Hi Nathan, I followed exact same steps as u did but ended up with an informational notice while updating my project after named selection that " (DP 0) The Model component in ACP (Pre) requires user input before it can be updated. For instructions on how to address the cell in its current state, click the blue triangle in the lower right corner of the cell in the Project Schematic." I am unable to understand where could I possibly go wrong. so please help me out with this. FYI my CAD part is of ".igs" and ANSYS 19.2 version my project is saved in .wbpg format please help me through this
Hi Nathan , thanks for this good video , understood very well. I have a small doubt, what if ,there is a shell and a solid in a assembly . Which one i should choose while doing static structural ? And also solid doesn't have any stack up sequence, so should I do the same how you did for honey comb structure ?
Hi Nathan, I'm trying to do design a carbon fibre composite monocoque WITH honeycomb core for our formula student competition. So far, I just have the thickness of my model at 20mm (for every surface/all the way round). I plan to do various structural tests in ANSYS and from these tests I want to determine weak points in the structure and then reinforce them with more material in Solidworks/ANSYS (not sure) and retest again until I have an optimum model. I have just been watching through this tutorial and I noticed you assigned a thickness of 3mm at around (2:37 - 2:48) and said: "ACP will reset that thickness and apply the correct thickness later on". My first question is: What was the thickness of the model before you imported it and made that 3mm assignment? And my second question is: Does the thickness of your model (in Solidworks for my case) matter, in that could you have a completely solid monocoque for example and import that? And my third question, (which depends on the answer of the first 2 questions) is: When I want to reinforce certain areas (when I find out they are weak from the structural tests), is there a way of applying more layers at specific regions in ANSYS or do I need to change the thickness in Solidworks at the appropriate regions I want to reinforce? And how do I do this? Any advice would be extremely helpful to me and I can't tell you how much I'd appreciate it.
Hi Fred, so the way that I did the analysis (and the preferable way for most geometries) is to use sheet bodies instead of solid bodies. A sheet body has no thickness associated with it which is why I had to assign a thickness initially. By using sheets, Ansys can add additional "layers" of elements that represent the additional plies and it doesn't conflict with a pre-determined thickness of a solid body. The process I use to get these sheet bodies is to create a solid body of my geometry and then "extract" the faces that will be contacting the mold. To define sections of the sheet body that you want to add additional plies, I'd recommend adding sketches on the surface and using a "divide face" tool to divide the face at the sketches. I use these operations in NX but I'm sure SolidWorks has similar tools.
@@nathan_orf Nathan, thank you so much for your response. From what you've said I was just unsure about the sheet body part...I was wondering firstly if you create the sheet body in ANSYS or if you do that in SolidWorks? Also the part about adding sketches on the surface using a "divide face" tool you refer to, I was unsure how you would do this if you have a solid body model in NX (SolidWorks). I'm unsure because you said that the outside of the solid body is the outermost layer ("faces that will be contacting the mold") , so if I'm adding a sketch on the outermost layer wouldn't that become an issue because essentially my rosette direction would already be pointing inwards (building ply layers inwards), so when I select that sketch on the outer layer to add additional layers to, won't that mess up the layers that are already there? I was thinking I need to select an inner layer sketch as I'd be reinforcing my structure internally. The problem I'm predicting that might happen when selecting a sketch that is part of the outer layer is that when I start defining the ply structure for that sketch, I'm thinking the honeycomb core for that region may get out of alignment with the rest of the honeycomb core, or even some of the carbon fibre ply's being out of line with each other? I would really appreciate your thoughts on this. Hopefully Iv'e been clear enough. Thanks again for your last reply, very helpful.
