billyvray
Well-Known Member
I'm learning about composite construction and design and have a question.
I wonder why there aren't more aircraft (lightweight simple ones) using a composite wing construction in which the skin is laid up in such a fashion to carry the "spar" loads. This would mean a single hotwire cut for the main wing and then lay up the skins, using thinner sections around the spar location. This would eliminate fabricating a spar separately.
I know the Quickie 1 was built this way.
I understand if landing gear and other devices involving stress concentrations were mounted in the wings it would change things. But, if you have just a wing, would this not be a good way to build a composite wing more quickly?
Just something to ponder....
Billyvray
I wonder why there aren't more aircraft (lightweight simple ones) using a composite wing construction in which the skin is laid up in such a fashion to carry the "spar" loads. This would mean a single hotwire cut for the main wing and then lay up the skins, using thinner sections around the spar location. This would eliminate fabricating a spar separately.
I know the Quickie 1 was built this way.
I understand if landing gear and other devices involving stress concentrations were mounted in the wings it would change things. But, if you have just a wing, would this not be a good way to build a composite wing more quickly?
Just something to ponder....
Billyvray