CN212373639U

CN212373639U - Aircraft slide lock

Info

Publication number: CN212373639U
Application number: CN202020321249.3U
Authority: CN
Inventors: 张晓冬; 杨智; 郑朝; 陈雷鸣; 畅海涛; 张少康; 陈进
Original assignee: Shaanxi China Aero-Industry Gas Spring Co Ltd
Current assignee: Shaanxi China Aero-Industry Gas Spring Co Ltd
Priority date: 2020-03-16
Filing date: 2020-03-16
Publication date: 2021-01-19
Anticipated expiration: 2030-03-16

Abstract

The utility model discloses an aircraft slide lock, including the slide pedal, fixedly connected with locking plate on the slide pedal, the terminal surface all fixedly connected with fixed column around the locking plate lower part, and locking plate rear end face fixed column passes hinge seat, and fixedly connected between hinge seat and the aircraft body, hinge seat right-hand member articulate has the hinge, and it has logical groove one to open on the hinge, and hinge seat left part fixedly connected with fixed pin, fixed pin pass logical groove one, and fixed pin outer end damping articulates there is the locking piece; the utility model is not only simple in structure, use cost is lower, and is effectual to the fixed of aircraft slide, and is all very convenient to the fixed of aircraft slide and expansion operation simultaneously.

Description

Aircraft slide lock

Technical Field

The utility model relates to an aircraft slide lock technical field specifically is aircraft slide lock.

Background

The aircraft slide is the passageway that the passenger got on or off the aircraft, is an important component of aircraft, and the aircraft slide needs manual indentation when the aircraft flies, and the slide after the indentation needs to be fixed, and current aircraft slide is fixed comparatively troublesome, and the fixed operation of slide is comparatively loaded down with trivial details, leads to the trouble that the fixed of slide and expansion all are very, and it is comparatively inconvenient to use.

Based on this, the utility model designs an aircraft slide lock to solve the above-mentioned problem.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide an aircraft slide lock to solve the problem that proposes among the above-mentioned background art.

In order to achieve the above object, the utility model provides a following technical scheme: aircraft slide lock, including the slide is pedal, fixedly connected with locking plate on the slide is pedal, the equal fixedly connected with fixed column of terminal surface around the locking plate lower part, the hinge seat is passed to locking plate rear end face fixed column, fixed connection between hinge seat and the aircraft body, hinge seat right-hand member articulates there is the hinge, it has logical groove one to open on the hinge, hinge seat left part fixedly connected with fixed pin, the fixed pin passes logical groove one, fixed pin outer end damping articulates there is the locking piece.

Preferably, the fixed pin is sleeved with a first spring, one end of the first spring is abutted to the front end face of the hinge seat, and the other end of the first spring is abutted to the rear end face of the hinge.

Preferably, the fixing column on the front end face of the locking plate penetrates through the first through groove.

Preferably, the height of the stop block is greater than that of the first through groove.

Preferably, the fixed pin includes the round pin body, the external side of round pin is opened flutedly, be equipped with the second spring in the recess, third spring outer end butt has the ejector pin, the ejector pin outer end is hemispherical, the caulking groove has all been opened to stop block top and inboard, in the ejector pin tip embedding caulking groove.

Aircraft slide lock, including the slide is pedal, fixedly connected with locking plate on the slide is pedal, open the locking plate lower part has the draw-in groove, it passes to have the lockpin in the draw-in groove, it has logical groove two to open on the lockpin, it passes to have the swing arm in the logical groove two, the terminal surface has the round pin axle to pass before the lockpin, the round pin axle passes the swing arm, the slide lock still includes the lock seat, lock seat and aircraft body fixed connection, the lockpin passes the lock seat, open the swing arm lower part has two sets of card holes, it passes to have the staple in the card hole

Preferably, two groups of through holes are formed in the lock base, and the diameter of each through hole is the same as that of the corresponding clamping hole.

Preferably, a third spring is arranged in the lock pin.

Preferably, the front end face and the rear end face of the lock seat are both provided with a limiting groove, the pin shaft penetrates through the limiting groove, and the pin shaft slides in the limiting groove.

Compared with the prior art, the beneficial effects of the utility model are that: the utility model is not only simple in structure, use cost is lower, and is effectual to the fixed of aircraft slide, and it is all very convenient to the fixed of aircraft slide and expansion operation simultaneously, has to dial formula fixed and two kinds of fixed methods of push type fixed, can select according to actual conditions, and it is very convenient to use, has high spreading value.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to these drawings without creative efforts.

