CN218929775U

CN218929775U - Quick-release tail wing and aircraft

Info

Publication number: CN218929775U
Application number: CN202223514357.0U
Authority: CN
Inventors: 胡华智; 邓益
Original assignee: Ehang Intelligent Equipment Guangzhou Co Ltd
Current assignee: Ehang Intelligent Equipment Guangzhou Co Ltd
Priority date: 2022-12-28
Filing date: 2022-12-28
Publication date: 2023-04-28
Anticipated expiration: 2032-12-28

Abstract

The utility model discloses a quick-release tail wing and an aircraft, wherein a locking mechanism comprises a plug hole formed in the end part of a first wing body and a plug rod formed in the end part of a second wing body, a locking groove is formed in the outer side wall of the plug rod, a locking part is detachably arranged in the plug hole, the end part of the first wing body is abutted against the end part of the second wing body, the plug rod penetrates through the plug hole and is positioned in the locking groove, when the first wing body and the second wing body are combined, the plug rod penetrates into the plug hole, the locking part in the plug hole is clamped in the locking groove of the plug rod so as to prevent the plug rod from accidentally falling out from the plug hole, and the plug rod can be released after the locking part is detached, so that the plug hole and the plug rod are quickly separated.

Description

Quick-release tail wing and aircraft

Technical Field

The utility model relates to the technical field of aircrafts, in particular to a quick-release tail wing and an aircraft.

Background

The tail fin of the existing fixed wing aircraft is generally provided with a connecting plate at the root of the tail fin, and a plurality of through holes are arranged on the connecting plate so as to connect the tail fin on a machine body through bolts (or rivets), or two tail fins are connected into a whole through the connecting plate and the bolts (or rivets). In order to improve the connection strength, a large number of bolts (or rivets) are required to be connected to the connecting plate, so that a large number of working hours are required to be consumed when the tail wing is detached.

Disclosure of Invention

In order to overcome the defects of the prior art, the utility model aims to provide a quick-dismantling tail wing and an aircraft so as to solve the problem that the existing aircraft tail wing is difficult to disassemble and assemble.

The utility model adopts the following technical scheme:

a quick-release tail wing comprises a first wing body, a second wing body and a locking mechanism;

the locking mechanism comprises a plug hole formed in the end part of the first wing body and a plug rod arranged in the end part of the second wing body, a locking groove is formed in the outer side wall of the plug rod, a locking part is detachably arranged in the plug hole, the end part of the first wing body is abutted to the end part of the second wing body, the plug rod penetrates through the plug hole, and the locking part is located in the locking groove.

In some optional embodiments, the locking mechanism includes a plug tube with the plug hole, the plug tube is fixedly connected to the first wing body, a connection through hole is formed in a wall surface of the plug tube, and the locking component passes through the connection through hole and penetrates into the plug hole.

In some alternative embodiments, two locking parts are disposed in the plugging hole in parallel, and the two locking parts are respectively located at two sides of the plugging rod.

In certain alternative embodiments, the locking groove is disposed about the axis of the insertion rod.

In some alternative embodiments, both inner side walls of the locking groove are disposed obliquely to the axis of the plug rod.

In some alternative embodiments, the end of the plug rod is provided with a guiding conical surface, and a generatrix of the guiding conical surface is obliquely arranged with the axis of the plug rod.

In some optional embodiments, the first wing body is provided with a first fixing tube, the first fixing tube is fixedly connected to the wing spar and the wing rib of the first wing body, and the plug tube penetrates through the first fixing tube.

In some optional embodiments, the second wing body is provided with a second fixing tube, the second fixing tube is fixedly connected to the spar and the rib of the second wing body, and the plugging rod penetrates through the second fixing tube.

In some optional embodiments, the plug tube is provided with a mounting block, the mounting block is provided with the connection through hole, and the connection through hole penetrates through the plug hole.

