CN109878738B - Aviation seat angle adjusting device - Google Patents
Aviation seat angle adjusting device Download PDFInfo
- Publication number
- CN109878738B CN109878738B CN201910170296.4A CN201910170296A CN109878738B CN 109878738 B CN109878738 B CN 109878738B CN 201910170296 A CN201910170296 A CN 201910170296A CN 109878738 B CN109878738 B CN 109878738B
- Authority
- CN
- China
- Prior art keywords
- floating
- base
- locking
- seat
- state
- 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
- 238000006243 chemical reaction Methods 0.000 claims description 15
- 238000013016 damping Methods 0.000 claims description 12
- 238000005192 partition Methods 0.000 claims description 9
- 230000033001 locomotion Effects 0.000 claims description 7
- 230000000694 effects Effects 0.000 claims description 4
- 230000005540 biological transmission Effects 0.000 claims description 3
- 230000002093 peripheral effect Effects 0.000 claims description 3
- 230000001105 regulatory effect Effects 0.000 claims 1
- 238000000034 method Methods 0.000 abstract description 4
- 238000009434 installation Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 206010020649 Hyperkeratosis Diseases 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000003028 elevating effect Effects 0.000 description 1
Images
Landscapes
- Seats For Vehicles (AREA)
- Chairs Characterized By Structure (AREA)
Abstract
The invention discloses an angle adjusting device for an aviation seat, which is provided with a floating assembly, wherein the floating assembly can automatically adjust the inclined state of a base according to the shaking state of an aviation aircraft so as to keep the upper end of the base in a horizontal state as much as possible, so that even if the aircraft is in a bumping state, the floating assembly can be rotationally adjusted according to bumping of the aircraft, the seat is kept in the horizontal state as much as possible, and the comfort and the stability are ensured as much as possible; the invention can also lock and convert the floating assembly, so that passengers can select the floating assembly according to requirements, the switching between a locking state and a floating state is realized, the use performance is ensured, the problems that the conventional aviation seat can only be longitudinally adjusted and cannot be transversely adjusted in the actual use process are solved, the seat and the base rotate through the bearing, and when the seat rotates to a proper angle, the lifting column and the limiting hole are mutually clamped to fix the angle of the seat.
Description
Technical Field
The invention relates to the technical field of seats, in particular to an angle adjusting device for an aviation seat.
Background
The aircraft or the high-speed rail business cabin is provided with more high-grade seats to provide comfortable riding environment, the backrest angle can be adjusted by applying more aviation seats, but in the actual use process, the backrest angle is only adjusted, so that the space behind the seats can be occupied, and the activity space of passengers in the back row is squeezed. Furthermore, during flight, the aircraft is prone to jolting and oscillating, which can cause great discomfort to passengers and affect riding comfort.
Accordingly, the present invention provides an angle adjustment device for an aircraft seat that solves the problems set forth above in the background.
Disclosure of Invention
The invention aims to provide an aviation seat angle adjusting device to solve the problems in the prior art.
In order to achieve the purpose, the invention provides the following technical scheme:
an aviation seat angle adjusting device comprises a shell, a base, a mounting seat and a controller, wherein the bottom of the shell is connected and mounted on the upper part of the base, the bottom of the base is connected and mounted on the upper part of the mounting seat,
the bottom of the base is installed in the installation seat by adopting a floating assembly, and the floating assembly can automatically adjust the inclination state of the base according to the shaking state of the aircraft, so that the upper end of the base is kept in a horizontal state as much as possible;
the floating assembly is also provided with a locking conversion piece, and the locking conversion piece is controlled by the controller so as to control the floating assembly to be switched between a floating state and a locking state by the locking conversion piece;
when the floating assembly is in the floating state, the floating assembly automatically adjusts the inclination state of the base according to the shaking state of the aircraft;
when the floating assembly is in the locking state, the floating assembly is locked by the locking conversion piece so as to enable the base and the mounting seat to be in locking rigid fixed connection;
the bottom of the shell is rotatably arranged on the base around the central axis of the shell so as to adjust the angle of the shell;
an aviation seat is arranged on the shell and can move back and forth on the top of the shell so as to adjust the front and back position of the aviation seat.
