CN216834339U

CN216834339U - Portable aircraft wheel chock

Info

Publication number: CN216834339U
Application number: CN202220457461.1U
Authority: CN
Inventors: 姜鹏; 姜文利; 范立宏
Original assignee: Gongzhuling Dapeng Aviation Equipment Co ltd
Current assignee: Gongzhuling Dapeng Aviation Equipment Co ltd
Priority date: 2022-03-03
Filing date: 2022-03-03
Publication date: 2022-06-28
Anticipated expiration: 2032-03-03

Abstract

The utility model discloses a portable aircraft wheel fender, comprising a base plate, the bottom plate upper end is rotated through the pivot and is connected with the baffle, the bottom plate upper end is rotated and is connected with hydraulic cylinder, the hydraulic cylinder expansion end is rotated with the baffle lower extreme and is connected, two bar chambeies have been seted up to the bottom plate lower extreme bar intracavity wall sealing sliding connection has two slides, two the bar chamber is close to two connecting pipes of inner wall fixedly connected with of slide, two in the connecting pipe a plurality of sucking discs of bottom fixedly connected with, two the gliding actuating mechanism of drive slide is installed to the bar intracavity. The utility model discloses an it is flexible to adjust hydraulic cylinder, and then drives and rotate the baffle of being connected with the hydraulic cylinder expansion end, and then the baffle can cooperate with the aircraft wheel of different model sizes, and the practicality is strong, removes through the slide and makes pressure lower in the sucking disc, and then the bottom plate tightly adsorb under the effect of pressure subaerial, increases the stability after the bottom plate is placed.

Description

Portable aircraft wheel chock

Technical Field

The utility model relates to an aircraft wheel fender technical field especially relates to a portable aircraft wheel fender.

Background

An aircraft wheel chock is an object intended to be placed under the wheels of an aircraft to prevent the aircraft from sliding freely when stopped.

The size is fixed unchangeable when the preparation at present aircraft wheel fender, but because the aircraft model is different, its aircraft gyro wheel size is also different, and then when using the wheel fender to the aircraft wheel of different models, still need select suitable wheel fender, the practicality is lower, present wheel fender is directly put subaerial in addition, mainly relies on the friction between bottom plate lower surface and the ground to hinder the aircraft and slides, this appears easily that the wheel fender is placed the back stability relatively poor, the condition that the hindrance aircraft that can not be fine slides takes place.

Based on this, the utility model provides a portable aircraft wheel fender.

SUMMERY OF THE UTILITY MODEL

The utility model aims at solving the defects existing in the prior art and providing a portable airplane wheel chock.

In order to realize the purpose, the utility model adopts the following technical scheme:

the utility model provides a portable aircraft wheel fender, includes the bottom plate, the bottom plate upper end is rotated through the pivot and is connected with the baffle, the bottom plate upper end is rotated and is connected with hydraulic cylinder, hydraulic cylinder expansion end rotates with the baffle lower extreme and is connected, two bar chambeies, two are seted up to the bottom plate lower extreme bar intracavity wall sealing sliding connection has two slides, two the bar chamber is close to two connecting pipes of the inner wall fixedly connected with of slide, two in the connecting pipe a plurality of sucking discs of bottom fixedly connected with, two the gliding actuating mechanism of drive slide is installed to the bar intracavity.

Preferably, actuating mechanism is including rotating two lead screws of connection at two bar intracavity walls, two equal threaded connection of lead screw lateral wall has the slider, the slider respectively with bar intracavity wall sliding connection, the slider lateral wall is through two dead levers and slide lateral wall fixed connection.

Preferably, one end of each of the two lead screws penetrates through the side wall of the base plate and is fixedly connected with two hand wheels, and rubber pads are glued on the side walls of the two hand wheels.

Preferably, through holes are formed in the inner walls of the two strip-shaped cavities far away from the sliding plate.

Preferably, bottom plate and baffle all are the U type form, the equal fixedly connected with a plurality of elastic bulge of bottom plate and baffle inner wall.

