Abaqus Guide
Introduction
The purpose of this document is to provide guidelines by which to analyze a model aircraft wing structure in Abaqus. The guide assumes that the user has little experience with Abaqus and/or may not have encountered many of the features used. The design of the structure is based largely on previous semesters of AERO 402-Aircraft. It is assumed that the user has already created a working assembly of the wing structure using CAD software. This document will assume that the CAD software used is SolidWorks.
The layout of the wing structure used in this example is shown below with the upper surface skin and sheeting removed. The wing uses the NACA 63-210 airfoil and has a leading edge sweep of 30 degrees. There is a 12 inch root chord with a taper ratio of 0.5. There is a root incidence angle of 2 degrees and a wing twist of -2.5 degrees. The tip therefore has an incidence of -0.5 degrees. These parameters were chosen in order to demonstrate the techniques that will allow students to analyze a wide variety of wing structures whether simpler or more complex than this example.
Importing the SolidWorks Model
The model must be saved in a format that is most compatible to be used by Abaqus. Although there are many formats which can be imported into Abaqus, it should be noted that geometric features created in Abaqus CAE are stored in ACIS (.sat) format. The Abaqus documentation therefore suggests using this format for part imports.
Using the ACIS format, every part in an assembly
can be imported into Abaqus at once whereas
importing other part formats may require each
individual part to be saved and imported. In the
case of this structure there are 60 individual
parts that must be imported. Furthermore, the
geometry in stored to an accuracy of 1*10-6 in
ACIS formatting, but according to the Abaqus
documentation other available formats can be
much less accurate.
In SolidWorks, open the wing structure assembly
to be analyzed. Go to File->Save As and use the
pull-down arrow to select ACIS (*.sat) in the
“Save as type:” field. Use the Options button in
the bottom right of the “Save As” window.
Ensure that “Solid/Surface geometry” is selected
for the “Output as:” option and check that the
units are as desired. Check that the highest
number is select ed for “Version”. Click “OK” and
save the file.
Open a new model database in Abaqus CAE.
Under the model tree, right click on Parts and
select Import. Ensure that ACIS is selected for
the File Filter and locate the assembly file that
was exported from SolidWorks. If an error is
given that the file is not a valid ACIS file, return
to SolidWorks and resave the file with the next
lower Version in the Export Options and re-
import the new file.
Import all parts as 3D, Deformable Solids and in
general do not scale the parts. Select OK and
Abaqus will create a new part for every member of
the assembly. If an error or warning is given that
any of the parts have “imprecise geometry”, there
are two logical courses of action. The first is to use
the “Convert to precise representation geometry”
option when importing. Typically the best action
however is to return to the CAD program and
carefully check the parts for errors. Possible errors include regions of overlapping volume or self-intersection as well as minute slivers of material
that may be left when using cut features.
Because wing structural assemblies typically consist of numerous individual parts (in this example there are 60), it is recommended for each part to right click and rename each part with a more descriptive name, i.e. “Rib 1 Center”, “Front Top Spar Cap”, etc.
Partitioning
Partitioning parts is generally recommended when a single part makes contact in a joint with two or more parts. Partitioning is especially necessary when multiple parts contact a single surface of another part. Later when contact constraints are added to the model, the need for partitioning becomes evident and which parts require partitions becomes clearer.
Observe the joints shown to the right. The rib has a partition where it
will join the shear web of the rear shear web because the spar caps also
join the web and the rib. The top spar cap is removed to show the
partitions on the shear web segments. Note that the web segments are
partitioned for the joints with the caps as well as with one another.
To partition for the joints, first select one of the shear web
segments in the part module. Select “Partition Face: Sketch”.
Select the front face (the face with normal vector
approximately in the negative x-direction) and click done.
Choose to select an edge to appear “vertical and on the
left” and select the left edge.
Sketch a simple vertical line, press escape if prompted to enter
the next point, and click done at the “Sketch partition geometry”
prompt.
For the joints between web segments, it is necessary that the
part itself be partitioned into cells rather than just
partitioning the face. To do this, select “Partition Cell:
Extrude/Sweep Edges” as shown.
Select the edge that was created by the face partition, click
“Done”, and select “Extrude Along Direction”. Select the
edge shown to the right for the extrude direction and click
“OK” then click “Create Partition” and “Done”. Use these
steps to partition cells on each shear web segment where it
will join another web segment. Also partition cells on the
rear of the central rib segments as shown at the beginning
of this section. Partition the front faces of all rear shear
web segments as shown at the beginning of the section.
Material Properties
The structure of this example consists of materials that are primarily used in creating model aircraft: balsa wood, birch ply-wood, and Monokote skin. Because wood is highly orthotropic, it is critical that orthotropic material properties be specified for all wooden components and that material directions be specified to simulate the wood grain directions.
Use the pull-down arrow to go to the Property
module and create a new material for each of
balsa, birch, and Monokote.
Choose to define elastic mechanical
properties as shown.
For the woods, select Type: Orthotropic using
the pull-down menu.
