ABAQUS_Standard用户材料子程序实例-Johnson-Cook金属本构模型卢剑锋庄茁
abaqus金属切削参数
abaqus金属切削参数金属非稳态切削材料属性1、工件、切屑密度：8250弹性：杨氏模量2.2e11，泊松比0.3膨胀：膨胀系数温度1. 1.23e-5 3002 1.26e-5 4003 1.37e-5 500传导率：传导率温度1 12.47 2932 12.73 3933 13.04 4934 13.53 5935 13.79 6936 14.47 7937 15.05 893非弹性热份额：0.9塑性：硬化Johnson-cook，依赖于变化率C=0.0157，Epsilon dot zero=1A B N M 融化温度过渡温度1 2.18e8 7.04e8 0.62 0.93 850 300比热：2032、分离线剪切损伤：断裂应变2，损伤演化：破坏位移4e-63、刀具传导率：46质量密度：15000弹性：杨氏模量8e11，泊松比0.2膨胀：4.7e-6比热：20000截面属性均质实体，平面应力/应变厚度0.002分析步切削分析步：动力，温度-位移，显式时间长度：2.5e-5接触属性1、切向行为：粗糙；法向行为：不允许接触后分离；热传导2、切向行为：无摩擦；法向行为：允许接触后分离；热传导；生热：分布在从表面上的换热百分比0.9热传导：conductance clearance10000000 00 0.00013、切向行为：无摩擦；法向行为：允许接触后分离相互作用初始、表面与表面接触、接触属性1：切屑下&分离线上，工件上&分离线下（罚接触方法、有限滑移）切削、表面与表面接触、接触属性2：刀具&切屑下，工件上&切屑下（运动接触法、有限滑移）切削、自接触、接触属性3：切屑表面（运动接触法）幅度曲线时间/频率幅值1 0 02 2e-6 13 2.3e-5 14 2.5e-5 0进给速度：40温度场工件、切屑、分离线：300刀具：600网格网格控制属性：工件（四边形、结构）；刀具（三角形、自由）单元类型：工件（CPE4RT: 四结点热耦合平面应变四边形单元, 双线性位移和温度, 减缩积分, 沙漏控制.）；刀具（CPE3T: 三结点平面应变热耦合三角形单元, 位移和温度均线性.）金属稳态切削材料属性1、工件、切屑密度：7850弹性：杨氏模量2.08e11，泊松比0.3 膨胀：传导率：44.5非弹性热份额：0.9塑性：硬化Johnson-cook ，依赖于变化率C=0.014，Epsilon dot zero=1 比热：5022、刀具：解析刚体截面属性均质实体，平面应力/应变厚度1分析步初始分析步切削分析步：动力，显式时间长度：0.08接触属性切向行为：罚摩擦（各项同性摩擦系数0.4）；法向行为相互作用切削分析步、表面与表面接触、接触属性：刀具&工件幅度曲线时间/频率幅值 1 0 0 2 0.001 1 3 0.079 1膨胀系数温度1. 1.23e-5 293 2 1.26e-5 523 3 1.37e-5773A B N M 融化温度过渡温度 1 1.15e9 7.39e8 0.26 1.03 1723 2984 0.08 0进给速度：1温度场工件、刀具：298网格网格控制属性：工件（四边形、结构）单元类型：工件（CPE4RT: 四结点热耦合平面应变四边形单元, 双线性位移和温度, 减缩积分, 沙漏控制.）。
abaqus1用户材料子程序
19 ABAQUS用户材料子程序(UMAT)虽然ABAQUS为用户提供了大量的单元库和求解模型，使用户能够利用这些模型处理绝大多数的问题；但是现实世界毕竟十分复杂，ABAQUS不可能把所有可能出现的问题都包含进去。
所以ABAQUS提供了大量的用户子程序（User Subroutine）。
用户子程序允许用户在找不到合适模型的情况下自行定义符合自己问题的模型。
这些用户子程序涵盖了建模从载荷到单元的几乎各个部分。
ABAQUS为用户提供的这个接口，允许用户通过自定义的子程序定制ABAQUS，以实现特定的功能。
用户子程序具有以下的功能和特点：（1）如果ABAQUS的一些固有选项模型功能有限；用户子程序可以提高ABAQUS中这些选项的功能；（2）通常用户子程序是用FORTRAN语言的代码写成；（3）它可以以几种不同的方式包含在模型中；（4）由于它们没有存储在restart文件中，如果需要的话，可以在重新开始运行时修改它；（5）在某些情况下它可以利用ABAQUS允许的已有程序。
要在模型中包含用户子程序，可以利用ABAQUS执行程序，在abaqus执行程序中应用user选项指明包含这些子程序的FORTRAN源程序或者目标程序的名字。
提示：ABAQUS的输入文件除了可以通过ABAQUS/CAE的作业模块中提交运行外，还可以在ABAQUS Command窗口中输入ABAQUS执行程序直接运行：ABAQUS job=输入文件名 user=用户子程序的Fortran文件名ABAQUS/Standard和ABAQUS/Explicit都支持用户子程序功能，但是他们所支持的用户子程序种类不尽相同，读者在需要使用时请注意查询手册。
在接下来的最后两章里，我们将讨论两种常用的用户子程序——用户材料子程序和用户单元子程序。
本章将通过在ABAQUS/Standard中创建Johnson-Cook的材料模型，对编写Standard 的用户材料子程序UMAT进行一个简单介绍。
Abaqus User Subroutines Reference Guide 用户材料子程序帮助文档
1.1.41 UMATUser subroutine to define a material's mechanical behavior.Product: Abaqus/StandardWarning: The use of this subroutine generally requires considerable expertise. Y ou arecautioned that the implementation of any realistic constitutive model requires extensivedevelopment and testing. Initial testing on a single-element model with prescribedtraction loading is strongly recommended.References“User-defined mechanical material behavior,” Section 26.7.1 of the Abaqus Analysis User's Guide“User-defined thermal material behavior,” Section 26.7.2 of the Abaqus Analysis User's Guide*USER MA TERIAL“S D V I N I,” Section 4.1.11 of the Abaqus V erification Guide“U M A T and U H Y P E R,” Section 4.1.21 of the Abaqus V erification GuideOv erv iewUser subroutine U M A T:can be used to define the mechanical constitutive behavior of a material;will be called at all material calculation points of elements for which the material definition includes auser-defined material behavior;can be used with any procedure that includes mechanical behavior;can use solution-dependent state variables;must update the stresses and solution-dependent state variables to their values at the end of theincrement for which it is called;must provide the material Jacobian matrix, , for the mechanical constitutive model;can be used in conjunction with user subroutine U S D F L D to redefine any field variables before they are passed in; andis described further in “User-defined mechanical material behavior,” Section 26.7.1 of the AbaqusAnalysis User's Guide.Storage of stress and strain componentsIn the stress and strain arrays and in the matrices D D S D D E, D D S D D T, and D R P L D E, direct components are stored first, followed by shear components. There are N D I direct and N S H R engineering shear components. The order of the components is defined in “Conventions,” Section 1.2.2 of the Abaqus Analysis User's Guide. Since the number of active stress and strain components varies between element types, the routine must be coded toprovide for all element types with which it will be used.Defining local orientationsIf a local orientation (“Orientations,” Section 2.2.5 of the Abaqus Analysis User's Guide) is used at the same point as user subroutine U M A T, the stress and strain components will be in the local orientation; and, in the case of finite-strain analysis, the basis system in which stress and strain components are stored rotates with the material.StabilityY