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  1. SWComposites

    Mesh singularity on non-manifold geometry

    that is likely the cause of the stress peaks at the spar web at the root. but you have two lugs at the root of the spars. how exactly are you modelling that area? note: you are unlikely to get accurate stresses in those lugs with the current mesh refinement, and since the stresses in the lugs...
  2. SWComposites

    JetZero Blended wing proposal

    oh they will eventually ask the US govt for more $, like any good R&D project. and its just a demonstrator. building a certified design and getting it into actual production is WAY harder and expensive.
  3. SWComposites

    Subdivision Work - Pricing

    OP - why not ask the architect what his fee schedule is?
  4. SWComposites

    SpaceX Starship missions

    those LH2 tanks leaked.
  5. SWComposites

    Splice Theory Question

    there is also shear transfer due to the moment. resolve the moment into a tension / compression couple at the centerlines of the two thinner sections, then transfer that load across the joint in shear.
  6. SWComposites

    Thread embedment required for bolt in tension

    the general rule of thumb is min of 3 full threads. and the nut material/type needs to be strong enough to fail the bolt in tension.
  7. SWComposites

    Prying Action Plate Bending (AISC)

    well what is your definition of "any"??? nothing is perfectly rigid. well, what is "some"? a sketch of this plate, with applied loads (a balanced fbd) and boundary conditions / connections would greatly help.
  8. SWComposites

    Coaxiality tolerance for the welded structures

    is there a hole in the plate with diameter equal to pipe ID? what is the application? where did the drawing come from? if it came from a customer of yours, then contact them and discuss the requirements
  9. SWComposites

    Coaxiality tolerance for the welded structures

    what is the issue? the tolerance looks to be on the left hand side, referencing datum A shown on the right.
  10. SWComposites

    viscoelastic behavior + Damage

    then with displacement controlled tests, you will see load drops in the response curve which will not show up in a load controlled curve. these load drops are an artifice of the displacement controlled loading, as when there is a stiffness drop (due to damage, etc) there will be a load drop and...
  11. SWComposites

    viscoelastic behavior + Damage

    was the test conduced a load-controlled or displacement-controlled?
  12. SWComposites

    Fatigue justification of a thread bolt

    1) suggest you delete and repost in the Aircraft Engineering forum 2) can you show a sketch of the joint? 3) is the bolt threaded into the fitting? (I hope not) or a thru bolt with proper nut/collar on it?
  13. SWComposites

    Tria/Tetra vs Quad/Hex

    3 node triangles are not good. 4 noded tets are very bad. avoid both. auto meshers create triangles/tets because it is "easy". grrrrrr.
  14. SWComposites

    Air India 787 crashes on take off

    wrong. was GE engines.
  15. SWComposites

    Bruhn C10.18

    I agree.
  16. SWComposites

    Fasteners substitution %'s

    So what is the issue? Just tell the tech to remove the substituted fasteners and replace with the proper ones per the SRM.
  17. SWComposites

    How can I stop water entering under porch and seeping through basement walls?

    First step in these type of problems is to get the water away from the wall, so move downspouts and regrade the outside areas.
  18. SWComposites

    Composite Anisotropy

    Yes, there are spar or rib webs with a large percentage of 45 and -45 plies where the difference in D16 and D26 can be critical, if load cases are not fully reversed.
  19. SWComposites

    Residual Strength Composites- Last Ply Failure-Purpose Vs FARs.

    Oh, and most progressive damage analyses are based on interactive failure criteria which have been proven, despite the text books, to be rubbish.
  20. SWComposites

    Residual Strength Composites- Last Ply Failure-Purpose Vs FARs.

    Assuming this is for carbon fiber composites, And assuming well designed laminates with fibers in the load direction, Then ultimate failure is driven by the fibers and any “predicted” matrix failures which occur before fiber failure are either wrong or insignificant. Therefore no need for...

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