Ducted unmanned aerial vehicle

Abstract

The invention provides a ducted unmanned aerial vehicle. The ducted unmanned aerial vehicle comprises a ducted unmanned aerial vehicle assembly and airborne electronic and electrical equipment. A ducted propeller propelling device at the tail of the ducted unmanned aerial vehicle assembly serves as a power device, a sweepback trapezoidal wing serves as a lifting surface during forward flight, a head detection device is a detection device with a servo mechanism, and the middle of the ducted unmanned aerial vehicle assembly can be loaded with corresponding loads according to task requirements. The unmanned aerial vehicle is a ducted high-speed unmanned aerial vehicle with servo detection, and integrates the advantages of a rotor unmanned aerial vehicle, a ducted unmanned aerial vehicle and a fixed-wing unmanned aerial vehicle; the unmanned aerial vehicle has the capabilities of vertical take-off and landing, high-speed flight and large-angle detection, and can be used for racing flight, target tracking and the like of the unmanned aerial vehicle.

Description

Technical Field

[0001] The present invention belongs to the technical field of unmanned aerial vehicles (UAVs), and in particular relates to a ducted UAV, in particular a ducted high-speed UAV with servo detection. Background Art

[0002] In the prior art, conventional multi-rotor drones generally have a small body inclination angle during forward flight, and the direction of flight speed is almost consistent with the direction of blade rotation linear velocity. Limited by the influence of blade tip speed, blade strength, and power, their forward flight speed is generally difficult to be too fast. Furthermore, limited by the overall configuration layout and blade size, conventional multi-rotor drones are generally large in size. Fixed-wing drones propelled by propellers or ducted propellers can have a faster forward flight speed than conventional multi-rotor drones, but generally cannot take off and land vertically, are larger in size, and have limited usage scenarios. In addition, the detection devices of multi-rotor drones and fixed-wing drones are generally located on the belly or back of the fuselage, and their detection field of view is severely blocked by the fuselage. In addition, many detection devices do not have servo rotation capabilities, resulting in a small detection field of view and limited detection capabilities.

[0003] At present, the existing relevant technical achievements mainly include:

[0004] A fixed-wing unmanned aerial vehicle capable of vertical take-off and landing and powered by four-ducted propellers (patent document CN108284950A) discloses a fixed-wing unmanned aerial vehicle capable of vertical take-off and landing and powered by four-ducted propellers. The fuselage of the unmanned aerial vehicle is a lifting body with a plane-symmetrical structure. During horizontal flight, the fuselage cannot withstand excessive roll angles because it needs to provide aerodynamic lift. Otherwise, a large lateral force will be generated, causing the aircraft to skid or stall.

[0005] In response to the technical problems existing in the prior art, the present invention proposes a ducted UAV, whose fuselage adopts an axisymmetric structure. The fuselage itself does not generate aerodynamic lift, and the wing aerodynamic force is symmetrical along the axis of the fuselage. The UAV can achieve 360° free roll during flight, is not prone to side slip or stall, and has better roll and maneuverability characteristics; at the same time, it has vertical take-off and landing, high-speed flight and large-angle detection capabilities, and can be used for UAV racing flights, tracking targets, etc. Summary of the Invention

[0006] In view of the defects in the prior art, the purpose of the present invention is to provide a ducted UAV.

[0007] A ducted UAV provided according to the present invention comprises: a ducted UAV assembly and an onboard electronic and electrical device;

[0008] The ducted UAV assembly includes: a detection device, a servo mechanism, a fuselage, wings, and a ducted propeller propulsion device;

[0009] The wing is connected between the fuselage and the ducted propeller propulsion device, the detection device is installed on the head of the fuselage through a servo mechanism and is driven to rotate by the servo mechanism, and the airborne electronic and electrical equipment is arranged on the fuselage.

[0010] Preferably, the ducted propeller propulsion device further comprises: a duct and a propeller;

[0011] The base of the motor is firmly connected to the inner wall of the duct;

[0012] The central rotating shaft of the propeller is coaxially connected with the rotating shaft of the motor, and is arranged inside the duct and coaxial with the duct; the propeller is driven to rotate by the motor.

[0013] Preferably, the onboard electronic and electrical equipment includes: a battery, a power board, an electric adjustment board, a flight control board, an information processing board, a data transmission module, and an image transmission module;

[0014] The batteries are electrically connected to the power supply board and the electric adjustment board respectively;

[0015] The electric adjustment board is electrically connected to the flight control board;

[0016] The power supply board is electrically connected to the information processing board and the data transmission module;

[0017] The information processing board is electrically connected to the flight control board and the image transmission module.

