IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0790960
(2013-03-08)
|
등록번호 |
US-8725319
(2014-05-13)
|
우선권정보 |
DE-10 2010 044 678 (2010-09-08) |
발명자
/ 주소 |
- Recksiek, Martin
- Heintjes, Mark
- Winkelmann, Christoph
|
출원인 / 주소 |
|
대리인 / 주소 |
Jenkins, Wilson, Taylor & Hunt, P.A.
|
인용정보 |
피인용 횟수 :
0 인용 특허 :
3 |
초록
▼
A monitoring device is disclosed for an actuation system of an aircraft for monitoring a guiding device of a regulating flap with a load sensor. An actuation system with the monitoring device and a method for reconfiguring such an actuation system are disclosed. The monitoring device includes an int
A monitoring device is disclosed for an actuation system of an aircraft for monitoring a guiding device of a regulating flap with a load sensor. An actuation system with the monitoring device and a method for reconfiguring such an actuation system are disclosed. The monitoring device includes an interface to the load sensor and an interface to a driving device for adjusting the regulating flap. The monitoring device can determine or receive in-flight information actively signaling a predefined flight attitude and/or a predefined operational state of the aircraft. The monitoring device can compare a load value corresponding to a sensor value acquired by the load sensor and a limiting value corresponding to a minimum operational load for the predefined flight attitude and/or the predefined operational state of the aircraft and a monitoring function. The monitoring function can assign a fault mode to the regulating flap.
대표청구항
▼
1. An actuation system of an aircraft, comprising a guiding device for an adjustable flap with a load sensor and a monitoring device with a function for monitoring the guiding device, wherein an interface to the load sensor and an interface to a driving device for adjusting the regulating flap are i
1. An actuation system of an aircraft, comprising a guiding device for an adjustable flap with a load sensor and a monitoring device with a function for monitoring the guiding device, wherein an interface to the load sensor and an interface to a driving device for adjusting the regulating flap are integrated into the monitoring device, wherein the monitoring device is realized in such a way that it determines or receives in-flight information that actively signals a predefined flight attitude and/or a predefined operational state of the aircraft;wherein the monitoring device comprises a comparing function for carrying out a comparison between a load value that corresponds to a sensor value acquired by the load sensor and a limiting value that corresponds to a minimum operational load for the predefined flight attitude and/or the predefined operational state of the aircraft; andwherein the monitoring function is realized in such a way that it assigns a fault mode to the regulating flap if it is determined that the predefined flight attitude and/or the predefined operational state of the aircraft exists as a result of the comparison showing that the limiting value corresponding to the minimum operational load is not reached. 2. The actuation system according to claim 1, wherein the predefined flight attitude and/or operational state of the aircraft exists if at least one of the following conditions is fulfilled: the monitoring function determines or receives in-flight information as to the fact that the regulating flap is and/or has been moved into one of several selectable positions that is specially predefined for the assignment of the fault mode and/orat least a predefined time after generating an actuation command for the driving device in order to move the regulating flap into one of several selectable positions that is specially predefined for the assignment of the fault mode and/orthe monitoring function determines or receives in-flight information as to the fact that a predefined aerodynamic angle of attack or loading state or flight weight exists. 3. The actuation system according to claim 1, wherein the limiting value that corresponds to a minimum operational load is specified in the form of a value that is lower than 70% of the permissible maximum load for flying operations at the location of the load sensor. 4. The actuation system according to claim 1, wherein the monitoring device is realized in such a way that, if a fault mode is assigned to a regulating flap, it no longer activates this regulating flap during the same flight. 5. The actuation system according to claim 1, wherein the monitoring device determines that a predefined flight attitude exists by comparing specified flight attitude data with acquired flight attitude data. 6. The actuation system according to claim 1, wherein the limiting value that corresponds to a minimum operational load has the value of a cruising load at the location of the load sensor that is acquired during the same flight by the at least one load sensor. 7. The actuation system according to claim 1, wherein the monitoring device is realized in such a way that the comparing function carries out a comparison between a sensor value acquired by the load sensor and a limiting value that corresponds to a minimum operational load, as well as a comparison between a sensor value acquired by the load sensor and a second limiting value that corresponds to a maximum operational load, and in that the monitoring function assigns a fault mode to the regulating flap if it is determined that the predefined flight attitude and/or the predefined operational state of the aircraft exists as a result of the comparison showing that the limiting value corresponding to the minimum operational load is not reached or the limiting value corresponding to the maximum operational load is exceeded. 