CN220884854U - Unmanned aerial vehicle wing structure of scalable folding - Google Patents
Unmanned aerial vehicle wing structure of scalable folding Download PDFInfo
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- CN220884854U CN220884854U CN202322844474.1U CN202322844474U CN220884854U CN 220884854 U CN220884854 U CN 220884854U CN 202322844474 U CN202322844474 U CN 202322844474U CN 220884854 U CN220884854 U CN 220884854U
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Abstract
The utility model discloses a telescopic folding unmanned aerial vehicle wing structure, which relates to the technical field of unmanned aerial vehicle wings and comprises a first wing and a second wing, wherein a first connecting piece is fixedly connected to the left side of the inside of the first wing, the inside of the second wing is divided into a telescopic cavity and a sliding cavity by a partition plate, a third wing is slidably connected to the inside of the telescopic cavity, a sliding plate is slidably connected to the inside of the sliding cavity, a compression spring is arranged in the sliding cavity, the left side of the compression spring is fixedly connected with the inner wall of the sliding cavity, the right side of the compression spring is fixedly connected with the right wall of the sliding plate, a second connecting piece is fixedly connected with the right side of the sliding plate, the second connecting piece is rotationally connected with the first connecting piece through a rotating shaft, a plurality of limiting blocks are fixedly connected to the inside of the left side of the second wing, a plurality of sliding grooves are formed in the outer surface of the third wing, and can adapt to operation flight sites of different sizes and shapes, so that the storage space can be stored and carried more easily, the utilization efficiency of the storage space is improved, and the cost and the complexity of transportation are reduced.
Description
Technical Field
The utility model relates to the technical field of unmanned aerial vehicle wings, in particular to a telescopic folding unmanned aerial vehicle wing structure.
Background
The unmanned plane is called as unmanned plane for short, and is a unmanned plane operated by radio remote control equipment and a self-contained program control device. The unmanned aerial vehicle can be applied to the fields of reconnaissance, aerial photography, agriculture, plant protection, miniature self-timer, express delivery transportation, disaster relief, wild animal observation, infectious disease monitoring, mapping, news reporting, electric power inspection, disaster relief, video shooting, romantic manufacturing and the like, and has very wide requirements, and along with the rapid development and application of unmanned aerial vehicle technology, miniaturization and portability of the unmanned aerial vehicle become important development trends.
The existing unmanned aerial vehicle wing is usually fixed in length, so that the operation capability of the unmanned aerial vehicle in a narrow or limited space is limited, meanwhile, the oversized wing means that a larger storage space is needed for storing the unmanned aerial vehicle, the unmanned aerial vehicle needs a larger carrier or special transportation equipment for carrying, the transportation cost and the complexity can be increased, and the problem is solved by providing a telescopic folding unmanned aerial vehicle wing structure.
Disclosure of utility model
In order to solve the above technical problems, a scalable folding unmanned aerial vehicle wing structure is provided, which solves the problems that the length of the existing unmanned aerial vehicle wing is usually fixed, so that the operation capability of the unmanned aerial vehicle in a narrow or limited space is limited, and meanwhile, an oversized wing means that a larger storage space is needed to store the unmanned aerial vehicle, and the unmanned aerial vehicle needs a larger carrier or special transportation equipment to carry, which may increase the transportation cost and complexity.
In order to achieve the above purpose, the utility model adopts the following technical scheme: the utility model provides a scalable folding unmanned aerial vehicle wing structure, includes first wing and second wing, the inside left side fixedly connected with first connecting piece of first wing, the inside flexible chamber and the sliding chamber of separating by the baffle of second wing, flexible intracavity portion sliding connection has the third wing, the inside sliding connection of sliding chamber has the slide, the inside compression spring that is provided with of sliding chamber, compression spring left side and sliding intracavity wall fixed connection, compression spring right side and slide right wall fixed connection, slide right side fixedly connected with second connecting piece, the second connecting piece rotates with first connecting piece through the pivot to be connected, a plurality of stopper of inside fixedly connected with in second wing left side, a plurality of sliding grooves have been seted up to the third wing surface, stopper sliding connection is inside the sliding groove.
Preferably, the right side of the outer surface of the second wing is sleeved with a fastening sleeve, the left side of the fastening sleeve is fixedly connected with a limiting ring, a rotating groove is formed in the position, corresponding to the limiting ring, of the surface of the second wing, and the limiting ring is slidably connected inside the rotating groove.
Preferably, the left side surface of the first wing is provided with external threads, and the right side of the first wing surface and the external threads are fixedly connected with a limit baffle.
Preferably, the left side fixedly connected with mount pad of third wing, mount pad upper end fixedly connected with motor, the output fixedly connected with of motor has a plurality of rotors.