Further, as the preferred, the floating assembly comprises a floating support rod, a floating adjustment driver and a damping sleeve, wherein the upper end of the mounting seat is provided with an accommodating adjustment groove, two sides of the accommodating adjustment groove are provided with hinge limiting grooves which are oppositely arranged, two sides of the bottom of the base are provided with hinge columns which are oppositely arranged, the hinge columns are rotatably hinged in the hinge limiting grooves, the damping sleeve is further arranged between the inner wall of the hinge limiting groove and the outer peripheral wall of the hinge column, the damping sleeve enables the base to be adjusted in a floating mode around the hinge line of the hinge column under certain damping, the bottom wall of the accommodating adjustment groove of the mounting seat is further provided with a plurality of floating adjustment drivers which are circumferentially arranged, the output end of each floating adjustment driver is connected with the floating support rod, and the top of the floating support rod is connected with the bottom wall of the base by adopting a universal ball hinge, the controller controls the telescopic motion of each floating adjusting driver to adjust the floating angle of the base.
Further, as preferred, the locking conversion part includes locking dish, atmospheric pressure lock sleeve and locking air pump, wherein, the locking dish is fixed to be set up hold on the installation base of regulation and control groove lower part, the last perforation of having seted up of the position that corresponds the bracing piece floats on the locking dish, it is provided with to go up to perforate the atmospheric pressure lock sleeve, the bracing piece that floats follows upwards pass in the atmospheric pressure lock sleeve, each atmospheric pressure lock sleeve with locking air pump intercommunication, the atmospheric pressure lock sleeve can be right the bracing piece that floats locks fixedly.
Further, preferably, the floating adjustment actuator is an air cylinder, a hydraulic cylinder, or a magnetostrictive actuator.
Further, as preferred, the constant head tank has been seted up on the top of base, the fixed outer lane that is provided with the bearing in inside of constant head tank, just the bottom at the casing is fixed at the top of the inner circle of bearing, the rectangular channel has been seted up to the inside of base, the through-hole has been seted up to one side of rectangular channel, the through-hole communicates with the rectangular channel each other, the inside of through-hole is provided with the lift post, spacing hole has been seted up to the bottom of casing, the tip of lift post can stretch into/stretch out the inside in spacing hole.
Further, as preferred, the inner wall fixedly connected with pivot of rectangular channel, the outside fixedly connected with gear of pivot, the inner wall at the through-hole is installed to the tip of gear, the gear meshes the transmission with the tooth on the lift post, so that by gear drive the elevating movement of lift post.
Further, as preferred, the outer wall of base has seted up and has accomodate the groove, the inside in accomodating the groove is provided with changes the handle, change the outer wall that the handle runs through the base, change the end at the pivot.
Further, as preferred, the top of casing is provided with the baffle, the bottom fixedly connected with truckle of baffle, the outer fixed surface of baffle is connected with the cushion, the both sides of baffle are provided with the buckle, fixedly connected with hinge between buckle and the baffle.
Further, as preferred, the top surface of casing has seted up the spout, the truckle is installed in the inside of spout, the draw-in groove has been seted up to the both sides inner wall of casing, the end fixing of buckle is in the inside of draw-in groove.
Further, as preferred, the front surface of casing fixedly connected with callus on the sole, the both sides top fixedly connected with of casing holds up the handle, the tip fixedly connected with back of casing, the surface fixedly connected with cushion of back.
