Hello all
Im having a thought experiment where an airplane wing has foam core ribs and spars and sheeting the wing instead of one continuous fiberglass skin layer multiple preformed smaller Panels bonded at the seems. Of course the skin would be in direct contact with spars and ribs. Would this work or since the UNI fibers keep getting "broken" at the seems will it not carry the torsion loads and just break at the seems?
Im having a thought experiment where an airplane wing has foam core ribs and spars and sheeting the wing instead of one continuous fiberglass skin layer multiple preformed smaller Panels bonded at the seems. Of course the skin would be in direct contact with spars and ribs. Would this work or since the UNI fibers keep getting "broken" at the seems will it not carry the torsion loads and just break at the seems?
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