CN215753042U - Lifting device for aviation seat - Google Patents
Lifting device for aviation seat Download PDFInfo
- Publication number
- CN215753042U CN215753042U CN202122373658.5U CN202122373658U CN215753042U CN 215753042 U CN215753042 U CN 215753042U CN 202122373658 U CN202122373658 U CN 202122373658U CN 215753042 U CN215753042 U CN 215753042U
- Authority
- CN
- China
- Prior art keywords
- lifting rod
- lifting
- rod
- locking
- slide rail
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Landscapes
- Seats For Vehicles (AREA)
Abstract
The utility model relates to a lifting device for an aviation seat, which comprises a slide rail group, two lifting rod groups, a first connecting piece, at least one driving piece and at least one locking assembly, wherein the slide rail group comprises two slide rails which are arranged at intervals; the two lifting rod groups are arranged in one-to-one correspondence with the two sliding rails, each lifting rod group comprises a first lifting rod and a second lifting rod, the middle part of each first lifting rod is hinged to the middle part of each second lifting rod, one end of each first lifting rod is inserted into the corresponding sliding rail in a sliding manner, and one end of each second lifting rod is hinged to the corresponding sliding rail; two ends of the first connecting piece are respectively connected to the two second lifting rods; each driving piece is connected to the second lifting rod respectively and used for changing an included angle between the second lifting rod and the sliding rail; each locking assembly is connected to the first lifting rod and used for limiting the sliding of the first lifting rod relative to the sliding rail. The lifting device for the aviation seat provided by the utility model is simple in structure, high in stability and convenient to operate.
Description
Technical Field
The utility model relates to the technical field of aviation seats, in particular to a lifting device for an aviation seat.
Background
With the continuous progress of society, the continuous development of economy and the progress of aviation industry, most people can select a novel and rapid transportation means, namely an airplane, to go out. The airplane is provided with a row of seats for customers to rest, most of the seats are standard aviation seats with uniform fixed height, and a small number of the seats on the airplane can be lifted and lowered in an adjustable mode.
Common aviation seat lift adjusting device includes parallel link mechanism, tower-shaped mechanism and fork mechanism, but parallel link mechanism part is more, and weight is overweight partially, and tower-shaped mechanism is difficult to satisfy dynamic impact strength requirement, and traditional fork mechanism seat shakes the momentum great, influences accurate nature and the security that the aircraft was controlled. Patent document CN109969403A discloses a device for adjusting the lift of an aircraft seat, which uses the cooperation of a motor, a gear, a rack, a lifting rod, a first rotating wheel, a second rotating wheel, a third rotating wheel and a reduction gear to realize the lift of the aircraft seat, and the device has a complex structure and is inconvenient to maintain.
SUMMERY OF THE UTILITY MODEL
In view of the above, it is desirable to provide a lifting device for an aircraft seat, which solves the problem of complex structure of the lifting device for the aircraft seat in the prior art.
The utility model provides a lifting device for an aviation seat, which comprises a slide rail group, two lifting rod groups, a first connecting piece, at least one driving piece and at least one locking assembly, wherein the slide rail group comprises two slide rails arranged at intervals; the two lifting rod groups are arranged in one-to-one correspondence with the two slide rails, each lifting rod group comprises a first lifting rod and a second lifting rod, the middle part of each first lifting rod is hinged to the middle part of each second lifting rod, one end of each first lifting rod is slidably inserted into the corresponding slide rail, and one end of each second lifting rod is hinged to the corresponding slide rail; two ends of the first connecting piece are respectively connected to the two second lifting rods; each driving piece is connected to the second lifting rod respectively and used for changing an included angle between the second lifting rod and the sliding rail; each locking assembly is connected to the first lifting rod and used for limiting the sliding of the first lifting rod relative to the sliding rail.
Further, locking Assembly includes dead lever, lock sleeve, lock axle and elastic component, the dead lever is followed the direction of rise fixed connection of lifter group is in one of them slide rail, the blind hole has been seted up to lock sleeve one end, the lock sleeve passes through the blind hole activity is inserted and is located the upper end of dead lever, the lock sleeve have one with blind hole vertically through-hole, other end fixed connection in through-hole, the activity of lock axle one end are worn to locate through-hole, other end fixed connection in first lifter, the aperture of through-hole is greater than the diameter of lock axle, through-hole inner wall lower part has the internal thread, the lock axle with one side of through-hole lower part contact have with interior screw-thread fit's external screw thread, the elastic component cover is located the dead lever just is located the dead lever with between the lock sleeve.
