CN214566185U - Device for limiting stroke of aviation seat actuator cylinder - Google Patents
Device for limiting stroke of aviation seat actuator cylinder Download PDFInfo
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- CN214566185U CN214566185U CN202120831443.0U CN202120831443U CN214566185U CN 214566185 U CN214566185 U CN 214566185U CN 202120831443 U CN202120831443 U CN 202120831443U CN 214566185 U CN214566185 U CN 214566185U
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- cylinder
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- half cylinder
- fixing lug
- locking hole
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Abstract
A device for limiting the stroke of an aviation seat actuator cylinder comprises a left half cylinder and a right half cylinder which are symmetrically arranged; the outer wall of the left half cylinder is provided with a pair of left fixing lugs, and the outer wall of the right half cylinder is provided with a pair of right fixing lugs; the left half cylinder and the right half cylinder are assembled into a limiting cylinder by the locking bolt and the nut which penetrate through the left fixing lug and the right fixing lug. A round opening is formed in the center of the top of the limiting cylinder and communicated with the inside of the limiting cylinder, so that a boss-shaped cylinder cavity is formed in the limiting cylinder. And a plurality of hoop tightening grooves are uniformly formed in the outer wall of the limiting cylinder at two sides of the left fixing lug and the right fixing lug. A round locking hole is formed in the right fixing lug, and a track-shaped locking hole corresponding to the round locking hole is formed in the left fixing lug. The left half cylinder and the right half cylinder in the device can be installed in a staggered mode, the actuator cylinders of the aviation seat with the faults are limited in energy efficiency, the device is suitable for limiting the actuator cylinders of different types and different strokes, and the applicability is good.
Description
Technical Field
The utility model relates to an aircraft route maintenance field especially relates to a device of restriction aviation seat pressurized strut stroke.
Background
The airplane is provided with a seat adjusting mechanism to adjust the inclination angle of the seat, so that the riding comfort of passengers is improved. As shown in fig. 1, the seat adjusting mechanism includes an adjusting button and a wire rope installed inside an armrest, a ram 100 installed at the backrest of an airplane, a motion limiting bush 300 coaxially installed on a ram stroke shaft 200, and a mounting base 400. The adjustment button can adjust the telescopic length of the actuator cylinder 100 on the stroke shaft 200, and the seat inclination angle is determined by the stroke of the actuator cylinder 100. The actuator cylinder 100 retracts downward, and the backrest tilts backward; the ram 100 is extended upwardly with the backrest fixed in an upright position. When the seat adjustment mechanism fails, the ram 100 will normally retract and bear against the restraint bushing 300, and the failed seat is in a reclined position, which will affect the ingress and egress and safety of the adjacent occupant. Therefore, when an airline releases an airplane, only a failed seat can be labeled and forbidden so as to reach the airworthiness standard. Meanwhile, in order to prevent passengers in other seats from entering or exiting the safe passage, the failed seat needs to be fixed in the upright position through some temporary binding measures. However, the temporary binding measures cannot well guarantee that the failed seat is in the upright position state for a long time, and the failed seat is easily touched by other passengers, so that instability exists and safety is not ensured. Therefore, there is a need for a device that can limit the ram of a failed seat to the upper end of the travel shaft to ensure that the failed seat remains in an upright position.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to overcome shortcoming and not enough among the prior art, provide a device of restriction aviation seat actuator cylinder stroke, its installation is convenient, fixed reliable, the suitability is good, can effectually restrict the aviation seat adjustment mechanism who has a fault to reduce the influence that the seat trouble caused to the aircraft operation, protect seat adjustment mechanism's part not further to break down.
In order to achieve the purpose, the scheme is realized by the following technical scheme:
a device for limiting the stroke of an aviation seat actuator cylinder comprises a left half cylinder and a right half cylinder which are symmetrically arranged; the outer wall of the left half cylinder is provided with a pair of left fixing lugs, and the outer wall of the right half cylinder is provided with a pair of right fixing lugs; the left half cylinder and the right half cylinder are assembled into a limiting cylinder by the locking bolt and the nut which penetrate through the left fixing lug and the right fixing lug. A round opening is formed in the center of the top of the limiting cylinder and communicated with the inside of the limiting cylinder, so that a boss-shaped cylinder cavity is formed in the limiting cylinder.
Furthermore, a plurality of hoop tightening grooves are evenly formed in the two sides of the left fixing lug and the right fixing lug on the outer wall of the limiting cylinder.
