Adjustment of wings for variable camber for optimum take-off and landing
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
G05D-001/12
B64C-013/00
B64C-021/00
B64C-009/20
B64C-009/24
B64C-013/16
출원번호
US-0968383
(2010-12-15)
등록번호
US-9327824
(2016-05-03)
발명자
/ 주소
Good, Mark
Johnson, Paul
출원인 / 주소
The Boeing Company
대리인 / 주소
Ostrager Chong Flaherty & Broitman P.C.
인용정보
피인용 횟수 :
1인용 특허 :
8
초록▼
An aircraft wing system for differentially adjusting a first deployable lift device and a second deployable lift device on a wing during take-off and landing, the system having a controller, which is programmed to determine desired positions for the first and second deployable lift devices, based on
An aircraft wing system for differentially adjusting a first deployable lift device and a second deployable lift device on a wing during take-off and landing, the system having a controller, which is programmed to determine desired positions for the first and second deployable lift devices, based on a desired position signal, and to activate high and low horsepower motors to move the first deployable lift devices to desired positions. The system has a controller which determines an adjustment amount for each motor, based on the system architecture.
대표청구항▼
1. A method for differentially adjusting a first deployable lift device on an aircraft wing and a second deployable lift device on the aircraft wing during takeoff and landing, wherein said first deployable lift device and said second deployable lift device are coupled to a single power drive link c
1. A method for differentially adjusting a first deployable lift device on an aircraft wing and a second deployable lift device on the aircraft wing during takeoff and landing, wherein said first deployable lift device and said second deployable lift device are coupled to a single power drive link coupled to a controller, said method comprising: determining in the controller a first desired position for said first deployable lift device on the aircraft wing and a second desired position for said second deployable lift device on the aircraft wing, based on a desired position signal during takeoff and landing;receiving in the controller a first current position of said first deployable lift device;determining in the controller a second current position of said second deployable lift device by subtracting the first current position of said first deployable lift device from a current differential position;activating a first motor to move said first deployable lift device by a first total movement amount, said first total movement amount being determined by subtracting the first current position of said first deployable lift device from said first desired position;determining in the controller a second total movement amount for said second deployable lift device by subtracting the second current position of said second deployable lift device from said second desired position;determining in the controller a first differential movement amount by subtracting said first total movement amount from said second total movement amount;activating a second motor to move said second deployable lift device by said first differential movement amount;determining a third total movement amount for a third deployable lift device on the aircraft wing by subtracting a third current position of said third deployable lift device from a third desired position for said third deployable lift device;determining a second differential movement amount for said third deployable lift device by subtracting said second total movement amount from said third total movement amount; andactivating a third motor to move said third deployable lift device by said second differential movement amount. 2. The method of claim 1, wherein: said first desired position and said second desired position are further determined based on an aircraft weight, altitude and airspeed. 3. The method of claim 1, further comprising: engaging a first differential brake prior to activating said first motor;disengaging said first differential brake after moving said first deployable lift device is complete; andactivating said second motor. 4. The method of claim 1, further comprising: determining said second current position by adding said first current position to a first differential position. 5. The method of claim 1, further comprising: determining said third current position by adding said second current position to a second differential position. 6. The method of claim 1, further comprising: engaging a second differential brake prior to activating said second motor;disengaging said second differential brake after moving said second deployable lift device is complete; andactivating said third motor. 7. An aircraft wing system for differentially adjusting a first deployable lift device on an aircraft wing and a second deployable lift device on the aircraft wing during takeoff and landing, said system comprising: a first deployable lift device on the aircraft wing;a second deployable lift device on the aircraft wing, wherein said first deployable lift device and said second deployable lift device are coupled to a single power drive link;a high horsepower motor providing power to said power drive link;a first low horsepower motor;a first differential configured to receive power from said drive link and said first low horsepower motor, and to provide power to said second deployable lift device; anda controller programmed to:determine a first desired position for said first deployable lift device and a second desired position for said second deployable lift device, based on a desired position signal during takeoff and landing;activate said high horsepower motor to move said first deployable lift device by a first total movement amount, said first total movement amount being determined by subtracting a first current position of said first deployable