Orthotropic material behavior is defined by:
Where the D matrix for balsa is given using values from the USDA Enycyclopedia of Wood as: 544477.0317 8464.503486 15429.48139 0 0 0 8464.503486 9609.681717 5447.54364 0 0 0 15429.48139 5447.54364 260031.5336 0 0 0
0 0 0 1.99E+04 0 0
0 0 0 0 2.91E+04 0
0 0 0 0 0 2.70E+03
Similarly the D matrix for birch, calculated using values from the USDA, is: 2306606.945 138833.8032 195951.2595 0 0 0 138833.8032 161031.5298 79197.24615 0 0 0 195951.2595 79197.24615 253126.8765 0 0 0
0 0 0 1.50E+05 0 0
0 0 0 0 1.64E+05 0
0 0 0 0 0 3.76E+04
If basswood should instead be used for any components, the D matrix using USDA values is: 1657603.957 81770.03951 130932.8106 0 0 0 81770.03951 64579.6542 40144.71305 0 0 0 130932.8106 40144.71305 158411.8644 0 0 0
0 0 0 7.39E+04 0 0
0 0 0 0 8.99E+04 0
0 0 0 0 0 1.61E+04
After using the above properties to define the wood
materials, create Monokote as an isotropic material with the
properties shown. Distributors of Monokote acknowledge
that it is a Mylar film, but will not provide specific properties.
The properties shown are therefore taken from information
for Mylar films manufactured by DuPont Teijin Films.
Material Libraries
In Abaqus versions 6.7EF and later, material properties can managed
through the use of Material Libraries. Material Libraries allow the
use of consistent material properties without the need to research
properties for each individual material. Because of the number of
values required to define orthotropic materials, libraries are
especially useful for these materials. While in the Property module,
note that there is a tab for Material Library.
In the work directory create a folder named “abaqus_plugins” if there is not one already there. Go to the Material Library tab and use the “Material Library Manager” button.
Create a new Material L ibrary using the “Create”
button. Select each material and use the “ < ”
button to add the material to the library. Save
the library and the materials in it can be added to
any other project. Again, this is primarily to
ensure consistent properties are used and to save
time in finding the necessary parameters.
To use materials from a library in a project, first ensure that the .lib
file is saved in the “abaqus_plugins” folder. In the Material Library
Tab use the pull-down arrow to select the desired library (if there
are multiple in the plugin folder). Select the material and use the
“Add Material to Curent Model” button.
Material Directions
In order to accurately apply the material properties to the parts,
material directions must be assigned for each orthotropic part. To
demonstrate this, first go to the model tab and find one of the spar
caps in the Parts list, right click on it, and select “Switch Context”.
Use the “Create Datum CSYS: 3 Points” button as shown
and choose to create a Rectangular coordinate system.
edges of the part. When prompted to select a point
along the x-axis, choose any other point that lies along
the same edge as already chosen. Choose the third
point as any point on an edge which is parallel to the
edge already chosen. The desired result is that the x-
axis should lie along the longitudinal direction of the
part. All other spar caps and all stringers should have
datum coordinate systems added in a like manner. Each
piece of the upper surface and lower surface sheets for
each leading edge and trailing edge should have
coordinate systems added in a similar manner.
to the Property module and choose to Assign Material Orientation.
the “Datum CSYS List” button in the bottom right,
and select the datum coordinate system that was
created with the three points. Leave the default
options in the “Edit Material Orientation” window
and click OK.
center rib segments and leading edge
segments can also be accomplished with
the same procedure. As shown, the corner notches provide the three points to define the coordinate system.
As the trailing edge segments do not have such
notches, other techniques can be used to create
logical material directions. For the trailing edge
segments, the desired material directions are
such that one axis lies along the left edge, one
axis lies perpendicular to that edge and in the plane of the face shown, and one axis is normal to the face shown.
First choose to create a point using “Create Datum Point:
Project Point On Line”.
Choose the point shown and the left
edge. The use the projected point,
the original point, and another point
along the left edge to define the
datum coordinate system. Assign
material directions with the same
steps as above.
Define material coordinates for the leading edge dowel such
that the x-axis coincides with the longitudinal direction of the
part.
Sections and Composite Layups
In the Property module, use the Create
Section button to create a Solid,
Homogeneous section of balsa material.
Assign this section to each spar cap and to
each stringer. Create another Solid,
Homogeneous section of birch and assign it
to the leading edge dowel rod
For the leading and trailing edge sheets,
create a Homogeneous, Shell section and
note that it is considered to be type:
Continuum Shell. Since the sheets are 1/32
inch balsa, enter .03125 for the thickness and
balsa material. Since this is a Continuum Shell
section, the true thickness is calculated based
on the dimensions of the part to which it is
assigned. The entered value is considered an
initial value for the calculations. Assign this
section to each of the upper and lower
surface leading and trailing edge sheets.
Create another Continuum Shell section for
the shear webs. Use a thickness of 1/16 inch
(.0625) and balsa material. Assign this
section to each of the three segments of the front shear web and the three segments of the rear shear web. Create a Continuum Shell section with 0.002 thickness and Monokote/Mylar material. Assign this section to the wing skin.
The rib segments should be modeled as 1/16 inch thickness
birch plywood with 3 plies oriented at 0-90-0 degrees. The most
accurate way to model these therefore is to use the composite
layup feature in Abaqus. In the property module, select “Create
Composite Layup” as sho wn
Create a 3-ply Continuum Shell layup.
Right click the Region box, select Edit Region,
highlight the entire part, and click done to set the
entire column. Right click the Material box, select
birch, and click OK to set the entire column. Since
the part is 1/16 inch thick, assign 0.020833,
0.020834, and 0.020833 for the thicknesses.
Near the top of the window, use the pull-down
arrow to set “Definitition: Coordinate system”.
