CN108216616B

CN108216616B - High-efficient unmanned aerial vehicle automatically regulated rotor structure

Info

Publication number: CN108216616B
Application number: CN201810062080.1A
Authority: CN
Inventors: 刘云朋; 王春霞; 张艳; 司国斌; 靳孝峰
Original assignee: Jiaozuo university
Current assignee: Wuhan Youtu Youmu Technology Co.,Ltd.
Priority date: 2018-01-23
Filing date: 2018-01-23
Publication date: 2021-03-30
Anticipated expiration: 2038-01-23
Also published as: CN108216616A

Abstract

The invention relates to a high-efficiency unmanned aerial vehicle automatically adjusting rotor structure, comprising a bearing base, a rotor, a driving mechanism, a turntable mechanism, an air duct and a control circuit. Slot, the end of the bearing base is hinged with the fuselage of the drone through the turntable structure, the air duct is embedded in the positioning groove, the rotor and the driving mechanism are embedded in the air duct, the driving mechanism is connected with the air duct through the positioning frame, and the control circuit is embedded. in the bearing base, and are respectively electrically connected with the drive mechanism and the turntable mechanism. The device of the invention is simple in structure, flexible and convenient to use, and has a high degree of operation automation, integration and modularization, which is helpful to improve the convenience and reliability of the assembly, disassembly and replacement of parts and components of the UAV equipment and improve the equipment of the UAV. The carrying capacity of operations and the purpose of flight control stability, flexibility and reliability.

Description

High-efficient unmanned aerial vehicle automatically regulated rotor structure

Technical Field

The invention relates to an automatic adjusting rotor wing structure of a high-efficiency unmanned aerial vehicle, and belongs to the technical field of unmanned aerial vehicles.

Background

At present, rotor type unmanned aerial vehicle is one of the main forms in current unmanned aerial vehicle structure, the use amount is huge, but discover in the in-service use, current rotor type unmanned aerial vehicle's rotor mechanism often all with unmanned aerial vehicle organism formula structure as an organic whole, although can satisfy the needs of using, but lead to current rotor type unmanned aerial vehicle in service to have rotor mechanism installation, dismantle and change the operation flexibility poor, the flexibility of rotor type unmanned aerial vehicle equipment operation use has seriously been influenced, also cause current rotor type unmanned aerial vehicle equipment in service simultaneously, rotor equipment in service produced drive power size, direction control and regulation flexibility are relatively poor and the control range is narrow, on the one hand, unmanned aerial vehicle rotor power performance and operating efficiency are relatively poor seriously influenced, and cause the operation energy consumption to increase, on the other hand also leads to current unmanned aerial vehicle equipment operation flexibility, the utility model discloses a, Reliability and flight stability homogeneous phase are relatively poor, to this problem, the urgent need develops a brand-new unmanned aerial vehicle rotor structure to satisfy the needs of in-service use.

Disclosure of Invention

The invention aims to overcome the defects and provide the automatic adjusting rotor wing structure of the high-efficiency unmanned aerial vehicle.

In order to realize the purpose, the invention is realized by the following technical scheme:

an automatic adjusting rotor wing structure of a high-efficiency unmanned aerial vehicle comprises a bearing base, rotor wings, a driving mechanism, a rotary table mechanism, an air pipe and a control circuit, wherein the bearing base is of a rectangular plate-shaped structure, at least one positioning groove is formed in the bearing base, the positioning grooves are uniformly distributed along the axial direction of the bearing base, the axial line of each positioning groove is perpendicular to and intersected with the axial line of the bearing base, the tail end of the bearing base is hinged with a body of the unmanned aerial vehicle through the rotary table structure, the axial line of the bearing base is intersected with the axial line of the body of the unmanned aerial vehicle and forms an included angle of 0-180 degrees, the air pipe is embedded in the positioning grooves and is hinged with the side walls of the positioning grooves through at least two rotary table mechanisms, the axial line of the air pipe and the lower surface of the bearing base form an included angle of 30-90 degrees, the driving mechanism is connected with the air pipe through the positioning frame, and the control circuit is embedded in the bearing base and is respectively electrically connected with the driving mechanism and the rotary table mechanism.

