Method for optimum economy cruise speed in an aircraft
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
G08G-005/00
B64D-031/06
G05D-001/00
출원번호
US-0059046
(2016-03-02)
등록번호
US-10049586
(2018-08-14)
우선권정보
EP-15382093 (2015-03-04)
발명자
/ 주소
Gallo Olalla, Eduardo
출원인 / 주소
The Boeing Company
대리인 / 주소
Kunzler, PC
인용정보
피인용 횟수 :
0인용 특허 :
3
초록▼
Method for calculating an optimum economy cruise speed in an aircraft and its use is disclosed herein. The method includes receiving a plurality of flight parameters including a weight of the aircraft, an aircraft bearing and an atmospheric pressure and temperature, a wind speed and a wind bearing a
Method for calculating an optimum economy cruise speed in an aircraft and its use is disclosed herein. The method includes receiving a plurality of flight parameters including a weight of the aircraft, an aircraft bearing and an atmospheric pressure and temperature, a wind speed and a wind bearing at the altitude of the aircraft; calculating a cost index associated with the flight of the aircraft; calculating a weight coefficient of the aircraft, a cost index coefficient, a wind Mach number and an absolute value of a difference between the wind bearing and the aircraft bearing. Additionally, the method includes calculating an optimum Mach number of the aircraft, which provides the optimum economy cruise speed. The calculation of the optimum Mach number includes the weight coefficient, the cost index coefficient, the wind Mach number and the absolute value of the difference between the wind bearing and aircraft bearing.
대표청구항▼
1. A method for calculating an optimum economy cruise speed of an aircraft, the method comprising: receiving a plurality of flight parameters including at least a weight of the aircraft, an aircraft bearing, an atmospheric pressure, an atmospheric temperature, a wind speed, and a wind bearing at a f
1. A method for calculating an optimum economy cruise speed of an aircraft, the method comprising: receiving a plurality of flight parameters including at least a weight of the aircraft, an aircraft bearing, an atmospheric pressure, an atmospheric temperature, a wind speed, and a wind bearing at a flight altitude of the aircraft; calculating a cost index coefficient associated with a flight of the aircraft, the cost index coefficient based on at least a cost index, the atmospheric pressure, and the atmospheric temperature; calculating a weight coefficient of the aircraft based on at least the weight of the aircraft and the atmospheric pressure at the flight altitude of the aircraft; calculating a wind Mach number; calculating an absolute value of a difference between the wind bearing and the aircraft bearing; and calculating an optimum Mach number of the aircraft, which provides the optimum economy cruise speed, wherein the calculation of the optimum Mach number comprises the weight coefficient, the cost index coefficient, the wind Mach number and the absolute value of the difference between the wind bearing and the aircraft bearing; and sending the optimum Mach number of the aircraft to an aircraft guidance and control system and controlling an instant speed of the aircraft to the optimum economy cruise speed. 2. The method according to claim 1, wherein a fuel load of the aircraft is dynamically and continuously measured to calculate the weight of the aircraft. 3. The method according to claim 1, wherein the atmospheric pressure at the altitude of the aircraft is dynamically and continuously measured to calculate the altitude of the aircraft. 4. The method according to claim 1, wherein the calculation of the optimum Mach number further comprises considering a realistic drag polar that includes compressibility effects and fuel consumption dependencies with aircraft speed and aircraft thrust. 5. The method according to claim 4, wherein the calculation of the optimum Mach number further comprises determining an instantaneous optimum Mach number as a function of the weight coefficient, the cost index coefficient, the wind Mach number and the absolute value of the bearing difference between the wind and the aircraft path. 6. The method according to claim 1, wherein the method is dynamically and continuously carried out. 7. The method according to claim 1, wherein the cost index comprises a fixed cost index relating a fuel cost of the aircraft and an hourly cost of the aircraft. 8. The method according to claim 1, wherein the cost index coefficient is calculated as the ratio of the cost index divided by the product of the atmospheric pressure and the square root of the atmospheric temperature. 9. The method according to claim 8, wherein calculating the weight coefficient comprises division of the weight of the aircraft by the atmospheric pressure at the altitude of the aircraft. 