Flight control module integrated support with heat dissipation channel

Abstract

The utility model discloses a flight control module integrated support with a heat dissipation channel, which comprises an integrated support main body, a mounting cavity is arranged above the integrated support main body, a heat dissipation air channel is arranged below the integrated support main body, and a cooling structure is arranged between the heat dissipation air channel and the mounting cavity. The heat dissipation end of the cooling structure is subjected to heat dissipation through the heat dissipation air duct; and the flight control system is fixedly arranged in the mounting cavity, and the bottom of the flight control system is in contact with the cooling end of the cooling structure, so that heat dissipation of the flight control system is realized. According to the integrated support, heat generated by the flight control system can be timely conducted out through the heat dissipation air channel and the cooling structure; and the temperature of the flight control system in the operation process is kept in a reasonable range, so that the stability and the reliability of the system are improved.

Description

Technical Field

[0001] This utility model relates to an integrated bracket, specifically to an integrated bracket for a flight control module with a heat dissipation channel. Background Technology

[0002] Against the backdrop of rapid development in drone technology, the performance and stability of flight control systems have become key factors in drone design and application.

[0003] Flight control systems generate a significant amount of heat during operation. Insufficient heat dissipation can lead to overheating, affecting performance and lifespan. Traditional flight control system integrated brackets often lack effective heat dissipation channels, preventing heat from dissipating in a timely manner and consequently impacting flight stability.

[0004] Existing flight control systems typically require the disassembly of multiple components during installation and replacement, making maintenance cumbersome. This not only increases operation time but also places higher demands on the skills of operators, reducing equipment availability and work efficiency. Utility Model Content

[0005] The technical problem to be solved by this utility model is to provide a flight control module integrated bracket with heat dissipation channels, so as to solve the problems existing in the background art.

[0006] The flight control module integrated bracket with heat dissipation channels of this utility model is achieved through the following technical solutions, including:

[0007] An integrated bracket body is provided, with an installation cavity at the top and a heat dissipation duct at the bottom. A cooling structure is provided between the heat dissipation duct and the installation cavity, and the heat dissipation end of the cooling structure is cooled through the heat dissipation duct.

[0008] The flight control system is fixedly installed in the mounting cavity, and the bottom of the flight control system is in contact with the cooling end of the cooling structure, thereby achieving heat dissipation of the flight control system.

[0009] As a preferred technical solution, a cover plate is provided on the top of the integrated bracket body to seal the mounting cavity; a connecting joint is provided on the top of the flight control system, and the connecting joint passes through the cover plate to connect with the connecting groove on the UAV body to realize the flight control of the UAV body.

[0010] As a preferred technical solution, the mounting cavity of the integrated bracket body is provided with mounting positions on all four sides, and the flight control system is placed on the mounting positions and fixed by screws; the cooling end of the cooling structure is placed in the mounting cavity, and the cooling end of the cooling structure is in contact with the bottom of the flight control system.

[0011] As a preferred technical solution, the cooling structure includes a fixed cavity disposed between the mounting cavity and the heat dissipation duct, a heat-conducting plate, and a semiconductor cooling chip;

[0012] The thermoelectric cooler is fixed in the cavity, and the heat-conducting plate is placed on the cooling end of the thermoelectric cooler. A heat dissipation fin is provided above the heat dissipation duct, and the heat dissipation fin is in contact with the heating end of the thermoelectric cooler, thereby dissipating heat from the thermoelectric cooler.

[0013] As a preferred technical solution, a connecting seat is provided below the cover plate, and the connecting seat is placed inside the mounting cavity and positioned by a positioning structure;

[0014] The positioning structure includes a spring groove and a positioning ball disposed on the connecting seat; the positioning ball is positioned at the end of the spring groove, and a compression spring is disposed between the positioning ball and the spring groove. The compression spring compresses the positioning ball to be placed in the positioning hole of the mounting cavity, thereby realizing the positioning and installation of the cover plate.

