CN220281675U

CN220281675U - Novel lightweight aviation seat skeleton

Info

Publication number: CN220281675U
Application number: CN202321761208.6U
Authority: CN
Inventors: 陆前峰
Original assignee: Shanghai Gaobo Aviation Manufacturing Co ltd
Current assignee: Shanghai Gaobo Aviation Manufacturing Co ltd
Priority date: 2023-07-06
Filing date: 2023-07-06
Publication date: 2024-01-02
Anticipated expiration: 2033-07-06

Abstract

The utility model relates to the technical field of aviation seats and discloses a novel light-weight aviation seat framework, which comprises a base, a seat cushion arranged on the base, an electric control back seat arranged on the left side of the seat cushion, armrests fixedly connected to one side of the seat cushion, and a processing assembly arranged on the upper portion of the base, wherein the processing assembly comprises an adjusting mechanism arranged on the top of the electric control back seat, a damping mechanism is arranged in the base, the headrest is rotationally connected with the electric control back seat through a rotating shaft, a torsion spring is sleeved on the outer wall of the rotating shaft, a first spring is sleeved on the outer wall of a telescopic column, the telescopic column is in sliding connection with a fixed plate through the first spring, a second spring is sleeved on the outer wall of the column, the top of a damper is fixedly connected with a connecting column, and the connecting column is in sliding connection with the base through the column. The utility model solves the problem that the backrest of the existing device can not adjust the head position of a consumer, thereby ensuring the consumer to feel more comfortable.

Description

Novel lightweight aviation seat skeleton

Technical Field

The utility model relates to the technical field of aviation seats, in particular to a novel light aviation seat framework.

Background

Aviation, which refers to the flying activities of aircrafts in the earth's atmosphere, and the fields related thereto, such as scientific education, industrial manufacture, public transportation, professional work, aviation sports, national defense military, government management, etc., can be subdivided into a plurality of independent industries and fields by utilizing the air space and aircrafts, typically, for example, the aviation manufacturing industry, civil aviation industry, etc., and it is often seen that people use the word from the respective fields, the connotation and the richness and diversity thereof, aircrafts engaged in the flying activities, also called aircrafts, are classified into two types, namely, aircrafts lighter than air and aircrafts heavier than air, the former being lifted by means of air buoyancy, such as balloons, airships, etc., and the latter being lifted by means of aerodynamic forces generated by relative movements with air, such as airplanes, helicopters, etc., and can be classified into unmanned and unmanned aircraft, according to whether or not people are carried.

In the reproduction process of a general aviation seat, a general framework is needed, production personnel can perfect the addition of accessories to the aviation seat according to the framework, the backrest angle of the general aviation seat is adjusted more hard and is generally adjusted in a plurality of angle layers, the use comfort is not high, and the consumption requirement of consumers cannot be met.

According to the aviation seat assembly framework disclosed in Chinese patent public number CN209008861U, the device has a certain elastic gap when the seat backrest is adjusted, so that the use comfort of a consumer is improved, and the consumption requirement of the consumer is met; however, the backrest of the device cannot be adjusted to the head position of the consumer, so that the consumer is more comfortable.

Therefore, a novel lightweight aviation seat framework is provided for solving the problem.

Disclosure of Invention

The utility model aims to provide a novel light aviation seat framework, which solves the problems in the background technology.

In order to achieve the above purpose, the present utility model provides the following technical solutions: a novel light aviation seat framework comprises a base;

a cushion arranged on the base;

an electric control back chair arranged at the left side of the cushion;

armrests fixedly connected to one side of the seat cushion;

and the processing assembly is arranged on the upper part of the base and comprises an adjusting mechanism arranged on the top of the electric control back chair, and a damping mechanism is arranged inside the base.

Preferably, the adjustment mechanism includes fixed plate of fixed mounting at automatically controlled back of body chair top, fixed plate inner wall fixed mounting has the pivot, the pivot outer wall is connected with the headrest through the bearing rotation, headrest inner wall fixedly connected with torsional spring, circular recess has been seted up to headrest one side, circular recess inner wall fixedly connected with magnet, fixed plate one side activity runs through there is the telescopic column, telescopic column one end fixedly connected with pull rod, fixed plate outer wall fixedly connected with first spring, fixed plate one end and pull rod fixed connection are kept away from to first spring.

