CN215928853U - Unmanned aerial vehicle aircraft control mechanism - Google Patents
Unmanned aerial vehicle aircraft control mechanism Download PDFInfo
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- CN215928853U CN215928853U CN202121829378.4U CN202121829378U CN215928853U CN 215928853 U CN215928853 U CN 215928853U CN 202121829378 U CN202121829378 U CN 202121829378U CN 215928853 U CN215928853 U CN 215928853U
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- aerial vehicle
- telescopic rod
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Abstract
The utility model relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle control mechanism, which improves the protection and improves the convenience; the on-line screen storage device comprises a base, the box, two branches No. one, two branches No. two, the apparatus further comprises a rotating shaft, two sets of door shield mechanisms, two cone pulleys No. one, two cone pulleys No. two, two lead screws, two bearings, the lifter plate, two sliders, controller and two servo motor, there is the cavity inside of base, the bottom at the cavity is all installed to two servo motor, there is the inner chamber inside of box, the top of box is provided with the opening, both ends all are provided with the sliding opening about the box, the top of base is connected to the bottom of box, the top of box is all connected to the bottom of two branches No. two, a pivot rotates the installation between two branches, another pivot rotates the installation between two branches No. two, two door shield mechanisms are installed respectively in two pivots, install respectively in two pivots No. two cone pulleys.
Description
Technical Field
The utility model relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle aircraft control mechanism.
Background
Unmanned aircraft, also known as "drones" for short, are unmanned aircraft that are operated by radio remote control devices and self-contained program control devices, and are often more suited to tasks that are too "fool, dirty, or dangerous" than are manned aircraft.
The unmanned aerial vehicle controller is a core system of the whole flight process of finishing takeoff, air flight, task execution, return recovery and the like of the unmanned aerial vehicle, but the existing unmanned aerial vehicle controller is directly exposed outside and lacks self-protection capability when not used.
SUMMERY OF THE UTILITY MODEL
In order to solve the technical problem, the utility model provides the unmanned aerial vehicle aircraft control mechanism which improves the protection performance and improves the convenience.
The utility model relates to an unmanned aerial vehicle aircraft control mechanism, which comprises a base, a box body, two first-grade supporting rods, two second-grade supporting rods, a rotating shaft and two sets of door stop mechanisms, wherein two first-grade cone wheels, two second-grade cone wheels, two lead screws, two bearings, a lifting plate, two sliders, a controller and two servo motors are arranged in the base, a cavity is formed in the base, the two servo motors are both arranged at the bottom end of the cavity, an inner cavity is formed in the box body, an opening is formed in the top end of the box body, sliding openings are formed in the left end and the right end of the box body, the bottom end of the box body is connected with the top end of the base, the bottom ends of the two first-grade supporting rods and the two second-grade supporting rods are both connected with the top end of the box body, one rotating shaft is rotatably arranged between the two first-grade supporting rods, the other rotating shaft is rotatably arranged between the two second-grade supporting rods, the two door stop mechanisms are respectively arranged on the two rotating shafts, the two first-grade cone wheels are respectively arranged on the two rotating shafts, the two bearings are respectively installed at the bottom ends of the two sliding openings, the two lead screws are respectively rotatably installed with the two bearings, the top ends of the two lead screws extend to the upper part of the box body and are respectively connected with the bottom ends of the two conical wheels, the two conical wheels are respectively meshed with the two conical wheels I, the bottom ends of the two lead screws extend into the cavity and are respectively connected with the output ends of the two servo motors, the controller is installed at the top end of the lifting plate, the left end and the right end of the lifting plate are respectively provided with a sliding block, the two sliding blocks are respectively installed in the two sliding openings in a sliding mode, and the two sliding blocks are respectively in threaded connection with the two lead screws;
the door shield mechanism comprises two connecting rods and a baffle plate, one ends of the two connecting rods are arranged on the rotating shaft, and one end of the baffle plate is connected with the other ends of the two connecting rods respectively.
