[특허]Airplane with a tailcoat tail assembly and rear engine

Airbus Operations S.A.S.

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Airplane with a tailcoat tail assembly and rear engine

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-001/00
미국특허분류(USC)	244/013; 244/055; 244/054
출원번호	US-0255720 (2010-03-12)
등록번호	US-8651414 (2014-02-18)
우선권정보	FR-09 51561 (2009-03-12)
국제출원번호	PCT/FR2010/050437 (2010-03-12)
§371/§102 date	20120207 (20120207)
국제공개번호	WO2010/103252 (2010-09-16)
발명자 / 주소	Cazals, Olivier Genty De La Sagne, Jaime
출원인 / 주소	Airbus Operations S.A.S.
대리인 / 주소	Oblon, Spivak, McClelland, Maier & Neustadt, L.L.P.
인용정보	피인용 횟수 : 5 인용 특허 : 5

초록
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An airplane, including a fuselage having an elongate shape along a longitudinal axis of the airplane, and at least one wing attached to the fuselage between front and back ends of the fuselage and a substantially cylindrical central portion and a rear scaleable portion on which a vertical tail assembly and a rear propulsion assembly are attached. Between a section for connecting the rear portion to the central portion of the fuselage and the back end: the maximum width of each fuselage section is constant or increases towards the rear up to a maximum fuselage width L; the height of each fuselage section decreases towards the rear, such that the back end of the fuselage forms a thin trailing edge substantially horizontal in the indicating line of the airplane and substantially rectilinear; a reactor for the propulsion assembly is provided in a so-called semi-buried configuration in the fuselage.

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청구항
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1. An airplane comprising: a fuselage including at least one wing attached to the fuselage between a front end and a rear end of the fuselage, the fuselage having a substantially cylindrical central part and a tapered rear part joined to the central part at a connecting section, onto which a vertical tail assembly is attached and onto which a rear propulsive assembly is attached substantially at a vertical symmetry plane of the fuselage,wherein, in the tapered rear part:a maximum height of each section of the fuselage decreases toward a rear of the airplane so that the rear end of the fuselage forms a trailing edge with a width L;a maximum width of each section of the fuselage increases continuously, the maximum width being locally constant or increasing toward the rear of the airplane, from a maximum width of the connection section up to the width L, the width L being greater than the maximum width of the connecting section;a rear engine of the rear propulsive assembly is situated in a rear part of the fuselage so that a lower part of the rear engine, at a maximum diameter of the rear engine, is partially inside the fuselage and an upper part of the rear engine is on top of the fuselage according to a semi-buried configuration; andthe rear propulsive assembly includes a nacelle having shapes which join with the rear part of the fuselage on each side of the nacelle. 2. The airplane according to claim 1, wherein the rear part of the fuselage includes, on each side of the rear propulsive assembly, a fuselage control surface joined onto the fuselage around an axis substantially horizontal to an airplane reference line and the trailing edge corresponding to the rear end of the fuselage. 3. The airplane according to claim 2, wherein the vertical tail assembly includes two substantially vertical stabilizers attached to the rear part of the fuselage in front of the fuselage control surfaces, each stabilizer being integral with the fuselage on one edge, right and left respectively of the airplane, of the rear part of the fuselage. 4. The airplane according to claim 3, wherein the stabilizers include longerons, the longerons of the stabilizers being arranged along a longitudinal direction of the airplane on the rear part of the fuselage in relation to the rear engine so that the longerons are outside a zone of ejection of debris from the rear engine. 5. The airplane according to claim 4, wherein the fuselage includes a movable structure having at least one retracted position in which the movable structure is situated inside the rear part of the fuselage and having at least one extended position in which the movable structure forms an extension toward a rear of the trailing edge of the fuselage at a rear end thereof, substantially in a horizontal plane of an airplane reference line and beneath the rear propulsive assembly. 6. The airplane according to claim 1, wherein a front end of the rear engine is situated along a longitudinal direction of the airplane behind an impervious rear cabin base of the fuselage. 7. The airplane according to claim 6, wherein the rear part of the fuselage includes, behind the rear cabin, base load-carrying frames, wherein the load-carrying frames comprises stabilizer frames configured to take up stresses introduced into the fuselage by the longerons,wherein the load-carrying frames comprises engine frames, the engine frames each including in respective upper parts thereof an arch having an opening with substantially the dimensions of an air intake of the rear engine, and the engine frames being arranged in front of the rear engine in order to have sufficient structural strength for taking up stresses introduced into the fuselage by the rear engine. 8. The airplane according to claim 7, wherein the rear engine is attached and suspended beneath a structural beam cantilevered behind the engine frames, the structural beam being integral with the arches of the engine frames. 9. The airplane according to claim 8, wherein the rear part of the fuselage comprises two longitudinal ribs, substantially in a vertical plane in an airplane reference line, integral with at least one of the load-carrying frames and extending cantilevered behind a rear load-carrying frame toward the rear of the airplane substantially up to the rear end of the fuselage, the ribs defining between them beneath the rear engine a maintenance well clear of any obstacle, via which the rear engine may be removed by gravity. 10. The airplane according to claim 9, wherein a rear frame comprises two outer portions integral with the longitudinal ribs on the side opposite the maintenance well onto which the fuselage control surfaces are joined.

이 특허에 인용된 특허 (5)

이 특허를 인용한 특허 피인용횟수: 5

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Airplane with a tailcoat tail assembly and rear engine

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이 특허에 인용된 특허 (5)

이 특허를 인용한 특허 피인용횟수: 5

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IPC 상세정보(version : 201201)

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Airplane with a tailcoat tail assembly and rear engine

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이 특허에 인용된 특허 (5)

이 특허를 인용한 특허 피인용횟수: 5

IPC 상위 출원인

상세정보조회

원문조회

IPC 상세정보(version : 201201)

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