Aircraft flap system with aileron functionality
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-003/50
B64C-009/18
B64C-009/04
B64C-009/16
B64C-013/38
B64C-009/00
출원번호
US-0285712
(2014-05-23)
등록번호
US-9555875
(2017-01-31)
우선권정보
EP-13169534 (2013-05-28)
발명자
/ 주소
Burchard, Alexander
출원인 / 주소
Airbus Operations GmbH
대리인 / 주소
Jenkins, Wilson, Taylor & Hunt, P.A.
인용정보
피인용 횟수 :
0인용 특허 :
8
초록▼
The present disclosure pertains to an actuation mechanism for a flap with aileron functionality, including a crank having a crank axle, a crank arm and a crank pivot; a displacement shaft articulated to the crank pivot at an actuating end portion; and a rotatable linear-motion bearing in which the d
The present disclosure pertains to an actuation mechanism for a flap with aileron functionality, including a crank having a crank axle, a crank arm and a crank pivot; a displacement shaft articulated to the crank pivot at an actuating end portion; and a rotatable linear-motion bearing in which the displacement shaft is slidably supported, wherein the displacement shaft is fixedly connectable to a flap body of the aircraft flap at a flap end portion of the displacement shaft opposite to the actuating end portion, and wherein the linear-motion bearing is rotatably attachable at a pivot point to an aircraft wing comprising the aircraft flap, so that the displacement shaft is able to rotate around an axis running spanwise of the aircraft wing around the pivot point. The present disclosure further pertains to an aircraft flap with such an actuation mechanism and an aircraft having an aircraft flap.
대표청구항▼
1. An aircraft flap with aileron functionality, the aircraft flap comprising: a flap body; andan actuation mechanism comprising: a crank having a crank axle, a crank arm, and a crank pivot;a displacement shaft articulated to the crank pivot at an actuating end portion; anda rotatable linear-motion b
1. An aircraft flap with aileron functionality, the aircraft flap comprising: a flap body; andan actuation mechanism comprising: a crank having a crank axle, a crank arm, and a crank pivot;a displacement shaft articulated to the crank pivot at an actuating end portion; anda rotatable linear-motion bearing in which the displacement shaft is slidably supported,the linear-motion bearing being rotatably attached at a pivot point to an aircraft wing comprising the aircraft flap, so that the displacement shaft is able to rotate around an axis running spanwise of the aircraft wing around the pivot point; andthe displacement shaft being statically and fixedly connected to the flap body of the aircraft flap at a flap end portion of the displacement shaft opposite to the actuating end portion. 2. The aircraft flap according to claim 1, wherein the linear-motion bearing is a spherical plain bearing or a spherical rolling element bearing. 3. The aircraft flap according to claim 1, wherein the crank is actuated by a linear actuator. 4. The aircraft flap according to claim 3, wherein the linear actuator comprises one of a hydraulic actuator, a pneumatic actuator, a rack and pinion drive actuator, a spindle actuator, and a chain drive actuator. 5. The aircraft flap according to claim 1, wherein the crank is actuated by a rotary actuator. 6. The aircraft flap according to claim 5, wherein the rotary actuator comprises one of a hydraulic rotary actuator, a pneumatic rotary actuator, and a mechanical rotary actuator. 7. The aircraft flap according to claim 1, further comprising: a rotary vane fixedly attached to the linear-motion bearing, wherein an outer surface of the rotary vane proximate to the flap body has a contour substantially conforming to a contour of the flap body. 8. The aircraft flap according to claim 7, wherein the rotary vane comprises an outer surface distal to the flap body which has a contour substantially conforming to the contour of the aircraft wing. 9. The aircraft flap according to claim 7 further comprising: a hinged aerofoil edge portion hingably attachable to a downside surface of the aircraft wing. 10. The aircraft flap according to claim 9, wherein the hinged aerofoil edge portion is connected to the outer surface of the rotary vane proximate to the flap body by a linear slide bearing. 11. The aircraft flap according to claim 1, wherein the crank arm is actuatable in such a way that the displacement shaft is pivotable around the pivot point of the linear-motion bearing within a range between a maximum negative pivot angle and a maximum positive pivot angle with respect to a neutral position of the displacement shaft. 12. The aircraft flap according to claim 11, wherein the neutral position of the displacement shaft corresponds to a cruise flight position of the aircraft flap. 13. The aircraft flap according to claim 11, wherein the maximum negative pivot angle corresponds to a maximum banking control position of the aircraft flap, and wherein the maximum positive pivot angle corresponds to a maximum lift assistance position of the aircraft flap. 14. An aircraft comprising: at least one aircraft wing; andat least one aircraft flap with aileron functionality according to claim 1, the flap being arranged at a trailing edge of the aircraft wing. 15. The aircraft according to claim 14, wherein the pivot point of the linear-motion bearing is located within an outer profile of the aircraft wing. 16. The aircraft according to claim 14, wherein the aircraft comprises a plurality of aircraft flaps with aileron functionality, all of which are used both as landing flaps and as ailerons.
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이 특허에 인용된 특허 (8)
Rudolph Peter K. C. (Seattle WA), Aileron system for aircraft and method of operating the same.
Reckzeh, Daniel; Dyke, Adrian R., Aircraft wing, method for operating an aircraft wing, and use of a pivotable trailing edge on a main wing of an aircraft, for adjusting the shape and width of an air gap.
Patzelt, Aicke; Reiprich, Michael; Stegmaier, Gunther; Wiglema, Wietse, Support structure for a retractable and extendable flap, and use of said structure.
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