[미국특허]
Aircraft wing systems for providing differential motion to deployable lift devices
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-003/50
B64C-003/00
B64C-009/00
출원번호
US-0935846
(2004-09-08)
등록번호
US-7494094
(2009-02-24)
발명자
/ 주소
Good,Mark S.
Viigen,Paul M.
Gitnes,Seth E.
Thomas,Glynn Michael
출원인 / 주소
The Boeing Company
대리인 / 주소
Perkins Coie LLP
인용정보
피인용 횟수 :
20인용 특허 :
214
초록▼
Systems and methods for providing differential motion to wing high lift devices are disclosed. A system in accordance with one embodiment of the invention includes a wing having a leading edge, a trailing edge, a first deployable lift device with a first spanwise location, and a second deployable li
Systems and methods for providing differential motion to wing high lift devices are disclosed. A system in accordance with one embodiment of the invention includes a wing having a leading edge, a trailing edge, a first deployable lift device with a first spanwise location, and a second deployable lift device with a second spanwise location different than the first. The wing system can further include a drive system having a drive link operatively coupleable to both the first and second deployable lift devices, and a control system operatively coupled to the drive system. The control system can have a first configuration for which the drive link is operatively coupled to the first and second deployable lift devices, and activation of at least a portion of the drive link moves the first and second deployable lift devices together. In a second configuration, the drive link is operatively coupled to at least the first deployable lift device and operatively decoupled from the second deployable lift device, so that actuation of at least a portion of the drive link moves the first deployable lift device relative to the second deployable lift device.
대표청구항▼
We claim: 1. An aircraft wing system, comprising: a wing having a leading edge and a trailing edge; a first deployable lift device having a first spanwise location and being movable relative to the wing from a stowed position to at least one first deployed position; a second deployable lift device
We claim: 1. An aircraft wing system, comprising: a wing having a leading edge and a trailing edge; a first deployable lift device having a first spanwise location and being movable relative to the wing from a stowed position to at least one first deployed position; a second deployable lift device having a second spanwise location different than the first and being movable relative to the wing from a stowed position to at least one second deployed position; a drive system having a drive link operatively coupleable to both the first and the second deployable lift devices; and a control system operatively coupled to the drive system, the control system having: a first configuration for which the drive link is operatively coupled to the first and second deployable lift devices, and activation of at least a portion of the drive link moves the first and second deployable lift devices together; a second configuration for which the drive link is operatively coupled to the first deployable lift device and operatively decoupled from the second deployable lift device, and activation of at least a portion of the drive link moves the first deployable lift device relative to the second deployable lift device; and a third configuration for which the drive link is operatively coupled to the second deployable lift device and operatively decoupled from the first deployable lift device, and wherein activation of at least a portion of the drive link moves the second deployable lift device relative to the first deployable lift device, and wherein the drive link includes a drive shaft, and the drive system, includes a first motor, a second motor and a differential coupled among the drive shaft, the first deployable lift device, the second deployable lift device, the first motor and the second motor, and wherein the control system includes: a first brake operatively coupled to the differential and engaged to move the first and second deployable lift devices when the control system has the first configuration; a second brake operatively coupled to the second deployable lift device and engaged to at least resist motion of the second deployable lift device when the control system has the second configuration; and a third brake operatively coupled to the first deployable lift device and engaged to at least resist motion of the first deployable lift device when the control system has the third configuration; wherein the first motor is operatively coupled to the first and second deployable lift devices and the second motor is operatively decoupled from the first and second deployable lift devices when the control system has the first configuration; the second motor is operatively coupled to the first deployable lift device and the first motor is operatively decoupled from the first and second deployable lift devices when the control system has the second configuration; and the second motor is operatively coupled to the second deployable lift device and the first motor is operatively decoupled from the first and second deployable lift devices when the control system has the third configuration. 2. The system of claim 1, further comprising a range limiter operatively coupled to the first and second deployable lift devices to provide a first range of motion when the control system has the first configuration, and provide a second range of motion less than the first range of motion when the control system has the second configuration. 3. The system of claim 1 wherein the drive link includes a mechanical drive shaft. 4. The system of claim 1 wherein the first deployable lift device is inboard of the second deployable lift device. 5. The system of claim 1 wherein the first deployable lift device is outboard of the second deployable lift device. 6. The system at claim 1, further comprising a fuselage coupled to the wing. 7. The system of claim 1 wherein the control system includes a computer having a computer-readable medium with instructions for changing between the first and second configurations. 