Hello everyone,
I am modeling a honeycomb core that's been experimentally tested in shear
in accordance with the ASTM C273 standards. In order to reduce
computational time, I removed the loading plates and replaced them with
boundary conditions, consisting of a rigid region connected with a master
node. This approach makes the structure much stiffer than the actual core
tested in the experiments, thus I want to introduce some spring stiffness (
maybe ) to reduce the stiffness of the rigid region better representing the
in-between situation of the experiment.
Is there a way to overcome this?
I use ANSYS APDL for my simulation.
Thank you all for your time and help.
Antonis
Student at the University of Athens
On Dec 19, 2022, at 10:59 AM, AntonisΤ useratsi98@gmail.com wrote:
in accordance with the ASTM C273 standards. In order to reduce
computational time, I removed the loading plates and replaced them with
boundary conditions, consisting of a rigid region connected with a
This is a really bad artifice, for many reasons but chiefly because you'll waste a lot of time convincing yourself that the associated error is negligible. Probably it won't be. Model it properly. If your computer can't handle it, make another problem or use another computer.
Christopher Wright P.E. (ret'd) |"They couldn't hit an elephant at
chrisw@skypoint.com | this distance" (last words of Gen.
http://www.skypoint.com/members/chrisw/ | John Sedgwick, Spotsylvania (1864)
Hello Antonis,
You can decompose the honeycomb using CMS reduction. You can see an example
here using the command snippet for reference
https://www.ansystips.com/2017/05/component-mode-synthesiscms.html?m=1
Just make sure to conservatively mesh and set master dofs at connection
points. More points you have the bigger your CMS substructure will be.
Thanks,
Nelson
On Mon, Dec 19, 2022 at 9:00 AM AntonisΤ useratsi98@gmail.com wrote:
Hello everyone,
I am modeling a honeycomb core that's been experimentally tested in shear
in accordance with the ASTM C273 standards. In order to reduce
computational time, I removed the loading plates and replaced them with
boundary conditions, consisting of a rigid region connected with a master
node. This approach makes the structure much stiffer than the actual core
tested in the experiments, thus I want to introduce some spring stiffness (
maybe ) to reduce the stiffness of the rigid region better representing the
in-between situation of the experiment.
Is there a way to overcome this?
I use ANSYS APDL for my simulation.
Thank you all for your time and help.
Antonis
Student at the University of Athens
Xansys mailing list -- xansys-temp@list.xansys.org
To unsubscribe send an email to xansys-temp-leave@list.xansys.org
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Hi Antonis,
I agree with Chris, adding springs is pretty much "cheating" as it is
impossible to know the stiffness of the springs apriori.
Perhaps try "symmetry" to half the model size. Secondly, the plates may be
further approximated with shell elements. I heard it is possible to offset
the interface to the thickness of the plate but have not looked into it
myself. Shell elements may be too much an approximation for what you're
after.
My guess is the swivel joint may throw you off. Note, also, the load axis
that is not parallel to the plates in this picture (in pink line):
https://www.universalgripco.com/astm-c273?lightbox=cwlo
In short, be extra careful in your experiment. This is a very challenging
problem.
Good luck,
Sze Kwan (Jason) Cheah
Graduate Student
University of Minnesota - Twin Cities
On Mon, Dec 19, 2022 at 7:17 PM Nelson Ho nelsonho567@gmail.com wrote:
Hello Antonis,
You can decompose the honeycomb using CMS reduction. You can see an example
here using the command snippet for reference
https://www.ansystips.com/2017/05/component-mode-synthesiscms.html?m=1
Just make sure to conservatively mesh and set master dofs at connection
points. More points you have the bigger your CMS substructure will be.
Thanks,
Nelson
On Mon, Dec 19, 2022 at 9:00 AM AntonisΤ useratsi98@gmail.com wrote:
Hello everyone,
I am modeling a honeycomb core that's been experimentally tested in shear
in accordance with the ASTM C273 standards. In order to reduce
computational time, I removed the loading plates and replaced them with
boundary conditions, consisting of a rigid region connected with a master
node. This approach makes the structure much stiffer than the actual core
tested in the experiments, thus I want to introduce some spring
stiffness (
maybe ) to reduce the stiffness of the rigid region better representing
the
in-between situation of the experiment.