Preferably, the damper comprises a connecting column sleeved inside the base, the inner wall of the base is fixedly connected with a cylinder, the bottom of the inner wall of the base is fixedly connected with a second spring, an inner groove is formed in the bottom of the connecting column, a damper is fixedly mounted at the bottom of the inner wall of the base, a sliding groove is formed in the inner wall of the base, the inner wall of the groove is fixedly connected with a sliding rod, and the outer wall of the sliding rod is slidably connected with a sliding block.

Preferably, the headrest is rotationally connected with the electric control back chair through the rotating shaft, the torsion spring is sleeved on the outer wall of the rotating shaft, the first spring is sleeved on the outer wall of the telescopic column, the telescopic column is slidably connected with the fixed plate through the first spring, the telescopic column is separated from the circular groove through the outward pulling of the pull rod by a consumer, then the head of the consumer leans against the headrest, the angle of the consumer is adjusted to a comfortable angle through the torsion spring, after the angle is adjusted but a proper angle, the pull rod is loosened, the telescopic column is clamped with the circular groove, so that the headrest is fixed, and the consumer takes more comfort through the cooperation of the electric control back chair.

Preferably, the quantity of magnet has a plurality of, and the equidistance distributes in circular recess, flexible post is iron material, flexible post and circular recess joint setting make flexible post and circular recess's joint effect better under the effect of suction through magnet to make the headrest more stable in the use.

Preferably, the second spring housing is established at the outer wall of cylinder, cylinder and inside groove adaptation, attenuator top and spliced pole fixed connection, the spliced pole passes through cylinder and base sliding connection, and when the seat received jolt, the cushion can be down to the second spring of pressing, reaches the shock attenuation effect under the effect of attenuator, under the cooperation of cylinder and inside groove, prevents that the second spring from excessively deforming in compression process to the second spring has been protected, the life of part has been increased.

Preferably, the quantity of slider has four, and the equidistance distributes in the base, the slider passes through slide bar and spout sliding connection, slider and spliced pole fixed connection, through the cooperation of slider and slide bar, makes the spliced pole more stable at the in-process of jolting, reduces simultaneously that the spliced pole receives with base interface department to the life of device has been increased.

The utility model provides a novel light aviation seat framework. This novel lightweight aviation seat skeleton possesses following beneficial effect:

(1) According to the novel light aviation seat framework, through the adjusting mechanism, the telescopic column is separated from the circular groove by pulling the pull rod outwards by a consumer, then the head of the consumer leans against the headrest, the angle of the consumer is adjusted to a comfortable angle through the torsion spring, and after the angle is adjusted but proper, the pull rod is loosened, so that the telescopic column is clamped with the circular groove, the headrest is fixed, and the consumer takes the chair more comfortably by matching with the electric control back chair;

(2) This novel lightweight aviation seat skeleton, through damper, under the effect of second spring, when the seat received jolting, the damper can reduce elasticity potential energy, reaches the shock attenuation effect, under the effect of cylinder and inside groove, prevent that the second spring from excessively deforming in the compression process, thereby protected the second spring, increased the life of part, under the effect of slider and slide bar, make the spliced pole more stable at jolting in-process, reduce simultaneously the butt pressure that spliced pole and base interface department received, thereby increased the life of device.

Drawings

FIG. 1 is a schematic diagram of the overall structure of the present utility model;

FIG. 2 is a schematic view of the whole cross-sectional structure of the present utility model;

FIG. 3 is a schematic view of the structure of the adjusting mechanism of the present utility model;

FIG. 4 is a schematic view of a partial cross-sectional structure of an adjusting mechanism according to the present utility model;

FIG. 5 is a schematic view of a shock absorbing mechanism according to the present utility model;

FIG. 6 is a schematic view of a partial cross-sectional structure of a shock absorbing mechanism according to the present utility model;

in the figure: 1. a base; 2. a cushion; 3. processing the assembly; 31. an adjusting mechanism; 311. a headrest; 312. a fixing plate; 313. a first spring; 314. a telescopic column; 315. a pull rod; 316. a torsion spring; 317. a rotating shaft; 318. a circular groove; 319. a magnet; 32. a damping mechanism; 321. a connecting column; 322. an inner tank; 323. a cylinder; 324. a second spring; 325. a damper; 326. a chute; 327. a slide bar; 328. a slide block; 4. an armrest; 5. an electric control back chair.

