CN210455181U - Unmanned aerial vehicle and wing thereof - Google Patents
Unmanned aerial vehicle and wing thereof Download PDFInfo
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- CN210455181U CN210455181U CN201920986567.9U CN201920986567U CN210455181U CN 210455181 U CN210455181 U CN 210455181U CN 201920986567 U CN201920986567 U CN 201920986567U CN 210455181 U CN210455181 U CN 210455181U
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- aileron
- main wing
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Abstract
The utility model provides an unmanned aerial vehicle and wing thereof, include: the main wing and the aileron are abutted; the linkage device is positioned between the main wing and the ailerons and comprises a left driving device, a left connecting rod mechanism, a steering engine, a right connecting rod mechanism and a right driving device; the linkage device controls the deflection angle of the ailerons; the ailerons are arranged below the rear edge of the main wing. The utility model discloses a change the configuration form of main wing and aileron, reach the purpose in elimination clearance. The cracking type aileron is arranged below the rear edge of the main wing, the smoothness of the surface of the wing is not damaged under the action of the driving of the steering engine, the aerodynamic appearance of the wing can be maintained, the change of the flight state can be realized, the problems of overweight and excessively thick aileron structure of the existing fixed-wing unmanned aerial vehicle are solved, meanwhile, the structure processing technology is simplified, and the installation of the aileron is convenient.
Description
Technical Field
The utility model belongs to the technical field of unmanned aerial vehicle, especially, unmanned aerial vehicle and wing thereof.
Background
Fixed wing drones are increasingly using non-conventional flap forms in order to improve aerodynamic performance. For an industrial-grade fixed wing unmanned aerial vehicle, how to design an unconventional aileron structure with light weight, simple structure and better aerodynamic performance becomes an important factor influencing the aerodynamic performance of the unmanned aerial vehicle.
An aileron structure of wide use among the fixed wing unmanned aerial vehicle at present, including installing in the drive steering wheel and the aileron main part of wing trailing edge. The aileron main body is arranged on the trailing edge of the wing in a connecting mode of a worm, a guy cable, a hinge and the like. Wherein the ailerons are in clearance fit with the rotating surface of the rotating shaft, and the rotating angle of the ailerons is about-30 degrees.
At present, an aileron commonly adopted by a fixed-wing unmanned aerial vehicle is of a traditional structure, the whole wing is divided into a front part and a rear part which are different, and the aerodynamic performance and the structural integrity of the wing are affected. Conventionally, mechanically driven ailerons must be designed and manufactured with a certain clearance on the surface of the aileron in order to achieve aileron adjustment, and in the case of such aileron configurations, the ailerons generate curvature discontinuities at the rotation axis of the deformation motion when the flight attitude adjustment is performed.
Generally, due to the assembly of the front and rear gaps between the wing main body and the ailerons, the integral shape of the upper surface of the wing is damaged, and the aerodynamic performance of the whole wing is further damaged; on the other hand, the layout of the ailerons not only increases the weight of the structure, but also increases the maintenance cost.
SUMMERY OF THE UTILITY MODEL
In order to eliminate the influence of clearance and camber sudden change to aircraft aerodynamic performance, the utility model provides an unmanned aerial vehicle and wing thereof.
The specific technical scheme is as follows:
an unmanned aerial vehicle wing, comprising: the main wing and the aileron are abutted; the linkage device is positioned between the main wing and the ailerons and comprises a left driving device, a left connecting rod mechanism, a steering engine, a right connecting rod mechanism and a right driving device; the linkage device controls the deflection angle of the ailerons; the ailerons are arranged below the rear edge of the main wing.
Preferably, the length of the aileron is 10-50% of the chord length of the main engine wing, and the position is 10-50% of the trailing edge of the main engine wing.
Preferably, the flap position is 25% at the trailing edge of the main wing.
Preferably, the deflection angle range of the ailerons is 0-45 degrees, and the ailerons are deflected in a unidirectional linear mode.
Preferably, the surface of the main wing is paved with a solar panel.
