I really appreciate this build sequence of nice photos.
If you know, how did you decide how many cross-braces, or whatever you call them, to use? I.E. How did you know to use, say, 13 X along the fuselage, not 6 or 20? Is there perhaps a preferred crossing angle between the various carbon pieces? I see several different crossing angles at different points along the fuselage length.
Is it based on a "good" maximum unsupported length along the fuselage exterior carbon?
Is it a That Looks About Right (TLAR) judgement?
My thinking is that perhaps you could use quite a fewer X and save some cost, labor, and weight. But then it would be less stiff. But in some places, less stiff could be desirable for impact-resistance.
Perhaps you did a finite element analysis of the planned design and then modified it for some measure of merit, like uniform displacement or twisting under load? Probably Not! :-)
Thanks so much!
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