Unmanned aerial vehicle flight control

Abstract

The utility model provides an unmanned aerial vehicle flight controller which comprises a protection frame, and a cover plate is arranged on the top of the protection frame. The four supporting frames are fixedly installed at the two ends of the two sides of the inner side face of the protection frame respectively, a sliding groove is formed in one side of each supporting frame, the inner side face of each sliding groove is slidably connected with a moving block, a damping rod is fixedly installed at the bottom of each moving block, and the outer side face of each damping rod is sleeved with a first spring. According to the flight control and electronic speed controller assembly of the unmanned aerial vehicle, through mutual cooperation of the protection frame, the supporting frame, the sliding groove, the moving block, the damping rod, the first spring, a positioning rod, a sliding rod, a second spring, a pressing plate and other structures, when vibration is generated, the moving block can drive the damping rod and the first spring to contract, and therefore the damping effect is achieved; the influence and damage to the flight control system are avoided, and the accuracy of the unmanned aerial vehicle in task execution is ensured.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) control technology, and in particular to a UAV flight control and electronic speed control (ESC) assembly. Background Technology

[0002] The drone flight controller is the core control system of a drone, similar to the autopilot of an airplane. It is the "brain" of the entire drone flight, and its main function is to control the drone's flight attitude and flight trajectory.

[0003] As shown in a patent application for a drone flight controller, the flight controller shell consists of an upper cover, a lower cover, and a housing. The flight controller board is fixed to the lower cover via the lower housing. One end of the housing has a power interface, a signal connector, and an antenna interface. The flight controller board includes a power module, a wireless communication module, and a CPU chip and an FPGA chip connected via an EMIF bus. The power module is connected to the power interface, and external devices are connected to the FPGA chip via the signal connector. The wireless communication module is connected to both the CPU chip and the antenna interface. This invention uses a fixed connection between the housing and the lower housing to protect the internal flight controller board, simplifying the hardware structure and further reducing its size. Multiple peripheral interfaces are configured in the peripheral mounting area on the left side of the housing, allowing for flexible configuration according to different needs without requiring interface expansion design.

[0004] However, the flight controller lacks a structure to dampen the flight control board. During the high-speed flight and tumbling of the drone, irregular vibrations of different frequencies are generated and transmitted to the flight control system, which can affect or even damage the flight control system, causing deviations when the drone performs its mission.

[0005] Therefore, it is necessary to provide a UAV flight control and ESC component to solve the above-mentioned technical problems. Utility Model Content

[0006] This utility model provides a flight control and electronic speed controller assembly for unmanned aerial vehicles (UAVs), which solves the problem that the lack of a shock-absorbing structure can easily affect and damage the flight control board, causing deviations when the UAV performs its mission.

[0007] To solve the above-mentioned technical problems, this utility model provides a drone flight control system, comprising:

[0008] A protective frame, the top of which is provided with a cover plate;

[0009] Four support frames are fixedly installed at both ends of the inner side of the protective frame. Each of the four support frames has a sliding groove on one side. A moving block is slidably connected to the inner side of the sliding groove. A damping rod is fixedly installed at the bottom of the moving block. A first spring is sleeved on the outer side of the damping rod. The bottom of the damping rod is fixedly installed at the bottom of the inner side of the sliding groove. A positioning rod is fixedly installed at the top of the moving block.

[0010] A sliding rod is slidably connected to the inside of the movable block. A pressure plate is fixedly installed on the top of the sliding rod. A through hole is opened inside the pressure plate. A second spring is sleeved on the outer side of the sliding rod. The second spring is set at the bottom of the movable block. A rubber ring is fixedly installed at the bottom of the pressure plate.

[0011] A control panel is disposed on the outer side of the positioning rod.

[0012] Preferably, a connector is fixedly installed at one end of the protective frame, and mounting plates are fixedly installed at both ends of both sides of the protective frame.

[0013] Preferably, a telescopic rod is fixedly installed on the top of the movable block, and the top of the telescopic rod is fixedly installed on the top of the inner side of the slide groove.

[0014] Preferably, a rubber pad is fixedly installed on the top of the movable block, the rubber pad is disposed at the bottom of the control board, and the pressure plate is disposed at the top of the control board.

[0015] Preferably, a limiting plate is fixedly installed at the bottom of the cover plate, and a sealing gasket is sleeved on the outer side of the limiting plate, with the bottom of the sealing gasket abutting against the top of the protective frame.

