CN216887210U - Anemometry mechanism for unmanned aerial vehicle - Google Patents
Anemometry mechanism for unmanned aerial vehicle Download PDFInfo
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- CN216887210U CN216887210U CN202122799010.4U CN202122799010U CN216887210U CN 216887210 U CN216887210 U CN 216887210U CN 202122799010 U CN202122799010 U CN 202122799010U CN 216887210 U CN216887210 U CN 216887210U
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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- Y02A—TECHNOLOGIES FOR ADAPTATION TO CLIMATE CHANGE
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Abstract
The utility model discloses a wind measuring mechanism for an unmanned aerial vehicle, which relates to the field of wind measuring mechanisms and solves the problems that the existing wind measuring mechanism for the unmanned aerial vehicle generally increases wind resistance by adding an external wind measuring device, and the rotor wing of the unmanned aerial vehicle can have great influence on the detection of the wind measuring device, so that the accuracy of the test is reduced. The device has the characteristics of convenience in installation and adjustment, capability of measuring wind in directions and capability of effectively improving the accuracy of testing.
Description
Technical Field
The utility model relates to the field of wind measuring mechanisms, in particular to a wind measuring mechanism for an unmanned aerial vehicle.
Background
Along with the rapid development of many rotor unmanned aerial vehicle technique in recent years, adopt many rotor unmanned aerial vehicle to carry out meteorological monitoring and be a research focus because of its self has convenient efficient advantage again.
But in prior art, through add solitary anemometer device on many rotor unmanned aerial vehicle, but like this through the installation with the anemometer device peripheral hardware, will lead to the windage increase of flight, and lead to unmanned aerial vehicle flight stability's reduction, but also can greatly reduce measurement accuracy because the anemometer receives the influence that rotor self produced the wind field at the during operation. Therefore, the anemometry mechanism for the unmanned aerial vehicle is provided.
SUMMERY OF THE UTILITY MODEL
The utility model aims to provide a wind measuring mechanism for an unmanned aerial vehicle, which solves the problems that the wind resistance is increased, the rotor wing of the unmanned aerial vehicle has great influence on the detection of the wind measuring device and the accuracy of the test is reduced by adding an external wind measuring device to the existing wind measuring mechanism for the unmanned aerial vehicle generally.
In order to achieve the purpose, the utility model provides the following technical scheme: the utility model provides a wind measuring mechanism for unmanned aerial vehicle, includes unmanned aerial vehicle, screw, and an equipment section of thick bamboo is installed to unmanned aerial vehicle's up end, and spacing slip cover is equipped with the inner tube in the equipment section of thick bamboo, the fixed slide that is provided with of inner wall array of inner tube, and the both sides inner wall of slide has all seted up the slide rail, every all slide in the slide and be provided with the slide bar, the both sides fixedly connected with stopper of slide bar, and the stopper slides and sets up in the slide rail of one side separately, every the slide bar has the airspeed tube along the equal fixed mounting in the radial outside of inner tube, and the slide bar is along the articulated seat of the equal fixedly connected with in the radial inboard of inner tube, the lower inner wall of an equipment section of thick bamboo rotates and is connected with the rotary drum, and the embedded electric cylinder of rotary drum, be provided with drive mechanism between the lower inner wall of rotary drum and an equipment section of thick bamboo, the rotary drum is provided with adjustment mechanism with each slide bar.
Preferably, the lower extreme of an equipment section of thick bamboo passes through bolt fixed mounting at unmanned aerial vehicle's up end, the spacing slip cover of inner tube is established in an equipment section of thick bamboo, and the upper end of inner tube extends in the top of an equipment section of thick bamboo.
Preferably, the transmission mechanism comprises a ring gear and a first gear, the ring gear is fixedly sleeved at the upper end of the outer side surface of the rotary drum, the motor is fixedly installed on the lower inner wall of the equipment drum, the first gear is fixedly installed at the output end of the motor, and the first gear is meshed with the ring gear.
