CN220501049U - Unmanned aerial vehicle quick detach fuselage - Google Patents
Unmanned aerial vehicle quick detach fuselage Download PDFInfo
- Publication number
- CN220501049U CN220501049U CN202321910467.0U CN202321910467U CN220501049U CN 220501049 U CN220501049 U CN 220501049U CN 202321910467 U CN202321910467 U CN 202321910467U CN 220501049 U CN220501049 U CN 220501049U
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- aerial vehicle
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- main body
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- 230000000149 penetrating effect Effects 0.000 claims description 15
- 238000013016 damping Methods 0.000 abstract description 10
- 238000012423 maintenance Methods 0.000 abstract description 3
- 230000002146 bilateral effect Effects 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000003032 molecular docking Methods 0.000 description 1
- 239000004033 plastic Substances 0.000 description 1
- 229920003023 plastic Polymers 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000013024 troubleshooting Methods 0.000 description 1
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Abstract
The utility model discloses an unmanned aerial vehicle quick-release fuselage, which comprises an unmanned aerial vehicle main body, wherein two sides of the unmanned aerial vehicle main body are symmetrically connected with a horn, the top end of the unmanned aerial vehicle main body is provided with an organic cover, the bottom end of the unmanned aerial vehicle main body is symmetrically fixed with supporting legs, a quick-release mechanism is arranged between the organic cover and the unmanned aerial vehicle main body, the bottom end of the supporting legs is provided with a landing damping mechanism, and the quick-release mechanism comprises: the connecting component is arranged at the joint between the cover and the unmanned aerial vehicle main body; according to the utility model, through the designed groove, the through hole and the push plate, the limit block can be conveniently pushed to withdraw from the inside of the limit groove so as to release the limit of the machine cover, and meanwhile, the machine cover and the machine body can be firmly positioned by matching with the designed movable positioning hole and the positioning screw rod, so that the loosening condition is avoided, and compared with the prior art, the disassembly, assembly and maintenance work of the unmanned aerial vehicle body is greatly facilitated.
Description
Technical Field
The utility model belongs to the technical field of unmanned aerial vehicles, and particularly relates to a quick-dismantling machine body of an unmanned aerial vehicle.
Background
Unmanned aerial vehicles, abbreviated as "unmanned aerial vehicles", abbreviated as "UAVs", are unmanned aerial vehicles that are operated by means of radio remote control devices and self-contained programmed control devices, or are operated autonomously, either entirely or intermittently, by an onboard computer. Unmanned aerial vehicle is through the inside actuating mechanism of fuselage operation use, when unmanned aerial vehicle breaks down, when need carry out trouble-shooting to the inside actuating mechanism of fuselage, because be through screw and plastics buckle block fixed connection between current lid and the fuselage, when taking apart the fuselage, need just can pull down the lid with the help of instrument such as screwdriver and crow bar to at the in-process of taking apart, very easily appear because the perk power degree is too big, thereby leads to the cracked condition of buckle, for this we propose an unmanned aerial vehicle quick detach fuselage.
Disclosure of Invention
The utility model aims to provide an unmanned aerial vehicle quick-release fuselage, which aims to solve the problem that the unmanned aerial vehicle fuselage provided in the background art is troublesome in disassembly, assembly and maintenance.
In order to achieve the above purpose, the present utility model provides the following technical solutions: the utility model provides an unmanned aerial vehicle quick detach fuselage, includes the unmanned aerial vehicle main part, the bilateral symmetry of unmanned aerial vehicle main part is connected with the horn, the top of unmanned aerial vehicle main part is provided with the bonnet, the bottom symmetry of unmanned aerial vehicle main part is fixed with the supporting leg, be provided with quick assembly disassembly mechanism between bonnet and the unmanned aerial vehicle main part, the bottom of supporting leg is provided with descending damper, quick assembly disassembly mechanism includes:
the connecting component is arranged at the joint between the cover and the unmanned aerial vehicle main body;
a guide assembly disposed inside the connection assembly
The limiting components are arranged on two sides of the cover and are connected with the connecting components;
the guide reset component is arranged in the limiting component;
the locating component is arranged on two sides of the cover and is connected with the unmanned aerial vehicle body.
