Wing of an aircraft and assembly of a wing comprising a device for influencing a flow
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-021/08
B64C-021/04
B64C-021/06
B64C-009/16
B64C-021/02
출원번호
US-0254841
(2010-03-04)
등록번호
US-9079657
(2015-07-14)
우선권정보
DE-10 2009 011 662 (2009-03-04)
국제출원번호
PCT/EP2010/001364
(2010-03-04)
§371/§102 date
20110903
(20110903)
국제공개번호
WO2010/099967
(2010-09-10)
발명자
/ 주소
Frey, Juergen
Goelling, Burkhard
Hansen, Heinz
Hildebrand, Veit
Neitzke, Klaus-Peter
출원인 / 주소
Airbus Operations GmbH
대리인 / 주소
Jenkins, Wilson, Taylor & Hunt, P.A.
인용정보
피인용 횟수 :
0인용 특허 :
2
초록▼
A wing of an aircraft is described, having: a main wing, at least one high lift flap which can be moved between a retracted and an extended position, and a spoiler. The main wing has ejection openings, arranged side-by-side along the main wing spanwise direction, and in the main wing chordwise direc
A wing of an aircraft is described, having: a main wing, at least one high lift flap which can be moved between a retracted and an extended position, and a spoiler. The main wing has ejection openings, arranged side-by-side along the main wing spanwise direction, and in the main wing chordwise direction, and which are connected via an air conduit with the outlet device of a flow delivery driver device on the main wing or on the spoiler. The spoiler has inlet openings for the intake of air, which are connected via an air conduit with the inlet device of the flow delivery driver device. The flow delivery driver device has a receiver device for the reception of command signals for purposes of adjustment of the flow delivery driver device. An arrangement of a wing with a device for purposes of flow control with such a wing is also described.
대표청구항▼
1. A wing of an aircraft with an upper side and a lower side, the wing comprising: a main wing, which has an upper surface positioned on the upper side, and a lower surface positioned on the lower side, which surfaces in each case run along a main wing chordwise direction;at least one high lift flap
1. A wing of an aircraft with an upper side and a lower side, the wing comprising: a main wing, which has an upper surface positioned on the upper side, and a lower surface positioned on the lower side, which surfaces in each case run along a main wing chordwise direction;at least one high lift flap coupled to the main wing such that the at least one high lift flap is movable between a retracted and an extended setting; andat least one spoiler coupled to the main wing such that the at least one spoiler is rotatable and projects beyond a trailing edge of the main wing; wherein the main wing has a plurality of ejection openings, of which a plurality are arranged side-by-side along a main wing spanwise direction, and which are connected in terms of flow via an air conduit with an outlet device of a flow delivery driver device arranged on the main wing or on the spoiler;wherein the spoiler has a plurality of inlet openings for intake of air, which are arranged side-by-side in a spoiler spanwise direction, and which in each case are connected in terms of flow via an air conduit with an inlet device of the flow delivery driver device; andwherein the flow delivery driver device has a receiver device for reception of command signals for purposes of adjustment of the flow delivery driver device in such a manner that air flowing around the wing is sucked in through the inlet openings on the spoiler and said air is ejected through the ejection openings on the main wing. 2. The wing in accordance with claim 1, wherein the plurality of ejection openings of the main wing are arranged side-by-side along the main wing spanwise direction, and in the main wing chordwise direction are arranged in a region between 40% and 90% of a wing chord of the total wing, and which are connected in terms of flow via the air conduit with the outlet device of the flow delivery driver device arranged on the main wing, or on the spoiler. 3. The wing in accordance with claim 1, wherein the plurality of inlet openings of the spoiler for the intake of air are arranged side-by-side in the spoiler spanwise direction and in a spoiler chordwise direction are arranged in a region between 70% and 100% of a spoiler chord as seen from a front end of the spoiler. 4. The wing in accordance with claim 1, wherein the wing has a leading edge slat, and wherein the plurality of ejection openings are positioned from a tip of the total wing in the main wing chordwise direction in a region between 40% and 90% of a wing chord of the wing, with the leading edge slat retracted, and with the high lift flap retracted. 5. The wing in accordance with claim 1, wherein at a location on the main wing spanwise direction and as seen in the main wing chordwise direction of the main wing a plurality of ejection openings are arranged one behind another. 6. The wing in accordance with claim 1, wherein ejection openings positioned side-by-side in the main wing spanwise direction as seen in the main wing chordwise direction of the main wing are arranged displaced relative to one another on the upper side of the main wing. 7. The wing in accordance with claim 1, wherein the ejection openings are arranged such that an angle between a direction of an opening out of the air conduit at each ejection opening and a planar extent of the upper surface at this location is between 0 degrees and 60 degrees, so that within predetermined limits a tangential ejection of air takes place through the ejection openings. 