The utility model discloses an unmanned aerial vehicle aircraft control mechanism, which further comprises a first fixing plate, a second fixing plate, a first spring, a connecting block and a first telescopic rod, wherein the bottom end of the first fixing plate is connected with the top end of a baffle, the bottom end of the second fixing plate is connected with the top end of another baffle, the first fixing plate is provided with a socket, the connecting block is installed on the first telescopic rod, the first spring is sleeved on the outer side of the first telescopic rod, the left ends of the first spring and the first telescopic rod are both connected with the right end of the second fixing plate, the right end of the first spring is connected with the left end of the connecting block, and the first telescopic rod is installed in the socket in a sliding manner.
The unmanned aerial vehicle aircraft control mechanism further comprises a second telescopic rod, a second spring and a base plate, the top ends of the second telescopic rod and the second spring are connected with the bottom end of the lifting plate, the bottom ends of the second telescopic rod and the second spring are connected with the top end of the base plate, and the second spring is sleeved on the outer side of the second telescopic rod.
The unmanned aerial vehicle aircraft control mechanism further comprises a plurality of universal wheels, and the top ends of the universal wheels are connected with the bottom end of the base.
The unmanned aerial vehicle aircraft control mechanism further comprises a plurality of brake plates, and one brake plate is mounted on any one universal wheel.
The utility model discloses an unmanned aerial vehicle aircraft control mechanism, which further comprises a traction lug, wherein the traction lug is arranged at the left end of the base.
The unmanned aerial vehicle aircraft control mechanism further comprises a bulb, and the bulb is installed at the front end of the box body.
Compared with the prior art, the utility model has the beneficial effects that: when the controller is not used, the close ends of the two baffles are contacted, the bottom ends of the two baffles are contacted with the top end of the box body, when the controller is used, the two servo motors are operated to rotate anticlockwise, so that the two lead screws drive the two conical wheels II to rotate under the coordination of the two bearings respectively, the two conical wheels II drive the two conical wheels I to rotate respectively, then the two conical wheels I drive the two rotating shafts to rotate respectively, then the two baffles are opened, the two lead screws drive the two sliding blocks to move upwards respectively, so that the two sliding blocks move upwards through the lifting plate belt controller, when the two baffles are opened, the controller is lifted out of the cavity, after the controller is used, the two servo motors are operated to rotate clockwise, so that the two baffles are closed when the controller descends, and the protection performance is improved, the convenience is improved.
Drawings
FIG. 1 is a schematic diagram of an axial structure of the present invention;
FIG. 2 is a partially enlarged view of the portion A in FIG. 1;
FIG. 3 is a schematic top view of the present invention;
FIG. 4 is a schematic view of an axial view of a partial cross-sectional configuration of the present invention;
FIG. 5 is a partially enlarged view of the portion B in FIG. 4;
in the drawings, the reference numbers: 1. a base; 2. a box body; 3. a first strut; 4. a second strut; 5. a rotating shaft; 6. a connecting rod; 7. a baffle plate; 8. a first conical pulley; 9. a second cone wheel; 10. a lead screw; 11. a bearing; 12. a lifting plate; 13. a slider; 14. a controller; 15. a servo motor; 16. a first fixing plate; 17. a second fixing plate; 18. a first spring; 19. connecting blocks; 20. a first telescopic rod; 21. a second telescopic rod; 22. a second spring; 23. a base plate; 24. a universal wheel; 25. a brake plate; 26. pulling the ears; 27. a bulb.
Detailed Description
The following detailed description of embodiments of the present invention is provided in connection with the accompanying drawings and examples. The following examples are intended to illustrate the utility model but are not intended to limit the scope of the utility model.