8. The actuation system according to claim 1, wherein the first limiting value corresponding to a minimum operational load and the limiting value corresponding to a maximum operational load are respectively specified in such a way that the first limiting value amounts to less than half of the second limiting value for the maximum operational load. 9. An actuation system for a regulating flap of an aircraft according to claim 1, wherein the actuation system comprises: at least one driving device for adjusting regulating flaps; andat least two guiding devices that are spaced apart from one another in the wingspan direction of the regulating flap and serve for adjusting the regulating flaps, wherein each guiding device comprises: an actuator, a transmission mechanism for transmitting the power of the respectively assigned driving device and an actuation mechanism for kinematically coupling the actuator to the regulating flap; wherein at least one load sensor is functionally connected to the monitoring device and arranged on at least one guiding device of the guiding devices assigned to at least one regulating flap, namely on at least one regulating flap of the actuation system and on at least one guiding device, in order to determine that an operational load is not reached. 10. The actuation system according to claim 9, wherein the actuation system comprises at least two regulating flaps on each airfoil, wherein a first load sensor is arranged on the regulating flap situated closest to the fuselage, namely on the guiding device situated closest to the aircraft fuselage, and wherein a second load sensor is arranged on the regulating flap situated farthest from the fuselage, namely on the guiding device situated farthest from the fuselage. 11. The actuation system according to claim 9, wherein the monitoring device comprises a function that is realized in such a way that it assigns a fault mode to a regulating flap during the movement of the regulating flap into a predefined position if the sensor value acquired by the load sensor falls short of a first limiting value that corresponds to a minimum operational load or exceeds a second limiting value that corresponds to a maximum operational load. 12. The actuation system according to claim 9, wherein a position sensor that serves for determining the adjusted position of the regulating flap and is functionally connected to the control and monitoring device is respectively arranged on both guiding devices, and in that the control and monitoring device is realized in such a way that it compares the values acquired by the position sensors with one another and assigns a fault mode to a regulating flap during the movement of the regulating flap into a predefined position if the comparison shows that the difference between the values of the position sensors exceeds a minimum difference and if the sensor value acquired by the load sensor falls short of a first limiting value that corresponds to a minimum operational load or exceeds a second limiting value that corresponds to a maximum operational load. 13. The actuation system according to claim 9, wherein the load sensor is arranged on the input side or the output side of the actuator of the guiding device in order to acquire the load occurring on the output side of the actuator due to the actuation of the regulating flap. 14. The actuation system according to claim 9, wherein the load sensor comprises a sensor for measuring the longitudinal force occurring in a drive rod that is arranged between the actuator and the regulating flap in order to adjust the regulating flap as a result of the adjusting movement of the actuator. 15. The actuation system according to claim 9, wherein each guiding device comprises a drive rod, by which the actuator is coupled to the regulating flap, and in that the load sensor is arranged in a connecting bolt for coupling the drive rod to the regulating flap and realized in such a way that it measures a lateral force in the bolt that results from the force exerted by the regulating flap. 16. The actuation system according to claim 9, wherein the load sensor comprises a sensor for measuring a torque that occurs on an output shaft of the actuator and is intended for realizing an adjusting movement of the actuator in order to adjust the regulating flap. 17. The actuation system according to claim 9, wherein a plurality of load sensors are arranged on a guiding device of a regulating flap, wherein the sensor value of one load sensor or the sensor values of several load sensors is/are used for determining whether a limiting value is exceeded and/or not reached. 18. The actuation system according to claim 1, wherein the fault-tolerant actuation system comprises a central driving unit that is activated by the control and monitoring device and mechanically coupled to the guiding devices of each wing by a rotary shaft in order to realize their actuation. 19. The actuation system according to claim 9, wherein at least two guiding devices are respectively connected to the at least one flap of each airfoil and spaced apart from one another in the wingspan direction of the, wherein the guiding devices are respectively coupled to the driving device assigned to the regulating flap by one respective driving connection; andwherein the fault-tolerant actuation system comprises driving devices for driving the guiding devices, wherein one driving device is respectively assigned to each regulating flap and functionally connected to a control and monitoring device that activates this driving device. 20. The actuation system according to claim 9, characterized in that the guiding devices comprise of a bearing device and an adjusting device and the adjusting device comprises: the actuator, the transmission mechanism for transmitting the power of the respectively assigned driving device and an actuation mechanism for kinematically coupling the actuator to the regulating flap. 21. A method for reconfiguring an actuation system with adjustable regulating flaps with the following steps: carrying out a comparison between a load value that corresponds to a sensor value acquired by the load sensor assigned to a regulating flap and a first limiting value that corresponds to a minimum operational load during a/each flight when the regulating flap is moved into a predefined position or when a control command for moving the regulating flap is generated or when it is determined that a predefined flight attitude exists; andassigning a fault mode to the regulating flap if this limiting value is not reached.
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