CN211364967U

CN211364967U - Angle adjuster for aviation seat

Info

Publication number: CN211364967U
Application number: CN201922456524.2U
Authority: CN
Inventors: 袁思聪; 余卫忠; 刘淑勉; 周永华; 周秋华
Original assignee: Changzhou Gas Spring Co ltd
Current assignee: Changzhou Gas Spring Co ltd
Priority date: 2019-12-30
Filing date: 2019-12-30
Publication date: 2020-08-28
Anticipated expiration: 2029-12-30

Abstract

The utility model relates to an aviation seat angle modulation ware, including outer cylinder, the front-end connection, air spring assembly and back connector, air spring assembly is including setting up the inside interior cylinder of outer cylinder, it is provided with vice piston to slide between outer cylinder and the interior cylinder, form first air cavity between interior cylinder and the front-end connection, inside main piston and the isolation piston of being provided with of interior cylinder, main piston and isolation piston are with the inside first oil pocket that falls into of interior cylinder, second oil pocket and second air cavity, interior cylinder center is provided with the piston rod, the piston rod stretches into inside and the cooperation of first oil pocket and is connected with main piston, main piston and interior cylinder inner wall sliding fit, the inside of piston rod is provided with the ejector pin, the one end of ejector pin stretches into in the front-end connection and is provided with control switch, the other end of ejector pin runs through main piston and is provided with. The utility model discloses simple structure, convenient to use can adjust the angle of aviation seat at will, and the flight that brings the preferred for the passenger is experienced, improves aviation seat's security and travelling comfort.

Description

Angle adjuster for aviation seat

Technical Field

The utility model relates to an aeronautical equipment technical field specifically is an aviation seat angle modulation ware.

Background

The angle adjuster is a device for realizing angle adjustment of the backrest of the seat, and is widely applied to the fields of automobiles, medical fitness equipment, building doors and windows, aviation and the like.

At present, most of adjusting devices on an aviation seat adopt mechanical angle adjusters, but the mechanical angle adjusters have the defect of poor stability and often bring uncomfortable flying experience to passengers.

SUMMERY OF THE UTILITY MODEL

The to-be-solved technical problem of the utility model is: in order to increase the stability of the adjusting device on the aircraft seat.

In order to achieve the above object, the utility model provides a following technical scheme: the utility model provides an angle regulator for aviation seats, which comprises an outer cylinder, a front joint connected with the outer cylinder, an air spring component and a rear joint, wherein the air spring component comprises an inner cylinder arranged inside the outer cylinder, an auxiliary piston is arranged between the outer cylinder and the inner cylinder in a sliding way, a first air cavity is formed between one end of the inner cylinder and the front joint, the other end of the inner cylinder is connected with the rear joint, a main piston and an isolation piston are arranged inside the inner cylinder, the main piston and the isolation piston divide the inside of the inner cylinder into a first oil cavity, a second oil cavity and a second air cavity, sealing elements are arranged between the main piston and the inner cylinder and between the isolation piston and the inner cylinder, a piston rod is arranged at the center of the inner cylinder, one end of the piston rod is connected with the front joint, the other end of the piston rod extends into the first oil cavity and is connected with the main piston in a matching way, one end of the ejector rod extends into the front connector and is provided with a control switch, the other end of the ejector rod penetrates through the main piston and is provided with a valve core for opening and closing the second oil cavity, and a guide sleeve is arranged between the piston rod and the inner cylinder barrel.

When the control switch touches the ejector rod, the ejector rod opens the valve core, the second oil cavity is in an open state, oil in the second oil cavity flows to the first oil cavity and fills the first oil cavity, then the guide sleeve drives the inner cylinder barrel to move to the first air cavity, the isolation piston also moves to the first air cavity, the volume of the second air cavity is enlarged, and the energy stored by the gas is released, so that the isolation piston is pushed to move; the outer cylinder barrel moves towards the opposite direction relative to the inner cylinder barrel, the inner cylinder barrel enters the inner part of the outer cylinder barrel, and at the moment, the inward adjustment of the angle of the aviation seat can be realized;

when the valve core is closed, the compressed gas in the first gas cavity generates a rebounding force to force the inner cylinder barrel to drive the guide sleeve to move towards the direction far away from the first gas cavity, the oil in the first oil cavity flows back to the second oil cavity, so that the isolation piston compresses the gas in the second gas cavity, and the gas stores energy after being compressed; then the outer cylinder removes to opposite direction for interior cylinder, and interior cylinder stretches out the outer cylinder outside promptly, at this moment, can realize outwards adjusting aviation seat's angle.