Detailed Description

For a clearer understanding of technical features, objects, and effects of the present utility model, a specific embodiment of the present utility model will be described with reference to the accompanying drawings.

Example 1

As shown in fig. 1-6, the present utility model provides a technical solution: the utility model provides a novel lightweight aviation seat skeleton, including base 1, set up cushion 2 above base 1, set up the automatically controlled back of the body chair 5 in cushion 2 left side, fixed connection is in handrail 4 on cushion 2 one side, and set up the processing subassembly 3 on base 1 upper portion, processing subassembly 3 is including setting up the adjustment mechanism 31 at automatically controlled back of the body chair 5 top, the inside damper 32 that is provided with of base 1, adjustment mechanism 31 includes fixed mounting at the fixed plate 312 at automatically controlled back of the body chair 5 top, fixed plate 312 inner wall fixed mounting has pivot 317, pivot 317 outer wall is connected with headrest 311 through the bearing rotation, headrest 311 inner wall fixedly connected with torsional spring 316, circular recess 318 has been seted up to headrest 311 one side, circular recess 318 inner wall fixedly connected with magnet 319, fixed plate 312 one side activity runs through there is telescopic column 314, telescopic column 314 one end fixedly connected with pull rod 315, fixed plate 312 outer wall fixedly connected with first spring 313, fixed plate 312 one end and pull rod 315 are kept away from to first spring 313.

In this embodiment, the headrest 311 is rotationally connected with the electric control back chair 5 through the rotating shaft 317, the torsion spring 316 is sleeved on the outer wall of the rotating shaft 317, the first spring 313 is sleeved on the outer wall of the telescopic column 314, the telescopic column 314 is slidably connected with the fixed plate 312 through the first spring 313, the telescopic column 314 is separated from the circular groove 318 by pulling the pull rod 315 outwards by a consumer, then the head of the consumer leans against the headrest 311, the angle of the consumer is adjusted to a comfortable angle through the torsion spring 316, after the angle is adjusted but the proper angle, the pull rod 315 is released, the telescopic column 314 is clamped with the circular groove 318, so that the headrest 311 is fixed, and the consumer takes more comfortable in cooperation with the electric control back chair 5.

Further, the number of the magnets 319 is a plurality, the magnets 319 are equidistantly distributed in the circular groove 318, the telescopic column 314 is made of iron materials, the telescopic column 314 is clamped with the circular groove 318, the telescopic column 314 and the circular groove 318 are better in clamping effect under the action of attraction force through the magnets 319, and therefore the headrest 311 is more stable in the use process

When the seat is used, firstly, the electric control back chair 5 is controlled by a consumer to adjust the angle to be comfortable, then the pull rod 315 is pulled outwards to enable the telescopic column 314 to be separated from the circular groove 318, then the head of the consumer leans against the headrest 311, the headrest 311 can be adjusted in angle through the torsion spring 316, after the consumer adjusts the head to be comfortable, the pull rod 315 is loosened, and under the action of the first spring 313, the telescopic column 314 is clamped with the circular groove 318, so that the headrest 311 is fixed, and the consumer takes more comfortable.

Example 2

On the basis of embodiment 1, a preferred embodiment of the novel lightweight aviation seat framework provided by the utility model is shown in fig. 1 to 6: the damper 32 comprises a connecting post 321 sleeved inside the base 1, a cylinder 323 is fixedly connected to the inner wall of the base 1, a second spring 324 is fixedly connected to the bottom of the inner wall of the base 1, an inner groove 322 is formed in the bottom of the connecting post 321, a damper 325 is fixedly mounted on the bottom of the inner wall of the base 1, a sliding groove 326 is formed in the inner wall of the base 1, a sliding rod 327 is fixedly connected to the inner wall of the groove, and a sliding block 328 is slidably connected to the outer wall of the sliding rod 327.

In this embodiment, the outer wall at cylinder 323 is established to second spring 324 cover, cylinder 323 and inside groove 322 adaptation, damper 325 top and spliced pole 321 fixed connection, spliced pole 321 passes through cylinder 323 and base 1 sliding connection, when the seat received jolting, cushion 2 can support down and press second spring 324, under the effect of damper 325, reach the shock attenuation effect, under the cooperation of cylinder 323 and inside groove 322, prevent that second spring 324 from excessively deforming in the compression process, thereby protected second spring 324, increased the life of part.