As shown in fig. 1 to 5, the unmanned aerial vehicle aircraft control mechanism of the utility model comprises a base 1, a box body 2, two first support rods 3, two second support rods 4, a rotating shaft 5, two sets of door stop mechanisms, two first cone wheels 8, two second cone wheels 9, two lead screws 10, two bearings 11, a lifting plate 12, two sliders 13, a controller 14 and two servo motors 15, wherein a cavity is arranged in the base 1, the two servo motors 15 are both arranged at the bottom end of the cavity, an inner cavity is arranged in the box body 2, an opening is arranged at the top end of the box body 2, sliding openings are arranged at the left end and the right end of the box body 2, the bottom end of the box body 2 is connected with the top end of the base 1, the bottom ends of the two first support rods 3 and the two second support rods 4 are both connected with the top end of the box body 2, one rotating shaft 5 is rotatably arranged between the two first support rods 3, the other rotating shaft 5 is rotatably arranged between the two second support rods 4, two door stop mechanisms are respectively arranged on two rotating shafts 5, two first conical pulleys 8 are respectively arranged on the two rotating shafts 5, two bearings 11 are respectively arranged at the bottom ends of two sliding openings, two lead screws 10 are respectively rotatably arranged with the two bearings 11, the top ends of the two lead screws 10 extend to the upper part of the box body 2 and are respectively connected with the bottom ends of two second conical pulleys 9, the two second conical pulleys 9 are respectively meshed with the two first conical pulleys 8, the bottom ends of the two lead screws 10 extend into a cavity and are respectively connected with the output ends of two servo motors 15, a controller 14 is arranged at the top end of a lifting plate 12, sliding blocks 13 are respectively arranged at the left end and the right end of the lifting plate 12, the two sliding blocks 13 are respectively slidably arranged in the two sliding openings, and the two sliding blocks 13 are respectively in threaded connection with the two lead screws 10;
the door stop mechanism comprises two connecting rods 6 and a baffle 7, one ends of the two connecting rods 6 are both arranged on the rotating shaft 5, and one end of the baffle 7 is respectively connected with the other ends of the two connecting rods 6; when the controller 14 is not used, the close ends of the two baffles 7 are contacted, the bottom ends of the two baffles 7 are contacted with the top end of the box body 2, when the controller 14 is used, the two servo motors 15 are operated to rotate anticlockwise, so that the two lead screws 10 respectively drive the two second-size cone wheels 9 to rotate under the cooperation of the two bearings 11, so that the two second-size cone wheels 9 respectively drive the two first-size cone wheels 8 to rotate, then the two first-size cone wheels 8 respectively drive the two rotating shafts 5 to rotate, then the two baffles 7 are opened, simultaneously the two lead screws 10 respectively drive the two sliders 13 to move upwards, so that the two sliders 13 drive the controller 14 to move upwards through the lifting plate 12, when the two baffles 7 are opened, the controller 14 is lifted out of the cavity, after the controller 14 is used, the two servo motors 15 are operated to rotate clockwise, so that the two baffles 7 are closed while the controller 14 descends, the protection performance is improved, and the convenience is improved.
The utility model discloses an unmanned aerial vehicle aircraft control mechanism, which further comprises a first fixing plate 16, a second fixing plate 17, a first spring 18, a connecting block 19 and a first telescopic rod 20, wherein the bottom end of the first fixing plate 16 is connected with the top end of a baffle 7, the bottom end of the second fixing plate 17 is connected with the top end of another baffle 7, the first fixing plate 16 is provided with a socket, the connecting block 19 is installed on the first telescopic rod 20, the first spring 18 is sleeved on the outer side of the first telescopic rod 20, the left ends of the first spring 18 and the first telescopic rod 20 are both connected with the right end of the second fixing plate 17, the right end of the first spring 18 is connected with the left end of the connecting block 19, and the first telescopic rod 20 is installed in the socket in a sliding manner; under the normality, telescopic link 20 inserts the socket of fixed plate 16 under the effect of the elastic deformation of spring 18 under, makes two baffles 7 tightly close, has improved the protectiveness, when using controller 14, makes connecting block 19 remove left to make telescopic link 20 break away from in the socket, then operate two servo motor 15 and carry out anticlockwise rotation and can make two baffles 7 open, improved the practicality.
The unmanned aerial vehicle aircraft control mechanism further comprises a second telescopic rod 21, a second spring 22 and a backing plate 23, the top ends of the second telescopic rod 21 and the second spring 22 are connected with the bottom end of the lifting plate 12, the bottom ends of the second telescopic rod 21 and the second spring 22 are connected with the top end of the backing plate 23, and the second spring 22 is sleeved on the outer side of the second telescopic rod 21; when the lifting plate 12 drives the controller 14 to descend, the bottom end of the backing plate 23 firstly contacts the bottom end of the inner cavity, the buffer effect is increased through the second telescopic rod 21 and the second spring 22, and the convenience is improved.
The unmanned aerial vehicle aircraft control mechanism further comprises a plurality of universal wheels 24, and the top ends of the universal wheels 24 are connected with the bottom end of the base 1; the device is moved in position by a plurality of universal wheels 24, which improves flexibility.
