Method, system, and computer program product for performance monitored aircraft rejected takeoff braking
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-025/42
B60T-008/17
출원번호
UP-0642126
(2006-12-20)
등록번호
US-7720579
(2010-06-10)
발명자
/ 주소
Goodman, William L.
Peck, Andrew J.
Imrich, Thomas
출원인 / 주소
The Boeing Company
대리인 / 주소
Toler Law Group
인용정보
피인용 횟수 :
7인용 특허 :
6
초록▼
In exemplary embodiments, braking of an airplane is controlled during a rejected takeoff. A rejected takeoff of an airplane from a runway is initiated. Position of the airplane is determined, such as by inputting aircraft position from a global positioning system. Distance remaining on the runway is
In exemplary embodiments, braking of an airplane is controlled during a rejected takeoff. A rejected takeoff of an airplane from a runway is initiated. Position of the airplane is determined, such as by inputting aircraft position from a global positioning system. Distance remaining on the runway is determined. Deceleration to stop the aircraft in the determined distance remaining on the runway is calculated, and the calculated deceleration is provided to an autobraking system of the airplane. When the aircraft can not be stopped in the determined distance remaining on the runway, a predetermined deceleration that correlates to maximum braking may be provided to the aircraft's autobraking system. The calculated deceleration may be provided to the autobraking system until a pilot takes command of the aircraft's brakes or the aircraft has stopped.
대표청구항▼
What is claimed is: 1. A method of controlling braking of an aircraft during a rejected takeoff, the method comprising: initiating a rejected takeoff of an aircraft from a runway; determining a position of the aircraft; determining a distance remaining on the runway; calculating a deceleration to s
What is claimed is: 1. A method of controlling braking of an aircraft during a rejected takeoff, the method comprising: initiating a rejected takeoff of an aircraft from a runway; determining a position of the aircraft; determining a distance remaining on the runway; calculating a deceleration to stop the aircraft in the distance remaining on the runway; when the aircraft can be stopped by an autobraking system of the aircraft in the distance remaining on the runway, providing a signal directing the deceleration to be applied by the autobraking system; and when the aircraft cannot be stopped by the autobraking system in the distance remaining on the runway, causing the autobraking system to apply a maximum braking. 2. The method of claim 1, further comprising applying braking to achieve the deceleration when the aircraft can be stopped by the autobraking system in the distance remaining on the runway. 3. The method of claim 1, further comprising applying the maximum braking when the aircraft cannot be stopped by the autobraking system in the distance remaining on the runway. 4. The method of claim 1, further comprising: determining a distance in which the aircraft can be stopped by the autobraking system using up to the maximum braking; and determining whether the aircraft can be stopped in the distance remaining on the runway by comparing the distance in which the aircraft can be stopped with the distance remaining on the runway. 5. The method of claim 4, wherein determining the distance in which the aircraft can be stopped by the autobraking system using up to the maximum braking is based on at least one of: airframe characteristics of the aircraft; and environmental factors. 6. The method of claim 1, wherein determining the position of the aircraft includes inputting the position of the aircraft from a global positioning system. 7. The method of claim 1, wherein the deceleration is provided to the autobraking system until occurrence of an event selected from a pilot taking command of brakes and the aircraft stopping. 8. The method of claim 1, further comprising displaying braking performance. 9. The method of claim 1, wherein the signal directing the deceleration to be applied indicates a brake pressure to be applied by the autobraking system. 10. A system for controlling braking of an aircraft during a rejected takeoff; the system comprising: a first input interface configured to receive a rejected takeoff signal indicative of initiation of a rejected takeoff of an aircraft from a runway; a second input interface configured to receive a position signal indicative of a position of the aircraft on the runway; a processor including: a first component configured to determine a distance remaining on the runway; a second component configured to calculate a deceleration to stop the aircraft in the distance remaining on the runway; a third component configured to determine whether the aircraft can be stopped by an autobraking control unit of the aircraft in the distance remaining on the runway; and an output interface configured to provide the deceleration to the autobraking control unit, and to provide a signal to the autobraking control unit, wherein: when the aircraft can be stopped by the autobraking control unit in the distance remaining on the runway, the signal causes the autobraking control unit to apply the deceleration to stop the aircraft in the distance remaining on the runway; and when the aircraft cannot be stopped by the autobraking control unit in the distance remaining on the runway, the signal causes the autobraking control unit to apply a maximum braking. 