CN216734740U - Connecting mechanism between unmanned aerial vehicle parts - Google Patents

Abstract

The utility model relates to the technical field of aircraft design, in particular to a connecting mechanism between components of an unmanned aerial vehicle. The utility model relates to a connecting mechanism between unmanned aerial vehicle parts, comprising: the wing-shaped extension piece is fixed on one side of the fuselage, the wing is matched with the extension piece, a positioning groove is formed in the extension piece, the connection assembly is arranged in the positioning groove, and two ends of the connection assembly are respectively inserted into the wing and the extension piece; when the wing is fixed, one end of the wing is abutted to the separating surface of the extending block, and the connecting component fixes the wing and the extending block. The utility model has simple structure, realizes quick assembly and disassembly through the design of the connecting mechanism, and reduces the assembly and disassembly time; meanwhile, tools are not needed in the process of assembly and disassembly, so that the problem that the tools are lost and cannot be assembled and disassembled is avoided; the utility model has simple structure and easy processing, only needs to punch a hole on the fixed casing and the fixed liner tube and additionally adds a locking buckle, and has low manufacturing cost.

Description

Connecting mechanism between unmanned aerial vehicle parts

Technical Field

The utility model relates to the technical field of aircraft design, in particular to a connecting mechanism between components of an unmanned aerial vehicle.

Background

Along with the rise of the unmanned aerial vehicle industry, unmanned aerial vehicle products are more and more diversified. While diversified, unmanned aerial vehicle product has many common characteristics again. In order to facilitate transportation, processing and manufacturing, most industrial unmanned aerial vehicles adopt a design with easy disassembly and assembly among components, such as detachable wings, detachable empennage and the like. Unmanned aerial vehicle's operational environment is comparatively harsh, and this requires unmanned aerial vehicle's working property good, and unmanned aerial vehicle can dismantle the quality of coupling mechanism between the part, directly influences unmanned aerial vehicle's working property.

In the prior art, connecting structures among unmanned aerial vehicle parts are mostly fixed by bolts, and the disassembly and the fixation need tools, so that the disassembly is complex, and the pneumatic appearance of a machine body is influenced by the connecting structures; therefore, the development of a connecting mechanism between components of the unmanned aerial vehicle is necessary.

SUMMERY OF THE UTILITY MODEL

The utility model aims to provide a connecting mechanism between unmanned aerial vehicle components to solve the technical problems that the connecting mechanism is complex to disassemble and needs to be operated by means of a professional tool in the prior art.

In order to achieve the above object, an embodiment of the present invention provides a connection mechanism between components of an unmanned aerial vehicle, including:

the aircraft comprises a wing, an extension block and a connecting assembly, wherein the extension block is fixed on one side of an aircraft body, the wing is matched with the extension block, a positioning groove is formed in the extension block, the connecting assembly is arranged in the positioning groove, and two ends of the connecting assembly are respectively inserted into the wing and the extension block; wherein

When the wing is fixed, one end of the wing is abutted against the separating surface of the extending block, and the connecting component fixes the wing and the extending block.

Preferably, the connection assembly includes: the fixed sleeve is hollow, one end of the fixed sleeve is fixed on the side wall of the wing, and the other end of the fixed sleeve faces the extension block;

one end of the fixed liner tube is fixed on the separating surface of the extending block, the other end of the fixed liner tube faces the wing, the fixed liner tube is matched with the fixed sleeve, and the fixed liner tube is suitable for being inserted into the fixed sleeve;

one end of the fixed sleeve close to the extension block is provided with a through hole, the corresponding position of the fixed liner tube is provided with the same through hole, and the locking buckle is suitable for being inserted into the through hole; wherein

When the fixing device is fixed, the fixed liner tube is inserted into the fixed sleeve until the two through holes are superposed, and then the locking buckle is inserted for locking.

Preferably, the locking buckle is an R-shaped buckle, and is made of elastic materials; when the fixing device is fixed, one end of the locking buckle is inserted into the coincident through hole to limit the fixed liner tube and the fixed sleeve, and the other end of the locking buckle is abutted to the outer wall of the fixed sleeve.

Preferably, the fixed liner and the fixed casing are round tubes.

Preferably, the fixed liner and the fixed casing are square tubes.

