CN220298791U - Assembled unmanned aerial vehicle tail wing - Google Patents
Assembled unmanned aerial vehicle tail wing Download PDFInfo
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- CN220298791U CN220298791U CN202321317978.1U CN202321317978U CN220298791U CN 220298791 U CN220298791 U CN 220298791U CN 202321317978 U CN202321317978 U CN 202321317978U CN 220298791 U CN220298791 U CN 220298791U
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- 230000007246 mechanism Effects 0.000 claims abstract description 37
- 230000008878 coupling Effects 0.000 claims description 8
- 238000010168 coupling process Methods 0.000 claims description 8
- 238000005859 coupling reaction Methods 0.000 claims description 8
- 230000006378 damage Effects 0.000 abstract description 8
- 238000000034 method Methods 0.000 abstract description 4
- 230000008569 process Effects 0.000 abstract description 2
- 208000027418 Wounds and injury Diseases 0.000 description 2
- 230000009471 action Effects 0.000 description 2
- 208000014674 injury Diseases 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000012544 monitoring process Methods 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 230000004720 fertilization Effects 0.000 description 1
- 238000011065 in-situ storage Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000002262 irrigation Effects 0.000 description 1
- 238000003973 irrigation Methods 0.000 description 1
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- 239000004033 plastic Substances 0.000 description 1
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Abstract
The utility model discloses an assembled unmanned aerial vehicle tail wing, and relates to the technical field of unmanned aerial vehicle tail wings. The utility model comprises the following steps: the unmanned aerial vehicle comprises an unmanned aerial vehicle body, wherein a clamping sleeve is sleeved on the surface of the unmanned aerial vehicle body, and the unmanned aerial vehicle further comprises a limiting mechanism, wherein the limiting mechanism is used for limiting the position of the clamping sleeve on the surface of the unmanned aerial vehicle body; the protection frame, the protection frame set up in the battery top of unmanned aerial vehicle body. When the unmanned aerial vehicle battery protection device is used, a user clamps the clamping sleeve on the surface of the battery of the unmanned aerial vehicle body through the limiting mechanism, and installs the protection frame above the battery of the unmanned aerial vehicle body through the connecting mechanism, at the moment, when the condition that the battery lands occurs in the flying process, the protection frame can land firstly, the unmanned aerial vehicle battery is effectively protected, and by the arrangement, the damage to the unmanned aerial vehicle battery is effectively reduced through the small cost, the larger property loss is avoided, and the practicability of the device is fully embodied.
Description
Technical Field
The utility model relates to the technical field of unmanned aerial vehicle tail wings, in particular to an assembled unmanned aerial vehicle tail wing.
Background
Unmanned aerial vehicles are unmanned aerial vehicles, the flight paths of which are controlled by remote controllers or preset flight plans, are generally composed of various sensors, cameras and other electronic devices, and can be used in many different application fields including agriculture, logistics, search and rescue, scientific research and the like, can perform various tasks such as aerial photography, delivering articles, monitoring environments, surveying and mapping buildings and the like, can be used for crop monitoring and fertilization and irrigation of paddy fields, can be used for article express delivery and cargo transportation in the logistics field, can be used for searching for missing persons and providing rescue, and can be used for collecting data and conducting experiments in the scientific research field.
Unmanned aerial vehicle battery landing refers to unmanned aerial vehicle is in the flight in-process, because battery electric quantity is insufficient or other reasons can't continue the flight, need carry out emergency landing and with the condition that the battery landed, unmanned aerial vehicle's battery landing probably can lead to the battery to destroy burning to further cause the injury that is difficult to the prosthetic to unmanned aerial vehicle is inside, consequently, need a neotype assembled unmanned aerial vehicle tail wing reduce the damage that the battery received when unmanned aerial vehicle battery lands.
