Analysis of loads on a composite wings

aclouston

I told Mike 262 that I literally fell off chair after I read his analysis of a composite wing last night. CLEAR, CONCISE, and understandable by non-composite engineers. It almost looks easy

How can someone like me, a classical mechanical engineer (or you reader?) can make an analysis of a modification of the wing attach of a composite plane ( Rutan's Varieze). The original uses a stiff/stubby fiberglass spar box onto which a metal attach fitting connects to the wing. On the designer's next plane (the LongEz which has a larger wing), the designer used a longer more slender spar beam and connected the wing using a three bolt friction/shear ass'y. I can send you sketches.

Some of us builders are interested in studying the possibilty of retro fitting the longer spar beam of the LongEz to the original Varieze wing which is a much better fuel efficient airfoil, and the plane handling is much more jet fighter like. The LongEz center spar beam cannot be fitted directly because the sweep, twist and wing thickness at same span is different between the 2 wings.

Would that study be difficult?, complicated for an engineer like me? I'd be really interested to know. I would think all I need is the reactions of the wing from the maximum wing loads at the spar beam junction and apply classical composite stress/strain equations to the spar beam as the wing itself is already proven upto the original metal attach point which is closer to the fuselage than the new method would be.

I'm not sure I am clear here. I may need to share sketches I think.

PS I have access to Solid Works but am just starting basic 3d drafting.

Thanks in advance
Allan