Aircraft aerodynamic surface with trailing edge deflector
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-003/50
B64C-021/00
출원번호
US-0958356
(2002-03-27)
우선권정보
FR-0004777 (1999-04-16)
국제출원번호
PCT/FR00/00864
(2000-04-06)
국제공개번호
WO00/63071
(2000-10-26)
발명자
/ 주소
Correge, Michel
Mignosi, Andre
Caruana, Daniel
Gobert, Jean-Louis
출원인 / 주소
Onera
대리인 / 주소
Stevens, Davis, Miller & Mosher, LLP
인용정보
피인용 횟수 :
22인용 특허 :
2
초록▼
An aerodynamic surface, such as a wing, empennage, angle of drift, nacelle pylon and the like for an aircraft includes at least one lightening hole pertaining to the trailing edge of the underwing, at least one hinged baffle that can be mounted in the lightening hole of the underwing, whereby the ch
An aerodynamic surface, such as a wing, empennage, angle of drift, nacelle pylon and the like for an aircraft includes at least one lightening hole pertaining to the trailing edge of the underwing, at least one hinged baffle that can be mounted in the lightening hole of the underwing, whereby the chord thereof is equal to a several hundredths of the chord of the aerodynamic surfacer and an actuator for the moveable baffle so that it can rotate around the hinge line.
대표청구항▼
1. An aircraft aerodynamic surface comprising a reduced-pressure face and a pressure face which are connected together, at the front, by a leading edge and, at the rear, by a trailing edge, and at least one moving deflector articulated via its front part about an axis at least essentially parallel t
1. An aircraft aerodynamic surface comprising a reduced-pressure face and a pressure face which are connected together, at the front, by a leading edge and, at the rear, by a trailing edge, and at least one moving deflector articulated via its front part about an axis at least essentially parallel to said trailing edge so as to be able to pivot about said axis of articulation under the action of actuating means, wherein: a chord of said at least one deflector is equal to a few hundredths of a chord of said aerodynamic surface; said at least one moving deflector is housed in a recess made in the thickness of said pressure face, forward of said trailing edge and extending as far as the latter, and said at least one deflector can adopt: either a retracted extreme position, for which said at least one deflector is fully housed in said pressure face recess, ensuring the continuity of said pressure face or any one of a number of deployed positions, for which said at least one deflector is turned with its rear part projecting from said pressure face recess, thus giving the trailing edge of said aerodynamic surface a parametrizable variable thickness. 2. The aerodynamic surface as claimed in claim 1, wherein the chord of said at least one deflector is at most equal to three hundredths of the chord of said aerodynamic surface. 3. The aerodynamic surface as claimed in claim 1, wherein when said at least one deflector is in the retracted extreme position, the rear edge thereof is aligned with the rear edge of said trailing edge base. 4. The aerodynamic surface as claimed in claim 1, wherein when said at least one deflector is in the retracted position, the rear edge thereof projects with respect to the edge of said trailing edge base. 5. The aerodynamic surface as claimed in claim 1, wherein said pressure face recess and said at least one deflector extend over most of the length of said trailing edge. 6. The aerodynamic surface as claimed in claim 1, wherein said recess and said at least one deflector extend over a limited portion of the length of said trailing edge. 7. The aerodynamic surface as claimed in claim 6, wherein it comprises several deflectors of limited length, arranged along said trailing edge. 8. The aerodynamic surface as claimed in claim 1, wherein said actuating means impart a fixed angular turning to said at least one moving deflector. 9. The aerodynamic surface as claimed in claim 1, wherein said actuating means impart a fluctuating angular turning to said at least one moving deflector. 10. The aerodynamic surface as claimed in claim 9, wherein said fluctuating angular turning is dependent on the measurement form sensors spread along the reduced-pressure face of said aerodynamic surface and making it possible, at every instant, to locate the levels of intensity of any air flow separation over said surface. 11. The aerodynamic surface as claimed in claim 10, wherein said sensors measure pressures.
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이 특허에 인용된 특허 (2)
Ross James C. (Oakland CA), Lift enhancing tabs for airfoils.
Subramaniyan, Moorthi; Chengappa, Manjunath Bangalore; Patel, Pradeep, Gas turbine diffuser strut including a trailing edge flap and methods of assembling the same.
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