CN221024231U - Unmanned aerial vehicle wing protective structure - Google Patents
Unmanned aerial vehicle wing protective structure Download PDFInfo
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- CN221024231U CN221024231U CN202322727892.2U CN202322727892U CN221024231U CN 221024231 U CN221024231 U CN 221024231U CN 202322727892 U CN202322727892 U CN 202322727892U CN 221024231 U CN221024231 U CN 221024231U
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- 230000001681 protective effect Effects 0.000 title claims description 10
- 230000004224 protection Effects 0.000 claims abstract description 107
- 230000007246 mechanism Effects 0.000 claims abstract description 47
- 230000035939 shock Effects 0.000 claims abstract description 19
- 239000008187 granular material Substances 0.000 claims description 4
- 238000010521 absorption reaction Methods 0.000 claims description 2
- 238000013016 damping Methods 0.000 abstract description 5
- 230000003139 buffering effect Effects 0.000 abstract description 3
- 238000009434 installation Methods 0.000 abstract description 2
- 238000007711 solidification Methods 0.000 abstract description 2
- 230000008023 solidification Effects 0.000 abstract description 2
- 230000008878 coupling Effects 0.000 description 10
- 238000010168 coupling process Methods 0.000 description 10
- 238000005859 coupling reaction Methods 0.000 description 10
- 239000002245 particle Substances 0.000 description 4
- 208000035473 Communicable disease Diseases 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 208000015181 infectious disease Diseases 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000009979 protective mechanism Effects 0.000 description 1
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- Vibration Dampers (AREA)
Abstract
The utility model discloses an unmanned aerial vehicle wing protection structure which comprises a main body mechanism, protection mechanisms and damping buffer mechanisms, wherein the protection mechanisms are arranged at four corners of the main body mechanism, and the damping buffer mechanisms are arranged outside the protection mechanisms. This main part mechanism can be convenient for the user fold the wing of this unmanned aerial vehicle and accomodate, can be connected the cooperation with main part mechanism through protection machanism, can carry out physical protection to this unmanned aerial vehicle wing periphery, adopt combined type package assembly simultaneously, convenient to use person carries out the dismouting, avoid traditional structure solidification to occupy the problem of position, satisfy the needs of nimble adjustment in the user's installation use, adaptable more not high wing uses, can cooperate with protection machanism through shock attenuation buffer mechanism, ensure this unmanned aerial vehicle in the use, when protection machanism receives the collision, can reduce the rigidity damage, promote flexible buffering, reduce the shock conduction of collision.
Description
Technical Field
The utility model relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle wing protection structure.
Background
Unmanned aerial vehicle is simply called "unmanned aerial vehicle", is unmanned aerial vehicle that utilizes radio remote control equipment and self-contained program control device to operate, unmanned aerial vehicle can divide into for military use and civilian according to application, at present unmanned aerial vehicle is in taking photo by plane, agriculture, plant protection, miniature self-timer shooting, express delivery transportation, disaster relief, observe wild animal, monitor infectious disease, survey and drawing, news report, electric power inspection, rescue, film and television shooting and manufacturing romantic etc. the application of field, great expansion unmanned aerial vehicle's application, in recent years, unmanned aerial vehicle receives the additional and more people's the back-up with its simple structure, convenient control and higher security characteristics.
In use, patent number CN217260680U discloses a wing protection structure for unmanned aerial vehicle, which belongs to the unmanned aerial vehicle field and can protect the unmanned aerial vehicle wing, so that the unmanned aerial vehicle wing is not easy to be damaged by other objects and is not easy to hurt human body, but the protection structure is inconvenient to carry, meanwhile, the wing is too dense to protect, the circulation of air flow is influenced, and the unmanned aerial vehicle is influenced to a certain extent.
Disclosure of utility model
The utility model aims to provide an unmanned aerial vehicle wing protection structure so as to solve the problems in the background art.
