CN220054174U - Unmanned aerial vehicle wing patrols and flies by carbon fiber composite material constitutes - Google Patents
Unmanned aerial vehicle wing patrols and flies by carbon fiber composite material constitutes Download PDFInfo
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- CN220054174U CN220054174U CN202321536037.7U CN202321536037U CN220054174U CN 220054174 U CN220054174 U CN 220054174U CN 202321536037 U CN202321536037 U CN 202321536037U CN 220054174 U CN220054174 U CN 220054174U
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- 239000002131 composite material Substances 0.000 title claims abstract description 19
- 229920000049 Carbon (fiber) Polymers 0.000 title claims abstract description 12
- 239000004917 carbon fiber Substances 0.000 title claims abstract description 12
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 title claims abstract description 12
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims 7
- 229910052799 carbon Inorganic materials 0.000 claims 7
- 239000000835 fiber Substances 0.000 claims 7
- 238000013461 design Methods 0.000 abstract description 5
- 238000012545 processing Methods 0.000 abstract description 2
- 238000005516 engineering process Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 238000011161 development Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 208000035473 Communicable disease Diseases 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 208000015181 infectious disease Diseases 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 239000011229 interlayer Substances 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000013507 mapping Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
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Abstract
The utility model discloses a patrol unmanned aerial vehicle wing formed by carbon fiber composite materials, which relates to the technical field of unmanned aerial vehicles and comprises a framework, a cover body and a front wing plate; the framework comprises a plurality of frame plates and tail wing plates which are integrally connected; the cover body is detachably assembled on the surface of the framework; the front wing plate is detachably assembled at the front end of the framework, and is used for positioning the position of the cover body on the framework; the technical key points are as follows: through design detachable skeleton, the cover body and preceding pterygoid lamina structure, regard each frame plate as the skeleton, very big alleviateed the weight of whole wing, the cover body can split, change simultaneously, can realize the location processing to whole wing after accomplishing the pterygoid lamina equipment before with, on the basis that need not with the help of the screw or only need with the help of a small amount of screws, can avoid the circumstances that the wing takes place to separate in the use, embodied the flexibility of global design.
Description
Technical Field
The utility model relates to the technical field of unmanned aerial vehicles, in particular to a patrol unmanned aerial vehicle wing formed by carbon fiber composite materials.
Background
The unmanned plane is called as an unmanned plane for short, is a unmanned plane which is controlled by using a radio remote control device and a self-contained program control device, or is fully or intermittently operated autonomously by a vehicle-mounted computer; unmanned aircraft tend to be more suitable for tasks that are too "fooled, messy, or dangerous" than manned aircraft; unmanned aerial vehicles can be classified into military and civil according to application fields; in the military aspect, unmanned aerial vehicles are divided into a reconnaissance plane and a target plane; in civil aspect, the unmanned aerial vehicle and the industrial application are really just needed by the unmanned aerial vehicle; the unmanned aerial vehicle is applied to the fields of aerial photography, agriculture, plant protection, miniature self-timer shooting, express delivery transportation, disaster relief, wild animal observation, infectious disease monitoring, mapping, news reporting, power inspection, disaster relief, film and television shooting, romantic manufacturing and the like, the application of the unmanned aerial vehicle is greatly expanded, and the developed countries are also actively expanding the application of industries and developing unmanned aerial vehicle technologies.
The patent numbers in the prior patent documents are as follows: CN 212709933U, named as a multi-wall type wing of unmanned aerial vehicle made of carbon fiber composite material, indicates that the main parts are made of carbon fiber composite material, and have high strength, light weight, no increase of load of the machine body, and simultaneously, structural holes are formed on the rib plates to reduce the weight of the rib plates, and the honeycomb interlayer is used to reduce the weight of the cover plate, so that the influence on the strength of the wing is reduced while the weight is reduced; along with the continuous development of science and technology, the application field of unmanned aerial vehicles made of high-end carbon fiber composite materials is also expanding continuously, so that the unmanned aerial vehicles are innovated and designed, and the unmanned aerial vehicles play an important role in development.
However, in the implementation process of the technical scheme, at least the following technical problems are found:
if the outer cover is damaged in the traditional integral wing, the integral wing needs to be replaced, so that the waste of materials is caused, and meanwhile, the integral wing needs to be fixed by means of more screws when being assembled, so that the efficiency and the progress of subsequent maintenance work are affected.
Disclosure of Invention
The technical problems to be solved are as follows:
aiming at the defects of the prior art, the utility model provides the unmanned aerial vehicle wing for patrol, which consists of the carbon fiber composite material, by designing the detachable framework, the cover body and the front wing plate structure, each frame plate is taken as the framework, the weight of the whole wing is greatly reduced, meanwhile, the cover body can be detached and replaced, the positioning treatment of the whole wing can be realized after the front wing plate is assembled, and the technical problems mentioned in the background art are solved.