Further, the number of the sliding blocks 328 is four, the sliding blocks 328 are equidistantly distributed in the base 1, the sliding blocks 328 are slidably connected with the sliding grooves 326 through the sliding rods 327, the sliding blocks 328 are fixedly connected with the connecting columns 321, the connecting columns 321 are more stable in the bumping process through the matching of the sliding blocks 328 and the sliding rods 327, and meanwhile the abutting force applied to the interface of the connecting columns 321 and the base 1 is reduced, so that the service life of the device is prolonged.

When the seat received jolt, cushion 2 can support downwards and press second spring 324, under the effect of attenuator 325, reach the shock attenuation effect, at second spring 324 compression in-process, under the cooperation of cylinder 323 and inside groove 322, prevent that second spring 324 from excessively deforming at compression in-process, increased the life of part, through the cooperation of slider 328 and slide bar 327, make connecting post 321 more stable at jolt in-process, reduce the supporting force that connecting post 321 received with 1 interface department simultaneously, thereby increased the life of device.

Although embodiments of the present utility model have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made therein without departing from the principles and spirit of the utility model, the scope of which is defined in the appended claims and their equivalents.

Claims

1. A novel light aviation seat framework comprises a base (1);

a cushion (2) arranged on the base (1);

an electric control back chair (5) arranged at the left side of the cushion (2);

an armrest (4) fixedly connected to one side of the seat cushion (2);

and a processing component (3) arranged on the upper part of the base (1), which is characterized in that: the processing assembly (3) comprises an adjusting mechanism (31) arranged at the top of the electric control back chair (5), and a damping mechanism (32) is arranged in the base (1).

2. The novel lightweight airline seat frame as set forth in claim 1, wherein: adjustment mechanism (31) are including fixed mounting fixed plate (312) at automatically controlled back of body chair (5) top, fixed plate (312) inner wall fixed mounting has pivot (317), pivot (317) outer wall is connected with headrest (311) through the bearing rotation, headrest (311) inner wall fixedly connected with torsional spring (316), circular recess (318) have been seted up to headrest (311) one side, circular recess (318) inner wall fixedly connected with magnet (319), fixed plate (312) one side activity is run through has telescopic column (314), telescopic column (314) one end fixedly connected with pull rod (315), fixed plate (312) outer wall fixedly connected with first spring (313), fixed plate (312) one end and pull rod (315) fixed connection are kept away from to first spring (313).

3. The novel lightweight airline seat frame as set forth in claim 1, wherein: the damping mechanism (32) comprises a connecting post (321) sleeved inside the base (1), a cylinder (323) is fixedly connected to the inner wall of the base (1), a second spring (324) is fixedly connected to the bottom of the inner wall of the base (1), an inner groove (322) is formed in the bottom of the connecting post (321), a damper (325) is fixedly mounted on the bottom of the inner wall of the base (1), a sliding groove (326) is formed in the inner wall of the base (1), a sliding rod (327) is fixedly connected to the inner wall of the groove, and a sliding block (328) is slidably connected to the outer wall of the sliding rod (327).

4. The novel lightweight airline seat frame as set forth in claim 2, wherein: the headrest (311) is rotationally connected with the electric control back chair (5) through a rotating shaft (317), the torsion spring (316) is sleeved on the outer wall of the rotating shaft (317), the first spring (313) is sleeved on the outer wall of the telescopic column (314), and the telescopic column (314) is slidably connected with the fixed plate (312) through the first spring (313).

5. The novel lightweight airline seat frame as set forth in claim 2, wherein: the number of the magnets (319) is a plurality, the magnets are equidistantly distributed in the circular groove (318), the telescopic columns (314) are made of iron materials, and the telescopic columns (314) are clamped with the circular groove (318).

6. A novel lightweight airline seat frame as set forth in claim 3, wherein: the second spring (324) is sleeved on the outer wall of the cylinder (323), the cylinder (323) is matched with the inner groove (322), the top of the damper (325) is fixedly connected with the connecting post (321), and the connecting post (321) is in sliding connection with the base (1) through the cylinder (323).

7. A novel lightweight airline seat frame as set forth in claim 3, wherein: the number of the sliding blocks (328) is four, the sliding blocks (328) are distributed in the base (1) at equal intervals, the sliding blocks (328) are connected with the sliding grooves (326) in a sliding mode through the sliding rods (327), and the sliding blocks (328) are fixedly connected with the connecting columns (321).