8. An aircraft wing system, comprising: a wing having a leading edge and a wailing edge; a first deployable lift device positioned proximate to the wing leading edge or the wing trailing edge at a first spanwise location, the first deployable lift device being movable relative to the wing from a stowed position to at least one first deployed position; a second deployable lift device positioned proximate to the wing leading edge or the wing trailing edge at a second spanwise location different than the first, the second deployable lift device being movable relative to the wing from a stowed position to at least one second deployed position; a drive system having a drive link operatively coupleable to both the first and the second deployable lift devices; and a control system operatively coupled to the drive link, the control system having: a first configuration for which activation of at least a portion of the drive link moves the first and second deployable lift devices together; a second configuration for which activation of at least a portion of the drive link moves the first deployable lift device relative to the second deployable lift device; and a third configuration for which activation of at least a portion of the drive link moves the second deployable lift device relative to the first deployable lift device, wherein the drive link includes a drive shaft and wherein the drive system includes a first motor, a second motor, and differential coupled among the drive shaft, the first deployable lift device, the second deployable lift device, the first motor and the second motor; and wherein the control system further includes: a first brake operatively coupled to the differential and engaged to move the first and second deployable lift devices when the control system has the first configuration; a second brake operatively coupled to the second deployable lift device and engaged to at least resist motion of the second deployable lift device when the control system has the second configuration; and a third brake operatively coupled to the first deployable lift device and engaged to at least resist motion of the first deployable lift device when the control system has the third configuration; wherein the first motor is operatively coupled to the first and second deployable lift devices and the second motor is operatively decoupled from the first and second deployable lift devices when the control system has the first configuration; the second motor is operatively coupled to the first deployable lift device and the first motor is operatively decoupled from the first and second deployable lift devices when the control system has the second configuration; and the second motor is operatively coupled to the second deployable lift device and the first motor is operatively decoupled from the first and second deployable lift devices when the control system has the third configuration. 9. The system of claim 8 wherein the drive link includes a mechanical drive shaft. 10. The system of claim 8 wherein the first deployable lift device is inboard of the second deployable lift device. 11. The system of claim 8 wherein the first deployable lift device is outboard of the second deployable lift device. 12. An aircraft wing system, comprising: a wing having a leading edge and a trailing edge; a first deployable lift device having a first spanwise location, the first deployable lift device being movable relative to the wing from a stowed position to at least one first deployed position; a second deployable lift device having a second spanwise location different than the first, the second deployable lift device being movable relative to the wing from a stowed position to at least one second deployed position; drive means having link means operatively coupleable to both the first and the second deployable lift devices; and control means operatively coupled to the drive means, the control means having: a first configuration for which the link means is operatively coupled to the first deployable lift device and activation of at least a portion of the link means moves the first and second deployable lift devices as a unit; and a second configuration for which the link means is operatively coupled to the first deployable lift device and operatively decoupled from the second deployable lift device, and activation of at least a portion of the link means moves the first deployable lift device relative to the second deployable lift device, wherein the control means has a third configuration for which the link means is operatively coupled to the second deployable lift device and operatively decoupled from the first deployable lift device, and wherein activation of at least a portion of the link means moves the second deployable lift device relative to the first deployable lift device, and wherein the link means includes a drive shaft, and the drive means includes a first motor, a second motor, and a differential coupled among the drive shaft, the first deployable lift device, the second deployable lift device, the first motor and the second motor, and wherein the control means includes: a first brake operatively coupled to the differential and engaged to move the first and second deployable lift devices when the control means has the first configuration; a second brake operatively coupled to the second deployable lift device and engaged to at least resist motion of the second deployable lift device when the control means has the second configuration; and a third brake operatively coupled to the first deployable lift device and engaged to at least resist motion of the first deployable lift device when the control means has the third configuration; wherein the first motor is operatively coupled to the first and second deployable lift devices and the second motor is operatively decoupled from the first and second deployable lift devices when the control means has the first configuration; the second motor is operatively coupled to the first deployable lift device and the first motor is operatively decoupled from the first and second deployable lift devices when the control means has the second configuration; and the second motor is operatively coupled to the second deployable lift device and the first motor is operatively decoupled from the first and second deployable lift devices when the control means has the third configuration. 13. The system of claim 12 wherein the first and second deployable lift devices have a first range of motion when the control means has the first configuration, and wherein the first deployable lift device has a second range of motion less than the first range of motion when the control means has the second configuration. 14. The system of claim 12 wherein the link means includes a mechanical drive shaft. 15. The system of claim 12 wherein the first deployable lift device is inboard of the second deployable lift device. 16. The system of claim 12 wherein the first deployable lift device is outboard of the second deployable lift device.
Moelter Gunther (Ottobrunn DEX) Mueller Hermann (Munich DEX) Kunz Ruediger (Munich DEX), Apparatus for operating flap means secured to the wing of an aircraft.
