CN204264452U - Electric single-rotor ducted unmanned aerial vehicle - Google Patents

Abstract

Electronic single rotor duct formula unmanned vehicles, it relates to unmanned vehicles technical field. The utility model discloses a solve current single rotor duct formula unmanned vehicles because of the noise that adopts the internal-combustion engine to lead to as power is big, energy resource consumption is big, volume and weight are big and then lead to inconvenient transportation and the problem of carrying. The utility model discloses an electronic single rotor duct formula unmanned vehicles is provided with the link on the outer wall of duct, and the piggyback pod is installed respectively on the link, and the electric cabin is installed to the frame upper end, and the central frame sets up the central point at the duct, installs between duct inner wall and the central frame and ends the fixed rudder face of revolving, and the central frame upper end is installed power device, and the oar is pulled in to the power device upper end connection, and the control cabin is installed to central frame lower extreme, and two sets of air current spout rudders are equipped with to the outside below of duct. The utility model relates to a rationally, simple structure, mobility and adaptability are stronger, energy-concerving and environment-protective, operation and maintenance are more convenient.

Description

Electric single-rotor ducted unmanned aerial vehicle

technical field

The utility model relates to an unmanned aerial vehicle, in particular to an electric single-rotor ducted unmanned aerial vehicle, which belongs to the technical field of unmanned aerial vehicles.

Background technique

At present, it is known that modern ordinary unmanned fixed-wing aircraft need a higher speed for take-off and landing to make the wings generate enough lift, causing about 50% of flight accidents to occur during take-off and landing, and parking on the ground takes up a lot of space. Most of the modern common rotor unmanned aerial vehicles adopt the structure of single rotor with tail rotor and coaxial double rotor of helicopter. The high-speed rotating blade is a fatal threat to the operator. The high-speed rotating blades are also easy to bump into objects and cause flight accidents. The single-rotor ducted unmanned aerial vehicles can solve the above problems well, but the existing single-rotor ducted unmanned aerial vehicles generally use internal combustion engines as power devices, which have high noise, high energy consumption, and relatively high volume and weight. Large, inconvenient to carry and transport, the landing gear and the aircraft are mostly integrated, and the control cabin is relatively closed, which brings a lot of inconvenience to the inspection and maintenance of the line.

Contents of the invention

The utility model aims to solve the problems that the existing single-rotor ducted unmanned aerial vehicle uses an internal combustion engine as a power source to cause large noise, large energy consumption, large volume and weight, and thus inconvenient transportation and portability, and further provides a Electric single-rotor ducted unmanned aerial vehicle with simple structure, small size, and more convenient operation and maintenance.

The technical scheme that the utility model takes for solving the problems of the technologies described above is:

The electric single-rotor ducted unmanned aerial vehicle of the present utility model comprises a landing gear, a connecting frame, a duct, a power cabin and a frame. The tripod, the upper ends of the four tripods are respectively connected with the four connecting frames, and the two power cabins are respectively installed on one of the pair of connecting frames. The upper end of the frame is connected with the electrical cabin, the electrical cabin is connected with the motor, the autopilot and avionics equipment are installed in the electrical cabin, and the central rack, power unit, pull-in propeller, control cabin, electrical equipment are also arranged inside the duct. The anti-rotation fixed rudder surface is reconciled, and the center frame is set at the center of the duct. The anti-rotation fixed rudder surface is evenly distributed between the inner wall of the duct and the center frame, and the power device is installed on the upper end of the center frame. The device is located on the central axis of the duct, and the power unit is connected to the motor. The upper end of the power unit is connected to the paddle through the paddle shaft, and the paddle is placed in the upper part of the duct. Cabin, control steering gear is installed in the control cabin, and electric adjustment is installed at the lower end of the control cabin. The electric single-rotor ducted unmanned aerial vehicle also includes airflow nozzle rudder and GPS antenna. Two groups of airflow nozzle rudders, one end of the rotating shaft of the airflow nozzle rudder is connected with the control steering gear, the other end of the rotating shaft is fixed on the connecting frame, and the GPS antenna is fixed on the outside of the duct.

The electric single-rotor ducted unmanned aerial vehicle of the above scheme has the structural characteristics that two power compartments with motors are arranged outside the duct, an electrical compartment is arranged on the upper part of the duct, and the autopilot and avionics equipment are arranged on the In the electrical cabin, the electrical cabin is far away from the motor, which effectively reduces electromagnetic interference. The landing gear is designed separately, and the control cabin adopts a hollow design. The whole machine has a reasonable design, simple structure, small size, easy to carry, low noise, and more convenient maintenance.