Compared with the prior art, the invention has the beneficial effects that:
1. the invention is provided with the floating assembly, the floating assembly can automatically adjust the inclined state of the base according to the shaking state of the aviation aircraft so as to ensure that the upper end of the base is kept in a horizontal state as much as possible, and thus, even if the aircraft is in a bumpy state, the floating assembly can be rotationally adjusted according to the bumping of the aircraft so as to ensure that the seat is kept in the horizontal state as much as possible, ensure the comfort and the stability as much as possible and improve the riding comfort of passengers;
2. the invention can also lock and convert the floating assembly, thus the passenger can select the floating assembly according to the requirement, the switching between the locking state and the floating state is realized, and the service performance is ensured;
3. the invention solves the problems that the space behind the seat can be occupied and the activity space of passengers in the back row can be extruded only by adjusting the angle of the backrest in the actual use process of the conventional aviation seat through the designed bearing, the seat and the base rotate through the bearing, the lifting column is controlled to move to be clamped with the limiting hole when the seat rotates to a proper angle, and the angle between the seat and the base is fixed.
4. Through baffle, truckle, buckle and the draw-in groove of design, solved aviation seat in the in-service use process, only adjust the back angle, then can occupy the space behind one's back, extrude back row passenger's activity space's problem, the cushion removes through the truckle of baffle bottom, when treating that the cushion adjusts comparatively comfortable position, the mutual block of control buckle and draw-in groove makes the cushion fix in this position.
Drawings
FIG. 1 is a schematic structural view of an aircraft seat angle adjustment device;
FIG. 2 is a schematic structural view of a housing of an aircraft seat angle adjustment device;
FIG. 3 is a schematic structural diagram of a base in the angle adjustment device of an aviation seat;
FIG. 4 is a schematic structural view of a lifting column in the angle adjusting device of an aviation seat;
FIG. 5 is a schematic structural view of a partition plate in the angle adjusting device of an aircraft seat;
fig. 6 is a schematic structural diagram of a caster in an aircraft seat angle adjusting device.
FIG. 7 is a schematic cross-sectional view of a float assembly of an aircraft seat angle adjustment assembly;
FIG. 8 is a schematic top plan view of a float adjustment actuator arrangement for a float assembly of an aircraft seat angle adjustment device;
FIG. 9 is a schematic view of the float adjustment of the float assembly of an aircraft seat angle adjustment device.
Detailed Description
Referring to fig. 1 to 9, in an embodiment of the present invention, an aviation seat angle adjusting device includes a housing 2, a base 3, a mounting seat 0, and a controller, wherein a bottom of the housing 2 is connected to and mounted on an upper portion of the base 3, a bottom of the base 3 is connected to and mounted on an upper portion of the mounting seat 0,
the bottom of the base 3 is installed in the installation seat 0 by adopting a floating assembly, and the floating assembly can automatically adjust the inclined state of the base 3 according to the shaking state of the aircraft, so that the upper end of the base 3 is kept in a horizontal state as much as possible;
the floating assembly is also provided with a locking conversion piece, and the locking conversion piece is controlled by the controller so as to control the floating assembly to be switched between a floating state and a locking state by the locking conversion piece;
when the floating assembly is in the floating state, the floating assembly automatically adjusts the inclination state of the base 3 according to the shaking state of the aircraft;
in the locked state of the floating assembly, the floating assembly is locked by the locking conversion piece so as to enable the base 3 and the mounting seat 0 to be in locking rigid fixed connection;
the bottom of the housing 2 is rotatably arranged on the base 3 around the central axis thereof so as to adjust the angle of the housing 2;
an aviation seat is arranged on the shell 2 and can move back and forth on the top of the shell 2 so as to adjust the front and back positions of the aviation seat.
In this embodiment, the floating assembly includes a floating support rod 26, a floating adjustment driver 24 and a damping sleeve 29, wherein the upper end of the mounting seat 0 is provided with a receiving adjustment groove, the two sides of the receiving adjustment groove are provided with hinge limiting grooves 27 which are oppositely arranged, the two sides of the bottom of the base 3 are provided with hinge columns 30 which are oppositely arranged, the hinge columns 30 are rotatably arranged in the hinge limiting grooves 27 in a hinge manner, the damping sleeve 29 is further arranged between the inner wall of the hinge limiting grooves 27 and the peripheral wall of the hinge columns 30, the damping sleeve 29 enables the base 3 to be adjusted in a floating manner around the hinge line of the hinge columns 30 under certain damping, the bottom wall of the receiving adjustment groove of the mounting seat 0 is further provided with a plurality of floating adjustment drivers 24 which are circumferentially arranged, the output end of the floating adjustment driver 24 is connected with the floating support rod 26, the top of the floating support rod 26 is connected with the bottom wall of the base 3 by a universal ball joint 28, and the floating angle of the base 3 is adjusted by controlling the telescopic motion of each floating adjusting driver 24 by the controller.
