[특허]Wide body aircraft architecture

Airbus Operations SAS

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Wide body aircraft architecture

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-001/00
미국특허분류(USC)	244/119; 244/137.1
출원번호	US-0108685 (2008-04-24)
등록번호	US-8398022 (2013-03-19)
우선권정보	FR-07 54689 (2007-04-25)
발명자 / 주소	Cazals, Olivier Druot, Thierry
출원인 / 주소	Airbus Operations SAS
대리인 / 주소	Perman & Green, LLP
인용정보	피인용 횟수 : 1 인용 특허 : 7

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A large-capacity airplane principally includes a fuselage which has no region of constant width between the front and the rear and a wing fixed to the fuselage. As a preference, the engines are fixed at the rear under a horizontal tail held above the fuselage by vertical stabilizers and maintenance wells are formed in the fuselage in vertical alignment with each engine to allow the engines to be fitted and removed. The width of the fuselage is determined, on the one hand, so that the airplane landing gear is fixed to the fuselage and in the up position i...

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1. An airplane comprising a fuselage and at least one wing fixed to the fuselage between a forward end of said fuselage and a rear end of said fuselage, the fuselage comprising a longitudinal axis directed in a direction X and an exterior surface determining an envelope shape determining geometries of cross sections perpendicular to the longitudinal axis in successive positions offset along the longitudinal axis, each cross section having a maximum width l in a direction Y in a horizontal plane of an aircraft reference system and a maximum height h in a direction Z in a vertical plane in the airplane reference system, wherein: the fuselage comprises a central region of the fuselage situated between a forward region comprising a flight deck at the forward end of the fuselage and a rear region situated toward the rear end of the fuselage, wherein the rear region comprises a tail;the maximum width l of the cross sections of the fuselage evolves substantially continuously between the forward end and the rear end;the maximum height h of the fuselage along the X direction is substantially constant in the central region;each cross section of the fuselage in the central region has approximately a rectangular shape with the maximum width l larger than the maximum height h to give a flattened appearance to said fuselage;the maximum height h of the cross sections of the forward region evolves in the X direction substantially continuously between the maximum height of the central region in a connecting section where the forward region meets said central region and a reduced end height at the forward end of the fuselage; andthe maximum height h of the cross sections of the rear region evolves in the X direction substantially continuously between the maximum height of the central region in a connecting section where the rear region meets said central region and a reduced end height at the rear end of the fuselage. 2. An airplane according to claim 1, in which the envelope shape in the central region is determined principally by four secant main curved surfaces, determining, at each cross section, four curved segments corresponding respectively to an upper limit, to a lower limit and to two lateral limits, one right and one left of the exterior surface of the fuselage, each of the four curved segments corresponding to an arc of circle or an arc of ellipse, wherein at least the curved segments corresponding to the upper limit and to the lower limit have a radii of curvature providing the cross section with an approximately rectangular shape and the fuselage with a flattened appearance. 3. An airplane according to claim 1, in which a floor area inside the fuselage and dedicated to payloads has a first floor area located forward of a point of reference of a mean aerodynamic chord of the wing and a second floor area located to the rear of the point of reference of the aerodynamic chord of the wing, said second floor area being substantially equal to the first floor area. 4. An airplane according to claim 1, comprising landing gear fixed to the fuselage and having at least two stable positions, one position comprising an up position, said landing gear being, in said up position, completely housed inside the volume delimited by the envelope shape of the fuselage. 5. An airplane according to claim 1, wherein the tail comprises a horizontal tail, the airplane comprising a substantially horizontal aerodynamic surface held above the fuselage by at least one substantially vertical aerodynamic surface. 6. An airplane according to claim 5, comprising at least one propulsion engine held above the fuselage and fixed under the horizontal tail. 7. An airplane according to claim 6 wherein a rear end fuselage width is at least sufficient to accommodate engines above the fuselage and wherein said fuselage comprises, under each engine fixed under the horizontal tail, a substantially vertical well passing through the fuselage and in vertical alignment with said each engine, the dimensions of each said well being large enough to fit an engine during an operation of fitting or removing said engine. 8. An airplane according to claim 7 in which a wall situated forward of each well corresponds with a rear wall of a rear cargo compartment inside the fuselage and in which said rear wall has at least one exit of the rear cargo bay opening inside the well. 9. An airplane according to claim 8, in which at least one ramp, articulated along a substantially horizontal line substantially perpendicular to the X direction and in the lower part of each wall situated forward of each well, has a raised position in which said ramp closes a lower opening of one or more wells, has at least one lowered position in which said ramp forms a surface for accessing the at least one exit in the rear wall of the rear cargo compartment and has an intermediate position in which an upper surface of the ramp is substantially in an horizontal plane of the aircraft reference system and corresponding to a plane for loading the rear cargo holds.

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이 특허를 인용한 특허 피인용횟수: 1

Cazals, Olivier; Genty De La Sagne, Jaime. Airplane with a tailcoat tail assembly and rear engine. USP2014028651414.

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Wide body aircraft architecture

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이 특허에 인용된 특허 (7)

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