A portable ducted micro single-rotor UAV

Abstract

The present invention discloses a portable ducted micro-sized single-rotor UAV, comprising a single propeller, a power transmission rod and a UAV shell, wherein a propeller power device, a first fixing plate, a small turbine, a turbine power device, a UAV built-in layer, a flight control box, a sensor, a battery, a second fixing plate, four air control surfaces and corresponding four control steering gears, an air circulation channel and an air inlet are installed inside the UAV shell; the single propeller is installed on the upper end of the power transmission rod, and the lower end of the power transmission rod is connected to the propeller power device; the propeller power device is installed on the first fixing plate; the small turbine is below the first fixing plate, and a turbine power device is installed below the small turbine; the UAV built-in layer separates the space below the small turbine and above the second fixing plate into two spaces inside and outside; the four air control surfaces are installed at the bottom of the UAV. The UAV has stronger portability, anti-interference and maneuverability and more reliable flight characteristics.

Description

Technical Field

[0001] The patented invention relates to the field of UAV design, and more particularly to a portable ducted micro single-rotor UAV. Background Art

[0002] With the rapid development of the drone industry, drones will enter the daily life, work and entertainment of ordinary consumers like cameras. In the past, quadcopter drones all had fixed arms, which were large in size and took up space. In particular, the thin and sharp blades made most people afraid when working at high speeds, and the products were not user-friendly. Currently, most cup-shaped drones use a coaxial double-propeller structure, which has the following problems: poor anti-interference and maneuverability, which cannot meet the needs of high-mobility combat, and the double-propeller structure has poor wind resistance, which cannot meet the needs of changing combat scenarios. Summary of the invention

[0003] The object of the present invention is to provide a portable ducted micro single-rotor UAV, which has better portability, better anti-interference and maneuverability, and more reliable flight characteristics.

[0004] The technical solution for achieving the purpose of the present invention is: a portable ducted micro-single-rotor UAV, comprising a single propeller, a power transmission rod and a UAV shell, wherein a propeller power device, a first fixing plate, a small turbine, a turbine power device, a UAV built-in layer, a flight control box, a sensor, a battery, a second fixing plate, four air control surfaces and corresponding four control servos, an air circulation channel and an air inlet are installed inside the UAV shell; the single propeller is located above the UAV shell and is installed on the upper end of the power transmission rod, and the lower end of the power transmission rod is connected to the propeller power device, and the propeller power device is installed on the first fixing plate; the small turbine is below the fixing plate, and a turbine power device is installed below the small turbine; the UAV built-in layer separates the space below the small turbine and above the second fixing plate into two spaces, an inner space and an outer space, wherein the outer space is an air circulation channel, and the inner space is sequentially installed with a flight control box, various sensors, batteries and four control servos, and the batteries and four control servos are installed on the second fixing plate; the four air control surfaces are installed at the bottom of the UAV and are separately controlled by four control servos.

[0005] Preferably, the first fixing plate, except for the portion used to fix the propeller power device, has a hollow structure for facilitating the circulation of airflow.

[0006] Preferably, the flight control box is internally equipped with a UAV flight controller and an autopilot.

[0007] Preferably, the drone built-in layer is installed in the middle part of the entire drone shell.

[0008] Preferably, two of the four air control surfaces are symmetrically installed on opposite sides of the inner wall of the drone shell, and the other two are symmetrically installed on the other two sides of the inner wall of the drone shell.

[0009] Preferably, the drone housing is cylindrical.

[0010] Preferably, the single propeller is detachably mounted on the upper end of the power transmission rod.

[0011] Compared with the prior art, the present invention has the following significant advantages: the present invention includes all parts of the drone body except the blades through a cylindrical drone shell, so that the single drone is more portable, anti-interference and maneuverable; because the battery is installed at the bottom of the entire body, the center of gravity of the drone is lower, which makes it easy to generate an unbalanced vector force when the air control surface at the bottom of the drone changes direction during flight. Under the action of this unbalanced vector force, it is easy to control the flight direction of the drone, so that the drone has more reliable flight characteristics. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] Figure 1 This is a structural diagram of the portable ducted micro single-rotor UAV of the present invention. DETAILED DESCRIPTION

[0013] The following will provide a complete and clear description of the technology implemented in the present invention in conjunction with the drawings in the patent of the present invention. Obviously, what is described is only a large part of the present invention, not all of it.