Fig. 1 is a schematic structural view of the hinge of embodiment 1 of the present invention after being opened;

fig. 2 is a schematic structural view of the hinge of embodiment 1 of the present invention after closing;

fig. 3 is a schematic structural view of embodiment 1 of the present invention;

fig. 4 is a schematic view of a connection structure of the fixing pin and the stopper according to embodiment 1 of the present invention;

FIG. 5 is a schematic structural view of the lock pin of embodiment 2 of the present invention when passing through the locking plate;

FIG. 6 is a schematic structural view of the lock pin of embodiment 2 of the present invention when the lock pin is withdrawn from the lock plate;

fig. 7 is a schematic structural view of embodiment 2 of the present invention;

fig. 8 is a schematic view of the connection between the lock pin and the swing arm according to embodiment 2 of the present invention.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by a person of ordinary skill in the art without creative efforts belong to the protection scope of the present invention.

Example 1

Referring to fig. 1-4, the present invention provides a technical solution of an aircraft slide lock: including slide pedal 1, fixedly connected with locking plate 2 on the slide pedal 1, the equal fixedly connected with fixed column 9 of terminal surface around the 2 lower parts of locking plate, hinge seat 3 is passed to terminal surface fixed column 9 behind the locking plate 2, fixed connection between hinge seat 3 and the aircraft body, 3 right-hand members of hinge seat articulate there is hinge 7, hinge 7 can rotate around hinge seat 3, it has logical groove 8 to open on the

hinge

7, 3 left part fixedly connected with fixed pin 5 of hinge seat, fixed pin 5 passes

logical groove

8, 5 outer end damping of fixed pin articulates there is stop block 6.

The fixed pin 5 is sleeved with a first spring 4, one end of the first spring 4 is abutted to the front end face of the hinge seat 3, the other end of the first spring 4 is abutted to the rear end face of the hinge 7, and the hinge 7 is abutted to the brake block under the action of the first spring 4, so that the brake block 6 can be prevented from rotating; the fixing column 9 on the front end face of the locking plate 2 penetrates through the first through groove 8, so that the locking plate 2 is fixed effectively; the height of the stop block 6 is greater than that of the first through groove 8, so that the hinge 7 can be prevented from rotating in a locking state; the fixing pin 5 comprises a pin body 51, a groove 52 is formed in the outer side of the pin body 51, a second spring 53 is arranged in the groove 52, the outer end of the second spring 53 is abutted to a mandril 54, the outer end of the mandril 54 is hemispherical, caulking grooves 61 are formed in the top and the inner side of the stop block 6, the end part of the mandril 54 is embedded into the caulking grooves 61, the stop block 6 can be limited, and the stop block 6 can be prevented from rotating due to the vibration of an airplane.

The specific working principle is as follows:

during the use, when needs are fixed pedal 1 to the slide, rotatable hinge 7, locking plate 2 is cliied to hinge 7 and hinge seat 3, at this moment, locking plate 2 preceding terminal surface fixed column 9 passes logical groove 8, rotatable stop block 6, rotate vertical position with stop block 6, it is fixed to closing page or leaf 7,

hinge

7 and 3 restriction locking plate 2's of hinge seat position, it fixes locking plate 2 to accomplish, because locking plate 2 and slide pedal fixed connection between 1, so can accomplish pedal 1 fixed to the slide. When loosening is needed, the stop block 6 can be rotated to the horizontal position, the hinge 7 is rotated, and then loosening of the lock piece 2 is completed.

Example 2

Referring to fig. 5-8, the present invention provides a technical solution of an aircraft slide lock: including slide pedal 1, fixedly connected with locking plate 2 on slide pedal 1, open the locking plate 2 lower part has draw-in groove 19, it has lockpin 13 to pass in the draw-in groove 19, lockpin 13 is fixed locking plate 2 through draw-in groove 19, it has logical groove two 16 to open on lockpin 13, it has swing arm 17 to pass in logical groove two 16, terminal surface has round pin axle 11 to pass before lockpin 13, round pin axle 11 passes swing arm 17, swing arm 17 can drive lockpin 13 linear motion, the slide lock still includes lock seat 10, lock seat 10 and aircraft body fixed connection, lockpin 13 passes lock seat 10, sliding contact between lockpin 13 and the lock seat 10, swing arm 17 lower part is opened there are two sets of card holes 18, it has lock nail 15 to pass to block in the hole 18.

Wherein, two groups of through holes 14 are arranged on the lock seat 10, the diameter of the through holes 14 is the same as that of the clamping holes 18, so that the locking nails 15 can be conveniently fixed; the locking nail 15 is internally provided with a third spring, so that the locking nail 15 cannot move after being inserted into the through hole 14 on the lock seat 10, the front end surface and the rear end surface of the lock seat 10 are both provided with a limiting groove 12, the pin shaft 11 penetrates through the limiting groove 12, and the pin shaft 11 slides in the limiting groove 12.