The technical scheme is as follows:
in order to achieve the above purpose, the utility model is realized by the following technical scheme:
the unmanned aerial vehicle wing for patrol flight consists of carbon fiber composite material and comprises a framework, a cover body and a front wing plate;
the framework comprises a plurality of frame plates and tail wing plates which are integrally connected; the cover body is detachably assembled on the surface of the framework; the front wing plate is detachably assembled at the front end of the framework, and the front wing plate is used for positioning the position of the cover body on the framework.
In one possible implementation manner, a plurality of the shelf boards are distributed in parallel, the specification of each shelf board is consistent, and the number of the shelf boards can be designed according to the requirement.
In a possible implementation manner, the surface of the frame plate is provided with an upper slot and a lower slot which are distributed in a staggered manner, the upper slot and the lower slot are used for inserting corresponding inserting strips, the stability of connection between the cover body and the framework can be preliminarily ensured after the inserting strips are inserted into each other, then the cover body and the framework can be ensured to be firmly connected by utilizing the baffle on the front wing plate, and the cover body and the framework can be detached after the front wing plate is detached.
In one possible implementation manner, the cover body comprises a top cover and a bottom cover, and the plugging strips are arranged on one sides of the surfaces of the top cover and the bottom cover, which face the framework; the plug strip is used for connecting each frame plate, and the notch formed in the surface of the plug strip is matched with the upper slot and the lower slot, so that the stability of the plug strip after being connected with each frame plate is ensured.
In one possible implementation manner, a connecting piece is arranged on one side, facing the framework, of the surface of the front wing plate, and a connecting groove for inserting the connecting piece is formed in the end face of the frame plate; the surface of the connecting piece is provided with the bulge, the inner wall of the connecting groove is provided with the groove matched with the bulge, and the bulge and the groove are matched to ensure the stability of the connecting piece in the use state without deflection.
In one possible implementation manner, the upper surface and the lower surface of the front wing plate are both provided with baffle plates, and in the assembled state of the framework and the cover body, the baffle plates cover gaps formed between the front wing plate and the cover body.
The beneficial effects are that:
in this scheme, through design detachable skeleton, cover body and front wing plate structure, regard each frame plate as the skeleton, very big alleviateed the weight of whole wing, the cover body can split, change simultaneously, can realize the location processing to whole wing after accomplishing the front wing plate equipment, on the basis that need not or only need with the help of a small amount of screws, can avoid the condition that the wing takes place the separation in the use, embodied the flexibility of global design.
Drawings
The foregoing description is only an overview of the present utility model, and is intended to provide a better understanding of the present utility model, as it is embodied in the following description, with reference to the preferred embodiments of the present utility model and the accompanying drawings.
FIG. 1 is a schematic view of the overall structure of the present utility model in a disassembled state;
FIG. 2 is a schematic view of the bottom cover structure of the present utility model;
FIG. 3 is a schematic view of a single rack plate structure according to the present utility model;
fig. 4 is an enlarged view of the partial structure a of fig. 1 according to the present utility model.
Legend description: 1. a frame plate; 2. a front wing plate; 3. tail wing plates; 4. a top cover; 5. a bottom cover; 6. a plug strip; 7. a lower slot; 8. an upper slot; 9. a connecting groove; 10. a connecting piece; 11. a baffle.
Detailed Description
According to the embodiment of the utility model, the unmanned aerial vehicle wing is formed by the carbon fiber composite material, the detachable framework, the cover body and the front wing plate structure are designed, and each frame plate is used as the framework, so that the weight of the whole wing is greatly reduced, meanwhile, the cover body can be detached and replaced, the positioning treatment of the whole wing can be realized after the front wing plate is assembled, and the technical problems in the background art are solved.
The technical scheme in the embodiment of the utility model aims to solve the problems of the background technology, and the general thought is as follows:
example 1:
the embodiment introduces a specific structure of a patrol unmanned aerial vehicle wing formed by carbon fiber composite materials, and comprises a framework, a cover body and a front wing plate 2 as shown in the figures 1-1;
the framework comprises a plurality of frame plates 1 and tail wing plates 3 which are integrally connected;
the cover body is detachably assembled on the surface of the framework and is used as a protection structure for the framework;
the front wing plate 2 is detachably assembled at the front end of the framework, the front wing plate 2 is used for positioning the position of the cover body on the framework, the front wing plate 2 at the position can be transversely inserted, and the pressing and positioning of the cover body are completed while the front ends of the frame plates 1 are connected.
In some examples, the shelves 1 are arranged in parallel, and the shelves 1 are of identical specifications.