Preferably, adjustment mechanism includes disc, commentaries on classics board, the output fixed mounting of electrical cylinder upside has the disc, the outer edge array fixed mounting of disc has articulated seat, the disc through self articulated seat respectively with each slide bar on the articulated seat of fixed mounting between rotate be connected with the commentaries on classics board.
Preferably, the motor is fixedly installed on one side of the lower inner wall of the equipment cylinder, and the first gear fixedly sleeved at the output end of the upper side of the motor is arranged on one side of the ring gear and is in meshed connection with the ring gear.
Preferably, each slide bar all slides and sets up in the slide of each side, and the slide bar runs through the surface of inner tube along the radial outside end of inner tube to the one end fixed mounting in the inner tube outside has the airspeed tube.
Preferably, each slide rod and a pitot tube fixedly arranged on the slide rod are arranged at the extending end of the inner cylinder above the equipment cylinder.
Preferably, both ends of each rotating plate are respectively and rotatably connected with the hinge seat on the sliding rod on one side of each rotating plate and the hinge seat on the disc through scroll hinges.
Compared with the related art, the wind measuring mechanism for the unmanned aerial vehicle provided by the utility model has the following beneficial effects:
1. the utility model provides a wind measuring mechanism for an unmanned aerial vehicle, wherein a motor is fixedly arranged on one side of the lower inner wall of an equipment cylinder, a first gear is fixedly sleeved at the output end of the motor, a ring gear is fixedly sleeved at the upper end of the outer side surface of a rotary cylinder, the first gear is meshed with the ring gear, and an inner cylinder is driven by the motor to rotate relative to the equipment cylinder.
2. The utility model provides a wind measuring mechanism for an unmanned aerial vehicle, wherein two ends of each rotating plate are respectively connected with a slide bar at one side of each rotating plate and a hinge seat fixedly arranged at the outer side of a rotating plate in a rotating way through a scroll hinge, so that the disk can be pushed to move upwards through an electric cylinder, at the moment, the gravity of an inner cylinder and the structure in the inner cylinder is smaller than the elasticity of the scroll hinge, so that the inner cylinder can be firstly driven to slide and move upwards in an equipment cylinder, when the inner cylinder moves upwards to be abutted against the equipment cylinder, the scroll hinge can be extruded along with the continuous extension of the electric cylinder, so that each rotating plate can rotate, the distance between each airspeed tube can be driven to be adjusted, meanwhile, the inner cylinder can be driven by a motor to rotate to drive each airspeed tube to rotate to different positions, so as to test the wind speeds in different directions, and simultaneously, the airspeed tubes are arranged above a propeller, and then can effectually avoid the rotor to improve the accurate nature of test to the influence that the test caused.
Drawings
Fig. 1 is a schematic structural diagram of a wind measuring mechanism for an unmanned aerial vehicle.
Fig. 2 is a schematic bottom view of an anemometer for an unmanned aerial vehicle.
Fig. 3 is a schematic sectional structure view of a wind measuring mechanism for an unmanned aerial vehicle.
Fig. 4 is a cross-sectional view showing a top view of a wind measuring mechanism for an unmanned aerial vehicle.
