Modeling Honeycomb Panel using PSHELL/Stiffness Method in Nastran
Modeling Honeycomb Panel using PSHELL/Stiffness Method in Nastran
(OP)
Hello,
I am heavily modifying my earlier post/thread (actually I prematurely deleted the earlier thread I had created).
Just to provide some background. I am analyzing a test case of an Titanium-Al Honeycomb Panel subjected to an uniform pressure with all sides simply supported. The facesheets are of Ti & the core is of 5052 Al.
Modeled the panel using 2D CQUAD elements with PCOMP (12I/T^3, Ts/T etc) definitions.
Up on further research, I found some miscalculations and omissions in my PSHELL definition and thus modified/updated the definition and reran the analysis.
I am getting fairly good agreement with hand calc values (< 5% difference) on peak deflection and facesheet stresses. However, I am unable to extract any transverse shear forces or stresses values from post-processor.
In the F06 file, I can see running Qx & Qy plate shear forces output.
How do I determine the core shear stress values, should I manually calculate the shear stresses from Qx & Qy values? Am I missing something?
- VN
I am heavily modifying my earlier post/thread (actually I prematurely deleted the earlier thread I had created).
Just to provide some background. I am analyzing a test case of an Titanium-Al Honeycomb Panel subjected to an uniform pressure with all sides simply supported. The facesheets are of Ti & the core is of 5052 Al.
Modeled the panel using 2D CQUAD elements with PCOMP (12I/T^3, Ts/T etc) definitions.
Up on further research, I found some miscalculations and omissions in my PSHELL definition and thus modified/updated the definition and reran the analysis.
I am getting fairly good agreement with hand calc values (< 5% difference) on peak deflection and facesheet stresses. However, I am unable to extract any transverse shear forces or stresses values from post-processor.
In the F06 file, I can see running Qx & Qy plate shear forces output.
How do I determine the core shear stress values, should I manually calculate the shear stresses from Qx & Qy values? Am I missing something?
- VN





RE: Modeling Honeycomb Panel using PSHELL/Stiffness Method in Nastran
Going through the other threads about Honeycomb Panel modeling, it seems like with Pshell definition, the core shear stresses are not directly available in Nastran post-processor. For that feature, either the laminate has to be defined as a PCOMP layup and/or defining facesheets with 2d/3d elements & core with 3d brick elements.
So, I take it there is a need to calculate the core shear stresses separately from F06 outputs. Any recommendations on which program I can use? I found a reference to Laminator. I was unable to find any program named such on the web.
RE: Modeling Honeycomb Panel using PSHELL/Stiffness Method in Nastran
If anyone is interested, I can do a detailed write up on the procedure followed so that the learning curve will be easier for other newbies.
RE: Modeling Honeycomb Panel using PSHELL/Stiffness Method in Nastran
RE: Modeling Honeycomb Panel using PSHELL/Stiffness Method in Nastran
I will try to do a write up of the above procedure over this weekend or the next. If you are in a hurry, let me know and I'll see how much I can get it done during the coming weekend.
RE: Modeling Honeycomb Panel using PSHELL/Stiffness Method in Nastran
Did you guys know about this s/w?
E-Xtreme's Digimat-HC http://www.e-xstream.com/products/solutions/digima...
Apparently it does a good job on constant thickens of honeycomb. Unfortunately my application has a different thickens over the span of a wing( thicker toward the fuselage and thinner toward the tip of a wing.
Anyhow I'm interested too, ...in any "interesting discovery" you might find
Cheers,D.
RE: Modeling Honeycomb Panel using PSHELL/Stiffness Method in Nastran
Within on Youtube: https://www.youtube.com/watch?v=stPbmGpvCuw&fe...
Please check this article too: http://www.deskeng.com/de/composites-analysis-maki...