CN211724671U

CN211724671U - Wing dismounting structure applied to aircraft

Info

Publication number: CN211724671U
Application number: CN202020100720.6U
Authority: CN
Inventors: 熊朝海
Original assignee: Individual
Current assignee: Individual
Priority date: 2020-01-17
Filing date: 2020-01-17
Publication date: 2020-10-23
Anticipated expiration: 2030-01-17

Abstract

The utility model discloses a be applied to wing dismouting structure of aircraft, close the subassembly and set up the block subassembly on the fuselage including inserting that sets up on the wing, insert and close subassembly and block subassembly phase-match. The inserting assembly comprises an inserting column and a silica gel nut, one end of the inserting column is connected with the wing, and the other end of the inserting column is connected with the silica gel nut; the clamping component comprises a clamping seat and a clamping core, the clamping seat is fixed on the machine body, the clamping core is hinged to the clamping seat, a through hole for a silica gel nut to pass through is formed in the clamping seat, a notch is formed in the clamping core, and the opening width of the notch is larger than the diameter of the inserting column and smaller than the diameter of the silica gel nut. The utility model discloses in, stretch into the cassette to insert the post and make fuselage and wing paste when tight, rotate the card core to can make with the cassette closure insert the post and can not loosen and take off by the locking, reverse stir card core to open the back with the cassette and insert the post and can easily take out from the cassette, the operation is convenient, and the assembly stability is strong.

Description

Wing dismounting structure applied to aircraft

Technical Field

The utility model relates to an aircraft equipment technical field specifically is a be applied to wing dismouting structure of aircraft.

Background

Along with the continuous development of economy, people's life is walked into gradually to the aeromodelling, and for the convenience of carrying, generally for can dismantling between fuselage and the wing part to be connected, the dismantled connection of current fuselage and wing is generally realized through the screw, and for the stability of improving wing and fuselage connection, this dismouting structure need be close to the bearing, consequently has the problem of wrong screw difficulty, and twists the screw and need the instrument, and is consuming time longer, and user experience is relatively poor.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a be applied to wing dismouting structure of aircraft, its simple structure, the operation is convenient, and the packaging stability is strong.

In order to achieve the above object, the utility model provides a following technical scheme:

the utility model provides a be applied to wing dismouting structure of aircraft, is including setting up the block subassembly that inserts the subassembly and set up on the fuselage on the wing, insert and close subassembly and block subassembly phase-match.

The inserting assembly comprises an inserting column and a silica gel nut, threads are arranged on the outer wall of the inserting column, one end of the inserting column is connected with the wing, and the other end of the inserting column is connected with the silica gel nut;

the clamping component comprises a clamping seat and a clamping core, the clamping seat is fixed on the machine body, the clamping core is hinged to the clamping seat, a through hole for a silica gel nut to pass through is formed in the clamping seat, a notch is formed in the clamping core, and the opening width of the notch is larger than the diameter of the inserting column and smaller than the diameter of the silica gel nut.

In one embodiment, the clamping assembly further comprises a positioning ball head, and the positioning ball head is arranged at the connecting position of the clamping seat and the clamping core.

In one embodiment, the clamping assembly further includes a limiting member fixed to the body, and the limiting member is disposed on one side of the clamping core hinged to the clamping seat.

In one embodiment, a handle is arranged on the clamping core and is arranged on the other side of the hinged side of the clamping core and the clamping seat.

In one embodiment, the silica gel screw cap is provided with anti-slip teeth.

In one embodiment, the silicone nut is provided with a straight groove.

In one embodiment, the wing is provided with a threaded seat for fixing the inserted column, the inserted column penetrates through the threaded seat, and the inner wall of the threaded seat is provided with threads matched with the inserted column.

In one embodiment, the clamping seat is fixed on the machine body through screws.

