CN117799880A - Unmanned aerial vehicle wing plug-in structure and unmanned aerial vehicle - Google Patents
Unmanned aerial vehicle wing plug-in structure and unmanned aerial vehicle Download PDFInfo
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- CN117799880A CN117799880A CN202410097290.XA CN202410097290A CN117799880A CN 117799880 A CN117799880 A CN 117799880A CN 202410097290 A CN202410097290 A CN 202410097290A CN 117799880 A CN117799880 A CN 117799880A
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- unmanned aerial
- aerial vehicle
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- wing
- beam assembly
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- 230000003014 reinforcing effect Effects 0.000 claims description 6
- 238000003466 welding Methods 0.000 description 7
- 229910000831 Steel Inorganic materials 0.000 description 6
- 239000010959 steel Substances 0.000 description 6
- 238000000034 method Methods 0.000 description 4
- 230000002787 reinforcement Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 238000009434 installation Methods 0.000 description 3
- 238000012546 transfer Methods 0.000 description 3
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 208000035473 Communicable disease Diseases 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000000694 effects Effects 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
- 238000011160 research Methods 0.000 description 1
Abstract
The invention provides an unmanned aerial vehicle wing plug-in structure and an unmanned aerial vehicle, and relates to the field of unmanned aerial vehicle mounting, wherein the unmanned aerial vehicle wing plug-in structure comprises a first stiffening beam assembly, a second stiffening beam assembly, a plurality of support rods and mounting connectors; the first stiffening beam assembly is arranged on a front beam of the wing, the second stiffening beam assembly is arranged on a rear beam of the wing, the plurality of support rods are connected with the first stiffening beam assembly and the second stiffening beam assembly, and two ends of the mounting connector are respectively connected with the bottom of the first stiffening beam assembly and the bottom of the second stiffening beam assembly. The invention can strengthen the front beam and the rear beam of the wing, increase the mounting capacity of the wing, improve the stability of the unmanned aerial vehicle and meet the carrying requirement of goods.
Description
Technical Field
The invention relates to the field of unmanned aerial vehicle mounting, in particular to an unmanned aerial vehicle wing plug-in structure and an unmanned aerial vehicle.
Background
Unmanned aerial vehicles, i.e., unmanned aerial vehicles, are unmanned aerial vehicles that are operated by a radio remote control device and a self-contained programming device, or are operated autonomously, either entirely or intermittently, by an onboard computer. Unmanned aerial vehicles can be classified into military and civilian applications according to the field of application. In the military sector, unmanned aerial vehicles are classified into reconnaissance and drones. In civil aspect, unmanned aerial vehicle + trade is the real just need of unmanned aerial vehicle, at present, in the application in fields such as take photo by plane, agriculture, plant protection, miniature selfie, express delivery transportation, disaster relief, observe wild animal, monitor infectious disease, survey, news report, electric power inspection, relief of disaster, film and television shooting, has expanded the use of unmanned aerial vehicle itself widely, and the world is all in the positive expansion trade application and development unmanned aerial vehicle technique.
The inventor researches and discovers that many existing fixed wing unmanned aerial vehicles transport by hanging cargoes on the wings, but the wings are fragile and have insufficient strength, so that the weight of the cargoes on the wings of the aircraft is small, the weight of the cargoes is limited, and the carrying requirements of the cargoes cannot be met.
Disclosure of Invention
The invention aims to provide an unmanned aerial vehicle wing plug-in structure and an unmanned aerial vehicle, which can strengthen a front beam and a rear beam of a wing, increase the mounting capacity of the wing, improve the stability of the unmanned aerial vehicle and meet the carrying requirement of goods.
Embodiments of the present invention are implemented as follows:
in a first aspect, the invention provides an unmanned aerial vehicle wing plug-in structure, which comprises a first stiffening beam assembly, a second stiffening beam assembly, a plurality of support rods and a mounting connector; the first stiffening beam assembly is arranged on a front beam of the wing, the second stiffening beam assembly is arranged on a rear beam of the wing, the support rods are connected with the first stiffening beam assembly and the second stiffening beam assembly, and two ends of the mounting connector are respectively connected with the bottom of the first stiffening beam assembly and the bottom of the second stiffening beam assembly.
