摘要 |
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.
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