IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0064754
(2011-04-13)
|
등록번호 |
US-8424801
(2013-04-23)
|
우선권정보 |
GB-1006099.4 (2010-04-13); GB-1013050.8 (2010-08-03) |
발명자
/ 주소 |
- Wildman, Eric
- Parker, Simon John
- Bryant, Anthony
- Folkard, Christian
|
출원인 / 주소 |
- Airbus Operations Limited
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
1 인용 특허 :
6 |
초록
▼
A support assembly for deployment and retraction of an aero surface from an aircraft is disclosed. The assembly comprises a guide track, a primary support arm having one end coupled to a carriage mounted on the track such that the primary support arm is rotatable relative to the carriage about multi
A support assembly for deployment and retraction of an aero surface from an aircraft is disclosed. The assembly comprises a guide track, a primary support arm having one end coupled to a carriage mounted on the track such that the primary support arm is rotatable relative to the carriage about multiple axes, and a control arm having one end coupled to the primary support arm and a second end pivotably attachable to a fixed support forming part of the structure of the aircraft. The assembly being configured such that, when the carriage is driven along the guide track, the control arm causes the primary support arm to pivot about said multiple axes to deploy and/or retract an aero surface pivotally attached to an opposite end of the primary support member along an arcuate path.
대표청구항
▼
1. A support assembly for deployment and retraction of an aero surface from an aircraft, the assembly comprising: a guide track mounted to a fixed support,a primary support arm having one end coupled to a carriage mounted on the track such that the primary support arm is configured to rotate relativ
1. A support assembly for deployment and retraction of an aero surface from an aircraft, the assembly comprising: a guide track mounted to a fixed support,a primary support arm having one end coupled to a carriage mounted on the track such that the primary support arm is configured to rotate relative to the guide track at least about a first axis parallel with the guide track and about a second axis extending at right angles to the guide track, anda control arm having one end coupled to the primary support arm and a second end pivotably attached to a fixed support for rotation about a third axis, wherein said guide track, said primary support arm and said control arm are configured to require said control arm to rotate about the third axis to cause said primary support arm to pivot about said second axis when the carriage is driven along the guide track, wherein the control arm is also configured to cause said primary support arm to pivot about said first axis when the carriage is driven along the guide track, and said aero surface is deployed or retracted along an arcuate path. 2. A support assembly according to claim 1, wherein said one end of the control arm is coupled to the primary support arm at a position spaced from either end of said primary support arm. 3. A support assembly according to claim 1, wherein the primary support arm is rotatable relative to the carriage about a first axis. 4. An aircraft wing assembly, including a slat and a support assembly according to claim 1 to control deployment and retraction of said slat. 5. An aircraft wing assembly, including a flap and a support assembly according to claim 1, to control deployment and retraction of said flap. 6. A support assembly according to claim 1, comprising a drive member extending along the fixed guide track, the drive member being coupled to the carriage such that the carriage is movable along the guide track in response to rotation of the drive member. 7. A support assembly according to claim 6, wherein the guide track comprises a recess extending along its length, the drive member being received within said recess. 8. A support assembly according to claim 7, wherein the carriage includes a drive coupling portion that is received in said recess when said carriage is mounted on the track. 9. A support assembly according to claim 8, wherein the drive member comprises a threaded shaft that extends through the drive coupling portion of the carriage and mates with a complimentary thread formed therein such that the carriage moves along the guide track in response to rotation of the threaded shaft. 10. A support assembly according to claim 1, wherein the primary support arm is rotatable relative to the carriage about multiple axes so that an aero surface pivotally attached to an opposite end of the primary support member is deployed and/or retracted along an arcuate path. 11. A support assembly according to claim 10, wherein the first and second axes are 90 degrees to each other. 12. A support assembly according to claim 1, wherein the primary support member comprises a pair of upper and a pair of lower arm portions, each of the upper arm portions and each of the lower arm portions extending in opposite directions from an intermediate mounting boss located between the ends of the primary support member. 13. A support assembly according to claim 1, when used to control the deployment or retraction of a slat or flap from an aircraft wing, wherein the guide track is pivotally mounted to a fixed rib forming the structure of the aircraft wing at one end, for pivotal movement about an axis in a plane of wing bending. 14. A support assembly according to claim 12, wherein a shaft extends between the intermediate mounting bosses of the upper and lower arm portions, said shaft including a part-spherical male bearing surface. 15. A support assembly according to claim 14, wherein the control arm has a collar at one end defining a part-spherical female bearing surface that mates with the male bearing surface on the shaft such that the control arm and primary support member can rotate relative to each other in any direction about said spherical bearing. 16. A support assembly for deployment and retraction of an aero surface from an aircraft, the assembly comprising: a guide track,a primary support arm having one end coupled to a carriage mounted on the track such that the primary support arm is rotatable relative to the carriage, anda control arm having one end coupled to the primary support arm and a second end pivotably attachable to a fixed support, wherein the assembly is configured such that, when the carriage is driven along the guide track, the control arm causes the primary support arm to pivot relative to the carriage to deploy or retract said aero surface pivotally attached to an opposite end of the primary support member, wherein the guide track has a mounting flange for connection of the guide track to a fixed support forming part of the structure of the aircraft, and a carriage mounting portion extending from said mounting flange, the flange and carriage mounting portion being connected to each other by a necked region. 17. A support assembly according to claim 16, wherein the carriage has an opening to receive the carriage mounting portion of the guide track such that the carriage mounting portion is surrounded by the carriage with the carriage mounting portion extending through said opening. 18. A support assembly according to claim 17, wherein the opening in the carriage has overhanging regions that extend into a space between the flange and the carriage mounting portion towards the necked region so that the carriage surrounds the carriage mounting portion. 19. A support assembly according to claim 17, wherein the carriage mounting portion has an outer surface that defines a plurality of bearing surfaces that extend along the length of the guide track. 20. A support assembly according to claim 19, wherein the carriage has bearing apertures therein and bearings received in said apertures with bearing surfaces that lie in rolling contact with the bearing surfaces on the carriage mounting portion. 21. A support assembly according to claim 20, wherein the carriage mounting portion has two upper bearing surfaces and two lower bearing surfaces, each of the upper and each of the lower bearing surfaces being arranged at an angle relative to its other upper and lower bearing surface, respectively. 22. A support assembly according to claim 21, wherein the apertures in the carriage includes two upper angled bearing apertures mounting upper bearings with their axes of rotation at an angle to each other corresponding to the angle of the upper bearing surfaces and, two lower bearing apertures mounting lower bearings with their axes of rotation at an angle to each other corresponding to the angle of the lower bearing surfaces. 23. A support assembly according to claim 22, wherein the angle between each of the upper bearings and each of the lower bearings is 90 degrees, respectively. 24. A support assembly for deployment and retraction of an aero surface from an aircraft, the assembly comprising: a guide track,a primary support arm having one end coupled to a carriage mounted on track such that the primary support arm is rotatable relative to the carriage, anda control arm having one end coupled to the primary support arm and a second end pivotably attachable to a fixed support, wherein the assembly is configured such that, when the carriage is driven along the guide track, the control arm causes the primary support arm to pivot relative to the carriage to deploy or retract said aero surface pivotally attached to an opposite end of the primary support member, wherein the primary support arm is rotatable relative to the carriage about multiple axes so that an aero surface pivotally attached to an opposite end of the primary support member is deployed and/or retracted along an arcuate path, wherein the carriage comprises a body, the body also comprising spaced parallel wall portions extending therefrom in a direction away from the guide track, the carriage also comprising an axle that extends between, and is pivotally mounted to, the spaced parallel wall portions for rotation of the axle about a first axis relative to the body, said one end of the primary support member being coupled to said axle. 25. A support assembly according to claim 24, wherein said one end of the primary support member is pivotally coupled to the axle for rotation about a second axis relative to the axle and to the carriage. 26. A support assembly for deployment and retraction of an aero surface from an aircraft, the assembly comprising: a guide track,a primary support arm having one end coupled to a carriage mounted on the track such that the primary support arm is rotatable relative to the carriage, anda control arm having one end coupled to the primary support arm and a second end pivotably attachable to a fixed support, wherein the assembly is configured such that, when the carriage is driven along the guide track. the control arm causes the primary support arm to pivot relative to the carriage to deploy and/or retract said aero surface pivotally attached to an opposite end of the primary support member, wherein the primary support arm is rotatable relative to the carriage about a first axis, wherein the guide track is mounted for rotation about a second axis extending along the length of the guide track so that, when the carriage is driven along the guide track, the control arm causes the primary support arm to pivot about said first axis, the control arm also causing the guide track to pivot about said second axis, together with said carriage and the primary support arm, so that an aero surface pivotally attached to an opposite end of the primary support member is deployed and/or retracted along an arcuate path. 27. A support assembly for deployment and retraction of an aero surface from an aircraft, the assembly comprising: a guide track mounted to a fixed support;a primary support arm having one end coupled to a carriage mounted on the track such that the primary support arm is configured to rotate relative to the carriage about at least a first axis extending at right-angles to the guide track and wherein the guide track and carriage are rotatable relative to a fixed support about a second, longitudinal, axis of the guide track; anda control arm having one end coupled to the primary support arm and a second end pivotably attached to a fixed support for rotation about a third axis, wherein said guide track, said primary support arm and said control arm are configured to require the control arm to rotate about the third axis to cause the primary support arm to pivot about the first axis, wherein the control arm is also configured to cause the primary support arm to pivot about the second, longitudinal, axis when the carriage is driven along the guide track and said aero surface is pivotally attached to an opposite end of the primary support member and is deployed or retracted along an arcuate path.
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