Flying tower structure and crossing machine

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a flying tower structure and a crossing air.The flying tower structure comprises a flying control plate, an electric adjusting plate and a damping assembly, the damping assembly comprises a fixing column and a damping sleeve, one end of the damping sleeve penetrates through the flying control plate, and the other end of the damping sleeve penetrates through the electric adjusting plate; the damping sleeve is of an elastic and hollow cylinder structure, and the fixing column penetrates through the damping sleeve. According to the utility model, the vibration influence of the fuselage on the flight control board and the electronic speed controller board is isolated through the damping assembly comprising the elastic damping sleeve, and meanwhile, the environment heat dissipation space of the flight control board and the electronic speed controller board is increased to a greater extent without any additional shell and cover plate, so that the heat dissipation performance is improved; and the influence of a redundant shell on wind resistance and the load of the system are also reduced.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles (UAVs), in particular to a flying tower structure and a flying drone. Background Art

[0002] With the rapid development of drone technology, especially in the racing arena, the integration, lightweighting, and vibration resistance of electronic components have become increasingly important. To maintain excellent controllability during high-speed flight, the flight control and electronic control boards must not only be modularized to reduce weight but also possess faster response times to ensure the drone can flexibly operate in complex environments. Furthermore, improvements to heat dissipation and vibration reduction systems are crucial. Adopting more convenient and effective heat dissipation and vibration reduction methods can reduce the impact of vibration and heat generation during high-power operation on electronic components, thereby improving overall stability, electronic lifespan, and flight accuracy.

[0003] In the prior art, during the flight of a FPV drone, the flight control board and the electronic control board on the main frame platform are susceptible to external factors and vibration. This vibration can affect the components of the flight control board, causing damage and uncontrollable damage. Conventional flight control shock absorption systems, while improving the shock absorption effect, also increase the overall weight, affecting heat dissipation and wind resistance during operation. For example, Chinese patent publication number CN205186542U discloses a UAV flight control shock absorption structure. When the drone is in flight at high speeds and in various postures, the fuselage inevitably resonates due to the influence of motor rotation frequency and air friction. This structure isolates the vibration generated by the fuselage through a 45-degree shock-absorbing bracket and shock-absorbing column at the bottom, thereby minimizing the impact of the fuselage vibration on the flight control board in the cover.

[0004] While the aforementioned patented technology effectively isolates vibrations from the flight control board's electronic control panel and the aircraft itself, the inclusion of a cover plate results in poor heat dissipation from the flight control board's electronic control panel, potentially posing potential risks to PCB components and the system, such as accelerated component aging and system shutdown caused by overheating. Furthermore, the aforementioned patented technology adds multiple structures and components, increasing the load on the drone and hindering its overall lightweight design. Utility Model Content

[0005] In view of this, the purpose of the present invention is to provide a fly tower structure and a flying drone, so as to at least solve the problem that the existing technology introduces a shock-absorbing structure, resulting in poor heat dissipation of the heat dissipation flight control board and the electric adjustment board, which is not conducive to overall lightweighting.

[0006] The utility model solves the above technical problems through the following technical means:

[0007] The first aspect of the present invention provides a fly tower structure, including a flight control board, an electric adjustment board and a shock-absorbing assembly, the shock-absorbing assembly including a fixed column and a shock-absorbing sleeve, one end of the shock-absorbing sleeve passes through the flight control board, and the other end passes through the electric adjustment board, the shock-absorbing sleeve is an elastic and hollow cylindrical structure, and the fixed column passes through the shock-absorbing sleeve.

[0008] In combination with the first aspect, in some embodiments, there are four shock absorbing assemblies, and the four shock absorbing assemblies are respectively arranged at four corners of the flight control board and the electric adjustment board.

[0009] In combination with the first aspect, in some embodiments, the flight control board and the electric adjustment board have mounting holes at the four corners, and the mounting holes on the flight control board and the mounting holes on the electric adjustment board correspond one to one, and one end of the shock-absorbing sleeve passes through the mounting hole of the flight control board, and the other end passes through the mounting hole of the electric adjustment board.

