Integrated multispar torsion box of composite material
View Patent ↗The invention relates to an integrated multispar torsion box structure of composite material for aircraft, comprising a lower skin ( 12 ), an upper skin ( 11 ), several spars ( 9 ), each of which comprises in turn a chord ( 13 ) and a web ( 14 ), several stringers ( 10 ) in the lower skin ( 12 ) and several stringers ( 10 ) in the upper skin ( 11 ), characterized in that the mentioned integrated torsion box structure is achieved by means of joining unitary U-shaped structural elements ( 15 ), unitary U-shaped structural elements ( 16 ) with a flap and unitary C-shaped structural elements ( 17 ) with a flap. The invention also relates to a method for manufacturing an integrated multispar torsion box structure of composite material for aircraft.
1. An integrated multispar torsion box structure of composite material for use in an aircraft, comprising a lower skin ( 12 ), an upper skin ( 11 ), a plurality of spars ( 9 ) each having a chord ( 13 ) and a web ( 14 ), a plurality of stringers ( 10 ) extending longitudinally from the lower skin ( 12 ) and the upper skin ( 11 ) having a T-shaped or I-shaped cross-section, wherein the integrated torsion box structure is achieved by means of joining unitary U-shaped structural elements ( 15 ), unitary U-shaped structural elements ( 16 ) having at least one flap and unitary C-shaped structural elements ( 17 ) having at least one flap.
2. An integrated multispar torsion box structure of composite material for aircraft according to claim 1 , characterized in that the composite material is carbon fiber.
3. An integrated multispar torsion box structure of composite material for aircraft according to claim 1 , characterized in that the composite material is fiberglass with thermosetting resin.
4. An integrated multispar torsion box structure of composite material for aircraft according to claim 1 , characterized in that the composite material is fiberglass with thermoplastic resin.