In order to achieve the above purpose, the present utility model provides the following technical solutions: the utility model provides an unmanned aerial vehicle wing protective structure, includes main part mechanism, protection machanism and shock attenuation buffer machanism, main part mechanism four corners is provided with protection machanism, and protection machanism's outside is provided with shock attenuation buffer machanism, protection machanism includes first protection frame, connects the chassis, connects buckle, connecting rod, screwed connection pole and second protection frame, and the first protection frame inboard is connected with the connection chassis, the one end of connecting the chassis is connected with the connection buckle, and connects the top of chassis and be provided with the connecting rod, the both ends of connecting rod are provided with the screwed connection pole, and the top of screwed connection pole is provided with the second protection frame.
Further, three groups of screw holes which are symmetrically distributed are formed in the top end of the first protection frame, and the first protection frame is integrally connected with the connecting underframe.
Further, the connecting rod is movably clamped and connected with the threaded connecting rod, and the threaded connecting rod is in threaded connection with the first protection frame and the second protection frame.
Further, the second protection frame and the first protection frame are horizontally and symmetrically distributed, and the protection mechanisms are provided with four groups which are symmetrically distributed.
Further, the main body mechanism comprises a main body, connecting components, connecting arms and blades, the connecting components are arranged on two sides of the main body, the connecting components are internally connected with the connecting arms, and one ends of the connecting arms are connected with the blades.
Further, the connecting arm is movably connected with the connecting component, and the connecting arm can rotate ninety degrees with the connecting component.
Further, shock attenuation buffer gear includes protection gum cover, draw-in groove, anti-skidding granule and elasticity buckle, and the inboard of protection gum cover is provided with the draw-in groove, the inner wall of draw-in groove is provided with anti-skidding granule, and the both ends of protection gum cover are provided with elasticity buckle.
Further, four groups of symmetrically distributed protection rubber sleeves are arranged in total, and the outer sides of the protection rubber sleeves are distributed in a wave mode.
Compared with the prior art, the utility model has the beneficial effects that: this unmanned aerial vehicle wing protective structure is provided with main part mechanism, protection machanism and shock attenuation buffer gear, and this main part mechanism can convenient to use person fold the wing of this unmanned aerial vehicle and accomodate, has strengthened operational flexibility simultaneously.
This protection machanism can be connected the cooperation with main part mechanism, can carry out physical protection to this unmanned aerial vehicle wing periphery, adopts combined type package assembly simultaneously, and convenient to use person carries out the dismouting, promotes the convenience that the user carried when having reduced the volume, avoids traditional structure solidification to occupy the problem of position, satisfies the needs of nimble adjustment in the user's installation use, and adaptable more not high wings use.
This shock attenuation buffer gear can cooperate with protection machanism to be connected, ensures that this unmanned aerial vehicle is in the use, when protection machanism received the collision, can reduce the rigidity and damage, promotes flexible buffering, reduces the shock transmission of collision, effectively strengthens unmanned aerial vehicle's stability of using.
Drawings
FIG. 1 is a schematic top view of the present utility model;
FIG. 2 is a schematic perspective view of a shock absorbing and buffering mechanism according to the present utility model;
fig. 3 is a schematic diagram of a three-dimensional splitting structure of the protection mechanism of the present utility model.
In the figure: 1. a main body mechanism; 101. a main body; 102. a connection assembly; 103. a connecting arm; 104. a blade; 2. a protective mechanism; 201. a first protection frame; 202. a connecting chassis; 203. a connecting buckle; 204. a connecting rod; 205. a threaded connecting rod; 206. a second protective frame; 3. a damping buffer mechanism; 301. protecting the rubber sleeve; 302. a clamping groove; 303. anti-slip particles; 304. and an elastic buckle.
