Impact resistant aircraft fuselage

Details Impact resistant aircraft fuselage Impact resistant aircraft fuselage

B - Operations, Transporting

64

C

B64C 1/00 (2006.01) B64D 27/02 (2006.01) B64D 27/14 (2006.01) B64D 29/04 (2006.01)

Patent

CA 2707092

The invention relates to a structural configuration of the rear fuselage (4) of an aircraft with propeller engines (1) comprising propellers (23) formed in turn by blades (3), the mentioned propeller engines (1) being located at the rear part of the aircraft and the empennage (5) of the aircraft in turn being located behind the plane of the propellers (23), characterized in that the structural configuration of the rear fuselage (4) comprises an outer skin (6) and an inner skin (7), both skins (6, 7) being joined by means of radial elements (13) configuring cells (14), such that the obtained structural configuration maximizes the torsional strength of the rear fuselage (4) of the aircraft in the event of damage of the mentioned rear fuselage (4) due to the detachment of one of the blades (3) of the propeller engines (1).

L'invention porte sur une configuration de structure du fuselage arrière (4) d'un avion avec des moteurs à hélice (1) comprenant des hélices (23) formées à leur tour par des pales (3), les moteurs à hélice mentionnés (1) étant situés au niveau de la partie arrière de l'avion et l'empennage (5) de l'avion étant à son tour située derrière le plan des hélices (23). L'invention est caractérisée par le fait que la configuration de structure du fuselage arrière (4) comprend un revêtement externe (6) et un revêtement interne (7), les deux revêtements (6, 7) étant réunis au moyen d'éléments radiaux (13) configurant des cellules (14), de telle sorte que la configuration de structure obtenue rend maximale la résistance en torsion du fuselage arrière (4) de l'avion dans le cas d'un endommagement du fuselage arrière mentionné (4) dû au détachement de l'une des pales (3) des moteurs à hélice (1).

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