Preferably, the locking buckle comprises: the handle section is in a circular ring shape, one end of the handle section is fixed with the limiting section, and the other end of the handle section is fixed with the locking section;

the limiting section is a vertical round pipe, and the outer diameter of the limiting section is not larger than the inner diameter of the through hole;

the locking section is wavy; when the fixing device is fixed, the limiting section is inserted into the through hole, and the locking section is abutted to the outer wall of the fixing sleeve.

Compared with the prior art, the embodiment of the utility model has the following beneficial effects: a connecting mechanism between components of an unmanned aerial vehicle realizes the effect of quickly disassembling and fixing wings and a machine body by matching a fixed sleeve, a fixed liner tube and a locking buckle, achieves the technical effect of quickly disassembling and assembling by inserting the fixed liner tube into the fixed sleeve and inserting the locking buckle into a superposed through hole, and greatly shortens the disassembling and assembling time; meanwhile, the locking buckle is disassembled without using other workpieces, so that the trouble that the locking buckle cannot be disassembled due to the loss of tools is avoided; the utility model has simple structure, easy processing and low manufacturing cost, and is suitable for large-batch popularization and use.

Drawings

The utility model is further illustrated with reference to the following figures and examples.

Figure 1 shows a perspective view of a connection between components of a drone according to the utility model;

FIG. 2 shows a perspective view of an extension block of the present invention;

figure 3 shows a fixed state view of the connection assembly of the present invention;

fig. 4 shows a separated state view of the connection assembly of the present invention.

In the figure:

1. an airfoil; 2. an extension block; 21. positioning a groove; 22. a separating surface; 3. a connecting assembly; 31. fixing the sleeve; 32. fixing the liner tube; 33. a locking buckle; 331. a limiting section; 332. a handle section; 333. and (4) locking the section.

Detailed Description

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

As shown in fig. 1 to 4, the present invention provides a connection mechanism between components of an unmanned aerial vehicle, including: the aircraft comprises wings 1, extension blocks 2 and a connecting assembly 3, wherein the extension blocks 2 are fixed on one side of an aircraft body, and the edges of the extension blocks 2 are streamline and consistent with the streamline of the aircraft body; the extension block 2 is used as the main connecting and fixing structure of the utility model, and plays a role in connecting and fixing the wing 1. The wing 1 is matched with the extension block, a positioning groove 21 is formed in the extension block 2, the connecting assembly 3 is arranged in the positioning groove 21, and two ends of the connecting assembly 3 are respectively inserted into the wing 1 and the extension block 2; when the wing is fixed, one end of the wing 1 is abutted against the parting surface 22 of the extension block 2, and the connecting component 3 fixes the wing 1 and the extension block 2. The wing assembly is simple in structure and convenient to operate, the wing 1 and the extension block 2 are fixedly connected through the connecting assembly 3, the wing 1 is rapidly disassembled, and meanwhile, the disassembling and assembling time is reduced; and the connecting assembly 3 does not need to be disassembled and assembled by means of an external tool, so that the trouble that the connecting assembly cannot be disassembled and assembled due to loss of the tool is avoided.

Optionally, the connection assembly 3 includes: the fixing device comprises a fixing sleeve 31, a fixing liner 32 and a locking buckle 33, wherein the fixing sleeve 31 is hollow, one end of the fixing sleeve 31 is fixed on the side wall of the wing 1, and the other end of the fixing sleeve 31 faces to an extension block 2; one or more fixed sleeves 31 are fixed in the wing 1, one or more fixed bushings are correspondingly fixed in the fixed bushings 32, and the fixed firmness of the wing 1 can be improved by arranging the plurality of fixed sleeves 31 according to the size of the wing 1. The fixed liner 32 is fixed at one end to the parting surface 22 of the extension block 2, the other end of the fixed liner 32 faces the wing 1, the fixed liner 32 is matched with the fixed casing 31, and the fixed liner 32 is suitable for being inserted into the fixed casing 31; the fixed liner tube 32 and the fixed sleeve 31 are circular tubes, square tubes or other tubular bodies. A through hole is formed in one end, close to the extension block 2, of the fixing sleeve 31, the same through hole is formed in the corresponding position of the fixing liner tube 32, and the locking buckle 33 is suitable for being inserted into the through hole; when the fixing is performed, the fixing liner tube 32 is inserted into the fixing sleeve 31 until the two through holes are overlapped, and then the locking buckle 33 is inserted for locking. After the locking buckle 33 is inserted into the overlapped through hole, the locking buckle 33 can limit the relative displacement between the fixed pipe sleeve and the fixed liner pipe 32, and the other end of the locking buckle 33 abuts against the outer wall of the fixed sleeve 31 to complete locking.