The unmanned aerial vehicle aircraft control mechanism further comprises a plurality of brake plates 25, and one brake plate 25 is mounted on any one universal wheel 24; the device is moved into position and then the plurality of brake pads 25 are opened to secure the device for improved stability.
The unmanned aerial vehicle aircraft control mechanism further comprises a traction lug 26, and the traction lug 26 is installed at the left end of the base 1; the pulling movement is performed by the pulling lugs 26, which improves convenience.
The unmanned aerial vehicle aircraft control mechanism further comprises a bulb 27, and the bulb 27 is installed at the front end of the box body 2; when the light is dark, the bulb 27 is turned on, and convenience is improved.
The utility model relates to an unmanned aerial vehicle aircraft control mechanism, which is characterized in that when in work, an operator moves a device to a proper position through the matching of a traction lug 26 and a plurality of universal wheels 24, then opens a plurality of brake plates 25 to fix the device, when a controller 14 is not used, one ends close to two baffles 7 are contacted, the bottom ends of the two baffles 7 are contacted with the top end of a box body 2, a first telescopic rod 20 is inserted into a socket of a first fixing plate 16 under the action of elastic deformation of a connecting block 19 and a first spring 18 to tightly close the two baffles 7, when the controller 14 is used, the connecting block 19 is moved leftwards to separate the first telescopic rod 20 from the socket, then two servo motors 15 are operated to rotate anticlockwise, so that two lead screws 10 respectively drive two second conical wheels 9 to rotate under the matching of two bearings 11, and the two second conical wheels 9 respectively drive the two first conical wheels 8 to rotate, then two cone pulleys 8 drive two pivots 5 respectively and rotate, then make two baffles 7 open, two lead screws 10 drive two sliders 13 rebound respectively simultaneously to make two sliders 13 pass through lifter plate 12 and drive controller 14 rebound, when forming two baffles 7 and open, controller 14 rises out from the cavity and uses, after controller 14 finishes using, operate two servo motor 15 clockwise rotations, thereby two baffles 7 close when making controller 14 descend.
According to the unmanned aerial vehicle aircraft control mechanism, the installation mode, the connection mode or the arrangement mode are common mechanical modes, and the unmanned aerial vehicle aircraft control mechanism can be implemented as long as the beneficial effects are achieved; the controller 14 and the two servo motors 15 of the unmanned aerial vehicle aircraft control mechanism are purchased from the market, and technicians in the industry only need to install and operate the unmanned aerial vehicle aircraft control mechanism according to the attached operating instructions.
The above description is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, several modifications and variations can be made without departing from the technical principle of the present invention, and these modifications and variations should also be regarded as the protection scope of the present invention.
Claims (7)
1. An unmanned aerial vehicle aircraft control mechanism is characterized by comprising a base (1), a box body (2), two first support rods (3), two second support rods (4), a rotating shaft (5) and two sets of door stop mechanisms, wherein two first cone wheels (8), two second cone wheels (9), two lead screws (10), two bearings (11), a lifting plate (12), two sliders (13), a controller (14) and two servo motors (15) are arranged in the base (1), a cavity is arranged in the base (1), the two servo motors (15) are both arranged at the bottom end of the cavity, an inner cavity is arranged in the box body (2), an opening is formed in the top end of the box body (2), sliding openings are formed in the left end and the right end of the box body (2), the bottom end of the box body (2) is connected with the top end of the base (1), the bottom ends of the two first support rods (3) and the two second support rods (4) are both connected with the top end of the box body (2), one rotating shaft (5) is rotatably installed between two first supporting rods (3), the other rotating shaft (5) is rotatably installed between two second supporting rods (4), two door stop mechanisms are respectively installed on the two rotating shafts (5), two first conical pulleys (8) are respectively installed on the two rotating shafts (5), two bearings (11) are respectively installed at the bottom ends of two sliding openings, two lead screws (10) are respectively rotatably installed with the two bearings (11), the top ends of the two lead screws (10) extend to the upper part of a box body (2) and are respectively connected with the bottom ends of the two second conical pulleys (9), the two second conical pulleys (9) are respectively meshed with the two first conical pulleys (8), the bottom ends of the two lead screws (10) extend into a cavity and are respectively connected with the output ends of two servo motors (15), a controller (14) is installed at the top end of a lifting plate (12), and the left end and the right end of the lifting plate (12) are respectively provided with a sliding block (13), the two sliding blocks (13) are respectively installed in the two sliding openings in a sliding mode, and the two sliding blocks (13) are respectively in threaded connection with the two lead screws (10);
the door shield mechanism comprises two connecting rods (6) and a baffle (7), one ends of the two connecting rods (6) are installed on the rotating shaft (5), and one end of the baffle (7) is connected with the other ends of the two connecting rods (6) respectively.