ou should ensure that the integration scheme coded in this routine is stable—no direct provision is made to include a stability limit in the time stepping scheme based on the calculations in U M A T.Convergence rateD D S D DE and—for coupled temperature-displacement and coupled thermal-electrical-structural analyses—D D S D D T, D R P L D E, and D R P L D T must be defined accurately if rapid convergence of the overall Newton scheme is to be achieved. In most cases the accuracy of this definition is the most important factor governing the convergence rate. Since nonsymmetric equation solution is as much as four times as expensive as the corresponding symmetric system, if the constitutive Jacobian (D D S D D E) is only slightly nonsymmetric (for example, a frictional material with a small friction angle), it may be less expensive computationally to use a symmetric approximation and accept a slower convergence rate.An incorrect definition of the material Jacobian affects only the convergence rate; the results (if obtained) are unaffected.Special considerations for various element typesThere are several special considerations that need to be noted.A v ailability of deformation gradientThe deformation gradient is available for solid (continuum) elements, membranes, and finite-strain shells(S3/S3R, S4, S4R, SAXs, and SAXAs). It is not available for beams or small-strain shells. It is stored as a 3× 3 matrix with component equivalence D F G R D0(I,J). For fully integrated first-order isoparametric elements (4-node quadrilaterals in two dimensions and 8-node hexahedra in three dimensions) the selectively reduced integration technique is used (also known as the technique). Thus, a modified deformation gradientis passed into user subroutine U M A T. For more details, see “Solid isoparametric quadrilaterals and hexahedra,”Section 3.2.4 of the Abaqus Theory Guide.Beams and shells that calculate transv erse shear energyIf user subroutine U M A T is used to describe the material of beams or shells that calculate transverse shear energy, you must specify the transverse shear stiffness as part of the beam or shell section definition to define the transverse shear behavior. See “Shell section behavior,” Section 29.6.4 of the Abaqus Analysis User's Guide, and “Choosing a beam element,” Section 29.3.3 of the Abaqus Analysis User's Guide, for informationon specifying this stiffness.Open-section beam elementsWhen user subroutine U M A T is used to describe the material response of beams with open sections (for example, an I-section), the torsional stiffness is obtained aswhere J is the torsional constant, A is the section area, k is a shear factor, and is the user-specified transverse shear stiffness (see “Transverse shear stiffness definition” in “Choosing a beam element,” Section29.3.3 of the Abaqus Analysis User's Guide).E lements w ith hourglassing modesIf this capability is used to describe the material of elements with hourglassing modes, you must define the hourglass stiffness factor for hourglass control based on the total stiffness approach as part of the element section definition. The hourglass stiffness factor is not required for enhanced hourglass control, but you can define a scaling factor for the stiffness associated with the drill degree of freedom (rotation about the surface normal). See “Section controls,” Section 27.1.4 of the Abaqus Analysis User's Guide, for information on specifying the stiffness factor.Pipe-soil interaction elementsThe constitutive behavior of the pipe-soil interaction elements (see “Pipe-soil interaction elements,” Section 32.12.1 of the Abaqus Analysis User's Guide) is defined by the force per unit length caused by relative displacement between two edges of the element. The relative-displacements are available as “strains” (S T R A N and D S T R A N). The corresponding forces per unit length must be defined in the S T R E S S array. The Jacobian matrix defines the variation of force per unit length with respect to relative displacement.For two-dimensional elements two in-plane components of “stress” and “strain” exist (N T E N S=N D I=2, andN S H R=0). For three-dimensional elements three components of “stress” and “strain” exist (N T E N S=N D I=3, and N S H R=0).Large volume changes with geometric nonlinearityIf the material model allows large volume changes and geometric nonlinearity is considered, the exact definition of the consistent Jacobian should be used to ensure rapid convergence. These conditions are most commonly encountered when considering either large elastic strains or pressure-dependent plasticity. In the former case, total-form constitutive equations relating the Cauchy stress to the deformation gradient are commonly used; in the latter case, rate-form constitutive laws are generally