CN216684879U - Unmanned aerial vehicle rapid disassembly structure - Google Patents
Unmanned aerial vehicle rapid disassembly structure Download PDFInfo
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- CN216684879U CN216684879U CN202220353068.8U CN202220353068U CN216684879U CN 216684879 U CN216684879 U CN 216684879U CN 202220353068 U CN202220353068 U CN 202220353068U CN 216684879 U CN216684879 U CN 216684879U
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Abstract
The utility model provides an unmanned aerial vehicle quick-release structure, which relates to the technical field of unmanned aerial vehicles, and solves the technical problems that the mounting equipment cannot be quickly dismounted by a traditional unmanned aerial vehicle in the prior art, the mounting equipment is low in replacement efficiency, and the working efficiency of the unmanned aerial vehicle is influenced, because a plurality of strong magnets are respectively arranged in a quick-release upper assembly and a quick-release lower assembly, and the quick-release upper assembly and the quick-release lower assembly are magnetically connected by utilizing the magnets, so that the unmanned aerial vehicle main body and an unmanned aerial vehicle mounting component are quickly dismounted.
Description
Technical Field
The utility model relates to the technical field of unmanned aerial vehicles, in particular to a quick release structure of an unmanned aerial vehicle.
Background
An unmanned aircraft, referred to as "drone", is an unmanned aircraft that is operated by a radio remote control device and a self-contained program control device, or is operated autonomously, either completely or intermittently, by an onboard computer.
Usually, mounting equipment can be set up on unmanned aerial vehicle, and various electrical components can be carried on the mounting equipment to supply unmanned aerial vehicle to use.
However, traditional unmanned aerial vehicle can't be quick carries out the dismouting with carry on equipment and unmanned aerial vehicle body, causes carry equipment to change inefficiency, influences unmanned aerial vehicle work efficiency.
SUMMERY OF THE UTILITY MODEL
The utility model aims to provide a rapid disassembly structure of an unmanned aerial vehicle, which solves the technical problems that the mounting equipment cannot be rapidly disassembled and assembled with an unmanned aerial vehicle body by a traditional unmanned aerial vehicle in the prior art, the replacement efficiency of the mounting equipment is low, and the working efficiency of the unmanned aerial vehicle is influenced.
In a first aspect, the present invention provides a fast dismounting structure for an unmanned aerial vehicle, comprising: a quick release upper assembly and a quick release lower assembly;
the quick detach upper portion subassembly is used for being connected with the unmanned aerial vehicle main part, quick detach lower part subassembly is used for being connected with unmanned aerial vehicle carry component, the quick detach upper portion subassembly with all be provided with the magnet in the quick detach lower part subassembly, the quick detach upper portion subassembly with quick detach lower part subassembly passes through magnet magnetic force connects.
In an alternative embodiment of the method of the present invention,
the quick-release upper assembly comprises an upper shell, an upper N-pole magnet and an upper S-pole magnet;
the upper N pole magnet and the upper S pole magnet are arranged in the inner cavity of the upper shell.
In an alternative embodiment of the method of the present invention,
a plurality of first fixing columns are arranged in the upper shell;
a plurality of first fixed column along go up the outward flange interval setting of N utmost point magnet, and a plurality of first fixed column all with go up N utmost point magnet butt.
In an alternative embodiment of the method of the present invention,
a plurality of second fixing columns are arranged in the upper shell;
a plurality of the second fixed column is along the outward flange interval setting of last S utmost point magnet, and a plurality of the second fixed column all with go up S utmost point magnet butt.
In an alternative embodiment of the method of the present invention,
the quick-release lower component comprises a lower shell, a lower N-pole magnet and a lower S-pole magnet;
and the inner cavity of the lower shell is internally provided with the lower N-pole magnet and the lower S-pole magnet.
In an alternative embodiment of the method of the present invention,
the rapid disassembly structure of the unmanned aerial vehicle further comprises a clamping component;
the clamping component is connected with the quick-release upper assembly, and the clamping component is detachably connected with the quick-release lower assembly.
In an alternative embodiment of the method of the present invention,
the clamping component is provided with a rotating shaft and is rotatably connected with the quick-release upper assembly through the rotating shaft.
In an alternative embodiment of the method of the present invention,
the joint component is close to the one end of quick detach lower part subassembly is provided with the joint arch, the surface of quick detach lower part subassembly is provided with the joint groove, the joint arch can stretch into in the joint groove.
In an alternative embodiment of the method of the present invention,
and one end of the clamping component, which is far away from the quick-release lower component, is provided with a pressing bulge.
In an alternative embodiment of the method of the present invention,
the rapid disassembly structure of the unmanned aerial vehicle further comprises a torsion spring;
the torsion spring is connected with the clamping component and is configured to enable the clamping protrusion to have a movement trend towards the clamping groove.