2. The unmanned aerial vehicle aircraft control mechanism of claim 1, further comprising a first fixing plate (16), a second fixing plate (17), a first spring (18), a connecting block (19) and a telescopic rod (20), wherein the top end of a baffle (7) is connected to the bottom end of the first fixing plate (16), the top end of another baffle (7) is connected to the bottom end of the second fixing plate (17), a socket is arranged on the first fixing plate (16), the connecting block (19) is installed on the first telescopic rod (20), the first spring (18) is sleeved on the outer side of the first telescopic rod (20), the left ends of the first spring (18) and the first telescopic rod (20) are connected to the right end of the second fixing plate (17), the right end of the first spring (18) is connected to the left end of the connecting block (19), and the first telescopic rod (20) is installed in the socket in a sliding manner.
3. The unmanned aerial vehicle aircraft control mechanism of claim 2, further comprising a second telescopic rod (21), a second spring (22) and a backing plate (23), wherein the top ends of the second telescopic rod (21) and the second spring (22) are connected with the bottom end of the lifting plate (12), the bottom ends of the second telescopic rod (21) and the second spring (22) are connected with the top end of the backing plate (23), and the second spring (22) is sleeved on the outer side of the second telescopic rod (21).
4. An unmanned aerial vehicle aircraft control mechanism as claimed in claim 3, further comprising a plurality of universal wheels (24), the top ends of the plurality of universal wheels (24) all being connected to the bottom end of the base (1).
5. An unmanned aerial vehicle aircraft control mechanism as claimed in claim 4, further comprising a plurality of brake pads (25), one brake pad (25) being mounted on any one of the universal wheels (24).
6. An unmanned aerial vehicle aircraft control mechanism as claimed in claim 5, further comprising a towing ear (26), the towing ear (26) being mounted at a left end of the base (1).
7. An unmanned aerial vehicle aircraft control mechanism as claimed in claim 6, further comprising a light bulb (27), the light bulb (27) being mounted at the front end of the tank (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121829378.4U CN215928853U (en) | 2021-08-06 | 2021-08-06 | Unmanned aerial vehicle aircraft control mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121829378.4U CN215928853U (en) | 2021-08-06 | 2021-08-06 | Unmanned aerial vehicle aircraft control mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN215928853U true CN215928853U (en) | 2022-03-01 |
Family
ID=80400052
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202121829378.4U Active CN215928853U (en) | 2021-08-06 | 2021-08-06 | Unmanned aerial vehicle aircraft control mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN215928853U (en) |
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2021
- 2021-08-06 CN CN202121829378.4U patent/CN215928853U/en active Active
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address |
Address after: Room 204, Building 5, No.1 Gufang Middle Road, Wujin National High tech Industrial Development Zone, Changzhou City, Jiangsu Province, 213100 Patentee after: Changzhou Lingheng Drone Technology Co.,Ltd. Address before: 448100 No. 201, Peigong Avenue, Duodao District, Jingmen City, Hubei Province (innovation and entrepreneurship studio 3, second floor, people's Wanfu c2-5) Patentee before: Hubei Lingheng UAV Technology Co.,Ltd. |
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| CP03 | Change of name, title or address | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20230930 Address after: Room 492, Building E3, Xingzhuang Science and Technology Industrial Park, No. 288 Qinhuai Avenue, Yongyang Street, Lishui District, Nanjing City, Jiangsu Province, 211200 Patentee after: Nanjing Xinlaili Network Technology Co.,Ltd. Address before: Room 204, Building 5, No.1 Gufang Middle Road, Wujin National High tech Industrial Development Zone, Changzhou City, Jiangsu Province, 213100 Patentee before: Changzhou Lingheng Drone Technology Co.,Ltd. |
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| TR01 | Transfer of patent right |