[0018] Preferably, the information processing board is electrically connected to the detection device and the servo mechanism;

[0019] The detection device is electrically connected to the servo mechanism and the data transmission module.

[0020] Preferably, the onboard electronic and electrical equipment includes: a battery, a power board, an electric adjustment board, a flight control board, an information processing board, a data transmission module, and an image transmission module;

[0021] The batteries are electrically connected to the power supply board and the electric adjustment board respectively;

[0022] The electric adjustment board is electrically connected to the flight control board;

[0023] The power supply board is electrically connected to the information processing board and the data transmission module;

[0024] The information processing board is electrically connected to the flight control board and the image transmission module;

[0025] The information processing board is electrically connected to the detection device and the servo mechanism;

[0026] The detection device is electrically connected to the servo mechanism and the data transmission module;

[0027] The electric adjustment board is electrically connected to the motor; the electric adjustment board adjusts the motor speed, thereby adjusting the propeller speed.

[0028] Preferably, the flight control board is externally connected to a remote control receiver and a navigation module.

[0029] Preferably, the number of the detection device is one and the shape is spherical;

[0030] There is one fuselage, which is cylindrical in shape;

[0031] There are four wings in the form of swept trapezoids, which are evenly distributed along the circumference at the tail of the fuselage.

[0032] Preferably, there are four groups of ducted propeller propulsion devices, each group including a duct, a propeller and a motor.

[0033] Preferably, the detection device is a detection device with a servo mechanism.

[0034] According to the present invention, a method for operating electronic and electrical equipment of a ducted high-speed UAV with servo detection is provided, using the ducted UAV provided by the present invention, comprising:

[0035] Step S1: The battery supplies power to the entire device;

[0036] Step S2: the power board converts the voltage and outputs it;

[0037] Step S3: the flight control board sends a control instruction to the electric control board;

[0038] Step S4: the electric control panel adjusts the operation of the ducted propeller propulsion device;

[0039] Step S5: The information processing board receives and processes the detection image information and flight mission information, and sends control instructions to the flight control board, servo mechanism and detection device;

[0040] Step S6: The data transmission module sends and receives information; the image transmission module is used to transmit images.

[0041] Compared with the prior art, the present invention has the following beneficial effects:

[0042] 1. The present invention sets the thrust direction through structural layout, has vertical take-off and landing capabilities, does not require a take-off and landing runway, or auxiliary equipment such as ejection and recovery, has a short deployment and take-off and landing time, and is not restricted by the site;

[0043] 2. The present invention has the ability to fly horizontally at high speed. By using the swept-back trapezoidal wings as the lifting surface during forward flight, the aircraft can fly faster than traditional multi-rotor drones, move more maneuverably, have a long endurance, and have good tracking performance.

[0044] 3. The airborne equipment of the present invention is arranged vertically, which is more compact and occupies less space than traditional fixed-wing UAVs and multi-rotor UAVs;

[0045] 4. The detection device of the drone of the present invention is connected to the fuselage through a servo mechanism. It has a roll angle of 360° and a pitch angle of 120°, and has three-dimensional omnidirectional servo detection capability. It has a larger detection field of view and a longer detection distance than ordinary drones. BRIEF DESCRIPTION OF THE DRAWINGS

[0046] Other features, objects and advantages of the present invention will become more apparent upon reading the detailed description of non-limiting embodiments with reference to the following drawings:

[0047] Figure 1 Schematic diagram of the overall ducted UAV assembly of the present invention.

[0048] Figure 2 This is a bottom view of the ducted UAV assembly of the present invention.

[0049] Figure 3 This is a schematic diagram of the connection of the onboard electronic and electrical equipment of the present invention.

[0050] The figure shows:

[0051] DETAILED DESCRIPTION

[0052] The present invention will be described in detail below with reference to specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those skilled in the art, several changes and improvements can be made without departing from the scope of the present invention. These all fall within the scope of protection of the present invention.