You would create the sheet body in Ansys. For your second question, you essentially want to project, draw, or offset a sketch onto the sheet body that was extracted from the solid. Also, your rosette direction defines the X and Y coordinates on the surface (like 0 and 90 degree ply directions), not the Z coordinate defining the stacking direction. I'm not really sure what you mean by your other question, but your divided face area will get projected normal to the surface. So let's say you have a divided face area that you just want to have a core material but you want there to be four plies above and four below the core (spanning the entire area of the part). ACP will apply the thickness of the first four plies, then project the core area normal to the surface and apply the core thickness. So if you're dealing with very very thick or high-curvature parts, your divided face area will get warped a little bit when applied to one of the interior plies
Hello, thank you very much for this wonderful lecture. I have a question in the ANSYS program. I want to prepare, for example, a superimposed material in the form of a layer consisting of two materials, the first is fiber of any kind, and the other is a polymer material, with dimensions of 10 * 10 cm and a thickness of 2 cm. How do I calculate or how can I enter the volume fraction values For both subjects in the ANSYS program, for example, the first subject is 60% and the second subject is 40%. I hope you will help me in solving this problem. I mean, how can the volumetric fraction or weight ratios be calculated for each subject in the ANSYS program? With appreciation❤❤
I liked the video, I am having a problem studying an assembly where one of the pieces is made of composite material. When placing the assembly in the ACP module, when I go to the setup only the part to which I am going to apply the composite material appears (I understand that it is because I defined it as a surface previously), but when I link the ACP module to the structural static I only see links the composite part and not the entire assembly.
very helpfull, when we have to use post ACP for that model can be made without Post ACP and Static structurl is enough so, what is benefitial of post ACP module ?
ACP Post allows you to perform more rigorous analysis on stuff like core failure and interlaminar stresses. It can also be more accurate for very complicated structures. For more basic structures you'll notice that the ACP Post and Static Structural results are basically identical.
As someone who has not a lot of experience in Ansys ACP is there an option to define E, and G-moduli after creating the composite with all it's plies? Like say if I want a composite with E1, E2 65 GPa and G12 5 GPa after creating a 45/90/45 or 0/45/90/45/0 composite or something like that?
Hi Nathan, This is my first-time use ACP.I'm trying to analysis V-Belt transmission transient structural with composite structures. The belt is a composite structure composed of glass-fiber, Base Rubber Compound, and Protective Cover. Could you please gave me some advice?
sorry, can i ask a question? how can i create a material with only E1, E2, v12 and G12? because in CLT plane element don't consider the direction of Z axial. i used ACP and transform to shell element, but if a change the value of G23, the result under torsion won't be the same? but i should be the same. why? can you help me? thanks.
Hi, when I transfer Acp pre setup to static structural's model there is no selection as shell or solid body like yours. I just want to combine with another solid model with acp and examine solution.
Hi Nathan! I get this error message when I want to add fabrics like in your video, do you have any idea why? 15:03:18: Failed to create property dialog of FabricHandler(Fabric.1)! 'ascii' codec can't decode byte 0xc3 in position 0: ordinal not in range(128)
Could you please explain the meaning of Top-down & Bottom-up in Layup sequence. I am little confused whether the ply starts from top surface to bottom one in Top-down layup sequence?
See my comment on it at 7:03 in the video. Top-down means that the first ply in the list will be the first ply laid into the mold. Bottom-up would be the inverse
hello I get this error "Update failed for the Setup component in ACP (Pre). The update of the Setup component completed but no outputs were generated. Please check that ACP is fully defined and try again." help
This error usually means that there is something in ACP pre that is required for solving, but you forgot to set up. Unfortunately, it's tough for me to troubleshoot further because there are a lot of steps to set up ACP pre
I want to simulate the process of liquid phase impregnation into composite C/C materials, After that Carbonization process is high temp, and want to calculate the porosity of the material through each impregnation process? Can you help me develop some ideas?