The wing dismounting structure of the utility model closes the clamping seat and the clamping core after the inserting component is inserted into the clamping seat, at the moment, the inserting component is locked in the clamping component, namely, the body is fixedly connected with the wing, and the silica gel nut is adjusted to prevent the wing and the body from loosening; the clamping core is reversely pulled to unlock the inserting assembly and the clamping assembly after the clamping seat and the clamping core are opened, and the inserting column can be taken out of the clamping seat to finish the disassembly of the wing. The wing dismounting structure can realize the tight connection of the wing and the fuselage only by closing the clamping seat and the clamping core when being used again, and has the advantages of high assembling speed, simple operation and strong stability after being assembled; due to the adjustability of the inserting assembly, the wing dismounting structure has low requirement on the wall thickness precision of the fuselage and has certain universality.

Drawings

FIG. 1 is a schematic structural view of a wing dismounting structure in one embodiment 1;

FIG. 2 is a schematic structural view of a wing dismounting structure according to an embodiment 2;

FIG. 3 is a schematic structural view of the insertion assembly of FIGS. 1 and 2;

fig. 4 and 5 are schematic structural views of the snap assembly in fig. 1 and 2.

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 in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

Fig. 1 and fig. 2 are schematic structural diagrams of a wing dismounting structure in an embodiment, where the wing dismounting structure includes an insertion component disposed on a wing 11 and a clamping component disposed on a fuselage 12, the insertion component and the clamping component are matched, fig. 1 is a schematic structural diagram of the wing 11 and the fuselage 12 before assembly, and fig. 2 is a schematic structural diagram of the wing 11 and the fuselage 12 after assembly. Wherein, the plug-in subassembly is including inserting post 21 and silica gel nut 22, be provided with the screw thread on the outer wall of inserting post 21, the one end of inserting post 21 with wing 11 is connected, the other end with silica gel nut 22 is connected, and is specific, as shown in fig. 3, silica gel nut 22's side is provided with anti-skidding tooth 23, and the top surface is equipped with a word groove 24 to make the user can break away from the direct manual this silica gel nut 22 of twisting of instrument, or use the screwdriver to twist this silica gel nut 22. The clamping assembly comprises a clamping seat 31 and a clamping core 32, the clamping seat 31 is fixed on the machine body 12, the clamping core 32 is hinged to the clamping seat 31, a through hole for the silica gel nut 22 to pass through is formed in the clamping seat 31, a notch is formed in the clamping core 32, and the opening width of the notch is larger than the diameter of the inserting column 21 and smaller than the diameter of the silica gel nut 22.

When the plug is used for the first time, the position of the silicone nut 22 in the plug 21 needs to be adjusted, and the specific operation is as follows: after the inserting assembly is inserted into the clamping seat 31, the clamping seat 31 and the clamping core 32 are closed, the clamping core 32 is clamped between the silica gel screw cap 22 and the outer wall of the machine body 12 at the moment, the inserting assembly is locked in the clamping assembly, namely, the fixed connection between the wing 11 and the machine body 12 is realized, and the silica gel screw cap 22 is adjusted to be not loosened between the wing 11 and the machine body 12. The wing dismounting structure can realize the tight connection between the wing 11 and the fuselage 12 only by adjusting the position of the silica gel screw cap 22 during the first assembly and closing the clamping seat 31 and the clamping core 32 during the second use, and has the advantages of high assembly speed, simple operation and strong stability after assembly; when the wing is disassembled, the locking of the inserting component and the clamping component can be released only by reversely pulling the clamping core 32 to open the clamping seat 31 and the clamping core 32, and the inserting column 21 can be taken out of the clamping seat 31 to complete the disassembly of the wing. Due to the adjustability of the inserting assembly, the wing dismounting structure has low requirement on the wall thickness precision of the fuselage and has certain universality.

In one embodiment, as shown in fig. 3, the wing 11 is provided with a threaded seat 25 for fixing the plug-in post 21, the plug-in post 21 penetrates through the threaded seat 25, and the inner wall of the threaded seat 25 is provided with threads matched with the plug-in post 21.