[0010] In combination with the first aspect, in some embodiments, the shock-absorbing sleeve includes an upper section, a middle section, and a lower section that are integrally formed and coaxially arranged, the upper section is located on the side of the flight control board facing away from the electric adjustment board, the middle section is located between the flight control board and the electric adjustment board, and the lower section is located on the side of the electric adjustment board facing away from the flight control board.

[0011] In combination with the first aspect, in some embodiments, the outer diameters of the upper section, the middle section and the lower section of the cylinder are all the same, and there is a first connecting cylinder between the upper section and the middle section of the cylinder, and between the middle section and the lower section of the cylinder. The first connecting cylinder is coaxially arranged with the middle section of the cylinder, and the outer diameter of the first connecting cylinder is smaller than the outer diameter of the middle section of the cylinder. The first connecting cylinder is inserted into the corresponding mounting hole.

[0012] In combination with the first aspect, in some embodiments, the shock-absorbing sleeve includes two coaxially arranged sleeve members, and the two sleeve members are respectively installed on the flight control board and the electric adjustment board. The sleeve member includes a cylinder body and a second connecting cylinder located in the middle of the cylinder body. The outer diameter of the second connecting cylinder is smaller than the outer diameter of the cylinder body, and the second connecting cylinder is passed through the corresponding mounting hole.

[0013] A second aspect of the present invention provides a flying drone, comprising the fly tower structure described in the first aspect.

[0014] The utility model is suitable for the fly tower structure of a racing drone. It isolates the vibration influence of the fuselage on the flight control board and the electric adjustment board through a shock-absorbing component including an elastic shock-absorbing sleeve. At the same time, without any additional shell or cover, it increases the space for the flight control board and the electric adjustment board to dissipate heat to the environment to a greater extent, improves the heat dissipation performance, and reduces the influence of the redundant shell on the wind resistance and the load of the system. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 1 is a schematic structural diagram of a fly tower structure according to Example 1;

[0016] Figure 2 This is a schematic diagram of the exploded structure of a fly tower structure in Example 1;

[0017] Figure 3 is an enlarged structural diagram of the shock-absorbing sleeve in Example 2;

[0018] Among them, the flight control board 100, the electric adjustment board 200, the fixing column 310, the shock-absorbing sleeve 320, the upper section of the tube 321, the middle section of the tube 322, the lower section of the tube 323, the first connecting tube 324, the tube body 325, the second connecting tube 326, and the mounting hole 001. DETAILED DESCRIPTION

[0019] The following describes the implementation of the present invention through specific embodiments. Those skilled in the art can understand the advantages and effects of the present invention from the content disclosed in this specification. It should be noted that the illustrations provided in the following embodiments are for illustrative purposes only and are only schematic diagrams, not actual drawings. They should not be understood as limiting the present invention. In order to better illustrate the embodiments of the present invention, some parts in the figures may be omitted, enlarged or reduced, and do not represent the dimensions of the actual product. It is understandable to those skilled in the art that some well-known structures and their descriptions may be omitted in the figures.

[0020] The same or similar numbers in the figures of the embodiments of the present invention correspond to the same or similar parts. In the description of the present invention, it should be understood that if the terms "up", "down", "left", "right", "front", "back", etc. indicate directions or positional relationships, they are based on the directions or positional relationships shown in the figures. This is only for the convenience of describing the present invention and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific direction, be constructed and operated in a specific direction. Therefore, the terms describing the positional relationship in the figures are only used for illustrative purposes and cannot be understood as limitations on the present invention. For ordinary technicians in this field, the specific meanings of the above terms can be understood according to specific circumstances. Example

[0021] Please refer to Figure 1 and Figure 2 :

[0022] The utility model provides a fly tower structure suitable for a racing drone, including a flight control board 100, an electric adjustment board 200 and a shock-absorbing assembly. The shock-absorbing assembly includes a fixed column 310 and a shock-absorbing sleeve 320. One end of the shock-absorbing sleeve 320 passes through the flight control board 100, and the other end passes through the electric adjustment board 200. The shock-absorbing sleeve 320 is an elastic cylindrical structure with a hollow interior, and the fixed column 310 passes through the shock-absorbing sleeve 320.