Preferably, the material of the main wing comprises one or more of an aircraft layer wood, a composite material, a carbon fiber material and an aluminum alloy material.
Preferably, the connection means of the main wing and the aileron comprises one or more of a connecting rod, a bearing and a screw connection.
Preferably, the thickness of the aileron is 1-3 mm.
An unmanned aerial vehicle comprising the wing of any of claims 1 to 8.
Compared with the prior art, an unmanned aerial vehicle and wing thereof have following advantage:
the utility model provides an unmanned aerial vehicle and wing thereof through the configuration form that changes the main wing and aileron, reaches the purpose in elimination clearance. The cracking type aileron is arranged below the rear edge of the main wing, the smoothness of the surface of the wing is not damaged under the action of the driving of the steering engine, the aerodynamic appearance of the wing can be maintained, the change of the flight state can be realized, the problems of overweight and excessively thick aileron structure of the existing fixed-wing unmanned aerial vehicle are solved, meanwhile, the structure processing technology is simplified, and the installation of the aileron is convenient.
Drawings
Fig. 1 is a schematic view of an unmanned aerial vehicle before wing deformation according to the present invention;
fig. 2 is a schematic diagram of the unmanned aerial vehicle after the wing is deformed according to the present invention;
fig. 3 is a schematic view of a wing surface configuration of an unmanned aerial vehicle according to the present invention;
fig. 4 is a schematic view of an aileron connected to a main wing.
Description of reference numerals:
1 main wing 2 aileron 3 left driving device 4 left connecting rod mechanism
5 steering engine 6 right link mechanism 7 right driving device
Detailed Description
The technical solution of the present invention will be described in detail with reference to the specific embodiments. It should be understood that the detailed description and specific examples, while indicating the invention, are intended for purposes of illustration only and are not intended to limit the invention.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "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; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art through specific situations.
The present invention will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.
Fig. 2 is the utility model provides a schematic diagram after unmanned aerial vehicle wing warp. The utility model provides a pair of unmanned aerial vehicle wing, include: the main wing 1 is abutted with the aileron 2; the linkage device is positioned between the main wing 1 and the ailerons (2), and comprises a left driving device 3, a left connecting rod mechanism 4, a steering engine 5, a right connecting rod mechanism 6 and a right driving device 7; the linkage device controls the deflection angle of the aileron 2, the deflection angle range of the aileron 2 is 0-45 degrees, and the aileron 2 deflects in a unidirectional linear way; the length of the aileron 2 is 10-50% of the chord length of the main wing 1, the position is 10-50% of the rear edge of the main wing 1, and the position which is 25% of the rear edge of the main wing 1 is optimized.
Fig. 4 is the sketch map of main wing is connected to the aileron, the utility model discloses a fracture formula aileron is located the wing trailing edge, installs in the 25% department of 1 chord length of main wing, and it is driven by steering wheel 5, through the transmission of left link mechanism 4 and right link mechanism 6, drives left drive arrangement 3 and the motion of right drive arrangement 7, and then the deflection of control aileron 2, and the deflection angle scope is 0 ~ 45. Starting at 0 degrees to the main wing 1, as shown in fig. 1, the deflection is downward, the maximum deflection angle being 45 °, this deflection being a linear deflection. When the flap 2 is at 0 degrees to the main wing 1, the flap 2 becomes a part of the main wing 1, so there is no gap and no curvature discontinuity is generated when deformed. The aileron 2 is located below the main wing 1 and does not affect the upper surface of the main wing 1. Therefore, the aerodynamic characteristics of the main wing 1 are not affected.
In general, in order to realize the adjustment of the aileron, the conventional mechanically driven aileron must flow a certain gap on the surface of the aileron during the design and manufacture, and in the configuration of the aileron, the aileron generates a curvature abrupt point at a rotating shaft of a deformation motion during the adjustment of the flight attitude. In order to eliminate clearance and camber sudden change to the influence of aircraft aerodynamic performance, the utility model discloses with a fracture formula aileron 2 configuration, through the neotype mode of fracture formula aileron 2 this kind, install aileron 2 in the below of main wing 1, realize main wing 1 in aileron 2 adjustment processes, the upper surface at main wing 1 trailing edge is not influenced, therefore, does not produce the influence to the aerodynamic characteristic of main wing (1). The cracking type aileron is a feasible scheme with lower cost in engineering.
