 N G-LOCAL NX NY NZ1 0.25790E+01 -0.76604E+00 0.00000E+00 0.64279E+002 0.31110E+01 -0.76604E+00 0.00000E+00 0.64279E+003 0.32230E+01 -0.76604E+00 0.00000E+00 0.64279E+004 0.32220E+01 -0.76604E+00 0.14611E-05 0.64279E+005 0.31100E+01 -0.76604E+00 -0.14612E-05 0.64279E+006 0.25790E+01 -0.76604E+00 0.00000E+00 0.64279E+00ENERGY RELEASE RATE SET 3 ALONG CRACK FRONT 1 - from contour 1 N G-LOCAL NX NY NZ1 0.31630E+01 -0.93969E+00 0.00000E+00 0.34202E+002 0.38150E+01 -0.93969E+00 0.00000E+00 0.34202E+003 0.39530E+01 -0.93969E+00 0.00000E+00 0.34202E+004 0.39530E+01 -0.93969E+00 0.17923E-05 0.34202E+005 0.38150E+01 -0.93969E+00 -0.17924E-05 0.34202E+006 0.31630E+01 -0.93969E+00 0.00000E+00 0.34202E+00ENERGY RELEASE RATE SET 4 ALONG CRACK FRONT 1 - from contour 1 N G-LOCAL NX NY NZ1 0.33650E+01 -0.10000E+01 0.00000E+00 0.38147E-062 0.40600E+01 -0.10000E+01 0.00000E+00 0.00000E+003 0.42060E+01 -0.10000E+01 0.00000E+00 0.00000E+004 0.42060E+01 -0.10000E+01 0.19073E-05 0.38147E-065 0.40600E+01 -0.10000E+01 -0.19074E-05 0.00000E+006 0.33660E+01 -0.10000E+01 0.00000E+00 0.00000E+00ENERGY RELEASE RATE SET 5 ALONG CRACK FRONT 1 - from contour 1 N G-LOCAL NX NY NZ1 0.31620E+01 -0.93969E+00 0.00000E+00 -0.34202E+002 0.38150E+01 -0.93969E+00 0.00000E+00 -0.34202E+003 0.39520E+01 -0.93969E+00 0.00000E+00 -0.34202E+004 0.39520E+01 -0.93969E+00 0.17923E-05 -0.34202E+005 0.38150E+01 -0.93969E+00 -0.17924E-05 -0.34202E+006 0.31630E+01 -0.93969E+00 0.00000E+00 -0.34202E+00ENERGY RELEASE RATE SET 6 ALONG CRACK FRONT 1 - from contour 1 N G-LOCAL NX NY NZ1 0.25770E+01 -0.76604E+00 0.00000E+00 -0.64279E+002 0.31100E+01 -0.76604E+00 0.00000E+00 -0.64279E+003 0.32220E+01 -0.76604E+00 0.00000E+00 -0.64279E+004 0.32220E+01 -0.76604E+00 0.14611E-05 -0.64279E+005 0.31100E+01 -0.76604E+00 -0.14612E-05 -0.64279E+006 0.25790E+01 -0.76604E+00 0.00000E+00 -0.64279E+00ENERGY RELEASE RATE SET 7 ALONG CRACK FRONT 1 - from contour 1 N G-LOCAL NX NY NZ1 0.16810E+01 -0.50000E+00 0.00000E+00 -0.86603E+002 0.20290E+01 -0.50000E+00 0.00000E+00 -0.86603E+003 0.21020E+01 -0.50000E+00 0.00000E+00 -0.86603E+004 0.21030E+01 -0.50000E+00 0.95367E-06 -0.86603E+005 0.20300E+01 -0.50000E+00 -0.95370E-06 -0.86603E+006 0.16830E+01 -0.50000E+00 0.00000E+00 -0.86603E+00GMAX DISTRIBUTION FOR CRACK FRONT 1N GMAX VALUES DIRECTION (X,Y,Z)1 0.33653E+01 -0.10000E+01 0.00000E+00 0.49112E-032 0.40600E+01 -0.10000E+01 0.00000E+00 0.22922E-033 0.42062E+01 -0.10000E+01 0.00000E+00 0.25253E-034 0.42061E+01 -0.10000E+01 0.19073E-05 0.31615E-045 0.40599E+01 -0.10000E+01 -0.19074E-05 -0.13273E-076 0.33662E+01 -0.10000E+01 0.00000E+00 -0.20204E-07G SUMMARY : MODE I CONVERSION FROM G TO K USING: K =SQRT(ExG/(1-NuxNu))THESE ARE PLANE STRESS AND PLANE STRAIN K VALUESN GMAX VALUES K, Nu=0.000 K, Nu1 0.33653E+01 0.82040E+03 0.86002E+032 0.40600E+01 0.90111E+03 0.94463E+033 0.42062E+01 0.91720E+03 0.96148E+034 0.42061E+01 0.91718E+03 0.96146E+035 0.40599E+01 0.90110E+03 0.94461E+036 0.33662E+01 0.82051E+03 0.86013E+03------------ ------------ ------------MEAN: 0.38773E+01 0.87958E+03 0.92205E+03------------ ------------ ------------MIN.: 0.33653E+01 0.82040E+03 0.86002E+03 AT N = 1MAX.: 0.42062E+01 0.91720E+03 0.96148E+03 AT N = 3N NODE NO. CURRENT COORDS (AT WHICH Gmax IS CALCULATED)1 472 0.62500E+01 0.12482E-04 0.50000E+012 588 0.62500E+01 0.50000E+00 0.50000E+013 673 0.62500E+01 0.10000E+01 0.50000E+014 777 0.62500E+01 0.15000E+01 0.50000E+015 861 0.62500E+01 0.20000E+01 0.50000E+016 973 0.62500E+01 0.25000E+01 0.50000E+01SUMMARY OF LOADING******************REPORTS OF MAXIMUM AND MINIMUM ENERGY RELEASE RATE VALUES,DELTA sqrt(G), DELTA K AND CRACK GROWTH DIRECTION VECTORS(DELTA K0 = PLANE STRESS VALUE, DELTA Knu = PLANE STRA IN VALUE)CRACK FRONT 1MAXIMUM Gmax MINIMUM Gmax DELTA sqrt(G) DELTA K0 DELTA Knu1 0.33653E+01 0.00000E+00 0.18345E+01 0.82040E+03 0.86002E+032 0.40600E+01 0.00000E+00 0.20150E+01 0.90111E+03 0.94463E+033 0.42062E+01 0.00000E+00 0.20509E+01 0.91720E+03 0.96148E+034 0.42061E+01 0.00000E+00 0.20509E+01 0.91718E+03 0.96146E+035 0.40599E+01 0.00000E+00 0.20149E+01 0.90110E+03 0.94461E+036 0.33662E+01 0.00000E+00 0.18347E+01 0.82051E+03 0.86013E+03DIRECTION (X,Y,Z)1 -0.10000E+01 0.00000E+00 0.49112E-032 -0.10000E+01 0.00000E+00 0.22922E-033 -0.10000E+01 0.00000E+00 0.25253E-034 -0.10000E+01 0.19073E-05 0.31615E-045 -0.10000E+01 -0.19074E-05 -0.13273E-076 -0.10000E+01 0.00000E+00 -0.20204E-07***ANALYSIS COMPLETE***NO CRACK GROWTH REQUESTED。

