CN212022961U - Control surface steering engine linkage structure of unmanned aerial vehicle and unmanned aerial vehicle - Google Patents
Control surface steering engine linkage structure of unmanned aerial vehicle and unmanned aerial vehicle Download PDFInfo
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- CN212022961U CN212022961U CN202020318587.1U CN202020318587U CN212022961U CN 212022961 U CN212022961 U CN 212022961U CN 202020318587 U CN202020318587 U CN 202020318587U CN 212022961 U CN212022961 U CN 212022961U
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Abstract
The utility model discloses an unmanned vehicles's rudder face steering wheel linkage and unmanned vehicles. This linkage structure includes: the crawler belt comprises a steering engine, a control surface and a crawler belt for connecting the steering engine and the control surface; a steering gear is arranged on the steering gear, and the steering gear are arranged inside the wings of the unmanned aerial vehicle; the control surface is provided with a control surface gear, the control surface is rotatably arranged on the wings of the unmanned aerial vehicle, and the control surface gear is positioned in the wings after the control surface is arranged; the crawler belt is sleeved on the steering engine gear and the control surface gear, so that the steering engine is linked with the control surface, and the control surface is driven to rotate relative to the wings when the steering engine rotates. The linkage structure comprises a plurality of linkage structure parts, wherein the linkage structure parts are arranged inside wings, a control surface is linked with a steering engine through the meshing action of a crawler and a gear, the drive and transmission parts of the structure are located inside the wings, and are not exposed, the installation is rapid, and the flight efficiency and the safety are improved.
Description
Technical Field
The utility model relates to an unmanned vehicles technical field, in particular to unmanned vehicles's rudder face steering wheel linkage and unmanned vehicles.
Background
At present, unmanned aerial vehicle aircraft obtains more and more people's favor, the application is also more and more extensive, simultaneously, people also more and more high to unmanned aerial vehicle's structure and control requirement, among the current unmanned aerial vehicle, the wing sets up under the condition of rudder face, rudder face steering wheel linkage mode is not good a bit in production and flight in-process, the rudder face steering wheel linkage structure (if rudder angle adds connecting rod transmission structure) of aircraft expose the covering outside at the wing, the production equipment is more troublesome, and the resistance is also very big in flight in-process, unmanned aerial vehicle's availability factor and steering wheel life-span have been influenced. For the linkage mode of the control surface steering engine of the aircraft, firstly, production is influenced, production efficiency is limited, secondly, resistance is increased in the flying process of the aircraft, the flying use efficiency is reduced, the service life of the steering engine is prolonged, and more seriously, the steering engine can be short-circuited, burnt and fried due to too large resistance of parts exposed outside and overheating of the steering engine, and the linkage mode is very unsafe.
SUMMERY OF THE UTILITY MODEL
In view of the problem that prior art unmanned vehicles's rudder face steering wheel linkage structure exposes outside influence flight efficiency and flight safety, provided the utility model discloses an unmanned vehicles' rudder face steering wheel linkage structure and an unmanned vehicles to overcome above-mentioned problem.
In order to achieve the above purpose, the utility model adopts the following technical scheme:
the foundation the utility model discloses an aspect provides an unmanned vehicles's rudder face steering wheel linkage structure, and this linkage structure includes: the crawler belt comprises a steering engine, a control surface and a crawler belt for connecting the steering engine and the control surface;
a steering gear is arranged on the steering gear, and the steering gear are arranged inside the wings of the unmanned aerial vehicle;
the control surface is provided with a control surface gear, the control surface is rotatably arranged on the wings of the unmanned aerial vehicle, and the control surface gear is positioned in the wings after the control surface is arranged;
the crawler belt is sleeved on the steering engine gear and the control surface gear, so that the steering engine is linked with the control surface, and the control surface is driven to rotate relative to the wings when the steering engine rotates.
Optionally, the steering gear and the region where the steering gear is arranged are separated from the control surface by a back beam of the wing, in the front region of the wing opposite to the control surface, the back beam of the wing is provided with a crawler belt through hole, the crawler belt penetrates through the crawler belt through hole, and the front end and the rear end of the crawler belt are respectively sleeved on the steering gear and the control surface gear.