Furthermore, the cross section of the bearing base is in any one of a shuttle-shaped structure and a water drop-shaped structure.

Further, bear the base and be airtight cavity structures, including bearing fossil fragments, protective housing and inside lining wall, the fossil fragments that bear be frame construction, the protective housing cladding at bear the fossil fragments surface, the inside lining wall cladding at bearing the fossil fragments internal surface, protective housing and inside lining wall between constitute inclosed cushion chamber, the inside lining wall constitute airtight structure's the chamber that bears.

Furthermore, the cushion chamber in establish the elasticity bed course, the bearing chamber in establish at least one booster pump, booster pump one end move the air duct and be connected with the tuber pipe lateral wall, the booster pump other end through at least one air duct with bear the weight of base upper surface intercommunication, just bear a plurality of thru holes of base upper surface equipartition, each thru hole all communicates with each other with the air duct.

Further, the tuber pipe include that the body bears body, guide plate and nozzle, wherein the body that bears be hollow tubular structure, bear body up end and lower terminal surface department and all establish a plurality of guide plates, the guide plate pass through rotary table mechanism and bear the internal surface of body articulated, just guide plate and bear the body axis and be 0-90 contained angle, and the interval is 1/6-1/3 for bearing the body diameter between two adjacent guide plates, the nozzle at least two, inlay in bearing the body lateral wall, and each nozzle encircles and bears the body axis equipartition to be 0-90 contained angle with bearing the body axis, the nozzle between each other parallel and through control valve and air duct intercommunication.

Furthermore, the cross section of the bearing pipe body is any one of a rectangular structure and an isosceles trapezoid structure.

Further, the driving mechanism is any one of an electric motor and an internal combustion engine.

Furthermore, the turntable mechanism is a three-dimensional turntable, and the turntable mechanism is provided with an angle sensor which is electrically connected with the control circuit.

Further, control circuit include data processing module, data communication module, data bus module, data communication terminal, wireless data communication antenna and drive module, data bus module respectively with data processing module, data communication module and drive module electrical connection, data communication module and data communication terminal, wireless data communication antenna electrical connection to through data communication terminal, wireless data communication antenna and unmanned aerial vehicle operating system electrical connection, drive module respectively with actuating mechanism, revolving stage mechanism electrical connection.

The unmanned aerial vehicle rotor wing system is simple in structure, flexible and convenient to use, high in operation automation degree, integration degree and modularization degree, capable of effectively improving the installation and positioning flexibility of the unmanned aerial vehicle rotor wing and the strength of a bearing structure and facilitating improvement of convenience and reliability of assembly, disassembly and part replacement of the unmanned aerial vehicle, and capable of effectively improving the power performance of the unmanned aerial vehicle rotor wing system and the flexibility and reliability of driving power regulation control, so that the purposes of improving the bearing capacity and flight control stability, flexibility and reliability of unmanned aerial vehicle equipment operation are achieved.

Drawings

FIG. 1 is a schematic structural view of the present invention;

fig. 2 is a schematic diagram of a control circuit structure.

Detailed Description

As shown in fig. 1 and 2, an efficient automatic adjusting rotor structure of an unmanned aerial vehicle comprises a bearing base 1, a rotor 2, a driving mechanism 3, a turntable mechanism 4, an air pipe 5 and a control circuit 6, wherein the bearing base 1 is a rectangular plate-shaped structure, the bearing base 1 is provided with at least one positioning groove 7, the positioning grooves 7 are uniformly distributed along the axis direction of the bearing base 1, the axes of the positioning grooves 7 are perpendicular to and intersected with the axis of the bearing base 1, the tail end of the bearing base 1 is hinged with an unmanned aerial vehicle body 8 through the turntable structure 4, the axis of the bearing base 1 is intersected with the axis of the unmanned aerial vehicle body 8 and forms an included angle of 0-180 degrees, the air pipe 5 is embedded in the positioning groove 7 and is hinged with the side wall of the positioning groove 7 through at least two turntable mechanisms 4, the axis of the air pipe 5 and the lower surface of the bearing base 1 form an included angle of 30-90 degrees, the rotor 2 and the driving mechanism 3 are both embedded in, rotor 2, actuating mechanism 3 all distribute with tuber pipe 5 is coaxial, and actuating mechanism 3 passes through locating rack 10 and tuber pipe 5 interconnect, and control circuit 6 inlays in bearing base 1 to respectively with actuating mechanism 3, 4 electrical connection of revolving stage mechanism.

