Flight control for unmanned aerial vehicle

Abstract

The utility model discloses a flight controller for an unmanned aerial vehicle, which belongs to the technical field of unmanned aerial vehicles and comprises a bottom plate, a flight controller body is arranged above the bottom plate, the bottom surface of the flight controller body is in contact with the upper surface of the bottom plate, the upper surface of the bottom plate is fixedly connected with two fixing blocks, and the inner wall of each fixing block is fixedly connected with a limiting cylinder. The inner wall of each limiting cylinder is slidably connected with two moving columns, and the ends, away from each other, of the moving columns in each set are fixedly connected with limiting blocks. According to the flight control for the unmanned aerial vehicle, a moving frame can move left and right when pushed, the moving frame moves to drive a moving column to move, a limiting block on the surface can be driven to move in the moving process of the moving column, and the moving column moves to extrude a first spring in a limiting cylinder; and when the limiting block moves out of the flight controller body, the limiting effect of the flight controller body can be relieved, so that the flight controller body can be conveniently disassembled, and on the contrary, subsequent installation work is also facilitated.

Description

Technical Field

[0001] The present application belongs to the field of UAV technology, and in particular relates to a flight control system for a UAV. Background Art

[0002] The UAV flight control system is the core system of the UAV, responsible for managing and controlling the UAV's flight parameters such as attitude, heading and speed. The flight control system senses the UAV's status by receiving data from various sensors, such as accelerometers, gyroscopes, magnetometers and GPS, and calculates corresponding control commands through control algorithms to adjust the UAV's flight status and ensure that it performs the intended flight mission stably and safely.

[0003] At present, when using existing drone flight controllers, it is usually necessary to use fixing bolts to firmly fix the flight controller to ensure that the flight controller is in a stable working state when the drone is flying. However, when the staff needs to inspect, clean or replace the flight controller, it is easy to be inconvenient to disassemble and install, which affects the work efficiency of the staff.

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

[0005] The purpose of this application is to solve the problem in the prior art that it is inconvenient to disassemble and assemble the flight controller when repairing the flight controller, and to propose a flight controller for drones.

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

[0007] 7. The swiftly and minutely adjusting device for a wood-planer working table as claimed in claim 1, wherein said linking rod and said adjusting base are pivotally connected to each other with a bolt, and said bolt has a round shank to contact with said linking rod. said linking rod is pivotally connected to said linking rod. said linking rod is pivotally connected to said linking rod.

[0008] Preferably, two mounting blocks are fixedly connected to both side surfaces of the base plate, and the inner wall of each mounting block is threadedly connected with a bolt.

[0009] Preferably, a fixed cover is fixedly connected to the upper surface of the base plate, and the outer surface of the fixed cover is slidably connected to the inner wall of the flight controller body.

[0010] Preferably, a battery is fixedly connected to the upper surface of the base plate, and the battery is electrically connected to the flight controller body through a wire.

[0011] Preferably, a protective frame is fixedly connected to the right side of the fixed cover, and the bottom surface of the protective frame is fixedly connected to the upper surface of the bottom plate.

[0012] Preferably, four reinforcement blocks are fixedly connected to the inner wall of the protective frame, and the bottom surface of each reinforcement block is fixedly connected to the upper surface of the bottom plate.

[0013] Preferably, four limiting posts are fixedly connected to the bottom surface of the flight controller body, and the outer surface of each limiting post is slidably connected to the inner wall of the bottom plate.

[0014] Preferably, three air inlet slots are provided on the front of the protective frame, and a fan is fixedly connected to the inner wall of the protective frame.

[0015] In summary, the technical effects and advantages of this application are:

[0016] 1. By arranging the fixed block, the limiting cylinder, the first spring, the movable column, the limiting block and the movable frame, the movable frame can be moved left and right when the staff pushes the movable frame. At the same time, the movement of the movable frame can drive the movable column to move. In the process of the movement of the movable column, the limiting block on the surface can be driven to move. The movement of the movable column can also squeeze the first spring inside the limiting cylinder. When the limiting block moves out of the flight controller body, the limiting effect of the flight controller body can be released, thereby facilitating the disassembly of the flight controller body and, conversely, facilitating the subsequent installation work.

[0017] 2. By providing the latch and the second spring, the latch can facilitate the moving frame to be moved to the disassembly position and then fixed, thereby preventing the moving frame from resetting during the disassembly and assembly process. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 This is a schematic diagram of the three-dimensional structure of the bottom plate of the utility model;

[0019] Figure 2 This is a schematic diagram of the structure of the protective cover of the utility model in a cutaway perspective;

[0020] Figure 3This is a schematic diagram of the three-dimensional structure of the bottom plate of the utility model;

[0021] Figure 4 This is a schematic diagram of the cross-sectional structure of the flight controller body of the present invention;

[0022] Figure 5 It is a schematic diagram of the structure of the limiting cylinder of the utility model in a sectional three-dimensional manner.

[0023] In the figure: 1. Base plate; 2. Flight controller body; 3. Mounting block; 4. Bolt; 5. Protective frame; 6. Fan; 7. Air inlet slot; 8. Fixed cover; 9. Reinforcement block; 10. Battery; 11. Moving frame; 12. Limiting column; 13. Fixed block; 14. Limiting cylinder; 15. Moving column; 16. Limiting block; 17. First spring; 18. Latch; 19. Second spring. DETAILED DESCRIPTION

[0024] 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.

[0025] Reference Figure 1-5 A flight control for an unmanned aerial vehicle includes a base plate 1, a flight controller body 2 is arranged above the base plate 1, the bottom surface of the flight controller body 2 is in contact with the upper surface of the base plate 1, two fixing blocks 13 are fixedly connected to the upper surface of the base plate 1, and two mounting blocks 3 are fixedly connected to the two side surfaces of the base plate 1, and the inner wall of each mounting block 3 is threaded with a bolt 4. By arranging the mounting blocks 3 and the bolts 4, the base plate 1 of the device can be firmly fixed so that it can be used stably.

[0026] The inner wall of each fixed block 13 is fixedly connected to a limiting cylinder 14, and the inner wall of each limiting cylinder 14 is slidably connected to two movable columns 15. The upper surface of the base plate 1 is fixedly connected to a fixed cover 8, and the outer surface of the fixed cover 8 is slidably connected to the inner wall of the flight controller body 2. By setting the fixed cover 8, it can provide good protection for the battery 10 to avoid damage during use.

[0027] One end of each group of movable columns 15 that is away from each other is fixedly connected to a limit block 16, and the outer surface of each limit block 16 is slidably connected to the inner wall of the flight controller body 2. The upper surface of the base plate 1 is fixedly connected to a battery 10, and the battery 10 is electrically connected to the flight controller body 2 through a wire. By setting up the battery 10, it can provide the flight controller body 2 with power consumption during operation, so that it can be used stably.

[0028] The ends of each group of movable columns 15 that are close to each other are fixedly connected to the first spring 17, and the ends of each group of first springs 17 that are close to each other are fixedly connected to the inner wall of the limiting cylinder 14. The right side of the fixed cover 8 is fixedly connected to the protective frame 5, and the bottom surface of the protective frame 5 is fixedly connected to the upper surface of the base plate 1. By setting the protective frame 5, a certain protection effect can be provided for the surrounding area of ​​the device, and a supporting and fixed platform can also be provided.

[0029] The outer surface of each movable column 15 is fixedly connected to the movable frame 11, and the outer surface of each movable frame 11 is slidably connected to the inner wall of the base plate 1. The inner wall of the protective frame 5 is fixedly connected to four reinforcement blocks 9, and the bottom surface of each reinforcement block 9 is fixedly connected to the upper surface of the base plate 1. By setting the reinforcement blocks 9, the stability effect of the protective frame 5 can be further improved to avoid separation during use.

[0030] The inner wall of each mobile frame 11 is slidably connected with a pin 18, and the side of each group of mobile frames 11 close to each other is fixedly connected with a second spring 19. The bottom surface of the flight controller body 2 is fixedly connected with four limit columns 12, and the outer surface of each limit column 12 is slidably connected to the inner wall of the base plate 1. By setting the limit columns 12, the flight controller body 2 can be conveniently placed and installed, and at the same time, it can also have a certain limiting effect.

[0031] One end of each group of second springs 19 that is close to each other is fixedly connected to the outer surface of the pin 18. Three air inlet slots 7 are provided on the front of the protective frame 5. The inner wall of the protective frame 5 is fixedly connected to a fan 6. By setting the air inlet slots 7 and the fan 6, the fan 6 can improve the heat dissipation effect of the device, and the air inlet slots 7 can increase the air intake during heat dissipation.

[0032] The working principle of the present invention is as follows: when in use, the staff first connects the power supply of the fan 6 and the battery 10 of the device to make it in a stable power-on state, and then the staff fixes the bottom plate 1 to the inside of the drone through four bolts 4, and then the staff manually pushes the mobile frame 11 and pulls the latch 18 on the surface of the mobile frame 11 at the same time. When the latch 18 moves, it can squeeze the second spring 19. At the same time, when the mobile frame 11 is pushed by the staff, the mobile frame 11 can move left and right. Then the movement of the mobile frame 11 can drive the mobile column 15 to move, and in the process of the movement of the mobile column 15, it can drive the limit block 16 on the surface to move, and the movement of the mobile column 15 can also move the inner limit cylinder 14. The first spring 17 of the part is squeezed until the movable frame 11 can be moved to the appropriate position and then the latch 18 is released. The latch 18 can be rebound to the fixed block 13 for limiting under the action of the second spring 19 to prevent the movable frame 11 from resetting during disassembly and assembly. Then the flight controller body 2 can be placed on the surface of the base plate 1 through the limiting column 12, and then the staff pulls out the latch 18 again. After that, the movable frame 11, the movable column 15 and the limiting block 16 can be reset under the action of the first spring 17, so that the limiting block 16 can be inserted into the flight controller body 2 for fixed installation, and then the fan 6 and the battery 10 can be turned on to work. When disassembly work is required, the same method can be used for disassembly.

[0033] 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.

[0034] 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.

[0035] 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 base plate (1), characterized in that: A flight controller body (2) is provided above the base plate (1), the bottom surface of the flight controller body (2) contacts the upper surface of the base plate (1), and the upper surface of the base plate (1) is fixedly connected to two fixed blocks (13), the inner wall of each fixed block (13) is fixedly connected to a limiting cylinder (14), the inner wall of each limiting cylinder (14) is slidably connected to two moving columns (15), and the ends of each group of moving columns (15) that are away from each other are fixedly connected to a limiting block (16), and the outer surface of each limiting block (16) is slidably connected to the inner wall of the flight controller body (2), and each group of moving columns (15) is mutually fixedly connected to a limiting block (16). The ends close to each other are fixedly connected to a first spring (17), the ends of each group of the first springs (17) close to each other are fixedly connected to the inner wall of the limiting cylinder (14), the outer surface of each of the movable columns (15) is fixedly connected to a movable frame (11), the outer surface of each of the movable frames (11) is slidably connected to the inner wall of the bottom plate (1), the inner wall of each of the movable frames (11) is slidably connected to a latch (18), the side surfaces of each group of the movable frames (11) close to each other are fixedly connected to a second spring (19), and the ends of each group of the second springs (19) close to each other are fixedly connected to the outer surface of the latch (18).

2. The UAV flight controller according to claim 1, characterized in that: Two mounting blocks (3) are fixedly connected to both side surfaces of the base plate (1), and the inner wall of each mounting block (3) is threadedly connected with a bolt (4).

3. The UAV flight controller according to claim 1, characterized in that: A fixed cover (8) is fixedly connected to the upper surface of the base plate (1), and the outer surface of the fixed cover (8) is slidably connected to the inner wall of the flight controller body (2).

4. The UAV flight controller according to claim 1, characterized in that: A storage battery (10) is fixedly connected to the upper surface of the base plate (1), and the storage battery (10) is electrically connected to the flight controller body (2) via a wire.

5. The UAV flight controller according to claim 3, characterized in that: The right side of the fixed cover (8) is fixedly connected to a protective frame (5), and the bottom surface of the protective frame (5) is fixedly connected to the upper surface of the bottom plate (1).

6. The UAV flight controller according to claim 5, characterized in that: Four reinforcement blocks (9) are fixedly connected to the inner wall of the protection frame (5), and the bottom surface of each reinforcement block (9) is fixedly connected to the upper surface of the bottom plate (1).

7. The UAV flight controller according to claim 1, characterized in that: Four limiting columns (12) are fixedly connected to the bottom surface of the flight controller body (2), and the outer surface of each limiting column (12) is slidably connected to the inner wall of the bottom plate (1).

8. The UAV flight controller according to claim 5, characterized in that: Three air inlet slots (7) are provided on the front of the protection frame (5), and a fan (6) is fixedly connected to the inner wall of the protection frame (5).

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