[0023] In this embodiment, the shock absorbing sleeve 320 is made of elastic silicone or rubber material, so that it has a good buffering and shock absorbing effect. The fixing column 310 is a threaded column with a threaded outer wall so as to be threadedly connected to the external circuit board.

[0024] In this embodiment, the flight control board 100 serves as the control board for the quadcopter drone. It houses a main control chip and several peripheral circuit interfaces. As the control module for the entire drone system, it is responsible for driving and controlling other modules. The electric control board 200 serves as the driver board for the quadcopter drone. It houses the motor drive circuits and receives control signals from the flight control board 100 to drive the motors.

[0025] There are four shock-absorbing assemblies, which are respectively arranged at the four corners of the flight control board 100 and the electric adjustment board 200. Specifically, there are mounting holes 001 at each of the four corners of the flight control board 100 and the electric adjustment board 200, and the mounting holes 001 on the flight control board 100 correspond one-to-one with the mounting holes 001 on the electric adjustment board 200. One end of the shock-absorbing sleeve 320 passes through the mounting hole 001 of the flight control board 100, and the other end passes through the mounting hole 001 of the electric adjustment board 200.

[0026] In this embodiment, the mounting hole 001 can be a circular through hole passing through the flight control board 100 and the electric adjustment board 200, or it can be an arc-shaped notch located at the four corners of the flight control board 100 and the electric adjustment board 200, as long as it can achieve convenient installation of the shock absorber assembly.

[0027] In this embodiment, the shock-absorbing sleeve 320 includes an integrally formed, coaxially arranged upper section 321, a middle section 322, and a lower section 323. The upper section 321 is located on the side of the flight control board 100 facing away from the electric adjustment board 200, the middle section 322 is located between the flight control board 100 and the electric adjustment board 200, and the lower section 323 is located on the side of the electric adjustment board 200 facing away from the flight control board 100. The upper section 321, the middle section 322, and the lower section 323 all have the same outer diameter. A first connecting tube 324 is located between the upper section 321 and the middle section 322, and between the middle section 322 and the lower section 323. The first connecting tube 324 is coaxially arranged with the middle section 322, and its outer diameter is smaller than that of the middle section 322. The first connecting tube 324 is inserted into the corresponding mounting hole 001.

[0028] The flight control board 100 and the electric adjustment board 200 are designed with mounting holes 001 for installing shock-absorbing components at the four corners of the PCB board. The mounting holes 001 of the flight control board 100 and the electric adjustment board 200 on the same plane are consistent and overlapped. By installing the shock-absorbing components, the electric adjustment board 200 and the flight control board 100 are made parallel to each other. Finally, the fly tower body and the drone frame are fixed by the fixing column 310. The shock-absorbing sleeve 320 is made of silicone or rubber material and has a certain degree of elasticity. Therefore, during assembly, the upper section 321 and the lower section 323 of the shock-absorbing sleeve 320 can be deformed and squeezed into the mounting hole 001 and snapped together. Then, the first connecting tube is inserted into the mounting hole 001, and the middle section 322 of the tube is located between the flight control board 100 and the electric adjustment board 200. The fixing column 310 is passed through the shock-absorbing sleeve 320 and connected to the external circuit board. Example

[0029] Please refer to Figure 3 The fly tower structure of this embodiment differs from that of Example 1 in the structural design of the shock-absorbing sleeve 320. The shock-absorbing sleeve 320 of this embodiment adopts a split design. Specifically, the shock-absorbing sleeve 320 of this embodiment includes two coaxially arranged sleeve members, which are respectively mounted on the flight control board 100 and the electric adjustment board 200. The sleeve member includes a barrel 325 and a second connecting barrel 326 located in the middle of the barrel 325. The outer diameter of the second connecting barrel 326 is smaller than that of the barrel 325, and the second connecting barrel 326 is inserted into the corresponding mounting hole 001. The two sleeve members in each shock-absorbing assembly are installed in contact to form the shock-absorbing sleeve 320. During assembly, one end of the sleeve member is squeezed into the mounting hole 001, so that the second connecting barrel 326 is inserted into the mounting hole 001, thereby achieving installation of the sleeve member on the flight control board 100 and the electric adjustment board 200.

[0030] The present invention uses an integrated or separate shock-absorbing sleeve 320 to isolate the vibration impact of the fuselage on the flight control board 100 and the electric adjustment board 200. At the same time, without any additional housing or cover, the space for the flight control board 100 and the electric adjustment board 200 to dissipate heat to the environment is increased to a greater extent, thereby improving the heat dissipation performance and reducing the impact of the redundant housing on wind resistance and the load on the system.

[0031] An embodiment of the present invention further discloses a flying drone, which includes the fly tower structure described in Example 1 or Example 2.

[0032] During actual flight, the drone's rapid flight and various postures inevitably generate high-frequency vibrations due to the influence of motor rotation frequency and air friction. This vibration is transmitted through the fixing column 310 to the fly tower composed of the flight control board 100 and the electric control board 200. The vibrations are isolated by the integrated or separate shock-absorbing sleeve 320, minimizing the impact of the vibrations on the flight control board 100 and the electric control board 200. At the same time, the shock-absorbing component structure provides a comprehensive heat dissipation outlet. During flight, the flight control board 100 and the electric control board 200 can fully exchange heat with the surrounding air to achieve better heat dissipation. No new additional structure is introduced, thus achieving the requirement of system portability.

[0033] The above embodiments are intended only to illustrate the technical solutions of the present invention and are not intended to limit the present invention. Although the present invention has been described in detail with reference to the preferred embodiments, those skilled in the art will appreciate that modifications or equivalent substitutions may be made to the technical solutions of the present invention without departing from the spirit and scope of the technical solutions of the present invention, and such modifications or equivalent substitutions shall be encompassed by the claims of the present invention. The techniques, shapes, and structural portions not described in detail in the present invention are well known.

Claims

1. A fly tower structure, characterized in that: It includes a flight control board, an electric adjustment board and a shock-absorbing assembly. The shock-absorbing assembly includes a fixed column and a shock-absorbing sleeve. One end of the shock-absorbing sleeve passes through the flight control board, and the other end passes through the electric adjustment board. The shock-absorbing sleeve is an elastic and hollow cylindrical structure. The fixed column passes through the shock-absorbing sleeve.

2. A fly tower structure according to claim 1, characterized in that: There are four shock absorbing components, which are respectively arranged at the four corners of the flight control board and the electric adjustment board.

3. A fly tower structure according to claim 2, characterized in that: The flight control board and the electric adjustment board have mounting holes at the four corners, and the mounting holes on the flight control board correspond to the mounting holes on the electric adjustment board one by one. One end of the shock-absorbing sleeve passes through the mounting hole of the flight control board, and the other end passes through the mounting hole of the electric adjustment board.

4. A fly tower structure according to claim 3, characterized in that: The shock-absorbing sleeve includes an upper section, a middle section and a lower section that are integrally formed and coaxially arranged. The upper section is located on the side of the flight control board facing away from the electric adjustment board, the middle section is located between the flight control board and the electric adjustment board, and the lower section is located on the side of the electric adjustment board facing away from the flight control board.

5. A fly tower structure according to claim 4, characterized in that: The outer diameters of the upper section, middle section and lower section of the cylinder are all the same. There is a first connecting cylinder between the upper section and the middle section, and between the middle section and the lower section. The first connecting cylinder is coaxially arranged with the middle section of the cylinder, and the outer diameter of the first connecting cylinder is smaller than the outer diameter of the middle section of the cylinder. The first connecting cylinder is inserted into the corresponding mounting hole.

6. A fly tower structure according to claim 3, characterized in that: The shock-absorbing sleeve includes two coaxially arranged sleeve members, which are respectively installed on the flight control board and the electric adjustment board. The sleeve member includes a cylinder body and a second connecting cylinder located in the middle of the cylinder body. The outer diameter of the second connecting cylinder is smaller than the outer diameter of the cylinder body, and the second connecting cylinder is inserted into the corresponding mounting hole.

7. A flying drone, characterized in that: It includes the fly tower structure described in any one of claims 1 to 6.

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