Further, a collision ring is arranged between the guide sleeve and the main piston, the collision ring is connected with the guide sleeve through a guide sealing piece, and a first oil cavity is formed among the guide sealing piece, the collision ring and the main piston. When the piston rod slides along the axial direction of the inner cylinder barrel, the guide sleeve and the guide sealing piece are used for guiding, the guide sealing piece plays a good sealing role, oil is prevented from being leaked to the outside, and the limit position of the main piston is limited by the collision ring.

Furthermore, in order to improve the sealing effect, annular grooves are formed in the main piston and the piston rod, sealing rings which are abutted to the ejector rods are arranged in the annular grooves, an oil inlet channel is further formed in the main piston, and oil in the second oil cavity can flow into the first oil cavity conveniently through the oil inlet channel.

The utility model has the advantages that: the utility model provides a pair of aviation seat angle modulation ware, simple structure, convenient to use, fixed stable can adjust aviation seat's angle at will, has improved aviation seat's security and travelling comfort when bringing the preferred flight experience for the passenger.

Drawings

The present invention will be further explained with reference to the drawings and examples.

Fig. 1 is a schematic structural diagram of the present invention;

FIG. 2 is an enlarged schematic view at A in FIG. 1;

FIG. 3 is an enlarged schematic view at B of FIG. 1;

in the figure: 1-front joint, 2-rear joint, 3-outer cylinder, 31-first air cavity, 4-inner cylinder, 41-first oil cavity, 42-second oil cavity, 43-second air cavity, 5-main piston, 51-sealing ring, 52-oil inlet channel, 53-annular groove, 6-collision ring, 7-guide sealing element, 8-ejector rod, 9-piston rod, 10-guide sleeve, 11-control switch, 12-auxiliary piston, 13-isolation piston, 14-sealing element and 15-valve core.

Detailed Description

The present invention will now be described in further detail with reference to the accompanying drawings. These drawings are simplified schematic drawings and illustrate the basic structure of the present invention only in a schematic manner, and thus show only the components related to the present invention.

As shown in figure 1, the utility model provides an angle regulator for aviation seats, which comprises an outer cylinder 3, a front joint 1 connected with the outer cylinder 3, an air spring assembly and a rear joint 2, wherein the air spring assembly comprises an inner cylinder 4 arranged inside the outer cylinder 3, an auxiliary piston 12 is arranged between the outer cylinder 3 and the inner cylinder 4 in a sliding way, a first air cavity 31 is formed between one end of the inner cylinder 4 and the front joint 1, the other end of the inner cylinder 3 is connected with the rear joint 2, a main piston 5 and an isolation piston 13 are arranged inside the inner cylinder 3, the main piston 5 and the isolation piston 13 divide the inside of the inner cylinder 4 into a first oil cavity 41, a second oil cavity 42 and a second air cavity 43, sealing elements 14 are arranged between the main piston 5 and the inner cylinder 4 and between the isolation piston 13 and the inner cylinder 4, a piston rod 9 is arranged at the center of the inner cylinder 4, one end of the piston rod 9 is connected with the front joint 1, the other end of the piston rod 9 extends into the first, the main piston 5 is in sliding fit with the inner wall of the inner cylinder 4, the push rod 8 is arranged inside the piston rod 9, one end of the push rod 8 extends into the front connector 1 and is provided with a control switch 11, the other end of the push rod 8 penetrates through the main piston 5 and is provided with a valve core 15 for opening and closing a second oil cavity 42, and a guide sleeve 10 is arranged between the piston rod 9 and the inner cylinder 4.

When the control switch 11 touches the ejector rod 8, the ejector rod 8 opens the valve core 15, the second oil chamber 42 is in an open state, oil in the second oil chamber 42 flows to the first oil chamber 41 and fills the first oil chamber 41, then the guide sleeve 10 drives the inner cylinder barrel 4 to move towards the first air chamber 31, the isolation piston 13 also moves towards the first air chamber 31, nitrogen is stored in the second air chamber 43, the volume of the nitrogen is increased, and the energy stored in the nitrogen is released, so that the isolation piston 13 is pushed to move; the outer cylinder barrel 3 moves in the opposite direction relative to the inner cylinder barrel 4, the inner cylinder barrel 4 enters the inner part of the outer cylinder barrel 3, and at the moment, the inward adjustment of the angle of the aviation seat can be realized;