[0053] like Figure 1 、 Figure 2As shown, the ducted UAV provided by the embodiment of the present invention includes: a ducted UAV component and airborne electronic and electrical equipment. The ducted UAV assembly includes: a detection device 1, a servo mechanism 2, a fuselage 3, wings 4, and a ducted propeller propulsion device 5; the ducted propeller propulsion device 5 is used to provide flight power, and includes: a duct 6, a propeller 7, and a motor 8; the base of the motor 8 is tightly connected to the inner wall of the duct 6; the central rotating shaft of the propeller 7 is coaxially matched with the rotating shaft of the motor 8, and is arranged inside the duct 6 and coaxial with the duct 6. Furthermore, the connection method is a tight connection; the propeller 7 is driven to rotate by the motor 8 to generate thrust; the duct 6 is used to protect the propeller 7 and the motor 8, rectify and generate additional thrust; the wing 4 is connected between the fuselage 3 and the ducted propeller propulsion device 5, and provides partial lift during forward flight; the detection device 1 is installed on the head of the fuselage 3 through the servo mechanism 2, and is driven to rotate by the servo mechanism 2, so as to detect and track targets in all directions without blind spots; the fuselage 3 is used for body rectification and structural connection, and is equipped with onboard electronic and electrical equipment. Furthermore, there is one detection device 1, which is spherical in shape; there is one fuselage 3, which is cylindrical in shape; there are four wings 4, which are swept trapezoidal in shape and are evenly distributed circumferentially at the tail of the fuselage 3; there are four groups of ducted propeller propulsion devices 5, each group includes a duct 6, a propeller 7, and a motor 8.

[0054] like Figure 3 As shown, the onboard electronic and electrical equipment includes: a battery 9, a power supply board 10, an electric adjustment board 11, a flight control board 12, an information processing board 13, a data transmission module 14, and an image transmission module 15. The battery 9 is used to power the entire device and is electrically connected to the power supply board 10 and the electric adjustment board 11 respectively; the electric adjustment board 11 is electrically connected to the flight control board 12; the power supply board 10 is used for voltage conversion and output and is electrically connected to the information processing board 13 and the data transmission module 14; the information processing board 13 is electrically connected to the flight control board 12 and the image transmission module 15; the flight control board 12 is used to send control instructions to the electric adjustment board 11; the data transmission module 14 is used to send and receive information; the image transmission module 15 is used to transmit images; the information processing board 13 is electrically connected to the detection device 1 and the servo mechanism 2; the information processing board 13 is used to receive and process detection image information and flight mission information, and send control instructions to the flight control board 12, the servo mechanism 2, and the detection device 1; the detection device 1 is electrically connected to the servo mechanism 2 and the data transmission module 14. The electric adjustment board 11 is electrically connected to the motor 8 ; the electric adjustment board 11 is used to adjust the speed of the motor 8 , and further adjust the speed of the propeller 7 .

[0055] In a more specific embodiment, the flight control board 12 can also be externally connected to a remote control receiver, a navigation module, etc.

[0056] Specifically, the present invention further provides an operating method for electronic and electrical equipment of a ducted high-speed UAV with servo detection, which uses the ducted UAV provided by the present invention, comprising:

[0057] Step S1: the battery 9 supplies power to the entire device;

[0058] Step S2: the power board 10 converts the voltage and outputs it;

[0059] Step S3: the flight control board 12 sends a control instruction to the electric adjustment board 11;

[0060] Step S4: the electric control panel 11 adjusts the operation of the ducted propeller propulsion device 5, specifically adjusting the speed of the motor 8;

[0061] Step S5: The information processing board 13 receives and processes the detection image information and the flight mission information, and sends control instructions to the flight control board 12, the servo mechanism 2 and the detection device 1;

[0062] Step S6: The data transmission module 14 sends and receives information; the image transmission module 15 is used to transmit images.

[0063] Furthermore, since the fuselage 3 adopts an axisymmetric structure, the fuselage 3 itself does not generate aerodynamic lift, and the wing aerodynamic force is symmetrical along the axis of the fuselage 3. The UAV can achieve 360° free roll during flight, is less likely to side-slip or stall, and has better roll and maneuverability characteristics; and since the detection device 1 is connected to the head of the fuselage 3 through the servo mechanism 2, the servo mechanism 2 has freedom in both roll and pitch directions, and can drive the detection device 1 to obtain a roll angle of 360° along the axis of the fuselage 3 and a pitch angle of 120° along the pitch direction. The pitch is coordinated with the roll, so that the UAV as a whole has three-dimensional omnidirectional detection capabilities.

[0064] In summary, the present invention provides a ducted UAV with a tail propeller propulsion unit 5 as the power plant, a swept trapezoidal wing as the lift surface during forward flight, and a head detection unit 1 with a servo mechanism. The central portion can be loaded with a payload according to mission requirements. This high-speed ducted UAV with servo detection combines the advantages of rotary-wing, ducted, and fixed-wing UAVs. The present invention boasts vertical takeoff and landing, high-speed flight, and wide-angle detection capabilities, making it suitable for UAV racing, target tracking, and other applications.

