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mike262
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HI Tsai wu failure theorem in this analysis is used to mainly get some idea of failure in the ribs and skins which are made up of bi directional carbon layups oriented at +-45 degrees to each elements U and V axes. i wasnt sure which interaction c…
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Thanks I modelled it using Onshape cad. I dont have any other info on other sites yet. We are planning to build it though! . here are some pics of the complete aircraft I analysed the the composite tail surfaces and tube steel fuselage truss us…
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Thanks !! This wing geometry was pretty simple. it has relatively few ribs and a symmetrical airfoil. I might have to go back to auto mesh and bonded contacts for the next wing, which is quite a bit more complicated.
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Results. I used a The Tsai wu Failure criteria that is implemented in Mecway as the failure criteria for this analysis. This is a screen grab of the Tsai Wu failure factor of safety with the minimum value of 2. The bright pink regions represen…
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MATERIALS INPUT All elements used in this analysis were quad4 elements with a laminate material. A typical cored skin panel was input in the following way The wing skins are made from Bidirectional carbon fibre prepreg layed up over nomex honey…
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LOADS One of the complexities of analysing wings like this is getting the loads correct. If the loads aren’t realistic and accurate then the rest of the analysis will be meaningless. Deriving flight loads is more of an aeronautical engineering probl…
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MESH I had to experiment a bit in order to generate a useable mesh. Originally I imported simplified geometry from the CAD model in the form of separate .step files then I auto meshed them and bonded them together using the mecway bonded contact fun…
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I'd be very interested to find out more about this!
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Is there some way to turn the skins off in the results so i can see whats happening internally to the wing?
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I have been getting pretty good results so far just need to stiffen up the the wing skins!
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I was having a few problems with my shell mesh. I read this thread and thought i would have a go at using Salome and it worked pretty well!. I started off with a surface model in onshape made up of lots of separate parts. I tried loading them in…
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what typical values would you use for a core material? below is the laminate entry i have tried unsuccessfully ....The face sheets are Kevlar with thickness 0f 0.03in E of 3200000 psi, poissons ratio of 0.1 and an in - plane shear modulus of 1200…
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Here is a composite mesh of a aircraft structural wing box i have made up. It has unidirectional fibers of varying thickness along the spar caps and BI directional carbon fibre for the skins and ribs. I have run it and it compares well with other an…
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Hi Victor, Thanks for this ....i think this is all i really need. Can you input a distribution that vary along two axis? I.e a parabolic lift distribution along the X-axis (wing span) and that varies linearly along the y - axis (wing width or Chord…
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Hi Im looking for more info on how to do this. If i have cfd outputs in spread sheet format that gives a say elliptical lift distribution how would i input it. or even being able to put a simple parabolic or elliptical pressure distribution would pr…
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I dont think what im trying to do is that complicated i guess. im mainly interested in static analysis and working out the failure loads and making sure the wing is not excessively heavy (i have weight data on similar wings).... I'm not really inter…
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i have done a fair bit of spread sheet analysis and have a fair bit of data on material properties for the composites i intend to use....and one text book i have on composite light aircraft suggests using the tsai wu failure criterion in spread shee…
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hi these are awesome! Im looking for info on analyzing a composite wing for a light aircraft using mecway. im also looking for info on the best way to model cored panels with honeycomb core and carbon facesheets. I guess carbon propellers are just m…