Preferably, the connecting assembly comprises a connecting groove formed in the top end of the unmanned aerial vehicle main body and a connecting block fixed inside the cover, and the connecting block is connected with the connecting groove in a clamping mode.
Preferably, the guide assembly comprises guide grooves symmetrically formed in the surface of the connecting block and guide blocks symmetrically fixed inside the connecting grooves, and the guide blocks are in sliding connection with the guide grooves.
Preferably, the limiting assembly comprises limiting grooves symmetrically formed in two sides of the unmanned aerial vehicle main body and grooves symmetrically formed in two sides of the cover, through holes are formed in the grooves in a penetrating mode, limiting rods penetrating through the through holes are arranged in the grooves, and the limiting rods are connected with the limiting grooves in a clamping mode.
Preferably, the reset component comprises a through groove which is formed in the surface of the limiting rod in a penetrating mode and a fixed block which is fixed in the groove, the fixed block is connected with the through groove in a sliding mode, and a telescopic spring is connected between the fixed block and the through groove.
Preferably, the locating component comprises locating holes symmetrically formed in two sides of the unmanned aerial vehicle main body and screw holes symmetrically formed in two sides of the inner wall of the machine cover in a penetrating mode, locating screws penetrating through the inside of the screw holes and connected with the locating holes are arranged on the side face of the machine cover, and the locating screws are fixedly connected with the locating holes in a screwing mode.
Preferably, the landing damper comprises a rubber damper sleeve sleeved at the bottom end of the supporting leg and clamping grooves symmetrically formed in two sides of the supporting leg, wherein buckles are symmetrically fixed on the inner wall of the rubber damper sleeve and are connected with the clamping grooves in a clamping mode.
Compared with the prior art, the utility model has the beneficial effects that:
according to the utility model, through the designed groove, the through hole and the push plate, the limit block can be conveniently pushed to withdraw from the inside of the limit groove so as to release the limit of the machine cover, and meanwhile, the machine cover and the machine body can be firmly positioned by matching with the designed movable positioning hole and the positioning screw rod, so that the loosening condition is avoided, and compared with the prior art, the disassembly, assembly and maintenance work of the unmanned aerial vehicle body is greatly facilitated.
Drawings
FIG. 1 is a schematic view of the appearance structure of the present utility model;
FIG. 2 is an enlarged schematic view of the utility model at A of FIG. 1;
FIG. 3 is an enlarged schematic view of the utility model at B of FIG. 1;
FIG. 4 is an enlarged schematic view of FIG. 3 at C in accordance with the present utility model;
FIG. 5 is an enlarged schematic view of the utility model at D of FIG. 1;
in the figure: 1. an unmanned aerial vehicle main body; 2. a horn; 3. a cover; 4. support legs; 100. a connecting groove; 101. a connecting block; 200. a guide groove; 201. a guide block; 300. a limit groove; 301. a groove; 302. a through hole; 303. a limit rod; 400. a through groove; 401. a fixed block; 402. a telescopic spring; 500. positioning holes; 501. a screw hole; 502. positioning a screw; 600. rubber damping sleeves; 601. a clamping groove; 602. and (5) a buckle.
Detailed Description
The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.
Referring to fig. 1 to 5, the present utility model provides a technical solution: the utility model provides an unmanned aerial vehicle quick detach fuselage, includes unmanned aerial vehicle main part 1, and unmanned aerial vehicle main part 1's bilateral symmetry is connected with horn 2, and unmanned aerial vehicle main part 1's top is provided with the bonnet 3, and unmanned aerial vehicle main part 1's bottom symmetry is fixed with supporting leg 4, is provided with quick assembly disassembly mechanism between bonnet 3 and unmanned aerial vehicle main part 1, and supporting leg 4's bottom is provided with descending damper, and quick assembly disassembly mechanism includes:
a connection assembly provided at a connection between the cover 3 and the unmanned aerial vehicle body 1;
a guide assembly disposed inside the connection assembly
The limiting components are arranged on two sides of the cover 3 and are connected with the connecting components;
the guide reset component is arranged in the limiting component;
the locating component is arranged on two sides of the cover 3 and is connected with the unmanned aerial vehicle body 1.