According to the rapid disassembly structure of the unmanned aerial vehicle, the rapid disassembly upper assembly and the rapid disassembly lower assembly are magnetically connected by the magnets through the strong magnets respectively arranged in the rapid disassembly upper assembly and the rapid disassembly lower assembly, so that the rapid disassembly and assembly of the unmanned aerial vehicle main body and the unmanned aerial vehicle mounting component are realized, and the technical problems that the mounting equipment is low in replacement efficiency and the working efficiency of the unmanned aerial vehicle is influenced because the mounting equipment and the unmanned aerial vehicle body cannot be rapidly disassembled and assembled by the traditional unmanned aerial vehicle in the prior art are solved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments or the prior art descriptions will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
Fig. 1 is a schematic overall structure diagram of a rapid disassembly structure of an unmanned aerial vehicle according to an embodiment of the present invention;
fig. 2 is a schematic view of an internal structure of a quick release upper assembly in a quick release structure of an unmanned aerial vehicle according to an embodiment of the present invention;
fig. 3 is a schematic view of an internal structure of a quick release lower assembly in the quick release structure of an unmanned aerial vehicle according to an embodiment of the present invention;
fig. 4 is a schematic structural diagram of a clamping member in the quick release structure of an unmanned aerial vehicle according to an embodiment of the present invention;
fig. 5 is a schematic structural view of a torsion spring in the quick release structure of an unmanned aerial vehicle according to an embodiment of the present invention.
Icon: 100-quick release upper assembly; 110-an upper housing; 120-upper N pole magnet; 130-upper S pole magnet; 140-a first fixed column; 150-a second fixed column; 200-quick release lower assembly; 210-a lower housing; 220-lower N-pole magnet; 230-lower S-pole magnet; 240-clamping groove; 300-a snap-fit member; 310-a rotating shaft; 320-clamping protrusions; 330-pressing the bump; 400-torsion spring.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the present invention, presented in the figures, is not intended to limit the scope of the utility model, as claimed, but is merely representative of selected embodiments of the utility model. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings or orientations or positional relationships that the products of the present invention are conventionally placed in use, and are only for convenience of describing the present invention and simplifying the description, but do not indicate or imply that the device or element to which the description refers must have a specific orientation, be constructed in a specific orientation, and be operated, and thus should not be construed as limiting the present invention. Furthermore, the terms "first," "second," "third," and the like are used solely to distinguish one from another and are not to be construed as indicating or implying relative importance.
Furthermore, the terms "horizontal", "vertical", "suspended" and the like do not imply that the components are absolutely horizontal or suspended, but may be slightly inclined. For example, "horizontal" merely means that the direction is more horizontal than "vertical" and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.
In the description of the present invention, it should also be noted that, unless otherwise explicitly specified or limited, the terms "disposed," "mounted," "connected," and "connected" are to be construed broadly and may, for example, be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Some embodiments of the utility model are described in detail below with reference to the accompanying drawings. The embodiments described below and the features of the embodiments can be combined with each other without conflict.
As shown in fig. 1, the unmanned aerial vehicle rapid disassembly structure that this embodiment provided includes: quick release upper assembly 100 and quick release lower assembly 200; quick detach upper portion subassembly 100 is used for being connected with the unmanned aerial vehicle main part, and quick detach lower part subassembly 200 is used for being connected with unmanned aerial vehicle carries the component, all is provided with the magnet in quick detach upper portion subassembly 100 and the quick detach lower part subassembly 200, and quick detach upper portion subassembly 100 and quick detach lower part subassembly 200 pass through magnet magnetic force and connect.
Specifically, the upper end and the unmanned aerial vehicle main part of quick detach upper assembly 100 are connected, the lower extreme and the unmanned aerial vehicle mounted component of quick detach lower part subassembly 200 are connected, set up magnet in quick detach upper assembly 100, correspond at quick detach lower part subassembly 200 and set up the opposite magnet of magnetic pole, quick detach upper assembly 100 and quick detach lower part subassembly 200 pass through magnetic connection, and the strong magnet direction of the magnet distribution in quick detach upper assembly 100 and the corresponding position in quick detach upper assembly 100 is unanimous, and the magnet magnetism at quick detach upper assembly 100 is opposite, the magnet magnetism at quick detach lower part subassembly 200 is opposite, avoid upper and lower subassembly direction adsorption error.
The unmanned aerial vehicle rapid disassembly structure that this embodiment provided, through respectively installing a plurality of strong magnets in quick detach upper assembly 100 and quick detach lower part subassembly 200, utilize the magnet to make quick detach upper assembly 100 and quick detach lower part subassembly 200 magnetic connection, realize the quick assembly disassembly of unmanned aerial vehicle main part and unmanned aerial vehicle carry component, the unable quick dismouting with carry equipment and unmanned aerial vehicle body of carrying equipment of traditional unmanned aerial vehicle who has alleviated that exists among the prior art, cause carry equipment to change inefficiency, influence unmanned aerial vehicle work efficiency's technical problem.