In the figure: 1. an unmanned aerial vehicle; 2. a propeller; 3. an equipment barrel; 4. an inner barrel; 5. a slideway; 6. A slide rail; 7. a slide bar; 8. a limiting block; 9. a pitot tube; 10. a hinged seat; 11. a rotating drum; 12. An electric cylinder; 13. a ring gear; 14. a first gear; 15. a disc; 16. and (6) rotating the plate.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments; all other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The first embodiment is as follows:
referring to fig. 1-4, the present invention provides a technical solution: a wind measuring mechanism for an unmanned aerial vehicle comprises an unmanned aerial vehicle 1 and a propeller 2, wherein an equipment barrel 3 is installed on the upper end face of the unmanned aerial vehicle 1, an inner barrel 4 is sleeved in the equipment barrel 3 in a limiting sliding manner, sliding ways 5 are fixedly arranged on the inner wall array of the inner barrel 4, sliding rails 6 are respectively arranged on the inner walls of the two sides of each sliding way 5, a sliding rod 7 is arranged in each sliding way 5 in a sliding manner, limiting blocks 8 are fixedly connected to the two sides of each sliding rod 7, each limiting block 8 is arranged in the corresponding sliding rail 6 in one side in a sliding manner, a pitot tube 9 is fixedly installed on each sliding rod 7 along the radial outer side of the inner barrel 4, a hinged seat 10 is fixedly connected to each sliding rod 7 along the radial inner side of the inner barrel 4, a rotary drum 11 is rotatably connected to the lower inner wall of the equipment barrel 3, an electric cylinder 12 is embedded in the rotary drum 11, a transmission mechanism is arranged between the rotary drum 11 and the lower inner wall of the equipment barrel 3, and an adjusting mechanism is arranged between the rotary drum 11 and each sliding rod 7, the lower end of the equipment cylinder 3 is fixedly arranged on the upper end face of the unmanned aerial vehicle 1 through bolts, the inner cylinder 4 is sleeved in the equipment cylinder 3 in a limiting sliding manner, the upper end of the inner cylinder 4 extends above the equipment cylinder 3, the transmission mechanism comprises a ring gear 13 and a first gear 14, the ring gear 13 is fixedly sleeved at the upper end of the outer side face of the rotary cylinder 11, a motor is fixedly arranged on the lower inner wall of the equipment cylinder 3, the first gear 14 is fixedly arranged at the output end of the motor, the first gear 14 is meshed with the ring gear 13, the adjusting mechanism comprises a disc 15 and a rotary plate 16, the disc 15 is fixedly arranged at the output end of the upper side of the electric cylinder 12, hinge seats 10 are fixedly arranged at the outer edge of the disc 15 in an array manner, the rotary plate 16 is rotatably connected between the disc 15 and the hinge seats 10 fixedly arranged on the slide rods 7 through the hinge seats 10, and the motor is fixedly arranged on one side of the lower inner wall of the equipment cylinder 3, and a first gear 14 fixedly sleeved at the output end of the upper side of the motor is arranged at one side of the ring gear 13 and is in meshed connection with the ring gear 13.
In the embodiment, an equipment cylinder 3 is installed on the upper end face of an unmanned aerial vehicle 1 through bolts, an inner cylinder 4 is sleeved on the equipment cylinder 3 in a sliding and limiting manner, a slide way 5 is arranged in the inner cylinder 4, slide rails 6 are arranged on two sides of the slide way 5, slide rods 7 are arranged in the slide way in a sliding manner, limit blocks 8 are fixedly connected on two sides of each slide rod 7, the limit blocks 8 are arranged in the slide rails 6 on one side of each slide way in a sliding manner, a rotary drum 11 is connected to the lower inner wall of the equipment cylinder 3 in a rotating manner, an electric cylinder 12 is embedded at the upper end of the rotary drum 11, a disc 15 is fixedly connected to the upper output end of the electric cylinder 12, a rotary plate 16 is rotatably connected between the outer edge of the disc 15 and each slide rod 7 through a hinge base 10, a motor is fixedly installed on one side of the lower inner wall of the equipment cylinder 3, a first gear 14 is fixedly installed at the output end of the motor, a ring gear 13 is fixedly installed at the upper end of the outer side face of the rotary drum 11, the first gear 14 is engaged with the ring gear 13, so that the inner cylinder 4 can be driven by the motor to rotate relative to the device cylinder 3.
Example two:
referring to fig. 1-4, on the basis of the first embodiment, the present invention provides a technical solution: each slide bar 7 is arranged in the slide way 5 on one side of the slide bar 7 in a sliding manner, the slide bar 7 penetrates through the surface of the inner barrel 4 along the radial outer side end of the inner barrel 4, an airspeed tube 9 is fixedly arranged at one end of the outer side of the inner barrel 4, each slide bar 7 and the airspeed tube 9 fixedly arranged on the slide bar 7 are arranged at the extending end of the inner barrel 4 above the equipment barrel 3, and two ends of each rotating plate 16 are respectively and rotationally connected with the hinge seat 10 on the slide bar 7 on one side of the slide bar and the hinge seat 10 on the disc 15 through scroll hinges.
