Sensor system for monitoring the synchronism of control surfaces of an aircraft
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-009/00
B64C-013/30
B64C-013/00
출원번호
US-0517790
(2008-09-29)
등록번호
US-8152110
(2012-04-10)
우선권정보
DE-10 2007 046 707 (2007-09-28)
국제출원번호
PCT/EP2008/008273
(2008-09-29)
§371/§102 date
20090604
(20090604)
국제공개번호
WO2009/043568
(2009-04-09)
발명자
/ 주소
Schlegel, Robert
Riech, Juergen
출원인 / 주소
Liebherr-Aerospace Lindenberg GmbH
대리인 / 주소
Alleman Hall McCoy Russell & Tuttle LLP
인용정보
피인용 횟수 :
3인용 특허 :
8
초록▼
The present invention relates to a sensor system for monitoring the synchronism of control surfaces of an aircraft with two transmission links for the mechanical transmission of the movements of one or more control surfaces to at least one sensor, wherein the two transmission links are coupled with
The present invention relates to a sensor system for monitoring the synchronism of control surfaces of an aircraft with two transmission links for the mechanical transmission of the movements of one or more control surfaces to at least one sensor, wherein the two transmission links are coupled with each other mechanically and/or via the at least one sensor, whereby a difference between the movements transmitted by the transmission links can be monitored.
대표청구항▼
1. A sensor system for monitoring the synchronism of control surfaces of an aircraft with two transmission links for mechanical transmission of movements of one or more control surfaces to at least one sensor, wherein the two transmission links are coupled with each other mechanically and/or via the
1. A sensor system for monitoring the synchronism of control surfaces of an aircraft with two transmission links for mechanical transmission of movements of one or more control surfaces to at least one sensor, wherein the two transmission links are coupled with each other mechanically and/or via the at least one sensor, whereby a difference between the movements transmitted by the transmission links is monitored, and wherein different desired travel distances are compensated by corresponding different transmission ratios of the movements transmitted by the transmission links to one or more coupling elements. 2. The sensor system according to claim 1, wherein the transmission links are coupled via one or more rotatively movable coupling elements. 3. The sensor system according to claim 1, wherein the two transmission links engage two coupling elements movable against each other, whose relative movement is monitored by the sensor. 4. The sensor system according to claim 1, wherein the two transmission links engage an inherently rigid coupling element and two sensors are provided, which monitor forces transmitted by the transmission links. 5. The sensor system according to claim 1, wherein the two transmission links each comprise a Bowden line. 6. The sensor system according to claim 5, wherein cables of the two Bowden lines are reeled up on one or more drums on at least one end. 7. The sensor system according to claim 6, wherein the Bowden lines are tensioned by one or more return springs of the one or more drums. 8. The sensor system according to claim 6, wherein the cables of the two Bowden lines are reeled up on the drum or drums in opposite directions. 9. The sensor system according to claim 6, wherein the cables of the two Bowden lines are reeled up on drums or drum regions with different diameters. 10. The sensor system according to claim 6, wherein the cables of the two Bowden lines are reeled up on a common drum on the at least one end, and the at least one sensor includes a plurality of cable force sensors integrated in the cables. 11. The sensor system according to claim 10, wherein the cable force sensors include a spring and a sensor, which monitors a change in length of the spring. 12. The sensor system according to claim 6, wherein the cables of the two Bowden lines are reeled up on two separate drums on at least one end, and the sensor monitors a difference in angle between the drums. 13. The sensor system according to claim 12, wherein the drums are coaxially arranged one beside the other. 14. The sensor system according to claim 1, wherein the transmission links transmit a rotational movement, via a revolving tube or a flexible shaft. 15. The sensor system according to claim 14, wherein the sensor monitors a difference in angle between the rotational movements transmitted by the transmission links. 16. The sensor system according to claim 1, wherein the transmission links transmit movements of a single control surface, wherein the movements of the single control surface occur at different points. 17. The sensor system according to claim 1, wherein the transmission links transmit movements of at least two different control surfaces. 18. The sensor system according to claim 1, wherein each transmission link transmits the movements of the one or more control surfaces. 19. A system, comprising: a first control surface of an aircraft;a second control surface of the aircraft, the first and second control surfaces being symmetrically moved control surfaces;a sensor system including at least one sensor, the sensor system monitoring synchronism of the first and second control surfaces;a first and a second transmission link for mechanical transmission of movements of the first and second control surfaces to the sensor, the first and second transmission links coupled with each other mechanically and via the sensor and one or more rotatively movable coupling elements, wherein the monitoring of the sensor system includes monitoring a difference between the movements transmitted by the first and second transmission links and detecting a breakage of one of the first and second transmission links, and wherein different desired travel distances are compensated by corresponding different transmission ratios of the movements transmitted by the first and second transmission links to one or more coupling elements.
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이 특허에 인용된 특허 (8)
Schievelbusch, Bernd; Winkelmann, Christoph, Device for the recognition of residual synchronization errors of multiple slats of flaps placed next to each other in aircraft.
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.
Huynh, Neal V.; Bleeg, Robert J.; Pepper, Ralph Scott; Standley, John A.; Bocksch, Brian L., Systems and methods for controlling aircraft flaps and spoilers.
Huynh,Neal V.; Bleeg,Robert J.; Pepper,Ralph Scott; Standley,John A.; Bocksch,Brian L., Systems and methods for controlling aircraft flaps and spoilers.
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