spar caps in the skin or spar caps in the shear web

[ultralights]

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,

 

[wsimpso1]

 

[dino]

 

[Richard Schubert]

 

[Hot Wings]

 

[dino]

 

[ultralights]