10. The method according to claim 9, wherein calculating the wind Mach number comprises division of the wind speed by the speed of sound. 11. The method according to claim 1, further comprising sending the optimum Mach number of the aircraft as calculated to a ground trajectory predictor, wherein the ground trajectory predictor is configured to predict a trajectory of the aircraft at the optimum Mach number. 12. An aircraft, comprising: an engine, configured to generate thrust for the aircraft; a guidance and control system configured to control a speed of the aircraft by controlling the thrust generated by the engine; and a flight management system comprising a computer programmed to execute the operations of: receiving a plurality of flight parameters including at least a weight of the aircraft, an aircraft bearing, an atmospheric pressure, an atmospheric temperature, a wind speed, and a wind bearing at an altitude of the aircraft; calculating a cost index coefficient associated with a flight of the aircraft, the cost index coefficient based on at least a cost index, the atmospheric pressure, and the atmospheric temperature; calculating a weight coefficient of the aircraft based on at least a weight of the aircraft and the atmospheric pressure at the altitude of the aircraft; calculating a wind Mach number; calculating an absolute value of a difference between the wind bearing and the aircraft bearing; and calculating an optimum Mach number of the aircraft, which provides an optimum economy range cruise speed, wherein the calculation of the optimum Mach number comprises the weight coefficient, the cost index coefficient, the wind Mach number, and the absolute value of the difference between the wind bearing and the aircraft bearing; wherein the guidance and control system controls the speed of the aircraft to the optimum economy cruise speed. 13. The aircraft according to claim 12, wherein the calculation of the optimum Mach number further comprises considering a realistic drag polar that includes compressibility effects and fuel consumption dependencies with aircraft speed and aircraft thrust. 14. The aircraft according to claim 13, wherein the calculation of the optimum Mach number further comprises determining an instantaneous optimum Mach number as a function of the weight coefficient, the wind Mach number, and the absolute value of the bearing difference between the wind and the aircraft path. 15. The aircraft according to claim 12, wherein the computer of the flight management system dynamically and continuously executes the operations. 16. A flight management system of an aircraft, comprising a computer programmed to execute the operations of: receiving a plurality of flight parameters including at least a weight of the aircraft, an aircraft bearing, an atmospheric pressure, an atmospheric temperature, a wind speed, and a wind bearing at the altitude of the aircraft; calculating a cost index coefficient associated with a flight of the aircraft, the cost index coefficient based on at least a cost index, the atmospheric pressure, and the atmospheric temperature; calculating a weight coefficient of the aircraft based on at least a weight of the aircraft and the atmospheric pressure at the altitude of the aircraft; calculating a wind Mach number; calculating an absolute value of a difference between the wind bearing and the aircraft bearing; and calculating an optimum Mach number of the aircraft, which provides an optimum economy cruise speed, wherein the calculation of the optimum Mach number comprises the weight coefficient, the cost index coefficient, the wind Mach number, and the absolute value of the difference between the wind bearing and the aircraft bearing; wherein the flight management system further comprises a guidance and control system controlling an instant speed of the aircraft to the optimum economy cruise speed in response to the optimum Mach number of the aircraft. 17. The flight management system according to claim 16, wherein the calculation of the optimum Mach number further comprises considering a realistic drag polar that includes compressibility effects and fuel consumption dependencies with aircraft speed and aircraft thrust. 18. The flight management system according to claim 17, wherein the calculation of the optimum Mach number further comprises determining an instantaneous optimum Mach number as a function of the weight coefficient, the wind Mach number, and the absolute value of the bearing difference between the wind and the aircraft path. 19. The flight management system according to claim 16, wherein the computer dynamically and continuously executes the operations.
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이 특허에 인용된 특허 (3)
DeJonge Michael K. (Wyoming MI), Flight performance data computer system.
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