阅读说明：本技术 一种共轴双桨八旋翼大载重无人机 (Big load unmanned aerial vehicle of eight rotors of coaxial double-oar ) 是由 高建琦 齐如海 娄英杰 周渤 汪文海 刘福有 于 2020-04-01 设计创作，主要内容包括：本发明公开了一种共轴双桨八旋翼大载重无人机,包括：无人机机臂,所述无人机机臂与无人机中心盘通过机臂折叠结构套件与无人机中心盘进行螺纹旋紧连接,所述无人机机臂通过鸭嘴扣进行锁紧于机臂卡位机构内部,Ⅰ号电调和Ⅱ号电调,所述Ⅰ号电调和Ⅱ号电调通过电机安装座固定于无人机机臂上,所述Ⅰ号电调和Ⅱ号电调的外部均设有电调保护壳,所述电调保护壳通过螺丝固定在电机安装座上。双电机和旋翼在单个机臂上的安装,减小了无人机整体尺寸；无人机机臂与无人机中心盘之间通过折叠机构连接,无人机实现了快速收纳和展开；无人机中心盘顶盖上方安装有降落伞舱可以在无人机出现故障坠落时快速弹出,帮助无人机实现安全降落。(The invention discloses a coaxial double-oar eight-rotor heavy load unmanned aerial vehicle, which comprises: unmanned aerial vehicle horn, unmanned aerial vehicle horn and unmanned aerial vehicle center disc pass through horn beta structure external member and carry out the screw thread with the unmanned aerial vehicle center disc and are screwed and be connected, the unmanned aerial vehicle horn is detained through the duckbilled and is locked inside horn screens mechanism, and No. I electricity is transferred and No. II electricity is transferred, No. I electricity is transferred and No. II electricity is transferred and is fixed in on the unmanned aerial vehicle horn through the motor mount pad, No. I electricity is transferred and the outside of No. II electricity is transferred all is equipped with electricity and is transferred the protective housing, electricity is transferred the protective housing and is passed through the screw fixation. The double motors and the rotor wing are arranged on a single horn, so that the overall size of the unmanned aerial vehicle is reduced; the unmanned aerial vehicle arm is connected with the unmanned aerial vehicle central disc through the folding mechanism, so that the unmanned aerial vehicle can be rapidly stored and unfolded; the parachute cabin is installed above the top cover of the central disc of the unmanned aerial vehicle, so that the unmanned aerial vehicle can be popped out quickly when the unmanned aerial vehicle breaks down and falls, and the unmanned aerial vehicle is helped to safely land.)

1. The utility model provides a big load unmanned aerial vehicle of eight rotors of coaxial double-oar which characterized in that includes:

the unmanned aerial vehicle arm (3), the unmanned aerial vehicle arm (3) and the unmanned aerial vehicle central disc (1) are in threaded screwing connection with the unmanned aerial vehicle central disc (1) through an arm folding structure suite (2), and the unmanned aerial vehicle arm (3) is locked inside an arm clamping mechanism (4) through a duckbilled buckle;

the real-time control link antenna (5), the real-time control link antenna (5) is connected with the unmanned aerial vehicle central disc (1) through a real-time control link antenna bracket (6);

the remote control and remote measurement data link antenna (7), the remote control and remote measurement data link antenna (7) is connected with the unmanned aerial vehicle central disc (1) through a remote control and remote measurement data link antenna bracket (8);

the RTK positioning antenna (9), wherein the RTK positioning antenna (9) is connected with the unmanned aerial vehicle central disc (1) through an RTK positioning antenna folding support (10);

the unmanned aerial vehicle center plate top cover (11), the unmanned aerial vehicle center plate top cover (11) is connected with the unmanned aerial vehicle center plate (1) through a hinge;

the unmanned aerial vehicle parachute bay cover (12), the unmanned aerial vehicle parachute bay cover (12) and the unmanned aerial vehicle center plate top cover (11) are fixed through gluing;

the unmanned aerial vehicle is characterized in that a No. I electric controller (15) and a No. II electric controller (16) are electrically controlled, the No. I electric controller (15) and the No. II electric controller (16) are fixed on an unmanned aerial vehicle arm (3) through a motor mounting seat (17), electric control protective cases (18) are arranged outside the No. I electric controller (15) and the No. II electric controller (16), and the electric control protective cases (18) are fixed on the motor mounting seat (17) through screws;

a rotor blade (14), the rotor blade (14) being connected to the motor by screws.

2. A coaxial twin-oar eight rotor heavy load drone according to claim 1, characterised in that: unmanned aerial vehicle horn (3) and horn screens mechanism (4) all set up to the aluminum product structure.

3. A coaxial twin-oar eight rotor heavy load drone according to claim 1, characterised in that: unmanned aerial vehicle center disk (1), unmanned aerial vehicle center disk top cap (11), unmanned aerial vehicle parachute bay lid (12) and unmanned aerial vehicle center disk foot rest (13) all set up to carbon fiber structure.