[0015] As a preferred technical solution, the side of the integrated bracket body is provided with a mounting plate, and the mounting plate is provided with a locking screw, which is used to fix the integrated bracket body to the drone body.

[0016] The beneficial effects of this utility model are:

[0017] This utility model's integrated bracket, through its heat dissipation duct and cooling structure, can promptly dissipate the heat generated by the flight control system, ensuring that the temperature of the flight control system remains within a reasonable range during operation, thereby improving the system's stability and reliability.

[0018] This invention, through its mounting position and positioning structure, makes the fixing and replacement of the flight control system more convenient and simplifies the maintenance process. Attached Figure Description

[0019] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0020] Figure 1 This is a three-dimensional structural diagram of the present invention;

[0021] Figure 2 This is a schematic diagram of the exploded structure of this utility model;

[0022] Figure 3 This is a schematic diagram of the cooling structure of this utility model;

[0023] Figure 4 This is a schematic diagram of the positioning structure of this utility model.

[0024] 1. Integrated bracket body; 2. Flight control system; 3. Mounting cavity; 4. Heat dissipation duct; 5. Cover plate; 6. Connecting joint; 7. Mounting position; 8. Fixing cavity; 9. Heat conduction plate; 10. Semiconductor cooling chip; 11. Heat dissipation fins; 12. Connecting seat; 13. Spring groove; 14. Positioning ball; 15. Mounting plate; 16. Locking screw. Detailed Implementation

[0025] All features disclosed in this specification, or all steps in all disclosed methods or processes, may be combined in any way, except for mutually exclusive features and / or steps.

[0026] like Figures 1-4 As shown, the present invention provides a flight control module integration bracket with a heat dissipation channel, comprising:

[0027] An integrated bracket body 1 is provided with an installation cavity 3 on the upper part of the integrated bracket body 1 and a heat dissipation duct 4 on the lower part of the integrated bracket body 1. A cooling structure is provided between the heat dissipation duct 4 and the installation cavity 3, and heat dissipation is provided to the heat dissipation end of the cooling structure through the heat dissipation duct 4.

[0028] Flight control system 2 is fixedly installed in mounting cavity 3, and the bottom of flight control system 2 is in contact with the cooling end of cooling structure, thereby realizing heat dissipation of flight control system 2.

[0029] The integrated bracket body 1 has a cover plate 5 on its upper part, which closes the mounting cavity 3. The flight control system 2 has a connecting joint 6 on its upper part, which passes through the cover plate 5 and connects to the connecting groove on the UAV body to realize the flight control of the UAV body.

[0030] The integrated bracket body 1 has mounting positions 7 around its mounting cavity 3, and the flight control system 2 is placed on the mounting positions 7 and fixed by screws; the cooling end of the cooling structure is placed inside the mounting cavity 3 and is in contact with the bottom of the flight control system 2.

[0031] In order to dissipate heat from the flight control system 2, in this embodiment, the cooling structure includes a fixed cavity 8, a heat conduction plate 9, and a semiconductor cooling chip 10 disposed between the mounting cavity 3 and the heat dissipation duct 4.

[0032] The semiconductor cooling chip 10 is fixed in the fixed cavity 8, and the heat-conducting plate 9 is disposed on the cooling end of the semiconductor cooling chip 10; a heat dissipation fin 11 is disposed above the heat dissipation air duct 4, and the heat dissipation fin 11 is in contact with the heat-generating end of the semiconductor cooling chip 10, thereby dissipating heat from the semiconductor cooling chip 10.

[0033] In order to install the cover plate 5, in this embodiment, a connecting seat 12 is provided below the cover plate 5, and the connecting seat 12 is placed inside the mounting cavity 3 and positioned by a positioning structure.

[0034] The positioning structure includes a spring groove 13 and a positioning ball 14 disposed on the connecting seat 12; the positioning ball 14 is positioned at the end of the spring groove 13, and a compression spring is disposed between the positioning ball 14 and the spring groove 13. The positioning ball 14 is placed in the positioning hole of the mounting cavity 3 by the compression spring, thereby realizing the positioning and installation of the cover plate 5.