In an alternative embodiment, the first stiffening beam assembly comprises a first beam, a first beam fixing seat connected with a plurality of supporting rods and a mounting joint connected with the mounting joint, wherein two first beam fixing seats are arranged on the front beam, the first beam is arranged on the front beam, two first beam fixing seats are connected with two ends of the first beam fixing seats, and the mounting joint is arranged on the front beam and connected with the middle part of the first beam.
In an alternative embodiment, the first beam is provided with a groove arranged along the length direction, and a plurality of reinforcing ribs are arranged in the groove.
In an alternative embodiment, the first beam fixing seat is in an i shape, and the first beam is connected to a side surface of the first beam fixing seat.
In an alternative embodiment, the second stiffening beam assembly includes a second beam connected to the mounting joint and a second beam fixing base connected to a plurality of support bars, two second beam fixing bases are provided on the back beam, the second beam is provided on the back beam, and two second beam fixing bases are connected to both ends.
In an alternative embodiment, a connecting part is arranged in the middle of the second cross beam, a plurality of connecting ribs are arranged on the connecting part, and the connecting part is connected with the mounting connector.
In an alternative embodiment, the second beam fixing seat is in an i shape, and the second beam is connected to a side surface of the first beam fixing seat.
In an alternative embodiment, the support rod comprises a circular tube, a fixed joint and a movable joint; the fixed joint is connected with one end of the circular tube, and the movable joint is connected with the other end of the circular tube in a telescopic way.
In an alternative embodiment, the supporting rod further comprises an adjusting sleeve, a first external thread is arranged at one end, far away from the fixed joint, of the round tube, a second external thread is arranged at the movable joint, the directions of the threads of the first external thread and the second external thread are opposite, internal threads are arranged inside two ends of the adjusting sleeve, and the round tube and the movable joint are in threaded connection with two ends of the adjusting sleeve respectively.
In a second aspect, the present invention provides an unmanned aerial vehicle, including an unmanned aerial vehicle wing plug-in structure according to any of the preceding embodiments.
The embodiment of the invention has the beneficial effects that:
the invention provides an unmanned aerial vehicle wing plug-in structure, which comprises a first stiffening beam assembly, a second stiffening beam assembly, a plurality of support rods and a mounting connector, wherein the first stiffening beam assembly is connected with the second stiffening beam assembly; the first stiffening beam assembly is arranged on a front beam of the wing, the second stiffening beam assembly is arranged on a rear beam of the wing, the plurality of support rods are connected with the first stiffening beam assembly and the second stiffening beam assembly, and two ends of the mounting connector are respectively connected with the bottom of the first stiffening beam assembly and the bottom of the second stiffening beam assembly. According to the invention, the first stiffening beam component and the second stiffening beam component are respectively arranged on the front beam and the rear beam of the wing to strengthen the mounting strength of the wing, the stiffening structure extends to the wing rib, so that the load is convenient to transfer, and meanwhile, the plurality of support rods are arranged between the first stiffening beam component and the second stiffening beam component to connect, so that the stability of the front beam and the rear beam is enhanced, and the stability of the wing when goods are mounted.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are needed in the embodiments will be briefly described below, it being understood that the following drawings only illustrate some embodiments of the present invention and therefore should not be considered as limiting the scope, and other related drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
Fig. 1 is a schematic structural diagram of an unmanned aerial vehicle according to an embodiment of the present invention;
FIG. 2 is an enlarged view of a portion of FIG. 1;
fig. 3 is a schematic view of a first view angle of an external wing hanging structure of an unmanned aerial vehicle according to an embodiment of the present invention;
fig. 4 is a schematic diagram of a second view angle of an unmanned aerial vehicle wing plug-in structure according to an embodiment of the present invention;
fig. 5 is a schematic diagram of a third view angle of an unmanned aerial vehicle wing plug-in structure according to an embodiment of the present invention;
fig. 6 is a schematic view of a support bar structure according to an embodiment of the present invention.