Optionally, the steering engine gear, the track via hole and the control surface gear are aligned such that the track passes through the track via hole and meshes with the steering engine gear and the control surface gear, respectively.
Optionally, the control surface gear is a gear hinge and is used as a hinge structure for rotatably connecting the wing and the control surface.
Optionally, the control surface gear is locked by a screw with a thread and a polished rod shaft with a preset length, and after the screw is locked, the control surface gear is sleeved on the polished rod shaft of the screw, so that the control surface is rotatably connected to the wing.
Optionally, two end hinges are further arranged between the wing and the control surface, the end hinges and the control surface gear are aligned along a straight line, and the two end hinges are locked through screws with threads and polished rod shafts with preset lengths; the end hinges are respectively arranged at two ends of the control surface, and the control surface gear serving as the gear hinge is arranged in the middle of the control surface.
Optionally, the gear ratio between the steering gear and the control surface gear is 1: 1, the steering engine drives the control surface to rotate at the same speed and at the same angle.
Optionally, the gear ratio between the steering engine gear and the control surface gear is greater than or less than 1: 1, the steering engine drives the control surface to rotate at variable speed and variable angle.
Optionally, the linkage structure further comprises: the detachable steering engine cover plate is arranged at the corresponding position of the wing shell and used for sealing the steering engine in the wing, and after the detachable steering engine cover plate is installed, the steering engine cover plate is flush with the surface of the wing or lower than the surface of the wing.
According to another aspect of the utility model, an unmanned vehicles is provided, including unmanned vehicles's rudder face steering wheel linkage structure as above any.
To sum up, the beneficial effects of the utility model are that:
the linkage structure of this application includes steering wheel, rudder face and the track of connecting steering wheel and rudder face, and the steering wheel is equipped with the steering wheel gear, and the rudder face is equipped with the rudder face gear, and steering wheel, steering wheel gear and rudder face gear all set up inside the wing, and the meshing effect through track and gear makes rudder face and steering wheel linkage, and the drive disk assembly of this structure all are located inside the wing, do not expose, and the installation is swift, and has improved flight efficiency and security.
Drawings
Fig. 1 is an explosion structure schematic diagram of a control surface steering engine linkage structure of an unmanned aerial vehicle according to an embodiment of the present invention;
fig. 2 is a schematic side sectional view of a control surface steering engine linkage structure of an unmanned aerial vehicle according to an embodiment of the present invention;
fig. 3 is a schematic view of a bottom view structure of a control surface steering engine linkage structure of an unmanned aerial vehicle according to an embodiment of the present invention;
FIG. 4 is an enlarged partial schematic view of FIG. 3;
in the figure: steering engine 100, steering engine gear 110, screw 120, rudder face 200, rudder face gear 210, screw 211, end hinge 220, track 300, track through hole 310, steering engine apron 400.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention clearer, embodiments of the present invention will be described in further detail below with reference to the accompanying drawings.
In the description of the present application, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "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 thus, should not be construed as limiting the present application. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present application, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; 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 application can be understood in a specific case by those of ordinary skill in the art.
The technical conception of the utility model is that: the linkage structure of this application includes steering wheel, rudder face and the track of connecting steering wheel and rudder face, and the steering wheel is equipped with the steering wheel gear, and the rudder face is equipped with the rudder face gear, and steering wheel, steering wheel gear and rudder face gear all set up inside the wing, and the meshing effect through track and gear makes rudder face and steering wheel linkage, and the drive disk assembly of this structure all are located inside the wing, do not expose, and the installation is swift, and has improved flight efficiency and security.
Fig. 1 to 4 show an exemplary embodiment of a control plane steering engine linkage structure of an unmanned aerial vehicle according to the present application.
As shown in fig. 1 explosion structure schematic diagram, a control surface steering engine linkage structure of unmanned vehicles, this control surface steering engine linkage structure includes: steering engine 100, control plane 200 and the track 300 of connecting steering engine 100 and control plane 200.
