Search results for query: *

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?

So does it mean that i would have to create the entire assembly in one goup and not part wise and then assemble it?

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.

is it not possible to delete the material and the propert defined in a .NAS file. if yes how do i do it 'cause i am not able to..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?

what would happen if all the bolts are rigid in a joint. would all the bolt carry the same load? and what about deflection?

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.

hey greg..yes it matches well with the test data.thanks

thanks everyone for ur inputs..i had used the bc as stated by airmail aleady and it worked perfectly fine. thanks once again

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...

Gbor, thanks for the patience.. i solved the problem that i had using 2d orthotropic.

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...