Aircraft wing and an aircraft comprising such aircraft wing
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-009/04
B64C-009/02
B64C-009/16
B64C-009/22
B64D-045/00
출원번호
US-0699085
(2015-04-29)
등록번호
US-9751615
(2017-09-05)
우선권정보
EP-14167726 (2014-05-09)
발명자
/ 주소
Recksiek, Martin
출원인 / 주소
Airbus Operations GmbH
대리인 / 주소
Lorenz & Kopf LLP
인용정보
피인용 횟수 :
0인용 특허 :
5
초록▼
An aircraft wing comprising a main wing, a high lift element, and at least two spaced connecting systems for moveably connecting the high lift element to the main wing, wherein each connecting system comprises a track element provided on the main wing, and having a first support surface and a first
An aircraft wing comprising a main wing, a high lift element, and at least two spaced connecting systems for moveably connecting the high lift element to the main wing, wherein each connecting system comprises a track element provided on the main wing, and having a first support surface and a first track side wall, an actuator device, a drive rod, and a carriage device connected to the high lift element and having an engagement portion. The object is to provide an aircraft wing which is configured in such a manner that when the connecting system for connecting the high lift element to the main wing fails the high lift element can still be held in a possibly unskewed position.
대표청구항▼
1. An aircraft wing comprising: a main wing,a high lift element, andat least two spaced connecting systems for moveably connecting the high lift element to the main wing, wherein each connecting system comprisesa track element fixedly mounted to the main wing, and having a first support surface and
1. An aircraft wing comprising: a main wing,a high lift element, andat least two spaced connecting systems for moveably connecting the high lift element to the main wing, wherein each connecting system comprisesa track element fixedly mounted to the main wing, and having a first support surface and a first track side wall extending transverse to the first support surface,an actuator device provided on the main wing for moving the high lift element relative to the main wing,a drive rod having an element end connected to the high lift element, and an actuator end connected to the actuator device, anda carriage device mounted to the high lift element and having an engagement portion engaging the track element in such a manner that a linear movement of the engagement portion along the track element is permitted,characterized in thatthe engagement portion comprises a bearing including a slide bearing, the bearing having a first bearing surface and a first bearing side wall extending transverse to the first bearing surface, wherein the first bearing surface is supported by and adapted to move along the corresponding first support surface of the track element,wherein the bearing and the track element engage in such a manner that,when the bearing is aligned with the track element the first track side wall and the first bearing side wall are spaced from each other so that the linear movement of the carriage device along the track element is permitted, andwhen the bearing is skewed with respect to the track element, the first bearing side wall contacts the first track side wall so that the bearing is locked against the track element and movement of the carriage device along the track element is inhibited. 2. An aircraft wing according to claim 1, wherein the track element comprises a second track side wall, wherein the bearing comprises a second bearing side wall, and wherein the bearing and the track element engage in such a manner that, when the bearing is aligned with the track element the second track side wall and the second bearing side wall are spaced from each other so that the linear movement of the carriage device along the track element is permitted, andwhen the bearing is skewed with respect to the track element the second bearing side wall contacts the second track side wall so that the bearing is locked against the track element and movement of the carriage device along the track element is inhibited. 3. An aircraft wing according to claim 2, wherein the bearing is formed as slide bearing, and wherein the first bearing surface is formed as a first slide surface adapted to slide along the corresponding first support surface of the track element. 4. An aircraft wing according to claim 3, wherein the first track side wall and the second track side wall are arranged in a track recess of the track element in an opposite manner such that surfaces of the first track side wall and the second track side wall point to one another, and wherein the first bearing side wall and the second bearing side wall are arranged on a bearing projection of the slide bearing in an opposite manner such that surfaces of the first bearing side wall and the second bearing side wall point away from one another. 5. An aircraft wing according to claim 4, wherein the first support surface is arranged on a side of the track recess, and wherein the first slide surface is arranged on a side of the bearing projection. 6. An aircraft wing according to claim 3, wherein the first track side wall and the second track side wall are arranged on a track projection of the track element in an opposite manner such that surfaces of the first track side wall and the second track side wall point away from one another, and wherein the first bearing side wall and the second bearing side wall are arranged in a bearing recess of the slide bearing in an opposite manner such that surfaces of the first bearing side wall and the second bearing side wall point to one another. 7. An aircraft wing according to claim 6, wherein the first support surface is arranged on a side of the track projection, and wherein the first slide surface is arranged on a side of the bearing recess. 