Hi, where did you get those materials from? Like, is there any special library out there or you just added them manually? It'd be of great help if someone could provide a rapid response. Thx in advance
They were included with the software but I didn't install the program so I don't know if you had to select a special library to retrieve the composite materials
Sir I have two named selection. When I am applying stress the stress is not applied to all layers .only stress is applied to bottom layer..how can I resolve
I always get an error, when i try to simulate a shell modell with two or more surfaces like the bowl in the tutorial. Mechanical always fails to do the structural analysis and in solutions everything gets a red bolt and under results everything is red
One thing to check is to make sure you are properly constraining the part. If you apply a load to the model and one of the degrees of freedom are unconstrained, it was fail the calculation. Try using a fixed constraint
Hi, i had a doubt. How do you create tapered plys with different lengths so as to create the tapered effect in acp pre while stacking up the different layers
The only way that I figured out how to do this is by dividing the surface into different sections. You can then select certain areas of the surface to define where the tapered ply begins and ends. Dividing the surfaces needs to be done in the CAD program that you're using
Hi thanks for your helpful video! Although I selected the materials in 'Engineering Data' just like you, it don't appear in my ACP Model>Material Data> Materials on the left side. This folder is empty. Any ideas? Thanks a lot!!!! Carina
Is there any significant difference in simulation when transferring shell or solid composite data? I see that both options show the plies we defined in ACP Pre, but how can I choose?
While I have not experimented with the differences between simulating shell and solid elements, I imagine the results would be quite different. When transferring shell data, ACP sends 2D planar elements (aka TRI or QUAD elements) to Static Structural. These type of elements have a thickness assigned to them that is used in calculating stresses/strains, but the thickness is not modelled. This is likely more accurate since a composite structure is essentially just a bunch of very thin 2D planes stacked on top of each other. On the other hand, when transferring solid data, 3D elements (aka TET or HEX elements) are used. These type of elements work great for something like a machined aluminum part, but are less accurate for thin structures like pressure vessels, sheet metal parts, or monocoque car bodies (for all you FSAE students out there). 3D elements are also going to take a lot longer to compute than 2D elements. Tldr: Shell elements are going to give you a more accurate result for thin composite structures.
Here's a good summary of 1D, 2D, and 3D element types. One thing that can be confusing is that some elements have different names in different FEA software but behave the exact same way (e.g. HEX20 and BRICK20 are both rectangular prism elements with nodes at the corners and midpoints) asrengineering.com/2019/09/23/fea-mesh-elements-nodes-guide-intro-to-fea/
@@nathan_orf It's really helpful. I'm simulating a i-beam with rounds and I've found some problems. The first one was in the ACP Pre, because the plies in a C format were misaligned when I created the solid model. The second one was the reason of this question. Briefly, I had to make an assembly with the beam and some external models (actuator and brackets). It went terrible wrong when I tried to transfer solid composite data, but I didn't know if there were some problems with transferring shell data to simulate composites. I'll try to do it now. Thanks!
I'm using ANSYS structural, I applied two forces of the same value on both sides of the body I"m working on (a plate) and I had an error saying there isn't enough stress applied to prevent rigid body movement, but the body shouldn't move since there are two forces of the same value applied in two opposite directions (and I don't want to use the fixed support) what should I do? thank you for the video, it was really helfup. Please help me if you can, I really need this.
To our human brains, it makes sense that the part wouldn't move when the forces are perfectly equal and opposite. However, computers are weird and a slight imbalance in the model (potentially from the mesh or node locations) can tip the simulation into rigid body motion. If you'd like to avoid using a fixed support, I would apply boundary conditions to a vertex. Set translation to zero in the directions that are causing you issues and this should fix the issues. You could also try doing this for a second vertex to prevent rotation as well. Hopefully this helps
@@nathan_orf Thank you so much. Would you please tell me where to set those conditions (where would I find that option) I'm sorry, I'm new to static structural. Thank you so much for answering.
@@nadj_b once you're in the Statuc Structural module, locate the toolbar on the left side. Right click on Static Structural, then click Insert, then Displacement. From here, you can select a vertex and define the directions of zero displacement
it depends on the direction of your forces and the directions that you're limiting vertex displacement. If you do it correctly and choose a vertex that's far away from where you expect large displacements to occur, it shouldn't have a big effect on deformations. Beyond that, I don't think I can help you there since I don't know what your model looks like
Does anybody know why the material data of the plies isn´t transferred to the static structural from the ACP Pre? When I open the Static Structural there is a blue question mark at the plies and the empty material data field in the information screen is highlighted in red. I couldn´t figure it out although I did everything exactly like in the video
Not sure, maybe just make sure you updated and saved the project in ACP Pre? Also make sure you're selecting "import shell composite data" if you're using shell elements. I don't think it will import anything if you try to import solid data and are using shell elements
@@nathan_orf thanks for answering. I did everything you mentioned ... updated everything, selected shell components (solid didn´t work either),etc. ... like I said I could not figure out where the problem could be it´s like the static structural could not load any material data from the previous steps
Hallo Nathan, my result inverse reserve Composite mac and min is ZERO (0), i think my step bye step is true, i follow your tutorials, so what can i do for result? Thanks Nathan
I'm not sure, it could be one of many things. Did you assign failure criteria like I did around 17:40 in the video? Did the simulation give you a result for the Safety Factor or Safety Margin?