Icon:
10-a first stiffening beam assembly; 11-a first cross beam; 111-reinforcing ribs; 12-a first beam fixing seat; 13-mounting a joint; 20-a second stiffening beam assembly; 21-a second cross beam; 211-a connection; 212-connecting ribs; 22-a second beam fixing seat; 30-supporting rods; 31-round tube; 32-fixing the joint; 33-a movable joint; 34-adjusting the sleeve; 40-mounting the joint; 50-front beam; 60-rear beam; 100-wing; 200-cargo.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments of the present invention. The components of the embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the invention, as presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
It should be noted that: like reference numerals and letters denote like items in the following figures, and thus once an item is defined in one figure, no further definition or explanation thereof is necessary in the following figures.
In the description of the present invention, it should be noted that, directions or positional relationships indicated by terms such as "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., are directions or positional relationships based on those shown in the drawings, or are directions or positional relationships conventionally put in use of the inventive product, are merely for convenience of describing the present invention and simplifying the description, and are not indicative or implying that the apparatus or element to be referred to must have a specific direction, be constructed and operated in a specific direction, and thus should not be construed as limiting the present invention. Furthermore, the terms "first," "second," "third," and the like are used merely to distinguish between descriptions and should not be construed as indicating or implying relative importance.
Furthermore, the terms "horizontal," "vertical," and the like do not denote a requirement that the component be absolutely horizontal or overhang, but rather may be slightly inclined. As "horizontal" merely means that its direction is more horizontal than "vertical", and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.
In the description of the present invention, it should also be noted that, unless explicitly specified and limited otherwise, the terms "disposed," "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
As shown in fig. 1 and fig. 2, this embodiment provides an unmanned aerial vehicle, is applicable to unmanned aerial vehicle with fixed wing, in order to solve among the prior art, unmanned aerial vehicle wing 100 bearing capacity is poor, and wing 100 is unstable when bearing goods 200 influences unmanned aerial vehicle flight, and this embodiment provides an unmanned aerial vehicle wing plug-in structure, specifically as follows.
As shown in fig. 3, the wing plug-in structure of the unmanned aerial vehicle provided in this embodiment includes a first stiffening beam assembly 10, a second stiffening beam assembly 20, a plurality of support rods 30 and a mounting connector 40; the first stiffening beam assembly 10 is arranged on the front beam 50 of the wing 100, the second stiffening beam assembly 20 is arranged on the rear beam 60 of the wing 100, the plurality of support rods 30 are connected with the first stiffening beam assembly 10 and the second stiffening beam assembly 20, and two ends of the mounting connector 40 are respectively connected with the bottom of the first stiffening beam assembly 10 and the bottom of the second stiffening beam assembly 20. In detail, the plurality of support rods 30 can adjust their own length, so that installation errors can be eliminated while installation is facilitated; the first reinforcement beam assembly 10 and the second reinforcement beam assembly 20 of the present embodiment are disposed inside the front beam 50 and the rear beam 60, respectively, so the unmanned aerial vehicle provided in the present embodiment is the same as the unmanned aerial vehicle of the prior art on the outside; the mounting joint 40 is integrally located below the wing 100, and is connected with the first stiffening beam assembly 10 and the second stiffening beam assembly 20 through bolts, so that the mounting joint can be conveniently installed and detached.
It can be appreciated that, in this embodiment, the front beam 50 and the rear beam 60 of the wing 100 are respectively provided with the first stiffening beam assembly 10 and the second stiffening beam assembly 20 to enhance the mounting strength of the wing 100, the reinforcing structure extends towards the wing rib to facilitate load transfer, and meanwhile, the plurality of support rods 30 are arranged between the first stiffening beam assembly 10 and the second stiffening beam assembly 20 to connect, so that the stability of the front beam 50 and the rear beam is enhanced, and the stability of the wing 100 when the cargo 200 is mounted is enhanced.
In a preferred embodiment, as shown in fig. 4, the first reinforcement beam assembly 10 includes a first beam 11, first beam holders 12 connecting a plurality of support rods 30, and a mounting joint 13 connecting the mounting joint 40, the first beam holders 12 are provided in two, two first beam holders 12 are provided on the front beam 50, the first beam 11 is provided on the front beam 50, and two first beam holders 12 are connected at both ends, and the mounting joint 13 is provided on the front beam 50 and connected at the middle of the first beam 11.