In this embodiment, the cross section of the supporting base 1 is any one of a shuttle structure and a water drop structure.

In this embodiment, the bearing base 1 is a closed cavity structure, and includes a bearing keel 101, a protective shell 102 and a lining wall 103, the bearing keel 101 is a frame structure, the protective shell 102 is coated on the outer surface of the bearing keel 101, the lining wall 103 is coated on the inner surface of the bearing keel 101, a closed buffer cavity 104 is formed between the protective shell 102 and the lining wall 103, and the lining wall 103 forms a bearing cavity 105 of the closed structure.

In this embodiment, the cushion chamber 104 is internally provided with an elastic cushion layer 11, the bearing chamber 105 is internally provided with at least one booster pump 12, one end of the booster pump 12 is connected with the side wall of the air duct 5 through an air duct 13, the other end of the booster pump 12 is communicated with the upper surface of the bearing base 1 through at least one air duct 13, the upper surface of the bearing base 1 is uniformly provided with a plurality of through holes 14, and each through hole 14 is communicated with the air duct 13.

In this embodiment, the air duct 5 includes a duct body 51, a plurality of flow deflectors 52 and nozzles 53, wherein the duct body 51 is a hollow tubular structure, the upper end surface and the lower end surface of the duct body 51 are provided with the plurality of flow deflectors 52, the flow deflectors 52 are hinged to the inner surface of the duct body 51 through the turntable mechanism 4, the flow deflectors 52 and the axis of the duct body 51 form an included angle of 0 ° to 90 °, the distance between two adjacent flow deflectors 52 is 1/6 to 1/3 of the diameter of the duct body 51, at least two nozzles 53 are embedded in the side wall of the duct body 51, the nozzle rings 53 are uniformly distributed around the axis of the duct body 51 and form an included angle of 0 ° to 90 ° with the axis of the duct body 51, and the nozzles 53 are mutually connected in parallel and are communicated with the air duct 13 through the control valve 15.

In this embodiment, the cross section of the bearing pipe 51 is any one of a rectangular structure and an isosceles trapezoid structure.

In the present embodiment, the drive mechanism 3 is either an electric motor or an internal combustion engine.

In this embodiment, the turntable mechanism 4 is a three-dimensional turntable, and the angle sensor 15 is arranged on the turntable mechanism 4, and the angle sensor 15 is electrically connected with the control circuit 6.

In this embodiment, the control circuit 6 includes a data processing module, a data communication module, a data bus module, a data communication terminal 61, a wireless data communication antenna 62 and a driving module, the data bus module is electrically connected with the data processing module, the data communication module and the driving module respectively, the data communication module is electrically connected with the data communication terminal 61 and the wireless data communication antenna 62 and is electrically connected with the unmanned aerial vehicle operation system through the data communication terminal 61 and the wireless data communication antenna 62, and the driving module is electrically connected with the driving mechanism 3 and the turntable mechanism 4 respectively.

The foregoing shows and describes the general principles and broad features of the present invention and advantages thereof. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are described in the specification and illustrated only to illustrate the principle of the present invention, but that various changes and modifications may be made therein without departing from the spirit and scope of the present invention, which fall within the scope of the invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.

