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Found 5 results

  1. Hi, I have some questions I was hoping someone could answer. I am trying to model a sandwhich structure with carbon fibre skins and aluminium honeycomb core and then perform a 3 point bending test in the software if possible. 1. Could someone please explain what the reason is for selecting PCOMPP, PSOLID etc, what are the reasons for choosing one of them over another? 2. Which compersite property: PCOMPP, PSOLID, PSHELL, etc, do I need to select for the task I want to achieve (3-point bending simulation)? 3. Another question relates to my understanding of the MAT 8 card....would I be correct in saying that as MAT8 only asks for the in-plane properties, it would not be possible to get proper results for a 3-point bending test in the software? (Or does the software still work this out?) 4. Would I need to use the MAT9 card for what I am trying to do and in that case what composite property do I select, PCOMPP, PSOLID, PSHELL, etc? 4. If I select for example PCOMPP for the honeycomb properties, do I have to select PCOMPP for the carbon fibre skin properties? Regards
  2. Hello, I'm trying to understand the theory behind Optistruct solver, I'm working on composites, I wanna know what is the theory used by optistruct to solve à plate (Laminated) problem? is CLT? FSDT ? and how can we know that and change it if we want? Does this have to do something with PCOMPP? I thank you in advance for your replies.
  3. Hello,Forums I am doing analysis of a unique CFRP pipe by Optistruct. I am receiving this following error message: *** ERROR # 605 *** Element 1 is referenced by STACK 1 (on PLY 1) and by STACK 2 (on PLY 5) simultaneously. Different stacks are created by dividing the upper and lower areas of the pipe into sets. There seems to be an error because it refers to the same element Is there any good way to do it? (Modeling is possible but analysis is error) CFRP-PIPE-Asymmetric laminated.hm
  4. Dear, I am trying to preform a buckling analysis of a composite sandwich material. But the Auto-SPC limits the DOF's of the composite skins, so that buckling can not happen in correct way. When the Auto-SPC is dissabled, the solver gives the error which states that the DOF's of these elements should be limited, because they have no stiffness in that direction. This is true, due to the material and property assignment (Mat 8, and PCOMPP) which does not provide stiffness in the 3th direction. Is there a work around? I also did a dynamic test (Radioss) where the specimen does not buckle according to the first mode. Test to be replicated: Optistruct First mode Faulty result due to Auto SPC RADIOSS Result Model : Eigenvalue_Bucke_2.hm
  5. Hi guys, I'm currently developing a complex composite structure und simulated it already with optistruct with shell elements (Mat8, PCOMPP). In order to distuguish different failure mechanisms I need analyse the stress in thickness direction of the structre. For that I used the "shell-to-solid conversion" within the aerospace menu. Now that I have a solid mesh, I'm not sure how to proceed. What property do I assign to the solid mesh ? What material card do I use for it ? Do I need to assign the material orientation to the new mesh again and if yes, how do I do that ? Thanks in advance
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