In detail, in this embodiment, the first transverse beam fixing seat 12 and the first transverse beam fixing seat 12 are both disposed on the front beam 50 through a welding process, and the first transverse beam 11 and the first transverse beam fixing seat 12 are connected through a welding process, but not limited to welding, and may be connected through a buckle, a bolt, or the like in other embodiments, besides, the mounting joint 13 is also connected to the front beam 50 and the middle part of the first transverse beam 11 through a welding process or a threaded connection, which is mainly used for conveniently connecting the mounting joint 40.
In a preferred embodiment, the first beam 11 has a groove disposed along a length direction, and a plurality of reinforcing ribs 111 are disposed in the groove. In detail, the first cross member 11 is formed in a rectangular parallelepiped shape, one of the side surfaces in the longitudinal direction is provided with a groove for reducing the use of steel as much as possible, the load of the unmanned aerial vehicle is reduced, and a reinforcing rib 111 is provided in the groove for reinforcing the strength of the first cross member 11, and in addition, the side surface opposite to the surface having the groove is connected to the front beam 50 by welding or by a bolt.
In a preferred embodiment, the first beam holder 12 is shaped like an i, and the first beam 11 is connected to a side of the first beam holder 12. In detail, the first transverse beam fixing seat 12 in the shape of an i is composed of an upper transverse plate, a lower transverse plate and a middle vertical plate, four supporting rods 30 in the embodiment are provided, one end of each of the two supporting rods 30 is connected to each first transverse beam fixing seat 12, and the two supporting rods 30 are respectively connected to the upper end and the lower end of the vertical plate.
It can be understood that the I-shaped steel has strong bending resistance, low cost and small residual stress compared with the common steel, does not need expensive welding data and welding line detection, and saves the manufacturing cost of the steel structure by about 30 percent.
In a preferred embodiment, as shown in fig. 5, the second reinforcement beam assembly 20 includes a second beam 21 connected to the mounting adapter 40 and a second beam fixing base 22 connected to the plurality of support rods 30, the second beam fixing base 22 is provided in two, two second beam fixing bases 22 are provided on the rear beam 60, the second beam 21 is provided on the rear beam 60, and two second beam fixing bases 22 are connected at both ends.
In detail, the second beam fixing seat 22 and the first beam fixing seat 12 have the same structure and are both in an i shape, and it is conceivable that the connection mode of the support rod 30 and the second beam fixing seat 22 is the same as that of the first beam fixing seat 12; the first beam 11 and the second beam are disposed opposite to each other, and the first beam fixing base 12 and the second beam fixing base 22 are disposed opposite to each other, so that both ends of one support bar 30 are connected to the first beam fixing base 12 and the second beam fixing base 22, respectively.
In a preferred embodiment, a connecting portion 211 is provided at the middle of the second beam 21, a plurality of connecting ribs 212 are provided on the connecting portion 211, and the connecting portion 211 is connected to the mounting connector 40. It will be appreciated that the connection portion 211 is mainly used for increasing the contact area between the second cross member 21 and the rear beam 60, so that the connection between the two members is more compact, and the purpose of the connection rib 212 is to increase the overall strength of the combination of the second cross member 21 and the rear beam 60.
In a preferred embodiment, as shown in fig. 6, the support bar 30 includes a circular tube 31, a fixed joint 32, and a movable joint 33; the fixed joint 32 is connected to one end of the circular tube 31, and the movable joint 33 is telescopically connected to the other end of the circular tube 31. In detail, the fixed joint 32 is fork-shaped at one end far away from the circular tube 31, and can just be forked on the I-shaped steel piece; the movable joint 33 is fork-shaped at the end far away from the circular tube 31, so that the I-shaped steel member can be better connected.
It will be appreciated that the support bar 30 may be adjusted by adjusting the extension and retraction of the movable joint 33 to adjust the overall length of the support bar 30, thereby facilitating the installation of the structure.
In the preferred embodiment, the support rod 30 further comprises an adjusting sleeve 34, a first external thread is arranged on one end of the circular tube 31 far away from the fixed joint 32, a second external thread is arranged on the movable joint 33, the directions of the threads of the first external thread and the second external thread are opposite, internal threads are arranged inside two ends of the adjusting sleeve 34, and the circular tube 31 and the movable joint 33 are respectively in threaded connection with two ends of the adjusting sleeve 34. It will be appreciated that the present embodiment requires only rotation of the adjustment sleeve 34 to effect length adjustment of the support rod 30.
