I am trying to analyse a divan and i just want to model a basic outline model to see how the deflection is using honeycomb structure.so i juss want to tie nodes at the interface.
how do we go about modeling a complicated honeycomb design using pcomp.suppose there are multiple parts connected to one another . do we have to assign local orientation to see that the face of each part falls on the x-y plane.
i always thought the significance of tying nodes is to force the 2 nodes to behave in the same fashion..isnt there a direct tie option in nastran? thanks for your patience.
Suppose i have a l-shaped honey comb structure. can i juss model the horizontal panel and verticla panel seperately and then tie the nodes at their intersection.or is there any other guidelines i need to follow. i know that i would have to define local orientation for the panels so that their...
actually its a simple assembly.not a complicated one.what i was thinking was to tie the nodes of the different parts.how do i tie the nodes in nastran?
in ne nastran how do i model different parts and then assemble them. like in abaqus u create different parts and then in assembly module u create an instance and assemble the model. is there a way i can follow this method in nastran?
if i have the midsurface can i still use pcomp method to idelaise a sandwich panel or should i use pshell method.and if i have to use pshell method do i have to give only the facing thickness as the Taverage. thanks.
what is the advantage of juss modeling the top face of a sandwich panel over modeling the midsurface of the panel? any insight. or can a sandiwch panel be idealised by midsurface modeling?
i got it to work. i actually had overconstrained the model and i constrained it in the right way later. it matches well wth the theoretical result. Thanks. Is there an example of composite laminate modeling. if there is could u send me the link. Thanks.
ok, i dnt understand where i could have gone wrong, this is what i have done:
i have modeled the top face of the skin and have defined 2 materials. one for the facing and the other for the core. and in property i have used laminate and have defined isotropic for the facings and have...
Thanks SW for your input. But for a honeycomb core E1 and E2 are zero and it has only compression modulus which is E3. But since i have modeled juss the upper facing of the skin and defined the thickness through section properties i am forced to used 2d elements which means that i dnt have an...
I have a question regarding the boundary condition for a plate which is simply supported on all four edges. How do i simulate this condition in a FE software. what i mean is what are the d.o.f that i would have to constrain considering each node has 6 d.o.f..Thanks.
Gbor, that is eactly how i modeled earlier. But it dsnt take 3d orthotropic properties since the core is a 2d representation and the thickness is given through section properties and not thru the nodes. So, i donno how to assign the material properties that i have for the core. the properties...
GBor, Thanks for your reply..I have some properties for the core but the things is i am trying to figure out where to input it. i am using orthotropic 2d for the core and i have modeled the top face of the upper facing in the 1-2 plane.And from the properties i have a compression modulus which...