[0065] In the description of this application, it should be understood that the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings, and are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on this application.

[0066] The above describes specific embodiments of the present invention. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art may make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. The embodiments of this application and the features in the embodiments may be combined with each other in any manner unless there is a conflict.

Claims

1. A ducted UAV, characterized in that: include: Ducted UAV components and onboard electrical and electronic equipment; The ducted UAV assembly comprises: a detection device (1), a servo mechanism (2), a fuselage (3), wings (4), and a ducted propeller propulsion device (5); The wing (4) is connected between the fuselage (3) and the ducted propeller propulsion device (5); the detection device (1) is installed on the head of the fuselage (3) through a servo mechanism (2) and is driven to rotate by the servo mechanism (2); and the airborne electronic and electrical equipment is arranged on the fuselage (3).

2. The ducted drone according to claim 1, characterized in that: The ducted propeller propulsion device (5) further includes: a duct (6) and a propeller (7); The base of the motor (8) is firmly connected to the inner wall of the duct (6); The central rotating shaft of the propeller (7) is coaxially connected with the rotating shaft of the motor (8), and is arranged inside the duct (6) and coaxial with the duct (6); the propeller (7) is driven to rotate by the motor (8).

3. The ducted drone according to claim 1, wherein: The onboard electronic and electrical equipment includes: a battery (9), a power supply board (10), an electric adjustment board (11), a flight control board (12), an information processing board (13), a data transmission module (14), and an image transmission module (15); The battery (9) is electrically connected to the power supply board (10) and the electric adjustment board (11) respectively; The electric adjustment board (11) is electrically connected to the flight control board (12); The power supply board (10) is electrically connected to the information processing board (13) and the data transmission module (14); The information processing board (13) is electrically connected to the flight control board (12) and the image transmission module (15).

4. The ducted UAV according to claim 3, characterized in that: The information processing board (13) is electrically connected to the detection device (1) and the servo mechanism (2); The detection device (1) is electrically connected to the servo mechanism (2) and the data transmission module (14).

5. The ducted UAV according to claim 2, wherein: The onboard electronic and electrical equipment includes: a battery (9), a power supply board (10), an electric adjustment board (11), a flight control board (12), an information processing board (13), a data transmission module (14), and an image transmission module (15); The battery (9) is electrically connected to the power supply board (10) and the electric adjustment board (11) respectively; The electric adjustment board (11) is electrically connected to the flight control board (12); The power supply board (10) is electrically connected to the information processing board (13) and the data transmission module (14); The information processing board (13) is electrically connected to the flight control board (12) and the image transmission module (15); The information processing board (13) is electrically connected to the detection device (1) and the servo mechanism (2); The detection device (1) is electrically connected to the servo mechanism (2) and the data transmission module (14); The electric adjustment board (11) is electrically connected to the motor (8); the electric adjustment board (11) adjusts the rotation speed of the motor (8), thereby adjusting the rotation speed of the propeller (7).

6. The ducted UAV according to any one of claims 3 to 5, characterized in that: The flight control board (12) is externally connected to a remote controller receiver and a navigation module.

7. The ducted drone according to any one of claims 1 to 6, characterized in that: The number of the detection device (1) is one, and the shape is spherical; The fuselage (3) is one in number and cylindrical in shape; The wings (4) are four in number, are in the shape of a swept-back trapezoid, and are evenly distributed along the circumferential direction at the tail of the fuselage (3).

8. The ducted UAV according to claim 2 or 5, characterized in that: The ducted propeller propulsion device (5) comprises four groups, each group comprising a duct (6), a propeller (7), and a motor (8).

9. The ducted drone according to claim 1, wherein: The detection device (1) is a detection device with a servo mechanism.

10. A method for operating electronic and electrical equipment of a ducted high-speed UAV with servo detection, characterized in that: The ducted drone according to any one of claims 3 to 9 comprises: Step S1: The battery (9) supplies power to the entire device; Step S2: the power board (10) converts the voltage and outputs it; Step S3: the flight control board (12) sends a control instruction to the electric adjustment board (11); Step S4: the electric control panel (11) adjusts the operation of the ducted propeller propulsion device (5); Step S5: the information processing board (13) receives and processes the detection image information and the flight mission information, and sends control instructions to the flight control board (12), the servo mechanism (2) and the detection device (1); Step S6: The data transmission module (14) sends and receives information; the image transmission module (15) is used to transmit images.

Images