[0016] To address the aforementioned problems, this utility model also provides an electronic speed control (ESC) assembly for a drone, comprising: a fixed base, a retaining ring fixedly installed on the inner side of the fixed base, a threaded ring threadedly connected to the bottom of the inner side of the fixed base, a base plate fixedly installed at the bottom of the threaded ring, a second sealing ring provided at the top of the threaded ring, an ESC plate provided at the top of the second sealing ring, the top of the ESC plate abutting against the bottom of the retaining ring, and a first sealing ring sleeved on the outer side of the threaded ring, the top of the first sealing ring abutting against the bottom of the fixed base.

[0017] Preferably, a heat sink is fixedly installed inside the base plate, the top of the heat sink is disposed at the bottom of the power control board, and heat dissipation fins are fixedly installed at the bottom of the heat sink, which are disposed at the bottom of the base plate.

[0018] Compared with related technologies, the UAV flight control and ESC assembly provided by this utility model has the following beneficial effects:

[0019] This utility model provides a flight control and electronic speed control (ESC) assembly for a drone. The assembly consists of a protective frame, a support frame, a slide groove, a moving block, a damping rod, a first spring, a positioning rod, a slide rod, a second spring, and a pressure plate. When vibration occurs, the moving block can drive the damping rod and the first spring to retract, thereby reducing vibration and preventing damage to the flight control system, ensuring the accuracy of the drone when performing its mission. Attached Figure Description

[0020] Figure 1 A schematic diagram of the structure of a first embodiment of a UAV flight control system provided by this utility model;

[0021] Figure 2 for Figure 1 The diagram shows the internal structure of the protective frame.

[0022] Figure 3 for Figure 2 The diagram shows the support frame structure.

[0023] Figure 4 A schematic diagram of the structure of a second embodiment of a UAV flight control system provided by this utility model;

[0024] Figure 5 This is a schematic diagram of the structure of an electronic speed controller (ESC) for a drone provided by this utility model.

[0025] The following are the labels in the diagram: 1. Protective frame, 11. Mounting plate, 12. Connector, 13. Cover plate, 2. Control plate, 3. Support frame, 31. Slide groove, 32. Telescopic rod, 33. Moving block, 34. Damping rod, 35. First spring, 36. Positioning rod, 37. Rubber pad, 4. Slide rod, 41. Second spring, 42. Pressure plate, 43. Through hole, 44. Rubber ring, 5. Limiting plate, 51. Sealing gasket, 6. Fixing seat, 61. Retaining ring, 62. Threaded ring, 63. Base plate, 64. First sealing ring, 65. Second sealing ring, 7. Electrical adjustment board, 8. Heat sink, 81. Heat sink fins. Detailed Implementation

[0026] The present invention will be further described below with reference to the accompanying drawings and embodiments.

[0027] First Embodiment

[0028] Please refer to the following: Figure 1 , Figure 2 , Figure 3 ,in, Figure 1 A schematic diagram of the structure of a first embodiment of a UAV flight control system provided by this utility model; Figure 2 for Figure 1 The diagram shows the internal structure of the protective frame. Figure 3 for Figure 2 The diagram shows a support frame structure. A drone flight controller includes: a protective frame 1, with a cover plate 13 on the top of the protective frame 1;

[0029] Four support frames 3 are fixedly installed at both ends of the inner side of the protective frame 1. Each of the four support frames 3 has a sliding groove 31 on one side. The inner side of the sliding groove 31 is slidably connected to a moving block 33. A damping rod 34 is fixedly installed at the bottom of the moving block 33. A first spring 35 is sleeved on the outer side of the damping rod 34. The bottom of the damping rod 34 is fixedly installed at the bottom of the inner side of the sliding groove 31. A positioning rod 36 is fixedly installed at the top of the moving block 33.

[0030] The slide rod 4 is slidably connected to the inside of the moving block 33. A pressure plate 42 is fixedly installed on the top of the slide rod 4. A through hole 43 is opened inside the pressure plate 42. A second spring 41 is sleeved on the outer side of the slide rod 44. The second spring 41 is set at the bottom of the moving block 33. A rubber ring 44 is fixedly installed at the bottom of the pressure plate 42.

[0031] Control panel 2 is disposed on the outer side of the positioning rod 36.