Is there a way to overcome this?
I use ANSYS APDL for my simulation.
Thank you all for your time and help.
Antonis
Student at the University of Athens
Xansys mailing list -- xansys-temp@list.xansys.org
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Oops just realized I mistyped in the email. CMS reduction of connecting
plate (not the honeycomb) if you want to go down that route of generating
super elements.
But if the geometry is simple I agree shelling or coarse mesh will give you
a better answer.
Thanks,
Nelson
On Tue, Dec 20, 2022 at 11:37 AM Sze Kwan Cheah via Xansys <
xansys-temp@list.xansys.org> wrote:
Hi Antonis,
I agree with Chris, adding springs is pretty much "cheating" as it is
impossible to know the stiffness of the springs apriori.
Perhaps try "symmetry" to half the model size. Secondly, the plates may be
further approximated with shell elements. I heard it is possible to offset
the interface to the thickness of the plate but have not looked into it
myself. Shell elements may be too much an approximation for what you're
after.
My guess is the swivel joint may throw you off. Note, also, the load axis
that is not parallel to the plates in this picture (in pink line):
https://www.universalgripco.com/astm-c273?lightbox=cwlo
In short, be extra careful in your experiment. This is a very challenging
problem.
Good luck,
Sze Kwan (Jason) Cheah
Graduate Student
University of Minnesota - Twin Cities
On Mon, Dec 19, 2022 at 7:17 PM Nelson Ho nelsonho567@gmail.com wrote:
Hello Antonis,
You can decompose the honeycomb using CMS reduction. You can see an
example
here using the command snippet for reference
https://www.ansystips.com/2017/05/component-mode-synthesiscms.html?m=1
Just make sure to conservatively mesh and set master dofs at connection
points. More points you have the bigger your CMS substructure will be.
Thanks,
Nelson
On Mon, Dec 19, 2022 at 9:00 AM AntonisΤ useratsi98@gmail.com wrote:
Hello everyone,
I am modeling a honeycomb core that's been experimentally tested in
shear
in accordance with the ASTM C273 standards. In order to reduce
computational time, I removed the loading plates and replaced them with
boundary conditions, consisting of a rigid region connected with a
master
node. This approach makes the structure much stiffer than the actual
core
tested in the experiments, thus I want to introduce some spring
stiffness (
maybe ) to reduce the stiffness of the rigid region better representing
the
in-between situation of the experiment.
Is there a way to overcome this?
I use ANSYS APDL for my simulation.
Thank you all for your time and help.
Antonis
Student at the University of Athens
Xansys mailing list -- xansys-temp@list.xansys.org
To unsubscribe send an email to xansys-temp-leave@list.xansys.org
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changing
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Hello,
Sze, what do you mean by offset the interface? I am using only shell
elements for the whole model.
Can you provide me with papers/documentation that I can look into ?
Thanks a lot,
Antonis
Στις Τρί 20 Δεκ 2022 στις 10:01 μ.μ., ο/η Nelson Ho nelsonho567@gmail.com
έγραψε:
Oops just realized I mistyped in the email. CMS reduction of connecting
plate (not the honeycomb) if you want to go down that route of generating
super elements.
But if the geometry is simple I agree shelling or coarse mesh will give you
a better answer.
Thanks,
Nelson
On Tue, Dec 20, 2022 at 11:37 AM Sze Kwan Cheah via Xansys <
xansys-temp@list.xansys.org> wrote:
Hi Antonis,
I agree with Chris, adding springs is pretty much "cheating" as it is
impossible to know the stiffness of the springs apriori.
Perhaps try "symmetry" to half the model size. Secondly, the plates may
be
further approximated with shell elements. I heard it is possible to
offset
the interface to the thickness of the plate but have not looked into it
myself. Shell elements may be too much an approximation for what you're
after.