11. The system of claim 10, wherein: the third component is further configured to calculate a distance in which the aircraft can be stopped by the autobraking control unit using up to the maximum braking; and the third component is further configured to compare the distance in which the aircraft can be stopped with the distance remaining on the runway to determine whether the aircraft can be stopped in the distance remaining on the runway. 12. The system of claim 11, wherein determining the distance in which the aircraft can be stopped by the autobraking control unit using up to the maximum braking is based on at least one of: airframe characteristics of the aircraft; and environmental factors. 13. The system of claim 10, wherein the second input interface is further configured to receive the position signal from a global positioning system. 14. The system of claim 10, wherein the first and second components of the processor are further configured to determine the distance remaining on the runway and to calculate the deceleration, respectively, until occurrence of an event selected from a pilot taking command of brakes and the aircraft stopping. 15. The system of claim 10, further comprising a display configured to display braking performance. 16. The system of claim 10, wherein the signal provided to the autobraking control unit indicates a brake pressure to be applied by the autobraking control unit. 17. A computer-readable storage medium storing instructions executable by a computer system to control braking of an aircraft during a rejected takeoff, the computer-readable storage medium storing instructions to: determine a position of the aircraft; determine a distance remaining on a runway; determine whether the aircraft can be stopped by an autobraking system of the aircraft in the distance remaining on the runway using up to a maximum braking; when the aircraft can be stopped by the autobraking system in the distance remaining on the runway, calculate a deceleration to be applied by the autobraking system to stop the aircraft in the distance remaining on the runway during a rejected takeoff from the runway; and when the aircraft cannot be stopped by the autobraking system in the distance remaining on the runway, direct the autobraking system to apply the maximum braking. 18. The computer-readable storage medium of claim 17, further comprising instructions to: calculate a distance in which the aircraft can be stopped by the autobraking system using up to the maximum braking; and determine whether the distance in which the aircraft can be stopped by the autobraking system is not more than the distance remaining on the runway. 19. The computer-readable medium of claim 18, wherein calculating the distance in which the aircraft can be stopped by the autobraking system using up to the maximum braking is based on at least one of: airframe characteristics of the aircraft; and environmental factors. 20. The computer-readable medium of claim 19, wherein the airframe characteristics include one or more of a configuration of flaps, flaperons, and other highlight devices. 21. The computer-readable medium of claim 19, wherein the environmental factors include one or more of runway slope, surface type, friction measurements provided by one of aircraft sensors and ground sensors, braking effectiveness reports, and atmospheric conditions. 22. The computer-readable storage medium of claim 17, wherein data generated by a global positioning system is used to determine the position of the aircraft. 23. The computer-readable storage medium of claim 17, further comprising instructions to determine the distance remaining on the runway and to calculate the deceleration, respectively, until occurrence of an event selected from a pilot taking command of brakes and the aircraft stopping. 24. The computer-readable storage medium of claim 17, further comprising instructions to cause brake performance to be displayed. 25. A system configured to brake an aircraft during a rejected takeoff, the system comprising: a first input interface configured to receive a rejected takeoff signal indicative of initiation of a rejected takeoff of an aircraft from a runway; a second input interface configured to receive a position signal indicative of a position of an aircraft on the runway; a processor including: a first component configured to determine a distance remaining on the runway; a second component configured to calculate deceleration to stop the aircraft in the distance remaining on the runway; and a third component configured to determine whether the aircraft can be stopped in the distance remaining on the runway by using up to a maximum braking; and an aircraft autobraking system configured to cause braking to be applied to aircraft brakes up to the maximum braking, wherein: when the aircraft can be stopped in the distance remaining on the runway, to apply the aircraft autobraking system according to the deceleration; and when the aircraft cannot be stopped in the distance remaining on the runway, to apply the maximum braking. 