Click the “Select” button, choose “Datum CSYS
List”, select the datum coordinate system
previously defined, and click OK. Set the rotation
angles for the plies to 0, 90, and 0. Click OK and
the part is now defined as a 3-ply composite. Use
the same sequence of steps to apply composite layups to each leading edge rib segment and each trailing edge rib segment.
Meshing
Notice that of all the parts that compose the structural assembly, the majority of them are plate-like, thin structures. All of the ribs and shear web segments are simple flat plates while the leading and trailing edge sheeting and the skin are curved shell structures. All of these type components can be analyzed in Abaqus using Continuum Shell Elements.
To use Continuum Shells in the analysis, mesh controls must be
assigned to each part that will use the shell elements. For each
plate-like and shell-like part, go to the Mesh modules and
select “Assign Mesh Controls”
Highlight the entire part and click done. Make sure that
the technique to be used is Sweep. On parts such as the
rib segments, Sweep meshing may have been selected as the default.
Choose “Assign Element Type”, highlight the entire part, and
click done.
Choose Continuum Shell, Hex and leave the
other options at the default settings. Note
that on parts that contain a cusp such as on
the trailing edge sheets, it is often desirable
to partition the cusp from the rest of the part.
Continuum Shell, Wedge elements can then
be applied to the cusp in order to provide a
better quality mesh than if only hex elements
were used.
Apply this sequence of steps to each of the rib segments, the shear web segments, the sheeting and the skin. The stringers, spar caps, and leading edge dowel can simply be assigned 3D Stress elements.
The parts of this example can be seeded by specifying the approximate global size as shown. Avoid meshing too finely on the ribs segments as the Academic Teaching License is limited to 100000 nodes for the entire assembly. The curvature of the wing skin will dictate a very fine mesh that will easily lead to a node count near that limit. Higher quality meshes can often be obtained using careful partitioning and edge seeds, but doing so can be quite tedious and often yields little benefits to the analysis.
Assembly
The first step in assembling the model is to create an Instance for each and every part.
Go to the Assembly module, right click on
Instances, and select “Create Instance” as shown.
Left click on the first part in the list, scroll to the
bottom, hold the Shift key, and left click on the
bottom-most part. Choose Dependent Instance
Type and click OK. This will create all 60
Instances at once
At this point each of the parts will be placed in
the position that the part held in the SolidWorks
assembly and therefore in the ACIS .sat file that
was used to import the geometry. By default, all
of the datum coordinate systems that were
created for the material directions are also
shown in the assembly. This
clutter can make assigning
constraints more annoying.
To remove the clutter from the
assembly, go to View->Assembly
Display Options. Go to the
Datum tab and unselect “Show
datum coordinate system”.
Changing the View Manipulation Options can often make constraining the assembly much less of an annoyance. To do this, go to Tools->Options. There one can set the mouse controls to coincide with controls in a number of CAD
programs with which the user may be more familiar such as SolidWorks or Catia.
Properly constraining the assembly requires a rather lengthy sequence of constraints between the various parts. It is generally easier to work with constraining some parts when other parts not in the view. In the Model tree, under Instances right click on the upper surface piece of the wing skin and
select “Suppress”. Do the same for the two p ieces of upper surface sheeting. This will allow the underlying structure to be visible. To add each part back to the assembly, simply right
click and select “Resume”.
To assign the constraints, the parts should be separated enough to select the contac t surfaces. For example, select the “Translate Instance” shown.
Select the top cap of the front spar, click done, enter (0,0,0) for the translation vector start point, enter (0,3,0) for the translation vector end point, and click OK.
In the Interaction module, use the “Create
Constraint” button to create a Tie Constraint.
Click continue, choose Surface for the master type, and
left click on the bottom surface of the spar cap.
Choose Surface for the slave type and select the top surface for each of the front shear web segments. Also select the top surface of the corner notch on each leading
edge rib segment and center rib segment as shown. To select multiple surfaces simply click a surface, hold the Shift key, and left click the next surface. To deselect one of the surfaces hold the Ctrl key and left click on the undesired surface.
Click Done to access the Edit Constraint window. The Position
Tolerance option should be set based upon the manner in
which the parts are assembled. In many cases the computed
default is sufficient especially when this is no separation or
negligible separation. In some assemblies, however, the
convergence calculations are helped by instead adding a small
separation between parts and then specifying the Position
Tolerance as slightly larger than the separation. In many cases
the “Adjust slave surface initial position” option will aid the
calculations. However, care should be taken especially in
contact between curved or complex surfaces as this option may
occasionally cause errors due to “Negative Element Volume”.
Once the constraint is completed the part should be translated
back to its original position. Constraints should then be added in
the same manner to define each joint between parts. As was shown previously, a single constraint can be added to define several joints that a single part has with several others. Multiple master surfaces can also be chosen in defining a single constraint, thereby further reducing the number of individual constraints which are to be used in defining the assembly. The list of constraints which were used in creating this example is shown to the right in order to demonstrate a possible combination of constraints to define the assembly. One primary concern in defining the constraints is that no node should have more than one master, although a master node may have any number of slave nodes.
Loads and Boundary Conditions
The loads and boundary conditions chosen for this example were
somewhat simple.
Go to the Step module and use the “Create Step” button to create a Static, General Step. The default options are sufficient to conduct basic analysis.
Go to the Load Module and use the “Create Load” button
to create a concentrated force in the Step that was just
created.
Make the load a 2lb force at the tip, centered about
the quarter-chord by selecting the two points shown
and entering a magnitude of 1 for CF2.
Use the “Create Boundary Condition” button to create
a boundary condition in the same step. Select the
Mechanical Category and Choose
Symmetry/Antisymmetry/Encastre.