Preferably, a threaded hole is formed in the bottom of the left side of the second wing, and a fastening screw is connected to the threaded hole in a threaded mode.
Preferably, the right side of the bottom of the third wing is provided with a first limiting hole, and the left side of the bottom of the third wing is provided with a second limiting hole.
Preferably, the fastening sleeve is internally provided with an internal thread which is matched with the external thread.
Compared with the prior art, the utility model has the advantages that: according to the utility model, the first wing and the second wing are folded through the cooperation between the first connecting piece and the second connecting piece, the first wing and the second wing are fixed through the mutual cooperation of the fastening sleeve and the external threads on the first wing, the third wing is connected in the telescopic cavity in the second wing in a sliding mode, the limit of the third wing is realized through the cooperation between the limit block and the sliding groove, the second wing and the third wing are fixed through the cooperation between the fastening screw and the first limit hole and the second limit hole, the operation flight sites with different sizes and shapes can be adapted by adopting the arrangement, the operation capacity in the space is improved, when the wings are folded or folded, the size of the unmanned aerial vehicle is reduced, the unmanned aerial vehicle can be stored and carried more easily, the utilization efficiency of the storage space is improved, and the cost and complexity of transportation are reduced.
Drawings
FIG. 1 is a schematic perspective view of the present utility model;
FIG. 2 is an exploded view of the present utility model;
FIG. 3 is a schematic view of the internal structure of a second airfoil according to the utility model;
fig. 4 is an enlarged partial schematic view at a in fig. 3.
The reference numerals in the figures are:
1. A first wing; 2. a second wing; 201. a telescopic chamber; 202. a limiting block; 203. a threaded hole; 204. a sliding chamber; 205. a compression spring; 206. a slide plate; 207. a fastening sleeve; 208. a limiting ring; 209. a rotating groove; 3. a third wing; 301. a first limiting hole; 302. a second limiting hole; 303. a sliding groove; 4. a mounting base; 5. a motor; 6. a rotor; 7. an external thread; 8. a limit baffle; 9. a first connector; 10. a second connector; 11. and (5) fastening a screw.
Detailed Description
The following description is presented to enable one of ordinary skill in the art to make and use the utility model. The preferred embodiments in the following description are by way of example only and other obvious variations will occur to those skilled in the art.
Referring to fig. 1-4, a scalable folding unmanned aerial vehicle wing structure, including first wing 1 and second wing 2, first connecting piece 9 of inside left side fixedly connected with of first wing 1, the inside flexible chamber 201 and the sliding chamber 204 of separating into by the baffle of second wing 2, flexible chamber 201 inside sliding connection has third wing 3, sliding chamber 204 inside sliding connection has slide 206, sliding chamber 204 inside is provided with compression spring 205, compression spring 205 left side and sliding chamber 204 inner wall fixed connection, compression spring 205 right side and slide 206 right wall fixed connection, slide 206 right side fixed connection has second connecting piece 10, second connecting piece 10 rotates with first connecting piece 9 through the pivot and is connected, a plurality of stopper 202 of inside fixedly connected with in the left side of second wing 2, a plurality of sliding grooves 303 have been seted up to the 3 surface of third wing, stopper 202 sliding connection is inside sliding groove 303.
Further, a fastening sleeve 207 is sleeved on the right side of the outer surface of the second wing 2, a limiting ring 208 is fixedly connected to the left side of the fastening sleeve 207, a rotating groove 209 is formed in the position, corresponding to the limiting ring 208, of the surface of the second wing 2, the limiting ring 208 is slidably connected to the inside of the rotating groove 209, the fastening sleeve 207 is used for fixing the first wing 1 and the second wing 2 together, and the first wing 1 and the second wing 2 achieve the folding function of the wing structure.
Specifically, the external screw thread 7 has been seted up on the surface of first wing 1 left side, and first wing 1 surface and external screw thread 7 right side fixedly connected with limit baffle 8, limit baffle 8 are used for preventing fastening sleeve 207's rotation volume too much, lead to appearing the problem of smooth silk.
The left side fixedly connected with mount pad 4 of third wing 3, mount pad 4 upper end fixed mounting has motor 5, and the output fixedly connected with of motor 5 has a plurality of rotor 6.
Further, a threaded hole 203 is formed in the bottom of the left side of the second wing 2, a fastening screw 11 is connected to the threaded hole 203 in a threaded manner, the fastening screw 11 is used for fixing the third wing 3 and the second wing 2 together, and the third wing 3 and the second wing 2 achieve the telescopic function of the wing mechanism.
Optionally, a first limiting hole 301 is formed on the right side of the bottom of the third wing 3, a second limiting hole 302 is formed on the left side of the bottom of the third wing 3, and the number of the limiting holes is not limited, but at least two limiting holes are distributed at two ends of the third wing 3, so that the maximum expansion amount and the minimum expansion amount of expansion are controlled.
