Flight control system of unmanned aerial vehicle

Abstract

The utility model discloses a flight control system of an unmanned aerial vehicle, which belongs to the technical field of flight control systems of unmanned aerial vehicles, and comprises a shell, the left side surface and the right side surface of the shell are fixedly connected with two rotating seats, the inner wall of each rotating seat is rotatably connected with a supporting arm, and the inner wall of each supporting arm is rotatably connected with a limiting shell. The bottom face of each limiting shell is fixedly connected with a rotating motor, the power output end of each rotating motor penetrates through the corresponding limiting shell and is fixedly connected with a rotor wing, the outer surface of each supporting arm is fixedly connected with a mounting frame, and the inner wall of each mounting frame is rotationally connected with an electric telescopic rod. The telescopic end of each electric telescopic rod is fixedly connected with a first rotating plate. According to the flight control system of the unmanned aerial vehicle, by detecting that the unmanned aerial vehicle shakes due to the influence of wind power, the direction of the limiting shell can be rapidly adjusted through the electric telescopic rod, the thrust direction of one or two rotor wings is changed, and the purpose of stabilizing the unmanned aerial vehicle is achieved.

Description

Technical Field

[0001] The present application belongs to the technical field of flight control systems for unmanned aerial vehicles (UAVs), and in particular to flight control systems for UAVs. Background Art

[0002] According to their application areas, drones can be divided into military and civilian use. In the military field, drones are divided into reconnaissance drones and target drones. In the civilian field, their applications in aerial photography, agriculture, plant protection, micro selfies, express delivery, disaster relief, wildlife observation, infectious disease monitoring, surveying and mapping, news reporting, power inspections, disaster relief, film and television shooting, creating romance, etc. have greatly expanded the uses of drones themselves.

[0003] When existing drones encounter sudden strong winds, it is difficult to achieve rapid and stable control by relying solely on the rotation speed of the four rotors. At this time, the drone may face the consequences of failure or crash.

[0004] To this end, we propose a UAV flight control system to solve the above problems. Utility Model Content

[0005] The purpose of this application is to solve the problem in the prior art that four rotors are difficult to resist sudden strong winds, and to propose a flight control system for a drone.

[0006] In order to achieve the above purpose, the present invention adopts the following technical solutions:

[0007] The flight control system of the unmanned aerial vehicle includes a shell, and the left and right side surfaces of the shell are fixedly connected to two rotating seats, the inner wall of each rotating seat is rotatably connected to a support arm, the inner wall of each support arm is rotatably connected to a limit shell, the bottom surface of each limit shell is fixedly connected to a rotating motor, the power output end of each rotating motor passes through the limit shell and is fixedly connected to a rotor, the outer surface of each support arm is fixedly connected to a mounting bracket, the inner wall of each mounting bracket is rotatably connected to an electric telescopic rod, the telescopic end of each electric telescopic rod is fixedly connected to a first rotating plate, the outer surface of each limit shell is fixedly connected to a second rotating plate, and the outer surface of each first rotating plate is rotatably connected to the inner wall of the second rotating plate.

[0008] Preferably, a laser radar module is fixedly connected to the upper surface of the shell, and a probe lens is fixedly connected to the front surface of the laser radar module.

[0009] Preferably, a signal receiver is provided above the shell, and the bottom surface of the signal receiver is fixedly connected to the upper surface of the laser radar module.

[0010] Preferably, the inner bottom wall of the shell is fixedly connected to a control mainboard, and the inner wall of the shell is clamped with a battery.

[0011] Preferably, four hinged seats are provided below the shell, and the upper surface of each hinged seat is fixedly connected to the bottom surface of the shell.

[0012] Preferably, the inner wall of each hinge seat is movably hinged with a support leg, and one end of each support leg away from the hinge seat is fixedly connected to a silicone ball.

[0013] Preferably, a camera is provided below the housing, and the upper surface of the camera is fixedly connected to the bottom surface of the housing.