Hi, My name is Julieth, I 'm a mechanical engineering, and your video is really good, but I have a question, is posible doing this type of analysis for a pressure vessel, I need to do that
Yes, I've done this before too. Just apply a pressure load to the interior surface of the vessel. Be careful with boundary conditions around the opening/gasket area because you can easily over constrain the system which can give you wacky results.
@@nathan_orf __________________________ my email is disotop@unal.edu.co, if you want to, I would like to exchage info about mechanical desing, wish you a nice day
Sorry, I haven't played around with solid models in ACP. I would recommend using a sheet body instead of a solid body since almost all composite parts are created using thin plies that are layered on top of each other
Can someone help me? I have a CAD file that imports as a solid and therefore I cannot shell mesh. How can I rectify this so that I can assign the thickness as Nathan does and shell mesh? Thanks in advance!
Charlotte Draper are you able to extract the surface from the solid CAD model? If you can do that, you should be able to easily import the surface into Ansys
Hi Nathan. I know you didn't cover this in your tutorial, however, I need to model frictional contact between two perpendicular panels. The contact will therefore comprise of a contact body on part of the surface of one panel and the target body on the thickness of the perpedicular panel, created by the layup in ACP Pre. In essence, I am struggling to find a way to define the contact target region, as that surface only exists as a result of the layup and not the defined geometry, therefore, there is not 'surface' to select. Grateful for any insights you may have (or anyone else!). Thanks in advance.
Hello, thank you very much for this wonderful lecture. I have a question in the ANSYS program. I want to prepare, for example, a superimposed material in the form of a layer consisting of two materials, the first is fiber of any kind, and the other is a polymer material, with dimensions of 10 * 10 cm and a thickness of 2 cm. How do I calculate or how can I enter the volume fraction values For both materials in the ANSYS program, for example, the first material is 60% and the second material is 40%. I hope you will help me in solving this problem. I mean, how can the volumetric fraction or weight ratios be calculated for each materials in the ANSYS program? With appreciation
Really helpful, simple and concise but at the same time complete and clear. Congrats man!
Probably the best Ansys tutorial out there
The best tutorial ever! thank you mate, you are the only guy on yt who is able to explain why you have to click stuff ...
This is a really great tutorial, thanks Nathan.
Thank you very much for this tutorial! Waiting for the next one!
Great Video. Thanks Nathan.
Excellent tutrial
Thanks for the video Norf!
Could you please make a video on how to plot/find residual stress distribution in composites induced while manufacturing/curing.
Excellent, Thank You!
Hi Nathan, I followed exact same steps as u did but ended up with an informational notice while updating my project after named selection that
" (DP 0) The Model component in ACP (Pre) requires user input before it can be updated. For instructions on how to address the cell in its current state, click the blue triangle in the lower right corner of the cell in the Project Schematic."
I am unable to understand where could I possibly go wrong. so please help me out with this.
FYI my CAD part is of ".igs"
and ANSYS 19.2 version
my project is saved in .wbpg format
please help me through this
Hi Nathan , thanks for this good video , understood very well. I have a small doubt, what if ,there is a shell and a solid in a assembly . Which one i should choose while doing static structural ? And also solid doesn't have any stack up sequence, so should I do the same how you did for honey comb structure ?