My guess is the swivel joint may throw you off. Note, also, the load axis
that is not parallel to the plates in this picture (in pink line):
https://www.universalgripco.com/astm-c273?lightbox=cwlo
In short, be extra careful in your experiment. This is a very challenging
problem.
Good luck,
Sze Kwan (Jason) Cheah
Graduate Student
University of Minnesota - Twin Cities
On Mon, Dec 19, 2022 at 7:17 PM Nelson Ho nelsonho567@gmail.com wrote:
Hello Antonis,
You can decompose the honeycomb using CMS reduction. You can see an
example
here using the command snippet for reference
https://www.ansystips.com/2017/05/component-mode-synthesiscms.html?m=1
Just make sure to conservatively mesh and set master dofs at connection
points. More points you have the bigger your CMS substructure will be.
Thanks,
Nelson
On Mon, Dec 19, 2022 at 9:00 AM AntonisΤ useratsi98@gmail.com wrote:
Hello everyone,
I am modeling a honeycomb core that's been experimentally tested in
shear
in accordance with the ASTM C273 standards. In order to reduce
computational time, I removed the loading plates and replaced them
with
boundary conditions, consisting of a rigid region connected with a
master
node. This approach makes the structure much stiffer than the actual
core
tested in the experiments, thus I want to introduce some spring
stiffness (
maybe ) to reduce the stiffness of the rigid region better
representing
the
in-between situation of the experiment.
Is there a way to overcome this?
I use ANSYS APDL for my simulation.
Thank you all for your time and help.
Antonis
Student at the University of Athens
Xansys mailing list -- xansys-temp@list.xansys.org
To unsubscribe send an email to xansys-temp-leave@list.xansys.org
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changing
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day.
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changing
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Antonis,
To clarify, I was suggesting the possibility of offsetting the nodes of the
loading plates so that you could use shell elements instead of solid
elements for the loading plate to reduce the size of the model. Sounds like
you're already doing that.
From the help manual:
https://www.mm.bme.hu/~gyebro/files/ans_help_v182/ans_cmd/Hlp_C_SECOFFSET.html#SECOFFSET.shells
I'm not sure if it is able to account for loading offset, or is purely a
graphical aid. Others who have tried it could chime in.
Thanks,
Sze Kwan (Jason) Cheah
Graduate Student
University of Minnesota - Twin Cities
On Tue, Dec 20, 2022 at 4:32 PM AntonisΤ useratsi98@gmail.com wrote:
Hello,
Sze, what do you mean by offset the interface? I am using only shell
elements for the whole model.
Can you provide me with papers/documentation that I can look into ?
Thanks a lot,
Antonis
Στις Τρί 20 Δεκ 2022 στις 10:01 μ.μ., ο/η Nelson Ho <nelsonho567@gmail.com
έγραψε:
Oops just realized I mistyped in the email. CMS reduction of connecting
plate (not the honeycomb) if you want to go down that route of generating
super elements.
But if the geometry is simple I agree shelling or coarse mesh will give
you
a better answer.
Thanks,
Nelson
On Tue, Dec 20, 2022 at 11:37 AM Sze Kwan Cheah via Xansys <
xansys-temp@list.xansys.org> wrote:
Hi Antonis,
I agree with Chris, adding springs is pretty much "cheating" as it is
impossible to know the stiffness of the springs apriori.
Perhaps try "symmetry" to half the model size. Secondly, the plates may
be
further approximated with shell elements. I heard it is possible to
offset
the interface to the thickness of the plate but have not looked into it
myself. Shell elements may be too much an approximation for what you're
after.
My guess is the swivel joint may throw you off. Note, also, the load
axis
that is not parallel to the plates in this picture (in pink line):
https://www.universalgripco.com/astm-c273?lightbox=cwlo
In short, be extra careful in your experiment. This is a very
challenging
problem.