The steering gear 100 is provided with the steering gear 110, and the steering gear 100 and the steering gear 110 are jointly arranged inside the wings of the unmanned aerial vehicle, so that the unmanned aerial vehicle is prevented from being exposed outside the wings, the flight resistance of the unmanned aerial vehicle is reduced, and the flight safety is improved. Specifically, the steering engine 100 is fixed to the steering engine fixing plate by three screws 120.
The control surface 200 is provided with a control surface gear 210, and the control surface 200 is rotatably installed on the wing of the unmanned aerial vehicle so that the angle can be changed relative to the wing body under the driving action to control the change of the flying direction and the attitude. When the control surface 200 is installed, the control surface gear 210 is located inside the wing.
The steering engine 100 is linked with the control surface 200 through the crawler 300, the crawler 300 is sleeved on the steering engine gear 110 and the control surface gear 210, when the steering engine 100 rotates, the steering engine gear 110 drives the crawler 300 to move, so that the control surface 200 is driven to rotate relative to the wing through the control surface gear 210, the angle control of the control surface 200 is realized, and the specific structure can be shown by referring to the sectional view in fig. 2.
Because parts such as steering wheel 100, steering wheel gear 110, rudder face gear 210 and track 300 of this application linkage structure all set up inside the wing, do not expose outside the covering of wing, therefore avoided current rudder face steering wheel linkage structure to expose and lead to the problem of flight resistance increase and threat flight safety, and the transmission structure installation of track and gear is convenient, when improving flight efficiency and security, has also improved production efficiency.
In this embodiment, referring to fig. 1, the area where the steering gear 110 and the steering gear 100 are disposed is separated from the control surface 200 by a back beam of the wing, in the front area of the wing opposite to the control surface 200, the back beam of the wing is provided with a crawler belt through hole 310, the crawler belt 300 passes through the crawler belt through hole 310, and the front end and the rear end of the crawler belt 300 are respectively sleeved on the steering gear 110 and the control surface gear 210.
Based on aerodynamic consideration, the control surface 200 is arranged on the rear side of the wing, and the driving mechanism comprising the steering engine 100 and the steering engine gear 110 is placed in the wing space on the front side of the control surface 200, as shown in fig. 1 and 3, a mounting groove is formed in the front area of the wing, which is located on the control surface 200, and the steering engine 100 and the control surface gear 210 are embedded in the mounting groove.
In this embodiment, this linkage structure still includes: and a separable steering engine cover plate 400 is arranged at a corresponding position of the wing shell, and the steering engine cover plate 400 is used for sealing the steering engine 100 in the wing to protect the safety of the wing structure. After installation, the steering engine cover plate 400 is flush with or lower than the surface of the wing, so that the flight resistance of the wing is not affected.
In this embodiment, as shown in fig. 1 and 2, the steering gear 110, the track through hole 310 and the control surface gear 210 are aligned such that the track 300 passes through the track through hole 310 to mesh with the steering gear 110 and the control surface gear 210, respectively. Keeping the steering engine gear 110, track via 310, and control plane gear 210 aligned, i.e.: the steering engine gear 110, the track through hole 310 and the control surface gear 210 are located on the same straight line, which is beneficial to maintaining the stable and reliable transmission matching relationship between the track 300 and the two gears.
In the present embodiment, as shown in fig. 3 and 4, the control surface gear 210 is a gear hinge, and the gear center of the control surface gear 210 has a hole through which a shaft (i.e., a screw 211) is engaged, thereby simultaneously serving as a hinge structure for rotatably connecting the wing and the control surface 200. As shown in the enlarged view of fig. 4, the control surface gear 210 is fixedly connected to the control surface 200, the right side of the control surface gear 210 serves as a hinge structure to realize rotation of the control surface 200, and the left side of the control surface gear 210 is in a gear shape, so that the caterpillar band 300 can be sleeved on the left side of the control surface gear 210 to realize linkage of the control surface 200 and the steering engine 100. The control surface gear 210 of the embodiment combines the gear structure and the hinge structure, thereby realizing two purposes, simplifying the installation and driving structure of the control surface 200, facilitating the realization of the light weight of the wing, and further improving the flight efficiency.