Perin Robert (Pibrac FRX) Jourdan Pierre (Blagnac FRX) Pauly Bernard (Blagnac FRX), Arrowlike aircraft wing equipped with a high-lift system and with a pylon for suspending the engine.
Manthey Heinz (Hamburg DEX) Glimmann Hans (Horneburg DEX) Tyburski Gustav (Stade DEX) Schultz Holger (Hamburg DEX) Probst Arne (Hamburg DEX) Poppinga Georg (Halstenbeck DEX) Nocon Guenther (Buxtehude, Ceiling luggage compartment combination for the passenger cabin of an aircraft.
John Harold Caton ; Michael James Hobey ; John David Groeneveld ; Jack Howard Jacobs ; Robert Henry Wille ; Lawrence Otto. Brase, Jr., Control surface for an aircraft.
Griffin ; III John C. ; Gunn Peter D. ; Hayes James D., Method and apparatus for an improved flight management system providing for synchronization of control display units in.
Beyer, Kevin W.; Fox, Stephen J.; Lacy, Douglas S.; Sakurai, Seiya, Method and apparatus for controlling airflow with a leading edge device having a flexible flow surface.
Kubbat Wolfgang (Jugenheim DEX) Mensen Heinrich (Frankfurt am Main DEX) Below Christian (Berlin DEX) Kling Heribert (Frankfurt DEX) von Viebahn Harro (Darmstadt-Eberstadt DEX), Method and apparatus for displaying flight-management information.
Matthew T. Smith ; Gary L. Owen, Method and apparatus for interactively and automatically selecting, controlling and displaying parameters for an avionics electronic flight display system.
Gautier, Jean-Pierre; Peransin-Delage, Cecile, Process and control system for an aircraft control surface actuated by multiple hydraulic jacks and with modular power.
Moutet nee Layrisse Helene Denise (Massy FR) Pugibet Maurice J. (Paris FR) Scherchen Jean-Jacques (Yerres FR), Processes for the manufacture of fuel blocks containing a metallic powder and in the corresponding blocks.
Brogdon ; Jr. Glenn F. (14505 Hamowell St. Manassas VA 22110), Quick-release roller attachment for supporting a rope or hose and the like on an aerial ladder.
Capbern Patrick (Cornebarrieu FRX) Charieras Jrme (Toulouse FRX) Chaumel Pascal (Plaisance du Touch FRX), Rigid kruger nose for the leading edge of an aircraft wing.
Vijgen Paul M. H. W. (Hampton VA) Howard Floyd G. (Hampton VA) Bushnell Dennis M. (Wicomico VA) Holmes Bruce J. (Newport News VA), Serrated trailing edges for improving lift and drag characteristics of lifting surfaces.
Bruce D. Charles ; Ahmed A. Hassan ; Hormoz Tadghighi ; Ram D. JanakiRam, Tapered/segmented flaps for rotor blade-vortex interaction (BVI) noise and vibration reduction.
Hiroaki Kitamoto JP; Kaoru Hasegawa JP; Kenjiro Shimada JP, Valve apparatus for controlling hydraulic pressure for a clutch or a brake and method for controlling hydraulic pressure.
Proksch Hans-Jrg (Hagnau DEX) Welte Dieter (Markdorf DEX) Zimmer Herbert (Friedrichshafen DEX) Lotz ; deceased Michael (late of Immenstaad DEX by Carla Lotz ; ne Post ; Andreas Lotz ; heirs), Wing for short take-off and landing aircraft.
Lotz ; deceased Michael (late of Immenstaad DEX by Carla Lotz ne Post ; heir and Andreas Lotz ; heir) Vanino ; deceased Rdiger (late of Hagnau DEX H. L. I. M. Vanino ; heir) Khl Peter (Immenstaad DEX, Wing sections, in particular lift-wing sections for aircraft.
Lacy, Douglas S.; Beyer, Kevin W.; Brown, Stephen T.; Dees, Paul W.; Huynh, Neal V.; Kordel, Jan A.; Prow, Clayton A.; Sakurai, Seiya, Aircraft trailing edge devices, including devices with non-parallel motion paths, and associated methods.
Pachikara, Abraham J.; Moser, Matthew A.; Carpenter, Paul H.; Finn, Michael R.; Koch, Thomas S.; Bieniawski, Stefan R.; Whitehead, Brian T., Closed loop control of aircraft control surfaces.
Moser, Matthew A.; Gardner, Mark J.; Finn, Michael R.; Good, Mark S.; Malachowski, Adam P.; Thommen, Monica E.; Amorosi, Stephen R.; Onu, Dan, Leading edge variable camber system and method.
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