abaqus 断裂图文实例在abaqus中创建裂纹1. create part，如图1所示:图12. 进入草图模式，创建一矩形板，点鼠标中键2次退出草图模式，点击Partition Face: Sketch,再次进入草图模式，创建一条seam，如图2所示:图213. 在草图模式下，创建4个半圆(为以后定义裂纹及mesh 做准备)，如图3所示:图34. 退出part模块，进入property模块，create material，create section，assign section，此过程不再细述。

(材料定义为线弹性即可)5. 进入assembly模块，create instance;进入step模块，create step，默认选择即可，不需要改动。

d6. 进入interaction模块，点击special——crack——assign seam，按住shift键，选择3段直线段作为seam(见图4)，然后点击special——crack——create，给裂纹起名，continue，选择内部小圆区域作为first contour region，选择圆心作为crack tip region，用向量q表示裂纹扩展方向(需输入向量起点和终点坐标)，进入edit crack菜单，定义裂尖奇异性，见图5所示，相关内容请参考abaqus manual，定义完成的裂纹见图6所示。

图4 2图5图67. 进入step模块，点击history output manager，点击edit，进入edit history output request菜单，设置见图7所示，详细内容请参考abaqus manual。

8. 进入load模块，定义外力及边界条件，定义好后见图8所示，此过程不再细述。

3图7图849. 进入mesh模块，设置边种子(根据建模情况考虑)，最内部用三角形单元，外层用四边形单元，最后效果如图9所示，此过程不再细述。