when the valve core 15 is closed, the compressed gas in the first air cavity 31 generates a rebound force to force the inner cylinder 4 to drive the guide sleeve 10 to move in a direction away from the first air cavity 31, the oil in the first oil cavity 41 flows back to the second oil cavity 42, so that the isolation piston 13 compresses the nitrogen in the second air cavity 43, and the nitrogen is compressed to store energy; then outer cylinder 3 moves to opposite direction for interior cylinder 4, and interior cylinder 4 stretches out outer cylinder 3 outside promptly, at this moment, can realize outwards adjusting aviation seat's angle.

As shown in fig. 1, a plunger ring 6 is disposed between the guide sleeve 10 and the main piston 5, the plunger ring 6 is connected to the guide sleeve 10 via a guide seal 7, and a first oil chamber 41 is formed between the guide seal 7, the plunger ring 6 and the main piston 5. When the piston rod 9 slides axially along the inner cylinder 4, the guide sleeve 10 and the guide sealing piece 7 are used for guiding, the guide sealing piece 7 plays a good sealing role, oil is prevented from leaking to the outside, and the limit position of the main piston 5 is limited by the collision ring 6.

As shown in fig. 2 and 3, in order to improve the sealing effect, annular grooves 53 are formed in the main piston 5 and the piston rod 9, a sealing ring 51 abutting against the rod 8 is disposed in the annular groove 53, an oil inlet passage 52 is further formed in the main piston 5, and the oil in the second oil chamber 42 can flow into the first oil chamber 41 through the oil inlet passage 52.

The utility model provides a pair of aviation seat angle modulation ware, simple structure, convenient to use, fixed stable can adjust aviation seat's angle at will, has improved aviation seat's security and travelling comfort when bringing the preferred flight experience for the passenger.

In light of the foregoing, it will be apparent to those skilled in the art from this disclosure that various changes and modifications can be made without departing from the spirit and scope of the invention. The technical scope of the present invention is not limited to the content of the specification, and must be determined according to the scope of the claims.

Claims

1. An aviation seat angle modulation ware which characterized in that: the gas spring comprises an outer cylinder barrel (3), a front connector (1) connected with the outer cylinder barrel (3), a gas spring assembly and a rear connector (2), wherein the gas spring assembly comprises an inner cylinder barrel (4) arranged inside the outer cylinder barrel (3), a secondary piston (12) is arranged between the outer cylinder barrel (3) and the inner cylinder barrel (4) in a sliding manner, a first gas cavity (31) is formed between one end of the inner cylinder barrel (4) and the front connector (1), the other end of the inner cylinder barrel (4) is connected with the rear connector (2), a main piston (5) and an isolation piston (13) are arranged inside the inner cylinder barrel (4), the main piston (5) and the isolation piston (13) divide the inside of the inner cylinder barrel (4) into a first oil cavity (41), a second oil cavity (42) and a second gas cavity (43), and the main piston (5) and the cylinder barrel (4) are connected, Sealing elements (14) are arranged between the isolation piston (13) and the inner cylinder barrel (4), a piston rod (9) is arranged at the center of the inner cylinder barrel (4), one end of the piston rod (9) is connected with the front joint (1), the other end of the piston rod (9) extends into the first oil chamber (41) and is connected with the main piston (5) in a matching way, the main piston (5) is in sliding fit with the inner wall of the inner cylinder barrel (4), a mandril (8) is arranged inside the piston rod (9), one end of the ejector rod (8) extends into the front joint (1) and is provided with a control switch (11), the other end of the mandril (8) penetrates through the main piston (5) and is provided with a valve core (15) for opening and closing the second oil cavity (42), and a guide sleeve (10) is arranged between the piston rod (9) and the inner cylinder barrel (4).

2. An aircraft seat recliner as set forth in claim 1 wherein: uide bushing (10) with be provided with between main piston (5) and bump circle (6), bump circle (6) with uide bushing (10) are connected through direction sealing member (7), direction sealing member (7) bump circle (6) with form between main piston (5) first oil pocket (41).

3. An aircraft seat recliner as set forth in claim 1 wherein: the main piston (5) and the piston rod (9) are both provided with annular grooves (53), sealing rings (51) which are abutted against the ejector rods (8) are arranged in the annular grooves (53), and the main piston (5) is also provided with an oil inlet channel (52).