Select the regions shown and choose the Encastre
boundary condition.
Stresses and Strains in Local Part Coordinate Directions
In the job module create a job and simply use the default options.
Submit the job for analysis. Once the analysis is complete, right click to view the results. The “Plot Contours on Deformed Shape” button is quite useful for locating stress concentrations and areas of high strain. Use Result-> Field Output to choose which variable is displayed. The invariant variables can be of particular interest.
Because the global coordinate system is used in expressing the stress
and strain components, these variables typically are not useful.
Instead it is much more useful to consider the stress and strain components of various parts in context of the material coordinate
ABAQUS高级应用技巧(文库中的一个)
1.在abaqus command中提交分析，命令为：abaqus job=job-name (cpu=8int)interactive 需要调用用户子程序时：abaqus job=job-name user=user-sub interactive 提交作业之前可以执行命令abaqus job=job-name datacheck interactive就可以查看dat文件中的错误信息和模型分析需要的磁盘空间、内存大小等。 暂停分析作业：abaqus suspend job=job-name 在暂停的位置继续运行分析作业abaqus resume job=job-name 如果彻底中止分析作业，以后不再使用上述abaqus resume命令继续分析，可选择a.在windows任务管理器中结束进程standard.exe或explicit.exe。b.按kill按钮。C.使用命令abaqus terminate job=job-name 对于ABAQUS/Explicit分析，如果出现意外情况而导致分析作业中止，可以①使用自动恢复机制，命令为：abaqus job=job_name recover②可以运用重启动分析作业。 2.分析结果输出到dat文件中 *EL PRINT将单元上的分析结果（应力、应变、截面力等）输出到dat文件中 *NODE PRINT将节点上的分析结果...... *CONTACT PRINT将接触对的分析结果…… *MODAL PRINT在基于模态的动力分析中，将位移和相位…… 3.历史变量输出到odb文件中 *OUTPUT,HISTORY,OP=NEW,FREQUENCY=1(OP=NEW表示清除先前定义的输出设置) 如：*INTEGRATED OUTPUT表示将变量对某个面的积分结果（如面上的合力）输出到odb文件中 4.寻找帮助文档中的inp文件和.for文件： D:\Program Files\SIMULIA\Documentation\docs\v6.10\books\eif
最新总结Abaqus操作技巧总结(个人)
Abaqus操作技巧总结 打开abaqus，然后点击file——set work directory，然后选择指定文件夹，开始建模，建模完成后及时保存，在进行运算以前对已经完成的工作保存，然后点击job，修改inp文件的名称进行运算。切记切 记！！！！！！ 1、如何显示梁截面（如何显示三维梁模型） 显示梁截面：view->assembly display option->render beam profiles，自己调节系数。 2、建立几何模型草绘sketch的时候，发现画布尺寸太小了 1）这个在create part的时候就有approximate size，你可以定义合适的（比你的定性尺寸大一倍）； 2）如果你已经在sketch了，可以在edit菜单－－sketch option ——general－－grid更改 3、如何更改草图精度 可以在edit菜单－－sketch option ——dimensions－－display——decimal更改 如果想调整草图网格的疏密，可以在edit菜单－－sketch option ——general——grid spacing中可以修改。 4、想输出几何模型 part步，file，outport－－part 5、想导入几何模型？ part步，file，import－－part 6、如何定义局部坐标系 Tool－Create Datum－CSYS－－建立坐标系方式－－选择直角坐标系or柱坐标系or球坐标 7、如何在局部坐标系定义载荷
laod－－Edit load－－CSYS－Edit（在BC中同理）选用你定义的局部坐标系 8、怎么知道模型单元数目（一共有多少个单元） 在mesh步，mesh verify可以查到单元类型，数目以及单元质量一目了然，可以在下面的命令行中查看单元数。 Query---element 也可以查询的。 9、想隐藏一些part以便更清楚的看见其他part，edge等 view－Assembly Display Options——instance，打勾 10、想打印或者保存图片 File——print——file——TIFF——OK 11、如何更改CAE界面默认颜色 view->Grahphic options->viewport Background->Solid->choose the wite colour! 然后在file->save options. 12、如何施加静水压力hydrostatic load --> Pressure, 把默认的uniform 改为hydrostatic。这个仅用于standard，显式分析不支持。 13、如何检查壳单元法向 Property module/Assign/normal 14、如何输出单元体积 set步---whole model ----volume/Tickness/Corrdinate-----EVOL 15、如何显示最大、最小应力 在Visualization>Options>contour >Limits中选中Min/Max:Show Location，同样的方法可以知道具体指定值的位置。 16、如何在Visualization中显示边界条件 View——ODB display option——entity display——show boundary conditions 17、后处理有些字符（图例啊，版本号啊，坐标系啊）不想显示， viewport－viewport annotation option ，选择打勾。同样可以修改这些字体大小、位置等等。