26. The system of claim 25, wherein the third component is further configured to calculate a distance in which the aircraft can be stopped by the aircraft autobraking system using up to the maximum braking and to compare the distance in which the aircraft can be stopped to the distance remaining on the runway; and the third component is further configured to determine when the aircraft can be stopped by the aircraft autobraking system in the distance remaining on the runway by determining when the distance in which the aircraft can be stopped is not more than the distance remaining on the runway. 27. The system of claim 26, wherein the third component is configured to calculate the distance in which the aircraft can be stopped by the aircraft autobraking system using up to the maximum braking using at least one of: airframe characteristics of the aircraft including one or more of a configuration of flaps, flaperons, and other highlight devices; and environmental factors including one or more of runway slope, surface type, friction measurements provided by one of aircraft sensors and ground sensors, braking effectiveness reports, and atmospheric conditions. 28. The system of claim 25, wherein the second input interface is further configured to receive the position signal from a global positioning system. 29. The system of claim 25, wherein the first and second components of the processor are further configured to determine the distance remaining on the runway and to calculate the deceleration, respectively, until occurrence of an event selected from a pilot taking command of brakes and the aircraft stopping. 30. The system of claim 25, further comprising a display configured to display braking performance. 31. The system of claim 25, wherein the processor includes a portion of one of a flight management computer and a flight management system. 32. An aircraft comprising: a fuselage; a pair of wings; at least one engine; landing gear including a nose gear and at least two main landing gear; and a system for braking the aircraft during a rejected takeoff from a runway, the system including: a first input interface configured to receive a rejected takeoff signal indicative of initiation of the rejected takeoff of the aircraft from the runway; a second input interface configured to receive a position signal indicative of a position of the aircraft on the runway; a processor including: a first component configured to determine distance remaining on the runway; a second component configured to calculate deceleration to stop the aircraft in the distance remaining on the runway; a third component configured to determine whether the aircraft can be stopped in the distance remaining on the runway by using up to a maximum braking; and an aircraft autobraking system configured to cause braking to be applied to aircraft brakes up to the maximum braking, wherein: when the aircraft can be stopped in the distance remaining on the runway, to apply the aircraft autobraking system according to the deceleration; and when the aircraft cannot be stopped in the distance remaining on the runway, to apply the maximum braking. 33. The aircraft of claim 32, wherein: the third component is further configured to calculate a distance in which the aircraft can be stopped by the aircraft autobraking system using up to the maximum braking and to compare the distance in which the aircraft can be stopped with the distance remaining on the runway; and the third component is further configured to determine when the aircraft can be stopped by the aircraft autobraking system in the distance remaining on the runway by determining when the distance in which the aircraft can be stopped is not more than the distance remaining on the runway. 34. The aircraft of claim 33, wherein the third component is configured to calculate the distance in which the aircraft can be stopped by the aircraft autobraking system using up to the maximum braking using at least one of: airframe characteristics of the aircraft including one or more of a configuration of flaps, flaperons, and other highlight devices; and environmental factors including one or more of runway slope, surface type, friction measurements provided by one of aircraft sensors and ground sensors, braking effectiveness reports, and atmospheric conditions. 35. The aircraft of claim 32, wherein the second input interface is further configured to receive the position signal from a global positioning system. 36. The aircraft of claim 32, wherein the first and second components of the processor are further configured to determine the distance remaining on the runway and to calculate the deceleration, respectively, until occurrence of an event selected from a pilot taking command of brakes and the aircraft stopping. 37. The aircraft of claim 32, wherein the system further includes a display configured to display braking performance.
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이 특허에 인용된 특허 (6)
DeVlieg Garrett H. ; Mackness Robert F. ; Yamamoto David T., Aircraft stop-to-position autobrake control system.
Michal, Benedicte; Pitard, Fabien; Demortier, Jean-Pierre; Charbonnier, Christine; Lacaze, Isabelle; Marchand, Gael; Le Duigou, Christine; Cayrou, Jerome; Blondin, Vincent; Lemoult, Frederic, Process for verifying the coherence between aircraft take-off parameters and an available runway length.
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