[특허]System and method for optimizing performance of an aircraft

The Boeing Company

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특허 상세정보

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내보내기 페이스북 공유 트위터 공유 카카오톡 공유

System and method for optimizing performance of an aircraft

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-003/38 B64C-013/16 B64C-009/16 B64C-013/04
출원번호	US-0034920 (2013-09-24)
등록번호	US-9359065 (2016-06-07)
발명자 / 주소	Moser, Matthew A. Finn, Michael R. Gardner, Mark J. Murphy, Robert M. Thoreen, Adam
출원인 / 주소	The Boeing Company
인용정보	피인용 횟수 : 0 인용 특허 : 22

초록

A system for optimizing performance of an aircraft may include a flight control computer for computing an optimum flap setting based on aircraft data. The system may further include a flap control system having a flap control device. The system may additionally include a flap actuation system coupled to the flap control system for positioning the trailing edge device at the optimum flap setting.

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1. A system for optimizing performance of an aircraft, comprising: a flight control computer configured to compute an optimum flap setting based on aircraft data;a flap control system having a flap control device for selecting one of multiple flap lever positions comprising non-designated flap lever positions and at least one designated flap lever position, the non-designated flap lever positions and the designated flap lever position each corresponding to a standard flap setting, the flap control device having a variable-trailing-edge-position switch being operative when the flap control device is in a designated flap lever position selected from a group consisting of a takeoff flaps position, a go-around flaps position, an approach flaps position, and a landing flaps position, the variable-trailing-edge-position switch allowing for fine tuning of the flap setting of a trailing edge device in real-time during flight within a range of flap deflection angles associated with the designated flap lever position to allow for selection of the optimum flap setting, the optimum flap setting being different than the standard flap setting for the designated flap lever position; anda flap actuation system coupled to the flap control system and being configured to position the trailing edge device at the optimum flap setting. 2. The system of claim 1, wherein the flight control computer is configured to determine an optimum thrust setting based on the aircraft data. 3. The system of claim 1, wherein: the variable-trailing-edge-position switch being non-operative when the flap control device is in a non-designated flap lever position. 4. The system of claim 1, wherein: the variable-trailing-edge-position switch is configured to change the flap setting such that the trailing edge device moves in flap deflection increments of no greater than approximately one degree of actual flap angle. 5. The system of claim 1, wherein the aircraft data includes at least one member of a group consisting of aircraft gross weight, aircraft center of gravity, and maximum takeoff thrust. 6. The system of claim 1, wherein the aircraft data includes at least one member of a group consisting of airport atmospheric data and airport parameters; the airport atmospheric data including at least one of outside air temperature, airport elevation, density altitude, pressure altitude, wind speed, and wind direction; andthe airport parameters including at least one of runway length, runway condition, and obstacle height. 7. An aircraft comprising: a wing having a trailing edge device mounted to a trailing edge;a system for optimizing a flap setting of the flap, comprising:a processor-based flight control computer configured to compute an optimum flap setting based on aircraft data;a flap control system having a flap control device for selecting one of multiple flap lever positions comprising non-designated flap lever positions and at least one designated flap lever position, the non-designated flap lever positions and the designated flap lever position each corresponding to a standard flap setting, the flap control device having a variable-trailing-edge-position switch allowing for fine tuning of the flap setting of the trailing edge device in real-time during flight within a range of flap deflection angles associated with the designated flap lever position to allow for selection of the optimum flap setting, the optimum flap setting being different than the standard flap setting for the designated flap lever position, the variable-trailing-edge-position switch being operative when the flap control device is in a designated flap lever position selected from a group consisting of a takeoff flaps position, a go-around flaps position, an approach flaps position, and a landing flaps position; anda flap actuation system coupled to the flap control system and being configured to position the trailing edge device at the optimum flap setting. 8. The aircraft of claim 7, wherein the flight control computer is configured to determine an optimum thrust setting based on the aircraft data. 9. A method of optimizing performance of an aircraft, comprising: determining an optimum flap setting based on aircraft data;selecting, using a flap control device, one of multiple flap lever positions comprising non-designated flap lever positions and at least one designated flap lever position, the non-designated flap lever positions and the designated flap lever position each corresponding to a standard flap setting;fine tuning in real-time during flight, using a variable-trailing-edge-position switch, the flap setting of a trailing edge device within a range of flap deflection angles associated with the designated flap lever position to select the optimum flap setting, the optimum flap setting being different than the standard flap setting for the designated flap lever position, the variable-trailing-edge-position switch being operative when the flap control device is in a designated flap lever position selected from a group consisting of a takeoff flaps position, a go-around flaps position, an approach flaps position, and a landing flaps position; andpositioning the trailing edge device at the optimum flap setting. 10. The method of claim 9, further comprising: determining an optimum thrust setting based on the aircraft data. 11. The method of claim 9, wherein the steps of selecting, using the flap control device, one of multiple flap lever positions and fine tuning, using the variable-trailing-edge-position switch, the flap setting comprise: moving a flap control lever to a designated flap lever position at which the variable-trailing-edge-position switch is operative; andmoving the switch position to the optimum flap setting after positioning the flap control lever at the designated flap lever position. 12. The method of claim 9, wherein: the variable-trailing-edge-position switch is non-operative when the flap control device is in a non-designated flap lever position. 13. The method of claim 11, further comprising: changing, using the variable-trailing-edge-position switch, the flap setting in a manner such that the trailing edge device moves in flap deflection increments of no greater than approximately one degree of actual flap angle. 14. The method of claim 9, wherein the aircraft data includes at least one member of a group consisting of aircraft gross weight, and aircraft center of gravity. 15. The method of claim 9, wherein the aircraft data includes at least one member of a group consisting of outside air temperature, airport elevation, density altitude, pressure altitude, wind speed, wind direction, runway length, runway condition, and obstacle height. 16. The aircraft of claim 7, wherein: the variable-trailing-edge-position switch is non-operative when the flap control device is in a non-designated flap lever position. 17. The aircraft of claim 7, wherein: the variable-trailing-edge-position switch is configured to change the flap setting such that the trailing edge device moves in flap deflection increments of no greater than approximately one degree of actual flap angle. 18. The aircraft of claim 7, wherein: the aircraft data includes at least one member of a group consisting of aircraft gross weight, and aircraft center of gravity. 19. The aircraft of claim 7, wherein: the aircraft data includes at least one member of a group consisting of airport atmospheric data and airport parameters;the airport atmospheric data including at least one of outside air temperature, airport elevation, density altitude, pressure altitude, wind speed, and wind direction; andthe airport parameters including at least one of runway length, runway condition, and obstacle height. 20. The aircraft of claim 7, wherein: the trailing edge device is one of a plain flap, a single-slotted flap, and a multi-slotted Fowler flap.

인용문헌 (22)

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System and method for optimizing performance of an aircraft

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System and method for optimizing performance of an aircraft

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인용문헌 (22)

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