Furthermore, the locking assembly further comprises an adjusting piece, one end of the adjusting piece is hinged to the sliding rail, the middle of the adjusting piece abuts against the locking sleeve, and the adjusting piece is used for adjusting the relative position of the locking sleeve relative to the fixing rod.
Further, the elastic member is a spring.
Furthermore, locking Assembly is two, two locking Assembly and two lifter group one-to-one, two the dead lever is connected respectively in two that correspond the slide rail, two the one end of lock axle is fixed connection respectively in the first lifter that corresponds.
Furthermore, elevating gear for aviation seat still includes the connecting rod, the both ends of connecting rod are connected respectively in two first lifter, two the one end of lock axle all connect in the connecting rod.
Furthermore, the adjusting device further comprises an operating lever, and two ends of the operating lever are respectively connected to one ends of the two adjusting levers, which are far away from the sliding rail.
Furthermore, the number of the driving parts is two, and the two driving parts are respectively in one-to-one correspondence with the two second lifting rods.
Furthermore, the driving member is an air spring, a piston end of the air spring is connected to the corresponding second lifting rod, and the other end of the air spring is fixedly connected to the corresponding sliding rail.
Furthermore, the lifting device also comprises a supporting piece, and two ends of the supporting piece are respectively connected to the two first lifting rods.
Compared with the prior art, the lifting device for the aviation seat is characterized in that the first lifting rod and the second lifting rod are hinged in a crossed mode, the driving piece drives the second lifting rod to rotate relative to the sliding rail, the second lifting rod drives the first lifting rod to slide along the sliding rail, the height of the aviation seat is adjusted by changing the included angle between the first lifting rod and the second lifting rod, the locking assembly is adopted to limit the sliding of the first lifting rod so as to fix the position of the lifting rod group, the two sliding rails and the two lifting rod groups are adopted, the lifting device is stable and simple in structure, and meanwhile the driving piece is used for controlling the rotation of the lifting rods, so that time and labor are saved.
The foregoing is a summary of the present invention, and in order to provide a clear understanding of the technical means of the present invention and to be implemented in accordance with the present specification, the following is a detailed description of the preferred embodiments of the present invention.
Drawings
FIG. 1 is a schematic structural view of an embodiment of a lifting device for an airline seat according to the present invention;
FIG. 2 is a schematic structural view of another angle in the present embodiment;
FIG. 3 is a schematic structural view of another angle in the present embodiment;
fig. 4 is a schematic structural view of a locking assembly in an embodiment of the present invention.
Detailed Description
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate preferred embodiments of the utility model and together with the description, serve to explain the principles of the utility model and not to limit the scope of the utility model.
As shown in fig. 1 to 4, the lifting device for an aircraft seat according to an embodiment of the present invention includes a slide rail set 1, two lifting rod sets 2, a first connecting member 3, at least one driving member 4, and at least one locking assembly 5, where the slide rail set 1 includes two slide rails 11 arranged at intervals; the two lifting rod groups 2 are arranged corresponding to the two slide rails 11 one by one, each lifting rod group 2 comprises a first lifting rod 21 and a second lifting rod 22, the middle part of each first lifting rod 21 is hinged to the middle part of each second lifting rod 22, one end of each first lifting rod 21 is slidably inserted into the corresponding slide rail 11, and one end of each second lifting rod 22 is hinged to the corresponding slide rail 11; two ends of the first connecting piece 3 are respectively connected to the two second lifting rods 22; each driving member 4 is connected to the second lifting rod 22, and is used for changing an included angle between the second lifting rod 22 and the slide rail 11; each locking assembly 5 is connected to the first lifting rod 21, and is configured to limit the sliding of the first lifting rod 21 relative to the sliding rail 11.
It should be noted that the first lifting rod 2 and the second lifting rod 22 are hinged to each other to form a fork shape, the aircraft seat is connected to the upper ends of the first lifting rod 21 and the second lifting rod 22, wherein the first lifting rod 21 can slide along the slide rail 11, the second lifting rod 22 can rotate relative to the slide rail 11, the driving member 4 drives the second lifting rod 22 to rotate relative to the slide rail 11 to change the relative angle between the first lifting rod 21 and the second lifting rod 22, so as to drive the first lifting rod 21 to slide along the slide rail 11, change the included angle between the first lifting rod 21 and the second lifting rod 22 to change the height of the aircraft seat, and by setting the first connecting member 3, the linkage of the two lifting rod sets can be realized, and by fixing the position of the first lifting rod 21 relative to the slide rail 11 by using the locking member 5, the height of the aircraft seat can be fixed.