In order to solve the same technical problems, the utility model also provides an aircraft, which comprises the quick-release tail wing.

Compared with the prior art, the utility model has the beneficial effects that:

when the first wing body is combined with the second wing body, the plug rod penetrates into the plug hole, and the locking part in the plug hole is clamped in the locking groove of the plug rod so as to prevent the plug rod from accidentally falling out of the plug hole, and the plug rod can be released after the locking part is detached, so that the plug hole and the plug rod are quickly separated.

Drawings

FIG. 1 is a schematic view of the overall structure of the quick release tail of the utility model;

FIG. 2 is one of the exploded schematic views of the quick release tail of the utility model;

FIG. 3 is a second schematic explosion diagram of the quick release tail of the present utility model;

FIG. 4 is an enlarged schematic view of FIG. 2 at A;

FIG. 5 is an enlarged schematic view at B in FIG. 3;

in the figure: 10. a first wing body; 11. a connecting pipe is inserted; 111. a mounting block; 12. a plug hole; 13. a first fixed tube; 20. a second wing body; 21. inserting a connecting rod; 211. a guide conical surface; 212. a locking groove; 22. a second fixed tube; 30. a locking member.

Detailed Description

In order that the utility model may be readily understood, a more complete description of the utility model will be rendered by reference to the appended drawings. Preferred embodiments of the present utility model are shown in the drawings. This utility model may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete.

It will be understood that when an element is referred to as being "fixed to" another element, it can be directly on the other element or intervening elements may also be present. When an element is referred to as being "connected" to another element, it can be directly connected to the other element or intervening elements may also be present. The terms "vertical," "horizontal," "left," "right," and the like are used herein for illustrative purposes only.

Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this utility model belongs. The terminology used herein in the description of the utility model is for the purpose of describing particular embodiments only and is not intended to be limiting of the utility model. The term "and/or" as used herein includes any and all combinations of one or more of the associated listed items.

Example 1

Referring to fig. 1 to 5, there is schematically shown a quick release tail of the present utility model, including a first wing 10, a second wing 20, and a locking mechanism.

The locking mechanism comprises a plug hole 12 formed in the end part of the first wing body 10 and a plug rod 21 formed in the end part of the second wing body 20, wherein the end part of the first wing body 10 is required to be connected with the end part of the second wing body 20, and the plug rod 21 penetrates into the plug hole 12, so that the first wing body 10 and the second wing body 20 can be connected. In order to prevent the first wing body 10 and the second wing body 20 from being separated accidentally, a locking groove 212 is formed on the outer side wall of the insertion rod 21, a locking component 30 is detachably arranged in the insertion hole 12, the end of the first wing body 10 is abutted against the end of the second wing body 20, the insertion rod 21 is penetrated in the insertion hole 12, the locking component 30 is located in the locking groove 212, and the locking component 30 is used for preventing the insertion rod 21 from being separated from the insertion hole 12. The plug rod 21 is released by simply removing the locking member 30 from the plug aperture 12.

Specifically, referring to fig. 4 and 5, the locking mechanism includes a socket 11 having a socket hole 12, the socket 11 is fixedly connected to the first wing 10, a connection through hole is formed in a wall surface of the socket 11, an axis of the connection through hole is perpendicular to an axis of the socket 11, the axis of the connection through hole is non-coplanar with an axis of the socket 11, and the locking member 30 passes through the connection through hole and penetrates into the socket hole 12. In this embodiment, two parallel locking members 30 are disposed in the plugging hole 12, and the two locking members 30 are respectively located at two sides of the plugging rod 21, so that the locking members 30 can keep the stress balance of the plugging rod 21 when locking the plugging rod 21.

Preferably, the locking groove 212 is provided around the axis of the insertion rod 21, and the locking member 30 can be smoothly inserted into the locking groove 212 even if the installation angle of the insertion rod 21 has a certain deviation (the installation angle is referred to as the axis of the insertion rod 21) when the insertion rod 21 is assembled to the second wing body 20.

