Example 3.4.a How to model a laminated composite using with thin shell elements in Abaqus

[@stevenongszekuan9932]

Hi Ever Barbero, can I know where did you get the engineering constant? I would like to acquire the engineering constant for carbon and basalt as I'm comparing both of the materials for my project. Thanks

[@EverBarbero]

see my response in Example 3.4.d

[@hitman5601]

Hello sir, I am doing impact analysis on composite material using explicit dynamic pn solid composite material plate But I am getting error as "excessive distortion of elements"

[@sashaazimi7429]

Hello How I can see other examples in abacus your teaching is great

[@EverBarbero]

yeah, KZbin is not so intuitive, I was confused when I started,... to see all my videos go to kzbin.info > to see Abaqus videos > Playlist > Abaqus FEA > View Full Playlist

[@anwarbraham9549]

i don't have the poisson ratio for my unidirectionnel glass fiber , is it possible to calculate it from the shear and youg modulus ?

[@EverBarbero]

Glass fiber material is isotropic, so yes! nu=-1+E/(2G)

[@mahaelsaeid3713]

Hi, thank you for the nice viedos, I have some questions tho: 1- can we in 3.4.d the layup method use for the part design shell instead of solid ? when shall i use the shell or the solid ? because from mz understanding , composite laminates are mostly modeled as continum shell, am i correct ? 2- can we while using the layup method add cohesive elements contact between the each play, without treating each lazer as a separate part? for example from your videos and other videos i have noticed that you mostly treat each layer as separet par and the cohesive layer as a separate part, you assemble them and you add the cohesive element ? so my question is, the lazup method alreadz creates several plzs , is there a way to insert a cohesive element between layers without treating the whole system as separet entities? 3- can you please make a video tutorial for delamination of composite laminates in tensile test speciman ? thank you in advance

[@gamex6923]

Hi sir i have plat composite with singl layer with fibre orientation 50° and i want extract young module Ex and Ey for 50°

[@EverBarbero]

The layer will shear when you apply a strain epsx to get Ex. Support one edge with Ux=0, another with Uy=0, then use a tie constraint for each of the opposite edges the ties each edge to a different reference point. apply ux=epsx*length of the perpendicular side, to get epsx=1. Add the stress in all elements times the element volumes, then divide by the total volume, the is Ex. See chapter 6.

[@gamex6923]

@@EverBarbero do you have any. Vidéo or fichier for more understanding please sir