In this embodiment, as shown in the enlarged view of fig. 4, the control surface gear 210 is locked by a screw 211 having a thread and a polished rod shaft with a preset length, the thickness of the hinged part of the control surface gear 210 is 3mm, the screw 211 is a limit screw, wherein the polished rod shaft is 3.5mm long, the diameter is 3.5mm, and the length of the thread is 3.5mm, so that it is only necessary to completely lock the 3.5mm thread, and there is no need to worry that the control surface cannot swing up and down. For example, the front section (section a in fig. 4) of the screw 211 is a polished rod shaft, the rear section (section b in fig. 4) has a screw thread, and after the screw 211 is locked (i.e., after the screw thread is partially locked), the control surface gear 210 is sleeved on the polished rod shaft of the screw 211 and can smoothly rotate, so that the control surface 200 is rotatably connected to the wing.
In the present embodiment, as shown in fig. 1 and fig. 3, two end hinges 220 are further disposed between the wing and the control surface 200, and the end hinges 220 are aligned with the control surface gear 210 along a straight line, that is: the two end hinges 220 and the control surface gear 210 are positioned on the same straight line, and the two end hinges 220 are locked by a screw 211 with a screw thread and a polished rod shaft with a preset length; end hinges 220 are provided at both ends of the control surface 200, respectively, and a control surface gear 210 as a gear hinge is provided at a middle position of the control surface 200.
Therefore, the stability and reliability of the rotary connection of the control surface 200 and the wing can be enhanced through the end hinge 220, and the rotary stress is balanced. The control surface gear 210 is arranged in the middle of the control surface 200, so that when the steering engine 100 drives the control surface 200 to rotate through linkage action, the driving stress position is more reasonable, and the rotating imbalance of the control surface 200 cannot be caused.
In this embodiment, the gear ratio between the steering gear 110 and the control surface gear 210 is 1: 1, the steering engine 100 drives the control surface 200 to rotate at the same speed and at the same angle, and the gear ratio is convenient to control.
Of course, in other embodiments of the present application, different gear ratios may be used to achieve rotation adjustment of control surface 200 for deceleration or acceleration. For example, the gear ratio between the steering gear 110 and the control surface gear 210 is designed to be greater than or less than 1: 1, the steering engine 100 drives the control surface 200 to rotate at a variable speed and a variable angle.
The application also discloses an unmanned vehicles, including as above arbitrary unmanned vehicles's control surface steering wheel linkage structure. Therefore, the wings of the unmanned aerial vehicle are provided with the control surface steering engine linkage mechanism positioned in the wings, the control surface rotation control and adjustment can be safely and stably realized, and an exposed structure is avoided, so that the unmanned aerial vehicle has smaller flight resistance and higher flight safety performance.
To sum up, the linkage structure of this application includes steering wheel, rudder face and the track of connecting steering wheel and rudder face, and the steering wheel is equipped with the steering wheel gear, and the rudder face is equipped with the rudder face gear, and steering wheel, steering wheel gear and rudder face gear all set up inside the wing, make rudder face and steering wheel linkage through the meshing effect of track and gear, and the drive unit of this structure all are located inside the wing, do not expose, and the installation is swift, and the generation is efficient, and has improved flight efficiency and security. In the preferred embodiment, the control surface gear integrates the hinge function and the gear function, so that the dual-purpose structure is realized, the structure is further simplified, and the lightweight design of the unmanned aerial vehicle is facilitated.
In view of the above, it is only the specific embodiments of the present invention that other modifications and variations can be made by those skilled in the art based on the above-described embodiments in light of the above teachings. It should be understood by those skilled in the art that the foregoing detailed description is for the purpose of better explaining the present invention, and the scope of the present invention should be determined by the scope of the claims.