Preferably, the side wall of the bottom plate is fixedly connected with a traction rope, and the side wall of the bottom plate, which is far away from the traction rope, is fixedly connected with two rollers.

The utility model discloses following beneficial effect has:

1. the hydraulic oil cylinder is adjusted to stretch and retract, so that the baffle plate which is rotatably connected with the movable end of the hydraulic oil cylinder is driven to rotate, and the baffle plate can be matched with airplane wheels of different models and sizes, and the airplane wheel mounting device is simple to operate and high in practicability;

2. the strip-shaped cavity, the sliding plate, the connecting pipe, the sucking disc and the driving mechanism are arranged, the screw rod is rotated, the sliding block in threaded connection with the screw rod slides towards the direction far away from the connecting pipe, the sliding block drives the sliding plate to move through the fixing rod, and then gas in the connecting pipe and the sucking disc is pumped out, so that the internal pressure of the sucking disc is lower, the external pressure is higher than the internal pressure of the sucking disc, the bottom plate is tightly adsorbed on the ground under the action of the pressure, the stability of the bottom plate after being placed is improved, and the protection effect on an airplane wheel is further improved;

3. through setting up haulage rope and gyro wheel, artifical pulling haulage rope for the bottom plate moves under the gyro wheel rotation effect, makes the bottom plate have certain portability.

Drawings

Fig. 1 is a schematic structural view of a portable airplane wheel chock provided by the present invention;

FIG. 2 is an enlarged view of the structure at A in FIG. 1;

fig. 3 is a schematic view of a rear sectional structure of a portable airplane wheel chock provided by the present invention.

In the figure: the device comprises a base plate 1, a baffle 2, a hydraulic oil cylinder 3, a strip-shaped cavity 4, a lead screw 5, a slide block 6, a fixed rod 7, a slide plate 8, a connecting pipe 9, a suction cup 10, a hand wheel 11, a traction rope 12, a roller 13 and an elastic bulge 14.

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.

In the description of the present invention, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention.

Referring to fig. 1-3, a portable aircraft wheel fender includes

bottom plate

1, and 1 upper end of bottom plate is rotated through the pivot and is connected with baffle 2, and 1 upper end of bottom plate is rotated and is connected with hydraulic cylinder 3, and 3 expansion ends of hydraulic cylinder are rotated with 2 lower extremes of baffle and are connected, and are flexible through adjusting hydraulic cylinder 3, and then drive baffle 2 and rotate, and then baffle 2 can cooperate with the aircraft wheel of different models size.

Two strip-shaped cavities 4 are formed in the lower end of the bottom plate 1, two sliding plates 8 are connected to the inner walls of the two strip-shaped cavities 4 in a sealing and sliding mode, the two strip-shaped cavities 4 are close to two connecting pipes 9 of the inner wall fixedly connected with of the sliding plates 8, a plurality of suckers 10 are fixedly connected to the bottoms of the two connecting pipes 9, and driving mechanisms for driving the sliding plates 8 to slide are installed in the two strip-shaped cavities 4.

The driving mechanism comprises two lead screws 5 which are rotatably connected to the inner walls of the two strip-shaped cavities 4, sliding blocks 6 are connected to the side walls of the two lead screws 5 in a threaded mode, the sliding blocks 6 are respectively in sliding connection with the inner walls of the strip-shaped cavities 4, and the side walls of the sliding blocks 6 are fixedly connected with the side walls of the sliding plates 8 through two fixing rods 7.

One end of each screw 5 penetrates through the side wall of the bottom plate 1 and is fixedly connected with two hand wheels 11, and rubber pads are glued on the side walls of the two hand wheels 11.

Through holes are formed in the inner walls, far away from the sliding plate 8, of the two strip-shaped cavities 4, and the through holes are used for balancing pressure changes in the strip-shaped cavities 4 when the sliding plate 8 slides on the inner walls of the strip-shaped cavities 4.

Bottom plate 1 and baffle 2 all are the U type form for in aircraft wheel can get into bottom plate 1 and baffle 2, a plurality of elastic bulge 14 of the equal fixedly connected with of bottom plate 1 and the 2 inner walls of baffle, can protect bottom plate 1 and the 2 inner walls of baffle, increase its life.