As a preferred embodiment, the locking conversion part includes a locking disc 31, an air pressure locking sleeve 25 and a locking air pump, wherein the locking disc 31 is fixedly disposed on the mounting base at the lower portion of the accommodating and controlling groove, an upper through hole is disposed on the locking disc 31 at a position corresponding to the floating support rod 26, the air pressure locking sleeve 25 is disposed in the upper through hole, the floating support rod 26 passes upward through the air pressure locking sleeve 25, each air pressure locking sleeve is communicated with the locking air pump, and the air pressure locking sleeve can lock and fix the floating support rod 26.
As a more preferred embodiment, the float adjustment actuator 24 is an air cylinder, a hydraulic cylinder, or a magnetostrictive actuator.
Wherein, constant head tank 14 has been seted up on the top of base 3, the fixed outer lane that is provided with bearing 8 in constant head tank 14's inside, just the bottom at casing 2 is fixed at the top of the inner circle of bearing 8, rectangular channel 16 has been seted up to the inside of base 3, through-hole 13 has been seted up to one side of rectangular channel 16, through-hole 13 and rectangular channel 16 communicate each other, the inside of through-hole 13 is provided with lift post 10, spacing hole 9 has been seted up to the bottom of casing 2, the tip of lift post 10 can stretch into/stretch out the inside in spacing hole 9.
In order to control the lifting of the lifting column 10, in fig. 4, a rotating shaft 15 is fixedly connected to the inner wall of the rectangular groove 16, a gear 17 is fixedly connected to the outer side of the rotating shaft 15, the end of the gear 17 is mounted on the inner wall of the through hole 13, and the gear 17 is in meshing transmission with the teeth on the lifting column 10, so that the lifting column is driven to move up and down by the gear.
To facilitate control of the switches of the steering mechanism, in fig. 3: the outer wall of the base 3 is provided with a containing groove 11, a rotating handle 12 is arranged inside the containing groove 11, the rotating handle 12 penetrates through the outer wall of the base 3, and the rotating handle 12 is fixed at the end part of the rotating shaft 15.
In order to facilitate the movement of the seat cushion 5, in fig. 5: the top of casing 2 is provided with baffle 21, the bottom fixedly connected with truckle 23 of baffle 21, the outer fixed surface of baffle 21 is connected with cushion 5, the both sides of baffle 21 are provided with buckle 19, fixedly connected with hinge 20 between buckle 19 and the baffle 21.
To facilitate movement of the partition 21, in fig. 6: the outer surface of the top end of the shell 2 is provided with a sliding groove 22, the caster 23 is installed inside the sliding groove 22, the inner walls of the two sides of the shell 2 are provided with clamping grooves 18, and the end portions of the buckles 19 are fixed inside the clamping grooves 18.
To facilitate the use of the seat, in fig. 1: the front surface of the shell 2 is fixedly connected with a foot pad 4, the top ends of the two sides of the shell 2 are fixedly connected with handles 6, the end part of the shell 2 is fixedly connected with a backrest 1, and the outer surface of the backrest 1 is fixedly connected with a back cushion 7.