Abaqus命令流分析
总规则 1、关键字必须以*号开头，且关键字前无空格 2、**为注释行，它可以出现在文件中的任何地方 3、当关键字后带有参数时，关键词后必须采用逗号隔开 4、参数间都采用逗号隔开 5、关键词可以采用简写的方式，只要程序能识别就可以了 6、不需使用隔行符，如果参数比较多，一行放不下，可以另起一行，只要在上一行的末尾加逗号便可以 *AMPLITUDE：定义幅值曲线 这个选项允许任意的载荷、位移和其它指定变量的数值在一个分析步中随时间的变化(或者在ABAQUS/Standard分析中随着频率的变化)。 必需的参数： NAME：设置幅值曲线的名字 可选参数： DEFINITION：设置definition=Tabular(默认)给出表格形式的幅值-时间(或幅值-频率)定义。设置DEFINITION=EQUALLY SPACED/PERIODIC/MODULATED/DECAY/SMOOTH STEP/SOLUTION DEPENDENT或BUBBLE来定义其他形式的幅值曲线。 INPUT：设置该参数等于替换输入文件名字。 TIME：设置TIME=STEP TIME(默认)则表示分析步时间或频率。TIME=TOTAL TIME表示总时间。 V ALUE：设置V ALUE=RELATIVE(默认)，定义相对幅值。V ALUE=ABSOLUTE表示绝对幅值，此时，数据行中载荷选项内的值将被省略，而且当温度是指定给已定义了温度TEMPERATURE=GRADIENTS(默认)梁上或壳单元上的节点，不能使用ABSOLUTE。 对于DEFINITION=TABULAR的可选参数： SMOOTH：设置该参数等于 DEFINITION=TABULAR的数据行 第一行 1、时间或频率 2、第一点的幅值(绝对或相对) 3、时间或频率 4、第二点的幅值(绝对或相对) 等等 基本形式： *Amplitude，name=Amp-1 0.，0.，0.2，1.5，0.4，2.，1.，1. *BEAM SECTION：当需要数值积分时定义梁截面 *BOND：定义绑定和绑定属性 *BOUNDARY：定义边界条件 用来在节点定义边界条件或在子模型分析中指定被驱动的节点。
Abaqus操作说明(可编辑修改word版)
1、创建部件： Step1：执行Part/Create 命令，或者单击左侧工具箱区域中的（create part）按钮，弹出如图1-1 所示的Create Part 对话框。在Name（部件名称）后面输入foundation，将Modeling Space（模型所在空间）设为2D Planar（二维平面），Type（类型）设为Deformable（可变形体），Base Feature（基本特征）设为Shell （壳）。单击Continue 按钮退出Create Part 对话框。ABAQUS/CAE 自动进入绘图（Sketcher）环境。 图1-1 Step2：选择绘图工具框右上方的创建矩形工具，在窗口底部的提示区显 示“Pick a starting corner for the rectangle—or enter X,Y”，输入坐标（0,0），按下Enter 键，在窗口底部的提示区显示“Pick the opposite corner for the rectangle— or enter X,Y”，输入（45.5,20），按下Enter 键。单击Done，创建part 完成，如图1-2。
图1-2 Step3：单击左侧工具箱区域中的，弹出如图1-3 的窗口。应用或 功能将groundwork（基础）在foundation 的位置绘制出来，点击Done，返回图1-4 所示窗口 图1-3 图1-4 Step4：执行Tools-Set-Create 弹出如图1-5 的Create Set 对话框，在Name 后
面输入all，点击Continue，将整个foundation 模块选中如图1-6 所示，点击Done，完成集合all 的创建。以相同的操作，将图1-4 中的小矩形区域创建Name 为remove 的集合。 图1-5 图1-6 以相同的方式分别创建名称为：groundwork，retaining，backfill 的part,依次如图1-7,1-8,1-9 所示。并分别创建于part 名称相同的集合。 图1-7
abaqus基本命令流
abaqus产生几类文件: 1. model_database_name.cae 模型信息、分析任务等。 2. model_databse_name.jnl 日志文件：包括用于复制已存储模型数据库的abaqus/cae命令 *.cae和*.jnl构成支持CAE的两个重要文件，要保证CAE下打开一个项目，这两个文件必须同时同在； 3. job_name.inp 输入文件。由abaqus Command支持计算起始文件，它也可由CAE打开； 4. job_name.dat 数据文件：文本输出信息，记录分析、数据检查、参数检查等信息。ABAQUS/Explicit的分析结果不会写入这个文件 5. job_name.sta 状态文件：包括分析过程信息 6. job_name.msg 是计算过程的详细记录，分析计算中的平衡迭代次数，计算时间，警告信息，等等可由此文件获得。用STEP模块定义 7. job_name.res 重启动文件，用STEP模块定义 8. job_name.odb 输出数据库文件，即结果文件，需要由visuliazition打开 9. job_name.fil 也为结果文件，可被其他应用程序读入的分析结果表示格式。ABAQUS/Standard记录分析结果。ABAQUS/Explicit的分析结果要写入此文件中则需要转换，convert=select 或convert=all 10.abaqus.rpy 记录一次操作中几乎所有的ABAQUS/CAE命令 11.job_name.lck 阻止并发写入输出数据库，关闭输出数据库则自行删除 12.model_database_name.rec 包含用于恢复内存中数据库的ABAQUS/CAE命令 13.job_name.ods 场输出变量的临时操作运算结果，自动删除 14.job_name.ipm 内部过程信息文件：启动ABAQUS/CAE分析时开始写入，记录了从ABAQUS/STANDARD 或ABAQUS/Explicit到ABAQUS/CAE的过程日志