[0014] In summary, the technical effects and advantages of this application are:

[0015] By setting a rotating seat to be installed on the outer surface of the shell, a support arm is installed inside each rotating seat, and the relationship between the limit shell and the support arm is used for rotation connection, and the power provided by the rotating motor is used to drive the rotor to rotate, the UAV can be provided with rising wind force to achieve the take-off effect. The mounting bracket is installed on the support arm to provide stability, and the first rotating plate can be driven by extending the electric telescopic rod. The relationship between the first rotating plate and the second rotating plate is used for rotation connection, so that the limit shell as a whole can rotate around the center of the support arm as the axis. At this time, the limit shell as a whole will produce deviation. If the UAV is affected by the wind and shakes at this time, the limit shell can be quickly adjusted using the electric telescopic rod to change the direction of the thrust of one or two rotors to achieve the purpose of stabilizing the UAV. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 This is a schematic diagram of the three-dimensional structure of the shell of the utility model;

[0017] Figure 2 This is a schematic diagram of the three-dimensional structure of the support arm of the utility model;

[0018] Figure 3 This is a three-dimensional structural diagram of the battery of the utility model;

[0019] Figure 4 It is a three-dimensional structural diagram of the control mainboard of the utility model.

[0020] In the figure: 1. Outer shell; 2. Rotating seat; 3. Support arm; 4. Limiting shell; 5. Rotating motor; 6. Rotor; 7. Mounting frame; 8. Electric telescopic rod; 9. Second rotating plate; 10. First rotating plate; 11. LiDAR module; 12. Probe lens; 13. Signal receiver; 14. Control main board; 15. Battery; 16. Articulated seat; 17. Support leg; 18. Silicone ball; 19. Camera. DETAILED DESCRIPTION

[0021] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.

[0022] Reference Figure 1-4 The flight control system of the UAV includes a shell 1, and two rotating seats 2 are fixedly connected to the left and right sides of the shell 1. A laser radar module 11 is fixedly connected to the upper surface of the shell 1, and a probe lens 12 is fixedly connected to the front of the laser radar module 11. The laser radar module 11 determines the distance by measuring the time difference and phase difference of the laser signal, measures the angle by horizontal rotation scanning, and establishes a two-dimensional polar coordinate system based on these two parameters. Then, the height information in three dimensions is obtained by obtaining signals at different pitch angles. The probe lens 12 plays a protective role to prevent dust from entering.

[0023] The inner wall of each rotating seat 2 is rotatably connected to a support arm 3, and the inner wall of each support arm 3 is rotatably connected to a limiting shell 4. A signal receiver 13 is provided above the outer shell 1, and the bottom surface of the signal receiver 13 is fixedly connected to the upper surface of the laser radar module 11. The signal receiver 13 is an electromagnetic signal received by the antenna and sent into the receiver, which is convenient for connection with the ground staff controller.

[0024] The bottom surface of each limiting shell 4 is fixedly connected to a rotating motor 5, and the power output end of each rotating motor 5 passes through the limiting shell 4 and is fixedly connected to the rotor 6. The inner bottom wall of the outer shell 1 is fixedly connected to the control mainboard 14, and the inner wall of the outer shell 1 is clamped with a battery 15. The control mainboard 14 is the core component of the drone, and its function is to calculate and convey instructions. The battery 15 provides power for the drone.

[0025] The outer surface of each support arm 3 is fixedly connected to a mounting bracket 7, and the inner wall of each mounting bracket 7 is rotatably connected to an electric telescopic rod 8. Four hinged seats 16 are provided under the outer shell 1, and the upper surface of each hinged seat 16 is fixedly connected to the bottom surface of the outer shell 1. The hinged seat 16 is used to clamp the support leg 17, which facilitates disassembly and storage.

[0026] The telescopic end of each electric telescopic rod 8 is fixedly connected to the first rotating plate 10, the outer surface of each limit shell 4 is fixedly connected to the second rotating plate 9, the outer surface of each first rotating plate 10 is rotatably connected to the inner wall of the second rotating plate 9, the inner wall of each articulated seat 16 is movably hinged with a support leg 17, and each support leg 17 is fixedly connected to a silicone ball 18 at one end away from the articulated seat 16. The four support legs 17 support the drone, and the silicone ball 18 can be used to cushion the impact of landing.