Detailed Description
Example 1
Referring to fig. 1-2, the present utility model provides a technical solution: the utility model provides an unmanned aerial vehicle wing protective structure, including main part mechanism 1, protection machanism 2 and shock attenuation buffer mechanism 3, main part mechanism 1 four corners is provided with protection machanism 2, and protection machanism 2's outside is provided with shock attenuation buffer mechanism 3, main part mechanism 1 includes host computer body 101, coupling assembling 102, coupling arm 103 and blade 104, and the both sides of host computer body 101 are provided with coupling assembling 102, coupling assembling 102's internal connection has coupling arm 103, and coupling arm 103's one end is connected with blade 104, be swing joint between coupling arm 103 and the coupling assembling 102, and carry out ninety degrees rotations between coupling arm 103 and the coupling assembling 102, this main part mechanism 1 can be convenient to use person fold to take in this unmanned aerial vehicle's wing, and simultaneously, shock attenuation buffer mechanism 3 includes protection gum cover 301, draw-in groove 302, anti-slip particle 303 and elasticity buckle 304, and protection gum cover 301's inboard is provided with draw-in groove 302, the inner wall of draw-in groove 302 is provided with anti-slip particle 303, and protection gum cover 301's both ends are provided with elasticity buckle 304, protection gum cover 301 is provided with four sets of symmetric distribution, and protection gum cover 301 is provided with four sets, and protection gum cover's outside is the vibration of this vibration absorbing mechanism 3, and vibration damping mechanism is effectively used in the protection mechanism 2 when the collision has reduced, can reduce the shock attenuation stability, and the collision is effectively can be reduced, and the shock absorption mechanism is broken by the collision mechanism is effectively by the collision mechanism 2 when using the human-free, and has reduced.
Example 2
Referring to fig. 3, the present utility model provides a technical solution: the utility model provides an unmanned aerial vehicle wing protective structure, including main part mechanism 1, protection machanism 2 and shock attenuation buffer machanism 3, main part mechanism 1 four corners is provided with protection machanism 2, and protection machanism 2's outside is provided with shock attenuation buffer machanism 3, protection machanism 2 includes first protection frame 201, connect chassis 202, connect buckle 203, connecting rod 204, threaded connection pole 205 and second protection frame 206, and first protection frame 201 inboard is connected with and connects chassis 202, the one end of connecting chassis 202 is connected with connect buckle 203, and the top of connecting chassis 202 is provided with connecting rod 204, connecting rod 204's both ends are provided with threaded connection pole 205, and threaded connection pole 205's top is provided with second protection frame 206, the top of first protection frame 201 is provided with the three screw of symmetric distribution, and be connected as an organic whole between connecting rod 204 and the threaded connection pole 205, and threaded connection is carried out with first protection frame 201, second protection frame 206 and first protection frame 201 are horizontal symmetric distribution, protection machanism 2 is provided with four groups of symmetric distribution, this protection machanism 2 carries out the cooperation with this protection frame 1 and carries out the flexible carrier's of the cooperation, the high user's of the demand of the user can be reduced, the adjustment of the side is realized, the high user's side is realized, the demand of the aircraft wing is realized, the side is realized, the user is more is easy to be realized, and the user is easy to be mounted, and is convenient to use, and is easy to use is easy to be equipped with the structure, and is easy to use.
Working principle: for the unmanned aerial vehicle wing protection structure, the connecting arms 103 on two sides of the main body 101 of the main body mechanism 1 are firstly unfolded, then the first protection frame 201 of the protection mechanism 2 is clamped and fixed with the connecting arms 103 through the connecting underframe 202, then the connecting buckles 203 are clamped and fixed with the middle parts of the connecting arms 103, then the connecting rods 204 are connected with the surface screw holes of the first protection frame 201 through the threaded connecting rods 205, the other ends of the threaded connecting rods 205 are connected with the second protection frame 206 through the threads, the telescopic adjustment is carried out between the threaded connecting rods 205 and the connecting rods 204, the height between the first protection frame 201 and the second protection frame 206 can be adjusted, the blades 104 with more height sizes can be adapted, then the protection rubber sleeves 301 of the damping buffer mechanism 3 are clamped with the outer sides of the first protection frame 201 and the second protection frame 206 through the clamping grooves 302, the surfaces of the first protection frame 201 and the second protection frame 206 are only attached through the anti-skidding particles 303, the two ends of the first protection frame 201 and the second protection frame 206 are clamped through the elastic buckles 304, the unmanned aerial vehicle wing protection structure can be prevented from falling off, and the damage of the unmanned aerial vehicle wing protection structure can be reduced in use.