8. An aircraft wing according to claim 6, wherein the first support surface is arranged on the track element adjacent the track projection on a first side of the track projection, wherein a second support surface is arranged on the track element adjacent the track projection on a second side of the track projection opposite the first side,wherein the bearing recess is defined between a first bearing projection portion and a second bearing projection portion,wherein the first slide surface is arranged on a side of the first bearing projection portion,wherein a second slide surface is arranged on a side of the second bearing projection portion, andwherein the second slide surface is adapted to slide along the corresponding second support surface. 9. An aircraft wing according to claim 2, wherein the bearing comprises a roller arrangement having at least a first roller element, wherein a peripheral surface of the first roller element comprises the first bearing surface, andthe slide bearing, which comprises a first slide element having the first bearing side wall, and a second slide element having the second bearing side wall, wherein the first slide element and the second slide element are arranged in an opposite manner such that the first bearing side wall and the second bearing side wall face one another. 10. An aircraft wing according to claim 9, wherein the track element has a T-shaped cross section including a first portion which is connected to the main wing and which extends away from a surface of the structure element of the main wing, anda second portion which extends in parallel to said surface of the structure element and which has a first surface pointing away from the surface of the structure element, a second surface facing the surface of the structure element, as well as first and second side surfaces pointing away from each other and connecting the first surface to the second surface,wherein the first surface comprises the first support surface,wherein the roller arrangement has a second roller element the peripheral surface of which comprises a second bearing surface, and a third roller element the peripheral surface of which comprises a third bearing surface,wherein the second surface comprises a second support surface on a first side of the first portion and a third support surface on a second side of the first portion opposite the first side,wherein the second bearing surface is supported by and adapted to move along the corresponding second support surface, and the third bearing surface is supported by and adapted to move along the corresponding third support surface, andwherein the first side surface comprises the first track side wall, and the second side surface comprises the second track side wall. 11. An aircraft wing according to claim 10, wherein the roller arrangement comprises a fourth roller element that is arranged in line with the first roller element,a fifth roller element that is arranged in line with the second roller element, anda sixth roller element that is arranged in line with the third roller element,wherein alignment lines of the first and fourth roller elements, of the second and fifth roller elements, and the third and sixth roller elements extend in parallel to the track element, andwherein first and second slide elements are arranged between the first, second and third roller elements on the one hand, and the fourth, fifth and sixth roller elements on the other hand. 12. An aircraft wing according to claim 1, wherein a first ratchet mechanism is provided between the first track side wall and the first bearing side wall, wherein the first ratchet mechanism comprises a first ratchet component mounted to the first track side wall and a second ratchet component mounted to the first bearing side wall,wherein the first ratchet component and the second ratchet component are adapted to engage in a direction of engagement, when the first bearing side wall contacts the first track side wall, such that upon engagement a relative movement of the first and second ratchet components opposite the direction of engagement is inhibited. 13. An aircraft wing according to claim 12, wherein the track element comprises a second track side wall, wherein the bearing comprises a second bearing side wall, and wherein the bearing and the track element engage in such a manner that, when the bearing is aligned with the track element the second track side wall and the second bearing side wall are spaced from each other so that the linear movement of the carriage device along the track element is permitted, andwhen the bearing is skewed with respect to the track element the second bearing side wall contacts the second track side wall so that the bearing is locked against the track element and movement of the carriage device along the track element is inhibited,wherein a second ratchet mechanism is provided between the second track side wall and the second bearing side wall,wherein the second ratchet mechanism comprises a third ratchet component mounted to the second track side wall and a fourth ratchet component mounted to the second bearing side wall,wherein the third ratchet component and the fourth ratchet component are adapted to engage in the direction of engagement, when the second bearing side wall contacts the second track side wall, such that upon engagement a relative movement of the third and fourth ratchet components opposite the direction of engagement is inhibited. 14. An aircraft wing according to claim 1, wherein at least one of the first and second track side walls and the first and second bearing side walls is provided with an anti-slip surface.
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