IRLIST

*Get,mass_x,ELEM,0,MTOT,X

*Get,cg_x,ELEM,0,MC,X

*Get,moi_x,ELEM,0,IMC,X

I've found an example online that uses the below code and then uses the above *Get commands tograb individual component results. But it appears that PSOLVE is now a legacy command. Is there a new command that has taken its place that I need to be using? Or a different approach I should be using for this?

irlf,-1 ! Precalculate masses for summary printout only (no inertia relief) psolve,elform ! Getting information about partial solving psolve,elprep ! Solving

I tried to perform a response spectrum in my structure. However I can't proceed because of the error (**ERROR: Data file file.db does not exist for RESUME**). My modal analysis run successfully but I am getting this error when performing response spectrum. How can I fix this error?

Thanks

]]>Also there is an APDL command to figure out the contact area. Could you check if it looks ok?

]]>First of all, thanks for creating this extension.

I performed heat somulation by using one of the ACT extension that is MovingHear. I can define a path that heat source follows. However, I want it to travel this path more than once. For example, it finishes first travelling in 15 ms and than it should do it again lets say 15 times more. Basically, in the video, the heat source starts from one corner of square and travel around the square. However, it is done only one time. I want to get it travel same path as many as I want.

I will be grateful if you provide a solution that enlighthen my issue☺️

Thank you in advance.

Looking forward your reply!

]]>How can I automate this process?

]]>I would like to understand which is the best way to perform the study. My plan is to start with 2D analysis and eventually, it can turn into a 3D analysis.

Here are two ways that I think it might work:

- Generating a mesh from an existing accurate tooth geometry, and use nodal relocation to find the best node positioning and hence best geometry. Then, to simplify the manufacture process, I can interpolate a curve and get the optimized geometry of the root fillet (the main challenge in this way is how to relocate nodes - I'm not sure if that can be done using APDL);

- Perform a parametric optimization of the involution curve based on the stress results from the FEA (the main challenge in this case is how to model the involution curve from Space Claim or APDL).

Perhaps with the integration of certain tools, such as the Python Language and Libraries, they can assist in the geometry design process or even in the optimization process.

I'm open to suggestions!

Thank you!

]]>working on automation process in ANSYS Mechanical, I studied the "Scripting in Mechanical Guide".

Inside I found an example that fits my needs really well. Sadly in this examples I can not finde an example that does not uses the GUI to run the python-script.

So all I would like to do is to run the python script mentioned in the "Scripting in Mechanical Guide" in section "Post Processing Options" (p. 267) from the batch, while ANSYS is not running and the existing project is not loaded already. It is not important if the GUI opens or not, but I don't want to take a single click.

Greetings

Philipp

]]>I tried to change the load steps for an imported pressure but there was something wried. I have attached three figures below to show the issue.

I wanted to make the imported pressure be zero (Scale 0) at time 0 s and increases it to the full magnitude at time 0.5s and then stay until the end time of 1s. However, as shown in both tabular data and load graph, the pressure starts directly from Row_2 rather than Row_1. This would usually cause my simulation to fail. Is this because that I could not use a scale of 0? Any suggestions on this would be appreciated.

I have an aluminum tool, for a heat press, that needs to be heated with resistors and is coated with silicone on the contact face and with insulation on the sides. I know the contact face needs to be at 220ºC 10 minutes after start-up and that there's convection with the air around the tool. I want to find the needed heat flow/heat flux through the surface where I'll put the resistors, so I know how much power I need to use for startup and then for heat maintenance.

Materials and so on are not important... I just want to know how to solve to find the needed heat flow needed to heat the contact surface to 220ºC in 10 minutes, bearing in mind heat loss through other surfaces.

I attach some pictures and upload the model (though I'm a noob and don't know if I've uploaded the proper file).

I appreciate very much your time and attention, whoever you might be! Thank you!

Miguel

Moving heat flux does not appear on the script. What is the reason and How can I manipulate the parameters?

It only shows heat flux.

Hi guys,

I was doing thermo structural analysis of brake discs based on a paper. I am getting an almost similar value of von mises to stress but the distribution is not coming. Usually, stress will be maximum on the bolt hole side where it is mounted?. Please help me regarding this on an urgent basis.