In this embodiment, preferably, the connection assembly includes a connection slot 100 formed in the top end of the unmanned aerial vehicle body 1 and a connection block 101 fixed inside the cover 3, and the cover 3 can be connected with the unmanned aerial vehicle body 1 by engaging the connection block 101 with the connection slot 100.
In this embodiment, preferably, the guiding assembly includes a guiding groove 200 symmetrically formed on the surface of the connecting block 101 and a guiding block 201 symmetrically fixed inside the connecting groove 100, and the guiding block 201 is slidably connected with the guiding groove 200, so as to perform a docking guiding function on the connecting block 101.
In this embodiment, preferably, the limiting component includes a limiting groove 300 symmetrically formed on two sides of the unmanned aerial vehicle main body 1 and a groove 301 symmetrically formed on two sides of the cover 3, a through hole 302 is formed in the groove 301 in a penetrating manner, a limiting rod 303 penetrating through the through hole 302 is arranged in the groove 301, and the limiting rod 303 is clamped with the limiting groove 300 to be connected, so that the cover 3 is temporarily positioned, and the positioning hole 500 and the screw hole 501 are aligned accurately.
In this embodiment, preferably, the reset component includes a through groove 400 formed on the surface of the stop lever 303 and a fixing block 401 fixed inside the groove 301, and the fixing block 401 is slidably connected with the through groove 400, so as to play a role in moving and guiding the stop lever 303, and a telescopic spring 402 is connected between the fixing block 401 and the through groove 400, so that the stop lever 303 can be driven to reset.
In this embodiment, preferably, the positioning assembly includes positioning holes 500 symmetrically formed on two sides of the unmanned aerial vehicle main body 1 and screw holes 501 symmetrically formed on two sides of the inner wall of the cover 3, and positioning screws 502 penetrating through the screw holes 501 and connected with the positioning holes 500 are disposed on the side surface of the cover 3, and the cover 3 can be firmly fixed by screwing the positioning screws 502 into the positioning holes 500.
In this embodiment, preferably, the falling damping mechanism includes a rubber damping sleeve 600 sleeved at the bottom end of the supporting leg 4 and a clamping groove 601 symmetrically arranged at two sides of the supporting leg 4, wherein a buckle 602 is symmetrically fixed on the inner wall of the rubber damping sleeve 600, and the rubber damping sleeve 600 can be limited by being clamped and connected with the clamping groove 601 through the buckle 602.
The working principle and the using flow of the utility model are as follows: when the equipment in the unmanned aerial vehicle main body 1 needs to be overhauled, the positioning screw 502 is unscrewed firstly, the end part of the positioning screw 502 is withdrawn from the inside of the positioning hole 500 and screwed into the screw 501, the limit of the cover 3 is released, then the limiting rod 303 in the groove 301 is pulled, the end part of the positioning screw is withdrawn from the inside of the limiting groove 300 and retracted into the inside of the through hole 302, the through groove 400 is driven to slide on the surface of the fixed block 401 to extrude the telescopic spring 402 to deform, the limit of the cover 3 is released, then the cover 3 is lifted to be separated from the unmanned aerial vehicle main body 1, the connecting block 101 is driven to withdraw from the inside of the connecting groove 100, the guide groove 200 is driven to be separated from the guide block 201, the detachment work of the cover 3 and the unmanned aerial vehicle main body 1 can be completed, then the unmanned aerial vehicle main body 1 can be overhauled through the connecting groove 100, the rubber damping sleeve 600 is sleeved with the supporting leg 4 when the unmanned aerial vehicle main body 1 needs to stably drop, the rubber damping sleeve 600 can be positioned by the clamping connection of the clamping groove 601 and the clamping buckle 602, and the rubber damping sleeve 600 can conveniently take the role of damping the supporting leg 4.
Although embodiments of the present utility model have been shown and described in detail with reference to the foregoing detailed description, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations may be made therein without departing from the principles and spirit of the utility model, the scope of which is defined in the appended claims and their equivalents.
