ultralights
Well-Known Member
I'm designing a wing of a light two-seater aircraft with composite structure. The wing is of type D-type torsion box spar and fabric.
For un "D"-type composite torsion box spar, what is the most desirable from the viewpoint of the stress in the bonding:
1- laminate the leading edge skin box and spar caps cocured and bonding to a shear web type "C"
or
2- laminate spar caps cocured with shear web and bonding this one to leading edge skin ?
I have seen the two forms of construction but I'm sure you know all the considerations for an election or other.
thanks,
For un "D"-type composite torsion box spar, what is the most desirable from the viewpoint of the stress in the bonding:
1- laminate the leading edge skin box and spar caps cocured and bonding to a shear web type "C"
or
2- laminate spar caps cocured with shear web and bonding this one to leading edge skin ?
I have seen the two forms of construction but I'm sure you know all the considerations for an election or other.
thanks,