Good luck,
Sze Kwan (Jason) Cheah
Graduate Student
University of Minnesota - Twin Cities
On Mon, Dec 19, 2022 at 7:17 PM Nelson Ho nelsonho567@gmail.com
wrote:
Hello Antonis,
You can decompose the honeycomb using CMS reduction. You can see an
example
here using the command snippet for reference
Just make sure to conservatively mesh and set master dofs at
connection
points. More points you have the bigger your CMS substructure will
be.
wrote:
Hello everyone,
I am modeling a honeycomb core that's been experimentally tested in
shear
in accordance with the ASTM C273 standards. In order to reduce
computational time, I removed the loading plates and replaced them
with
boundary conditions, consisting of a rigid region connected with a
master
node. This approach makes the structure much stiffer than the
actual
core
tested in the experiments, thus I want to introduce some spring
stiffness (
maybe ) to reduce the stiffness of the rigid region better
representing
the
in-between situation of the experiment.
Is there a way to overcome this?
I use ANSYS APDL for my simulation.
Thank you all for your time and help.
Antonis
Student at the University of Athens
Xansys mailing list -- xansys-temp@list.xansys.org
To unsubscribe send an email to xansys-temp-leave@list.xansys.org
If you are receiving too many emails from XANSYS please consider
changing
account settings to Digest mode which will send a single email per
day.
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xansys-mod@tynecomp.co.uk and not to the list
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If you are receiving too many emails from XANSYS please consider
changing
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day.
Please send administrative requests such as deletion from XANSYS to
xansys-mod@tynecomp.co.uk and not to the list
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I see you were only referring to the elements, not something I could change
in the modeling process.
Thanks a lot again.
Στις Τετ 21 Δεκ 2022 στις 1:03 π.μ., ο/η Sze Kwan Cheah via Xansys <
xansys-temp@list.xansys.org> έγραψε:
Antonis,
To clarify, I was suggesting the possibility of offsetting the nodes of the
loading plates so that you could use shell elements instead of solid
elements for the loading plate to reduce the size of the model. Sounds like
you're already doing that.
From the help manual:
https://www.mm.bme.hu/~gyebro/files/ans_help_v182/ans_cmd/Hlp_C_SECOFFSET.html#SECOFFSET.shells
I'm not sure if it is able to account for loading offset, or is purely a
graphical aid. Others who have tried it could chime in.
Thanks,
Sze Kwan (Jason) Cheah
Graduate Student
University of Minnesota - Twin Cities
On Tue, Dec 20, 2022 at 4:32 PM AntonisΤ useratsi98@gmail.com wrote:
Hello,
Sze, what do you mean by offset the interface? I am using only shell
elements for the whole model.
Can you provide me with papers/documentation that I can look into ?
Thanks a lot,
Antonis
Στις Τρί 20 Δεκ 2022 στις 10:01 μ.μ., ο/η Nelson Ho <
έγραψε:
Oops just realized I mistyped in the email. CMS reduction of connecting
plate (not the honeycomb) if you want to go down that route of
generating
super elements.
But if the geometry is simple I agree shelling or coarse mesh will give
you
a better answer.
Thanks,
Nelson
On Tue, Dec 20, 2022 at 11:37 AM Sze Kwan Cheah via Xansys <
xansys-temp@list.xansys.org> wrote:
Hi Antonis,
I agree with Chris, adding springs is pretty much "cheating" as it is
impossible to know the stiffness of the springs apriori.
Perhaps try "symmetry" to half the model size. Secondly, the plates
may
be
further approximated with shell elements. I heard it is possible to
offset
the interface to the thickness of the plate but have not looked into
it
myself. Shell elements may be too much an approximation for what
you're
after.
My guess is the swivel joint may throw you off. Note, also, the load
axis
that is not parallel to the plates in this picture (in pink line):
https://www.universalgripco.com/astm-c273?lightbox=cwlo
In short, be extra careful in your experiment. This is a very
challenging
problem.
Good luck,
Sze Kwan (Jason) Cheah
Graduate Student
University of Minnesota - Twin Cities
On Mon, Dec 19, 2022 at 7:17 PM Nelson Ho nelsonho567@gmail.com
wrote:
Hello Antonis,
You can decompose the honeycomb using CMS reduction. You can see an
example
here using the command snippet for reference
Just make sure to conservatively mesh and set master dofs at
connection
points. More points you have the bigger your CMS substructure will
be.
wrote:
Hello everyone,
I am modeling a honeycomb core that's been experimentally tested
in
shear
in accordance with the ASTM C273 standards. In order to reduce
computational time, I removed the loading plates and replaced
them
with
boundary conditions, consisting of a rigid region connected with
a
master
node. This approach makes the structure much stiffer than the
actual
core
tested in the experiments, thus I want to introduce some spring
stiffness (
maybe ) to reduce the stiffness of the rigid region better
representing
the
in-between situation of the experiment.