Thanx a lot.. helpfull 👌
Hi Nathan, I'm trying to do design a carbon fibre composite monocoque WITH honeycomb core for our formula student competition. So far, I just have the thickness of my model at 20mm (for every surface/all the way round). I plan to do various structural tests in ANSYS and from these tests I want to determine weak points in the structure and then reinforce them with more material in Solidworks/ANSYS (not sure) and retest again until I have an optimum model.
I have just been watching through this tutorial and I noticed you assigned a thickness of 3mm at around (2:37 - 2:48) and said:
"ACP will reset that thickness and apply the correct thickness later on".
My first question is:
What was the thickness of the model before you imported it and made that 3mm assignment?
And my second question is: Does the thickness of your model (in Solidworks for my case) matter, in that could you have a completely solid monocoque for example and import that?
And my third question, (which depends on the answer of the first 2 questions) is: When I want to reinforce certain areas (when I find out they are weak from the structural tests), is there a way of applying more layers at specific regions in ANSYS or do I need to change the thickness in Solidworks at the appropriate regions I want to reinforce? And how do I do this?
Any advice would be extremely helpful to me and I can't tell you how much I'd appreciate it.
Hi Fred, so the way that I did the analysis (and the preferable way for most geometries) is to use sheet bodies instead of solid bodies. A sheet body has no thickness associated with it which is why I had to assign a thickness initially. By using sheets, Ansys can add additional "layers" of elements that represent the additional plies and it doesn't conflict with a pre-determined thickness of a solid body. The process I use to get these sheet bodies is to create a solid body of my geometry and then "extract" the faces that will be contacting the mold. To define sections of the sheet body that you want to add additional plies, I'd recommend adding sketches on the surface and using a "divide face" tool to divide the face at the sketches. I use these operations in NX but I'm sure SolidWorks has similar tools.
@@nathan_orf Nathan, thank you so much for your response. From what you've said I was just unsure about the sheet body part...I was wondering firstly if you create the sheet body in ANSYS or if you do that in SolidWorks?
Also the part about adding sketches on the surface using a "divide face" tool you refer to, I was unsure how you would do this if you have a solid body model in NX (SolidWorks). I'm unsure because you said that the outside of the solid body is the outermost layer ("faces that will be contacting the mold") , so if I'm adding a sketch on the outermost layer wouldn't that become an issue because essentially my rosette direction would already be pointing inwards (building ply layers inwards), so when I select that sketch on the outer layer to add additional layers to, won't that mess up the layers that are already there? I was thinking I need to select an inner layer sketch as I'd be reinforcing my structure internally. The problem I'm predicting that might happen when selecting a sketch that is part of the outer layer is that when I start defining the ply structure for that sketch, I'm thinking the honeycomb core for that region may get out of alignment with the rest of the honeycomb core, or even some of the carbon fibre ply's being out of line with each other? I would really appreciate your thoughts on this. Hopefully Iv'e been clear enough. Thanks again for your last reply, very helpful.
?
You would create the sheet body in Ansys.
For your second question, you essentially want to project, draw, or offset a sketch onto the sheet body that was extracted from the solid. Also, your rosette direction defines the X and Y coordinates on the surface (like 0 and 90 degree ply directions), not the Z coordinate defining the stacking direction. I'm not really sure what you mean by your other question, but your divided face area will get projected normal to the surface. So let's say you have a divided face area that you just want to have a core material but you want there to be four plies above and four below the core (spanning the entire area of the part). ACP will apply the thickness of the first four plies, then project the core area normal to the surface and apply the core thickness. So if you're dealing with very very thick or high-curvature parts, your divided face area will get warped a little bit when applied to one of the interior plies
Hello, thank you very much for this wonderful lecture. I have a question in the ANSYS program. I want to prepare, for example, a superimposed material in the form of a layer consisting of two materials, the first is fiber of any kind, and the other is a polymer material, with dimensions of 10 * 10 cm and a thickness of 2 cm. How do I calculate or how can I enter the volume fraction values For both subjects in the ANSYS program, for example, the first subject is 60% and the second subject is 40%. I hope you will help me in solving this problem. I mean, how can the volumetric fraction or weight ratios be calculated for each subject in the ANSYS program? With appreciation❤❤
I liked the video, I am having a problem studying an assembly where one of the pieces is made of composite material. When placing the assembly in the ACP module, when I go to the setup only the part to which I am going to apply the composite material appears (I understand that it is because I defined it as a surface previously), but when I link the ACP module to the structural static I only see links the composite part and not the entire assembly.