In some examples, the surface of the frame plate 1 is provided with an upper slot 8 and a lower slot 7 which are distributed in a staggered manner, and the upper slot 8 and the lower slot 7 are used for inserting the corresponding plugging strip 6, wherein the specifications of the upper slot 8 and the lower slot 7 are consistent; the cover body comprises a top cover 4 and a bottom cover 5, and the plugging strip 6 is arranged on one side of the surfaces of the top cover 4 and the bottom cover 5 facing the framework; the plugging strip 6 is used for connecting each frame plate 1, and a notch formed in the surface of the plugging strip 6 is matched with the upper slot 8 and the lower slot 7; the entire top cover 4 and bottom cover 5 can be seen with reference to fig. 1 when assembled with the chassis 1.
In some examples, a connecting piece 10 is arranged on one side of the surface of the front wing plate 2 facing the framework, and a connecting groove 9 for inserting the connecting piece 10 is formed in the end face of the frame plate 1; the surface of the connecting piece 10 is provided with a bulge, the inner wall of the connecting groove 9 is provided with a groove matched with the bulge, and the bulge and the groove at the position are matched with each other, so that the connecting piece 10 cannot rotate after being connected with each frame plate 1.
In some examples, the upper and lower surfaces of the front wing plate 2 are provided with baffle plates 11, and in the assembled state of the framework and the cover body, the baffle plates 11 cover gaps formed between the front wing plate 2 and the cover body, so that the cover body and the framework are prevented from loosening in the use process.
By adopting the technical scheme:
the detachable framework, the cover body and the front wing plate 2 are designed, the frame plates 1 are used as the framework, the weight of the whole wing is greatly reduced, the cover body can be detached and replaced, the positioning treatment of the whole wing can be realized after the front wing plate 2 is assembled, the situation that the wing is separated in the using process can be avoided on the basis that the screw is not needed or only a small amount of screw is needed, and the flexibility of the whole design is embodied.
Finally, it should be noted that: it is apparent that the above examples are only illustrative of the present utility model and are not limiting of the embodiments. Other variations or modifications of the above teachings will be apparent to those of ordinary skill in the art. It is not necessary here nor is it exhaustive of all embodiments. And obvious variations or modifications thereof are contemplated as falling within the scope of the present utility model.
Claims (8)
1. Unmanned aerial vehicle wing patrols by carbon fiber composite material constitutes, its characterized in that includes:
the framework comprises a plurality of frame plates (1) and tail wing plates (3) which are connected integrally;
the cover body is detachably assembled on the surface of the framework; and
the front wing plate (2) is detachably assembled at the front end of the framework, and the front wing plate (2) is used for positioning the position of the cover body on the framework.
2. A drone cruising wing composed of carbon fibre composite material as claimed in claim 1 characterised in that: the plurality of frame plates (1) are distributed in parallel, and the specifications of the frame plates (1) are consistent.
3. A drone cruising wing composed of carbon fibre composite material as claimed in claim 1 characterised in that: the surface of the frame plate (1) is provided with an upper slot (8) and a lower slot (7) which are distributed in a staggered mode, and the upper slot (8) and the lower slot (7) are used for inserting corresponding plug-in strips (6).
4. A drone cruising wing composed of carbon fibre composite material as claimed in claim 3, characterised in that: the cover body comprises a top cover (4) and a bottom cover (5), and the plugging strip (6) is arranged on one side of the surfaces of the top cover (4) and the bottom cover (5) facing the framework.
5. A drone cruising wing composed of carbon fibre composite material as claimed in claim 3, characterised in that: the plug strip (6) is used for connecting each frame plate (1), and a notch formed in the surface of the plug strip (6) is matched with the upper slot (8) and the lower slot (7).
6. A drone cruising wing composed of carbon fibre composite material as claimed in claim 1 characterised in that: a connecting piece (10) is arranged on one side, facing the framework, of the surface of the front wing plate (2), and a connecting groove (9) for inserting the connecting piece (10) is formed in the end face of the frame plate (1).
7. A drone cruising wing composed of carbon fibre composite material as claimed in claim 6 characterised in that: the surface of the connecting piece (10) is provided with a bulge, and the inner wall of the connecting groove (9) is provided with a groove matched with the bulge.
8. A drone cruising wing composed of carbon fibre composite material as claimed in claim 1 characterised in that: the upper surface and the lower surface of the front wing plate (2) are respectively provided with a baffle (11), and the baffle (11) covers a gap formed between the front wing plate (2) and the cover body in an assembled state of the framework and the cover body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321536037.7U CN220054174U (en) | 2023-06-16 | 2023-06-16 | Unmanned aerial vehicle wing patrols and flies by carbon fiber composite material constitutes |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321536037.7U CN220054174U (en) | 2023-06-16 | 2023-06-16 | Unmanned aerial vehicle wing patrols and flies by carbon fiber composite material constitutes |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220054174U true CN220054174U (en) | 2023-11-21 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202321536037.7U Active CN220054174U (en) | 2023-06-16 | 2023-06-16 | Unmanned aerial vehicle wing patrols and flies by carbon fiber composite material constitutes |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220054174U (en) |
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2023
- 2023-06-16 CN CN202321536037.7U patent/CN220054174U/en active Active
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