Specifically, the fastening sleeve 207 is internally provided with an internal thread adapted to the external thread 7.
Working principle: when the wing device is used, the first wing 1 is welded on the unmanned aerial vehicle body in a welding mode, the second wing 2 is rotated to be horizontal to the first wing 1 through the first connecting piece 9 and the second connecting piece 10, then the second wing 2 is pushed into the first wing 1, the rotation fastening sleeve 207 is matched with the external threads 7 through the fastening sleeve 207, the first wing 1 and the second wing 2 are fixed together, the third wing 3 is pulled out of the telescopic cavity 201, the first limiting hole 301 corresponds to the threaded hole 203, the fastening screw 11 is screwed to fix the third wing 3 and the second wing 2 together, the wing device is unfolded, and when the wing device is stored, the wing device is reversely operated, and the second limiting hole 302 is matched with the threaded hole 203 when the wing device is stored.
The foregoing has shown and described the basic principles, principal features and advantages of the utility model. It will be understood by those skilled in the art that the present utility model is not limited to the embodiments described above, and that the above embodiments and descriptions are merely illustrative of the principles of the present utility model, and various changes and modifications may be made therein without departing from the spirit and scope of the utility model, which is defined by the appended claims. The scope of the utility model is defined by the appended claims and equivalents thereof.
Claims (7)
1. Scalable folding unmanned aerial vehicle wing structure, including first wing (1) and second wing (2), its characterized in that: the novel wing structure is characterized in that a first connecting piece (9) is fixedly connected to the left side of the inside of the first wing (1), a telescopic cavity (201) and a sliding cavity (204) are formed in the second wing (2) in a separated mode through a partition plate, a third wing (3) is connected to the telescopic cavity (201) in a sliding mode, a sliding plate (206) is connected to the inside of the sliding cavity (204) in a sliding mode, a compression spring (205) is arranged in the sliding cavity (204), the left side of the compression spring (205) is fixedly connected with the inner wall of the sliding cavity (204), the right side of the compression spring (205) is fixedly connected with the right wall of the sliding plate (206), a second connecting piece (10) is fixedly connected to the right side of the sliding plate (206) in a rotating mode through a rotating shaft, a plurality of limiting blocks (202) are fixedly connected to the left side of the second wing (2), a plurality of sliding grooves (303) are formed in the outer surface of the third wing (3), and the limiting blocks (202) are slidingly connected to the inside of the sliding grooves (303).
2. A telescopic folding unmanned aerial vehicle wing structure according to claim 1, wherein: the right side of the outer surface of the second wing (2) is sleeved with a fastening sleeve (207), the left side of the fastening sleeve (207) is fixedly connected with a limiting ring (208), a rotating groove (209) is formed in the position, corresponding to the limiting ring (208), of the surface of the second wing (2), and the limiting ring (208) is slidably connected inside the rotating groove (209).
3. A telescopic folding unmanned aerial vehicle wing structure according to claim 1, wherein: external threads (7) are formed on the left side surface of the first wing (1), and a limit baffle (8) is fixedly connected to the right side of the external threads (7) on the surface of the first wing (1).
4. A telescopic folding unmanned aerial vehicle wing structure according to claim 1, wherein: the left side fixedly connected with mount pad (4) of third wing (3), mount pad (4) upper end fixedly connected with motor (5), the output fixedly connected with of motor (5) has a plurality of rotor (6).
5. A telescopic folding unmanned aerial vehicle wing structure according to claim 1, wherein: screw holes (203) are formed in the left bottom of the second wing (2), and fastening screws (11) are connected with the screw holes (203) in a threaded mode.
6. A telescopic folding unmanned aerial vehicle wing structure according to claim 1, wherein: the right side of the bottom of the third wing (3) is provided with a first limiting hole (301), and the left side of the bottom of the third wing (3) is provided with a second limiting hole (302).
7. A telescopic folding unmanned aerial vehicle wing structure according to claim 2, wherein: an internal thread matched with the external thread (7) is arranged inside the fastening sleeve (207).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322844474.1U CN220884854U (en) | 2023-10-23 | 2023-10-23 | Unmanned aerial vehicle wing structure of scalable folding |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322844474.1U CN220884854U (en) | 2023-10-23 | 2023-10-23 | Unmanned aerial vehicle wing structure of scalable folding |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220884854U true CN220884854U (en) | 2024-05-03 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202322844474.1U Active CN220884854U (en) | 2023-10-23 | 2023-10-23 | Unmanned aerial vehicle wing structure of scalable folding |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220884854U (en) |
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2023
- 2023-10-23 CN CN202322844474.1U patent/CN220884854U/en active Active
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