Method and apparatus for optimizing a load in a flight control system while an aircraft is on the ground
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-013/02
B64C-013/16
B64C-013/50
B64D-045/00
G05D-001/00
출원번호
US-0237731
(2011-09-20)
등록번호
US-9708054
(2017-07-18)
발명자
/ 주소
Huynh, Neal Van
Andersen, Peter James
출원인 / 주소
THE BOEING COMPANY
대리인 / 주소
Yee & Associates, P.C.
인용정보
피인용 횟수 :
0인용 특허 :
2
초록▼
A method, apparatus, and computer program product for managing movement of a flight control surface on an aircraft. A control signal is received to move the flight control surface to a position. Travel in a number of actuators in a plurality of actuators coupled to the flight control surface is limi
A method, apparatus, and computer program product for managing movement of a flight control surface on an aircraft. A control signal is received to move the flight control surface to a position. Travel in a number of actuators in a plurality of actuators coupled to the flight control surface is limited to an amount that reduces a load on the number of actuators in the plurality of actuators in response to receiving the control signal while the aircraft is on the ground and the speed of the aircraft is less than a threshold.
대표청구항▼
1. A method for managing movement of a flight control surface on an aircraft, the method comprising: receiving a control signal, in a computer, to move the flight control surface to an end stop position associated with the flight control surface;using a number of actuators in a plurality of actuator
1. A method for managing movement of a flight control surface on an aircraft, the method comprising: receiving a control signal, in a computer, to move the flight control surface to an end stop position associated with the flight control surface;using a number of actuators in a plurality of actuators coupled to the flight control surface to move the flight control surface; andlimiting a travel towards the end stop position, using the computer and responsive to receiving the control signal while the aircraft is on a ground and a speed of the aircraft is less than a threshold, in the number of actuators to an amount that reduces at least one of a bottoming load and a mismatched load on the number of actuators in the plurality of actuators. 2. The method of claim 1, wherein limiting the travel further comprises limiting at least one of a travel rate and a travel distance for the number of actuators in the plurality of actuators. 3. The method of claim 1, wherein limiting the travel further comprises limiting the travel to around 90 percent of a full travel distance to reduce at least one of the bottoming load and the mismatched load on the number of actuators in the plurality of actuators. 4. The method of claim 1, wherein limiting the travel further comprises limiting a travel rate, using the computer, in the number of actuators in the plurality of actuators to a travel rate of around 50 percent of a full travel rate to reduce at least one of the bottoming load and the mismatched load on the number of actuators in the plurality of actuators. 5. The method of claim 1, wherein limiting the travel further comprises limiting a travel rate, using the computer, of the number of actuators in the plurality of actuators to around 50 percent of a full travel rate and a travel distance for the number of actuators in the plurality of actuators to around 90 percent of a full travel distance to reduce at least one of the bottoming load and the mismatched load on an actuator of the number of actuators or the plurality of actuators. 6. The method of claim 1, wherein the limiting step comprises: responsive to receiving the control signal while the aircraft is on the ground, selecting a portion of the plurality of actuators from actuators that were unused in a previous flight to form the number of actuators; andresponsive to receiving the control signal while the aircraft is on the ground, operating only the number of actuators to move the flight control surface. 7. The method of claim 1, wherein the receiving step comprises: receiving the control signal to move the flight control surface to the position in response to a manipulation of a rudder pedal in the aircraft. 8. The method of claim 1, wherein the method is a process executed by a data processing system. 9. The method of claim 1, wherein the aircraft is selected from one of an airplane and a helicopter. 10. The method of claim 1, wherein the flight control surface is selected from one of a rudder, a flap, an aileron, a spoiler, an elevator, and an airbrake. 11. An apparatus comprising: a computer configured to: receive a control signal to move a flight control surface on an aircraft to an end stop position associated with the flight control surface;use a number of actuators in a plurality of actuators coupled to the flight control surface to move the flight control surface; andlimit travel towards the end stop position in the number of actuators to an amount that reduces at least one of a bottoming load and a mismatched load on the number of actuators in the plurality of actuators while the aircraft is on a ground and a speed of the aircraft is less than a threshold. 12. The apparatus of claim 11 further comprising: the plurality of actuators; andthe flight control surface. 13. The apparatus of claim 11, further comprising the computer configured to limit the travel by limiting at least one of a travel rate and a travel distance for the number of actuators in the plurality of actuators. 14. The apparatus of claim 11, further comprising the computer being configured to select a portion of the plurality of actuators from actuators that were unused in a previous flight control check to form the number of actuators, and operating only the number of actuators to move the flight control surface. 15. A non-transitory computer readable storage medium storing a computer program product for managing movement of a flight control surface on an aircraft, the computer program product comprising: a program code, that when executed by a processor, causing the processor to: receive a control signal to move the flight control surface to an end stop position associated with the flight control surface;use a number of actuators in a plurality of actuators coupled to the flight control surface to move the flight control surface; and,responsive to receiving the control signal while the aircraft is on a ground and a speed of the aircraft is less than a threshold, limit travel towards the end stop position in the number of actuators to an amount that reduces at least one of a bottoming load and a mismatched load on the plurality of actuators. 16. The non-transitory computer readable storage medium of claim 15, further comprising the program code causing the processor to limit the travel in the number of actuators in the plurality of actuators to the amount that reduces at least one of the bottoming load and the mismatched load on the number of actuators in the plurality of actuators by limiting at least one of a travel rate and a travel distance for the number of actuators in the plurality of actuators. 17. The non-transitory computer readable storage medium of claim 15, further comprising the program code causing the processor to limit the travel of all of the plurality of actuators to around 90 percent of a full travel distance to reduce at least one of the bottoming load and the mismatched load on the plurality of actuators. 18. The non-transitory computer readable storage medium of claim 15, further comprising the program code causing the processor to limit the travel by limiting a travel rate in all of the plurality of actuators to a travel rate of around 50 percent of a full travel rate to reduce at least one of the bottoming load or the mismatched load on the plurality of actuators. 19. The non-transitory computer readable storage medium of claim 15, further comprising the program code causing the processor to select a portion of the plurality of actuators from actuators that were unused in a previous flight to form the number of actuators, and to operate only the number of actuators to move the flight control surface.
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이 특허에 인용된 특허 (2)
Bilange Thierry (Tournefeuille FRX) Le Tron Xavier (Toulouse FRX), Electrical flight control system for an airplane, with attitude protection on takeoff.
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