Abaqus基本操作中文教程
Abaqus基本操作中文教程
目录 1 Abaqus 软件基本操作 .................... 常用的快捷键 .......................... 单位的一致性 .......................... 分析流程九步走 ....................... 几何建模（Part） ..................... 属性设置（Property） ................... 建立装配体（Assembly） ................... 定义分析步（Step） ................... 相互作用（In teracti on................ ） 载荷边界（Load） ..................... 划分网格（Mesh） .................. 作业（Job） ...................... 可视化（Visualization ）................. 1 Abaqus软件基本操作 常用的快捷键 「旋转模型一Ctrl+Alt+ 鼠标左键 于平移模型一Ctrl+Alt+鼠标中键 " 缩放模型一Ctrl+Alt+ 鼠标右键 单位的一致性 CAE软件其实是数值计算软件，没有单位的概念，常用的国际单位制如下表1所示，建议采用SI （mm）进行建模。
国际单位制 SI (m) SI (mm) 「长度 m mm 力 N N 质量 kg t 时间 s s 应力 2 Pa (N/m ) 2 MPa (N/mm) 质量密度 kg/m 3 3 t/mm 加速度 m/s 2 mm/s 例如，模型的材料为钢材，采用国际单位制 SI （m ）时，弹性模量为 m,重力加速度m/s 2 ，密度为7850 kg/m 3,应力Pa;采用国际单位制SI （mm ） 时，弹性模量为 口金 重力加速度 9800 mm/s 2 ，密度为7850e-12??T/mm 5, 应力MPa 分析流程九步走 几何建模（Part 属性设置（Property ） 建立装配体（Assembly ） T 定义分析步（Step ） T 相互作用 （Interaction ）宀载荷边界（Load ） T 划分网格 （Mesh ）T 作业（Job ）T 可视化（Visualization ） ' 以上给出的是软件 ! 常规的建模和分析的流 程，用户可以根据自己 ；的建模习惯进行调整。 I 另外，草图模块可以进 !行参数化建模，建议用 」户可以参考相关资料进--- 几何建模（Part ） 关键步骤的介绍： 部件（Part ）导入 Pro/E 等CAD 软件建好的模型后，另存成 iges 、sat 、step 等格式； 然后导入Abaqus 可以直接用，实体模型的导入通常采用 sat 格式文件导 謝t fti5 忧化 fkit 可泯忧
abaqus cmd提交小结
cmd提交inp文件小结 有时候需要用command提交inp文件（比如少数keywords不为CAE识别），以下是对aba版中提交inp中出现问题的一个小结。（假设将运行的inp是jobname1.inp jobname2.inp等等，也假设这些inp是可以运行的。 1、提交方式： 在WINDOWS中点击 [开始] → [程序] → [ABAQUS 6.x] → [ABAQUS Command]，然后在DOS窗口中输入： 提交任务：abaqus job=jobname1 int(int就是interactive） 任务暂停：abaqus suspend job=jobname1 int （可恢复） 恢复运算：abaqus resume job=jobname1 int（从上次分析结束的地方重新开始分析） 杀死任务：abaqus terminate job=jobname1 int （一般不可恢复）,杀死任务不可恢复，但是如果有restart文件的话，可以restart继续计算: restart重启计算: abaqus job=xnewx oldjob=xoldx int 打开CAE界面：abaqus cae %（aba后处理界面即出现） 打开viewer后处理界面：abaqus viewer %（aba后处理界面即出现） 查看aba帮助文件：abaqus doc %（aba帮助文件即在默认浏览器中出现） 查看cmd命令帮助：abaqus help %（这个太有用了，通过这个可以找到以上所有命令。） 2、几点说明： 1）Old job files exist. Overwrite?
abaqus关键字的中文说明1
(一)总规则 1、关键词必须以*符号开头，且关键词前无空格； 2、**为解释行，它可以出现在文件中的任何地方； 2、当关键词后带有参数时，关键词后必须采用逗号相隔； 3、参数间采用都好相隔； 4、关键词可以采用简写的方式，只要程序能够识别就可以了； 5、没有隔行符，如果参数比较多，一行放不下，可以另起一行，只要在上 一行的末尾加逗号便可以； (二)建模部分关键词 在我的学习过程中，是将ansys的模型倒入abaqus的，最简单的方法就是在ansys中提取单元与节点信息，将提取出来的信息在abaqus中形成有限元模型。因此首先从节点的关键词来开始吧。 1、*heading 描述行 这是.inp文件的开头语，相当于你告诉abaqus，我要进行工程建模与分析了。另起一行可以对模型进行描述，这个描述可有可无，只是为了以后阅读的方便。abaqus中对每个模块没有清晰的界定，根据关键词的不同来判别进入哪个模块。而在ansys中对模块要求比较严格，如/prep7为前处理模块，/solu为求解模块,/post26为后处理模块。 2、*node,<input>,<nset=结点集名称>,<system> 数据行 (a) 通知软件，我要开始建立结点了。<>的意思是<>中的内容可有可无，这两个也称为node 命令的参数。 (b) <input>: 指出包含结点所在的文件名称，包括文件的扩展名。当这项参数省略时，程序认为*node下的数据为所需要建立的结点。 (c) <nset=结点集名称>: 熟悉ansys的人应该了解，为了选择的方便对某些合适的点可以采用cm命令建立component(cm,结点集名称,node)，在abaqus中<nset=结点集名称>与此相对应。 (d) <system>: 坐标系标识参数，system=r（缺省）定义坐标系为笛卡尔坐标系，system=c定义坐标系为柱面坐标系，system=s定义坐标系为球面坐标系。这个坐标系为局部坐标系. 3、*element,type=单元类型,<elset=>,<input> 数据行 (a) 建立单元关键词；这一命令将单元类型，单元特性，单元结点以及单元集这几个过程全部统一起来。 (b) *element与type=单元类型必须同时使用，否则程序不知道你的单元是什么形状，哪种类型。在ansys中对模型划分网格，你需要做两步：指定单元类型（et），确定单元特性（keyopt）,然后建立单元;在abaqus中单元类型与单元特性通过单元的名称可以完全确定下来。 (c) <elset=>这个参数来确定单元集的名称; ansys中需要采用（cm,,elem）来定义。 (d) <input> 指出包含单元信息的文件名称,包括文件的扩展名。