In one embodiment, as shown in fig. 5, the clamping seat 31 is fixed on the machine body 12 through a pressing piece 36, the pressing piece is arranged at the bottom of the clamping seat 31, and the clamping seat 31 is fixed on the machine body 12 by a screw 37 sequentially penetrating through the pressing piece 36 and the clamping seat 31; the upper portion of the cartridge 31 is fixed to the body 12 by screws 37.

In one embodiment, as shown in fig. 4 and 5, the clamping assembly further includes a positioning ball 33, the positioning ball 33 is disposed at a connection position of the clamping seat 31 and the clamping core 32, after the clamping core 32 and the clamping seat 31 are closed, the positioning ball 33 can play a role of locking, and under the absence of an external force, it is ensured that the clamping core 32 and the clamping seat 31 are not loosened; when the wing 11 needs to be disassembled, the clamping core 32 can be opened by force. When the card core 32 and the card seat 31 are opened, in order to avoid that the opening angle of the card core 32 is too large to cause the reverse locking of the card core 32 and the card seat 31, the clamping assembly further comprises a limiting member 34, the limiting member 34 is fixed on the machine body 12, the limiting member 34 is arranged on one side of the card core 32, which is hinged to the card seat 31, when the card core 32 rotates to a certain angle, the limiting member 34 is touched, the rotating angle cannot be continuously increased under the action of the limiting member 34, and the maximum included angle between the card core 32 and the card seat 31 is limited. Preferably, the card core 32 is provided with a handle 35, the handle 35 is disposed on the other side of the hinged side of the card core 32 and the card seat 31, specifically, the handle 35 and the card core 32 are integrally formed, and a user can toggle the handle 35 to close and open the card seat 31 and the card core 32, so as to exert force.

The foregoing examples, while indicating preferred embodiments of the invention, are given by way of illustration and description, it is to be understood that the invention is not limited to the disclosed forms herein but is not intended to be exhaustive or to exclude other examples and may be used in various other combinations, modifications, and environments and is capable of changes within the scope of the inventive concept as expressed herein, commensurate with the above teachings or the skill or knowledge of the relevant art, and not to limit the scope of the invention. It should be noted that, for those skilled in the art, various changes and modifications can be made without departing from the spirit and scope of the present invention, and these changes and modifications can be made by those skilled in the art without departing from the spirit and scope of the present invention, which is to be construed as being limited only by the appended claims. Therefore, the protection scope of the present invention should be subject to the appended claims.

Claims

1. A wing dismounting structure applied to an aircraft is characterized by comprising an inserting assembly arranged on a wing and a clamping assembly arranged on a fuselage, wherein the inserting assembly is matched with the clamping assembly;

2. The wing assembly and disassembly structure applied to the aircraft of claim 1, wherein the clamping assembly further comprises a positioning ball head, and the positioning ball head is arranged at the joint of the clamping seat and the clamping core.

3. The wing assembly and disassembly structure applied to an aircraft of claim 2, wherein the engaging assembly further comprises a limiting member fixed on the fuselage, and the limiting member is disposed on a side of the core and the engaging seat that are hinged to each other.

4. The wing dismounting structure applied to aircraft according to claim 1, wherein a handle is arranged on the clamping core, and the handle is arranged on the other side of the hinged side of the clamping core and the clamping seat.

5. The wing dismounting structure applied to aircraft according to claim 1, wherein the silica gel screw cap is provided with anti-slip teeth.

6. The wing dismounting structure applied to aircraft according to claim 1, wherein the silicone nut is provided with a straight groove.

7. A wing dismounting structure applied to an aircraft according to claim 1, wherein the wing is provided with a screw seat for fixing the inserted column, the inserted column penetrates through the screw seat, and the inner wall of the screw seat is provided with a screw thread matched with the inserted column.

8. A wing assembly and disassembly structure as claimed in claim 1, wherein the cartridge is fixed to the fuselage by screws.