I have another question, will be happy if could answer it
Is there any possibility to change the sketch plane in abaqus?
the default sketch plane in abaqus is XY, can I change it to XZ or YZ?
I tried shell section instead of composite lay-uo definition and used 5 integration points and the problem still persist!
I will refined my mesh through the thickness of laminate and find if it works! I am trying to verify a paper that used 1 element in thickness of a ply! so I did the same
Dear SWComposites
No, I dont. When i model an angelply laminate [45/-45]2s using the the Coordinate system an material orientation illustrated in pictures, I get the wrong result. the Stress distribution I collected along the thickness of laminate is not symmetric. I also tried a wider laminate...
Thanks for your help![bow]
Pls take into account model works but does not give accurate result
If you check the stress distribution far from the scarf region you will see the stress through the thickness of laminate is not symmetric. That is the thing I cannot handle!
Besides. It's a failure...
Shell Section and material ORI Approach https://files.engineering.com/getfile.aspx?folder=052f09fb-345d-4716-9bd5-e284bddc6291&file=0-ShellSectionDefined.inp
Thanks for your quick reply.
Sure, I am trying to attached 2 .inp files in t=current and my next post.
0-Layupdefined.inp : I have defined a composite latyup (one ply) for the shell part of my model.
0-Shellsection.inp : I have defined shell part of composites using shell section and then...
Dear All
I am trying to analyse the failure of a composite scarf joint. Composite adherends are bonded together by adhesive.Image of the joint is attached.
I have modeled each ply as a part instance.
I used solid elements in plies tips and in order to take advantage of Hashin criteria of ABAQUS...
Thanks for your replies.
I had specified output frequency based on "evenly spaced time intervals" and set 50 as number of intervals. This setting resulted in nothing written on odb file.
I found out when I change the output frequency to "every x units of time" and set x as 50*stable time...
Dear All,
I did not get any result from Abaqus explicit as attached result image.
I have no clue of possible reasons!
I changed the amplitude and BCs and nothing happened.
I would appreciate any thoughts.
Attached the
Dear FEA way,
Finally my model converged. The problem caused by negative eigenvalues of stiffness matrix, resulting in " FORCE EQUILIBRIUM NOT ACHIEVED WITHIN TOLERANCE" and made the solution locally unstable. I specified the damping factor 1e-6 instead of using default dissipated energy...
Yes, the same error happened
I tried default and slave nodes initially in contact options, but same error happened!
I guess it was related to Tie constraint defined for the other interface. Because When I removed the tie constraint and defined another cohesive contact for that interface the...
Hi there,
I tried dynamic,explicit solver and it's running right now!
I faced a problem during simulation and I'd be glad if I can have your opinion on it!
Actually I think I haven't completely understood the General Contact yet!
Here is my difficulty with this type of CONTACT!
As I have...
I will try other Solvers and will let you know of the result!
Meanwhile,you can find BCs and load as attached images.
Reference Point 1 and Reference point 2 are constrained to the ends of the specimen via MPC and load and BCs are defined for those points.
I have already tried the option and it doesn't work!
I observed another wired behavior in the result, I want to share with you and will be more than happy if I can have your opinion.
As I said before, I encastred one side of my structure and applied a displacement to the other side. The...
Thanks for your help.
Using meh refinement, defining a new material orientation and adjusting some features of contact property definition, I could solve my problem for cohesive interface containing pre-existing cracks. But I have still some difficulties for the model without a flaw in...
here is the title and DOI:
Effects of bondline flaws on the damage tolerance of composite scarf joints
https://doi.org/10.1016/j.compositesa.2013.07.017
Because of the geometry, I have to use cohesive contact behavior to model the interface between adhesive and adherend.
I have a scarf joint, modeled in 2D ABAQUS . Two similar laminates (20 plies, symmetric laminates) are bonded together using adhesive. A picture of the assembly is attached. It's under a tensile load from one side and the other side is encastred. I have defined cohesive contact for the interface...