abaqus常用命令
abaqus常用指令小结 *HEADING 定义分析的标题，输出地显示示窗口，无参数。 数据行： 1、标题 标题可以是几行长，但只有第一行的前80个字符会被保存并显示。 *RESTART 保存重用数据及分析结果 本选项可能导致产生大量数据。用于控制重启数据的要求读，至少有以下一个参数：READ：本次分析是对前次分析的重启，基本模型定义数据（单元、材料、结点）本次重启不能更改；但是单元集、结点集、振幅表可以增加，本部件并发产生的历史数据可能改变已分析产生的历史数据。 WRITE：本次分析将写入重启数据。 如果使用了READ参数以下能数可选： ENDSTEP：用户希望在该点终止现在的STEP与STED相对使用 INC：使本参数等于“STEP”参数定义的步骤数之内的一个增量，在读步后可以重新进行分析 STEP：本参数等于重启时的步骤数，省略时分析在最后一步重启 如果使用了WRITE参数以下参数可选 FREQVENCY：重启信息数据写入的频率，如FREQVENCY=2则在第2、4、6…步时写入数据。FREQVENCY=0则停止重启数据的写入 OVERLAY：覆盖上一步所产生的数据，省略则写入每步的数据 *NODE 定义结点，用于通过坐标直接定义结点。 可选参数 INPVT：等于外部数据文件名 NSET：等于节点集的名称 SYSTEM：缺省SYSYEM=R代表坐标直角点（X、Y、Z），SYSTEM=C代表圆柱坐标（R、θ、Z），SYSTEM=S代表球坐标（R、θ、?） 定义节点的数据行： 第一行数据： 1、节点号 2、节点坐标第一分量 3、节点坐标第二分量 4、节点坐标第三分量 5、与标准节点间的第一方向导弦（可选参数） 6、与标准节点间的第二方向导弦（可选参数），圆柱坐标或球形坐标数为角度（度数） 7、与标准节点间的第三方向导弦（可选参数），圆柱坐标或球形坐标数为角度（度数） 重复以上数据行定义多个结点 *NGEN
超级经典abaqus命令流分析
经验值 1960 美味虾36 注册日期 2005-4-13 最近登陆 2011-12-22 来自江西－九江 状态2009-8-20 16:53 t T#1 ABAQUS帮助里关键字（keywords）翻译 总规则 1、关键字必须以*号开头，且关键字前无空格 2、**为注释行，它可以出现在文件中的任何地方 3、当关键字后带有参数时，关键词后必须采用逗号隔开 4、参数间都采用逗号隔开 5、关键词可以采用简写的方式，只要程序能识别就可以了 6、不需使用隔行符，如果参数比较多，一行放不下，可以另起一行，只要在上一行的末尾加逗号便可以 *AMPLITUDE：定义幅值曲线 这个选项允许任意的载荷、位移和其它指定变量的数值在一个分析步中随时间的变化(或者在 ABAQUS/Standard分析中随着频率的变化)。 必需的参数： NAME：设置幅值曲线的名字 可选参数： DEFINITION：设置definition=Tabular(默认)给出表格形式的幅值-时间(或幅值-频率)定义。设置DEFINITION=EQUALLY SPACED/PERIODIC/MODULATED/DECAY/SMOOTH STEP/SOLUTION DEPENDENT或BUBBLE来定义其他形式的幅值曲线。 INPUT：设置该参数等于替换输入文件名字。 TIME：设置TIME=STEP TIME(默认)则表示分析步时间或频率。TIME=TOTAL TIME表示总时间。 VALUE：设置VALUE=RELATIVE(默认)，定义相对幅值。VALUE=ABSOLUTE表示绝对幅值，此时，数据行中载荷选项内的值将被省略，而且当温度是指定给已定义了温度TEMPERATURE=GRADIENTS(默认)梁上或壳单元上的节点，不能使用ABSOLUTE。 对于DEFINITION=TABULAR的可选参数： SMOOTH：设置该参数等于 DEFINITION=TABULAR的数据行 第一行 1、时间或频率 2、第一点的幅值(绝对或相对) 3、时间或频率 4、第二点的幅值(绝对或相对) 等等 基本形式： *Amplitude，name=Amp-1
abaqus经典问题
Q:预拉钢筋怎样施加预应力，请各位指点~~~~ Q:我在文档里看到要在inp文件定义一个rebar，但是rebar只能用于shell, membrane, and solid elements 。我现在想做的是一个预应力拉索，不是镶嵌在shell, membrane, and solid 这些单元里的，而是独立的一根拉锁。拉索单元打算用truss,但是怎样在truss上使用rebar啊？请高手指点 还有个问题，我看到别人的inp文件，如下： *rebar,element=continuum,material=rebar2,name=ubar top1,1.005e-4,0.15,0.0,0.5,1 第二行第一个是setname（top1),第二个是rebar的截面面积（1.005e-4)，那第三、第四、第五是指什么？（0.15,0,0.5),最后一个应该是方向，是1方向。哪位高人指点下第三、四、五项分别代表什么？ A:施加预应力 *initinial conditions,type=stress,rebar elset,rebar name,所施加预应力的值 ,另prestress hold 为保持所施加的预应力的值不变，我的理解是防止别的构件吃掉所施加的预应力，造成所施加预应力的损失。使用了这个命令之后就避免了这种损失，保证所施加的预应力都施加到了钢筋上。 A:谢谢指点，你所说的应该是把预应力加在rebar上面，但我发觉truss单元不能定义成rebar，其实是我多想了，truss本来就可以当拉索，实际工程中加预应力只是为了使钢绞线拉紧，起到张拉作用，而在abaqus里，truss本身就是拉紧的，不用施加预应力 A:我知道模拟加强筋的时候需要用rebar，但钢筋确实可以直接用truss来模拟 ,而lz所说的预应力其实其实只是施工时的张力而并不是真正意义上的预应力，比如螺栓预应力之类的。如果是索的话可能是要施加预应力的，仅个人看法。 Q:请教：做一个空间钢框架结构，梁柱用梁元，板采用壳元，打算采用tie命令（共用节点），但不知该如何实现？ A:我想可以用*equation实现，共用节点的约束情况自己在这一命令下定义。 