dcascap
Aerospace
- Feb 6, 2024
- 18
Hi,
I'm doing a project about an aircraft skin modification, and my client has some guidelines about the FE model that I would like to discuss with you.
Do you know why for a thin metallic structure as the skin, that are mostly modelled as shell elements (linear static) it is allowed to take the von Mises stress of the middle of the plate to calculate reserve factors?
For me this is counterintuitive as shell elements have bending capabilities, and therefore, top/bottom face tend to have higher stresses.
I can imagine that for ultimate load it is permitted to take the middle layer as the top/bottom will probably yield, and then the stresses will redistribute (I'm not sure if this is the correct reasoning).
Anyone has a similar experience, or can guide me to a more complete explanation?
Thanks!
I'm doing a project about an aircraft skin modification, and my client has some guidelines about the FE model that I would like to discuss with you.
Do you know why for a thin metallic structure as the skin, that are mostly modelled as shell elements (linear static) it is allowed to take the von Mises stress of the middle of the plate to calculate reserve factors?
For me this is counterintuitive as shell elements have bending capabilities, and therefore, top/bottom face tend to have higher stresses.
I can imagine that for ultimate load it is permitted to take the middle layer as the top/bottom will probably yield, and then the stresses will redistribute (I'm not sure if this is the correct reasoning).
Anyone has a similar experience, or can guide me to a more complete explanation?
Thanks!