Disclosure of Invention
The utility model adopts the following technical scheme for realizing the purposes:
assembled unmanned aerial vehicle fin includes:
the unmanned aerial vehicle comprises an unmanned aerial vehicle body, wherein a clamping sleeve is sleeved on the surface of the unmanned aerial vehicle body, and the unmanned aerial vehicle further comprises a limiting mechanism, wherein the limiting mechanism is used for limiting the position of the clamping sleeve on the surface of the unmanned aerial vehicle body;
the protection frame, the protection frame set up in the battery top of unmanned aerial vehicle body still includes coupling mechanism, coupling mechanism is used for connecting the protection frame with the cutting ferrule.
Further, stop gear including fixed mounting in the first snap ring of unmanned aerial vehicle body's battery both sides, the equal fixed mounting in inner wall both sides of cutting ferrule has the second snap ring.
Further, the protection frame includes two fluorescence frames that the symmetry set up, a plurality of bracing piece, a plurality of the both ends of bracing piece respectively fixed mounting in two the fluorescence frame is close to one side each other, two the part of fluorescence frame is the rubber material.
Further, coupling mechanism including fixed mounting in the connecting plate at cutting ferrule top, T-shaped groove has been seted up to the surface of connecting plate, the inner wall slip grafting in T-shaped groove has the rubber slab, the both ends of rubber slab respectively fixed mounting in two one side of fluorescence frame, the inner wall slip in T-shaped groove runs through there is the T-shaped plate.
Further, one side of the two fluorescent frames is provided with the same buffer plate, and the fluorescent frame further comprises a rebound mechanism, wherein the rebound mechanism is used for connecting the buffer plate with the two fluorescent frames and applying force for keeping the buffer plate in situ.
Further, the rebound mechanism comprises two straight plates and a rotating rod which are fixedly installed on the surfaces of the fluorescent rack respectively, through grooves are formed in the surfaces of the two straight plates, rebound blocks are slidably inserted into the inner walls of the through grooves respectively, two ends of the rotating rod respectively rotate and penetrate through two sides of the buffer plate, the rebound blocks are fixedly sleeved on the surfaces of the rotating rod respectively, springs are fixedly installed on the surfaces of the rebound blocks respectively, and the other ends of the springs are fixedly installed on the other sides of the through grooves respectively.
The beneficial effects of the utility model are as follows:
1. when the unmanned aerial vehicle battery protection device is used, a user clamps the clamping sleeve on the surface of the battery of the unmanned aerial vehicle body through the limiting mechanism, and installs the protection frame above the battery of the unmanned aerial vehicle body through the connecting mechanism, at the moment, when the condition that the battery lands occurs in the flying process, the protection frame can land firstly, the unmanned aerial vehicle battery is effectively protected, and by the arrangement, the damage to the unmanned aerial vehicle battery is effectively reduced through the small cost, the larger property loss is avoided, and the practicability of the device is fully embodied.
Drawings
FIG. 1 is a schematic perspective view of the present utility model;
FIG. 2 is a schematic view of a partial perspective view of another aspect of the present utility model;
FIG. 3 is a half cross-sectional view of a portion of the structure of the present utility model;
fig. 4 is a schematic perspective view of another part of the present utility model.
Reference numerals: 1. an unmanned aerial vehicle body; 2. a cutting sleeve; 3. a limiting mechanism; 301. a first snap ring; 302. a second snap ring; 4. a protective frame; 401. a fluorescent rack; 402. a support rod; 5. a connecting mechanism; 501. a connecting plate; 502. a T-shaped groove; 503. a rubber plate; 6. a buffer plate; 7. a rebound mechanism; 701. a straight plate; 702. a rotating lever; 703. a rebound block; 704. and (3) a spring.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present utility model more clear, the technical solutions of the embodiments of the present utility model will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present utility model.