[0035] In order to install the integrated bracket body 1, in this embodiment, the side of the integrated bracket body 1 is provided with a mounting plate 15, and the mounting plate 15 is provided with a locking screw 16, which is used to fix the integrated bracket body 1 to the drone body.

[0036] This utility model's integrated bracket, through its heat dissipation duct and cooling structure, can promptly dissipate the heat generated by the flight control system, ensuring that the temperature of the flight control system remains within a reasonable range during operation, thereby improving the system's stability and reliability. Furthermore, the mounting position and positioning structure make fixing and replacing the flight control system more convenient, simplifying the maintenance process.

[0037] The above description is merely a specific embodiment of this utility model, but the protection scope of this utility model is not limited thereto. Any changes or substitutions conceived without inventive effort should be included within the protection scope of this utility model. Therefore, the protection scope of this utility model should be determined by the scope defined in the claims.

Claims

1. A flight control module integrated support with heat dissipation channels, characterized in that, include: An integrated bracket body (1) is provided with an installation cavity (3) on the upper part of the integrated bracket body (1) and a heat dissipation duct (4) is provided on the lower part of the integrated bracket body (1). A cooling structure is provided between the heat dissipation duct (4) and the installation cavity (3), and the heat dissipation end of the cooling structure is dissipated through the heat dissipation duct (4). The flight control system (2) is fixedly installed in the mounting cavity (3), and the bottom of the flight control system (2) is in contact with the cooling end of the cooling structure, thereby realizing the heat dissipation of the flight control system (2).

2. The flight control module integrated support with heat dissipation channels of claim 1, wherein: The integrated bracket body (1) is provided with a cover plate (5) above it, which closes the mounting cavity (3); the flight control system (2) is provided with a connecting joint (6) above it, and the connecting joint (6) passes through the cover plate (5) and connects to the connecting groove on the UAV body to realize the flight control of the UAV body.

3. The flight control module integrated support with heat dissipation channels of claim 1, wherein: The mounting cavity (3) of the integrated bracket body (1) is provided with mounting positions (7) around it, and the flight control system (2) is placed on the mounting position (7) and fixed by screws; the cooling end of the cooling structure is placed in the mounting cavity (3), and the cooling end of the cooling structure is in contact with the bottom of the flight control system (2).

4. The flight control module integration bracket with heat dissipation channel according to claim 1, characterized in that: The cooling structure includes a fixed cavity (8) disposed between the mounting cavity (3) and the heat dissipation duct (4), a heat-conducting plate (9), and a semiconductor cooling chip (10); The semiconductor cooling chip (10) is fixed in the fixed cavity (8), and the heat-conducting plate (9) is disposed on the cooling end of the semiconductor cooling chip (10); a heat dissipation fin (11) is disposed above the heat dissipation duct (4), and the heat dissipation fin (11) contacts the heat-generating end of the semiconductor cooling chip (10) to dissipate heat from the semiconductor cooling chip (10).

5. The integrated support for flight control module with heat dissipation channels of claim 2, wherein: A connecting seat (12) is provided below the cover plate (5), and the connecting seat (12) is placed inside the mounting cavity (3) and positioned by a positioning structure; The positioning structure includes a spring groove (13) and a positioning ball (14) disposed on the connecting seat (12); the positioning ball (14) is positioned at the end of the spring groove (13), and a compression spring is disposed between the positioning ball (14) and the spring groove (13). The positioning ball (14) is placed in the positioning hole of the mounting cavity (3) by the compression spring, thereby realizing the positioning and installation of the cover plate (5).

6. The flight control module integrated support with heat dissipation channels of claim 1, wherein: The integrated bracket body (1) has a mounting plate (15) on its side, and a locking screw (16) is provided on the mounting plate (15). The integrated bracket body (1) is fixed to the drone body by the locking screw (16).

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