Hi I’m exactly facing this same issue. Did you come to know the solution for this?
very helpfull, when we have to use post ACP for that model can be made without Post ACP and Static structurl is enough so, what is benefitial of post ACP module ?
ACP Post allows you to perform more rigorous analysis on stuff like core failure and interlaminar stresses. It can also be more accurate for very complicated structures. For more basic structures you'll notice that the ACP Post and Static Structural results are basically identical.
As someone who has not a lot of experience in Ansys ACP is there an option to define E, and G-moduli after creating the composite with all it's plies? Like say if I want a composite with E1, E2 65 GPa and G12 5 GPa after creating a 45/90/45 or 0/45/90/45/0 composite or something like that?
Hi Nathan, This is my first-time use ACP.I'm trying to analysis V-Belt transmission transient structural with composite structures. The belt is a composite structure composed of glass-fiber, Base Rubber Compound, and Protective Cover. Could you please gave me some advice?
sorry, can i ask a question? how can i create a material with only E1, E2, v12 and G12? because in CLT plane element don't consider the direction of Z axial. i used ACP and transform to shell element, but if a change the value of G23, the result under torsion won't be the same? but i should be the same. why? can you help me? thanks.
Hi, when I transfer Acp pre setup to static structural's model there is no selection as shell or solid body like yours. I just want to combine with another solid model with acp and examine solution.
Could you do one on defining a ply-drop off and making a tapered symmetrical beam?
Hi Nathan! I get this error message when I want to add fabrics like in your video, do you have any idea why?
15:03:18: Failed to create property dialog of FabricHandler(Fabric.1)! 'ascii' codec can't decode byte 0xc3 in position 0: ordinal not in range(128)
Sorry Patrick, I've never seen that error before
Could you please explain the meaning of Top-down & Bottom-up in Layup sequence. I am little confused whether the ply starts from top surface to bottom one in Top-down layup sequence?
See my comment on it at 7:03 in the video. Top-down means that the first ply in the list will be the first ply laid into the mold. Bottom-up would be the inverse
@@nathan_orf Thank you
thank you very much, please i have question, how i can export this composite material from ACP to material data in Ansys
Am trying to do the same for solid bodies. My geometry loads up correctly in geometry modeler but I can only see surfaces in ACP setup.Any idea why?
Sorry Joseph, I've never used solids in ACP so I won't be able to help you there
hello
I get this error "Update failed for the Setup component in ACP (Pre). The update of the Setup component completed but no outputs were generated.
Please check that ACP is fully defined and try again." help
This error usually means that there is something in ACP pre that is required for solving, but you forgot to set up. Unfortunately, it's tough for me to troubleshoot further because there are a lot of steps to set up ACP pre
I want to simulate the process of liquid phase impregnation into composite C/C materials, After that Carbonization process is high temp, and want to calculate the porosity of the material through each impregnation process? Can you help me develop some ideas?
What next, sir?
How to create the hybride composite beam i.e. Shape memory alloys wire is embedded in one layer
Hi, where did you get those materials from? Like, is there any special library out there or you just added them manually? It'd be of great help if someone could provide a rapid response. Thx in advance
They were included with the software but I didn't install the program so I don't know if you had to select a special library to retrieve the composite materials
Sir I have two named selection. When I am applying stress the stress is not applied to all layers .only stress is applied to bottom layer..how can I resolve
I always get an error, when i try to simulate a shell modell with two or more surfaces like the bowl in the tutorial. Mechanical always fails to do the structural analysis and in solutions everything gets a red bolt and under results everything is red
One thing to check is to make sure you are properly constraining the part. If you apply a load to the model and one of the degrees of freedom are unconstrained, it was fail the calculation. Try using a fixed constraint
Hi, i had a doubt. How do you create tapered plys with different lengths so as to create the tapered effect in acp pre while stacking up the different layers
The only way that I figured out how to do this is by dividing the surface into different sections. You can then select certain areas of the surface to define where the tapered ply begins and ends. Dividing the surfaces needs to be done in the CAD program that you're using
Hi thanks for your helpful video! Although I selected the materials in 'Engineering Data' just like you, it don't appear in my ACP Model>Material Data> Materials on the left side. This folder is empty. Any ideas? Thanks a lot!!!! Carina
Sorry, that's a weird issue and I'm not too sure why the materials aren't showing up for you
Hello Nathan , I'm fracture mechanics student. I'm working on fiber reinforced composite can you help with that ?