The application provides assembled unmanned aerial vehicle fin, mainly used solves unmanned aerial vehicle battery when the unmanned aerial vehicle battery lands and leads to battery damage burning to further cause the problem of the injury that is difficult to repair to unmanned aerial vehicle inside, and provides following technical scheme, will combine the detailed description of fig. 1-4 below:
assembled unmanned aerial vehicle fin includes: the unmanned aerial vehicle comprises an unmanned aerial vehicle body 1, wherein a cutting ferrule 2 is sleeved on the surface of the unmanned aerial vehicle body 1, the unmanned aerial vehicle further comprises a limiting mechanism 3, and the limiting mechanism 3 is used for limiting the position of the cutting ferrule 2 on the surface of the unmanned aerial vehicle body 1; the protection frame 4, the protection frame 4 set up in unmanned aerial vehicle body 1's battery top still includes coupling mechanism 5, coupling mechanism 5 is used for connecting protection frame 4 with cutting ferrule 2. In some embodiments, when using, the user passes through stop gear 3 with cutting ferrule 2 card behind the surface of unmanned aerial vehicle body 1's battery, install the protection frame 4 in the top of unmanned aerial vehicle body 1's battery through coupling mechanism 5, at this moment, when the circumstances that the battery lands appears in the flight, protection frame 4 can land first, the effectual unmanned aerial vehicle battery of having protected, so set up, through less cost, the effectual damage that reduces unmanned aerial vehicle battery and receives, great loss of property has been avoided, the abundant practicality of embodying the device.
As shown in fig. 2 and fig. 4, specifically, the limiting mechanism 3 includes a first clamping ring 301 fixedly installed on two sides of the battery of the unmanned aerial vehicle body 1, and two sides of an inner wall of the clamping sleeve 2 are fixedly installed with a second clamping ring 302, which needs to be described as follows: the user breaks the two sides of the cutting sleeve 2 made of plastic materials, and clamps the second clamping ring 302 on the surface of the first clamping ring 301, so that the cutting sleeve 2 can be installed.
As shown in fig. 2, specifically, the protection frame 4 includes two symmetrical fluorescent frames 401, a plurality of support rods 402, two ends of each support rod 402 are respectively and fixedly mounted on two sides of each fluorescent frame 401, and a part of each fluorescent frame 401 is made of rubber, which needs to be described as follows: the fluorescence frame 401 is used for the in-process that flies at unmanned aerial vehicle, to user sign unmanned aerial vehicle position, avoids unmanned aerial vehicle to lose, simultaneously, a plurality of bracing piece 402 and two fluorescence frames 401 have carried out effectual protection to unmanned aerial vehicle's battery.
As shown in fig. 3, specifically, the connection mechanism 5 includes a connection board 501 fixedly mounted on the top of the ferrule 2, a T-shaped slot 502 is provided on the surface of the connection board 501, a rubber plate 503 is slidingly inserted into the inner wall of the T-shaped slot 502, two ends of the rubber plate 503 are respectively fixedly mounted on two sides of the fluorescent rack 401, and the inner wall of the T-shaped slot 502 slidingly penetrates through the T-shaped board, which needs to be explained: the user inserts the rubber plate 503 through the opening part of the T-shaped groove 502, and then limits through the T-shaped plate, so that the installation of the protection frame 4 can be realized.
As shown in fig. 1, specifically, one side of two fluorescent frames 401 is provided with the same buffer plate 6, and further includes a rebound mechanism 7, where the rebound mechanism 7 is used to connect the buffer plate 6 and two fluorescent frames 401 and apply a force for keeping the buffer plate 6 in place, and it should be noted that: when the fluorescent frame 401 contacts the ground, since the rubber portion thereof is connected with the rubber plate 503, it is inclined so that the buffer plate 6 collides with the relatively hard housing portion of the unmanned aerial vehicle, thereby discharging the impact force under the action of the rebound mechanism 7.
As shown in fig. 3, specifically, the rebound mechanism 7 includes two straight plates 701 and a rotating rod 702 respectively fixedly mounted on the surfaces of the fluorescent frames 401, the surfaces of the two straight plates 701 are respectively provided with a through groove, the inner walls of the two through grooves are respectively slidably inserted with rebound blocks 703, two ends of the rotating rod 702 respectively rotate and penetrate through two sides of the buffer plate 6, the two rebound blocks 703 are respectively fixedly sleeved on the surfaces of the rotating rod 702, springs 704 are fixedly mounted on the surfaces of the two rebound blocks 703, and the other ends of the two springs 704 are respectively fixedly mounted on the other sides of the two through grooves, which should be explained is that: when the buffer plate 6 collides with the unmanned aerial vehicle shell, the rebound block 703 can compress the spring 704, so that the impact force is buffered under the action of the rebound force of the spring 704, namely, the unmanned aerial vehicle shell is effectively protected, the damage to the surface of the unmanned aerial vehicle shell is avoided, and the practicability is fully embodied.
