I see now that you were referring to socket tube placement by the
book, but mount the leg lower in the socket, rather than a lower
mounting of the socket tube. The original post referenced both
methods, so maybe this clarification is useful.
Maybe the "E" word still comes into this, and the question is best
posed to Europa? Because I note that they've cut a taper in the leg
inside the tube, and I wonder if that's to relieve some of the stress
of bending where it exits the tube, and repositioning the leg alters
that picture. Ignorant guess, but if they're just saving weight, at
9 lbs, it didn't do much.
Regards,
Fred F., A063
Rob Housman wrote:
>
> My education is in engineering (BS, ChE) and my industrial experience is in
> metals (non-ferrous), so in that context this is an engineering analysis. I
> did not "do the math" but from my understanding of the fundamentals of
> statics (yes, I know, some of the loading is dynamic but the dynamic load
> uses the same levers and arms), if the gear leg fits snugly into its socket
> it will behave as a single member. Thus, you are correct in saying that the
> fulcrum is at the fuselage skin. However, your assumption that the shorter
> length inside the tube affects leverage implies a different assumption, to
> wit, that the leg does not fit snugly in its socket. So, take your pick:
> snug fit means that the socket is an extension of the leg, and loose fit
> means the lever arm within the socket is the length of the leg within (and
> the socket is loaded only at the lower end at the fulcrum, and the upper end
> of the leg where the bolt goes through). As long as the leg within the
> socket does not fail it transfers the same forces to the ribs under either
> assumption about snugness of fit.
>
> Perhaps a structural engineer will read this thread and comment.
>
> Best regards,
>
> Rob Housman
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