used.For total-form constitutive laws, the exact consistent Jacobian is defined through the variation in Kirchhoff stress:Here, J is the determinant of the deformation gradient, is the Cauchy stress, is the virtual rate of deformation, and is the virtual spin tensor, defined asFor rate-form constitutive laws, the exact consistent Jacobian is given byUse with incompressible elastic materialsFor user-defined incompressible elastic materials, user subroutine U H Y P E R should be used rather than user subroutine U M A T. In U M A T incompressible materials must be modeled via a penalty method; that is, you must ensure that a finite bulk modulus is used. The bulk modulus should be large enough to model incompressibility sufficiently but small enough to avoid loss of precision. As a general guideline, the bulk modulus should be about – times the shear modulus. The tangent bulk modulus can be calculated fromIf a hybrid element is used with user subroutine U M A T, Abaqus/Standard will replace the pressure stress calculated from your definition of S T R E S S with that derived from the Lagrange multiplier and will modify the Jacobian appropriately.For incompressible pressure-sensitive materials the element choice is particularly important when using user subroutine U M A T. In particular, first-order wedge elements should be avoided. For these elements the technique is not used to alter the deformation gradient that is passed into user subroutine U M A T, which increases the risk of volumetric locking.Increments for which only the Jacobian can be definedAbaqus/Standard passes zero strain increments into user subroutine U M A T to start the first increment of all the steps and all increments of steps for which you have suppressed extrapolation (see “Defining an analysis,”Section 6.1.2 of the Abaqus Analysis User's Guide). In this case you can define only the Jacobian (D D S D D E).Utility routinesSeveral utility routines may help in coding user subroutine U M A T. Their functions include determining stress invariants for a stress tensor and calculating principal values and directions for stress or strain tensors. These utility routines are discussed in detail in “Obtaining stress invariants, principal stress/strain values and directions, and rotating tensors in an Abaqus/Standard analysis,” Section 2.1.11.U ser subroutine interfaceS U B R O U T I N E U M A T(S T R E S S,S T A T E V,D D S D D E,S S E,S P D,S C D,1R P L,D D S D D T,D R P L D E,D R P L D T,2S T R A N,D S T R A N,T I M E,D T I M E,T E M P,D T E M P,P R E D E F,D P R E D,C M N A M E,3N D I,N S H R,N T E N S,N S T A T V,P R O P S,N P R O P S,C O O R D S,D R O T,P N E W D T,4C E L E N T,D F G R D0,D F G R D1,N O E L,N P T,L A Y E R,K S P T,K S T E P,K I N C)CI N C L U D E'A B A_P A R A M.I N C'C H A R A C T E R*80C M N A M ED I ME N S I O N S T R E S S(N T E N S),S T A T E V(N S T A T V),1D D S D D E(N T E N S,N T E N S),D D S D D T(N T E N S),D R P L D E(N T E N S),2S T R A N(N T E N S),D S T R A N(N T E N S),T I M E(2),P R E D E F(1),D P R E D(1),3P R O P S(N P R O P S),C O O R D S(3),D R O T(3,3),D F G R D0(3,3),D F G R D1(3,3)user coding to define D D S D D E,S T R E S S,S T A T E V,S S E,S P D,S C Dand, if necessary,R P L,D D S D D T,D R P L D E,D R P L D T,P N E W D TR E T U R NE N DV ariables to be definedIn all situationsD D S D D E(N TE N S,N T E N S)Jacobian matrix of the constitutive model, , where are the stress increments and are the strain increments. D D S D D E(I,J) defines the change in the I th stress component at the end of the time increment caused by an infinitesimal perturbation of the J th component of the strain increment array.Unless you invoke the unsymmetric equation solution capability for the user-defined material,Abaqus/Standard will use only the symmetric part of D D S D D E. The symmetric part of the matrix iscalculated by taking one half the sum of the matrix and its transpose.S T R E S S(N T E N S)This array is passed in as the stress tensor at the beginning of the increment and must be updated in this routine to be the stress tensor at the end of the increment. If you specified initial stresses (“Initial conditions in Abaqus/Standard and Abaqus/Explicit,” Section 34.2.1 of the Abaqus Analysis User's Guide), this array will contain the initial stresses at the start of the analysis. The size of this array depends on the value of N T E N S as defined below. In finite-strain problems the stress tensor has already been rotated to account for rigid body motion in the increment before U M A T is called, so that only the corotational part of the stress integration should be done in U M A T. The measure of stress used is “true” (Cauchy) stress.S T A T E V(N S T A T V)An array containing the solution-dependent state variables. These are passed in as