Hey whitewas! Thank you for the response.
I actually wrote down the thickness wrong earlier. The thickness of the model is .045 inches, so therefore I was thinking shell elements are better??
Also the total stress versus ply stress: the stress of the overall FEM (stress at each element), would...
Hey @SWcomposites,
Thank you so much! That actually helps a lot. I have done a lot of reading on CLT but haven't seen anything about how the modulus is calculated from the inverse A... Just curious if you could point me to a book or a formula?
and that makes sense about the displacement. Thank...
Hey guys,
can anyone shed some light on classical laminate theory (CLT)? Let's say I have a laminate made from 3 plies: 2 outter carbon fiber plies and 1 inner fiber glass ply...
I go through the Q, Q bar, and ABD matrices steps... Now, lets say i have my inverse ABD matrices. this can be...
Hey there,
I was hoping someone with experience using PCOMP elements could help me out with my project.
So I have a small trapezoidal 'stiffener' sample (about 2.25" tall by 2" wide with a material thickness of about .45") that is to be compressed in unaxial load (strictly uniaxial)... The...
Hey there,
I was hoping someone with experience using PCOMP elements could help me out with my project.
So I have a small trapezoidal 'stiffener' sample (about 2.25" tall by 2" wide with a material thickness of about .45") that is to be compressed in unaxial load (strictly uniaxial)...
Thank you SWcomposites for your response.. but when I create a new material in my FEA software it asks for E1,2 and 3. So you're saying ignore E3 since I'll be meshing with shell elements??
Any chance you could shed some light on the compressive modulus too? Is this a necessary value to have...
Hey guys, I'm trying to get G12 of a cured composite. The fibers are weave, so is there a special formula I can use to find G12 (Huber's Formula?).. or is it only determined experimentally. Let's assume there's no data sheet for the material, and currently I have E1 (which equals E2) and poissons...
I believe I am getting myself confused and seeking clarification.
Lets say I have a unidirectional carbon fiber laminate. From testing, I have E11 and the E22 properties. I am looking to get G12, say for an FEA model. Since I have a composite material it's not isotropi, so the isotropic formula...
Hmm. Well I am modeling with shell elements, but this is for my material definitions.
But what you said makes more sense; if I am only doing in plane linear static loading, then E33 should not matter (because everything will be in plane). That makes sense...
But just for kicks: my fabric is...
Okay, lets assume I am trying to model a thin strip of carbon fiber weave sample for compression loading in FEA.
When creating my material, I have my E11 and E22 from my material testing. Since I am assuming the weave to be perfect, I am assuming E11 = E22.
Now, where do I get E33 (out of plane)...
