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why'd you start with this loadcase (which really shouldn't be That critical) ? I'd design the wing for max/min bending and then look into these "funny" cases. I have the spar bending/shear designed (maybe,... perhaps or needs work) see "Built up Spar Question" this forum also attachment. The...

"i think the LE attach point should be at the shear center of the Dnose, i'd buy some point between 1/2 and 2/3 of the Dnose chord aft of the LE." Thank you very much. "i'd've thought that you wanted just about the minimum number of wing/fuse attachments (due to transport ?); which would be...

" 3.)...kinking fwd to the Dnose fuselage attachment (which should be on the centroid) Yes a little bit of fudging. case 3 is the LE centroid kinking forward to the LE fitting. case 4 and 5 did not give good results as the end of that load path was not at the LE fitting. "(which should be on...

Thank you very much. http://files.engineering.com/getfile.aspx?folder=a8e265d2-0e96-4f58-90a9-eec96f99bc27&file=sparquestion4.pdf

"you haven't said how this is attached." Planed on solid root rib and bolt and fitting at LE....Note this is not per carbon dragon plan, and would cause different results from same. attached are the different diagrams I have looked at. My fittings are assumed fixed, Rear spar attach, Main Spar...

1.)so you've got a large drag moment to react on the Dnose and the rear spar ? couple between RS and centroid of Dnose. if the load acts only aft, then the rear spar will be in compression and the Dnose in tension. 2.)if there's a main spar and a rear spar, isn't that the natural loadpath for...

"i'd hope that the 0.016" would elastically buckle under test." My fears exactly.

what is drawn is the rear spar, main spar, ribs, drag spar, phantom spar at centroid of LE. horizontal load at tip I also have drawn only the solid ribs, main spar, drag spar, rear spar. horizontal load at tip. I also have drawn only the solid ribs, main spar, drag spar, rear spar. horizontal...

as you said difficult to mount the whole problem, those are (2) .093 rectangular caps, One .040 spar web, one .016 angle. this is a cross section looking outboard from WS 2.5 I am not understanding your statement "your drawing shows everything at 90deg ." unless you mean I have not shown the...

ouch... could you be more specific, maybe a sketch of your FBD

if not then "odd". odd "what is that flange(angle) doing, that the spar cap couldn't ?" attaching to the LE skin and aft skin fabric "i think the question you're asking is i have this thin gauge angle attached to the spar, can i consider it ineffective" yes and no, great idea short...

Your example [AC43.13-1b for fastener row area-out] does not blend-well with Your original statement... I am not the OP however it seemed like he was doing a repair of a light aircraft, and reading 43.13 may get him were he needs to go faster than trying to learn stress analysis. I can do the...

"your picture doesn't look right ... the angle flanges should be at 90deg to each other, no?" you are looking at the top compression cap and flange only, standard solid AD rivets 3/32 flat head, dimpled skin. I plan on Oratex glued on fabric, probably pop riveted to the ribs unless the...

Here is a page from AC 43-13-1b. It is free on line FAA site google search. Go to this section and there will be more than you ever wanted to know about aircraft repair. See attached file. Don A&P...

I am looking for more specific engineering answers than I have been able to get on the other site. I have often seen specific reference to chapter numbers and equation numbers in Bruhn on this site. I will consider anything but until I understand and am able to calculate the specific shear...

the leading edge skin and fabric aft of that. "what does the 0.016" angle attach to ?"

My cad will give me what ever I want, if I build from rectangles I can get "I" for each rectangle, or it will give me the total "I" for the section. I am not a stress specialist, and not sure how to check each rectangle stress, however if that is possible (MY/I) it might solve my concerns. How...

I really like that idea. thank you very much. "if you're worried about the angle picking up unwanted bending loads ... make it out of short segments rather than a single long piece."

you bet it is unconventional, however the caps transition to one cap outboard as the bending moment decreases. This is similar to the Midget Mustang. Conventional factory built might have machined from solid caps. Every thing is aluminum 2024-T3 however the skin aft of the LE attach to the...

rear spar attach node 17 main spar node 20 the Phantom beam at centroid of the LE transitions to tip of root rib at node 16. the other 16 is element 16. Element 19 the diagonal line is the drag spar. This is the structure geometry (except for the Phantom Beam at the centroid of the LE) of the...