the values at thebeginning of the increment unless they are updated in user subroutines U S D F L D or U E X P A N, in which case the updated values are passed in. In all cases S T A T E V must be returned as the values at the end of the increment. The size of the array is defined as described in “Allocating space” in “User subroutines:overview,” Section 18.1.1 of the Abaqus Analysis User's Guide.In finite-strain problems any vector-valued or tensor-valued state variables must be rotated to account for rigid body motion of the material, in addition to any update in the values associated with constitutivebehavior. The rotation increment matrix, D R O T, is provided for this purpose.S S E,S P D,S C DSpecific elastic strain energy, plastic dissipation, and “creep” dissipation, respectively. These are passed in as the values at the start of the increment and should be updated to the corresponding specific energy values at the end of the increment. They have no effect on the solution, except that they are used forenergy output.Only in a fully coupled thermal-stress or a coupled thermal-electrical-structural analysisR P LV olumetric heat generation per unit time at the end of the increment caused by mechanical working of the material.D D S D D T(N TE N S)V ariation of the stress increments with respect to the temperature.D R P L D E(N TE N S)V ariation of R P L with respect to the strain increments.D R P L D TV ariation of R P L with respect to the temperature.Only in a geostatic stress procedure or a coupled pore fluid diffusion/stress analysis for pore pressure cohesive elementsR P LR P L is used to indicate whether or not a cohesive element is open to the tangential flow of pore fluid. Set R P L equal to 0 if there is no tangential flow; otherwise, assign a nonzero value to R P L if an element is open.Once opened, a cohesive element will remain open to the fluid flow.V ariable that can be updatedP N E W D TRatio of suggested new time increment to the time increment being used (D T I M E, see discussion later in this section). This variable allows you to provide input to the automatic time incrementation algorithms in Abaqus/Standard (if automatic time incrementation is chosen). For a quasi-static procedure the automatic time stepping that Abaqus/Standard uses, which is based on techniques for integrating standard creep laws (see “Quasi-static analysis,” Section 6.2.5 of the Abaqus Analysis User's Guide), cannot becontrolled from within the U M A T subroutine.P N E W D T is set to a large value before each call to U M A T.If P N E W D T is redefined to be less than 1.0, Abaqus/Standard must abandon the time increment andattempt it again with a smaller time increment. The suggested new time increment provided to theautomatic time integration algorithms is P N E W D T × D T I M E, where the P N E W D T used is the minimum value for all calls to user subroutines that allow redefinition of P N E W D T for this iteration.If P N E W D T is given a value that is greater than 1.0 for all calls to user subroutines for this iteration and the increment converges in this iteration, Abaqus/Standard may increase the time increment. The suggestednew time increment provided to the automatic time integration algorithms is P N E W D T × D T I M E, where the P N E W D T used is the minimum value for all calls to user subroutines for this iteration.If automatic time incrementation is not selected in the analysis procedure, values of P N E W D T that aregreater than 1.0 will be ignored and values of P N E W D T that are less than 1.0 will cause the job to terminate. V ariables passed in for informationS T R A N(N T E N S)An array containing the total strains at the beginning of the increment. If thermal expansion is included in the same material definition, the strains passed into U M A T are the mechanical strains only (that is, thethermal strains computed based upon the thermal expansion coefficient have been subtracted from the total strains). These strains are available for output as the “elastic” strains.In finite-strain problems the strain components have been rotated to account for rigid body motion in the increment before U M A T is called and are approximations to logarithmic strain.D S T R A N(N TE N S)Array of strain increments. If thermal expansion is included in the same material definition, these are the mechanical strain increments (the total strain increments minus the thermal strain increments).T I M E(1)V alue of step time at the beginning of the current increment or frequency.T I M E(2)V alue of total time at the beginning of the current increment.D T I M ETime increment.T E M PTemperature at the start of the increment.D TE M PIncrement of temperature.P R E D E FArray of interpolated values of predefined field variables at this point at