CN213057502U - High-speed flight unmanned vehicles that VTOL - Google Patents
High-speed flight unmanned vehicles that VTOL Download PDFInfo
- Publication number
- CN213057502U CN213057502U CN202021553982.4U CN202021553982U CN213057502U CN 213057502 U CN213057502 U CN 213057502U CN 202021553982 U CN202021553982 U CN 202021553982U CN 213057502 U CN213057502 U CN 213057502U
- Authority
- CN
- China
- Prior art keywords
- duct
- aircraft
- brushless motor
- propeller
- shell
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Landscapes
- Toys (AREA)
Abstract
The utility model provides a high-speed flying unmanned aerial vehicle taking off and landing vertically, which comprises an aircraft shell and a propeller, wherein a vertical duct vertically penetrates through the aircraft shell, and the propeller is erected at the upper end of the vertical duct through a bracket; a horizontal duct is horizontally arranged at the rear side part of the vertical duct; the lower port of the vertical duct and the horizontal duct are both provided with automatic opening and closing devices; the horizontal duct is communicated and separated with the vertical duct through an automatic opening and closing device; the blades of the propeller are surrounded outside the inner ring shell, and the brushless motor is arranged in a motor groove in the inner ring shell; the stator of the brushless motor is fixed on the bracket through a fixed shaft. The utility model can realize the vertical take-off and landing and the flat flying of the aircraft without tilting, thereby reducing the flat flying resistance, greatly reducing the overall gravity center and the volume of the propeller, and improving the balance of the aircraft; the aircraft has the characteristics of high flight stability and low failure rate of equipment.
Description
[ technical field ] A method for producing a semiconductor device
The utility model relates to an unmanned vehicles field, concretely relates to high-speed flight unmanned vehicles of VTOL.
[ background of the invention ]
The unmanned plane is called unmanned plane for short, and is an unmanned plane operated by radio remote control equipment and a self-contained program control device, and is also called unmanned aerial vehicle.
The existing tilting multi-rotor vertical take-off and landing aircraft adopts a rotating motor installation arm to change the angle between a motor and a propeller and an aircraft body, so that the force generated by the propeller is distributed in the horizontal and vertical directions, and finally the rotation and the horizontal flight are realized. Because the motor and the propeller have rotational inertia, the resistance is very large when the motor and the propeller tilt, and the failure rate is high. Meanwhile, the existing tilting structure of the tilting multi-rotor vertical take-off and landing aircraft is large, multiple and large, the structure is complex, and the aircraft is not beneficial to flight and design maintenance.
The propeller of the unmanned aerial vehicle is directly driven by an outer rotor brushless motor, and the motor needs to be output; the weight of the power set is increased to a certain extent, and the bending or deformation of the output shaft of the motor is often caused by vibration, impact and the like when the unmanned aerial vehicle flies for many times, so that the whole coaxiality is influenced on the dynamic balance, and further vibration and propeller imbalance are generated in the flying process. In addition, because the motor and the propeller of the existing multi-rotor aircraft both adopt a fixed output shaft mode, and the motor and the propeller need low gravity center during design; this limits the stator height of the brushless motor to a certain extent.
[ Utility model ] content
The technical problem to be solved by the utility model is to provide a high-speed flying unmanned aerial vehicle capable of taking off and landing vertically, which can take off and landing vertically and fly without tilting, thereby reducing the resistance to flying, greatly reducing the overall gravity center and volume of the propeller, and improving the balance of the aircraft; the aircraft has the characteristics of high flight stability and low failure rate of equipment.
The utility model discloses a realize like this:
the utility model provides a high-speed unmanned vehicles that flies of VTOL which characterized in that: the unmanned aerial vehicle comprises an aircraft shell and a propeller, wherein a vertical duct vertically penetrates through the aircraft shell, and the propeller is erected at the upper end of the vertical duct through a bracket; a horizontal duct is horizontally arranged at the rear side part of the vertical duct positioned at the rear end of the aircraft shell; the lower port of the vertical duct positioned at the rear end of the aircraft shell and the horizontal duct are both provided with automatic opening and closing devices; the horizontal duct is communicated and separated with the corresponding vertical duct through an automatic opening and closing device;
the propeller comprises an inner ring shell, blades and a brushless motor, wherein the inner ring shell is cylindrical, the blades are arranged outside the inner ring shell in a surrounding manner, a motor groove is formed in the inner ring shell, and the brushless motor is arranged in the motor groove; the upper end of the inner ring shell is provided with a connecting part, and the connecting part is provided with a mounting hole; the brushless motor comprises a stator, a rotor, a fixing part and a connecting shaft, wherein the stator is sleeved in the rotor; the upper end of the brushless motor is connected with the mounting hole of the connecting part through a connecting shaft, and the fixing part is arranged at the lower end of a stator of the brushless motor.