It should be noted that the two slide rails 11 may be distributed in parallel, may also be distributed in a splayed shape, may also be distributed in a V shape, may be distributed relatively, may also be distributed in a staggered shape, and it should be understood that the first lifting rod 21 may only be required to slide along it; when the two slide rails 11 are arranged in a non-parallel manner, the length of the first connecting piece 3 can be adjusted, and when the two slide rails 11 are arranged in a parallel manner, the length of the first connecting piece 3 is fixed or can be adjusted; specifically, in the present embodiment, the two slide rails 11 are distributed in parallel, and the first connecting member 3 is a certain length.
As a preferred embodiment, the locking assembly 5 includes a fixing rod 51, a locking sleeve 52, a locking shaft 53 and an elastic member 54, the fixing rod 51 is fixedly connected to one of the slide rails 11 along the lifting direction of the lifting rod group 2, one end of the locking sleeve 52 is provided with a blind hole, the locking sleeve 52 is movably inserted into the upper end of the fixed rod 51 through the blind hole, the locking sleeve 52 is provided with a through hole vertical to the blind hole, one end of the locking shaft 53 is movably inserted into the through hole, the other end is fixedly connected to the first lifting rod 21, the aperture of the through hole is larger than the diameter of the locking shaft 53, the lower part of the inner wall of the through hole is provided with internal threads, the side of the locking shaft 53 contacting the lower portion of the through hole has an external thread matching the internal thread, the elastic member 54 is sleeved on the fixing rod 51 and located between the fixing rod and the locking sleeve.
It should be noted that, in the present embodiment, the elastic member 54 is a spring structure, and it is understood that, in other embodiments, the elastic member 54 may be other mechanisms with elasticity, such as an elastic steel sheet, etc.
It should be noted that, in the present embodiment, a reinforcing member is connected between the two slide rails 11, so as to ensure the relative stability of the positions of the two slide rails 11, wherein the fixing rod 51 is connected to the reinforcing member.
It should be noted that, in the present embodiment, the locking assembly 5 further includes a housing, and the housing is covered outside the fixing rod 51, the locking sleeve 52 and the elastic member 54 to prevent dust from falling inside the housing.
It should be noted that, when the locking assembly 5 is in the natural state under the action of the elastic member 54, the lock shaft 53 abuts against the lower portion of the locking sleeve 52, and since the lock shaft 53 and the lower portion of the locking sleeve 52 have the mutually matched threads, the lock shaft 53 is in the fixed state, and the lock shaft 53 is connected with the first lifting rod 21, so that the first lifting rod 21 cannot slide along the slide rail 11, the included angle between the second lifting rod 22 and the first lifting rod 21 is not changed, and the height of the aircraft seat is not changed.
When the aircraft seat needs to be lifted, the locking sleeve 52 is pressed to slide downwards along the fixing rod 51 and compress the spring, at this time, the locking shaft 53 is separated from the lower part of the locking sleeve 52, the locking shaft 53 can slide along the locking sleeve 52, the driving piece 4 drives the second lifting rod 22 to rotate to enlarge the angle between the second lifting rod 22 and the slide rail 11, the second lifting rod 22 rotates to drive the bottom end of the first lifting rod 21 to move towards the direction close to the second lifting rod 22 along the slide rail, so that the included angle between the first lifting rod 21 and the second lifting rod 22 is reduced, the aircraft seat is lifted, after the aircraft seat is adjusted to a certain position, the locking sleeve 52 is released, the locking sleeve 52 moves upwards under the action of the spring force until the locking sleeve 53 abuts against, the position of the locking shaft 53 is fixed, and the relative position of the first lifting rod 21 and the second lifting rod 22 is fixed.
When the aviation seat needs to be lowered, the driving part 3 drives the second lifting rod 22 to rotate to reduce the included angle between the second lifting rod 22 and the slide rail 11, and meanwhile, the bottom end of the first lifting rod 21 moves along the slide rail 11 in the direction away from the bottom end of the second lifting rod 22 to increase the included angle between the second lifting rod 22 and the slide rail, so that the aviation seat is lowered.
As a preferred embodiment, the locking assembly 5 further includes an adjusting member 55, one end of the adjusting member 55 is hinged to the slide rail 11, and a middle portion of the adjusting member 55 abuts against the locking sleeve 52, so as to adjust a relative position between the locking sleeve 52 and the fixing rod 51.
It should be noted that, by providing the adjusting rod 55, the locking sleeve 52 can be driven to slide relative to the fixing rod 51 by pressing the adjusting member 55.
It should be noted that, in the present embodiment, one end of the adjustment lever 55 is hinged to the reinforcement member.