[0032] A connector 12 is fixedly installed at one end of the protective frame 1, and mounting plates 11 are fixedly installed at both ends of both sides of the protective frame 1.

[0033] A telescopic rod 32 is fixedly installed on the top of the movable block 33, and the top of the telescopic rod 32 is fixedly installed on the top of the inner side of the slide groove 31.

[0034] A rubber pad 37 is fixedly installed on the top of the movable block 33. The rubber pad 37 is located at the bottom of the control plate 2, and the pressure plate 42 is located at the top of the control plate 2.

[0035] By installing a rubber pad 37 on the top of the moving block 33 and a rubber ring 42 on the bottom of the pressure plate 42, the rubber pad 37 and the rubber ring 42 are pressed against the bottom and top of the control plate 2 respectively, thus protecting the control plate 2.

[0036] Control board 2 is a flight control board, and control board 2 and connector 12 are electrically connected;

[0037] When it is necessary to install the protective frame 1, the user can insert screws into the inside of the mounting plate 11 and then install the screws on the drone to install the protective frame 1. The cover plate 13 and the protective frame 1 are installed with screws.

[0038] The telescopic rod 32 is installed on the top of the movable block 33, which can increase the limiting effect of the movable block 33 and increase the stability of the movable block 33 when it moves up and down.

[0039] The positioning rod 36 is inserted into the control board 2, which can limit the control board 2 and prevent the control board 2 from sliding on the rubber pad 37.

[0040] When in use, the elasticity of the second spring 41 can always pull the slide rod 4 and the pressure plate 42 downward, so that the through hole 43 is inserted into the outer side of the positioning rod 36, thereby limiting the pressure plate 42 and preventing the pressure plate 42 from rotating.

[0041] The working principle of the UAV flight control system provided by this utility model is as follows:

[0042] When in use, place the control plate 2 on top of the rubber pad 37, so that the positioning rod 36 is inside the control plate 2. Then move the pressure plate 42 upward, so that the pressure plate 42 drives the slide rod 4 to slide inside the moving block 33, thereby causing the second spring 41 to contract. Then rotate the pressure plate 42, so that the pressure plate 42 rotates to the top of the control plate 2. Then release the pressure plate 42. At this time, the second spring 41 will drive the slide rod 4 to move downward, so that the slide rod 4 drives the pressure plate 42 to move downward, so that the pressure plate 42 drives the rubber ring 44 to press on the top of the control plate 2, thereby inserting the positioning rod 36 into the inner side of the through hole 43. In this way, the control plate 2 can be limited.

[0043] Then, the cover plate 13 is installed on the top of the protective frame 1 with screws. When vibration occurs during subsequent use, the moving block 33 will slide on the inner side of the slide groove 31, thereby pressing the damping rod 34 and the first spring 35. This can play a role in shock absorption and buffering of the moving block 33 and the control plate 2.

[0044] Compared with related technologies, the UAV flight control provided by this utility model has the following beneficial effects:

[0045] The protective frame 1, support frame 3, slide 31, moving block 33, damping rod 34, first spring 35, positioning rod 36, slide 4, second spring 41 and pressure plate 42 work together to reduce vibration. When vibration occurs, the moving block 33 can drive the damping rod 34 and the first spring 35 to retract, thereby reducing vibration and preventing damage to the flight control system, ensuring the accuracy of the UAV when performing missions.

[0046] Second Embodiment

[0047] Please refer to the following: Figure 4 Based on the UAV flight control provided in the first embodiment of this application, the second embodiment of this application proposes another UAV flight control. The second embodiment is merely a preferred embodiment of the first embodiment, and the implementation of the second embodiment will not affect the separate implementation of the first embodiment.

[0048] Specifically, the second embodiment of this application provides a drone flight controller that differs in that a limiting plate 5 is fixedly installed at the bottom of the cover plate 13, and a sealing gasket 51 is sleeved on the outer side of the limiting plate 5, with the bottom of the sealing gasket 51 abutting against the top of the protective frame 1.

[0049] The outer side of the limiting plate 5 is fitted with the inner side of the protective frame 1, so that it can limit the cover plate 13 when in use.

[0050] The working principle of the UAV flight control system provided by this utility model is as follows:

[0051] When in use, the user installs the cover plate 13 on the top of the protective frame 1 with screws, at which time one side of the sealing gasket 51 will abut against the top of the protective frame 1.