the start of the increment, based on the values read in at the nodes.D P RE DArray of increments of predefined field variables.C M N A M EUser-defined material name, left justified. Some internal material models are given names starting with the “ABQ_” character string. To avoid conflict, you should not use “ABQ_” as the leading string for C M N A M E. N D INumber of direct stress components at this point.N S H RNumber of engineering shear stress components at this point.N T E N SSize of the stress or strain component array (N D I + N S H R).N S T A T VNumber of solution-dependent state variables that are associated with this material type (defined asdescribed in “Allocating space” in “User subroutines: overview,” Section 18.1.1 of the Abaqus Analysis User's Guide).P R O P S(N P R O P S)User-specified array of material constants associated with this user material.N P R O P SUser-defined number of material constants associated with this user material.C O O RD SAn array containing the coordinates of this point. These are the current coordinates if geometricnonlinearity is accounted for during the step (see “Defining an analysis,” Section 6.1.2 of the Abaqus Analysis User's Guide); otherwise, the array contains the original coordinates of the point.D R O T(3,3)Rotation increment matrix. This matrix represents the increment of rigid body rotation of the basis system in which the components of stress (S T R E S S) and strain (S T R A N) are stored. It is provided so that vector-or tensor-valued state variables can be rotated appropriately in this subroutine: stress and straincomponents are already rotated by this amount before U M A T is called. This matrix is passed in as a unit matrix for small-displacement analysis and for large-displacement analysis if the basis system for thematerial point rotates with the material (as in a shell element or when a local orientation is used).C E L E N TCharacteristic element length, which is a typical length of a line across an element for a first-order element;it is half of the same typical length for a second-order element. For beams and trusses it is a characteristic length along the element axis. For membranes and shells it is a characteristic length in the referencesurface. For axisymmetric elements it is a characteristic length in the plane only. For cohesiveelements it is equal to the constitutive thickness.D F G R D0(3,3)Array containing the deformation gradient at the beginning of the increment. If a local orientation is defined at the material point, the deformation gradient components are expressed in the local coordinate system defined by the orientation at the beginning of the increment. For a discussion regarding the availability of the deformation gradient for various element types, see “Availability of deformation gradient.”D F G R D1(3,3)Array containing the deformation gradient at the end of the increment. If a local orientation is defined at the material point, the deformation gradient components are expressed in the local coordinate system defined by the orientation. This array is set to the identity matrix if nonlinear geometric effects are not included in the step definition associated with this increment. For a discussion regarding the availability of thedeformation gradient for various element types, see “Availability of deformation gradient.”N O E LElement number.N P TIntegration point number.L A Y E RLayer number (for composite shells and layered solids).K S P TSection point number within the current layer.K S T E PStep number.K I N CIncrement number.Example: Using more than one user-defined mechanical material modelTo use more than one user-defined mechanical material model, the variable C M N A M E can be tested for different material names inside user subroutine U M A T as illustrated below:I F(C M N A M E(1:4).E Q.'M A T1')T H E NC A L L U M A T_M A T1(argument_list)E L S E I F(C M N A M E(1:4).E Q.'M A T2')T H E NC A L L U M A T_M A T2(argument_list)E N D I FU M A T_M A T1 and U M A T_M A T2 are the actual user material subroutines containing the constitutive material models for each material M A T1 and M A T2, respectively. Subroutine U M A T merely acts as a directory here. The argument list may be the same as that used in subroutine U M A T.Example: Simple linear viscoelastic materialAs a simple example of the coding of user subroutine U M A T, consider the linear, viscoelastic model shown in Figure 1.1.41–1. Although this is not a very useful model for real materials, it serves to illustrate how to code the routine.Figure 1.1.41–1 Simple linear viscoelastic model.The behavior of the one-dimensional model shown in the figure iswhere and are the time rates of change of stress and strain. This can be generalized for small straining of an isotropic solid asandwhereand , , , , and are material constants ( and are the Lamé constants).A simple, stable integration operator for this equation is the central difference operator:where f is some function, is its value at the beginning of the increment, is the change in the function over the increment, and is the time increment.Applying this to the rate constitutive equations above givesandso that the Jacobian matrix has the termsandThe total change in specific energy in an increment for this material iswhile the change in specific elastic strain energy iswhere D is the elasticity matrix:No state variables are needed for this material, so the allocation of space for them is not necessary. In a morerealistic case a set of parallel models of this type might be used, and the stress components in each model might be stored as state variables.For our simple case a user material definition can be used to read in the five constants in the order , , , , and so thatThe routine can then be coded as follows:S U B R O U T I N E U M A T(S T R E S S,S T A T E V,D D S D D E,S S E,S P D,S C D,1R P L,D D S D D T,D R P L D E,D R P L D T,2S T R A N,D S T R A N,T I M E,D T I M E,T E M P,D T E M P,P R E D E F,D P R E D,C M N A M E,3N D I,N S H R,N T E N S,N S T A T V,P R O P S,N P R O P S,C O O R D S,D R O T,P N E W D T,4C E L E N T,D F G R D0,D F G R D1,N O E L,N P T,L A Y E R,K S P T,K S T E P,K I N C)CI N C L U D E'A B A_P A R A M.I N C'CC H A R A C T E R*80C M N A M ED I ME N S I O N S T R E S S(N T E N S),S T A T E V(N S T A T V),1D D S D D E(N T E N S,N T E N S),2D D S D D T(N T E N S),D R P L D E(N T E N S),3S T R A N(N T E N S),D S T R A N(N T E N S),T I M E(2),P R E D E F(1),D P R E D(1),4P R O P S(N P R O P S),C O O R D S(3),D R O T(3,3),D F G R D0(3,3),D F G R D1(3,3)D I ME N S I O N D S T R E S(6),D(3,3)CC E V A L U A T E N E W S T R E S S T E N S O RCE V=0.D E V=0.D O K1=1,N D IE V=E V+S T R A N(K1)D E V=D E V+D S T R A N(K1)E N D D OCT E R M1=.5*D T I M E+P R O P S(5)T E R M1I=1./T E R M1T E R M2=(.5*D T I M E*P R O P S(1)+P R O P S(3))*T E R M1I*D E VT E R M3=(D T I M E*P R O P S(2)+2.*P R O P S(4))*T E R M1ICD O K1=1,N D ID S T RE S(K1)=T E R M2+T E R M3*D S T R A N(K1)1+D T I M E*T E R M1I*(P R O P S(1)*E V2+2.*P R O P S(2)*S T R A N(K1)-S T R E S S(K1))S T R E S S(K1)=S T R E S S(K1)+D S T R E S(K1)E N D D OCT E R M2=(.5*D T I M E*P R O P S(2)+P R O P S(4))*T E R M1II1=N D ID O K1=1,N S H RI1=I1+1D S T RE S(I1)=T E R M2*D S T R A N(I1)+1D T I M E*T E R M1I*(P R O P S(2)*S T R A N(I1)-S T R E S S(I1)) S T R E S S(I1)=S T R E S S(I1)+D S T R E S(I1)E N D D OCC C R E A T E N E W J A C O B I A NCT E R M2=(D T I M E*(.5*P R O P S(1)+P R O P S(2))+P R O P S(3)+12.*P R O P S(4))*T E R M1IT E R M3=(.5*D T I M E*P R O P S(1)+P R O P S(3))*T E R M1ID O K1=1,N TE N SD O K2=1,N TE N SD D S D D E(K2,K1)=0.E N D D OE N D D OCD O K1=1,N D ID D S D D E(K1,K1)=TE R M2E N D D OCD O K1=2,N D IN2=K1–1D O K2=1,N2D D S D D E(K2,K1)=TE R M3D D S D D E(K1,K2)=TE R M3E N D D OE N D D OT E R M2=(.5*D T I M E*P R O P S(2)+P R O P S(4))*T E R M1II1=N D ID O K1=1,N S H RI1=I1+1D D S D D E(I1,I1)=TE R M2E N D D OCC T O T A L C H A N G E I N S P E C I F I C E N E R G YCT D E=0.D O K1=1,N TE N ST D E=T D E+(S T R E S S(K1)-.5*D S T R E S(K1))*D S T R A N(K1)E N D D OCC C H A N G E I N S P E C I F I C E L A S T I C S T R A I N E N E R G YCT E R M1=P R O P S(1)+2.*P R O P S(2)D O K1=1,N D ID(K1,K1)=T E R M1E N D D OD O K1=2,N D IN2=K1-1D O K2=1,N2D(K1,K2)=P R O P S(1)D(K2,K1)=P R O P S(1)E N D D OE N D D OD E E=0.D O K1=1,N D IT E R M1=0.T E R M2=0.D O K2=1,N D IT E R M1=T E R M1+D(K1,K2)*S T R A N(K2)T E R M2=T E R M2+D(K1,K2)*D S T R A N(K2)E N D D OD E E=D E E+(T E R M1+.5*T E R M2)*D S T R A N(K1)E N D D OI1=N D ID O K1=1,N S H RI1=I1+1D E E=D E E+P R O P S(2)*(S T R A N(I1)+.5*D S T R A N(I1))*D S T R A N(I1)E N D D OS S E=S S E+D E ES C D=S C D+T D E– D E ER E T U R NE N D。
abaqus中johnson-cook本构模型理解
Johnson-Cook本构模型是一种在冲击动力学中应用广泛的模型，适用于模拟许多材料在高应变率下的变形。
这个模型考虑了流变应力、应变、应变速率和温度之间的关系，其公式简单明了。
该模型由三部分构成，分别表征了材料的应变硬化、应变速率强化以及热软化。
然而，这个模型采用简单的乘积形式将三项联立，这意味着它只是单独考虑了应变、应变速率和温度的影响，而并未考虑各因素之间的耦合影响。
因此，在某些特殊情况下，模型的精度可能会存在问题。
此外，Johnson-Cook塑性模型是一种具有硬化规律和速率依赖的解析形式的米塞斯塑性模型，主要适用于许多材料的高应变率变形模拟，包括大多数金属。
它通常用于绝热瞬态动态模拟，可以与Abaqus/Explicit中的Johnson-Cook动态失效模型结合使用。
在Abaqus/Explicit中，它可以结合拉伸破坏模型来模拟拉伸剥落或压力断口。
此外，它可以与渐进损伤和失效模型结合使用，以指定不同的损伤起始准则和损伤演化规律，同时允许材料刚度的渐进退化和网格单元的移除。
需要注意的是，必须与线弹性材料模型或状态方程材料模型结合使用。
总的来说，Johnson-Cook本构模型在模拟高应变率变形方面具有重要应用，但在使用时需要注意其局限性。
abaqus johnson cook失效准则