8. The wing in accordance with claim 1, wherein the ejection openings on the main wing are designed as a slot and a length of at least a fraction of the ejection openings as seen in the main wing spanwise direction is between 1% and 50% of a main wing chord at a spanwise location of the respective slot. 9. The wing in accordance with claim 1, wherein the inlet openings on the spoiler are designed as slots and a length of at least a fraction of the inlet openings as seen in the spoiler spanwise direction is between 1/10 and ¼ of a spoiler chord of the spoiler at this location. 10. The wing in accordance with claim 1, wherein the main wing has: on at least a fraction of the ejection openings of the main wing in each case an opening alteration device for purposes of opening and closing the respective ejection opening with an opening alteration mechanism and an actuator coupled to the latter for purposes of actuating the respective opening alteration mechanism. 11. The wing in accordance with claim 10, wherein the opening alteration device has a slider, which, by virtue of an actuation by the actuator, partially or completely opens or closes the respective ejection opening. 12. The wing in accordance with claim 11, wherein the actuator on the basis of a driver signal periodically opens and closes the slider and thereby the ejection opening in order to effect a pulsed ejection of the air through the ejection opening. 13. An arrangement of a wing with a device for purposes of flow control, the wing formed in accordance with claim 10, wherein the device for purposes of flow control has: a driver device functionally connected with a flight control device to control the opening alteration device, wherein the driver device has a driver function, which receives from the flight control device at least one of a setting status of the spoiler and setting status of the high lift flap as an input parameter, and on the basis of the setting statuses in each case generates an appropriate regulating signal for purposes of driving the opening alteration device and transmits this to the latter to control adjustment of the opening alteration device. 14. The wing in accordance with claim 1, wherein on at least a fraction of the ejection openings of the main wing in each case is arranged a pulse generator-actuator, which upon an appropriate input signal effects a pulsed ejection of the air. 15. The wing in accordance with claim 1, wherein on at least a fraction of the ejection openings of the main wing in each case is arranged an opening alteration device with an actuator, with which an orientation of a respective ejection opening relative to a surface of the main wing is adjustable. 16. An arrangement of a wing with a device for purposes of flow control, the wing formed in accordance with claim 1, wherein the device for purposes of flow control has: a driver device functionally connected with a flight control device to control performance of the flow delivery driver device, wherein the driver device has a driver function, which receives from the flight control device at least one of a setting status of the spoiler and a setting status of the high lift flap as an input parameter, and on the basis of the setting statuses in each case generates an appropriate regulating signal for purposes of driving the flow delivery driver device and transmits this to the latter to control through flow of the flow delivery driver device. 17. The arrangement of the wing with the device for purposes of flow control in accordance with claim 16, wherein the device for purposes of flow control has: a sensor device arranged on at least one of the main wing, the spoiler, and the high lift flap, with a sensor for purposes of recording flow status of the flow attached to or separated from at least one of an upper side of the spoiler and an upper side of the high lift flap, which is functionally connected with the driver device, andthe driver function has a control function for purposes of controlling a prescribed flow parameter of the adjustable flap, which is functionally connected with the sensor device for purposes of receiving current flow parameters, with a setting flap positioning device for purposes of receiving a parameter for the setting status of the adjustable flap, and with at least one of the flow delivery driver device and an opening alteration device for purposes of transmitting a regulating signal for purposes of control through flow of at least one of the flow delivery driver device and the opening alteration device. 18. The arrangement of the wing with the device for purposes of flow control in accordance with claim 17, wherein the sensor device is positioned in at least one of a region between 40 and 90 percent of a total main wing chord of the main wing, a region between 40 and 90 percent of a total spoiler chord of the spoiler, and a region between 40 and 90 percent of a total flap chord of the high lift flap. 19. The arrangement of the wing with the device for purposes of flow control in accordance with claim 17, wherein the sensor is a hot wire sensor for purposes of recording a velocity gradient and wherein the driver function has a function for purposes of converting the velocity gradient into a wall shear stress, and the determination of driver signals takes place on the basis of the wall shear stress determined. 20. The arrangement of the wing with the device for purposes of flow control in accordance with claim 17, wherein the sensor is a piezo-wall shear stress sensor for purposes of recording wall shear stress.
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이 특허에 인용된 특허 (2)
Reckzeh, Daniel; Schlipf, Bernhard; Andreani, Luc; Sutcliffe, Mark, Advanced trailing edge control surface on the wing of an aircraft.
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