The working principle of the invention is as follows: when the aircraft seat is used, when the floating assembly is in the floating state and the fuselage of the aircraft 32 oscillates, the floating assembly of the seat automatically adjusts the inclined state of the base 3 according to the shaking state of the aircraft so as to enable the upper end of the base 3 to be kept in a horizontal state as much as possible, thus the comfort of the seat can be ensured, and if a passenger does not need the state mode, the floating assembly can be locked by the locking assembly so as to enable the floating assembly to be in locking rigid fixed connection with the mounting seat 0 in the locking state. Meanwhile, the rotating handle 12 inside the accommodating groove 11 on the outer side of the rotating base 3 is rotated, the rotating handle 12 drives the gear 17 to rotate through the rotating shaft 15, the sawtooth part of the gear 17 is meshed with the thread part of the lifting column 10, the gear 17 rotates to drive the lifting column 10 to move up and down, the lifting column 10 is accommodated inside the through hole 13, the lifting column 10 is not clamped with the limiting hole 9, the shell 2 can rotate through the bearing 8, after the shell 2 is rotated to a target direction, the lifting column 10 is lifted from the through hole 13 by reversely rotating the rotating handle 12, the lifting column 10 is clamped with the limiting hole 9 at the bottom of the shell 2, the shell 2 and the base 3 are fixed in directions, the partition plate 21 slides along the sliding groove 22 through the caster 23, the buckle 19 rotates with the hinge 20 as a circle center, the buckle 19 is clamped with the clamping groove 18, and the partition plate 21 and the shell 2 are fixed. 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 person skilled in the art should be considered to be within the technical scope of the present invention, and the technical solutions and the inventive concepts thereof according to the present invention are equivalent to or changed within the technical scope of the present invention.
Claims (9)
1. An aviation seat angle adjusting device comprises a shell (2), a base (3), a mounting seat (0) and a controller, wherein the bottom of the shell (2) is connected and mounted on the upper part of the base (3), the bottom of the base (3) is connected and mounted on the upper part of the mounting seat (0), and the aviation seat angle adjusting device is characterized in that,
the bottom of the base (3) is mounted in the mounting seat (0) by adopting a floating assembly, and the floating assembly can automatically adjust the inclined state of the base (3) according to the shaking state of the aircraft, so that the upper end of the base (3) is kept in a horizontal state;
the floating assembly is also provided with a locking conversion piece, and the locking conversion piece is controlled by the controller so as to control the floating assembly to be switched between a floating state and a locking state by the locking conversion piece;
the floating assembly is in the floating state and automatically adjusts the inclination state of the base (3) according to the shaking state of the aircraft;
in the locking state of the floating assembly, the floating assembly is locked by the locking conversion piece so as to enable the base (3) and the mounting seat (0) to be in locking rigid fixed connection;
the bottom of the shell (2) is arranged on the base (3) in a rotating mode around the central axis of the base so as to adjust the angle of the shell (2);
an aviation seat is arranged on the shell (2) and moves back and forth on the top of the shell (2) so as to adjust the front and back positions of the aviation seat;
the floating assembly comprises a floating support rod (26), a floating adjusting driver (24) and a damping sleeve (29), wherein the upper end of the mounting seat (0) is provided with a containing adjusting groove, two sides of the containing adjusting groove are provided with hinged limiting grooves (27) which are oppositely arranged, two sides of the bottom of the base (3) are provided with hinged columns (30) which are oppositely arranged, the hinged columns (30) are hinged and rotatably arranged in the hinged limiting grooves (27), the damping sleeve (29) is further arranged between the inner wall of the hinged limiting grooves (27) and the outer peripheral wall of the hinged columns (30), the damping sleeve (29) enables the base (3) to be wound around the hinged line of the hinged columns (30) under the damping effect for floating adjustment, and the bottom wall of the mounting seat (0) containing adjusting groove is further provided with a plurality of floating adjusting drivers (24) which are circumferentially arranged, the output end of the floating adjusting driver (24) is connected with the floating supporting rod (26), the top of the floating supporting rod (26) is connected with the bottom wall of the base (3) through a universal spherical hinge (28), and the controller controls the telescopic motion of each floating adjusting driver (24) to realize the adjustment of the floating angle of the base (3).