abaqus johnson cook失效准则Abaqus Johnson-Cook Failure Criterion: An In-depth AnalysisIntroduction:The Abaqus Johnson-Cook failure criterion is widely used in the field of computational modeling and simulation to predict material failure under extreme conditions. This criterion is paramount in accurately predicting how a material will deform and eventually fail under various loading conditions. In this article, we will provide a step-by-step analysis of the Abaqus Johnson-Cook failure criterion, its underlying principles, and its applications in engineering simulations.1. Background and Theory:The Johnson-Cook failure criterion was originally proposed by G.R. Johnson and W.H. Cook in 1983. It provides a phenomenological representation of the material behavior leading to failure under high strain rates and elevated temperatures. The criterion takes into account the effects of strain, strain rate, and temperature on the material's response to loading. By considering these factors, thefailure criterion allows for a more accurate prediction of material failure.2. Formulation of the Criterion:The Abaqus Johnson-Cook failure criterion can be mathematically represented as follows:σ_eq = (1 + αε˙_pl^* (T - T_0))^m (1 - β(T - T_0))^nwhere σ_eq is the equivalent stress, αand βare material constants, ε˙_pl^* is the plastic strain rate, T is the temperature, T_0 is a reference temperature, and m and n are exponent parameters. This equation describes the relationship between stress, strain rate, temperature, and material failure.3. Parameter Determination:To accurately define the material constants α, β, m, and n, experimental data is necessary. These constants are typically obtained through a series of experimental tests, such as tensile tests at different strain rates and temperatures. The results fromthese tests are then used to fit the parameters in the Johnson-Cook equation to obtain a reliable representation of the material behavior.4. Material Model Implementation:In Abaqus, the Johnson-Cook failure criterion is implemented through a specific material model. The material model incorporates the Johnson-Cook equation and provides a framework to simulate the behavior of materials subjected to high strain rates and elevated temperatures. The user must input the relevant material properties and the determined values for α, β, m, and n into the material model.5. Applications:The Abaqus Johnson-Cook failure criterion has found numerous applications across various engineering disciplines. It is particularly relevant in the fields of impact dynamics, projectile penetration, blast effects, and metal forming processes. By accurately predicting material failure, engineers can design structures and components with a higher level of safety and durability.6. Validation and Verification:Before utilizing the Abaqus Johnson-Cook failure criterion in engineering simulations, it is crucial to validate and verify the accuracy of the material model. This involves comparing the simulation results with experimental data obtained from laboratory tests. If the simulation results closely match the experimental results, it provides confidence in the predictive capability of the model.7. Advantages and Limitations:The Abaqus Johnson-Cook failure criterion allows engineers to simulate and predict material failure under extreme conditions, providing valuable insights for design and analysis purposes. However, it is important to note that the accuracy of the model heavily relies on accurate parameter determination and appropriate material model selection. Additionally, the criterion may not be suitable for all materials and certain scenarios, necessitating the use of alternative failure criteria.Conclusion:In conclusion, the Abaqus Johnson-Cook failure criterion is a valuable tool in predicting material failure under high strain rates and elevated temperatures. By considering the effects of strain, strain rate, and temperature in the material's response to loading, this criterion provides engineers with important insights during the design and analysis stages. However, it is crucial to accurately determine the material constants and validate the model to ensure reliable predictions. The Abaqus Johnson-Cook failure criterion continues to play a pivotal role in engineering simulations, contributing to safer and more efficient designs.。
abaqus 子程序 简单案例
abaqus 子程序简单案例1. 案例一：ABAQUS子程序在计算机辅助工程中的应用在计算机辅助工程中，ABAQUS子程序是一种被广泛应用的工具，用于求解各种复杂的物理问题。
它可以在ABAQUS有限元软件中调用，通过编写用户自定义的子程序来实现特定的功能。
下面将介绍一些常见的ABAQUS子程序案例。
2. 案例二：ABAQUS子程序在材料力学中的应用ABAQUS子程序在材料力学中的应用非常广泛。
例如，可以通过自定义的子程序来模拟材料的非线性行为、塑性变形、断裂行为等。
通过在子程序中编写相应的材料本构模型和损伤模型，可以准确地预测材料的力学性能。
3. 案例三：ABAQUS子程序在流体力学中的应用ABAQUS子程序在流体力学中也有重要的应用。
例如，可以通过自定义的子程序来模拟流体的非牛顿性、多相流动、湍流等现象。
通过在子程序中编写相应的流体本构模型和湍流模型，可以准确地模拟流体的流动行为。
4. 案例四：ABAQUS子程序在结构力学中的应用ABAQUS子程序在结构力学中也非常有用。
例如，可以通过自定义的子程序来模拟结构的非线性行为、接触和摩擦、动力响应等。
通过在子程序中编写相应的结构本构模型和接触模型，可以准确地预测结构的力学性能。
5. 案例五：ABAQUS子程序在热传导中的应用ABAQUS子程序在热传导中的应用也非常广泛。
例如，可以通过自定义的子程序来模拟材料的热传导行为、热辐射、相变等。
通过在子程序中编写相应的热传导模型和相变模型，可以准确地预测材料的热学性能。
6. 案例六：ABAQUS子程序在电磁场中的应用ABAQUS子程序在电磁场中的应用也有一定的研究价值。
例如，可以通过自定义的子程序来模拟电磁场的非线性行为、磁饱和、电磁感应等。