Furthermore, each automatic opening and closing device comprises a plurality of blocking pieces, linkage structures and driving devices, wherein the blocking pieces are arranged at equal intervals along the circular inner wall of the duct, one end of each blocking piece is rotatably connected with the circular inner wall through a rotating shaft, the blocking pieces are mutually connected through the linkage structures, and the driving devices drive the blocking pieces to rotate.
Further, the driving device is a rotating motor.
Further, the lower end of the fixing part is fixed on the aircraft; the lower end of the connecting shaft is fixed on the rotor, and the upper end of the connecting shaft penetrates through the mounting hole and is fixed with the connecting part through a nut.
Further, still include the installation department, brushless motor sets up in the installation department, the installation department sets up at the motor inslot, brushless motor's rotor with the inner wall fixed connection of installation department, the installation department is fixed mutually through connecting axle and mounting hole and connecting part.
Further, threaded holes are formed in the upper portion of the mounting portion, threads are arranged on the lower portion of the connecting shaft, and the lower portion of the connecting shaft penetrates through the mounting hole and is in threaded connection with the threaded holes.
The utility model has the advantages that:
the utility model has simple structure, can realize the flat flight of the aircraft without tilting, reduces the flat flight resistance, is beneficial to the flight of the aircraft, and reduces the failure rate of equipment; in addition, the adjustment of the flying speed can be realized by controlling the size of the ducted nozzle, and the speed and the flying accuracy of the aircraft can be accurately controlled. Meanwhile, the design of the utility model that the brushless motor is arranged in the propeller shell makes the overall gravity center of the propeller and the brushless motor obviously lower than the combination of the existing conventional brushless motor and the propeller; the overall height of the motor is lower than the combination of the conventional brushless motor and the propeller, and the volume is smaller; can be better install on many rotor unmanned aerial vehicle or other unmanned vehicles.
[ description of the drawings ]
The invention will be further described with reference to the following examples with reference to the accompanying drawings.
Fig. 1 is a schematic view of the high-speed flying unmanned aerial vehicle taking off and landing vertically.
Fig. 2 is a sectional view taken along a-a of fig. 1.
Fig. 3 is one of the schematic diagrams of the circular inner wall of the duct and the automatic opening and closing device of the present invention.
Fig. 4 is a second schematic view of the circular inner wall of the duct and the automatic opening and closing device of the present invention.
Fig. 5 is a schematic structural view of one embodiment of the propeller of the present invention.
Fig. 6 is a schematic structural diagram of a brushless motor according to an embodiment of the present invention.
Fig. 7 is a perspective view of a second embodiment of the propeller of the present invention.
Fig. 8 is a cross-sectional view of a second embodiment of the propeller of the present invention.
Fig. 9 is an exploded view of a second embodiment of the propeller of the present invention.
[ detailed description ] embodiments
For better understanding of the above technical solutions, the following detailed descriptions will be provided in conjunction with the drawings and the detailed description of the embodiments.
Referring to fig. 1 to 6, the high-speed flying unmanned aerial vehicle for vertical take-off and landing of the present invention includes an aircraft casing 1 and a propeller 2, wherein a vertical duct 11 vertically penetrates through the aircraft casing 1, and the propeller 2 is erected at the upper end of the vertical duct 11 through a bracket 3; a horizontal duct 12 is horizontally arranged at the rear side part of the vertical duct 11 positioned at the rear end of the aircraft shell 1; the lower port of the vertical duct 11 and the horizontal duct 12 which are positioned at the rear end of the aircraft shell 1 are both provided with automatic opening and closing devices 4; the horizontal duct 12 is communicated and separated with the corresponding vertical duct 11 through the automatic opening and closing device 4.
Each of the automatic opening and closing devices 4 includes a plurality of blocking pieces 41, a linkage structure (not shown), and a driving device (not shown), each of the blocking pieces 41 is disposed at equal intervals along the circular inner wall of the duct, one end of each of the blocking pieces 41 is rotatably connected to the circular inner wall through a rotating shaft 42, and each of the blocking pieces 41 is connected to each other through the linkage structure and is driven by the driving device to rotate by the blocking piece 41.
The driving device is a rotating motor.
The utility model is provided with the vertical duct 11 and the horizontal duct 12, and the lower port of the vertical duct 11 and the horizontal duct 12 are both provided with the automatic opening and closing devices 4, so that the switching between the vertical duct 11 and the horizontal duct 12 and the adjustment of the size of the duct nozzle can be realized through the opening and closing of the automatic opening and closing devices 4 on each duct; the force generated by the propeller 2 is distributed in the horizontal and vertical directions, and finally the stable vertical take-off and landing and high-speed horizontal flight of the aircraft are realized.