Furthermore, a round locking hole is formed in the right fixing lug, and a runway-shaped locking hole corresponding to the round locking hole is formed in the left fixing lug.
Preferably, the left half cylinder and the right half cylinder have the same structure and are symmetrically arranged.
Preferably, the left fixing lugs on the left half cylinder are symmetrically arranged in front and back.
Preferably, the pair of right fixing lugs on the right half cylinder are symmetrically arranged in front and back.
Compared with the prior art, the beneficial effects of the utility model are that:
1) the device is convenient to install and reliable in fixation, and can effectively limit the faulty aircraft seat, improve the utilization rate of the adjacent position of the faulty seat, reduce the pressure of the seat fault on the operation of an airline company, and protect the components of the seat regulating mechanism from further fault;
2) the left half cylinder and the right half cylinder in the device can be installed in a staggered mode, the device is suitable for limiting the actuating cylinders of different types and different strokes, the applicability is good, and the manufacturing cost can be reduced.
In order to make the present invention more clearly understood, preferred embodiments of the present invention will be described below with reference to the accompanying drawings.
Drawings
FIG. 1 is a schematic view of the operation principle of an adjusting mechanism of an aircraft seat in the background art;
fig. 2 is a front view of the present invention;
fig. 3 is a schematic three-dimensional structure of the present invention;
FIG. 4 is a cross-sectional view of the present invention taken along the central axis;
FIG. 5 is a schematic structural view of the present invention when the left half cylinder and the right half cylinder are separated;
fig. 6 is an assembly view of the present invention;
fig. 7 and 8 are reference diagrams of the usage status of the present invention.
Detailed Description
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are used merely for convenience of description and for simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention. In the description of the present invention, "a plurality" means two or more unless otherwise specified.
Furthermore, if the terms "first," "second," and the like are used for descriptive purposes only, they are used for mainly distinguishing different devices, elements or components (the specific types and configurations may be the same or different), and they are not used for indicating or implying relative importance or quantity among the devices, elements or components, but are not to be construed as indicating or implying relative importance.
Referring to fig. 1 to 8, a device for limiting the stroke of an actuator cylinder of an aircraft seat includes a left half cylinder 10 and a right half cylinder 20, which are symmetrically disposed; a pair of left fixing lugs 11 is symmetrically arranged on the front and back of the outer wall of the left half barrel 10, and a pair of right fixing lugs 21 is symmetrically arranged on the front and back of the outer wall of the right half barrel 20 and respectively corresponds to the left fixing lugs 11; the left half cylinder 10 and the right half cylinder 20 can be assembled into a limiting cylinder 1 by a pair of lock bolt nuts 30 respectively passing through the left fixing lug 11 and the right fixing lug 21. The center of the top of the limiting cylinder 1 is provided with a round opening 12 matched with the stroke shaft 200 and an opening at the bottom of the limiting cylinder 1, so that the limiting cylinder 1 can be sleeved on the stroke shaft 200 of the seat adjusting mechanism and the limiting bush 300 is sleeved in the cylinder cavity of the limiting cylinder 1, and the upper end of the limiting cylinder 1 is abutted against the actuating cylinder 100, and the lower end of the limiting cylinder 1 is abutted against the mounting base 400. Since the limiting cylinder 1 is clamped between the actuating cylinder 100 and the limiting bush 300, the telescopic stroke of the actuating cylinder 100 on the stroke shaft 200 is limited, so that the faulty aircraft seat is always kept in the upright posture.
Specifically, the left half cylinder 10 and the right half cylinder 20 have the same structure and are both obtained by half-splitting the limiting cylinder 1, and the left half cylinder 10 and the right half cylinder 20 are arranged in bilateral symmetry with the stroke shaft 200 as an axis. The round opening 12 at the top of the limiting cylinder 1 is communicated with the inside of the limiting cylinder 1, so that a boss-shaped cylinder cavity 13 is formed inside the limiting cylinder 1, the upper part of the boss-shaped cylinder cavity 13 is matched and sleeved with the stroke shaft 200, and the lower part of the boss-shaped cylinder cavity 13 is matched and sleeved with the movable bushing 300.