lift device from said first desired position;determine a second total movement amount for said second deployable lift device by subtracting a second current position of said second deployable lift device from said second desired position;determine a first differential movement amount by subtracting said first total movement amount from said second total movement amount;activate said first low horsepower motor to move said second deployable lift device by said first differential movement amount;determine a third total movement amount for said third deployable lift device by subtracting a third current position of said third deployable lift device from a third desired position;determine a second differential movement amount for said third deployable lift device by subtracting said second total movement amount from said third total movement amount; andactivate a second low horsepower motor to move said third deployable lift device by said second differential movement amount. 8. The system of claim 7, wherein: said controller is programmed to determine said first desired position and said second desired position based on an aircraft weight, altitude and airspeed. 9. The system of claim 7, wherein: said controller is further programmed to:engage a first differential brake prior to activating said high horsepower motor;disengage said first differential brake after moving said first deployable lift device is complete; andactivate said first low horsepower motor. 10. The system of claim 7, wherein: said controller is further programmed to determine a second current position by adding said first current position to a first differential position. 11. The system of claim 7, wherein: said controller is further programmed to:determine said third current position by adding said second current position to a second differential position. 12. The system of claim 7, wherein: said controller is further programmed to:engage a second differential brake prior to activating said first low horsepower motor;disengage said second differential brake and engage said first differential brake after moving said second deployable lift device is complete; andactivate said second low horsepower motor. 13. An aircraft employing an aircraft wing system for differentially adjusting a first deployable lift device, a second deployable lift device and a third deployable lift device during takeoff and landing, said aircraft comprising: an aircraft body;a wing having a first deployable lift device, a second deployable lift device and a third deployable lift device wherein said first deployable lift device on the wing and said second deployable lift device on the wing are coupled to a single power drive link;a high horsepower motor providing power to said power drive link;a first low horsepower motor;a first differential control device configured to receive power from said drive link and said first low horsepower motor, and to provide power to said second deployable lift device; anda controller programmed to:determine a first desired position for said first deployable lift device on the wing and a second desired position for said second deployable lift device on the wing, based on a desired position signal during takeoff and landing;activate said high horsepower motor to move said first deployable lift device by a first total movement amount, said first total movement amount being determined by subtracting a first current position of said first deployable lift device from said first desired position;determine a second total movement amount for said second deployable lift device by subtracting a second current position of said second deployable lift device from said second desired position;determine a first differential movement amount by subtracting said first total movement amount from said second total movement amount;activate said first low horsepower motor to move said second deployable lift device by said first differential movement amount;determine a third total movement amount for said third deployable lift device by subtracting a third current position of said third deployable lift device from a third desired position;determine a second differential movement amount for said third deployable lift device by subtracting said second total movement amount from said third total movement amount; andactivate a second low horsepower motor to move said third deployable lift device by said second differential movement amount. 14. The system of claim 13, wherein: said controller is programmed to determine said first desired position and said second desired position based on an aircraft weight, altitude and airspeed. 15. The system of claim 13, wherein: said controller is further programmed to:engage a first differential brake prior to activating said high horsepower motor;disengage said first differential brake after moving said first deployable lift device is complete; andactivate said first low horsepower motor. 16. The system of claim 13, wherein: said controller is further programmed to determine a second current position by adding said first current position to a first differential position. 17. The system of claim 13, wherein: said controller is further programmed to:determine said third current position by adding said second current position to a second differential position.
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이 특허에 인용된 특허 (8)
Good,Mark S.; Viigen,Paul M.; Gitnes,Seth E.; Thomas,Glynn Michael, Aircraft wing systems for providing differential motion to deployable lift devices.
Onu, Dan; Winter, John D.; Carr, Candy L.; Vijgen, Paul M.; Emch, Gary A.; Renzelmann, Michael E., Dynamic adjustment of wing surfaces for variable camber.
Good, Mark S.; Vijgen, Paul M.; Gitnes, Seth E.; Thomas, Glynn Michael, Systems and methods for providing differential motion to wing high lift device.
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