The propeller 2 comprises an inner ring shell 21, blades 22 and a brushless motor 23, wherein the inner ring shell 21 is cylindrical, the blades 22 surround the outer part of the inner ring shell 21, a motor groove 211 is formed in the inner part of the inner ring shell 21, and the brushless motor 23 is installed in the motor groove 211; a connecting part 24 is arranged at the upper end of the inner ring shell 21, and a mounting hole 241 is formed in the connecting part 24; the brushless motor 23 comprises a stator 231, a rotor 232, a fixing part 233 and a connecting shaft 234, wherein the stator 231 is sleeved in the rotor 232; the upper end of the brushless motor 23 is connected to the mounting hole 241 of the connecting portion 24 through a connecting shaft 234, and the fixing portion 233 is disposed at the lower end of the stator 231 of the brushless motor 23.
Referring specifically to fig. 5-6, in one embodiment of the propeller of the present invention, the fixing portion 233 is fixedly disposed below the stator 231, and the lower end of the fixing portion 233 is fixed to the aircraft; the lower end of the connecting shaft 234 is fixed to the rotor 232, and the upper end of the connecting shaft 234 is inserted into the mounting hole 241 and fixed to the connecting portion by a nut 25.
Specifically referring to fig. 7-9, in the second embodiment of the propeller of the present invention, the propeller further includes an installation portion 26, the brushless motor 23 is disposed in the installation portion 26, the installation portion 26 is disposed in the motor groove 211, the rotor 232 of the brushless motor 23 is fixedly connected to the inner wall of the installation portion 26, and the installation portion 26 is fixed to the connection portion 24 through the connection shaft 234 and the installation hole 241.
A threaded hole 261 is formed in the upper portion of the mounting portion 26, threads 2341 are arranged below the connecting shaft 234, and the lower portion of the connecting shaft 234 penetrates through the mounting hole 241 and is in threaded connection with the threaded hole 261.
When the brushless motor 23 is energized, the rotor 232 rotates, the connecting shaft 234 transmits the rotational power to the connecting portion 24, and the connecting portion 24 transmits the rotational power to the inner ring housing 21, so as to rotate the blades 22.
In a word, the utility model discloses simple structure need not to vert and can realize the flat flight of aircraft, has reduced flat flight resistance, does benefit to the flight of aircraft, has reduced the fault rate of equipment simultaneously; in addition, the adjustment of the flying speed can be realized by controlling the size of the ducted nozzle, and the speed and the flying accuracy of the aircraft can be accurately controlled. Meanwhile, the design of the utility model that the brushless motor is arranged in the propeller shell makes the overall gravity center of the propeller and the brushless motor obviously lower than the combination of the existing conventional brushless motor and the propeller; the overall height of the motor is lower than the combination of the conventional brushless motor and the propeller, and the volume is smaller; can be better install on many rotor unmanned aerial vehicle or other unmanned vehicles.
Although specific embodiments of the present invention have been described, it will be understood by those skilled in the art that the specific embodiments described are illustrative only and are not limiting upon the scope of the invention, and that equivalent modifications and variations can be made by those skilled in the art without departing from the spirit of the invention, which is to be limited only by the claims appended hereto.
Claims (6)
1. The utility model provides a high-speed unmanned vehicles that flies of VTOL which characterized in that: the unmanned aerial vehicle comprises an aircraft shell and a propeller, wherein a vertical duct vertically penetrates through the aircraft shell, and the propeller is erected at the upper end of the vertical duct through a bracket; a horizontal duct is horizontally arranged at the rear side part of the vertical duct positioned at the rear end of the aircraft shell; the lower port of the vertical duct positioned at the rear end of the aircraft shell and the horizontal duct are both provided with automatic opening and closing devices; the horizontal duct is communicated and separated with the corresponding vertical duct through an automatic opening and closing device;
the propeller comprises an inner ring shell, blades and a brushless motor, wherein the inner ring shell is cylindrical, the blades are arranged outside the inner ring shell in a surrounding manner, a motor groove is formed in the inner ring shell, and the brushless motor is arranged in the motor groove; the upper end of the inner ring shell is provided with a connecting part, and the connecting part is provided with a mounting hole; the brushless motor comprises a stator, a rotor, a fixing part and a connecting shaft, wherein the stator is sleeved in the rotor; the upper end of the brushless motor is connected with the mounting hole of the connecting part through a connecting shaft, and the fixing part is arranged at the lower end of a stator of the brushless motor.