The invention aims to provide a cracking type aileron structure, which aims to solve the problems that the aileron structure of the existing fixed-wing unmanned aerial vehicle is too heavy and thick, the structure processing technology is complicated, and the aileron structure is inconvenient to install. Meanwhile, the technical problems that the aerodynamic efficiency of the main wing is reduced and the like due to the fact that an assembly gap is formed on the upper surface of the main wing and the integrity and smoothness of the surface of the main wing are damaged in the whole assembling and running process between the main wing 1 and the aileron 2 are solved.
The working principle of the cracking type aileron structure of the invention is that the main wing 1 and the aileron 2 which are assembled in the original clearance are changed in the configuration form to achieve the purpose of eliminating the clearance. The split type aileron structure is arranged below the rear edge of the main wing 1, and under the driving action of the steering engine 5, the capability of changing the flight state of the unmanned aerial vehicle by the ailerons 2 can be realized ingeniously under the condition of not damaging the smooth surface of the main wing 1 and maintaining the aerodynamic appearance of the wings. The layout form can improve the laying number of the solar panels to 6-8% particularly for an aircraft for laying the solar panels.
The structural composition of the flap 2 will now be described in detail. The cracking type aileron 2 is arranged at the position (far from the trailing edge of the wing) 25% of the chord length of the main wing 1, is driven by a steering engine 5, and drives a left driving device 3 and a right driving device 7 to move through the transmission of a left connecting rod mechanism 4 and a right connecting rod mechanism 6, thereby controlling the deflection of the aileron 2. Wherein, the deflecting direction of the cracking type aileron 2 is only unidirectional deflection, the deflecting angle range is 0-45 degrees, and the deflection is linear deflection. When the deflection angle of the cracking type aileron 2 is 0 degree, as shown in figure 1, the cracking type aileron 2 is jointed with the main wing 1 to form a whole with the wing. When the cracking type aileron 2 deflects a certain angle, as shown in fig. 2, the cracking type aileron 2 and the rear edge of the main wing 1 form an included angle ranging from 0 degree to 45 degrees.
The main reasons for the innovative inventive split flap 2 are: first, in the conventional aileron structure, because the ailerons are mounted on the trailing edge of the wing and the assembly between the ailerons causes a gap, particularly when the ailerons deflect, the ailerons generate curvature discontinuities at the rotating shaft of the deformation motion, which damages the smoothness of the wing surface, brings about greater flight resistance and reduces the aerodynamic performance of the aircraft. By adopting the structure of the cracking type aileron 2 provided by the utility model, the cracking type aileron 2 is arranged below the rear edge of the main wing 1, and does not interfere with the upper surface of the main wing 1, so that the adverse effect of the streamline shape of the main wing 1 caused by the conventional aileron 2 can be avoided; secondly, in the traditional aileron structure, when the deflection angle is 0 degree, the structure of the aileron and the wing form a whole, and the thickness of the traditional aileron is too large due to the configuration mode, so that the structure is difficult to install and process, and the manufacturing cost is increased. Adopt the utility model provides a fracture formula aileron 2 configuration, when fracture formula aileron 2 deflection angle was 0, fracture formula aileron 2 and main wing 1 constitute a whole equally. However, as the split type aileron 2 is arranged below the rear edge of the main wing 1, the flaeron 2 with a thinner and lighter structure can be manufactured, the structure of the split type aileron 2 is only 2mm, the weight of the split type aileron 2 is greatly reduced, the manufacturing cost is reduced, and meanwhile, the structure is convenient to install; thirdly, due to the layout of the split ailerons 2 on the lower surface of the rear edge of the main wing 1, the solar panel is not damaged on the upper surface of the main wing 1, so that compared with the traditional wing structure with fixed wings, the laying efficiency of the solar panel can be improved by 6% -8%, and as shown in fig. 3, the split ailerons 2 are arranged on the lower surface of the main wing 1, and the laying of the solar panel is not influenced.
