Monitoring of high-lift systems for aircraft
IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0852828
(2013-03-28)
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등록번호 |
US-9073643
(2015-07-07)
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발명자
/ 주소 |
- Moy, George
- Padilla, Peter A.
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출원인 / 주소 |
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대리인 / 주소 |
Duft Bornsen & Fettig LLP
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인용정보 |
피인용 횟수 :
2 인용 특허 :
5 |
초록
▼
Monitoring of high-lift systems for aircraft. In one configuration, a method for monitoring a high-lift system includes monitoring a first current draw of a first drive station of the high-lift system, and monitoring a second current draw of a second drive station of the high-lift system. The method
Monitoring of high-lift systems for aircraft. In one configuration, a method for monitoring a high-lift system includes monitoring a first current draw of a first drive station of the high-lift system, and monitoring a second current draw of a second drive station of the high-lift system. The method further includes comparing the first current draw and the second current draw to determine if a differential between the first current draw and the second current draw exceeds a threshold, and generating a failure signal if the differential between the first current draw and the second current draw exceeds the threshold.
대표청구항
▼
1. A method of monitoring a high-lift system on an aircraft, wherein the high-lift system includes a controller coupled to a first drive station and a second drive station, the method comprising: monitoring, by the controller, a first current draw of an electric motor in the first drive station that
1. A method of monitoring a high-lift system on an aircraft, wherein the high-lift system includes a controller coupled to a first drive station and a second drive station, the method comprising: monitoring, by the controller, a first current draw of an electric motor in the first drive station that is installed on a first side of a flap;monitoring, by the controller, a second current draw of an electric motor in the second drive station that is installed on a second side of the same flap or another flap;comparing the first current draw and the second current draw to determine if a differential between the first current draw and the second current draw exceeds a first threshold; andgenerating a failure signal in the controller if the differential between the first current draw and the second current draw exceeds the first threshold to indicate a failure in the high-lift system. 2. The method of claim 1 wherein comparing the first current draw and the second current draw comprises: comparing the first current draw from the first drive station on an outboard side of a left wing flap, and the second current draw from the second drive station on an outboard side of a right wing flap. 3. The method of claim 2 further comprising: monitoring a third current draw of a third drive station on an inboard side of the left wing flap;monitoring a fourth current draw of a fourth drive station on an inboard side of the right wing flap;comparing the third current draw and the fourth current draw to determine if a differential between the third current draw and the fourth current draw exceeds a second threshold; andgenerating the failure signal if the differential between the third current draw and the fourth current draw exceeds the second threshold. 4. The method of claim 3 further comprising: comparing the first current draw of the first drive station on the outboard side of the left wing flap, and the third current draw of the third drive station on the inboard side of the left wing flap to determine if a differential between the first current draw and the third current draw exceeds a third threshold;comparing the second current draw of the second drive station on the outboard side of the right wing flap, and the fourth current draw of the fourth drive station on the inboard side of the right wing flap to determine if a differential between the second current draw and the fourth current draw exceeds a fourth threshold; andgenerating the failure signal if one of the differentials exceeds one of the thresholds. 5. The method of claim 1 wherein comparing the first current draw and the second current draw comprises: comparing the first current draw from the first drive station on an outboard side of a left wing flap, and the second current draw from the second drive station on an inboard side of the left wing flap. 6. The method of claim 5 further comprising: monitoring a third current draw of a third drive station on an outboard side of a right wing flap;monitoring a fourth current draw of a fourth drive station on an inboard side of the right wing flap;comparing the third current draw and the fourth current draw to determine if a differential between the third current draw and the fourth current draw exceeds a second threshold; andgenerating the failure signal if the differential between the third current draw and the fourth current draw exceeds the second threshold. 7. The method of claim 6 wherein: the first threshold and the second threshold vary as a function of airspeed. 8. A method of monitoring a high-lift system on an aircraft for a freewheeling skew failure, wherein the high-lift system includes a left wing flap and a right wing flap, the method comprising: monitoring, in a controller of the high-lift system, a first current draw of an electric motor in a first drive station that is installed on an outboard side of the left wing flap;monitoring, in the controller, a second current draw of an electric motor in a second drive station installed on an outboard side of the right wing flap, wherein there is no mechanical interaction between the first drive station and the second drive station;comparing the first current draw and the second current draw to determine whether a differential between the first current draw and the second current draw exceeds a threshold; andgenerating a failure signal by the controller if the differential between the first current draw and the second current draw exceeds the first threshold to indicate that one of the drive stations is disconnected from its associated flap. 9. A high-lift system on an aircraft that detects freewheeling skew failures on a flap, the high-lift system comprising: a first drive station installed on a first side of the flap and having a first electric motor to impart movement on the first side of the flap;a second drive station installed on a second side of the same flap or a different flap on the aircraft, and having a second electric motor to impart movement on the second side of the same flap or different flap; anda controller having a monitoring system that is coupled to a first motor sensor attached to the first electric motor, and coupled to a second motor sensor attached to the second electric motor;the monitoring system is configured to monitor a first current draw of the first electric motor by receiving a signal from the first motor sensor, and to monitor a second current draw of the second electric motor by receiving a signal from the second motor sensor;the monitoring system is configured to compare the first current draw and the second current draw to determine if a differential between the first current draw and the second current draw exceeds a threshold, and to generate a failure signal if the differential between the first current draw and the second current draw exceeds the threshold to indicate that the first drive station is disconnected from the first side of the flap or that the second drive station is disconnected from the second side of the same flap or the different flap.
이 특허에 인용된 특허 (5)
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Recksiek,Martin; Rechter,Harald; Besing,Wolfgang, Adaptive flap and slat drive system for aircraft.
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Johnson, Andrew T.; Hanlon, Casey; Potter, Calvin C., Distributed flight control surface actuation system.
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Marx, Alan D.; Emch, Gary A.; Gardner, Mark J.; Apfel, Richard I.; Renzelmann, Michael E.; Feet, Christopher D.; Finn, Michael R.; Good, Mark S.; Seehusen, Gregory J., In-flight detection of wing flap free wheeling skew.
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Recksiek, Martin; Giebeler, Christoph; Brueckner, Ina, Landing flap drive system.
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Lindstrom Jeffrey V. ; Reed R. David ; Platin Bradley E. ; Beyer Kevin W. ; Reusch David C., Method and apparatus for detecting skew and asymmetry of an airplane flap.
이 특허를 인용한 특허 (2)
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Moser, Matthew A.; Finn, Michael R.; Thoreen, Adam, Control interface for leading and trailing edge devices.
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Larson, Lowell Van Lund; Moore, Christopher A., Fail-safe electromechanical actuator.
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