As shown in FIG. 2, in an alternative embodiment, the quick release upper assembly 100 includes an upper housing 110, an upper N pole magnet 120, and an upper S pole magnet 130; an upper N-pole magnet 120 and an upper S-pole magnet 130 are disposed in the inner cavity of the upper case 110.
Specifically, the upper case 110 forms a cavity structure, and an upper N-pole magnet 120 and an upper S-pole magnet 130 are disposed in the upper case 110, and the upper N-pole magnet 120 and the upper S-pole magnet 130 are respectively located at two sides of the inside of the upper case 110.
In an alternative embodiment, a plurality of first fixing posts 140 are provided in the upper housing 110; the plurality of first fixing posts 140 are arranged at intervals along the outer edge of the upper N-pole magnet 120, and the plurality of first fixing posts 140 are abutted against the upper N-pole magnet 120; a plurality of second fixing posts 150 are arranged in the upper housing 110; a plurality of second fixed columns 150 are arranged along the outer edge of the upper S pole magnet 130 at intervals, and the plurality of second fixed columns 150 are all abutted against the upper S pole magnet 130.
Specifically, a plurality of first fixing posts 140 and a plurality of second fixing posts 150 are provided in the upper housing 110, the plurality of first fixing posts 140 are spaced apart from each other at an outer edge of the upper N-pole magnet 120, the plurality of second fixing posts 150 are spaced apart from each other at an outer edge of the upper S-pole magnet 130, the plurality of first fixing posts 140 are used to restrict movement of the upper N-pole magnet 120, and the plurality of second fixing posts 150 are used to restrict movement of the upper S-pole magnet 130.
As shown in FIG. 3, in an alternative embodiment, the quick release lower assembly 200 includes a lower housing 210, a lower N-pole magnet 220, and a lower S-pole magnet 230; a lower N-pole magnet 220 and a lower S-pole magnet 230 are disposed in the inner cavity of the lower case 210.
Specifically, the lower case 210 forms a cavity structure, a lower N-pole magnet 220 and a lower S-pole magnet 230 are disposed in the lower case 210, and the lower N-pole magnet 220 and the lower S-pole magnet 230 are respectively disposed on two sides of the inside of the lower case 210.
The quick release structure of unmanned aerial vehicle that this embodiment provided, through last N utmost point magnet 120, last S utmost point magnet 130 and N utmost point magnet 220, the setting of S utmost point magnet 230 down, make quick release upper assembly 100 be connected with quick release lower part subassembly 200 through magnetic force.
On the basis of the foregoing embodiment, as shown in fig. 4, in an alternative implementation, the quick release structure of an unmanned aerial vehicle provided in this embodiment further includes a clamping member 300; snap member 300 is connected to quick release upper assembly 100, and snap member 300 is configured to be removably connected to quick release lower assembly 200.
Specifically, the clamping member 300 is installed on the quick release upper assembly 100, and after the quick release upper assembly 100 is connected with the quick release lower assembly 200, the clamping member 300 can clamp the quick release lower assembly 200, so as to connect and fix the quick release upper assembly 100 and the quick release lower assembly 200.
In an alternative embodiment, latch member 300 is provided with a pivot shaft 310, and latch member 300 is pivotally connected to quick release upper assembly 100 via pivot shaft 310.
Specifically, a rotating shaft 310 is disposed inside the clamping member 300, and the rotating shaft 310 is connected to the quick release upper assembly 100, so that the clamping member 300 can rotate around the rotating shaft 310 relative to the quick release upper assembly 100.
In an alternative embodiment, clamping member 300 is provided with a clamping protrusion 320 at an end adjacent to quick release lower assembly 200, and a clamping groove 240 is provided on an outer surface of quick release lower assembly 200, and clamping protrusion 320 can extend into clamping groove 240.
Specifically, the bottom end of the clamping member 300 is provided with a clamping protrusion 320, a clamping groove 240 is correspondingly formed on the quick release lower assembly 200, and when the quick release upper assembly 100 is connected with the quick release lower assembly 200, the clamping protrusion 320 extends into the clamping groove 240.
In an alternative embodiment, the end of clamping member 300 remote from quick release lower assembly 200 is provided with a press projection 330.
Specifically, the top of the clamping member 300 is provided with a pressing protrusion 330, and an operator can apply force to the pressing protrusion 330 to rotate the clamping member 300 relative to the quick release upper assembly 100, so that the clamping protrusion 320 extends out of the clamping groove 240 to release clamping.