The boundary conditions applied have been shown here.

*DO,j,1,cycles+1

*DIM,P_ELMAT%J%,TABLE,ELNUM,1,1

*VFILL,P_ELMAT%j%(1,0),RAMP,1,1

*ENDDO

esel,all

*DO,i,1,ELNUM

*GET,P_ELMAT1(i,1),ELEM,i,ATTR,MAT

*ENDDO

*CFOPEN,'emat_initial','txt',' '

*VWRITE,P_ELMAT1(1,1), , , , , , , , ,

(F4.0)

*CFCLOS

]]>*VFILL,ELDENS(1,0),RAMP,1,1

*SET,ELDENS(1,1),1E-6

*DO,i,2,100

*SET,ELDENS(i,1),i/100*2 ! Density range: [1E-6;2]

*ENDDO

*SET,ELDENS(0,0),0

*SET,ELDENS(0,1),1

*DO,i,1,100

*SET,E_x,c_x*ELDENS(i)**gamma_E

*SET,E_y,c_y*ELDENS(i)**gamma_E

MP,EX,i,E_x

MP,EY,i,E_y

MP,EZ,i,E_y

MP,GXY,i,E_x/4

MP,GXZ,i,E_x/4

MP,GYZ,i,E_x/4

MP,PRXY,i,nu_xy

MP,PRYZ,i,nu_xy

MP,PRXZ,i,nu_xy

*enddo

*get,ELNUM,ELEM, ,count

*get,NNUM,NODE, ,count

*CFOPEN,ELNUM,txt

*VWRITE,ELNUM

**%8I**

*CFCLOS

]]>If you can share an example with me in this regard, I would be very happy. I could not find any literature on the card below. What is the difference between using the old card and using this card? Also, if you have any documents about the new card, I would be glad if you can share it. (I'm looking for other than manuel) And I need sample of any metal material.

BR

]]>Awlad.

]]>I am doing a vibration analysis and Shock / Transient analysis with 1.5 G acceleration for 30 milli-seconds time duration.

First of all I did Modal analysis and then response spectrum analysis (Linear) in Ansys Workbench Mechanical. Then did separate Non Linear Transient analysis. The acceleration boundary condition for each analysis is in the attached picture.

1) I am not sure if I applied acceleration Boundary conditions to Response spectrum analysis is true or not. Is it true ??? i.e. RS Acceleration 33,33 Hz to 15000 mm/S^2

2) If it is true then I am getting equivalent stress is very different for both ( for response spectrum it is in range of 6

00 MPa and for Transient it is around 100 MPa). Which Analysis should I consider ?? I want to find weak points.

In Response spectrum I have considered CQC mode combination type and tried with SRSS as well but Stress value is very higher then Transient analysis.

I am looking more about Fatigue tool option in Transient analysis result what kind of setting to consider. Is there any tutorial or link about it ?

Can anyone please help me ? If I need to change some setting or anything.

Thank you !

Vishal

*MODEL [remote force is in the center but a few mm forward in the z direction]:*

*FORCE REACTION VECTOR (for one of the beams) [just few mm before the fixed support]:*

*FORCE REACTION (at the support) [for the same beam]:*

First of all, I want to ask that the vectors which are shown in the second picture, why do I see the vectors in both the directions (i.e. +z and -z)? Since the concerned beam is above the neutral axis, I was expecting all the vectors to be in the same direction. This is quite confusing for me.

Secondly, the 'Results' that I am seeing only gives me the resultant forces along X, Y and Z direction, right? Rather it be at a cross section a few mm before the fixed support (second picture), or it be the fixed support itself (last picture). But imagine if I want to size the beam depending upon the maximum amount of force passing through any of the node in that beam, then I would need to know the maximum values along a cross section or at the fixed support, not the net maximum resultant. Can anyone please tell me that how can I find the maximum force (among all the nodes) at a specific cross section, or the fixed support? For this model it might be done analytically, but I want to use ANSYS to do that.

Thirdly, how can I calculate the Y axis maximum force value (at any of the nodes of a cross section or at the fixed support), because I want to include that in my sizing. No matter if I try to retrieve the force results at any cross section or at the fixed supports, the force value in the Y axis is always zero. And it makes sense since it should cancel out at that face, but there exists a Y force and I want to know the maximum of it among all the nodes. How can I do that?