Preferably, the locking buckle 33 is an R-shaped buckle, and the locking buckle 33 is made of an elastic material; when the fixing device is fixed, one end of the locking buckle 33 is inserted into the coincident through hole to limit the fixed liner tube 32 and the fixed casing 31, and the other end of the locking buckle 33 is abutted to the outer wall of the fixed casing 31. The locking buckle 33 includes: the handle comprises a limiting section 331, a handle section 332 and a locking section 333, wherein the handle section 332 is annular, one end of the handle section 332 is fixed with the limiting section 331, and the other end of the handle section 332 is fixed with the locking section 333; the limiting section 331 is a vertical round tube, and the outer diameter of the limiting section 331 is not larger than the inner diameter of the through hole; the locking section 333 is wavy; when the fixing is performed, the limiting section 331 is inserted into the through hole, and the locking section 333 is abutted against the outer wall of the fixing sleeve 31; during disassembly, the handle section 332 is pinched and pulled outwards, so that the limiting section 331 is separated from the through hole, meanwhile, the locking section 333 is separated from the fixed sleeve 31, and the wing 1 is pulled outwards, so that the fixed sleeve 31 is separated from the fixed liner 32, the effect of quickly disassembling the wing 1 can be realized, the assembling and disassembling time is shortened, and the working efficiency is improved.

The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims (6)

1. The utility model provides a coupling mechanism between unmanned aerial vehicle part which characterized in that includes:

the wing-shaped extension piece is fixed on one side of the fuselage, the wing is matched with the extension piece, a positioning groove is formed in the extension piece, the connection assembly is arranged in the positioning groove, and two ends of the connection assembly are respectively inserted into the wing and the extension piece; wherein

When the wing is fixed, one end of the wing is abutted against the separating surface of the extending block, and the connecting component fixes the wing and the extending block.

2. A connection mechanism between unmanned aerial vehicle components as claimed in claim 1,

the connecting assembly includes: the fixed sleeve is hollow, one end of the fixed sleeve is fixed on the side wall of the wing, and the other end of the fixed sleeve faces the extension block;

one end of the fixed liner tube is fixed on the separating surface of the extending block, the other end of the fixed liner tube faces the wing, the fixed liner tube is matched with the fixed sleeve, and the fixed liner tube is suitable for being inserted into the fixed sleeve;

one end of the fixed sleeve close to the extension block is provided with a through hole, the corresponding position of the fixed liner tube is provided with the same through hole, and the locking buckle is suitable for being inserted into the through hole; wherein

When the fixing device is fixed, the fixed liner tube is inserted into the fixed sleeve until the two through holes are superposed, and then the locking buckle is inserted for locking.

3. A connection mechanism between unmanned aerial vehicle components as claimed in claim 2,

the locking buckle is an R-shaped buckle and is made of an elastic material; when the fixing device is fixed, one end of the locking buckle is inserted into the coincident through hole to limit the fixed liner tube and the fixed sleeve, and the other end of the locking buckle is abutted to the outer wall of the fixed sleeve.

4. An inter-drone component connection mechanism according to claim 2,

the fixed liner tube and the fixed casing are circular tubes.

5. An inter-drone component connection mechanism according to claim 2,

the fixed liner tube and the fixed sleeve are square tubes.

6. A connection mechanism between unmanned aerial vehicle components as claimed in claim 3,

the locking buckle includes: the handle section is in a circular ring shape, one end of the handle section is fixed with the limiting section, and the other end of the handle section is fixed with the locking section;

the limiting section is a vertical round pipe, and the outer diameter of the limiting section is not larger than the inner diameter of the through hole;

the locking section is wavy; when the fixing device is fixed, the limiting section is inserted into the through hole, and the locking section is abutted to the outer wall of the fixing sleeve.

Images