In this embodiment, because both ends of each rotating plate 16 are respectively connected with the sliding rod 7 on one side of each rotating plate and the hinge seat 10 fixedly arranged on the outer side of the rotating disc 15 through the scroll hinges in a rotating manner, the elasticity of the scroll hinges is large, and the rotating plate can be extended by the electric cylinder 12 when in use, so as to push the disc 15 to move upwards, at this time, because the gravity of the inner cylinder 4 and the inner structure thereof will be smaller than the elasticity of the scroll hinges, so as to firstly drive the inner cylinder 4 to slide and move upwards in the equipment cylinder 3, when the inner cylinder 4 moves upwards to be abutted against the equipment cylinder 3, at this time, along with the continuous extension of the electric cylinder 12, a plurality of scroll hinges will be needed, and then each rotating plate 16 can rotate to push the sliding rods 7 to slide away from each other in the slideways 5 on one side of each rotating plate, so as to drive the space between each pitot tube 9 to be adjusted, and simultaneously, the motor can drive the inner cylinder 4 to rotate to drive each pitot tube 9 to rotate to different positions, test with the wind speed to different position, test through airspeed head 9 simultaneously, and airspeed head 9 sets up the top at screw 2 again, and can effectually avoid the rotor to improve the accurate nature of test to the influence that the test caused.
The working principle is as follows: when the device is installed and used, the upper end face of the unmanned aerial vehicle 1 is provided with the equipment cylinder 3 through bolts, the equipment cylinder 3 is internally provided with the inner cylinder 4 in a sliding and limiting manner, the two sides of the inner cylinder 4 are provided with the slide rails 6, the slide rails are internally provided with the slide rods 7 in a sliding manner, the limiting blocks 8 are arranged in the slide rails 6 on one side of each equipment cylinder in a sliding manner, meanwhile, the lower inner wall of the equipment cylinder 3 is rotatably connected with the rotary cylinder 11, the upper end of the rotary cylinder 11 is embedded with the electric cylinder 12, the upper side output end of the electric cylinder 12 is fixedly connected with the disc 15, the outer edge of the disc 15 and each slide rod 7 are rotatably connected with the rotary plate 16 through the hinge seat 10, the motor is fixedly installed on one side of the lower inner wall of the equipment cylinder 3, the output end of the motor is fixedly sleeved with the first gear 14, and the upper end of the outer side face of the rotary cylinder 11 is fixedly sleeved with the annular gear 13, the first gear 14 is meshed with the ring gear 13, so that the inner barrel 4 can be driven by the motor to rotate relative to the equipment barrel 3; because the two ends of each rotating plate 16 are respectively connected with the slide rod 7 on one side and the hinge seat 10 fixedly arranged on the outer side of the rotating disc 15 through the scroll hinges in a rotating way, the elasticity of the scroll hinges is larger, and the rotating plate can be extended through the electric cylinder 12 when in use, so that the disk 15 can be pushed to move upwards, at the moment, the gravity of the inner cylinder 4 and the structure in the inner cylinder will be smaller than the elasticity of the scroll hinges, so that the inner cylinder 4 can be firstly driven to slide upwards in the equipment cylinder 3, when the inner cylinder 4 moves upwards to be abutted against the equipment cylinder 3, the scroll hinges will be extruded along with the continuous extension of the electric cylinder 12, so that each rotating plate 16 can rotate to push the slide rods 7 to mutually move away from each other in the slide ways 5 on one side, so as to drive the space among the airspeedles 9 to be adjusted, and simultaneously, the inner cylinder 4 can be driven by the motor to rotate to drive each airspeed tube 9 to rotate to different positions, test with the wind speed to different position, test through airspeed head 9 simultaneously, and airspeed head 9 sets up the top at screw 2 again, and can effectually avoid the rotor to improve the accurate nature of test to the influence that the test caused.