Claims (7)
1. The utility model provides an unmanned aerial vehicle quick detach fuselage, includes unmanned aerial vehicle main part (1), the both sides symmetry of unmanned aerial vehicle main part (1) is connected with horn (2), the top of unmanned aerial vehicle main part (1) is provided with organic lid (3), the bottom symmetry of unmanned aerial vehicle main part (1) is fixed with supporting leg (4), its characterized in that: be provided with quick assembly disassembly mechanism between lid (3) and unmanned aerial vehicle main part (1), the bottom of supporting leg (4) is provided with descending damper, quick assembly disassembly mechanism includes:
the connecting component is arranged at the connecting part between the cover (3) and the unmanned aerial vehicle main body (1);
a guide assembly disposed inside the connection assembly
The limiting components are arranged on two sides of the cover (3) and are connected with the connecting components;
the reset component is arranged in the limit component;
the positioning components are arranged on two sides of the cover (3) and are connected with the unmanned aerial vehicle main body (1).
2. The unmanned aerial vehicle quick release fuselage of claim 1, wherein: the connecting assembly comprises a connecting groove (100) formed in the top end of the unmanned aerial vehicle main body (1) and a connecting block (101) fixed inside the cover (3), and the connecting block (101) is connected with the connecting groove (100) in a clamping mode.
3. The unmanned aerial vehicle quick release fuselage of claim 1, wherein: the guide assembly comprises guide grooves (200) symmetrically formed in the surface of the connecting block (101) and guide blocks (201) symmetrically fixed inside the connecting groove (100), and the guide blocks (201) are in sliding connection with the guide grooves (200).
4. The unmanned aerial vehicle quick release fuselage of claim 1, wherein: the limiting assembly comprises limiting grooves (300) symmetrically formed in two sides of the unmanned aerial vehicle main body (1) and grooves (301) symmetrically formed in two sides of the cover (3), through holes (302) are formed in the grooves (301) in a penetrating mode, limiting rods (303) penetrating through the through holes (302) are arranged in the grooves (301), and the limiting rods (303) are connected with the limiting grooves (300) in a clamping mode.
5. The unmanned aerial vehicle quick release fuselage of claim 1, wherein: the reset assembly comprises a penetrating groove (400) penetrating through the surface of the limiting rod (303) and a fixed block (401) fixed inside the groove (301), the fixed block (401) is connected with the penetrating groove (400) in a sliding mode, and a telescopic spring (402) is connected between the fixed block (401) and the penetrating groove (400).
6. The unmanned aerial vehicle quick release fuselage of claim 1, wherein: the positioning assembly comprises positioning holes (500) symmetrically formed in two sides of the unmanned aerial vehicle main body (1) and screw holes (501) symmetrically formed in two sides of the inner wall of the cover (3), positioning screws (502) penetrating through the screw holes (501) and connected with the positioning holes (500) are arranged on the side face of the cover (3), and the positioning screws (502) are fixedly connected with the positioning holes (500) in a screwing mode.
7. The unmanned aerial vehicle quick release fuselage of claim 1, wherein: the landing damper comprises a rubber damper sleeve (600) sleeved at the bottom end of a supporting leg (4) and clamping grooves (601) symmetrically formed in two sides of the supporting leg (4), buckles (602) are symmetrically fixed on the inner wall of the rubber damper sleeve (600), and the buckles (602) are connected with the clamping grooves (601) in a clamping mode.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321910467.0U CN220501049U (en) | 2023-07-19 | 2023-07-19 | Unmanned aerial vehicle quick detach fuselage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321910467.0U CN220501049U (en) | 2023-07-19 | 2023-07-19 | Unmanned aerial vehicle quick detach fuselage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220501049U true CN220501049U (en) | 2024-02-20 |
Family
ID=89879360
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202321910467.0U Active CN220501049U (en) | 2023-07-19 | 2023-07-19 | Unmanned aerial vehicle quick detach fuselage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220501049U (en) |
-
2023
- 2023-07-19 CN CN202321910467.0U patent/CN220501049U/en active Active
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