[0052] Compared with related technologies, the UAV flight control provided by this utility model has the following beneficial effects:

[0053] By installing the cover plate 13 on top of the protective frame 1, one side of the sealing gasket 51 abuts against the top of the protective frame 1, thereby increasing the sealing between the cover plate 13 and the protective frame 1.

[0054] Please see Figure 5 To address the aforementioned issues, this utility model also provides an electronic speed control (ESC) assembly for a drone, comprising: a fixed base 6, a retaining ring 61 fixedly mounted on the inner side of the fixed base 6, a threaded ring 62 threadedly connected to the bottom of the inner side of the fixed base 6, a base plate 63 fixedly mounted on the bottom of the threaded ring 62, a second sealing ring 65 provided on the top of the threaded ring 62, an ESC plate 7 provided on the top of the second sealing ring 65, the top of the ESC plate 7 abutting against the bottom of the retaining ring 61, and a first sealing ring 64 sleeved on the outer side of the threaded ring 62, the top of the first sealing ring 64 abutting against the bottom of the fixed base 6.

[0055] Preferably, a heat sink 81 is fixedly installed inside the base plate 63, the top of the heat sink 81 is disposed at the bottom of the power control board 7, and heat dissipation fins 81 are fixedly installed at the bottom of the heat sink 81, which are disposed at the bottom of the base plate 6.

[0056] When in use, the ESC plate 7 is placed inside the mounting base 6, so that the top of the second sealing ring 65 abuts against the bottom of the ESC plate 7. At this time, the threaded ring 62 will be threadedly connected to the inner side of the mounting base 6, thereby fixing the ESC plate 7. In this way, when the ESC plate 7 needs to be maintained in the future, it is only necessary to rotate the base plate 63, so that the base plate 63 drives the threaded ring 62 to be threadedly connected inside the mounting base 6, and the threaded ring 62 can be removed from the inner side of the mounting base 6, thereby disassembling the ESC plate 7. The operation is convenient and quick.

[0057] The first sealing ring 64 and the second sealing ring 65 cooperate with each other to increase the sealing performance inside the fixed seat 6.

[0058] The heat generated by the ESC board 7 during operation can be directed to the top of the heat dissipation fins 81 through the heat sink 8, and then dissipated through the heat dissipation fins 81, thereby increasing the heat dissipation effect of the ESC board 7.

[0059] The above description is merely an embodiment of this utility model and does not limit the patent scope of this utility model. Any equivalent structural or procedural transformations made based on the content of this utility model specification and drawings, or direct or indirect applications in other related technical fields, are similarly included within the patent protection scope of this utility model.

Claims

1. A flight control system for unmanned aerial vehicles (UAVs), characterized in that, include: A protective frame, the top of which is provided with a cover plate; Four support frames are fixedly installed at both ends of the inner side of the protective frame. Each of the four support frames has a sliding groove on one side. A moving block is slidably connected to the inner side of the sliding groove. A damping rod is fixedly installed at the bottom of the moving block. A first spring is sleeved on the outer side of the damping rod. The bottom of the damping rod is fixedly installed at the bottom of the inner side of the sliding groove. A positioning rod is fixedly installed at the top of the moving block. A sliding rod is slidably connected to the inside of the movable block. A pressure plate is fixedly installed on the top of the sliding rod. A through hole is opened inside the pressure plate. A second spring is sleeved on the outer side of the sliding rod. The second spring is set at the bottom of the movable block. A rubber ring is fixedly installed at the bottom of the pressure plate. A control panel is disposed on the outer side of the positioning rod.

2. The UAV flight control system according to claim 1, characterized in that, A connector is fixedly installed at one end of the protective frame, and mounting plates are fixedly installed at both ends of both sides of the protective frame.

3. The UAV flight control system according to claim 1, characterized in that, A telescopic rod is fixedly installed on the top of the movable block, and the top of the telescopic rod is fixedly installed on the top of the inner side of the slide groove.

4. The UAV flight control system according to claim 1, characterized in that, A rubber pad is fixedly installed on the top of the moving block, the rubber pad is located at the bottom of the control board, and the pressure plate is located at the top of the control board.

5. A UAV flight control system according to claim 1, characterized in that, A limiting plate is fixedly installed at the bottom of the cover plate, and a sealing gasket is fitted on the outer side of the limiting plate, with the bottom of the sealing gasket abutting against the top of the protective frame.

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