[0014] Reference Figure 1, a portable ducted micro-sized single-rotor UAV structural design, including a single propeller 1, a power transmission rod 2 and a UAV shell 5, wherein a propeller power device 3, a first fixing plate 4, a small turbine 6, a turbine power device 7, a UAV built-in layer 8, a flight control box 9, various sensors 10, a battery 11, a second fixing plate, four air control surfaces 12 and corresponding four control steering gears 13, an air circulation channel 14 and an air inlet 15 are installed inside the UAV shell 5; the UAV shell 5 is cylindrical, the single propeller 1 is located above the UAV shell 5, and can be detachably installed on the upper end of the power transmission rod 2, and the lower end of the power transmission rod 2 is connected to the propeller power device 3, and the propeller power device 3 is installed on the first fixing plate 4; the small turbine 6 is below the first fixing plate 4, A turbine power device 7 is installed below the small turbine 6; the built-in layer 8 of the drone is installed in the middle part of the entire drone shell 5, and the built-in layer 8 of the drone isolates the space below the small turbine 6 and above the second fixed plate into two spaces, inside and outside, wherein the external space is an air circulation channel 14, and the internal space is sequentially installed with a flight control box 9, various sensors 10, a battery 11 and four control servos 13, wherein the flight control box 9 is equipped with a drone flight controller and an autopilot, and the battery 11 and the four control servos 13 are installed on the second fixed plate; the four air control surfaces 12 are installed at the bottom of the drone, wherein two are symmetrically installed on opposite sides of the inner wall of the drone shell 5, and the other two are symmetrically installed on the other two sides of the inner wall of the drone shell 5, and are respectively controlled separately by four control servos 13.

[0015] The first fixing plate 4, except for the part used to fix the propeller power device 3, has a hollow structure in the rest part to facilitate the circulation of airflow.

[0016] When the single-rotor UAV of the present invention is in working state, the propeller power device 3 provides power for the single propeller 1, thereby generating lift (pulling force) of the UAV, and at the same time, the single propeller 1 in working state will drive the movement of the surrounding airflow, and the generated airflow will enter the cylindrical fuselage 5 of the UAV through the air inlet 15; the small turbine 6 works at the same time, and plays an auxiliary role in the airflow entering the cylindrical fuselage 5 of the UAV, which not only increases the amount of airflow entering the fuselage, but also enhances the flow intensity of the airflow inside the UAV; the four independent air control surfaces 13 located at the bottom of the UAV can be separately controlled by four control servos 12, and when one or more of the air control surfaces are deflected, the flowing airflow inside the fuselage will generate an unbalanced vector force on the UAV at the bottom of the UAV, and the UAV will deflect in a certain direction under the action of this vector force, thereby realizing the flight control of the single-rotor UAV.

Claims

1. A portable ducted micro single-rotor UAV, characterized in that: The invention comprises a single propeller (1), a power transmission rod (2) and an unmanned aerial vehicle shell (5), wherein the unmanned aerial vehicle shell (5) is internally installed with a propeller power device (3), a first fixing plate (4), a small turbine (6), a turbine power device (7), an unmanned aerial vehicle internal layer (8), a flight control box (9), a sensor (10), a battery (11), a second fixing plate, four air control surfaces (12) and corresponding four control steering gears (13), an air circulation channel (14) and an air inlet (15); the single propeller (1) is located above the unmanned aerial vehicle shell (5) and is installed on the upper end of the power transmission rod (2), and the lower end of the power transmission rod (2) is connected to the propeller power device (3), and the propeller power device (3) is connected to the unmanned aerial vehicle shell (5). The device (3) is mounted on a first fixing plate (4); the small turbine (6) is below the first fixing plate (4), and a turbine power device (7) is mounted below the small turbine (6); the built-in layer (8) of the drone separates the space below the small turbine (6) and above the second fixing plate into two spaces, an inner space and an outer space, wherein the outer space is an air circulation channel (14), and the inner space is sequentially installed with a flight control box (9), various sensors (10), a battery (11) and four control steering gears (13), and the battery (11) and the four control steering gears (13) are mounted on the second fixing plate; the four air control surfaces (12) are mounted on the bottom of the drone and are individually controlled by the four control steering gears (13); The drone built-in layer (8) is installed in the middle part of the entire drone shell (5).

2. A portable ducted micro-single-rotor UAV according to claim 1, characterized in that: The first fixing plate (4), except for the portion used to fix the propeller power device (3), has a hollow structure in the remaining portion to facilitate the circulation of airflow.

3. A portable ducted micro-single-rotor UAV according to claim 1, characterized in that: The flight control box (9) contains a UAV flight controller and an autopilot.

4. The portable ducted micro single-rotor UAV according to claim 1, characterized in that: Two of the four air control surfaces (12) are symmetrically mounted on opposite sides of the inner wall of the drone shell (5), and the other two are symmetrically mounted on the other two sides of the inner wall of the drone shell (5).

5. The portable ducted micro single-rotor UAV according to claim 1, characterized in that: The drone housing (5) is cylindrical.

6. The portable ducted micro single-rotor UAV according to claim 1, characterized in that: The single propeller (1) is detachably mounted on the upper end of the power transmission rod (2).

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