通过在子程序中编写相应的电磁场模型和电磁感应模型，可以准确地模拟电磁场的行为。
7. 案例七：ABAQUS子程序在声学中的应用ABAQUS子程序在声学领域中也有一定的应用。
abaqus中johnson-cook本构模型理解 -回复
abaqus中johnson-cook本构模型理解-回复Abaqus中Johnson-Cook本构模型理解引言：材料的本构模型是描述材料力学行为的数学方程。
在有限元分析中，本构模型可以用于模拟材料的变形和损伤行为，从而预测材料在不同加载条件下的响应。
Johnson-Cook本构模型是一种常用的本构模型，广泛应用于材料科学和工程领域。
本文将从基本原理开始，逐步解释和理解Abaqus 中Johnson-Cook本构模型。
1. 弹塑性本构模型首先需要了解的是，弹塑性本构模型是最基本的材料模型之一。
它基于线弹性理论，假设材料在小应变范围内具有弹性行为，而在大应变范围内表现出塑性行为。
弹塑性本构模型可以描述材料的应力-应变关系，并预测材料的弹性变形和塑性变形。
2. 材料的温度效应在考虑Johnson-Cook本构模型之前，还需要考虑材料的温度效应。
温度对材料力学行为的影响是复杂而重要的。
温度的增加可以引起材料的软化、蠕变和断裂等现象。
因此，在模拟材料行为时，必须考虑材料的温度效应，并选择适当的本构模型来描述。
3. Johnson-Cook本构模型的基本原理Johnson-Cook本构模型是一种经验模型，用于描述材料的塑性行为和温度效应。
它采用以下形式的应力-应变关系：σ= (A + B ε^n) (1 + C ln(ε˙/ε˙_0))^m (1 - T/T_m)^p其中，σ是材料的应力，ε是应变，ε˙是应变速率，T是材料的温度，A、B、C、n、m、p和T_m是需要通过实验来确定的材料参数。
4. 材料参数的确定为了使用Johnson-Cook本构模型，需要通过实验来确定材料参数。
这些参数通常由材料的拉伸实验和冲击实验等得到。
拉伸实验可以提供材料的应力-应变曲线，以及材料的屈服强度和断裂应变等信息。
冲击实验可以提供材料的应变率敏感性和断裂韧性等信息。
根据实验数据，可以使用不同的方法来确定Johnson-Cook本构模型的参数。
abaqus中johnson-cook本构模型理解 -回复
abaqus中johnson-cook本构模型理解-回复什么是Johnson-Cook本构模型？Johnson-Cook本构模型是一种经验性本构模型，用于描述金属材料在高速冲击、爆炸、高温和高应变率等极端条件下的力学行为。
它是由Johnson、Cook和Mackenzie等人于1983年提出的，并在后续的研究中进行了改进和发展。
Johnson-Cook本构模型已广泛应用于工程领域，尤其在汽车碰撞、航空航天以及防卫等领域中。
Johnson-Cook模型的核心思想是将材料的流变行为与材料的动力学参数相联系，从而描述材料在极端条件下的力学响应。
该模型基于一系列有效的材料试验数据，并引入了一些物理参数，以实现更准确的预测。
下面将详细介绍Johnson-Cook本构模型的具体形式以及其各个参数的含义：1. 应变率项：Johnson-Cook模型中的应变率项描述了材料在高应变率条件下的变形行为。
该项通常采用一般性的动力学方程，其中引入材料的应变硬化参数（A）、热软化参数（B）和应变率硬化指数（n）。
2. 温度项：Johnson-Cook模型中的温度项描述了材料在高温条件下的变形行为。
该项通常采用Arrhenius方程来表示材料的温度依赖性。
在此项中，引入材料的活化能（Q）、材料的平均绝对温度（T）和一些温度相关的材料常数。
3. 存在塑性起始的切应力项：Johnson-Cook模型中的切应力项描述了材料在塑性变形开始时所需的应力水平。
通过引入材料的初始应力（σ_0），可以实现对材料塑性变形起点的准确描述。
4. 塑性变形表征的切应变项：Johnson-Cook模型中的切应变项描述了材料的塑性变形行为。
该项通常采用一般性的功率方程，其中引入了材料的切应变硬化参数（C）和切应变硬化指数（m）。
5. 材料非均匀性描述的尺寸因子项：Johnson-Cook模型中的尺寸因子项用于考虑材料在非均匀加载条件下的力学响应。
在此项中，引入了材料的尺寸因子（δ）和一些与材料非均匀应变有关的参数。
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的 TAMU 关有守遵须必此因�量变些一用共至甚�递传据数在存间之 TAMU 与序程主于由 传上点质物一每元单义定新重”DLFDSU“过通�用使合联”DLFDSU“序程子户用和以可 )4( 量增变应对量增力应即�阵矩�naibocaJ�比可雅的型模构本料材供提中 TAMU 在须必 )3( 中 SUQABA 予赋性属料材户用把以可乎几 �程过析分何任的析分为行学力于用以可乎几 )2(
集文论会年户用度年 3002 件软 SUQABA
用使须必户用候时这以所。值数的量模切剪到不得候时的理处预行进件文入输序程对 SUQABA
�数个的量分力应接直� IDN
�阵矩量增变应� ) SNETN ( NARTSD
kcaB
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行进分部的触接件试和杆力出�杆力入及以件试对�中型模在。示所 2 图如型模称对轴维二
M 8
C 7
B 5
A 4
数常料材 TAMU 1 表 图程流 TAMU 1 图
集文论会年户用度年 3002 件软 SUQABA
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5.0
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集文论会年户用度年 3002 件软 SUQABA
�为式格常通�义定以予头开件文在量变的用常中 TAMU�式格写书 。值数的量变场中 TAMU 到递
,DCS,DPS,ESS,EDDSDD,VETATS,SSERTS(TAMU ENITUORBUS
。率化变的
�元单何任的
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3m/gK[
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质 性
数参型模 kooC-nosnhoJ
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义定料材的件试 3 表 。序程合拟值数的面前于源来值数的数参中
型模 kooC-nosnhoJ 中其�示所 3 表如数参料材�料材义定自中 TAMU 在户用用采件试。3m/gk
301×58.7
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D CS � D PS � ESS
) SPORPN ( SPORP
。数维
。值的定设数常”STNATSNOC“中”LAIRETAM RESU*“字键关于等�数个的数常料材 的阵矩量变态状为即值数的行据数面下字键关�义定”RAVPED*“字键关的中件文入输 SUQABA 过 通 数 维 的 阵 矩 量 变 态 状 。 值 数 的 义 定 ”RAVPED*“ 字 键 关 于 等 � 数 维 的 阵 矩 量 变 态 状
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�下如义定 dC 速波料材和 eL 度长征特元单用以可限极定稳�算 估的元单个一于基。限极定稳的元单下一算计单简先要需�长步间时大最的步量增定确了为 冲脉力应入输
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) SNETN , SNETN ( EDDSDD
序顺的间之量分各。个 RHSN 有量分切剪�个 IDN 有量分接直。后在储存量分切剪�前在储存量
集文论会年户用度年 3002 件软 SUQABA
对 面 下 。 别 类 的 元 单 用 使 所 到 虑 考 要 时 T AM U 写 编 以 所 � 异 差 些 一 有 同 不 的 度 由 自 元 单 据 根
�候时的 TAMU 用使是但。义定项选”CITSALE*“过通中义定料材在常通�值的量模切剪始初料 材于基度刚些这。的义定质性性弹的中性属料材过通是度刚切剪向横的元单梁、壳、板和度刚制 控漏沙的元单分积缩减常通。度刚切剪向横和度刚制控漏沙的元单意注要需时 TAMU 用使 。 RHSN + IDN = SNETN �数个的量分力应总� SNETN �数个的量分力应切剪� RHSN �量增间时的步量增� EMITD �阵矩变应� ) SNETN ( NARTS �量变他其 。出输量能为作
TDWENP ,TDLPRD ,EDLPRD ,TDDSDD ,LPR ,yrassecen fi ,dna
)3,3(1DRGFD,)3,3(0DRGFD,)3,3(TORD,)3(SDROOC,)SPORPN(SPORP 3 ,)1(DERPD,)1(FEDERP,)2(EMIT,)SNETN(NARTSD,)SNETN(NARTS 2 ,)SNETN(EDLPRD,)SNETN(TDDSDD,)SNETN,SNETN(EDDSDD 1 ,)VTATSN(VETATS,)SNETN(SSERTS NOISNEMID EMANMC 08*RETCARAHC
) V E T A T S N ( V ET A T S
的量张力应中 TAMU。分部旋共的量张力应理处需只中 TAMU 在此因�动转体刚了行进的量张 力应对经已就前之 TAMU 用调步量增个一�题问变应限有的动转体刚含包于对。新更阵矩量张 阵矩量张力应�始开的步量增在。量分切剪个 RHSN 和量分接直个 IDN 应对�阵矩量张力应 力应对将 TAMU 束结的步量增在�中 TAMU 到递传口接的间之序程主和 TAMU 过通值数的中
例实序程子料材户用 dradnatS/SUQABA
集文论会年户用度年 3002 件软 SUQABA
kcaB
分接直是都�等 EDLPRD � TDDSDD � EDDSDD 阵矩及以阵矩变应、阵矩力应的中 TAMU DNE NRUTER
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DCS ,DPS ,ESS ,VETATS ,SSERTS ,EDDSDD enifed ot gnidoc resu
义定料 材 035 061 035 数个元单 点节总 息信型模 2 表 型模元限有称对轴维二 2图 4XAC 4XAC 4XAC 型类元单 0001×52 22×81 杆力出 件试 杆力入 型 模
0221
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型 模 维 二
数 数元单总
集文论会年户用度年 3002 件软 SUQABA
。示所 1 图如程流的 TAMU 个整。序程主回返口接过通将值新更的量变
规口接的序程子料材户用 SUQABA 照参�法算新更力应和式公料材关相率的述所面上于基
序程的应相了出给还中节一后最在�出给节一下在将果结拟模元限有。程编的 TAMU 行进�范