[특허]Aircraft

Airbus Operations GmbH

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특허 상세정보

MyON담기

내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Aircraft

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-003/58
미국특허분류(USC)	244/213; 244/214
출원번호	US-0595886 (2008-04-24)
등록번호	US-8408499 (2013-04-02)
국제출원번호	PCT/EP2008/054985 (2008-04-24)
§371/§102 date	20091214 (20091214)
국제공개번호	WO2008/129074 (2008-10-30)
발명자 / 주소	Cerne, Gerd
출원인 / 주소	Airbus Operations GmbH
대리인 / 주소	Greer, Burns & Crain Ltd.
인용정보	피인용 횟수 : 4 인용 특허 : 3

초록
▼

The invention provides according to one aspect an aircraft, comprising a fuselage, an airfoil mounted to the fuselage and a flap for steering the aircraft. Furthermore, connecting means articularly connect the flap to the airfoil such that the flap is allowed to rotate around a rotation axis substantial parallel to the trailing or leading edge of the airfoil between a retracted position and an extended position and to translate in a direction substantially parallel to the rotation axis. A rod articularly connect the flap to the airfoil or to the fuselage, wherein the rod defines the translation of the flap in the direction parallel to the rotation axis. Hence, by way of one aspect of the invention, forces acting of the flap in a direction parallel to the rotation axis can be taken up by the rod. Consequently, there is no need for using locating bearings having negative aerodynamic effects due to their by comparison large dimensions in a direction substantially perpendicular to the direction of flight of the aircraft.

대표
청구항
▼

1. Aircraft, comprising: a fuselage;an airfoil mounted to the fuselage;a flap for steering the aircraft;connecting means articulately connecting the flap to the airfoil such that the flap is allowed to rotate around a rotation axis, which is stationary with respect to the airfoil and substantially parallel to the trailing or leading edge of the airfoil, between a retracted position and an extended position and to translate in a direction substantially parallel to the rotation axis; anda rod articulately connecting the flap to the airfoil or to the fuselage, wherein the rod defines the translation of the flap in the direction parallel to the rotation axis. 2. Aircraft according to claim 1, wherein the rod is configured such that the flap translates in the direction parallel to the rotation axis as the flap is rotated between its retracted position and its extended position. 3. Aircraft according to claim 1, wherein the rod extends substantially parallel to the rotation axis in the retracted position of the flap and forms an angle with the rotation axis in the extended position of the flap. 4. Aircraft according to claim 1, wherein the rod has an articulate joint connecting it to the leading edge, trailing edge or one of the sides of the flap at its one end and an articulate joint connecting it to the airfoil or to the fuselage at its other end. 5. Aircraft according to claim 4, wherein the articulate joint at the other end of the rod connecting the rod to the airfoil is fixedly attached to the rear spar or front spar of the airfoil by means of a plurality of struts. 6. Aircraft according to claim 5, wherein adjacent struts are arranged in a V-shape. 7. Aircraft according to claim 1, wherein the connecting means comprise at least two levers spaced apart from each other along the rotation axis and articulately connecting the flap to at least one of the airfoil and the fuselage. 8. Aircraft according to claim 7, wherein at least one of the levers is triangular in shape having an articulate joint at its one corner connecting it to the airfoil and a hinge joint along the side opposing the articulate joint connecting it to the flap. 9. Aircraft according to claim 7, wherein at least one of the levers has an articulate joint to the fuselage at its one end and an articulate joint to a trunnion fixed to the flap at its other end, wherein the trunnion is non-rotatably fixed to the lever in a plane substantially perpendicular to the rotation axis. 10. Aircraft according to claim 9, wherein the rod has an articulate joint connecting it to the trunnion of the flap at its one end and an articulate joint connecting it to the fuselage at its other end. 11. Aircraft according to claim 7, wherein the airfoil has at least one support beam attached to it, wherein an end section of the support beam extends away from the airfoil and wherein at least one of the levers has an articulate joint connecting it to the end section. 12. Aircraft according to claim 7, wherein the at least one support beam extends in the direction of flight of the aircraft. 13. Aircraft according to claim 7, wherein the airfoil has for at least part of its length a trailing or leading edge extending at an angle not equal to 90° with respect to the direction of flight. 14. Aircraft according to claim 11, wherein an actuator is mounted to the support beam, the actuator having a linkage connected to the flap, the linkage being extendible substantially in the plane of the support beam to operate the flap between its retracted position and its extended position. 15. Aircraft according to claim 14, wherein the actuator is configured as a spindle drive or a lever arm drive. 16. Aircraft, comprising: a fuselage;an airfoil mounted to the fuselage;a flap for steering the aircraft;at least two levers spaced apart from each other along a rotation axis and articulately connecting the flap to at least one of the airfoil and the fuselage such that the flap is allowed to rotate around the rotation axis substantially parallel to the trailing or leading edge of the airfoil between a retracted position and an extended position and to translate in a direction substantially parallel to the rotation axis; anda rod articulately connecting the flap to the airfoil or to the fuselage,wherein the rod defines the translation of the flap in the direction parallel to the rotation axis. 17. Aircraft according to claim 16, wherein at least one of the levers is triangular in shape having an articulate joint at its one corner connecting it to the airfoil and a hinge joint along the side opposing the articulate joint connecting it to the flap. 18. Aircraft according to claim 16, wherein at least one of the levers has an articulate joint to the fuselage at its one end and an articulate joint to a trunnion fixed to the flap at its other end, wherein the trunnion is non-rotatably fixed to the lever in a plane substantially perpendicular to the rotation axis. 19. Aircraft according to claim 18, wherein the rod has an articulate joint connecting it to the trunnion of the flap at its one end and an articulate joint connecting it to the fuselage at its other end. 20. Aircraft according to claim 16, wherein the airfoil has at least one support beam attached to it, wherein an end section of the support beam extends away from the airfoil and wherein at least one of the levers has an articulate joint connecting it to the end section. 21. Aircraft according to claim 16, wherein the at least one support beam extends in the direction of flight of the aircraft. 22. Aircraft according to claim 16, wherein the airfoil has for at least part of its length a trailing or leading edge extending at an angle not equal to 90° with respect to the direction of flight. 23. Aircraft according to claim 22, wherein an actuator is mounted to the support beam, the actuator having a linkage connected to the flap, the linkage being extendible substantially in the plane of the support beam to operate the flap between its retracted position and its extended position. 24. Aircraft according to claim 23, wherein the actuator is configured as a spindle drive or a lever arm drive.

이 특허에 인용된 특허 (3)

이 특허를 인용한 특허 (4)

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상세정보
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특허 상세정보

Aircraft

초록
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대표
청구항
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이 특허에 인용된 특허 (3)

이 특허를 인용한 특허 (4)

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과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

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특허 상세정보

Aircraft

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대표청구항 ▼

이 특허에 인용된 특허 (3)

이 특허를 인용한 특허 (4)

IPC 상위 출원인

과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

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청구항
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