Dear Meric Büyükkoyuncu, thank you very very much for the wonderful job of teaching the theory and the software side by side. I have learned a lot from you and always look forward to your tutorials. I requested you for some damage tutorials of composite material and I can see you are progressing towards that. I appreciate your effort. Hats off Sir.
first of all thank you for the hard work , i have a little problem : im working on a similar example ( bendig of composite plates simply supported in the two opposite edges ( X direction ) and loaded with a linear pressure ( in x=a/2) and i would like to know the expression of w(x,y) in this case !! hope u read this comment ASAP
@@mericbuyukkoyuncu385 no sir this example is very well explained , im looking for the deflaction in case we have plates with two opposite edges simply supported
@@mouradboussik7268 I got it now. You can use this book to derive governing equation for your case "Plate and Panel Structures of Isotropic, Composite and Piezoelectric Materials, Including Sandwich Construction (Solid Mechanics and Its Applications)"
First of all ,thank you for appreciable explaining , I want to ask you about the boundary conditions, if I'm using another theory different from the assumption that you have made it , what should I do and how to simulate it ?
Thank you for your nice comments. Firstly, the only thing you need to change is boundary conditions. Then, you can solve your case. I don't know your case's boundary conditions, but you can check these boundary conditions from literature.
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. and 1:02 how comes the formula of v23, because i used this formula to verify any composite material from google, it's all wrong.
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Amazing skills with Ansys Meric! WOW!
Dear Meric Büyükkoyuncu, thank you very very much for the wonderful job of teaching the theory and the software side by side. I have learned a lot from you and always look forward to your tutorials. I requested you for some damage tutorials of composite material and I can see you are progressing towards that. I appreciate your effort. Hats off Sir.
Thank you for your kind comments. I am working on fracture topics and delamination of composites etc. Wait for the next videos. Probably next month.
Thank you.. I am learning ansys ACP its more useful for me and waiting for more videos
Nice and helpful work!
Thank you
Thank you for your efforts
Très intéressant, Merci beaucoup.
first of all thank you for the hard work ,
i have a little problem : im working on a similar example ( bendig of composite plates simply supported in the two opposite edges ( X direction ) and loaded with a linear pressure ( in x=a/2) and i would like to know the expression of w(x,y) in this case !!
hope u read this comment ASAP
Thank you for your kind comments. I can not understand what do you mean with expression ? Is not clear in the video ?
@@mericbuyukkoyuncu385 no sir this example is very well explained , im looking for the deflaction in case we have plates with two opposite edges simply supported
@@mouradboussik7268 I got it now. You can use this book to derive governing equation for your case "Plate and Panel Structures of Isotropic, Composite and Piezoelectric Materials, Including Sandwich Construction (Solid Mechanics and Its Applications)"
@@mericbuyukkoyuncu385 thank you very much sir for your help
thank you very much, please i have question, how i can export this composite material from ACP to material data in Ansys
جزاك الله خيرا
First of all ,thank you for appreciable explaining , I want to ask you about the boundary conditions, if I'm using another theory different from the assumption that you have made it , what should I do and how to simulate it ?
Thank you for your nice comments. Firstly, the only thing you need to change is boundary conditions. Then, you can solve your case. I don't know your case's boundary conditions, but you can check these boundary conditions from literature.
The video clearly explains everything. Can I get the reference to do fixed boundary condition , any books or journals for the same .
I have a serious problem 😕 , I can't fix my engineering data therefore I can't add any new material , May You Help me please , I need a serious help 🙏
@@EsraaElias you can reach me via linkedin.
Good job, I learned something here :)
Thank you
Thank you very much
what should I insert for bending analysis of composite beams?
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.
and 1:02 how comes the formula of v23, because i used this formula to verify any composite material from google, it's all wrong.
plz timesteps in description