Further design of the scheme: In order to provide a full range of avionics equipment, the avionics equipment includes: expander, digital transmission station, image transmission transmitter, power supply module, remote control receiver, high-definition synchronous camera.

Further design of the scheme: In order to ensure the normal communication between the digital radio station and the image transmission transmitter, a radio antenna is installed on the upper part of the digital transmission station, and an image transmission antenna is installed on the upper part of the image transmission transmitter.

Further design of the scheme: In order to play a role of waterproof and dustproof so as to further protect the collected video data, the high-definition synchronous camera is equipped with a protective case.

Further design of the scheme: In order to better play the role of the anti-rotation fixed rudder surface, the anti-rotation fixed rudder surface 5 is composed of 3-100 rudder surfaces.

Further design of the scheme: In order to better play the role of the airflow nozzle rudder, the airflow nozzle rudder 15 is composed of 1-100 rudder surfaces.

The beneficial effects of the utility model are: the electric single-rotor ducted unmanned aerial vehicle of the utility model has reasonable design, simple structure, smaller volume, and is easy to carry; Quick start, vertical take-off and landing, hovering, circling anywhere; with electric energy as the power source, energy saving and environmental protection, low noise; the electrical cabin is far away from the motor, and the electromagnetic interference is small; easy to disassemble and carry, and more convenient for line inspection and maintenance.

Description of drawings

Fig. 1 is the overall structural representation of the utility model;

Fig. 2 is a schematic diagram of the internal structure of the utility model;

Fig. 3 is the front view of the utility model;

Fig. 4 is a side view of the utility model;

Fig. 5 is the rear view of the utility model;

Fig. 6 is a top view of the utility model;

Fig. 7 is the bottom view of the utility model;

In the figure: 1-GPS antenna, 2-duct, 3-frame, 4-power cabin, 5-rotating fixed rudder surface, 6-connecting frame, 7-landing gear, 8-image transmission antenna, 9- Image transmission transmitter, 11-radio antenna, 12-high-definition synchronous camera, 13-pulling propeller, 14-power unit, 15-airflow nozzle rudder, 16-digital radio station, 17-control cabin, 18-electric adjustment, 19 -motor, 20-power supply module, 21-extender, 22-electric compartment, 23-autopilot, 24-remote control receiver, 25-propeller shaft, 26-control steering gear, 27-central frame.

Detailed ways

Specific embodiments: for illustration in conjunction with Figures 1-7, the electric single-rotor ducted unmanned aerial vehicle of the present invention includes a landing gear 7, a connecting frame 6, a duct 2, a power cabin 4 and a frame 3, and the duct Two pairs of connecting frames 6 are arranged symmetrically on the outer wall of 2, and the undercarriage 7 includes four separate legs. On the connecting frame 6, a motor 19 is housed inside the power cabin 4, a frame 3 is installed on the top of the duct 2, the frame 3 is connected to the connecting frame 6, an electrical cabin 22 is installed on the upper end of the frame 3, and the electrical cabin 22 is connected to the motor 19 , the electric cabin 22 is equipped with an autopilot 23 and avionics equipment, and the inside of the duct 2 is also provided with a central frame 27, a power unit 14, a pull-in paddle 13, a control cabin 17, an electric adjustment 18 and a fixed rudder surface 5 , the center frame 27 is arranged at the central part of the duct 2, the anti-rotation fixed rudder surface 5 evenly distributed in the circumferential direction is installed between the inner wall of the duct 2 and the center frame 27, and the power unit 14 is installed on the upper end of the center frame 27, The power unit 14 is on the central axis of the duct 2, the power unit 14 is connected to the motor 19, the upper end of the power unit 14 is connected to the pull-in paddle 13 through the paddle shaft 25, and the pull-in paddle 13 is placed in the upper part of the duct 2, and the lower end of the center frame 27 A control cabin 17 is installed, and the cabin body of the control cabin 17 is a hollow cabin body. The control steering gear 26 is installed in the control cabin 17, and the electric adjustment 18 is installed at the lower end of the control cabin 17. The electric single-rotor ducted unmanned aerial vehicle also includes air flow. Nozzle rudder 15 and GPS antenna 1, two groups of airflow nozzle rudders 15 are installed symmetrically in the horizontal and vertical directions below the outside of duct 2, and one end of the rotating shaft of airflow nozzle rudder 15 is connected with the control steering gear 26, and the other end of the rotating shaft is fixed on the connecting frame 6, the GPS antenna 1 is fixed outside the duct 2. The motor 19 in the power cabin 4 is connected with the electrical cabin 22 and the power plant 14, provides power for the electrical cabin 22 and the power plant 14, and the autopilot 24 and various avionics equipment in the electrical cabin work through the power provided by the motor 19 , the power of the power unit 14 drives the pull-in paddle 13 to rotate, which provides power for the flight of the aircraft. The equipment in the control cabin 17 and the airflow nozzle rudder are used to control the flight action of the aircraft. The anti-rotation fixed rudder surface 5 provides reaction force to make the aircraft more stable. , the GPS antenna 1 can locate the aircraft.