Claims (8)
1. The utility model provides a wind measuring mechanism for unmanned aerial vehicle, includes unmanned aerial vehicle (1), screw (2), and an equipment section of thick bamboo (3) is installed to the up end of unmanned aerial vehicle (1), and spacing slip cover is equipped with inner tube (4) in an equipment section of thick bamboo (3), its characterized in that, the inner wall array of inner tube (4) is fixed and is provided with slide rail (5), and slide rail (6) have all been seted up to the both sides inner wall of slide rail (5), every slide rail (5) are all slided and are provided with slide bar (7), the both sides fixedly connected with stopper (8) of slide bar (7), and stopper (8) slide and set up in slide rail (6) of one side separately, every slide bar (7) are along the radial outside of inner tube (4) equal fixedly mounted with airspeed tube (9), and slide bar (7) along the radial inboard equal fixedly connected with articulated seat (10) of inner tube (4), the lower inner wall of an equipment section of thick bamboo (3) rotates and is connected with rotary drum (11), an electric cylinder (12) is embedded in the rotary drum (11), a transmission mechanism is arranged between the rotary drum (11) and the lower inner wall of the equipment drum (3), and the rotary drum (11) and each sliding rod (7) are provided with an adjusting mechanism.
2. The anemometry mechanism for the unmanned aerial vehicle of claim 1, wherein the lower end of the equipment barrel (3) is fixedly installed on the upper end face of the unmanned aerial vehicle (1) through bolts, the inner barrel (4) is slidably sleeved in the equipment barrel (3) in a limiting manner, and the upper end of the inner barrel (4) extends above the equipment barrel (3).
3. The anemometry mechanism for the unmanned aerial vehicle according to claim 2, wherein the transmission mechanism comprises a ring gear (13) and a first gear (14), the ring gear (13) is fixedly sleeved at the upper end of the outer side surface of the rotary drum (11), the motor is fixedly installed on the lower inner wall of the equipment drum (3), the first gear (14) is fixedly installed at the output end of the motor, and the first gear (14) is meshed with the ring gear (13).
4. The anemometry mechanism for the unmanned aerial vehicle according to claim 3, wherein the adjusting mechanism comprises a disc (15) and a rotating plate (16), the disc (15) is fixedly installed at the output end of the upper side of the electric cylinder (12), the hinge seats (10) are fixedly installed on the outer edge of the disc (15) in an array mode, and the rotating plate (16) is rotatably connected between the disc (15) and the hinge seats (10) fixedly installed on the sliding rods (7) through the hinge seats (10).
5. The anemometry mechanism for the unmanned aerial vehicle according to claim 4, wherein the motor is fixedly installed at one side of the lower inner wall of the equipment cylinder (3), and a first gear (14) fixedly sleeved at the output end of the upper side of the motor is arranged at one side of the ring gear (13) and is in meshed connection with the ring gear (13).
6. The anemometry mechanism for the unmanned aerial vehicle according to claim 4, wherein each sliding rod (7) is slidably arranged in the slideway (5) on one side of the sliding rod, the sliding rod (7) penetrates through the surface of the inner cylinder (4) along the radial outer end of the inner cylinder (4), and a airspeed head (9) is fixedly arranged at one end of the outer side of the inner cylinder (4).
7. A wind measuring mechanism for unmanned aerial vehicles according to claim 6, characterized in that each slide bar (7) is provided with a pitot tube (9) fixedly mounted thereon at the extending end of the inner cylinder (4) above the equipment cylinder (3).
8. A wind measuring mechanism for unmanned aerial vehicles according to claim 7, characterized in that both ends of each said rotating plate (16) are respectively rotatably connected with the hinge base (10) on the sliding rod (7) and the hinge base (10) on the disc (15) on the respective side through scroll hinges.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122799010.4U CN216887210U (en) | 2021-11-16 | 2021-11-16 | Anemometry mechanism for unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122799010.4U CN216887210U (en) | 2021-11-16 | 2021-11-16 | Anemometry mechanism for unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216887210U true CN216887210U (en) | 2022-07-05 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122799010.4U Active CN216887210U (en) | 2021-11-16 | 2021-11-16 | Anemometry mechanism for unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216887210U (en) |
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2021
- 2021-11-16 CN CN202122799010.4U patent/CN216887210U/en active Active
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