[특허]Aircraft high lift system and method for determining an operating condition of an aircraft high lift system

Liebherr-Aerospace Lindenberg GmbH

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특허 상세정보

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Aircraft high lift system and method for determining an operating condition of an aircraft high lift system

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-013/16 B64D-045/00
미국특허분류(USC)	244/076A; 244/099.2; 244/099.3; 244/213; 244/214; 244/215
출원번호	US-0778743 (2010-05-12)
등록번호	US-8814082 (2014-08-26)
우선권정보	DE-10 2009 020 840 (2009-05-12)
발명자 / 주소	Schievelbusch, Bernd Hauber, Bernhard
출원인 / 주소	Liebherr-Aerospace Lindenberg GmbH
대리인 / 주소	Alleman Hall McCoy Russell & Tuttle LLP
인용정보	피인용 횟수 : 1 인용 특허 : 2

초록

The present disclosure relates to an aircraft high lift system with at least one load station for actuating a flap of a wing, preferably a landing flap and/or a leading-edge flap, at least one transmission with transmission portions located between branch transmissions, wherein by means of the branch transmissions actuating energy can be branched off from the transmission to the load station, and to a method for determining an operating condition of an aircraft high lift system.

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1. An aircraft high lift system comprising at least two load stations for actuating a flap of a wing, a central drive unit converting aircraft supply energy into mechanical actuating energy, the actuating energy transmitted from the central drive unit to a transfer gear, the transfer gear distributing the actuating energy to at least one transmission, each transmission comprising at least one transmission portion, each transmission portion arranged between respective branch transmissions of two load stations associated to the flap, wherein via each branch transmission, actuating energy is selectively transmitted from the transmission to the corresponding load station, the system further comprising a detection sensor arranged in each transmission portion by which an operating condition of the transmission or of one or more of the two load stations is determined. 2. The aircraft high lift system according to claim 1, wherein torque applied at the transmission or a time course of the torque is detected via the detection sensor, and wherein the flap is one of a landing flap and a leading-edge flap. 3. The aircraft high lift system according to claim 1, wherein the detection sensor is a torque sensor. 4. The aircraft high lift system according to claim 2, wherein the system does not include a mechanical torque limiter in the transmission on an output side of the transfer gear. 5. The aircraft high lift system according to claim 2, wherein the system does not include a mechanical torque limiter in any of the load stations. 6. The aircraft high lift system according to claim 1, further comprising an evaluation unit which has a signal connection with each detection sensor and by which signals of each detection sensor are evaluated in order to determine the said operating condition. 7. The aircraft high lift system according to claim 6, wherein the evaluation unit is a central evaluation unit which has a signal connection with each of a plurality of detection sensors of the aircraft high lift system. 8. The aircraft high lift system according to claim 7, wherein the load station includes a station actuator and a spindle with a spindle nut, wherein the station actuator transmits actuating torque to the spindle and the spindle nut converts a rotatory movement into a translational movement for the flap. 9. The aircraft high lift system according to claim 1, wherein there is only one torque sensor per flap. 10. The aircraft high lift system according to claim 8, wherein via the detection sensor arranged in each transmission portion, torque applied at the transmission or a time course of the torque is determined. 11. The aircraft high lift system according to claim 10, wherein by monitoring a ratio of load components of at least one load station, faulty operating conditions are determined via the evaluation unit. 12. The aircraft high lift system according to claim 10, wherein by monitoring and comparing pairs of actuating forces applied at load stations of a left and right wing of the aircraft, faulty operating conditions are determined via the evaluation unit. 13. The aircraft high lift system according to claim 12, wherein a desired value for the actuating force applied at at least one load station is calculated via the evaluation unit based on current values for wing configuration, aircraft weight, airspeed, or temperature, and wherein by matching actual values determined with the calculated desired values, faulty operating conditions are determined via the evaluation unit. 14. The aircraft high lift system according to claim 13, wherein by direct or indirect comparison of load components of two load stations, one or more of a jamming case in one of the two load stations associated with the flap is determined via a rising operating torque in a first load station associated with the flap with constant operating torque of a second load station associated with the flap;an interruption of a load path in the first load station associated with the flap is determined via a presence of an entire load on an intact load path of the second load station associated with the flap;a skewing of the flap after an interruption or a jump in the time course of the torque in a load station associated with the flap is determined;an interruption of a transmission portion between flaps is determined via a torque decrease at both of the two load stations by using at least one signal from a position measuring means for determining a flap position;an interruption of a transmission portion between load stations of an outer flap is determined via a reaction of an inner load station; oran interruption of a transmission portion between load stations of an inner flap is determined via a change in ratios of load components of the load stations of the inner and outer flaps by using the evaluation unit. 15. A method for an aircraft high lift system, comprising: determining an operating condition of the aircraft high lift system with at least two load stations for actuating a flap of a wing, and with at least one transmission for transmitting actuating energy to the at least two load stations, wherein the said operating condition of the aircraft high lift system is determined directly or indirectly based on signals from only one detection sensor per flap, the detection sensor for each flap arranged in the transmission and detecting one or more of a torque applied at the transmission, a torque applied in one or more of the load stations, or a time course of the torque. 16. The method according to claim 15, wherein by monitoring and comparing pairs of actuating forces applied at load stations of a left and right wing of the aircraft, faulty operating conditions are determined, orwherein desired values for the actuating forces applied at the load stations are calculated based on current values for wing configuration, aircraft weight, airspeed or temperature and by matching actual values determined with the calculated desired values, faulty operating conditions are determined,wherein the flap is a landing flap or a leading-edge flap. 17. The method according to claim 16, wherein by monitoring a ratio of load components of the load stations, faulty operating conditions are determined. 18. The method according to claim 17, wherein by direct or indirect comparison of the load components of two load stations a jamming case in one of the two load stations associated with the flap is determined via a rising operating torque in a first load station associated with the flap with constant operating torque of a second load station associated with the flap oran interruption of a load path in the first load station associated with the flap is determined via a presence of an entire load on an intact load path of the second load station associated with the flap ora skewing of the flap after an interruption or a jump in the time course of the torque in a load station associated with the flap is determined oran interruption in a transmission portion between flaps is determined via a torque decrease at both load stations by using at least one signal from a position measuring means for determining a flap position oran interruption of a transmission portion between load stations of an outer flap is determined via a reaction of an inner load station oran interruption of a transmission portion between load stations of an inner flap is determined via a change in ratios of load components of the load stations of the inner and outer flaps.

이 특허에 인용된 특허 (2)

이 특허를 인용한 특허 피인용횟수: 1

Randerath, Bernhard; Gerdes, Mike; Scholz, Dieter. Method and device for condition monitoring. USP2016049321543.

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Aircraft high lift system and method for determining an operating condition of an aircraft high lift system

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Aircraft high lift system and method for determining an operating condition of an aircraft high lift system

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