Both inner side walls of the locking groove 212 are inclined with the axis of the insertion rod 21, and the outer wall surface of the locking member 30 abuts against both inner side walls of the locking groove 212. The end of the insertion rod 21 is provided with a guiding conical surface 211, a generatrix of the guiding conical surface 211 is obliquely arranged with the axis of the insertion rod 21, and the guiding conical surface 211 can facilitate the insertion rod 21 to penetrate into the insertion hole 12.

The first wing body 10 is provided with a first fixed pipe 13, the first fixed pipe 13 is fixedly connected with the wing spar and the wing rib of the first wing body 10, and the plug pipe 11 is arranged on the first fixed pipe 13 in a penetrating mode, and the wing spar and the wing rib of the first wing body 10 are of main stress structures, so that the connection between the plug pipe 11 and the first wing body 10 is more stable. Correspondingly, the second wing body 20 is provided with a second fixed pipe 22, the second fixed pipe 22 is fixedly connected with the spar and the rib of the second wing body 20, and the inserting connection rod 21 penetrates through the second fixed pipe 22, and the spar and the rib of the second wing body 20 are of main stress structures, so that the connection between the inserting connection rod 21 and the second wing body 20 is more stable.

The mounting block 111 is arranged on the plug tube 11, the mounting block 111 is provided with a connecting through hole, the connecting through hole penetrates through the plug hole 12, and the mounting block 111 can be conveniently provided with the connecting through hole.

Example 2

In order to solve the same technical problems, the utility model also provides an aircraft, which comprises the quick-release tail wing

In summary, when the first wing body 10 and the second wing body 20 are combined, the inserting rod 21 penetrates into the inserting hole 12, the locking component 30 in the inserting hole 12 is clamped in the locking groove 212 of the inserting rod 21 to prevent the inserting rod 21 from accidentally falling out of the inserting hole 12, and the inserting rod 21 can be released by removing the locking component 30, so that the inserting hole 12 and the inserting rod 21 are rapidly separated.

The foregoing description is only illustrative of the present utility model and is not intended to limit the scope of the utility model, and all equivalent structures or equivalent processes or direct or indirect application in other related technical fields are included in the scope of the present utility model.

Claims

1. The quick-dismantling tail wing is characterized by comprising a first wing body, a second wing body and a locking mechanism;

2. The quick release tail wing according to claim 1, wherein the locking mechanism comprises a plug tube with the plug hole, the plug tube is fixedly connected to the first wing body, a connecting through hole is formed in a wall surface of the plug tube, and the locking component penetrates through the connecting through hole and penetrates into the plug hole.

3. The quick release tail according to claim 1, wherein two locking parts are arranged in parallel in the insertion hole, and the two locking parts are respectively positioned at two sides of the insertion rod.

4. The quick release tail of claim 1, wherein the locking groove is disposed about an axis of the splicing rod.

5. The quick release tail of claim 4, wherein both inner side walls of the locking groove are disposed obliquely to the axis of the attachment post.

6. The quick release tail according to claim 1, wherein the end of the plugging rod is provided with a guiding conical surface, and a generatrix of the guiding conical surface is obliquely arranged with the axis of the plugging rod.

7. The quick release tail of claim 2, wherein the first wing body is provided with a first fixed tube fixedly connected to the spar and rib of the first wing body, and the plug tube is disposed through the first fixed tube.

8. The quick release tail of claim 1, wherein the second wing body is provided with a second fixed tube fixedly connected to the spar and rib of the second wing body, and the plugging rod is inserted into the second fixed tube.

9. The quick release tail wing according to claim 2, wherein the insertion tube is provided with an installation block, the installation block is provided with the connection through hole, and the connection through hole penetrates through the insertion hole.

10. An aircraft comprising a quick release tail as claimed in any one of claims 1 to 9.