# Wiko

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1. ## Extract nodal forces from a truss

Hi Prakash, tnx for the answer. I've produced the .gpf file and there are the Grid point forces for node # listed. The values of one node can be seen below. There are The XYZ-forces and -moments. But what are the values "Appl., F-MPC, BAR and Total"? Why is the total value that small? Can you give me some explanation regarding the below listed values? Best regards Wiko
2. ## Extract nodal forces from a truss

Hi, I'm currently analyzing a truss (3D) which is modeled with CBEAML-elements. The model is made out of lines and the lines where meshed via "line mesh". What I do need are the forces acting on the "knots" where the Beams are connected together. I've activated in the output card already "GPFORCE"&""GPSTRESS" but the results in HyperView are not satisfactory... In the post processing are the results "Grid Point Forces (s)" & "Grid Point Forces (Elements)" available. "Grip Point Forces (s)" - results (Total FX for example) show very low forces (3.3*E-10) and "Grid Point Forces (Elements)" doesn't provide any results.... Can some one please give some hints for solving such a problem? I need only the nodal forces (as shown in the figure below; point E for example) of the connections so I can design mounting brackets for the truss assembly Best regards
3. ## Topology optmization & static analysis fails

Hello Jaideep, one last thing. In aviation, there are the flight maneuver loads in up-, down-, fwd-, back- and side-direction (x,y,z). Let’s assume that the loads in up- and down-direction are just two loads with the same magnitude but in the opposite directions (force_up=150N in y-direction and force_down=N in negative y-direction). How can I get a result in topology optimization with both load cases considered for the optimized shape? In my calculations, I always get an empty design space which looks like the load cases cancel each other out. Regards
4. ## Topology optmization & static analysis fails

Hi Jaideep, I've installed inspire 2017 yesterday in the company and I'm currently working on my workstation there. I'll send you a pm. Tnx! Best regards
5. ## Topology optmization & static analysis fails

Hi guys, since I need a quick concept structure, I've decided to do the analysis and optimization with inspire. Well, i do have a small solid which is loaded by a simple force and supported (don't evaluate the support, it's like "anything" for the test run). I have created a design space and the forces and supports are located on "non-design" parts. Every time I try to do a topology optimization, it fails and the following message pops up: "Optimization Error 157". The parts from the tutorials do work... I need an urgent help and thank you in advance for your answers You will find the file in sthe attachment Arm.stmod
6. ## Wing rib assembly to wing skin

Oh, I get it Thanks! Well does that mean that I have to build up the interface laminate according to the element normal? Like ply8 on the bottom and ply 4 as the second ply?
7. ## Wing rib assembly to wing skin

Hi Prakash, thank you for the presentation. I tried to realize the sample with a T-beam. The lay-up can be compared to the example, which can be found in the HW-Help (XXXX/Altair/13.0/help/hwsolvers/stack.htm?zoom_highlightsub=ply example 2). I have attached the .fem-file of my model and a short summary of the lay-up. Actually, I have 4 sublaminates and an interfacelaminate to "bond" all sublaminates together. I have assigned PCOMPP-property to all mesh-elements. After modeling, I have started a short analysis of the beam but the following error-msg appeared: Can you give me a feedback with hints to solve this problem? Another question is, does the geometry have to be "connected together" for modeling a laminate with sublaminates? Best regards Wiko T-Beam.fem T-Beam_summary.pdf
8. ## Wing rib assembly to wing skin

Hi guys, do you have any ideas how to model an assembly with multiple composite components? As shown here http://www.rowlandcarson.org.uk/aviation/europa_435/_images/dscn1733.jpg I want to model ribs which are bonded to a specific surface. Do I have to do that with sub-laminates? Are there any tutorials for sub-laminate modeling? I am using HW13.0 Thank you in advance.
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