IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0275676
(2011-10-18)
|
등록번호 |
US-8596582
(2013-12-03)
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발명자
/ 주소 |
- Uchida, Minoru
- Yamanouchi, Hiroshi
|
출원인 / 주소 |
- Honda Patents & Technologies North America, LLC
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
10 인용 특허 :
7 |
초록
▼
An aircraft control surface operating device is provided for operating a control surface on an aircraft body portion to move between a retracted position and an extended position. The aircraft control surface operating device includes a control surface mounting assembly which movably secures the con
An aircraft control surface operating device is provided for operating a control surface on an aircraft body portion to move between a retracted position and an extended position. The aircraft control surface operating device includes a control surface mounting assembly which movably secures the control surface to the aircraft body portion, a drive arm rotatable about a drive axis relative to the aircraft body portion, an actuator for rotating the drive, and a drive link connecting the drive arm to the control surface mounting assembly. The drive link has a control end connected to the control surface mounting assembly and a driven end connected to the drive arm via a drive bearing joint. The drive link connects the drive arm and the control surface mounting assembly such that rotation of the drive arm is causes extending or retracting movement of the control surface.
대표청구항
▼
1. An aircraft control surface operating device for operating a control surface provided on an aircraft body portion to move between a retracted position and at least one extended position, the aircraft control surface operating device comprising: a control surface mounting assembly configured to mo
1. An aircraft control surface operating device for operating a control surface provided on an aircraft body portion to move between a retracted position and at least one extended position, the aircraft control surface operating device comprising: a control surface mounting assembly configured to movably secure the control surface to the aircraft body portion;a drive arm rotatably mounted to an aircraft body portion so as to be rotatable about a drive axis relative to said aircraft body portion;an actuator configured to rotate the drive arm in a first direction about the drive axis and a second direction about the drive axis, the second direction being opposite to the first direction; anda drive link having a control end connected to the control surface mounting assembly via a control bearing joint, and a driven end connected to the drive arm via a drive bearing joint,whereinthe drive bearing joint includes a substantially spherical drive bearing rotatably held within an opening defined through the drive link at the driven end, the drive bearing including a pair of drive bearing connecting portions provided opposite to one another on a surface of the drive bearing, the drive bearing being fixedly connected to the drive arm at the drive bearing connecting portions such that the drive link is rotatable about the drive bearing relative to the drive arm,the control bearing joint includes a substantially spherical control bearing rotatably held within an opening defined through the drive link at the control end, the control bearing including a pair of control bearing connecting portions provided opposite to one another on a surface of the control bearing, the control bearing being fixedly connected to the control surface mounting assembly at the control bearing connecting portions such that the drive link is rotatable about the control bearing relative to the control surface mounting assembly,an axis of rotation of the drive link about the drive bearing is nonparallel to an imaginary line connecting the drive bearing connecting portions, and an axis of rotation of the drive link about the control bearing is parallel to an imaginary line connecting the control bearing connecting portions, andthe drive link connects the drive arm and the control surface mounting assembly such that rotation of the drive arm in the first direction about the drive axis causes the drive link to exert a retracting force on the control surface mounting assembly, and rotation of the drive arm in the second direction about the drive axis causes the drive link to exert an extending force on the control surface mounting assembly. 2. The aircraft control surface operating device according to claim 1, wherein the drive link includes an extended body portion disposed between the driven end and control end,the opening defined through the drive link at the driven end in which the drive bearing is received passes entirely through the drive link at the driven end between a first surface of the drive link at the driven end and a second surface of the drive link at the driven end,the opening defined through the drive link at the control end in which the control bearing is received passes entirely through the drive link at the control end between the first surface of the drive link at the control end and the second surface of the drive link at the control end,the drive link control end and body are substantially linearly aligned with one another, and the drive link driven end is provided at an angle relative to the drive link body and control end such that a driven end imaginary line is non-parallel with a control end imaginary line, the driven end imaginary line passing through the drive opening and oriented perpendicularly to the first surface and the second surface of the drive link at the driven end, and the control end imaginary line passing through the control opening and oriented perpendicularly to the first surface and the second surface of the drive link at the control end. 3. A drive link for connecting an aircraft control surface operating device driving mechanism to an aircraft control surface mounting assembly so as to translate a rotational motion of the driving mechanism to an exertion of a retracting and extending force on the aircraft control surface mounting assembly, the drive link comprising: a drive bearing joint