2. The aircraft seat angle adjusting device of claim 1, wherein the locking conversion part comprises a locking disc (31), an air pressure locking sleeve (25) and a locking air pump, wherein the locking disc (31) is fixedly arranged on the mounting base at the lower part of the accommodating and regulating groove, an upper through hole is formed in the locking disc (31) corresponding to the position of the floating support rod (26), the air pressure locking sleeve (25) is arranged in the upper through hole, the floating support rod (26) passes upwards from the air pressure locking sleeve (25), the air pressure locking sleeve is communicated with the locking air pump, and the air pressure locking sleeve can lock and fix the floating support rod (26).
3. An aircraft seat angle adjustment device according to claim 2, characterized in that the floating adjustment drive (24) is an air cylinder, a hydraulic cylinder or a magnetostrictive drive.
4. The aircraft seat angle adjusting device according to claim 2 or 3, characterized in that a positioning groove (14) is formed in the top end of the base (3), an outer ring of the bearing (8) is fixedly arranged inside the positioning groove (14), the top of the inner ring of the bearing (8) is fixed at the bottom of the housing (2), a rectangular groove (16) is formed inside the base (3), a through hole (13) is formed in one side of the rectangular groove (16), the through hole (13) is communicated with the rectangular groove (16), a lifting column (10) is arranged inside the through hole (13), a limiting hole (9) is formed in the bottom of the housing (2), and the end of the lifting column (10) can extend into/out of the limiting hole (9).
5. An angle adjusting device of an aircraft seat as claimed in claim 4, characterized in that the inner wall of the rectangular groove (16) is fixedly connected with a rotating shaft (15), the outer side of the rotating shaft (15) is fixedly connected with a gear (17), the end part of the gear (17) is installed on the inner wall of the through hole (13), and the gear (17) is in meshed transmission with teeth on the lifting column (10) so as to drive the lifting motion of the lifting column by the gear.
6. The aircraft seat angle adjusting device of claim 5, characterized in that the outer wall of the base (3) is provided with a receiving groove (11), a rotating handle (12) is arranged inside the receiving groove (11), the rotating handle (12) penetrates through the outer wall of the base (3), and the rotating handle (12) is fixed at the end of the rotating shaft (15).
7. An angle adjusting device for an aviation seat according to claim 6, characterized in that a partition plate (21) is arranged at the top end of the housing (2), casters (23) are fixedly connected to the bottom of the partition plate (21), a cushion (5) is fixedly connected to the outer surface of the partition plate (21), buckles (19) are arranged on two sides of the partition plate (21), and hinges (20) are fixedly connected between the buckles (19) and the partition plate (21).
8. The aircraft seat angle adjusting device according to claim 7, characterized in that the top end outer surface of the housing (2) is provided with a sliding groove (22), the caster (23) is installed inside the sliding groove (22), the inner walls of the two sides of the housing (2) are provided with clamping grooves (18), and the end parts of the buckles (19) are fixed inside the clamping grooves (18).
