Integrated multispar torsion box of composite material

Details Integrated multispar torsion box of composite material Integrated multispar torsion box of composite material

2007-07-02

2010-10-05

Dinh, Tien (Department: 3644)

Aeronautics and astronautics

Aircraft structure

Airfoil construction

Reexamination Certificate

active

07806367

ABSTRACT:
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.

REFERENCES:
patent: 4749155 (1988-06-01), Hammer et al.
patent: 6475320 (2002-11-01), Masugi
patent: 6502788 (2003-01-01), Noda et al.
patent: 6513757 (2003-02-01), Amaoka et al.
patent: 6689246 (2004-02-01), Hirahara et al.
patent: 2003/0192990 (2003-10-01), Simpson et al.
patent: 2006/0249626 (2006-11-01), Simpson et al.

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