including a substantially spherical drive bearing, the drive bearing joint configured to be connected to the driving mechanism;a driven end connected to the drive bearing joint such that the drive link is movable in an x-direction, a y-direction, and a z-direction relative to the driving mechanism;a control bearing joint including a substantially spherical control bearing, the control bearing joint configured to be connected to the aircraft control surface mounting assembly;a control end connected to the control bearing joint such that the drive link is movable in the x-direction, the y-direction, and the z-direction relative to the aircraft control surface mounting assembly; anda drive link body connecting the driven end and the control end,whereinthe drive bearing joint is integrated in the driven end with the drive bearing rotatably received in a drive opening defined entirely through the driven end, the drive opening extending between a first surface of the drive link and a second surface of the drive link at the driven end,the control bearing joint is integrated in the control end with the control bearing rotatably received in a control opening defined entirely through the control end, the control opening extending between the first surface of the drive link and the second surface of the drive link at the control end, andthe drive link body and control end are substantially linearly aligned with one another, and the driven end is provided at an angle relative to the drive link body and control end such that a driven end imaginary line is non-parallel with a control end imaginary line, the driven end imaginary line passing through the drive opening and oriented perpendicularly to the first surface and the second surface of the drive link at the driven end, and the control end imaginary line passing through the control opening and oriented perpendicularly to the first surface and the second surface of the drive link at the control end. 4. The drive link according to claim 3, wherein the drive bearing further comprises at least one connecting portion configured to fixedly connect the drive bearing to the driving mechanism. 5. The drive link according to claim 4, wherein the control bearing further comprises at least one connecting portion configured to fixedly connect the control bearing to the aircraft control surface mounting assembly. 6. An aircraft wing comprising a wing body, a flap movably mounted on the wing body via a flap mounting assembly, and a flap operating device configured to move the flap relative to the wing body between a retracted position and at least one extended position, the flap operating device comprising: a drive arm mounted to the wing body so as to be rotatable about a drive axis relative to the wing body;an actuator including a linearly displaceable actuator rod operatively connected to the drive arm such that movement of the actuator rod in a first linear direction causes the drive arm to rotate about the drive axis in a first rotational direction, and movement of the actuator rod in a second linear direction causes the drive arm to rotate about the drive axis in a second rotational direction, the second linear direction and second rotational direction being opposite to the first linear direction and first rotational direction, respectively; anda drive link having a control end connected to the control surface mounting assembly via a control bearing joint, and a driven end connected to the drive arm via a drive bearing joint,whereinthe drive bearing joint includes a substantially spherical drive bearing rotatably held within an opening defined entirely through the drive link at the driven end, the drive opening extending between a first surface of the drive link at the driven end and a second surface of the drive link at the driven end,the control bearing joint includes a substantially spherical control bearing rotatably held within an opening defined entirely through the drive link at the control end, the control opening extending between a first surface of the drive link at the control end and a second surface of the drive link at the control end,the driven end is provided at an angle relative to the control end such that a driven end imaginary line is non-parallel with a control end imaginary line, the driven end imaginary line passing through the drive opening and oriented perpendicularly to the first surface and the second surface of the drive link at the driven end, and the control end imaginary line passing through the control opening and oriented perpendicularly to the first surface and the second surface of the drive link at the control end, andthe drive link connects the drive arm and the control surface mounting assembly such that rotation of the drive arm in the first direction about the drive axis causes the drive link to exert a retracting force on the control surface mounting assembly, and rotation of the drive arm in the second direction about the drive axis causes the drive link to exert an extending force on the control surface mounting assembly. 7. The aircraft wing according to claim 6, wherein the drive bearing includes a pair of drive bearing connecting portions provided opposite to one another on a surface of the drive bearing, the drive bearing being fixedly connected to the drive arm at the drive bearing connecting portions such that the drive link is rotatable about the drive bearing relative to the drive arm, the control bearing includes a pair of control bearing connecting portions provided opposite to one another on a surface of the control bearing, the control bearing being fixedly connected to the control surface mounting assembly at the control bearing connecting portions such that the drive link is rotatable about the control bearing relative to the control surface mounting assembly, andan axis of rotation of the drive link about the drive bearing is nonparallel to an imaginary line connecting the drive bearing connecting portions, and an axis of rotation of the drive link about the control bearing is parallel to an imaginary line connecting the control bearing connecting portions.
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