The side wall of the bottom plate 1 is fixedly connected with a traction rope 12, and the side wall of the bottom plate 1 far away from the traction rope 12 is fixedly connected with two rollers 13, so that the bottom plate 1 is convenient to move and has certain portability.

In the utility model, the traction rope 12 is pulled manually, so that the bottom plate 1 moves under the rotating action of the roller 13, the airplane wheel is positioned inside the bottom plate 1, then the hydraulic oil cylinder 3 which is rotatably connected to the upper end of the bottom plate 1 is adjusted to stretch according to the size of the airplane wheel, and then the baffle 2 which is rotatably connected with the movable end of the hydraulic oil cylinder 3 is driven to rotate, and the baffle 2 can be matched with airplane wheels with different sizes, so that the movement of the airplane wheel is better hindered;

place behind ground at bottom plate 1 level, rotate hand wheel 11, drive the lead screw 5 rotation with 11 lateral wall fixed connection of hand wheel, the slider 6 that drives 5 lateral wall threaded connection with the lead screw slides to the direction that is close to hand wheel 11, and then slider 6 drives slide 8 through dead lever 7 and removes, and then strip chamber 4 takes out the gas in connecting pipe 9 and the sucking disc 10, make the internal pressure of sucking disc 10 lower, and then external pressure is greater than the internal pressure of sucking disc 10, make bottom plate 1 closely adsorb subaerial under the effect of pressure, increase the stability after bottom plate 1 places, further improve the effect of hindering to aircraft wheel removal.

Above, only be the concrete implementation of the preferred embodiment of the present invention, but the protection scope of the present invention is not limited thereto, and any person skilled in the art is in the technical scope of the present invention, according to the technical solution of the present invention and the design of the present invention, equivalent replacement or change should be covered within the protection scope of the present invention.

Claims

1. The utility model provides a portable aircraft wheel fender, includes bottom plate (1), its characterized in that, bottom plate (1) upper end is rotated through the pivot and is connected with baffle (2), bottom plate (1) upper end is rotated and is connected with hydraulic cylinder (3), hydraulic cylinder (3) expansion end is rotated with baffle (2) lower extreme and is connected, two bar-shaped chamber (4), two have been seted up to bottom plate (1) lower extreme bar-shaped chamber (4) inner wall sealing sliding connection has two slides (8), two bar-shaped chamber (4) are close to two connecting pipes (9) of inner wall fixedly connected with of slide (8), two a plurality of sucking discs (10) of bottom fixedly connected with in connecting pipe (9), two install gliding actuating mechanism of drive slide (8) in bar-shaped chamber (4).

2. The portable airplane wheel chock of claim 1, wherein the driving mechanism comprises two lead screws (5) rotatably connected to the inner walls of the two strip-shaped cavities (4), the side walls of the two lead screws (5) are both in threaded connection with sliding blocks (6), the sliding blocks (6) are respectively in sliding connection with the inner walls of the strip-shaped cavities (4), and the side walls of the sliding blocks (6) are fixedly connected with the side walls of the sliding plates (8) through two fixing rods (7).

3. The portable airplane wheel chock of claim 2, wherein one end of each of the two lead screws (5) penetrates through the side wall of the bottom plate (1) and is fixedly connected with two hand wheels (11), and rubber pads are glued on the side walls of the two hand wheels (11).

4. A portable aircraft wheel chock according to claim 1, characterised in that the two strip-shaped cavities (4) are perforated away from the inner wall of the skid plate (8).

5. The portable airplane wheel chock of claim 1, wherein the bottom plate (1) and the baffle (2) are both U-shaped, and a plurality of elastic protrusions (14) are fixedly connected to the inner walls of the bottom plate (1) and the baffle (2).

6. A portable aircraft wheel chock according to claim 1, characterized in that a towing rope (12) is fixedly connected to the side wall of the base plate (1), and two rollers (13) are fixedly connected to the side wall of the base plate (1) remote from the towing rope (12).