2. The high-speed flying vertical take-off and landing unmanned aerial vehicle of claim 1, wherein: each automatic opening and closing device comprises a plurality of blocking pieces, a linkage structure and a driving device, wherein the blocking pieces are arranged at equal intervals along the circular inner wall of the duct, one end of each blocking piece is rotatably connected with the circular inner wall through a rotating shaft, the blocking pieces are mutually connected through the linkage structure, and the driving device drives the blocking pieces to rotate.
3. The high-speed flying vertical take-off and landing unmanned aerial vehicle of claim 2, wherein: the driving device is a rotating motor.
4. The high-speed flying vertical take-off and landing unmanned aerial vehicle of claim 1, wherein: the lower end of the fixing part is fixed on the aircraft; the lower end of the connecting shaft is fixed on the rotor, and the upper end of the connecting shaft penetrates through the mounting hole and is fixed with the connecting part through a nut.
5. The high-speed flying vertical take-off and landing unmanned aerial vehicle of claim 1, wherein: the brushless motor is characterized by further comprising an installation part, the brushless motor is arranged in the installation part, the installation part is arranged in the motor groove, a rotor of the brushless motor is fixedly connected with the inner wall of the installation part, and the installation part is fixed with the connection part through a connection shaft and an installation hole.
6. The VTOL high-speed flying unmanned aerial vehicle of claim 5, wherein: threaded holes are formed in the upper portion of the mounting portion, threads are arranged below the connecting shaft, and the mounting hole is penetrated below the connecting shaft and is in threaded connection with the threaded holes.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021553982.4U CN213057502U (en) | 2020-07-31 | 2020-07-31 | High-speed flight unmanned vehicles that VTOL |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021553982.4U CN213057502U (en) | 2020-07-31 | 2020-07-31 | High-speed flight unmanned vehicles that VTOL |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN213057502U true CN213057502U (en) | 2021-04-27 |
Family
ID=75578757
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202021553982.4U Active CN213057502U (en) | 2020-07-31 | 2020-07-31 | High-speed flight unmanned vehicles that VTOL |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN213057502U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2024088114A1 (en) * | 2022-10-26 | 2024-05-02 | 亿航智能设备（广州）有限公司 | Power plant with variable thrust direction, and aircraft |
-
2020
- 2020-07-31 CN CN202021553982.4U patent/CN213057502U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2024088114A1 (en) * | 2022-10-26 | 2024-05-02 | 亿航智能设备（广州）有限公司 | Power plant with variable thrust direction, and aircraft |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN205916329U (en) | Coaxial double -oar unmanned vehicles | |
| AU2020101802A4 (en) | Air-jet steering drone | |
| CN213057502U (en) | High-speed flight unmanned vehicles that VTOL | |
| CN109455295B (en) | Rotor control device and rotor craft | |
| CN108116672A (en) | A kind of DCB Specimen Electrostatic Absorption unmanned plane | |
| CN112644701A (en) | Transverse double-rotor unmanned aerial vehicle | |
| CN112158330A (en) | Unmanned aerial vehicle | |
| CN113148136B (en) | Unmanned aerial vehicle with fixed wing and many rotors switch function | |
| CN107031835B (en) | Rotor unmanned aerial vehicle becomes oar radius variable pitch device | |
| CN107161330A (en) | A kind of variable abnormally-structured displacement multi-rotor unmanned aerial vehicle | |
| CN212921968U (en) | Unmanned vehicles fan duct structure of adjustable spout | |
| CN109367773B (en) | Tilting mechanism with control surface | |
| CN112046745A (en) | Portable modularization unmanned aerial vehicle platform | |
| CN209757550U (en) | Motor with outer rotor, outer circle provided with rotor wing seat, inner stator and center provided with spherical ring | |
| CN212709964U (en) | But VTOL aircraft based on rotor and fan wing | |
| CN212890915U (en) | Unmanned plane | |
| CN115367106A (en) | Tilt rotor unmanned aerial vehicle | |
| CN210526851U (en) | Variable-pitch drive assembly for an aircraft | |
| CN211844880U (en) | Aircraft and flight system | |
| CN210162251U (en) | Multidirectional four rotor crafts of formula of landing | |
| CN114030610A (en) | Flapping wing micro aircraft based on motor antisymmetric layout driving | |
| CN111332463A (en) | Counter-rotating vertical take-off and landing unmanned aerial vehicle | |
| CN112340003A (en) | Unmanned plane | |
| CN206466172U (en) | A kind of tandem type derotation wing power set | |
| CN211391664U (en) | Variable-pitch and fixed-pitch mixed lift device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |