Unmanned aerial vehicle flight attitude control device

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle flight attitude control device, which comprises an unmanned aerial vehicle, a flight control unit and a control unit. The mounting mechanism is arranged at the top of the unmanned aerial vehicle; wherein the mounting mechanism comprises a buffer frame fixedly connected to the top of the unmanned aerial vehicle, the top of the buffer frame is fixedly connected with four guide blocks, the four guide blocks are distributed in a rectangular shape, the inner wall of the flight controller is slidably connected to the surfaces of the guide blocks, and the inner wall of the buffer frame is slidably connected with a mounting frame; the rear end of the mounting frame penetrates through the guide block and abuts against the top of the flight controller. According to the device, the flight controller is rapidly mounted in the buffer frame through the guide block, the eccentric wheel and the mounting frame, the flight controller is stably mounted in the buffer frame through the sliding block, the driven groove and the screw rod, and the control effect of the flight controller on the flight attitude of the unmanned aerial vehicle is guaranteed.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, and particularly relates to a flight attitude control device for an unmanned aerial vehicle. Background Art

[0002] An unmanned aerial vehicle is an aircraft that can fly without direct control by a pilot. The flight attitude control device of an unmanned aerial vehicle is one of the core components in the unmanned aerial vehicle system, responsible for monitoring and controlling the attitude of the unmanned aerial vehicle to ensure its stable flight in the air. The flight attitude of the unmanned aerial vehicle, such as pitch, yaw and roll, is automatically controlled through the cooperation of sensors, a flight control computer and actuators.

[0003] After retrieval, the Chinese patent "A flight control system for controlling the flight of an unmanned aerial vehicle" with the authorization announcement number "CN216611644U" realizes the installation of the flight control device on the unmanned aerial vehicle through a connecting frame, a device frame, a sliding rod and a spring, and the installation of the flight control device on the unmanned aerial vehicle is simple to operate.

[0004] During the flight of the above-mentioned unmanned aerial vehicle in the air, vibration force will be generated and transmitted to the spring. Due to the elasticity of the spring, the sliding rod is pushed by the spring to install the flight control device on the unmanned aerial vehicle, which easily leads to unstable installation of the flight control device and further affects the flight attitude control effect of the unmanned aerial vehicle.

[0005] Therefore, a flight attitude control device for an unmanned aerial vehicle is proposed to solve the above problems. Summary of the Utility Model

[0006] The purpose of the utility model is to provide a flight attitude control device for an unmanned aerial vehicle to solve the above problems and improve the problem of unstable installation of the flight control device on the unmanned aerial vehicle.

[0007] The utility model realizes the above purpose through the following technical solutions. A flight attitude control device for an unmanned aerial vehicle includes: an unmanned aerial vehicle, on the top of which a flight controller is provided; an installation mechanism, which is arranged on the top of the unmanned aerial vehicle; wherein, the installation mechanism includes a buffer frame fixedly connected to the top of the unmanned aerial vehicle, on the top of the buffer frame, four guide blocks are fixedly connected, the four guide blocks are distributed in a rectangle, the inner wall of the flight controller is slidably connected to the surface of the guide blocks, an installation frame is slidably connected to the inner wall of the buffer frame, the rear end of the installation frame penetrates through the guide blocks and abuts against the top of the flight controller, an eccentric wheel is rotatably connected to the inner wall of the buffer frame, a screw rod is arranged on the upper end surface of the eccentric wheel, and the surface of the screw rod is threadedly connected to the inner wall of the buffer frame.

[0008] Preferably, a sliding hole is formed in the inner wall of the screw, a slider is slidably connected to the inner wall of the sliding hole, a driven groove is formed in the upper end surface of the eccentric wheel, and the surface of the slider is slidably connected to the inner wall of the driven groove. Through the guide block, the eccentric wheel and the mounting frame, the flight controller is quickly installed in the buffer frame. Through the slider, the driven groove and the screw, the flight controller is stably installed in the buffer frame, ensuring the control effect of the flight controller on the flight attitude of the drone.

[0009] Preferably, a protective cover is rotatably connected to the surface of the screw, and the surface of the protective cover is slidably connected to the top of the buffer frame. By using the protective cover, the surface of the screw is protected, preventing impurities from adhering to the surface of the screw and reducing the wear between the screw and the buffer frame.

[0010] Preferably, a long rod is fixedly connected to the bottom end of the protective cover, and the lower end surface of the long rod is clamped inside the eccentric wheel. By using the long rod, the positioning of the eccentric wheel is realized, improving the stability of the flight controller installed inside the buffer frame.

[0011] Preferably, a push rod is fixedly connected to the upper end surface of the screw.

[0012] Preferably, a limit block is fixedly connected to the front end of the mounting frame, and the lower end surface of the eccentric wheel contacts one side of the limit block. By using the limit block, the rotation direction of the eccentric wheel is restricted, ensuring that the long rod can be accurately inserted into the eccentric wheel.

[0013] Preferably, a soft pad is fixedly connected to the upper end surface of the slider, and the bottom of the soft pad contacts the top end of the screw. By using the soft pad, the top end of the screw is sealed, preventing impurities from entering the through hole.

[0014] Preferably, the surface of the guide block is in an isosceles trapezoid shape.

[0015] The beneficial effects of the present utility model are:

[0016] 1. Through the guide block, the eccentric wheel and the mounting frame, the flight controller is quickly installed in the buffer frame. Through the slider, the driven groove and the screw, the flight controller is stably installed in the buffer frame, ensuring the control effect of the flight controller on the flight attitude of the drone;

[0017] 2. By using the protective cover, the surface of the screw is protected, preventing impurities from adhering to the surface of the screw and reducing the wear between the screw and the buffer frame. By using the long rod, the positioning of the eccentric wheel is realized, improving the stability of the flight controller installed inside the buffer frame. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 is a schematic diagram of the overall structure of the present utility model;

[0019] Figure 2 Structural schematic diagram of the flight controller and the mounting mechanism of the present utility model;

[0020] Figure 3 is Figure 2 an enlarged view of A in

[0021] Figure 4 Structural schematic diagram of the mounting mechanism of the present utility model;

[0022] Figure 5 is Figure 4 an enlarged view of B in

[0023] In the figure: 1, unmanned aerial vehicle; 2, flight controller; 3, mounting mechanism; 31, buffer frame; 32, guide block; 33, mounting bracket; 34, eccentric wheel; 35, screw; 36, driven groove; 37, slider; 38, protective cover; 39, long rod; 310, sliding hole; 311, soft pad; 312, limit block; 313, push rod. Specific embodiments

[0024] Next, the technical solutions in the embodiments of the present utility model will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present utility model. Obviously, the described embodiments are only a part of the embodiments of the present utility model, rather than all the embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without making creative efforts shall fall within the protection scope of the present utility model.

[0025] During specific implementation: As Figures 1-5 shown, a flight attitude control device for an unmanned aerial vehicle includes: an unmanned aerial vehicle 1, a flight controller 2 is provided on the top of the unmanned aerial vehicle 1; a mounting mechanism 3, the mounting mechanism 3 is arranged on the top of the unmanned aerial vehicle 1; wherein, the mounting mechanism 3 includes a buffer frame 31 fixedly connected to the top of the unmanned aerial vehicle 1, four guide blocks 32 are fixedly connected to the top of the buffer frame 31, the four guide blocks 32 are distributed in a rectangular shape, the inner wall of the flight controller 2 is slidably connected to the surface of the guide block 32, a mounting bracket 33 is slidably connected to the inner wall of the buffer frame 31, the rear end of the mounting bracket 33 penetrates through the guide block 32 and abuts against the top of the flight controller 2, an eccentric wheel 34 is rotatably connected to the inner wall of the buffer frame 31, a screw 35 is provided on the upper end surface of the eccentric wheel 34, the surface of the screw 35 is threadedly connected to the inner wall of the buffer frame 31, a sliding hole 310 is formed in the inner wall of the screw 35, a slider 37 is slidably connected to the inner wall of the sliding hole 310, a driven groove 36 is formed in the upper end surface of the eccentric wheel 34, the surface of the slider 37 is slidably connected to the inner wall of the driven groove 36, the surface of the guide block 32 is in an isosceles trapezoid shape, and a push rod 313 is fixedly connected to the upper end surface of the screw 35. There is a gap between the inner side of the screw 35 and the upper end surface of the eccentric wheel 34. Sensors, a flight control computer and an actuator are provided in the flight controller 2.

[0026] When the flight controller 2 needs to be installed on the UAV 1, due to the isosceles trapezoidal shape of the surface of the guide block 32, the flight controller 2 can be quickly and accurately placed in the buffer frame 31. Push the slider 37 to make the slider 37 abut against the driven groove 36. At this time, push the push rod 313, and the rotation of the push rod 313 drives the screw rod 35 to move downward while rotating on the inner wall of the buffer frame 31. The rotation of the screw rod 35 drives the eccentric wheel 34 to rotate in the buffer frame 31 through the slider 37. The rotating eccentric wheel 34 pushes the mounting bracket 33 to move, so that the mounting bracket 33 abuts against the top of the flight controller 2, and the flight controller 2 is firmly installed in the buffer frame 31. At this time, manually turn on the UAV 1 and the flight controller 2 through the console, so that the UAV 1 flies in the air. The sensors on the flight controller 2 measure external information, and the measured data is transmitted into the flight controller 2 and the control instructions are calculated to automatically adjust the flight attitude of the UAV 1. The flight controller 2 uses complex algorithms such as PID control and Kalman filtering to maintain flight stability.

[0027] As Figure 5 As shown, the surface of the screw rod 35 is rotatably connected with a protective cover 38. The surface of the protective cover 38 is slidably connected to the top of the buffer frame 31. The bottom end of the protective cover 38 is fixedly connected with a long rod 39. The lower end of the surface of the long rod 39 is clamped in the inner wall of the eccentric wheel 34.