Is there any significant difference in simulation when transferring shell or solid composite data? I see that both options show the plies we defined in ACP Pre, but how can I choose?
While I have not experimented with the differences between simulating shell and solid elements, I imagine the results would be quite different. When transferring shell data, ACP sends 2D planar elements (aka TRI or QUAD elements) to Static Structural. These type of elements have a thickness assigned to them that is used in calculating stresses/strains, but the thickness is not modelled. This is likely more accurate since a composite structure is essentially just a bunch of very thin 2D planes stacked on top of each other. On the other hand, when transferring solid data, 3D elements (aka TET or HEX elements) are used. These type of elements work great for something like a machined aluminum part, but are less accurate for thin structures like pressure vessels, sheet metal parts, or monocoque car bodies (for all you FSAE students out there). 3D elements are also going to take a lot longer to compute than 2D elements.
Tldr: Shell elements are going to give you a more accurate result for thin composite structures.
Here's a good summary of 1D, 2D, and 3D element types. One thing that can be confusing is that some elements have different names in different FEA software but behave the exact same way (e.g. HEX20 and BRICK20 are both rectangular prism elements with nodes at the corners and midpoints)
asrengineering.com/2019/09/23/fea-mesh-elements-nodes-guide-intro-to-fea/
@@nathan_orf It's really helpful. I'm simulating a i-beam with rounds and I've found some problems. The first one was in the ACP Pre, because the plies in a C format were misaligned when I created the solid model. The second one was the reason of this question. Briefly, I had to make an assembly with the beam and some external models (actuator and brackets). It went terrible wrong when I tried to transfer solid composite data, but I didn't know if there were some problems with transferring shell data to simulate composites. I'll try to do it now. Thanks!
I'm using ANSYS structural, I applied two forces of the same value on both sides of the body I"m working on (a plate) and I had an error saying there isn't enough stress applied to prevent rigid body movement, but the body shouldn't move since there are two forces of the same value applied in two opposite directions (and I don't want to use the fixed support) what should I do? thank you for the video, it was really helfup. Please help me if you can, I really need this.
To our human brains, it makes sense that the part wouldn't move when the forces are perfectly equal and opposite. However, computers are weird and a slight imbalance in the model (potentially from the mesh or node locations) can tip the simulation into rigid body motion.
If you'd like to avoid using a fixed support, I would apply boundary conditions to a vertex. Set translation to zero in the directions that are causing you issues and this should fix the issues. You could also try doing this for a second vertex to prevent rotation as well. Hopefully this helps
@@nathan_orf Thank you so much. Would you please tell me where to set those conditions (where would I find that option) I'm sorry, I'm new to static structural. Thank you so much for answering.
@@nadj_b once you're in the Statuc Structural module, locate the toolbar on the left side. Right click on Static Structural, then click Insert, then Displacement. From here, you can select a vertex and define the directions of zero displacement
@@nathan_orf Okay, thank you so much for your time !