The material of the wing adopts aviation laminated wood, composite material, carbon fiber material, aluminum alloy material and the like;
the materials of the split type ailerons adopt balsa, composite materials, carbon fiber materials, aluminum alloy materials and the like;
the connection mode of the wings and the cracking type ailerons can be realized through connecting rods, bearings, screws and the like;
the utility model also provides an unmanned aerial vehicle, including above an arbitrary wing, simultaneously, still include organism, aircraft control system etc..
To sum up, the utility model provides an unmanned aerial vehicle and wing thereof through the configuration form that changes the main wing and aileron, reaches the purpose in elimination clearance. The cracking type aileron is arranged below the rear edge of the main wing, the smoothness of the surface of the wing is not damaged under the action of the driving of the steering engine, the aerodynamic appearance of the wing can be maintained, the change of the flight state can be realized, the problems of overweight and excessively thick aileron structure of the existing fixed-wing unmanned aerial vehicle are solved, meanwhile, the structure processing technology is simplified, and the installation of the aileron is convenient.
The above embodiments are preferred embodiments of the present invention, and do not limit the scope of the present invention. Any technical personnel in the technical field that the utility model belongs to, under the prerequisite that does not deviate from the spirit and scope of the utility model discloses, it is right that the equivalent structure that the content was done of the utility model all falls into within the patent scope that the utility model claims protection.
Claims (9)
1. An unmanned aerial vehicle wing, comprising: the aircraft comprises a main wing (1), an aileron (2) and a linkage device, wherein the main wing (1) is abutted against the aileron (2);
the linkage device is positioned between the main wing (1) and the ailerons (2) and comprises a left driving device (3), a left connecting rod mechanism (4), a steering engine (5), a right connecting rod mechanism (6) and a right driving device (7);
the linkage controls the deflection angle of the aileron (2);
the ailerons (2) are arranged below the rear edge of the main wing (1).
2. An unmanned aerial vehicle wing as claimed in claim 1, wherein the length of the aileron (2) is 10-50% of the chord length of the main wing (1) and is located at 10-50% of the trailing edge of the main wing (1).
3. A wing for unmanned aerial vehicles according to claim 2, wherein the aileron (2) is located 25% of the trailing edge of the main wing (1).
4. A wing for a drone according to claim 1, characterised in that the range of the deflection angle of the aileron (2) is 0-45 ° and is a unidirectional linear deflection.
5. A wing for unmanned aerial vehicles according to claim 1, wherein the main wing (1) is surfaced with solar panels.
6. An unmanned aerial vehicle wing as claimed in claim 1, wherein the material of the main wing (1) comprises one or more of an aerospace laminated wood, a composite material, a carbon fibre material and an aluminium alloy material.
7. A wing for unmanned aerial vehicles according to claim 1, wherein the connection means of the main wing (1) and the aileron (2) comprises one or more of a link, a bearing and a screw connection.
8. A wing for a drone according to claim 1, characterised in that the thickness of the aileron (2) is between 1 and 3 mm.
9. An unmanned aerial vehicle comprising the wing of any one of claims 1 to 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920986567.9U CN210455181U (en) | 2019-06-28 | 2019-06-28 | Unmanned aerial vehicle and wing thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920986567.9U CN210455181U (en) | 2019-06-28 | 2019-06-28 | Unmanned aerial vehicle and wing thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210455181U true CN210455181U (en) | 2020-05-05 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920986567.9U Active CN210455181U (en) | 2019-06-28 | 2019-06-28 | Unmanned aerial vehicle and wing thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210455181U (en) |
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- 2019-06-28 CN CN201920986567.9U patent/CN210455181U/en active Active
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