A:我因为用命令比较多，但是用cae我想一样，在CAE里进入命令编辑器，然后编辑就是了，写入*equation命令，指定约束的自由度（这个看一下标准手册，写得很清楚） Q:“Response spectrum analysis（响应谱分析）与Modal dynamic analysis（模态动力分析）区别在什么地方？如Response spectrum analysis可以进行结构设计？但Modal dynamic analysis是用来干什么的阿？ A:就我知道的，modal dynamic analysis应该是振型分解法做动力解析。分解为单自由度体系再取有限个进行组合求反应。 Q:abaqus如何施加地震荷载？ A:可以参考abaqus 6.3的例子，Seismic Analysis of a Concrete Gravity Dam 可以使用： 1。*amplitude, name=amp, input=seismicdata.dat输入地震波 2。*boundary, type=acceleration, amplitude=amp 来施加荷载。 在
ABAQUS命令汇总及参数的默认设置
ABAQUS命令汇总及参数的默认设置(ABAQUS Command Summary and Command line default parameters) 2011-02-13 20:33:50| 分类：ABAQUS | 标签：|字号大中小订阅 Command summary abaqus job=job-name [analysis | datacheck | parametercheck | continue | convert={select | odb | state | all} | recover | syntaxcheck | information={environment | local | memory | release | support | system | all}] [input=input-file] [user={source-file | object-file}] [oldjob=oldjob-name] [fil={append | new}] [globalmodel={results file-name | output database file-name}] [cpus=number-of-cpus] [parallel={domain | loop}] [domains=number-of-domains] [mp_mode={mpi | threads}] [standard_parallel={all | solver}] [memory=memory-size] [interactive | background | queue=[queue-name][after=time]] [double={explicit | both}] [scratch=scratch-dir] [output_precision={single | full}] [madymo=MADYMO-input-file] [port=co-simulation port-number] [host=co-simulation hostname] [timeout=co-simulation timeout value in seconds] [unconnected_regions={yes | no}] Command line default parameters The following parameters provide default values for various settings that would otherwise have to be specified on the command line (see “Execution procedure for Abaqus/Standard and Abaqus/Explicit,” Section 3.2.2). Values given on the command line override values specified in the environment files. cpus Number of processors to use if parallel processing is available. The default is 1.
第二讲 在Abaqus 中编写脚本(全面)
在 Abaqus 中编写脚本
第2讲
? Dassault Systèmes, 2008
L2.2
概要
? Abaqus 中的脚本接口 ? Abaqus 中的对象模型 ? Abaqus 中的数据类型 ? Abaqus 中的模块 ? Abaqus 的默认设置 ? 交互式输入 ? 例子 ? 习题
Introduction to Python and Scripting in Abaqus
? Dassault Systèmes, 2008
Abaqus 中的脚本接口
? Dassault Systèmes, 2008
L2.4
Abaqus 中的脚本接口
? Abaqus 中的脚本接口 ? Abaqus 中的脚本接口（ASI）是在 Python 应用程序的基础上开发的。 ? 基于 Abaqus 中的脚本接口，用户可以实现下列功能： ? 可以自定义 Abaqus 环境文件（ abaqus_v6.env ） ? 创建宏来自动进行前后处理 ? 读取或写出输出数据库文件（ODB 文件） ? 进行参数分析 ? 创建 Abaqus 插件程序
Introduction to Python and Scripting in Abaqus
? Dassault Systèmes, 2008
L2.5
Abaqus 中的脚本接口
? 执行脚本接口命令 ? 可以通过 GUI、命令行接口或脚 本执行命令。 ? 经过内核的命令构成了所创建的 模型。
Abaqus/CAE
1
GUI
command line interface (CLI) commands
2
3
script
Python interpreter
replay files
Abaqus/CAE kernel
input file
Abaqus/Standard Abaqus/Explicit
output database file
Introduction to Python and Scripting in Abaqus
? Dassault Systèmes, 2008
L2.6
Abaqus 中的脚本接口
? 术语 ? 信息提示区和命令行窗口 ? 用 TAB 键进行二者之间 的切换
信息提示区
命令行窗口（CLI）
当前显示的是命令行窗口中的内容
Introduction to Python and Scripting in Abaqus
? Dassault Systèmes, 2008