A stiffened skin panel of an aircraft that includes an aircraft skin panel of composite material and a composite stringer consolidated with the aircraft skin panel. The stringer has a pair of stringer sides, each extending from a stringer top to a stringer leg. The stringer sides may each extend through a wide radius, smooth continuous curve to a stringer leg. The wide radius, smooth continuous curve may be proximate the base of the stringer side in a region where the stringer side transitions to the stringer leg.
Method of making shaped composite stringers
Herstellungsverfahren für Verbundlängsgurte
Procédé de fabrication de lisses en matériau composite
07.12.2016
Patent
Elektronische Ressource
Englisch