Claims (6)
1. Assembled unmanned aerial vehicle fin, including, its characterized in that includes:
the unmanned aerial vehicle comprises an unmanned aerial vehicle body (1), wherein a cutting ferrule (2) is sleeved on the surface of the unmanned aerial vehicle body (1), the unmanned aerial vehicle further comprises a limiting mechanism (3), and the limiting mechanism (3) is used for limiting the position of the cutting ferrule (2) on the surface of the unmanned aerial vehicle body (1);
the protection frame (4), protection frame (4) set up in unmanned aerial vehicle body (1) battery top still includes coupling mechanism (5), coupling mechanism (5) are used for connecting protection frame (4) with cutting ferrule (2).
2. The assembled unmanned aerial vehicle fin according to claim 1, wherein the limiting mechanism (3) comprises a first clamping ring (301) fixedly mounted on two sides of a battery of the unmanned aerial vehicle body (1), and second clamping rings (302) are fixedly mounted on two sides of an inner wall of the clamping sleeve (2).
3. The assembled unmanned aerial vehicle fin according to claim 1, wherein the protection frame (4) comprises two fluorescent frames (401) which are symmetrically arranged, a plurality of support rods (402), two ends of the plurality of support rods (402) are respectively and fixedly arranged on one sides of the two fluorescent frames (401) which are close to each other, and part of the two fluorescent frames (401) is made of rubber.
4. The assembled unmanned aerial vehicle fin according to claim 3, wherein the connecting mechanism (5) comprises a connecting plate (501) fixedly installed at the top of the clamping sleeve (2), a T-shaped groove (502) is formed in the surface of the connecting plate (501), a rubber plate (503) is slidably inserted into the inner wall of the T-shaped groove (502), two ends of the rubber plate (503) are fixedly installed on one side of the two fluorescent frames (401) respectively, and a T-shaped plate (504) is slidably penetrated into the inner wall of the T-shaped groove (502).
5. An assembled unmanned aerial vehicle tail according to claim 3, wherein two of the fluorescent brackets (401)
The fluorescent lamp is characterized in that the fluorescent lamp is provided with the same buffer plate (6), and further comprises a rebound mechanism (7), wherein the rebound mechanism (7) is used for connecting the buffer plate (6) and the two fluorescent racks (401) and applying a force for keeping the buffer plate (6) in place.
6. The tail fin of the assembled unmanned aerial vehicle according to claim 5, wherein the rebound mechanism (7) comprises two straight plates (701) and a rotating rod (702) which are respectively fixedly arranged on the surfaces of the two fluorescent frames (401),
the two surfaces of straight board (701) all have seted up logical groove, two the inner wall that leads to the groove all slides and peg graft has rebound piece (703), the both ends of dwang (702) rotate respectively run through in the both sides of buffer board (6), two rebound piece (703) all fixed cup joint in the surface of dwang (702), two the equal fixed mounting in surface of rebound piece (703) has spring (704), two the other end of spring (704) is fixed mounting respectively in two the opposite side that leads to the groove.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321317978.1U CN220298791U (en) | 2023-05-29 | 2023-05-29 | Assembled unmanned aerial vehicle tail wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321317978.1U CN220298791U (en) | 2023-05-29 | 2023-05-29 | Assembled unmanned aerial vehicle tail wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220298791U true CN220298791U (en) | 2024-01-05 |
Family
ID=89353061
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202321317978.1U Active CN220298791U (en) | 2023-05-29 | 2023-05-29 | Assembled unmanned aerial vehicle tail wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220298791U (en) |
-
2023
- 2023-05-29 CN CN202321317978.1U patent/CN220298791U/en active Active
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