Robust systems and methods for improving passenger jet aircraft fuel economy
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
G06F-007/00
G06F-011/30
G07C-005/00
G07C-005/08
B64D-045/00
출원번호
US-0576988
(2014-12-19)
등록번호
US-9311759
(2016-04-12)
발명자
/ 주소
Shelley, Shawn
Collins, Kevin
Molnar, George A.
Lovas, Steve
Gockowski, III, Joseph E.
출원인 / 주소
Alaska Airlines, Inc.
대리인 / 주소
Klarquist Sparkman, LLP
인용정보
피인용 횟수 :
0인용 특허 :
11
초록▼
A method for improving fuel economy on a passenger jet aircraft comprises automatically receiving a communication from the aircraft to a ground station comprising at least one subsystem operating parameter measured during the current flight, detecting whether the operating parameter meets predetermi
A method for improving fuel economy on a passenger jet aircraft comprises automatically receiving a communication from the aircraft to a ground station comprising at least one subsystem operating parameter measured during the current flight, detecting whether the operating parameter meets predetermined criteria and, if the criteria are met, automatically sending a communication to indicate the aircraft's status for a next flight. If the criteria are not met, a status of the aircraft is automatically changed and a communication is sent. Other methods and systems are also described.
대표청구항▼
1. A method for improving fuel economy on a passenger jet aircraft implemented on one or more processors of one or more networked computers, comprising: receiving a communication at a networked computer comprising at least an exhaust gas temperature value for an auxiliary power unit measured while t
1. A method for improving fuel economy on a passenger jet aircraft implemented on one or more processors of one or more networked computers, comprising: receiving a communication at a networked computer comprising at least an exhaust gas temperature value for an auxiliary power unit measured while the auxiliary power unit is operating during a current flight of the aircraft and previously communicated via an aircraft to ground station communications link transmission;automatically detecting, using a networked computer, whether the exhaust gas temperature value exceeds at least one threshold temperature;wherein, if the exhaust gas temperature does not exceed at least one threshold temperature, then using a networked computer to automatically set the aircraft's future flight status to operating the auxiliary power unit on demand and to automatically send a communication to indicate the aircraft's future flight status, andwherein, if the exhaust gas temperature exceeds at least one threshold temperature, then using a networked computer to automatically set the aircraft's future flight status to operating the auxiliary power unit continuously and to automatically send a communication to indicate the aircraft's future flight status; andautomatically updating a database, using a networked computer, to reflect the aircraft's future flight status. 2. The method of claim 1, further comprising coordinating completion of any maintenance on the auxiliary power unit to automatically trigger resumption of a programmed maintenance routine. 3. The method of claim 1, further comprising accounting for the aircraft's future flight status in calculations of a fuel load required for the future flight. 4. The method of claim 1, wherein the at least one threshold temperature is a first threshold temperature and the communication is a first alert, and further comprising detecting whether the exhaust gas temperature value meets or exceeds a second threshold temperature higher than the first threshold temperature, wherein if the second temperature threshold is met or exceeded, then a second alert is communicated. 5. The method of claim 1, wherein if the exhaust gas temperature value exceeds a first threshold temperature but does not exceed a second threshold temperature, automatically setting the aircraft's future flight status to a watch-listed status, and sending a communication regarding the aircraft's watch-listed status to at least a power plant engineer responsible for the aircraft. 6. The method of claim 1, wherein if the exhaust gas temperature value does not exceed at least one threshold temperature, then updating a database to indicate that the aircraft's status is unchanged. 7. The method of claim 1, further comprising monitoring the communications link between the aircraft and the ground station to determine if a communications outage has occurred, and wherein if no exhaust gas temperature value is received after a predetermined time period has elapsed, then changing the aircraft's status for the next flight to operating the auxiliary power unit continuously. 8. The method of claim 1, wherein receiving a communication comprises receiving a communication specifying that the auxiliary power unit failed to start during the current flight, further comprising determining whether the auxiliary power unit operates when the aircraft is on the ground, and, if so, updating the aircraft's status for the next flight to operating the auxiliary power unit continuously. 9. The method of claim 1, further comprising determining if the aircraft to ground station communications link is exhibiting an outage, and if so, initiating a troubleshooting operation to troubleshoot the communications link. 10. The method of claim 9, wherein if any outage in the communications link lasts longer than a predetermined time, then seeking confirmation of the outage, and wherein if the outage is confirmed, then updating the status of the aircraft and other affected aircraft that use the same communications link to a no extended flight status. 11. The method of claim 1, wherein the exhaust gas temperature value is measured while the aircraft is undergoing a cold soak start test. 12. The method of claim 11, wherein if at least one of an in-flight auxiliary power unit start or the cold soak start test is unsuccessful, then a communication is sent and the system is updated. 13. The method of claim 1, further comprising conducting a test to determine if the auxiliary power unit operates normally on the ground. 14. A computer-implemented aircraft maintenance management system for a fleet of aircraft, comprising: one or more processors associated with a plurality of networked computers;memory linked to the one or more processors, at least one memory location having stored aircraft status information for multiple extended operations aircraft; andat least one display linked to at least one of the controllers processors and at least one of the memory elements;wherein the memory has stored instructions to cause the one or more processors to receive a predetermined subset of routine data transmitted via a communications link from an aircraft in current operation to a ground station, to control setting an extended flight eligibility status for a future flight of the aircraft in current operation based on comparing a current exhaust gas temperature value of the aircraft's auxiliary power unit as received in the routine data to predetermined criteria, to control sending communications to multiple recipients, to update records stored in the memory elements, and to display messages regarding at least the status of the aircraft in operation, the status of other aircraft in the fleet or the status of the communications link. 15. The system of claim 14, wherein, for the aircraft in current operation, the controller sets the status of the aircraft for a future extended operations flight to allowing operation of an auxiliary power unit on an on demand basis or requiring operation of the auxiliary power unit continuously. 16. The system of claim 14, wherein if the exhaust gas temperature value exceeds a first threshold temperature but does not exceed a second threshold temperature, the controller automatically sets the aircraft's status to a watch-listed status, and sends a communication regarding the aircraft's watch-listed status to at least a power plant engineer responsible for the aircraft. 17. The system of claim 14, wherein the controller determines if communications link is exhibiting an outage, and if so, initiates a troubleshooting operation to troubleshoot the communications link.
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이 특허에 인용된 특허 (11)
Schmidt Dennis E. ; Hanus Michael D., APU troubleshooting system.
Harbert, Richard H., Even fire 90°V12 IC engines, fueling and firing sequence controllers, and methods of operation by PS/P technology and IFR compensation by fuel feed control.
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