]]>I am trying to model some sort of friction based damping that works for harmonic analysis in APDL.

So far i was able to model the friction for static analysis using CONTA178. However the results of the harmonic analysis don't seem to make sense.

The following image shows my setup:

Its basicly a simple oscillator with added friction between node 2 (the one with mass) and node 3.

The spring between node 2 and 4 is pretensioned in order to apply the normal force to the friction.

This is the APDL Code:

`mu = 0.05`

`Fx = 1000`

`Fy = 0`

`Kx = 1000`

`Ky = 100`

`/PREP7`

`/ESHAPE,1,1`

`NROPT,UNSYM`

`TB,FRIC,1,,,ISO`

`TBDATA,1,mu`

`ET,1,MPC184`

`KEYOPT,1,1,1`

`R,2,Kx,0 `

`ET,2,COMBIN14 `

`KEYOPT,2,2,1 `

`R,2,Kx,0,0 `

`R,3,Ky,0 `

`ET,3,COMBIN14 `

`KEYOPT,3,3,0 `

`R,3,Ky,0,0,,,0.2 `

`ET,4,MASS21`

`KEYOPT,4,1,0`

`KEYOPT,4,2,1`

`KEYOPT,4,3,0`

`R,4,1,1,1`

`ET,5, CONTA178`

`KEYOPT,5,1,0`

`KEYOPT,5,4,1`

`KEYOPT,5,5,5 `

`KEYOPT,5,10,2 `

`R,5,1,0,2,1`

`N,1,0,0,0 `

`N,2,1,0,0`

`N,3,1,0.1,0`

`N,4,1,-0.1,0`

`NSEL, ALL`

`D,ALL,UZ,0 `

`D,1,UX,0 `

`D,1,UY,0 `

`D,3,UX,0 `

`D,3,UY,0 `

`D,4,UY,0 `

`TYPE,2`

`REAL,2`

`E,1,2`

`TYPE,3 `

`REAL,3`

`E,2,4`

`TYPE,4`

`REAL,4`

`E,2`

`TYPE,5`

`REAL,5`

`E,2,3`

`F,2,FX,Fx`

`/SOLU`

`ANTYPE, HARMIC, NEW`

`HARFRQ, 0, 10`

`NSUBST, 100`

`DMPSTR, 0.01`

`ALLSEL`

`SOLVE`

`FINISH`

`/POST26`

`NSOL,2,2,U,X, UX_1`

`PLVAR,2`

Does anybody have any advice on how to fix this problem?

]]>The outer cylinder is fully constrained through fixed constraints applied to the front and back surfaces (the ones normal to z direction). The inner cylinder in constrained so that it can move only horizontally (along x direction). An horizontal force is applied to the inner cylinder. The distance (clearance) between the external surface of the inner cylinder and the inner surface of the outer cylinder is equal to 0.20 mm. The inner diameters of the two solids measures 17.6 and 20 mm respectively. Wall thickness is 1mm for both of them.

I've created a Contact Pair (frictionless) between the outer surface of the inner cylinder (Contact) and the inner surface of the outer cylinder (Target). Formulation: Normal Lagrange; Behavior: Asymmetric; Detection: Nodal Normal to Target; Trim Contact: OFF

The mesh is a structured mesh for both the solids.

When I lauch the simulation, these two messages appear:

Where am I mistaking?

Thanks to all those who will kindely help me.

Best regards, Christian

]]>I will be really grateful for your answer.

Thank You]]>

I am performing some cohesive zone modeling for adhesive applications, and when solving I run into the following error - 'An error occurred inside the SOLVER module: general error'. To gain more information and debug I would typically review the solver output file, but no such file is being generated (see attached screenshot below). Any help on how to navigate this issue would be greatly appreciated. I would be happy to follow up with any additional information about the study set-up, if necessary.

Regards,

Jamie

Best,

Shahriar

]]>hope someone will help me.

How can I export the final nodal global coordinates after I've run a generic small/large displacement static analysis?

Initially I've calculated the final coordinates simply by sum of initial nodal coordinates and their displacement, but I'm sure a more efficient method exists. Can you help me?

thank you in advance

]]>How can I validate my result?