This embodiment is only an exemplary description of this patent, and does not limit its protection scope. Those skilled in the art can also make partial changes to it, as long as it does not exceed the spirit and essence of this patent, all within the protection scope of this patent.

Claims (6)

1. Electric single-rotor ducted unmanned aerial vehicle, including landing gear (7), connecting frame (6), duct (2), power cabin (4) and frame (3), outer wall of duct (2) There are two pairs of connecting frames (6) symmetrically arranged on the upper part, and the feature is that: the landing gear (7) includes four separate legs, the upper ends of the four legs are respectively connected with the four connecting frames (6), and the two power cabins (4) are respectively installed on one of the pair of connecting frames (6), the motor (19) is installed inside the power compartment (4), the upper part of the duct (2) is installed with a frame (3), the frame (3) and the connection frame (6), the upper end of the frame (3) is equipped with an electrical cabin (22), the electrical cabin (22) is connected to the motor (19), and the electrical cabin (22) is equipped with an autopilot (23) and avionics equipment. The inside of the duct (2) is also provided with a central frame (27), a power unit (14), a pull-in paddle (13), a control cabin (17), an electric regulator (18) and an anti-rotation fixed rudder surface (5), The center frame (27) is set at the central part of the duct (2), and the anti-rotation fixed rudder surface (5) evenly distributed in the circumferential direction is installed between the inner wall of the duct (2) and the center frame (27). The power device (14) is installed on the upper end of the frame (27), and the power device (14) is on the central axis of the duct (2). 25) Connect the pull-in paddle (13), the pull-in paddle (13) is placed in the upper part of the duct (2), and the control cabin (17) is installed at the lower end of the central frame (27). The cabin of the control cabin (17) is The hollow cabin body is equipped with a control steering gear (26) in the control cabin (17), and an electric regulator (18) is installed at the lower end of the control cabin (17). The electric single-rotor ducted unmanned aerial vehicle also includes a flow nozzle rudder (15) With GPS antenna (1), two groups of airflow nozzle rudders (15) are equipped with respectively symmetrically horizontally and longitudinally below the outside of the duct (2), and one end of the rotating shaft of the airflow nozzle rudder (15) links to each other with the control steering gear (26). The other end is fixed on the connecting frame (6), and the GPS antenna (1) is fixed on the outside of the duct (2). 2. The electric single-rotor ducted unmanned aerial vehicle according to claim 1, characterized in that: said avionics equipment includes: expander (21), digital transmission station (16), image transmission transmitter (9) , a power supply module (20), a remote control receiver (24), and a high-definition synchronous camera (12). 3. The electric single-rotor ducted unmanned aerial vehicle according to claim 2, characterized in that: the top of the digital transmission station (16) is equipped with a radio antenna (11), and the top of the picture transmission transmitter (9) An image transmission transmitting antenna (8) is installed. 4. The electric single-rotor ducted unmanned aerial vehicle according to claim 2, characterized in that: the high-definition synchronous camera (12) is equipped with a protective case. 5. The electric single-rotor ducted unmanned aerial vehicle according to claim 1, characterized in that: the anti-rotation fixed rudder surface (5) is composed of 3-100 rudder surfaces. 6. The electric single-rotor ducted unmanned aerial vehicle according to claim 1, 2, 3, 4 or 5, characterized in that: the airflow nozzle rudder (15) is composed of 1-100 rudder surfaces.