The unmanned aerial vehicle wing plug-in structure provided by the embodiment has the following advantages:
according to the embodiment, the front beam 50 and the rear beam 60 of the wing 100 are respectively provided with the first stiffening beam assembly 10 and the second stiffening beam assembly 20 to strengthen the mounting strength of the wing 100, the stiffening structure extends towards the wing rib to facilitate load transfer, and meanwhile, the plurality of support rods 30 are arranged between the first stiffening beam assembly 10 and the second stiffening beam assembly 20 to be connected to strengthen the stability of the front beam 50 and the rear beam and the stability of the wing 100 when goods 200 are mounted.
The above description is only of the preferred embodiments of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. The unmanned aerial vehicle wing plug-in structure is characterized by comprising a first stiffening beam assembly, a second stiffening beam assembly, a plurality of support rods and a mounting connector; the first stiffening beam assembly is arranged on a front beam of the wing, the second stiffening beam assembly is arranged on a rear beam of the wing, the support rods are connected with the first stiffening beam assembly and the second stiffening beam assembly, and two ends of the mounting connector are respectively connected with the bottom of the first stiffening beam assembly and the bottom of the second stiffening beam assembly.
2. The unmanned aerial vehicle wing plug-in structure of claim 1, wherein the first stiffening beam assembly comprises a first beam, a first beam fixing seat for connecting a plurality of support rods and a mounting joint for connecting the mounting joint, the first beam fixing seat is provided with two, two first beam fixing seats are arranged on the front beam, the first beam is arranged on the front beam, two first beam fixing seats are respectively connected at two ends, and the mounting joint is arranged on the front beam and is connected with the middle part of the first beam.
3. The unmanned aerial vehicle wing plug-in structure of claim 2, wherein the first cross beam is provided with a groove arranged along the length direction, and a plurality of reinforcing ribs are arranged in the groove.
4. The unmanned aerial vehicle wing plug-in structure of claim 2, wherein the first beam fixing base is in an i-shape, and the first beam is connected to a side surface of the first beam fixing base.
5. The unmanned aerial vehicle wing plug-in structure of claim 1, wherein the second stiffening beam assembly comprises a second beam connected with the mounting connector and a second beam fixing seat connected with a plurality of support rods, two second beam fixing seats are arranged on the rear beam, the second beam is arranged on the rear beam, and two second beam fixing seats are connected at two ends.
6. The unmanned aerial vehicle wing plug-in structure of claim 5, wherein a connecting portion is arranged in the middle of the second cross beam, a plurality of connecting ribs are arranged on the connecting portion, and the connecting portion is connected with the mounting connector.
7. The unmanned aerial vehicle wing plug-in structure of claim 5, wherein the second beam fixing base is in an i-shape, and the second beam is connected to a side surface of the second beam fixing base.
8. The unmanned aerial vehicle wing plug-in structure of claim 1, wherein the support bar comprises a circular tube, a fixed joint and a movable joint; the fixed joint is connected with one end of the circular tube, and the movable joint is connected with the other end of the circular tube in a telescopic way.
9. The unmanned aerial vehicle wing plug-in structure of claim 8, wherein the support rod further comprises an adjusting sleeve, a first external thread is arranged on one end of the circular tube away from the fixed joint, a second external thread is arranged on the movable joint, the directions of the threads of the first external thread and the second external thread are opposite, internal threads are arranged inside two ends of the adjusting sleeve, and the circular tube and the movable joint are respectively connected with two ends of the adjusting sleeve in a threaded mode.
10. An unmanned aerial vehicle comprising an unmanned aerial vehicle wing pylon according to any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410097290.XA CN117799880A (en) | 2024-01-23 | 2024-01-23 | Unmanned aerial vehicle wing plug-in structure and unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410097290.XA CN117799880A (en) | 2024-01-23 | 2024-01-23 | Unmanned aerial vehicle wing plug-in structure and unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117799880A true CN117799880A (en) | 2024-04-02 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202410097290.XA Pending CN117799880A (en) | 2024-01-23 | 2024-01-23 | Unmanned aerial vehicle wing plug-in structure and unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117799880A (en) |
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2024
- 2024-01-23 CN CN202410097290.XA patent/CN117799880A/en active Pending
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