Hi
I wonder about torsional strength of a fuselage for a light airplane with a big asymmetric hstab all on
1 side. The fuselage sizing is like any fiberglass sailplane, about 9in near vertical. So with hstab and elevator it's pretty asymmetric and causing a torsional effect.
Doing it in composite I got a first analysis that show lot of UNI ply over few 45 bias fiber, making the overall a thick layup. Can I decreased this layup by going with a more semi monocoque structure of hat stringer all around of many bulkhead ?
And if the stringer will be all in 45 or with uni tape too ..?
Thanks
I wonder about torsional strength of a fuselage for a light airplane with a big asymmetric hstab all on
1 side. The fuselage sizing is like any fiberglass sailplane, about 9in near vertical. So with hstab and elevator it's pretty asymmetric and causing a torsional effect.
Doing it in composite I got a first analysis that show lot of UNI ply over few 45 bias fiber, making the overall a thick layup. Can I decreased this layup by going with a more semi monocoque structure of hat stringer all around of many bulkhead ?
And if the stringer will be all in 45 or with uni tape too ..?
Thanks