Claims

1. a high-efficiency unmanned aerial vehicle automatically adjusts the rotor structure, it is characterized in that, the described high-efficiency unmanned aerial vehicle automatically adjusts the rotor structure and comprises a bearing base, a rotor, a drive mechanism, a turntable mechanism, an air duct and a control circuit, and the described The bearing base is a rectangular plate-like structure, and at least one positioning groove is arranged on the bearing base, the positioning grooves are evenly distributed along the axis direction of the bearing base, and the axis of the positioning groove is perpendicular to the axis of the bearing base and Intersection, the end of the bearing base is hinged with the fuselage of the drone through the turntable structure, and the axis of the bearing base and the axis of the fuselage of the drone intersect and form an included angle of 0°-180°. The air duct is embedded in the positioning groove, and is hinged with the side wall of the positioning groove through at least two turntable mechanisms, and the axis of the air duct and the lower surface of the bearing base form an included angle of 30°-90°. The driving mechanism is embedded in the air duct, wherein the rotor is located directly above the driving mechanism and is connected with the driving mechanism through the transmission shaft. The rotor and the driving mechanism are distributed coaxially with the air duct, and the driving mechanism is positioned The frame and the air duct are connected to each other, and the control circuit is embedded in the bearing base and electrically connected to the drive mechanism and the turntable mechanism respectively.

2 . The high-efficiency UAV automatic adjusting rotor structure according to claim 1 , wherein the cross-section of the bearing base is any one of a shuttle-shaped structure and a water-drop-shaped structure. 3 .

3. A kind of high-efficiency unmanned aerial vehicle automatic adjustment rotor structure according to claim 1, it is characterized in that: described bearing base is a closed cavity structure, including bearing keel, protective shell and inner lining wall, described The bearing keel is a frame structure, the protective shell is wrapped on the outer surface of the bearing keel, the inner lining wall is wrapped on the inner surface of the bearing keel, and a closed buffer cavity is formed between the protective shell and the inner lining wall. The inner lining wall constitutes a bearing cavity of the closed cavity structure.

4. A high-efficiency unmanned aerial vehicle automatic adjustment rotor structure according to claim 3, characterized in that: an elastic cushion layer is arranged in the buffer cavity, at least one booster pump is arranged in the bearing cavity, and the One end of the booster pump is connected to the side wall of the air duct through an air duct, and the other end of the booster pump is communicated with the upper surface of the bearing base through at least one air duct, and the upper surface of the bearing base is evenly distributed with a number of through holes , and each through hole communicates with the air duct.

5. The high-efficiency unmanned aerial vehicle automatic adjustment rotor structure according to claim 1, wherein the air duct comprises a bearing pipe body, a deflector and a nozzle, wherein the bearing pipe body is a hollow tubular body Structure, the upper end face and the lower end face of the bearing pipe body are provided with several baffle plates, the baffle plates are hinged with the inner surface of the bearing pipe through the turntable mechanism, and the baffle plate and the axis of the bearing pipe body are at 0°— The included angle is 90°, and the distance between two adjacent baffles is 1/6-1/3 of the diameter of the bearing pipe body. At least two nozzles are embedded in the side wall of the bearing pipe body, and each nozzle surrounds The axis of the bearing pipe body is evenly distributed and forms an angle of 0°-90° with the axis of the bearing pipe body.

6 . The high-efficiency UAV automatic adjusting rotor structure according to claim 5 , wherein the cross-section of the bearing tube body is any one of a rectangular structure and an isosceles trapezoid structure. 7 .

7 . The high-efficiency UAV automatic adjusting rotor structure according to claim 1 , wherein the drive mechanism is any one of an electric motor and an internal combustion engine. 8 .

8. The high-efficiency UAV automatic adjustment rotor structure according to claim 1, wherein the turntable mechanism is a three-dimensional turntable, and the turntable mechanism is provided with an angle sensor, and the angle sensor and the control circuit electrical connections.

9. The high-efficiency UAV automatic adjustment rotor structure according to claim 1, wherein the control circuit comprises a data processing module, a data communication module, a data bus module, a data communication terminal, and a wireless data communication antenna and a drive module, the data bus module is electrically connected with the data processing module, the data communication module and the drive module respectively, the data communication module is electrically connected with the data communication terminal and the wireless data communication antenna, and is connected through the data communication terminal, wireless The data communication antenna is electrically connected with the UAV operation system, and the drive module is electrically connected with the drive mechanism and the turntable mechanism respectively.