]]>So I have a "trained neural network", which ultimately is just a matrix that can take inputs and predict outputs. This neural network (NN) is used as a specific constitutive equation sig = NN*eps. I'd like to use this in the Ansys solver, and came across USERMAT subroutines that are used for making custom constitutive equations.

My question is if anyone has done something similar and how you went about implementing it. The NN is "trained" in Python so I have a Python executable for making predictions. My first thought was to couple USERMAT with Python, but I have zero experience with doing this (I just have bolts for brains). I know USERMAT is written in FORTRAN, but doing some digging I didn't see anything straight forward for coupling FORTRAN with Python.

So maybe people on here much smarter than me have suggestions for tacking this? The NN is pretty big, over a million elements in the matrix, but maybe there is a not-so-painstaking way of outputting the Python matrix into a FORTRAN executable? I know that's a better question to ask on a FORTRAN/Python forum which I have, I'm just grasping at straws trying to figure out how I'm going to do this.

]]>I am using ANSYS 2021 R1 to calculate energy release rate for mode III.

The ANSYS fracture tool distribution of energy release rate is different when I obtain the energy release rate from nodal value directly. They are totally different at one side; moreover, there is a small difference between the values of Fracture tool and my calculation.

I have attached here both the values and graph.

Direct VCCT is the result of Fracture tool. In nodal VCCT, I export nodal force and displacement directly and calculate VCCT using the same formula that ANSYS uses.

ANSYS help for VCCT: https://ansyshelp.ansys.com/account/secured?returnurl=/Views/Secured/corp/v212/en/ans_frac/frac_parmcalctypes.html%23advvcctenrelrate

Does anyone have any suggestions about the root of this inconsistency and how I can solve it?

Thank you.

In the occasion, I performed a Pre-stressed Modal Analysis, and the results were pretty much as I expected:

Now, I am trying to reload the same model in Ansys 2021 R2, but when I set the solver, the software gives me the following message:

*"An unknown error occurred during solution. Check the Solver Output Information object for possible causes". *

In the Solver Output Information, the indicated errors are the ones below:

*"A boundary condition has been imposed on node 36, degree of freedom 3 of the element 10. Currently, Ansys does not upport such a set-up. Please avoid boundary conditions on nodes forming the revolute joint element."*

*"A boundary condition has been imposed on node 32, degree of freedom 3 of the element 8. Currently, Ansys does not support such a set-up. Please avoid boundary conditions on nodes forming the revolute joint element."*

*"A boundary condition has been imposed on node 34, degree of freedom 3 of the element 9. Currently, Ansys does not support such a set-up. Please avoid boundary conditions on nodes forming the revolute joint element."*

Hence, it seems the problem is related to the way I set the revolute joints (the "rotation springs"). Still, it is weird that a model which worked very well in a previous version of Ansys is no longer working in the newest release. Does anyone have any suggestion to fix the model and make it work again?

Thanks in advance.

Best regard

Mereen Hussain

]]>A4-70 M20 Bolt Yield Strenght 450 mPa

Maximum equivalent von mises stress is nearly 1000 mpa

Thank you for answers.

I'm running into a roadblock when trying to implement bearings into my rotor geometry in the ansys apdl command utility menu. I was thinking that because I already have a geometry I don't need to create apdl commands for rotor geometry, point masses, and nodes like specified in the example 7.8 Critical Speed Map Generation in Ansys_Mechanical_APDL_Rotordynamic_Analysis_Guide.pdf

Here's the commands I've been referencing

/filename,tutor-rag07s

/prep7

! *** material

mp, ex, 1, 1.33414e+11

mp, dens, 1, 7833.3834

mp, prxy, 1, 0.3

! *** rotor geometry

et, 1, beam188,,, 2

nbdiam = 34

*dim, diam, array, nbdiam

diam(1) = 0.06985

diam(2) = 0.110744

diam(3) = 0.127

diam(4) = diam(3)

diam(5) = 0.1651

diam(6) = 0.168148

diam(7) = 0.157988

diam(8) = 0.182372

diam(9) = 0.17018

diam(10) = diam(9)

diam(11) = diam(9)

diam(12) = diam(9)

diam(13) = diam(9)

diam(14) = diam(9)

diam(15) = diam(9)

diam(16) = diam(9)

diam(17) = diam(9)

diam(18) = diam(9)

diam(19) = diam(9)

diam(20) = diam(9)

diam(21) = diam(9)

diam(22) = diam(9)

diam(23) = diam(9)

diam(24) = diam(9)

diam(25) = diam(9)

diam(26) = 0.1778

diam(27) = 0.168148

diam(28) = diam(27)

diam(29) = 0.1651

diam(30) = 0.127

diam(31) = diam(30)

diam(32) = 0.118872

diam(33) = 0.094996

diam(34) = 0.093472

*do,i,1,nbdiam

sectype, i, beam, csolid

secdata, diam(i)/2

*enddo

! *** point masses

et, 2, mass21

r,101,72.1224,72.1224,72.1224

r,102,3.22056,3.22056,3.22056

r,103,4.58136,4.58136,4.58136

r,104,2.54016,2.54016,2.54016

r,105,4.39992,4.39992,4.39992

r,106,5.57928,5.57928,5.57928

r,107,5.67,5.67,5.67

r,108,7.4844,7.4844,7.4844

r,109,6.66792,6.66792,6.66792

r,110,33.3396,33.3396,33.3396,0.1805617,0.09042717,0.09042717 ! disk

r,111,7.80192,7.80192,7.80192,0.00992065,0.00520907,0.00520907

r,112,33.3396,33.3396,33.3396,0.1805617,0.09042717,0.09042717 ! disk

r,113,7.80192,7.80192,7.80192,0.00992065,0.00520907,0.00520907

r,114,33.3396,33.3396,33.3396,0.1805617,0.09042717,0.09042717 ! disk

r,115,7.80192,7.80192,7.80192,0.00992065,0.00520907,0.00520907

r,116,36.69624,36.69624,36.69624,0.1805617,0.09042717,0.09042717 ! disk

r,117,13.19976,13.19976,13.19976

r,118,36.92304,36.92304,36.92304,0.1805617,0.09042717,0.09042717 ! disk

r,119,9.5256,9.5256,9.5256,0.01436885,0.00793067,0.00793067

r,120,34.33752,34.33752,34.33752,0.1805617,0.09042717,0.09042717 ! disk

r,121,9.5256,9.5256,9.5256,0.01436885,0.0079014,0.0079014

r,122,34.33752,34.33752,34.33752,0.1805617,0.09042717,0.09042717 ! disk

r,123,9.5256,9.5256,9.5256,0.01436885,0.00793067,0.00793067

r,124,36.56016,36.56016,36.56016,0.1805617,0.09042717,0.09042717 ! disk

r,125,17.14608,17.14608,17.14608,0.04799371,0.03540999,0.03540999

r,126,5.62464,5.62464,5.62464

r,127,5.94216,5.94216,5.94216

r,128,5.71536,5.71536,5.71536

r,129,5.53392,5.53392,5.53392

r,130,4.39992,4.39992,4.39992

r,131,1.99584,1.99584,1.99584

r,132,3.58344,3.58344,3.58344

r,133,7.39368,7.39368,7.39368

r,134,9.43488,9.43488,9.43488

r,135,4.71744,4.71744,4.71744

! *** bearing (YZ plane)

et, 3, 214

keyopt, 3, 2, 1

keyopt, 3, 3, 0

*dim, kb, array, 10, 1, 1

kb(1,1) = 1751181.1, 3772744.57, 8128282.20, 17511811.02, 37717971.02, 81282646.93, 175118110.24, 377280585.83, 812826294.17, 1751181102.36

r,3, kb(1,1), kb(1,1)

! *** nodes (shaft along X)

n, 1 , 0.