As shown in fig. 5, in an alternative embodiment, the quick release structure of the drone further includes a torsion spring 400; a torsion spring 400 is coupled to the catching member 300, and the torsion spring 400 is configured to enable the catching protrusion 320 to have a tendency to move toward the catching groove 240.
Specifically, the torsion spring 400 is installed on the quick release upper assembly 100, so that the clamping member 300 has certain elasticity, and after the quick release lower assembly 200 contacts the quick release upper assembly 100, the clamping member 300 makes the clamping protrusion 320 extend into the clamping groove 240 due to the elasticity of the torsion spring 400.
The quick release structure of the unmanned aerial vehicle provided by the embodiment can clamp the quick release upper assembly 100 and the quick release lower assembly 200 through the arrangement of the clamping member 300, and can release the clamping of the quick release upper assembly 100 and the quick release lower assembly 200 through an operator.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the utility model has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.
Claims (10)
1. The utility model provides an unmanned aerial vehicle rapid disassembly structure which characterized in that includes: a quick release upper assembly (100) and a quick release lower assembly (200);
quick detach upper portion subassembly (100) are used for being connected with the unmanned aerial vehicle main part, quick detach lower part subassembly (200) are used for being connected with unmanned aerial vehicle carries the component, quick detach upper portion subassembly (100) with all be provided with the magnet in quick detach lower part subassembly (200), quick detach upper portion subassembly (100) with quick detach lower part subassembly (200) pass through magnet magnetic force connects.
2. The rapid disassembly structure of unmanned aerial vehicle of claim 1,
the quick release upper assembly (100) comprises an upper shell (110), an upper N-pole magnet (120) and an upper S-pole magnet (130);
the upper N-pole magnet (120) and the upper S-pole magnet (130) are arranged in the inner cavity of the upper shell (110).
3. The rapid disassembly structure of unmanned aerial vehicle of claim 2,
a plurality of first fixing columns (140) are arranged in the upper shell (110);
the first fixing columns (140) are arranged along the outer edge of the upper N-pole magnet (120) at intervals, and the first fixing columns (140) are abutted to the upper N-pole magnet (120).
4. The rapid disassembly structure of unmanned aerial vehicle of claim 3,
a plurality of second fixing columns (150) are arranged in the upper shell (110);
the second fixing columns (150) are arranged along the outer edge of the upper S-pole magnet (130) at intervals, and the second fixing columns (150) are abutted to the upper S-pole magnet (130).
5. The rapid disassembly structure of unmanned aerial vehicle of claim 2,
the quick release lower assembly (200) comprises a lower shell (210), a lower N-pole magnet (220) and a lower S-pole magnet (230);
the lower N-pole magnet (220) and the lower S-pole magnet (230) are arranged in the inner cavity of the lower shell (210).
6. The rapid disassembly structure of unmanned aerial vehicle of claim 1,
the rapid disassembly structure of the unmanned aerial vehicle further comprises a clamping component (300);
the clamping member (300) is connected with the quick-release upper assembly (100), and the clamping member (300) is detachably connected with the quick-release lower assembly (200).
7. The rapid disassembly structure of unmanned aerial vehicle of claim 6,
the clamping component (300) is provided with a rotating shaft (310), and the clamping component (300) is rotatably connected with the quick-release upper assembly (100) through the rotating shaft (310).
8. The rapid disassembly structure of unmanned aerial vehicle of claim 7,
clamping component (300) are close to the one end of quick detach lower part subassembly (200) is provided with joint arch (320), the surface of quick detach lower part subassembly (200) is provided with joint groove (240), joint arch (320) can stretch into in joint groove (240).
9. The rapid disassembly structure of unmanned aerial vehicle of claim 7,
and one end of the clamping component (300) far away from the quick-release lower assembly (200) is provided with a pressing bulge (330).
10. The rapid disassembly structure of unmanned aerial vehicle of claim 8,
the rapid unmanned aerial vehicle disassembly structure further comprises a torsion spring (400);
the torsion spring (400) is connected with the clamping component (300), and the torsion spring (400) is configured to enable the clamping protrusion (320) to have a movement trend towards the clamping groove (240).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220353068.8U CN216684879U (en) | 2022-02-21 | 2022-02-21 | Unmanned aerial vehicle rapid disassembly structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220353068.8U CN216684879U (en) | 2022-02-21 | 2022-02-21 | Unmanned aerial vehicle rapid disassembly structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216684879U true CN216684879U (en) | 2022-06-07 |
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|---|---|---|---|
| CN202220353068.8U Active CN216684879U (en) | 2022-02-21 | 2022-02-21 | Unmanned aerial vehicle rapid disassembly structure |
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| Country | Link |
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| CN (1) | CN216684879U (en) |
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- 2022-02-21 CN CN202220353068.8U patent/CN216684879U/en active Active
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