Claims (10)
1. The utility model provides an unmanned vehicles's rudder face steering wheel linkage structure which characterized in that, this linkage structure includes: the crawler belt comprises a steering engine, a control surface and a crawler belt for connecting the steering engine and the control surface;
a steering gear is mounted on the steering gear, and the steering gear are arranged inside wings of the unmanned aerial vehicle;
the control surface is provided with a control surface gear, the control surface is rotatably arranged on the wing of the unmanned aerial vehicle, and the control surface gear is positioned in the wing after the control surface is arranged;
the crawler belt is sleeved on the steering engine gear and the control surface gear, so that the steering engine is linked with the control surface, and when the steering engine rotates, the control surface is driven to rotate relative to the wings.
2. The unmanned aerial vehicle's rudder surface steering engine linkage structure of claim 1, wherein the steering engine gear and the region where the steering engine is disposed are separated from the rudder surface by a back beam of the wing, in the region of the wing in front of the rudder surface, the back beam of the wing is provided with a crawler via hole, the crawler passes through the crawler via hole, and the front end and the rear end of the crawler are respectively sleeved on the steering engine gear and the rudder surface gear.
3. The unmanned aerial vehicle's control plane steering engine linkage structure of claim 2, wherein the steering engine gear, the track via hole and the control plane gear align such that the track passes through the track via hole and meshes with the steering engine gear and the control plane gear, respectively.
4. The unmanned aerial vehicle's control plane steering engine linkage structure of claim 1, characterized in that the control plane gear is a gear hinge, and is simultaneously used as a hinge structure for rotationally connecting the wing and the control plane.
5. The unmanned aerial vehicle's control surface steering engine linkage structure of claim 4, wherein the control surface gear is locked by a screw having a thread and a polished rod shaft of a preset length, and after the screw is locked, the control surface gear is sleeved on the polished rod shaft of the screw, so that the control surface is rotatably connected to the wing.
6. The control surface steering engine linkage structure of the unmanned aerial vehicle as claimed in claim 5, wherein two end hinges are further arranged between the wing and the control surface, the end hinges and the control surface gear are aligned along a straight line, and the two end hinges are locked by screws with threads and polished rod shafts with preset lengths; the end hinges are respectively arranged at two ends of the control surface, and the control surface gear serving as the gear hinge is arranged in the middle of the control surface.
7. The unmanned aerial vehicle's control plane steering gear linkage structure of claim 1, characterized in that, the gear ratio between steering gear and the control plane gear is 1: and 1, driving the control plane to rotate at the same speed and at the same angle by the steering engine.
8. The unmanned aerial vehicle's control plane steering gear linkage structure of claim 1, wherein the gear ratio between the steering gear and the control plane gear is greater than or less than 1: and 1, driving the control surface to rotate by changing the speed and the angle of the steering engine.
9. The unmanned aerial vehicle's control surface steering engine linkage structure of claim 1, characterized in that, this linkage structure still includes: the detachable steering engine cover plate is arranged at the corresponding position of the wing shell and used for sealing the steering engine in the wing, and after the detachable steering engine cover plate is installed, the steering engine cover plate is flush with the surface of the wing or is lower than the surface of the wing.
10. An unmanned aerial vehicle, characterized by comprising a control surface steering engine linkage structure of the unmanned aerial vehicle according to any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020318587.1U CN212022961U (en) | 2020-03-13 | 2020-03-13 | Control surface steering engine linkage structure of unmanned aerial vehicle and unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020318587.1U CN212022961U (en) | 2020-03-13 | 2020-03-13 | Control surface steering engine linkage structure of unmanned aerial vehicle and unmanned aerial vehicle |
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| CN212022961U true CN212022961U (en) | 2020-11-27 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111204448A (en) * | 2020-03-13 | 2020-05-29 | 上海歌尔泰克机器人有限公司 | Control surface steering engine linkage structure of unmanned aerial vehicle and control surface driving method |
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2020
- 2020-03-13 CN CN202020318587.1U patent/CN212022961U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111204448A (en) * | 2020-03-13 | 2020-05-29 | 上海歌尔泰克机器人有限公司 | Control surface steering engine linkage structure of unmanned aerial vehicle and control surface driving method |
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