it depends on the direction of your forces and the directions that you're limiting vertex displacement. If you do it correctly and choose a vertex that's far away from where you expect large displacements to occur, it shouldn't have a big effect on deformations. Beyond that, I don't think I can help you there since I don't know what your model looks like
Hello,
How can I calculate DC resistance in Ansys Maxwell
Does anybody know why the material data of the plies isn´t transferred to the static structural from the ACP Pre? When I open the Static Structural there is a blue question mark at the plies and the empty material data field in the information screen is highlighted in red. I couldn´t figure it out although I did everything exactly like in the video
Not sure, maybe just make sure you updated and saved the project in ACP Pre? Also make sure you're selecting "import shell composite data" if you're using shell elements. I don't think it will import anything if you try to import solid data and are using shell elements
@@nathan_orf thanks for answering. I did everything you mentioned ... updated everything, selected shell components (solid didn´t work either),etc. ... like I said I could not figure out where the problem could be it´s like the static structural could not load any material data from the previous steps
Hallo Nathan, my result inverse reserve Composite mac and min is ZERO (0), i think my step bye step is true, i follow your tutorials, so what can i do for result? Thanks Nathan
I'm not sure, it could be one of many things. Did you assign failure criteria like I did around 17:40 in the video? Did the simulation give you a result for the Safety Factor or Safety Margin?
where is the geometry? :(
I coudn't find composite failure tool in solution?
hi there! why when I click on F1, I can't see the help? thanks in advance!
ruclips.net/video/29PdP814xkM/видео.html
@@engineeringsimulationstudi1404 What do you mean? thank you
Hi, My name is Julieth, I 'm a mechanical engineering, and your video is really good, but I have a question, is posible doing this type of analysis for a pressure vessel, I need to do that
Yes, I've done this before too. Just apply a pressure load to the interior surface of the vessel. Be careful with boundary conditions around the opening/gasket area because you can easily over constrain the system which can give you wacky results.
@@nathan_orf Thanks for your answer
@@nathan_orf __________________________
my email is disotop@unal.edu.co, if you want to, I would like to exchage info about mechanical desing, wish you a nice day
Hello, why did you add Honeycomb? I am learning about ansys, Thanks
I did this to demonstrate using core material and applying core-related failure criteria
I have a problem: Failed to move file from solver directory to scratch directory: file.rst
Failed to move file from solver directory to scratch directory: file.rst
at 2:00 could you send a link to your file? what should be taken if we don't have that file?
I would recommend creating your own model. Unfortunately, I haven't had access to that file for years
what is the difference betwen ASP(PRE) and ASP(POST)?
ACP (Pre) is used for defining the ply orientations, materials, and locations. ACP (Post) is used for analyzing the results of the simulation
Hello sir how to download this software
Can you please tell how to do acp for solid model
Sorry, I haven't played around with solid models in ACP. I would recommend using a sheet body instead of a solid body since almost all composite parts are created using thin plies that are layered on top of each other
Can someone help me? I have a CAD file that imports as a solid and therefore I cannot shell mesh. How can I rectify this so that I can assign the thickness as Nathan does and shell mesh? Thanks in advance!
Charlotte Draper are you able to extract the surface from the solid CAD model? If you can do that, you should be able to easily import the surface into Ansys
Sorted and managed to model my composite start to finish. Thanks for the tutorial!
Hi Nathan. I know you didn't cover this in your tutorial, however, I need to model frictional contact between two perpendicular panels. The contact will therefore comprise of a contact body on part of the surface of one panel and the target body on the thickness of the perpedicular panel, created by the layup in ACP Pre. In essence, I am struggling to find a way to define the contact target region, as that surface only exists as a result of the layup and not the defined geometry, therefore, there is not 'surface' to select.
Grateful for any insights you may have (or anyone else!).
Thanks in advance.
Sorry I haven't specifically tried this. I can definitely see where the issue arises though.
Thank you anyway!
Hello, thank you very much for this wonderful lecture. I have a question in the ANSYS program. I want to prepare, for example, a superimposed material in the form of a layer consisting of two materials, the first is fiber of any kind, and the other is a polymer material, with dimensions of 10 * 10 cm and a thickness of 2 cm. How do I calculate or how can I enter the volume fraction values For both materials in the ANSYS program, for example, the first material is 60% and the second material is 40%. I hope you will help me in solving this problem. I mean, how can the volumetric fraction or weight ratios be calculated for each materials in the ANSYS program? With appreciation