4. A coaxial twin-oar eight rotor heavy load drone according to claim 1, characterised in that: the bottom and the tail of the unmanned aerial vehicle central disc (1) are both pre-embedded with screws.

5. A coaxial twin-oar eight rotor heavy load drone according to claim 1, characterised in that: the motor mounting seat (17) is horizontally mounted on a motor mounting surface.

6. A coaxial twin-oar eight rotor heavy load drone according to claim 1, characterised in that: the edge of the electric tuning protection shell (18) is provided with a limiting hole and a limiting block.

7. A coaxial twin-oar eight rotor heavy load drone according to claim 1, characterised in that: the unmanned aerial vehicle horn (3) and the horn screens mechanism set up on same horizontal plane.

8. A coaxial twin-oar eight rotor heavy load drone according to claim 1, characterised in that: the bottom of unmanned aerial vehicle center disk (1) is through goat's horn nut fixedly connected with unmanned aerial vehicle center disk foot rest (13).

Technical Field

The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to a coaxial double-propeller eight-rotor heavy-load unmanned aerial vehicle.

Background

An unmanned aircraft, referred to as "drone", is an unmanned aircraft that is operated by a radio remote control device and a self-contained program control device, or is operated autonomously, either completely or intermittently, by an onboard computer.

The multi-option wing unmanned aerial vehicle has the characteristic of flexible take-off and landing, and the number of blades or the size of the unmanned aerial vehicle blades must be increased in order to increase the load weight of the multi-option wing unmanned aerial vehicle, so that the overall size of the unmanned aerial vehicle is very large. In order to solve the problem that the whole size of a large-load unmanned aerial vehicle is large, a large-load multi-option-wing unmanned aerial vehicle with coaxial double propellers is provided.

Disclosure of Invention

The invention aims to provide a coaxial double-propeller eight-rotor heavy-load unmanned aerial vehicle, which aims to solve the problem that the whole size of the unmanned aerial vehicle in the prior art is larger.

In order to achieve the purpose, the invention adopts the following technical scheme:

a big load unmanned aerial vehicle of eight rotors of coaxial double-oar includes:

the unmanned aerial vehicle arm and the unmanned aerial vehicle central disc are in threaded screwing connection through an arm folding structure suite, and the unmanned aerial vehicle arm is locked inside the arm clamping mechanism through a duckbilled buckle;

the real-time control link antenna is connected with the unmanned aerial vehicle central disk through a real-time control link antenna support;

the remote control and remote measurement data link antenna is connected with the unmanned aerial vehicle central disc through a remote control and remote measurement data link antenna bracket;

the RTK positioning antenna is connected with the central disk of the unmanned aerial vehicle through an RTK positioning antenna folding support;

the unmanned aerial vehicle center plate top cover is connected with the unmanned aerial vehicle center plate through a hinge;

the unmanned aerial vehicle parachute bay cover is fixed with the top cover of the unmanned aerial vehicle central disc through gluing;

the unmanned aerial vehicle is characterized by comprising a first electric speed controller and a second electric speed controller, wherein the first electric speed controller and the second electric speed controller are fixed on an unmanned aerial vehicle arm through a motor mounting seat;

the rotor blade, the rotor blade passes through the screw and connects on the motor.

Preferably, unmanned aerial vehicle horn and horn screens mechanism all set up to the aluminum product structure.

Preferably, unmanned aerial vehicle center disk top cap, unmanned aerial vehicle parachute bay lid and unmanned aerial vehicle center disk foot rest all set up to carbon fiber structure.

Preferably, the bottom and the afterbody of unmanned aerial vehicle center panel all embed the screw in advance.

Preferably, the motor mounting seat is horizontally mounted on the motor mounting surface.

Preferably, the edge of the electric tuning protective shell is provided with a limiting hole and a limiting block.

Preferably, unmanned aerial vehicle horn and horn screens mechanism set up on same horizontal plane.

Preferably, the bottom of unmanned aerial vehicle center panel is through goat's horn nut fixedly connected with unmanned aerial vehicle center panel foot rest.

The invention has the technical effects and advantages that: compared with the prior art, the coaxial double-propeller eight-rotor heavy-load unmanned aerial vehicle provided by the invention has the following advantages:

the invention realizes the installation of double motors and rotors on a single horn, thus reducing the overall size of the unmanned aerial vehicle; the unmanned aerial vehicle arm is connected with the unmanned aerial vehicle central disc through the folding mechanism, so that the unmanned aerial vehicle can be rapidly stored and unfolded; the parachute cabin is installed above the top cover of the central disc of the unmanned aerial vehicle, so that the unmanned aerial vehicle can be popped out quickly when the unmanned aerial vehicle breaks down and falls, and the unmanned aerial vehicle is helped to safely land.