9. The aircraft seat angle adjusting device of claim 8, characterized in that a foot pad (4) is fixedly connected to the front surface of the shell (2), handles (6) are fixedly connected to the top ends of the two sides of the shell (2), a backrest (1) is fixedly connected to the end of the shell (2), and a back cushion (7) is fixedly connected to the outer surface of the backrest (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910170296.4A CN109878738B (en) | 2019-03-07 | 2019-03-07 | Aviation seat angle adjusting device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910170296.4A CN109878738B (en) | 2019-03-07 | 2019-03-07 | Aviation seat angle adjusting device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109878738A CN109878738A (en) | 2019-06-14 |
| CN109878738B true CN109878738B (en) | 2021-07-02 |
Family
ID=66931077
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910170296.4A Active CN109878738B (en) | 2019-03-07 | 2019-03-07 | Aviation seat angle adjusting device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109878738B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113789719B (en) * | 2021-07-25 | 2023-07-28 | 铁正检测科技有限公司 | Bridge bottom detection device |
| CN116002055B (en) * | 2023-03-27 | 2023-06-27 | 成都旺美达航空科技有限公司 | Authority-based aviation seat adjusting method, device and medium |
Family Cites Families (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2121371U (en) * | 1992-06-26 | 1992-11-11 | 刘锦标 | Automatic-adjusting level seat of plane and automobile |
| CN2177628Y (en) * | 1993-12-23 | 1994-09-21 | 刘锦标 | Self-adjustable horizontal chair for aircraft and automobile |
| CN2228305Y (en) * | 1995-01-20 | 1996-06-05 | 林圣栋 | Bed-chair level self-adjusting device |
| CN201534508U (en) * | 2009-11-19 | 2010-07-28 | 北京明航技术研究所 | Automatic balancing corona-protective chair |
| CN102336155A (en) * | 2011-09-02 | 2012-02-01 | 王宝根 | Anti-dizziness chair capable of being automatically balanced |
| US9493242B2 (en) * | 2011-12-23 | 2016-11-15 | B/E Aerospace, Inc. | Aircraft passenger seat and seat swivel assembly |
| CN103359287B (en) * | 2013-07-05 | 2016-06-01 | 哈尔滨东安发动机（集团）有限公司 | The electronic seat level(l)ing device of aircraft |
| WO2015061688A2 (en) * | 2013-10-24 | 2015-04-30 | Zodiac Seat Shells U.S. Llc | Seat unit for a vehicle cabin |
| CN204249860U (en) * | 2014-11-11 | 2015-04-08 | 芜湖瑞泰汽车零部件有限公司 | A kind of back seat backrest frames assembly |
| CN105730293A (en) * | 2014-12-12 | 2016-07-06 | 西安丁子电子信息科技有限公司 | Automobile-mounted self-balancing seat |
| CN105197038B (en) * | 2015-09-28 | 2018-11-13 | 敏华家具制造(惠州)有限公司 | Swiveling seat |
| CN205589516U (en) * | 2016-05-10 | 2016-09-21 | 北京安达维尔航空设备有限公司 | Aircraft seat 360 degree rotary mechanism |
| CN105947220B (en) * | 2016-07-18 | 2017-12-26 | 陈玉红 | A kind of anti-aircraft seat that jolts for baby with massage functions |
| CN106183902B (en) * | 2016-10-09 | 2018-09-11 | 苏州美适宜医疗设备有限公司 | It adjusts chair frame and adjusts seat |
| CN107176177B (en) * | 2017-06-20 | 2023-08-22 | 北京安达维尔航空设备有限公司 | Universal flexible mounting multi-position adjusting mechanism |
| CN207291752U (en) * | 2017-07-27 | 2018-05-01 | 江苏省交通技师学院 | A kind of self-adjustable aviation and vehicle level seat |
| CN107914885A (en) * | 2017-10-30 | 2018-04-17 | 成都鑫晨航空科技有限公司 | A kind of passenger seat of spacecraft |
| CN108639353A (en) * | 2018-05-22 | 2018-10-12 | 江闯 | A kind of self balancing safety seat of aircraft |
| CN108891607A (en) * | 2018-08-07 | 2018-11-27 | 晨龙飞机（荆门）有限公司 | A kind of aircraft inner cavity adjusts the regulating device of chair |
-
2019
- 2019-03-07 CN CN201910170296.4A patent/CN109878738B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN109878738A (en) | 2019-06-14 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109878738B (en) | Aviation seat angle adjusting device | |
| US5622406A (en) | Seat cushion adjustment for vehicle seats | |
| CN109466386B (en) | Vehicle rear seat integrated with child seat and vehicle | |
| KR101553527B1 (en) | Automatic headrest | |
| CN104057856B (en) | Lifting type back seat handrail and there is its vehicle | |