As a preferred embodiment, there are two locking assemblies 5, two locking assemblies 5 correspond to two lifting rod sets 2 one by one, the two fixing rods 51 are respectively connected to the two corresponding slide rails 11, and one end of each of the two locking shafts 53 is respectively and fixedly connected to the corresponding first lifting rod 21.
It should be noted that, two locking assemblies 5 are arranged to correspond to the two lifting rod sets 2 one by one, each lifting rod set 2 is controlled by the independent locking assembly 5, the locking strength and precision can be ensured, and the two locking assemblies 5 are symmetrically distributed, so that the structural stability of the device can be improved.
As a preferred embodiment, the lifting device for aviation seats further comprises a connecting rod 6, two ends of the connecting rod 6 are respectively connected to the two first lifting rods 21, and one ends of the two locking shafts 53 are both connected to the connecting rod 6.
Through setting up connecting rod 6, set up two lock axles 53 on same connecting rod 6, can guarantee the synchronism of two lock axles 53 movements.
In a preferred embodiment, the device further comprises an operating lever 7, and two ends of the operating lever 7 are respectively connected to one ends of the two adjusting rods 55 far away from the slide rail.
It should be noted that, by providing the operating lever 7, the two adjusting members 55 can be pressed simultaneously when the operating lever 7 is pressed, so as to drive the two locking sleeves 52 to slide, thereby ensuring the synchronism of the two locking assemblies 5.
In a preferred embodiment, there are two driving members 4, and the two driving members 4 correspond to the two second lifting rods 22 one by one.
It should be noted that, through setting up two driving pieces 4, can increase drive power, guarantee to adjust efficiency, increase the equilibrium and the stability that two lifter groups 2 go up and down simultaneously, at this moment, first connecting piece 3 acts as support piece, increases the joint strength between two lifter groups 2.
Specifically, in the present embodiment, the driving member 4 is in the form of a gas spring, a piston end of the gas spring is connected to the second lifting rod 22, and the other end is connected to the corresponding slide rail 11; when the aircraft seat needs to be lifted, the air spring is utilized, the piston rod can be automatically lifted to be long under the condition that the locking force applied to the second lifting rod 22 disappears, so that the height of the aircraft seat is adjusted, and the driving piece 4 does not need to be controlled to adjust the angle of the second lifting rod 22 relative to the sliding rail 11; when the aviation seat needs to be lowered, under the condition that the locking assembly 5 is unlocked, a passenger sits on the seat, and a certain force is applied downwards to overcome the elastic force of the gas spring, so that the bottom ends of the first lifting rod 21 and the second lifting rod 22 can be driven to move towards the directions away from each other.
As a preferred embodiment, the lifting device further comprises a supporting member 8, and two ends of the supporting member 8 are respectively connected to the two first lifting rods 21.
Through setting up support piece 8, can increase the structural strength between two first lifter bars 21, guarantee the motion synchronism of two first lifter bars 21 simultaneously.
Compared with the prior art, the embodiment of the utility model at least has the following effects:
1. the two locking assemblies are arranged to control the movement of the two first lifting rods respectively, so that the accuracy of the locking assemblies is guaranteed, and the operating lever is adopted to control the unlocking and locking states of the two locking assemblies, so that the synchronous movement of the two lifting rod groups is realized;
2. the device has simple structure and convenient maintenance;
3. two locking assemblies are adopted, so that the constraint force on the lifting rod group is improved, and the stability and the safety of the structure are ensured.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention.
Claims (10)
1. A lifting device for an aircraft seat, comprising:
the sliding rail set comprises two sliding rails which are arranged at intervals;
the two lifting rod groups are arranged in one-to-one correspondence with the two slide rails, each lifting rod group comprises a first lifting rod and a second lifting rod, the middle part of each first lifting rod is hinged to the middle part of each second lifting rod, one end of each first lifting rod is slidably inserted into the corresponding slide rail, and one end of each second lifting rod is hinged to the corresponding slide rail;
the two ends of the first connecting piece are respectively connected to the two second lifting rods;
the driving pieces are respectively connected to the second lifting rod and used for changing an included angle between the second lifting rod and the sliding rail; and
and each locking assembly is connected to the first lifting rod and used for limiting the sliding of the first lifting rod relative to the sliding rail.
2. The lift device for aircraft seats of claim 1, wherein the locking assembly comprises a securing rod, a locking sleeve, a locking shaft and a resilient member, the fixed rod is fixedly connected with one of the slide rails along the lifting direction of the lifting rod group, one end of the locking sleeve is provided with a blind hole, the locking sleeve is movably inserted into the upper end of the fixed rod through the blind hole, the locking sleeve is provided with a through hole vertical to the blind hole, one end of the locking shaft is movably arranged in the through hole in a penetrating way, the other end of the locking shaft is fixedly connected with the first lifting rod, the aperture of the through hole is larger than the diameter of the lock shaft, the lower part of the inner wall of the through hole is provided with internal threads, the side of the lock shaft contacting with the lower part of the through hole is provided with an external thread matched with the internal thread, the elastic piece is sleeved on the fixed rod and is positioned between the fixed rod and the locking sleeve.