Claims (8)
1. The utility model provides an unmanned aerial vehicle wing protective structure, includes main part mechanism (1), protection machanism (2) and shock attenuation buffer gear (3), its characterized in that: the novel anti-vibration protection device is characterized in that protection mechanisms (2) are arranged at four corners of the main body mechanism (1), shock absorption buffer mechanisms (3) are arranged outside the protection mechanisms (2), the protection mechanisms (2) comprise a first protection frame (201), a connecting bottom frame (202), a connecting buckle (203), a connecting rod (204), a threaded connecting rod (205) and a second protection frame (206), the connecting bottom frame (202) is connected to the inner side of the first protection frame (201), the connecting buckle (203) is connected to one end of the connecting bottom frame (202), a connecting rod (204) is arranged at the top end of the connecting bottom frame (202), threaded connecting rods (205) are arranged at two ends of the connecting rod (204), and the second protection frame (206) is arranged at the top end of the threaded connecting rod (205).
2. The unmanned aerial vehicle wing protection structure of claim 1, wherein: three groups of screw holes which are symmetrically distributed are formed in the top end of the first protection frame (201), and the first protection frame (201) is integrally connected with the connecting underframe (202).
3. The unmanned aerial vehicle wing protection structure of claim 1, wherein: the connecting rod (204) is movably clamped and connected with the threaded connecting rod (205), and the threaded connecting rod (205) is in threaded connection with the first protection frame (201) and the second protection frame (206).
4. The unmanned aerial vehicle wing protection structure of claim 1, wherein: the second protection frames (206) and the first protection frames (201) are horizontally and symmetrically distributed, and the protection mechanisms (2) are provided with four groups which are symmetrically distributed.
5. The unmanned aerial vehicle wing protection structure of claim 1, wherein: the main body mechanism (1) comprises a main body (101), connecting components (102), connecting arms (103) and blades (104), wherein the connecting components (102) are arranged on two sides of the main body (101), the connecting arms (103) are connected to the inside of the connecting components (102), and one ends of the connecting arms (103) are connected with the blades (104).
6. The unmanned aerial vehicle wing protection structure of claim 5, wherein: the connecting arm (103) is movably connected with the connecting component (102), and ninety degrees of rotation can be carried out between the connecting arm (103) and the connecting component (102).
7. The unmanned aerial vehicle wing protection structure of claim 1, wherein: the shock attenuation buffer gear (3) is including protection gum cover (301), draw-in groove (302), anti-skidding granule (303) and elasticity buckle (304), and the inboard of protection gum cover (301) is provided with draw-in groove (302), the inner wall of draw-in groove (302) is provided with anti-skidding granule (303), and the both ends of protection gum cover (301) are provided with elasticity buckle (304).
8. The unmanned aerial vehicle wing protection structure of claim 7, wherein: the protective rubber sleeves (301) are provided with four groups which are symmetrically distributed, and the outer sides of the protective rubber sleeves (301) are distributed in a wave mode.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322727892.2U CN221024231U (en) | 2023-10-11 | 2023-10-11 | Unmanned aerial vehicle wing protective structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322727892.2U CN221024231U (en) | 2023-10-11 | 2023-10-11 | Unmanned aerial vehicle wing protective structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN221024231U true CN221024231U (en) | 2024-05-28 |
Family
ID=91131210
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202322727892.2U Active CN221024231U (en) | 2023-10-11 | 2023-10-11 | Unmanned aerial vehicle wing protective structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN221024231U (en) |
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2023
- 2023-10-11 CN CN202322727892.2U patent/CN221024231U/en active Active
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