B - Operations – Transporting – 64 – C
Patent
B - Operations, Transporting
64
C
B64C 5/02 (2006.01) B64C 9/02 (2006.01)
Patent
CA 2741827
Fitting (30) for trimming the horizontal stabilizer (1a) of an aircraft, made of composite material, said fitting (30) comprising side walls (2a and 2b) of a torsion box as well as joining elements (3a, 3b) which join the fitting (30) to the frames of the tail fuselage (1) of the aircraft, said side walls (2a, 2b) being joined together by means of a central element (4) which comprises a first end part (4a) joined to the first side wall (2a) of the fitting (30), a second end part (4b) joined to the second side wall (2b) of the fitting (30) and a central part (4c) which joins together said end parts (4a, 4b), the fitting (30) moreover comprising end elements (5a, 5b) which are joined to said side walls (2a, 2b) on their outer face, said fitting (30) having, owing to its greater rigidity in response to side load and vertical load stresses which tend to close the side walls (2a, 2b), its greater integration and the simplicity of the load path, an optimum structural behaviour in response to the aircraft stresses.
La présente invention concerne une ferrure pour l'équilibrage du stabilisateur horizontal d'un aéronef, réalisée en matériau composite, ladite ferrure (30) comprenant des parois latérales (2a et 2b) d'un caisson de torsion, ainsi que des moyens de liaison (3a, 3b) qui relient la ferrure (30) aux couples du fuselage de queue (1) de l'aéronef, lesdites parois latérales (2a, 2b) étant reliées l'une à l'autre au moyen d'un élément central (4) qui comporte une première partie terminale (4a) reliée à la première paroi latérale (2a) de la ferrure (30), une seconde partie terminale (4b) reliée à la seconde paroi latérale (2b) de la ferrure (30) et une partie centrale (4c) qui relie entre elles lesdites parties terminales (4a, 4b). Ladite ferrure (30) comprend également plusieurs éléments terminaux (5a, 5b) qui sont reliés auxdites parois latérales (2a, 2b) sur leur face externe, ladite ferrure (30) ayant, du fait de sa plus grande rigidité face aux contraintes de charge latérale et de charges dans la direction verticale qui tendent à fermer les parois latérales (2a, 2b), du fait de son intégration supérieure et de la simplicité du chemin de charge, un comportement structural optimal face aux contraintes auxquelles est soumis l'aéronef.
Airbus Operations S.l.
Ridout & Maybee Llp
LandOfFree
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