Further, evenly be provided with a plurality of circles on the outer wall of a spacing section of thick bamboo 1 and cramp the groove 4 in the both sides that are located left fixed ear 11 and right fixed ear 21, cramp the ring and just can cramp into a spacing section of thick bamboo 1 with half a section of thick bamboo 10 on the 4 endotheca of cramp groove and half a section of thick bamboo 20 on the right side, cramp the groove 4 and cramp the cooperation of ring and can realize the lock-free bolt nut installation of a spacing section of thick bamboo 1, the mounting means is various.
Furthermore, because the lengths and the strokes of the actuating cylinders 100 of different types of airplanes are slightly different, in order to enhance the applicability of the device, the device can limit the telescopic strokes of the actuating cylinders 100 with different lengths, a circular locking hole is arranged on the right fixing lug 21, and a runway-shaped locking hole corresponding to the circular locking hole is arranged on the left fixing lug 11. Thus, the left half cylinder 10 and the right half cylinder 20 can be assembled into the limit cylinder 1 by aligning up and down, or assembled into the staggered limit cylinder 1 by staggering up and down. When the actuator cylinder 100 is assembled in a staggered manner, the top of the left half cylinder 10 abuts against the actuator cylinder 100, and the bottom of the right half cylinder 20 abuts against the mounting base 400, so that the effect of limiting the actuator cylinder 100 can be achieved. In addition, when the assembly is assembled in a staggered manner, the tightening grooves 4 on the left half cylinder 10 and the tightening grooves 4 on the right half cylinder 20 are also staggered, and the left half cylinder 10 and the right half cylinder 20 can be tightened into the staggered limit cylinders 1 by the tightening rings.
Compared with the prior art, the beneficial effects of the utility model are that: the device is convenient to install and reliable in fixation, and can effectively limit the faulty aircraft seat, improve the utilization rate of the adjacent position of the faulty seat and reduce the pressure of the seat fault on the operation of an airline company; the left half cylinder and the right half cylinder in the device can be installed in a staggered mode, the device is suitable for limiting the actuating cylinders of different types and different strokes, the applicability is good, and the manufacturing cost can be reduced.
The above-mentioned embodiments only represent some embodiments of the present invention, and the description thereof is specific and detailed, but not to be construed as limiting the scope of the present invention. It should be noted that, for those skilled in the art, without departing from the spirit of the present invention, several variations and modifications can be made, which are within the scope of the present invention.
Claims (6)
1. A device for limiting the stroke of an aviation seat actuator cylinder comprises a left half cylinder and a right half cylinder which are symmetrically arranged; the outer wall of the left half cylinder is provided with a pair of left fixing lugs, and the outer wall of the right half cylinder is provided with a pair of right fixing lugs; the lock bolt nut that passes left fixed ear and the fixed ear in right side assembles into a spacing section of thick bamboo, its characterized in that with a left half section of thick bamboo and a right half section of thick bamboo: a round opening is formed in the center of the top of the limiting cylinder and communicated with the inside of the limiting cylinder, so that a boss-shaped cylinder cavity is formed in the limiting cylinder.
2. A device for limiting travel of an airline seat ram according to claim 1, wherein: and a plurality of hoop tightening grooves are uniformly formed in the outer wall of the limiting cylinder at two sides of the left fixing lug and the right fixing lug.
3. A device for limiting travel of an airline seat ram according to claim 2, wherein: a circular locking hole is formed in the right fixing lug, and a track-shaped locking hole corresponding to the circular locking hole is formed in the left fixing lug.
4. A device for limiting travel of an airline seat ram according to claim 3, wherein: the left half cylinder and the right half cylinder are identical in structure and are symmetrically arranged.
5. A device for limiting travel of an airline seat ram according to claim 3, wherein: and the left fixing lugs on the left half cylinder are symmetrically arranged front and back.
6. A device for limiting travel of an airline seat ram according to claim 3, wherein: and the pair of right fixing lugs on the right half cylinder are symmetrically arranged in front and back.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120831443.0U CN214566185U (en) | 2021-04-22 | 2021-04-22 | Device for limiting stroke of aviation seat actuator cylinder |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120831443.0U CN214566185U (en) | 2021-04-22 | 2021-04-22 | Device for limiting stroke of aviation seat actuator cylinder |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214566185U true CN214566185U (en) | 2021-11-02 |
Family
ID=78327451
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202120831443.0U Active CN214566185U (en) | 2021-04-22 | 2021-04-22 | Device for limiting stroke of aviation seat actuator cylinder |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN214566185U (en) |
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2021
- 2021-04-22 CN CN202120831443.0U patent/CN214566185U/en active Active
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