Drawings

Fig. 1 is a schematic diagram of an equiaxial structure of an unmanned aerial vehicle in an unfolded state;

fig. 2 is a schematic view of a stowed state overhead structure of the unmanned aerial vehicle of the present invention;

FIG. 3 is a first schematic structural view of a jib detent mechanism of the present invention;

FIG. 4 is a second schematic structural view of the arm positioning mechanism;

fig. 5 is a schematic diagram of an explosion structure of an unmanned aerial vehicle arm of the present invention;

FIG. 6 is a schematic view of the main structure of the unmanned aerial vehicle of the present invention;

FIG. 7 is a schematic diagram of an isometric structure of the unmanned aerial vehicle in a stowed state;

FIG. 8 is a schematic diagram of a real-time control link antenna mount configuration of the present invention;

fig. 9 is a schematic structural view of a central disk foot stand of the unmanned aerial vehicle.

In the figure: 1. an unmanned aerial vehicle central disk; 2. a horn fold configuration kit; 3. an unmanned aerial vehicle arm; 4. the machine arm clamping mechanism; 5. controlling a link antenna in real time; 6. controlling a link antenna mount in real time; 7. a remote telemetry data link antenna; 8. a remote telemetry data link antenna mount; 9. an RTK positioning antenna; 10. an RTK positioning antenna folding bracket; 11. a central disk top cover of the unmanned aerial vehicle; 12. an unmanned aerial vehicle canopy; 13. a central disk foot rest of the unmanned aerial vehicle; 14. a rotor blade; 15. electrically adjusting No. I; 16. electrically adjusting No. II; 17. a motor mounting seat; 18. electrically-adjusted protective shell.

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. The specific embodiments described herein are merely illustrative of the invention and do not delimit the invention. 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 invention provides a coaxial double-oar eight-rotor heavy load unmanned aerial vehicle as shown in figures 1-9, comprising:

the unmanned aerial vehicle comprises rotor blades 14, the rotor blades 14 are connected to a motor through screws, an unmanned aerial vehicle horn 3 is connected with an unmanned aerial vehicle center plate 1 through a horn folding structure suite 2 in a threaded screwing mode, the unmanned aerial vehicle horn 3 is locked inside a horn clamping mechanism 4 through a duckbilled buckle, the unmanned aerial vehicle horn 3 and the horn clamping mechanism 4 are both arranged to be aluminum structures, the unmanned aerial vehicle center plate 1, an unmanned aerial vehicle center plate top cover 11, an unmanned aerial vehicle canopy cover 12 and an unmanned aerial vehicle center plate foot rest 13 are all arranged to be carbon fiber structures, and the self weight of the unmanned aerial vehicle is favorably reduced;

the real-time control link antenna 5 is connected with the unmanned aerial vehicle central disc 1 through a real-time control link antenna support 6; the remote control and remote measurement data link antenna 7 is connected with the unmanned aerial vehicle central disc 1 through a remote control and remote measurement data link antenna support 8; the RTK positioning antenna 9 is connected with the unmanned aerial vehicle central disc 1 through an RTK positioning antenna folding support 10;

the unmanned aerial vehicle center plate top cover 11 is connected with the unmanned aerial vehicle center plate 1 through a hinge; the unmanned aerial vehicle parachute bay cover 12, the unmanned aerial vehicle parachute bay cover 12 and the unmanned aerial vehicle central disc top cover 11 are fixed through gluing;

no. I electric regulation 15 and No. II electric regulation 16, wherein the No. I electric regulation 15 and the No. II electric regulation 16 are fixed on an unmanned aerial vehicle horn 3 through a motor mounting seat 17, electric regulation protective cases 18 are arranged outside the No. I electric regulation 15 and the No. II electric regulation 16, the electric regulation protective cases 18 are fixed on the motor mounting seat 17 through screws, and the electric regulation protective cases 18 can protect the No. I electric regulation 15 and the No. II electric regulation 16;

screws are embedded in the bottom and the tail of the unmanned aerial vehicle center plate 1 in advance, and the unmanned aerial vehicle center plate foot rest 13 is fixedly connected with the claw nuts, so that the unmanned aerial vehicle center plate foot rest 13 is convenient to install. The motor mounting seat 17 is horizontally mounted on the motor mounting surface, which is beneficial to keeping the horizontality of the rotor blade 14. Limiting holes and limiting blocks are arranged at the shell edge of the electric tuning protective shell 18, so that the electric tuning protective shell 18 can be conveniently installed. The unmanned aerial vehicle horn 3 and the horn clamping mechanism 4 are arranged on the same horizontal plane, so that the unmanned aerial vehicle horn 3 can be clamped into the horn clamping mechanism 4 conveniently.

The working principle is as follows: the double motors and the rotor wing are arranged on a single horn, so that the overall size of the unmanned aerial vehicle is reduced; the unmanned aerial vehicle arm 3 is connected with the unmanned aerial vehicle central disc 1 through a folding mechanism, so that the unmanned aerial vehicle can be rapidly stored and unfolded; the parachute cabin is installed to unmanned aerial vehicle chassis top cap 11 top and can pop out fast when unmanned aerial vehicle breaks down and falls, and help unmanned aerial vehicle realizes safe descending.

Finally, it should be noted that: although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications may be made to the embodiments or portions thereof without departing from the spirit and scope of the invention.