The specific working principle is as follows:

when the slide pedal 1 needs to be fixed, the locking nail 15 can be rotated counterclockwise, the locking nail 15 drives the swing arm 17 to rotate together, the pin shaft 11 slides along the limiting groove 12, the swing arm 17 drives the lock pin 13 to move towards the left side, the lock pin 13 penetrates through the clamping groove 19 in the lock plate 2 to fix the lock plate 2, when the locking nail 15 rotates to correspond to one group of through holes 14 in the lock seat 10, the locking nail 15 is inserted into the through hole 14, the locking nail 15 is fixed, the swing arm 17 and the lock pin 13 are fixed, so that the locking plate 2 and the slide pedal 1 are fixed, when the slide pedal 1 needs to be loosened, the locking nail 15 can be lifted out of the through hole 14, the locking nail 15 is rotated reversely, the locking nail 15 drives the lock pin 13 to move towards the right side through the swing arm 17, and then the loosening is completed.

In the description herein, references to the description of "one embodiment," "an example," "a specific example," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

The preferred embodiments of the present invention disclosed above are intended only to help illustrate the present invention. The preferred embodiments are not intended to be exhaustive or to limit the invention to the precise embodiments disclosed. Obviously, many modifications and variations are possible in light of the above teaching. The embodiments were chosen and described in order to best explain the principles of the invention and its practical applications, to thereby enable others skilled in the art to best understand the invention for and utilize the invention. The present invention is limited only by the claims and their full scope and equivalents.

Claims

1. Aircraft slide lock, including slide pedal (1), its characterized in that: fixedly connected with locking plate (2) on slide pedal (1), equal fixedly connected with fixed column (9) of terminal surface around locking plate (2) lower part, hinge seat (3) is passed in locking plate (2) rear end face fixed column (9), fixed connection between hinge seat (3) and the aircraft body, hinge seat (3) right-hand member articulates there is hinge (7), it has logical groove (8) to open on hinge (7), hinge seat (3) left part fixedly connected with fixed pin (5), fixed pin (5) pass logical groove (8), fixed pin (5) outer end damping articulates there is stop block (6).

2. An aircraft slide lock according to claim 1, wherein: the hinge base is characterized in that a first spring (4) is sleeved on the fixing pin (5), one end of the first spring (4) is abutted to the front end face of the hinge base (3), and the other end of the first spring (4) is abutted to the rear end face of the hinge (7).

3. An aircraft slide lock according to claim 1, wherein: and the front end face fixing column (9) of the locking plate (2) penetrates through the first through groove (8).

4. An aircraft slide lock according to claim 1, wherein: the height of the stop block (6) is greater than that of the first through groove (8).

5. An aircraft slide lock according to claim 1, wherein: the fixing pin (5) comprises a pin body (51), a groove (52) is formed in the outer side of the pin body (51), a second spring (53) is arranged in the groove (52), an ejector rod (54) is abutted to the outer end of the second spring (53), the outer end of the ejector rod (54) is hemispherical, caulking grooves (61) are formed in the top and the inner side of the stop block (6), and the end of the ejector rod (54) is embedded into the caulking grooves (61).

6. Aircraft slide lock, including slide pedal (1), its characterized in that: fixedly connected with locking plate (2) on slide pedal (1), open locking plate (2) lower part has draw-in groove (19), it passes to have lockpin (13) in draw-in groove (19), it has logical groove two (16) to open on lockpin (13), it passes to have swing arm (17) in logical groove two (16), terminal surface has round pin axle (11) to pass before lockpin (13), round pin axle (11) pass swing arm (17), the slide lock still includes lock seat (10), lock seat (10) and aircraft body fixed connection, lockpin (13) pass lock seat (10), open swing arm (17) lower part has two sets of card holes (18), it has lock nail (15) to pass in card hole (18).

7. An aircraft slide lock according to claim 6, wherein: two groups of through holes (14) are formed in the lock seat (10), and the diameter of each through hole (14) is the same as that of the corresponding clamping hole (18).

8. An aircraft slide lock according to claim 6, wherein: and a third spring is arranged in the lock pin (15).

9. An aircraft slide lock according to claim 6, wherein: the lock is characterized in that the front end face and the rear end face of the lock seat (10) are provided with limiting grooves (12), the pin shaft (11) penetrates through the limiting grooves (12), and the pin shaft (11) slides in the limiting grooves (12).