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About LukeRM

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  1. The RBE3 element is there simply to apply the force load onto the skin. It seemed most logical to organise it under the skin component but I don't have much knowledge on the subject, would you suggest that I put it somewhere else?
  2. Ok, I've sent you my model using the secure file dropbox.
  3. Hi Prakash, I'm running the latest (full) version of HyperWorks Desktop and Solvers for Mac OS X. I downloaded and installed them from Altair Connect and then installed the latest hotfixes for both desktop and solvers. I'm also running the latest version of Mac OS (10.10.3) and XQuartz so I don't think there should be any problem with the software, are you sure that this error is a software problem not a problem with my model? I don't currently have access to a windows machine on HyperWorks so am unable to try running it on there. Thanks for the reply, Luke
  4. Hi, I've set up my topology optimisation to minimise the volume fraction and believe everything is set up correctly. However when I try to run it I get the following error message: 'Unknown beamsection data type "part_InitLengtangeLength" found in file.' Does anyone know why I might be seeing this and how I might resolve it? Thanks, Luke
  5. To expand on what I want to do..... I want to apply patches of pressure on the surface of the part acting in the normal direction to the surfaces. I want a total of 12 patches of constant pressure, 6 on the upper surface and 6 on the lower surface (see attached table). The patches need to be rectangular and each one needs to cover 1/6th of the width of the wing (chord) and it's entire length. The patches are not geometrically the same size as the surfaces that the wing's skin is made of so I'm trying to select the area by elements. It's obviously not feasible to select the elements individually and I've tried to select them by window but then it also selects the elements on the lower / side surfaces. Any tips would be appreciated! Also, just to clarify for anyone who isn't an aerospace engineer, the pressure distribution I'm approximating is the one in the attached diagram.
  6. The pressure loads are there to simulate the aerodynamic loading on the wing. For this particular wing I'm not actually expecting it to make that much difference to the structure as the payload forces and torsion about the wing are going to be much more structurally demanding. The primary objective for the optimisation is therefore to support the force and moment loads in the most efficient way with the pressure load being more there to make sure that the suggested material distribution doesn't have any huge voids near the skin which would cause it to buckle. So in that regard the magnitude of the pressures is less important than the magnitude of the other loads. I don't want to optimise the skin, in fact I want to set it as non-design space to prevent the optimiser from suggesting any non-sensical holes in it. The entire wing (the entire aircraft in fact) is made from carbon fibre reinforced polymer. I've also set the thickness of the shell (the skin) to 140mm. Also, please bear in mind that my project really is just to get the concept of the internal wing structure, I'm aware that I'm making some huge approximations and that if I wanted to design this structure for real it would be far beyond the scope of a third year university project!
  7. In case anyone else has a similar issue, the above advice worked. I made a coarser mesh and created RBE3 nodes to apply the torsion and forces. I'm still yet to apply the pressure loads so would appreciate any advice anyone could give me as to the best way to do it. Attached are screenshots that someone in a similar position to me may find useful. One end of the wing is fixed and the other has a moment applied to it via the RBE3.
  8. Thanks, that helped a lot! I think you might be right about my mesh refinement. It won't allow me to create RBE3's because it says the maximum number of elements (10000) has been exceeded. I'll remesh my part and try again. Can I ask what sort of element size you feel would be appropriate? For reference my part has a width of approximately 4000.
  9. Hi, a bit of a broad question here but I thought I'd ask one long one rather than many short ones when I inevitably get stuck at the next step! I'm a university student that's new to HyperWorks. I’ve never had any training nor does anyone else at my university know how to use it but I do have access to all the tutorials, however they are obviously simpler than what I’m trying to do so any help would be very much appreciated. I want to conduct a topology optimisation on the central wing of a twin fuselage aircraft with the skin being non design space and the entire internal volume being design space. I'd like to run the optimisation three times, for three separate load cases so that I can get three different internal layouts. I've imported a hollow CAD model, 2D meshed it's surfaces, 3D meshed it's volume and set the boundary conditions for all the nodes on both ends. I've also made collectors for the three different loads, two different boundary conditions (for the torsion load only one end will be fixed) as well as for the properties of carbon fibre reinforced plastic. I'm planning on using the load collectors to make the three different load cases and then use loadsteps to separate the three cases. The part I'm stuck at is how to approach setting the loads. For the pressure load I want to apply six different patches of uniform pressure along the upper and lower surfaces of the wing's chord to simulate the pressure distribution around it. I then want to set a force with a vertical and horizontal component to represent the weight and drag of the payload it's carrying (the aircraft is Virgin Galactic's White Knight Two). Finally I want to apply a moment about one of the ends whilst the other is fixed in order to simulate a difference in pitching moments between the two fuselages. A particular problem I'm having is how to apply the force and moments to entire surfaces rather than individual nodes, as in rather than applying a certain load to individual nodes I want to distribute the force / moment over all the nodes on that surface. I've already spent hours trying to teach HyperWorks to myself but any advice you could give me or any resources you could point be towards would be hugely helpful! I've attached a number of screenshots to try and show you what I'm trying to do. Thanks for taking the time to read this, Luke
  10. Thanks for the replies. I selected the nodes by window in order to select all the ones on the end surfaces which worked. With regard to: The poisson's ratio is for carbon fibre reinforced plastic. I agree it's rather large but that's the number that I found on a CFRP manufacturers website. Do you think it seems reasonable? Also the reason for the fine mesh is that I'm conducting a topology optimisation of the entire internal wing structure so I assumed that in order to get any kind of detailed internal structure I would need a fine mesh. Thanks again, Luke
  11. Hi, I'm a university student doing a topology optimisation using HyperMesh and OptiStruct. I've imported my part from an ACIS file and meshed it using 2D automesh and volume tetramesh. I'm now trying to fix both ends of the wing (it's the central wing of the twin fuselage aircraft WhiteKnightTwo, see screenshot) with 0 degrees of freedom but when I choose surfaces on the constraints option it only shows a single constraint in the middle of the surface whereas I want to constrain the entire area of the surface. Can anyone help? Thanks, Luke
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