| JPH1059037A (en) | Child seat having tiltable back | |
| KR20100019390A (en) | A power headrest for a vehicle's seat | |
| CN203449974U (en) | Adjustable seat | |
| CN108482682A (en) | A kind of lifting seat | |
| CN201833657U (en) | Printing platform lifting device for jet printer | |
| WO2023093199A1 (en) | Height adjustment and angle adjustment integrated automobile seat | |
| US11167665B2 (en) | Base frame for a vehicle seat as well as a vehicle seat | |
| CN207523515U (en) | Automotive seat four-way headrest controlling mechanism and automotive seat | |
| CN108128165B (en) | An adjusting bracket eight-direction adjusting mechanism and engineering truck | |
| CN109677307A (en) | Adjustable foot pedal apparatus and the vehicles | |
| CN204749929U (en) | Seat is just being driven to car | |
| CN110682834B (en) | Automobile driver seat | |
| CN207594761U (en) | Novel seat skeleton | |
| CN216805840U (en) | Aviation seat framework | |
| KR102338310B1 (en) | Seat for vehicle | |
| KR20210082813A (en) | Efficient Car Seat Headrest Adjuster | |
| CN114801900B (en) | Seat system and vehicle | |
| CN220281199U (en) | Automobile seat with telescopic armrests | |
| CN218907002U (en) | Length-adjustable automobile seat armrest | |
| KR101956985B1 (en) | Tilting apparatus of front seat for vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| CB02 | Change of applicant information | ||
| CB02 | Change of applicant information |
Address after: 215100 No.3, Fuhang Road, hejiajiao village, Wangting Town, Xiangcheng District, Suzhou City, Jiangsu Province Applicant after: SUZHOU HAOXIN PRECISION MECHANICAL Co.,Ltd. Address before: No. 399 Xinfeng Road, Xukou Town, Wuzhong District, Suzhou City, Jiangsu Province, 215000 Applicant before: SUZHOU HAOXIN PRECISION MECHANICAL Co.,Ltd. |
|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: 215000 No. 3, Fuhang Road, intelligent manufacturing industrial park, Wangting Town, Xiangcheng District, Suzhou City, Jiangsu Province Patentee after: Suzhou Haoxin Precision Technology Co.,Ltd. Address before: 215100 No.3, Fuhang Road, hejiajiao village, Wangting Town, Xiangcheng District, Suzhou City, Jiangsu Province Patentee before: SUZHOU HAOXIN PRECISION MECHANICAL CO.,LTD. |
|
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of invention: An aviation seat angle adjusting device Effective date of registration: 20220126 Granted publication date: 20210702 Pledgee: Bank of China Limited Suzhou Xiangcheng sub branch Pledgor: Suzhou Haoxin Precision Technology Co.,Ltd. Registration number: Y2022980001184 |
|
| PE01 | Entry into force of the registration of the contract for pledge of patent right | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20230129 Granted publication date: 20210702 Pledgee: Bank of China Limited Suzhou Xiangcheng sub branch Pledgor: Suzhou Haoxin Precision Technology Co.,Ltd. Registration number: Y2022980001184 |
|
| PE01 | Entry into force of the registration of the contract for pledge of patent right | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of invention: An aviation seat angle adjusting device Effective date of registration: 20230201 Granted publication date: 20210702 Pledgee: Bank of China Limited Suzhou Xiangcheng sub branch Pledgor: Suzhou Haoxin Precision Technology Co.,Ltd. Registration number: Y2023980031935 |
|
| PC01 | Cancellation of the registration of the contract for pledge of patent right | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20230327 Granted publication date: 20210702 Pledgee: Bank of China Limited Suzhou Xiangcheng sub branch Pledgor: Suzhou Haoxin Precision Technology Co.,Ltd. Registration number: Y2023980031935 |
|
| PE01 | Entry into force of the registration of the contract for pledge of patent right | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of invention: An aviation seat angle adjustment device Effective date of registration: 20230328 Granted publication date: 20210702 Pledgee: Bank of China Limited Suzhou Xiangcheng sub branch Pledgor: Suzhou Haoxin Precision Technology Co.,Ltd. Registration number: Y2023980036654 |