[0028] As Figures 4-5 As shown, the front end of the mounting bracket 33 is fixedly connected with a limiting block 312. The lower end of the surface of the eccentric wheel 34 contacts one side of the limiting block 312. The upper end of the surface of the slider 37 is fixedly connected with a soft pad 311. The bottom of the soft pad 311 contacts the top end of the screw rod 35. The buffer frame 31, the protective cover 38 and the soft pad 311 are all made of synthetic rubber components.

[0029] When the present utility model is in use, due to the isosceles trapezoidal shape of the surface of the guide block 32, the flight controller 2 can be quickly and accurately placed in the buffer frame 31. Push the slider 37 to make the slider 37 abut against the driven groove 36. At this time, push the push rod 313, and the rotation of the push rod 313 drives the screw rod 35 to move downward while rotating on the inner wall of the buffer frame 31. The rotation of the screw rod 35 drives the eccentric wheel 34 to rotate in the buffer frame 31 through the slider 37. When the rotating eccentric wheel 34 abuts against one side of the limiting block 312, the mounting bracket 33 abuts against the top of the flight controller 2. Push the slider 37 to move away from the driven groove 36 and retract into the sliding hole 310. Since the surface of the eccentric wheel 34 does not directly contact the inner side of the screw rod 35, the rotation of the screw rod 35 will not drive the eccentric wheel 34 to rotate. Push the push rod 313, so that the screw rod 35 drives the protective cover 38 and the long rod 39 to move downward during the rotation and downward movement, so that the long rod 39 is accurately clamped in the eccentric wheel 34. Stop pushing the push rod 313, and the flight controller 2 is firmly installed in the buffer frame 31.

[0030] It should be noted that in the above description, the drone 1, the flight controller 2, etc. are all devices with relatively mature applications in the prior art. The specific models can be selected according to actual needs. At the same time, the power supply for the drone 1 and the flight controller 2 can be an internal power supply or a mains power supply. The specific power supply method is selected according to the situation and will not be elaborated here.

[0031] In addition, it should be understood that although this specification is described according to embodiments, not every embodiment only contains an independent technical solution. This narrative method of the specification is only for clarity. Those skilled in the art should regard the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. An unmanned aerial vehicle flight attitude control device, characterized in that, Comprising: An unmanned aerial vehicle (1), with a flight controller (2) provided at the top of the unmanned aerial vehicle (1); A mounting mechanism (3), which is arranged at the top of the unmanned aerial vehicle (1); Among them, the mounting mechanism (3) includes a buffer frame (31) fixedly connected to the top of the unmanned aerial vehicle (1), the top of the buffer frame (31) is fixedly connected with four guide blocks (32), the four guide blocks (32) are distributed in a rectangular shape, the inner wall of the flight controller (2) is slidably connected to the surface of the guide blocks (32), the inner wall of the buffer frame (31) is slidably connected with a mounting frame (33), the rear end of the mounting frame (33) penetrates through the guide blocks (32) and abuts against the top of the flight controller (2), the inner wall of the buffer frame (31) is rotatably connected with an eccentric wheel (34), the upper end of the surface of the eccentric wheel (34) is provided with a screw rod (35), and the surface of the screw rod (35) is threadedly connected to the inner wall of the buffer frame (31).

2. The drone flight attitude control device according to claim 1, characterized in that: A sliding hole (310) is opened in the inner wall of the screw rod (35), a slider (37) is slidably connected to the inner wall of the sliding hole (310), a driven groove (36) is opened in the upper end of the surface of the eccentric wheel (34), and the surface of the slider (37) is slidably connected to the inner wall of the driven groove (36).

3. The drone flight attitude control device according to claim 1, characterized in that: A protective cover (38) is rotatably connected to the surface of the screw rod (35), and the surface of the protective cover (38) is slidably connected to the top of the buffer frame (31).

4. The drone flight attitude control device according to claim 3, characterized in that: The bottom end of the protective cover (38) is fixedly connected with a long rod (39), and the lower end of the surface of the long rod (39) is clamped in the inner wall of the eccentric wheel (34).

5. An unmanned aerial vehicle flight attitude control device according to claim 1, characterized in that: A push rod (313) is fixedly connected to the upper end of the surface of the screw rod (35).

6. A drone flight attitude control device according to claim 1, characterized in that: A limiting block (312) is fixedly connected to the front end of the mounting frame (33), and the lower end of the surface of the eccentric wheel (34) contacts one side of the limiting block (312).

7. An unmanned aerial vehicle flight attitude control device according to claim 2, characterized in that: A soft pad (311) is fixedly connected to the upper end of the surface of the slider (37), and the bottom of the soft pad (311) contacts the top end of the screw rod (35).

8. The drone flight attitude control device according to claim 1, characterized in that: The surface of the guide block (32) is in the shape of an isosceles trapezoid.

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