Is there a way to overcome this?
I use ANSYS APDL for my simulation.
Thank you all for your time and help.
Antonis
Student at the University of Athens
Xansys mailing list -- xansys-temp@list.xansys.org
To unsubscribe send an email to
If you are receiving too many emails from XANSYS please consider
changing
account settings to Digest mode which will send a single email
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to
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Hello All,
Looking any suggestion in element import in APDL. Here is the details of it.
I am running two analysis, one with Structural and other with thermal. I am modifying elements in Structural model (Some geometry) (SOLID185) and then importing it to the Thermal model (SOLID70), somehow, I can see nodes are created however, I could not see element created.
Please do let me if its not clear.
Thanks and Regards
Bhavesh V.
R & D Engineer
EGA, UAE
PS. I am changing ET type to SOLID 70 (On elements which require to import in thermal analysis) before Ewrite command in Structural analysis.
Bhaveshkumar Rameshchandra Varia
Engineer I - R&D
Technology Development & Transfer
Midstream
T +971 2 509 444
<BR>D +97148221034
<BR>M +971543924196
Emirates Global Aluminium
PO Box 109111, Abu Dhabi
United Arab Emirates
This is an e-mail from Emirates Global Aluminium PJSC. Its contents are confidential to the intended recipient. If you are not the intended recipient be advised that you have received this email in error and that any use, dissemination, forwarding, printing or copying of this e-mail is strictly prohibited. It may not be disclosed to or used by anyone other than its intended recipient, nor may it be copied in any way. If received in error please e-mail a reply to the sender and delete it from your system. Although this e-mail has been scanned for viruses, Emirates Global Aluminium cannot ultimately accept any responsibility for viruses and it is your responsibility to scan attachments (if any).
Hello,
See ETCHG command in ur APDL help, ANSYS with automatically change the element type based on the analysis you are performing.
Thanks
Anjum
-----Original Message-----
From: Bhaveshkumar Rameshchandra Varia via Xansys xansys-temp@list.xansys.org
Sent: 09 January 2023 13:54
To: XANSYS Mailing List Home xansys-temp@list.xansys.org
Cc: Bhaveshkumar Rameshchandra Varia bhavaria@ega.ae
Subject: [Xansys] Importing Element File
This mail has been sent by an external source
Hello All,
Looking any suggestion in element import in APDL. Here is the details of it.
I am running two analysis, one with Structural and other with thermal. I am modifying elements in Structural model (Some geometry) (SOLID185) and then importing it to the Thermal model (SOLID70), somehow, I can see nodes are created however, I could not see element created.
Please do let me if its not clear.
Thanks and Regards
Bhavesh V.
R & D Engineer
EGA, UAE
PS. I am changing ET type to SOLID 70 (On elements which require to import in thermal analysis) before Ewrite command in Structural analysis.
Bhaveshkumar Rameshchandra Varia
Engineer I - R&D
Technology Development & Transfer
Midstream
T +971 2 509 444
<BR>D +97148221034
<BR>M +971543924196
Emirates Global Aluminium
PO Box 109111, Abu Dhabi
United Arab Emirates
This is an e-mail from Emirates Global Aluminium PJSC. Its contents are confidential to the intended recipient. If you are not the intended recipient be advised that you have received this email in error and that any use, dissemination, forwarding, printing or copying of this e-mail is strictly prohibited. It may not be disclosed to or used by anyone other than its intended recipient, nor may it be copied in any way. If received in error please e-mail a reply to the sender and delete it from your system. Although this e-mail has been scanned for viruses, Emirates Global Aluminium cannot ultimately accept any responsibility for viruses and it is your responsibility to scan attachments (if any).
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