n, 2 , 0.034544

n, 3 , 0.20574

n, 4 , 0.24384

n, 5 , 0.287274

n, 6 , 0.375412

n, 7 , 0.429768

n, 8 , 0.51943

n, 9 , 0.60579

n, 10, 0.668274

n, 11, 0.747014

n, 12, 0.809498

n, 13, 0.888238

n, 14, 0.950722

n, 15, 1.029462

n, 16, 1.091946

n, 17, 1.251966

n, 18, 1.411986

n, 19, 1.484122

n, 20, 1.575054

n, 21, 1.64719

n, 22, 1.738122

n, 23, 1.810258

n, 24, 1.90119

n, 25, 2.028444

n, 26, 2.10185

n, 27, 2.160524

n, 28, 2.250694

n, 29, 2.30505

n, 30, 2.39268

n, 31, 2.436114

n, 32, 2.474214

n, 33, 2.61874

n, 34, 2.666238

n, 35, 2.806192

n, 40 , 0.24384

n, 310, 2.436114

! *** mesh

type, 1

mat, 1

*do,i,1,nbdiam

secnum, i

e, i, i+1

*enddo

type, 2

*do,i,1,nbdiam+1

real, i+100

e, i

*enddo

type, 3

real, 3

e, 4, 40

e, 31, 310

! *** boundary conditions

d, all, ux ,,,,,rotx

d, 40, all

d, 310, all

fini

! *** Example of how to determine critical speeds

! -------------------------------------------

! ** modify the bearing stiffness

/prep7

rmodif, 3, 1, kb(5,1), kb(5,1)

finish

! ** write the full file

/solu

antype, modal

modopt, damp, 2

coriolis, on,,, on

omega, 1.0 ! unit rotational velocity to get [G1]

wrfull, 1 ! stop solve when the full file is written

solve

fini

! ** read matrices on the full file

*smat, K , D,IMPORT,FULL,tutor-rag07s.full, STIFF

*smat, M , D,IMPORT,FULL,tutor-rag07s.full, MASS

*smat, G1, D,IMPORT,FULL,tutor-rag07s.full, DAMP

! ** obtain the new eigenproblem matrices

alpha = 1.0

*smat, zMbar, Z, COPY, M

*axpy,, -1/alpha, G1, 1,, zMbar

*smat, zK, Z, COPY, K

*free,K

*free,M

*free,G1

! ** solve the new eigenproblem

/solu

antype, modal

modopt, unsym , 10

*eigen, zK, zMbar,, eigenVal, eigenVec

fini

*free,zK

*free,eigenVec

! ** store the critical speeds

*dim, critspeed1, ARRAY, 5

_coefunit = 60/alpha ! Hz -> rpm

*do,_iloop,1,5

xx = eigenVal(_iloop*2,1)*_coefunit ! real part of the eigenvalue (FW)

critspeed1(_iloop) = xx

*enddo

*free,eigenVal

*status,critspeed1

! ** Obtain the complete critical speed map

! Macro CRITSPEEDMAP.MAC

! ARG1 Number of critical speeds

! ARG2 Number of excitations per revolution

! =0 Defaults to 1.0 (synchronous excitation)

! Bearings stiffness

! ARG3 Lowest value

! ARG4 Highest value

! ARG5 Number of steps

! =0 Defaults to 10

! Rotational velocity direction (normalized to unity)

! ARG6 X component

! ARG7 Y component

! ARG8 Z component

!

! Eigensolver parameter

! ARG9 Beginning of the frequency range (defaults to 1 Hz)

!--------------------------------------------

/show,JPEG

critspeedmap, 5,, kb(1,1), kb(10,1),, 1,0,

]]>I need to reproduce a cyclic loading experiment in ANSYS. I am solving a "static structural" analysis in ANSYS Workbench and ANSYS APDL. My model is two-dimensional with "plane strain" options. My material is non-linear (Voce+Chaboche). My analysis has many load steps (currently 50, but this number may increase).

My total amount of I/O written to disk and read from disk is of the order of 1000 GB. I managed to slightly reduce the amount by using OUTRES commands. I am using these commands to save only the stresses and strains in selected named selections (components).

Is there any way I could further decrease the amount of I/O? Using a coarser mesh or less load steps is not an option.

Kind regards,

rougiecorn

]]>Could I check the stresses induced in the welded joint using ANSYS

I want to heat the plate at 200 degree centigrade. The shaded portion is where I was going to apply the temp boundary condition.

Pls help

THanks

]]>I have tried splitting the block to use a frictional connection but then the body will still penetrate into itself at the bonded contact. Through the share topology in SpaceClaim, it will result in error when the surface generates a fine mesh within the surface and intersects.

Is there any way to prevent this?

Much appreciated.

I did the last one without refinining the mesh to save time.

]]>