[0027] A camera 19 is provided below the housing 1 , and the upper surface of the camera 19 is fixedly connected to the bottom surface of the housing 1 . The camera 19 is an existing structure of the UAV, which is convenient for recording images of the flight path and completing corresponding tasks.

[0028] The working principle of the present utility model is as follows: when in use, the rotating motor 5 is first electrically connected to the battery 15 through a wire, and then the rotating seat 2 is used to be installed on the outer surface of the shell 1, and a support arm 3 is installed inside each rotating seat 2. The limit shell 4 is rotatably connected to the support arm 3, and the power provided by the rotating motor 5 is used to drive the rotor 6 to rotate, which can provide the drone with rising wind force to achieve the take-off effect. If the drone detects a strong wind using the built-in wind sensor at this time, the drone is affected by the wind and shakes. At this time, the mounting bracket 7 is installed on the support arm 3 with stability and will not be affected by the wind. At this time, the control main board 14 issues an adjustment instruction according to the detection of the wind sensor, and the electric telescopic rod 8 is extended or retracted to drive the first rotating plate 10. The first rotating plate 10 and the second rotating plate 9 are rotatably connected, so that the limit shell 4 as a whole can rotate with the center of the support arm 3 as the axis. At this time, the limit shell 4 as a whole will produce a deflection, and the direction of the thrust of one or more rotors 6 is changed to achieve the purpose of stabilizing the drone.

[0029] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" and the like to indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention 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 should not be understood as a limitation on the present invention.

[0030] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of the technical features being referred to. Thus, a feature specified as "first" or "second" may explicitly or implicitly include one or more of such features. In the description of this utility model, "plurality" means two or more, unless otherwise specifically defined.

[0031] The above is only a preferred specific implementation method of the present invention, but the protection scope of the present invention is not limited to this. Any technician familiar with the technical field within the technical scope disclosed by the present invention can make equivalent replacements or changes based on the technical solution and utility model concept of the present invention, which should be covered by the protection scope of the present invention.

Claims

1. A flight control system for an unmanned aerial vehicle, comprising a housing (1), characterized in that: The left and right sides of the housing (1) are fixedly connected to two rotating seats (2); the inner wall of each rotating seat (2) is rotatably connected to a support arm (3); the inner wall of each support arm (3) is rotatably connected to a limit shell (4); the bottom surface of each limit shell (4) is fixedly connected to a rotating motor (5); the power output end of each rotating motor (5) passes through the limit shell (4) and is fixedly connected to a rotor (6); the outer surface of each support arm (3) is fixedly connected to a mounting bracket (7); the inner wall of each mounting bracket (7) is rotatably connected to an electric telescopic rod (8); the telescopic end of each electric telescopic rod (8) is fixedly connected to a first rotating plate (10); the outer surface of each limit shell (4) is fixedly connected to a second rotating plate (9); the outer surface of each first rotating plate (10) is rotatably connected to the inner wall of the second rotating plate (9).

2. The UAV flight control system according to claim 1, characterized in that: A laser radar module (11) is fixedly connected to the upper surface of the housing (1), and a probe lens (12) is fixedly connected to the front surface of the laser radar module (11).

3. The UAV flight control system according to claim 2, characterized in that: A signal receiver (13) is provided above the housing (1), and the bottom surface of the signal receiver (13) is fixedly connected to the upper surface of the laser radar module (11).

4. The UAV flight control system according to claim 1, characterized in that: The inner bottom wall of the housing (1) is fixedly connected to a control mainboard (14), and the inner wall of the housing (1) is clamped with a battery (15).

5. The UAV flight control system according to claim 1, characterized in that: Four hinged seats (16) are provided below the housing (1), and the upper surface of each hinged seat (16) is fixedly connected to the bottom surface of the housing (1).

6. The UAV flight control system according to claim 5, characterized in that: The inner wall of each hinge seat (16) is movably hinged with a support leg (17), and one end of each support leg (17) away from the hinge seat (16) is fixedly connected with a silicone ball (18).

7. The UAV flight control system according to claim 1, characterized in that: A camera (19) is provided below the housing (1), and the upper surface of the camera (19) is fixedly connected to the bottom surface of the housing (1).

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