3. The lift device for aircraft seats of claim 2, wherein the locking assembly further comprises an adjusting member, one end of the adjusting member is hinged to the slide rail and the middle portion of the adjusting member abuts against the locking sleeve, so as to adjust the relative position of the locking sleeve with respect to the fixing rod.
4. The lift device of claim 2 wherein said resilient member is a spring.
5. The lifting device for an aircraft seat as claimed in claim 2, wherein there are two locking assemblies, two locking assemblies are corresponding to two lifting rod sets one by one, two fixing rods are respectively connected to the two corresponding slide rails, and one end of each of the two locking shafts is respectively fixedly connected to the corresponding first lifting rod.
6. The aircraft seat lifting device according to claim 5, further comprising a connecting rod, wherein two ends of the connecting rod are respectively connected to the two first lifting rods, and one ends of the two lock shafts are both connected to the connecting rod.
7. The lift device for an aircraft seat according to claim 3, further comprising an operating lever, wherein both ends of the operating lever are respectively connected to the ends of the two adjusting rods that are away from the slide rail.
8. The lift device for an airline seat according to claim 1, wherein there are two of the driving members, and the two driving members correspond to the two second lift levers one-to-one, respectively.
9. The lift mechanism of claim 7, wherein said drive member is a gas spring, and the piston end of said gas spring is connected to the corresponding second lifting rod, and the other end of said gas spring is fixedly connected to the corresponding slide rail.
10. The lift device for an airline seat according to claim 1, further comprising a support member, both ends of which are connected to the two first lift levers, respectively.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122373658.5U CN215753042U (en) | 2021-09-28 | 2021-09-28 | Lifting device for aviation seat |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122373658.5U CN215753042U (en) | 2021-09-28 | 2021-09-28 | Lifting device for aviation seat |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN215753042U true CN215753042U (en) | 2022-02-08 |
Family
ID=80092878
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122373658.5U Active CN215753042U (en) | 2021-09-28 | 2021-09-28 | Lifting device for aviation seat |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN215753042U (en) |
-
2021
- 2021-09-28 CN CN202122373658.5U patent/CN215753042U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102905579A (en) | Counterforce mechanism for backrest of chair and chair incorporating the said | |
| CN103395490A (en) | Lifting-opening linkage structure for turn-over airliner cabin door | |
| CN106800254B (en) | A kind of elastic auxiliary actuating apparatus of horizontal drive Fork lifting platform | |
| CN109223360B (en) | Medical nursing sickbed capable of being lifted in linkage manner and inclining in multiple directions | |
| CN215753042U (en) | Lifting device for aviation seat | |
| CN104760700A (en) | Self-locking aero seat capable of adjusting height steplessly | |
| CN110477622A (en) | Desktop can any angle hovering desk | |
| CN109645666B (en) | Small table plate controlled by single motor and screw rod for automobile | |
| CN103231690B (en) | A kind of engineering special vehicle and fence sytsem thereof | |
| CN217624166U (en) | Vehicle-mounted unmanned aerial vehicle take-off and landing platform and vehicle | |
| CN201633919U (en) | Cabin door stay bar for airplane | |
| CN2309244Y (en) | Shock frame for vehicle seat | |
| CN201597758U (en) | Elevating mechanism for boarding vehicle of airplane | |
| CN211968435U (en) | Automatic leveling mechanism of 3D printer | |
| CN212532153U (en) | Bottom horizontal driving scissor fork lifting table | |
| CN114274848A (en) | Zero-gravity seat | |
| CN211672902U (en) | Multi-column synchronous pneumatic lifting system | |
| CN217227949U (en) | Novel aircraft fuselage bracket | |
| CN204587309U (en) | The self-locking type aero seat that the stepless height of a kind of energy regulates | |
| CN205575462U (en) | A disabled person's car elevating system for rail transit train | |
| CN111997356A (en) | Green building templates of accurate lift type | |
| CN218320555U (en) | Sliding connection structure and erecting equipment | |
| CN112224420B (en) | Crash-resistant seat capable of changing load and absorbing energy | |
| CN220349541U (en) | Headrest lifting mechanism of automobile seat | |
| CN219954394U (en) | Electric actuator with angular travel |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |