Bearing and heat dissipation integrated unmanned aerial vehicle engine compartment heat dissipation structure

Abstract

The utility model discloses an unmanned aerial vehicle engine compartment heat dissipation structure integrating bearing and heat dissipation, and relates to the technical field of unmanned aerial vehicles, the unmanned aerial vehicle engine compartment heat dissipation structure comprises an unmanned aerial vehicle body, an upper heat dissipation mounting plate and a lower heat dissipation mounting plate; a vertically-through mounting cavity is formed in the middle of the unmanned aerial vehicle body, and an air inlet channel and an air outlet channel are formed in the front wall face and the rear wall face of the unmanned aerial vehicle body correspondingly. The upper heat dissipation mounting plate and the lower heat dissipation mounting plate are detachably connected to an upper opening and a lower opening of the mounting cavity respectively, a plurality of upper ventilation pipes are arranged on the bottom wall of the upper heat dissipation mounting plate, a plurality of lower ventilation pipes are arranged on the bottom wall of the lower heat dissipation mounting plate, and the two ends of the upper ventilation pipes and the two ends of the lower ventilation pipes are connected with an air inlet channel and an air outlet channel respectively. A cavity formed by the upper heat dissipation mounting plate, the lower heat dissipation mounting plate and the mounting cavity is used for mounting a power mechanism. The heat dissipation function and the bearing function of the unmanned aerial vehicle engine compartment are organically combined, the integrated design of heat dissipation and bearing is achieved, and the heat dissipation problem of a power system is effectively solved.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, and more specifically to a heat dissipation structure for an integrated power compartment of an UAV that supports heat dissipation. Background Technology

[0002] With the rapid development of drone technology, its applications in military, civilian, and industrial fields are becoming increasingly widespread. The power system of a drone is one of its core components, and its performance directly affects the drone's flight performance and endurance. However, the power system generates a large amount of heat during operation. If it is not dissipated effectively and in a timely manner, it can lead to overheating of components such as the engine and motor, thereby affecting their performance and service life, and may even cause malfunctions or safety accidents.

[0003] Traditional drone cooling methods primarily rely on natural convection or simple fan cooling. However, these methods suffer from low cooling efficiency and limited heat dissipation area, making it difficult to meet the high cooling requirements of high-performance drones. Furthermore, traditional cooling designs often separate the heat sink from the fuselage structure, resulting in a large space-consuming and heavy cooling system, and complex installation and maintenance processes.

[0004] To overcome the shortcomings of existing technologies, this invention proposes an integrated heat dissipation structure for the power compartment and fuselage of a UAV. By organically combining the fuselage shell and the power structure, a highly efficient heat dissipation effect is achieved, while simplifying the installation process and improving the overall performance and reliability of the UAV. Utility Model Content

[0005] In view of this, the present invention provides a heat dissipation structure for an unmanned aerial vehicle (UAV) power compartment that integrates load-bearing and heat dissipation functions, aiming to solve the above-mentioned technical problems.

[0006] To achieve the above objectives, the present invention adopts the following technical solution:

[0007] A heat dissipation structure for an integrated power compartment of a drone, comprising:

[0008] The drone body has a vertically penetrating mounting cavity in the middle, and air inlet and outlet channels are respectively opened on the front and rear walls of the drone body.

[0009] An upper heat dissipation mounting plate and a lower heat dissipation mounting plate are detachably connected to the upper and lower openings of the mounting cavity, respectively. The bottom wall of the upper heat dissipation mounting plate has multiple upper ventilation pipes, and the bottom wall of the lower heat dissipation mounting plate has multiple lower ventilation pipes. The two ends of the upper and lower ventilation pipes are respectively connected to the air inlet channel and the air outlet channel. The cavity formed by the upper and lower heat dissipation mounting plates and the mounting cavity is used to install the power mechanism.

[0010] Through the above technical solution, this utility model establishes a vertically penetrating mounting cavity in the middle of the UAV body, and opens air inlet and outlet channels on the front and rear walls. Simultaneously, it utilizes the ventilation pipes connecting the upper and lower heat dissipation mounting plates to form a complete ventilation and heat dissipation path. This structure organically combines heat dissipation with the load-bearing function of the UAV's power compartment, achieving an integrated design of heat dissipation and load-bearing, effectively solving the heat dissipation problem of the power system, improving the performance and reliability of the UAV, and optimizing space utilization.

[0011] Preferably, in the above-mentioned integrated heat dissipation structure for the power compartment of a UAV, the exposed surface of the upper heat dissipation mounting plate and the lower heat dissipation mounting plate has an upper heat dissipation fin and a lower heat dissipation fin, respectively, which correspond to the sidewalls of the upper ventilation pipe and the lower ventilation pipe.

[0012] Preferably, in the above-mentioned integrated heat dissipation structure for the power compartment of a UAV, the upper heat dissipation mounting plate, the lower heat dissipation mounting plate, the upper ventilation pipe, the lower ventilation pipe, the upper heat dissipation fin, and the lower heat dissipation fin are all made of aluminum alloy.

[0013] Preferably, in the above-mentioned integrated heat dissipation structure for a UAV power compartment, both the upper heat dissipation mounting plate and the lower heat dissipation mounting plate are connected to the opening of the mounting cavity by bolts.

[0014] Preferably, in the above-mentioned integrated cooling structure for a UAV power compartment, a mounting bracket spanning the lower ventilation duct is fixed on the top surface of the lower cooling mounting plate, and the power mechanism is mounted on the mounting bracket.

[0015] Preferably, in the above-mentioned integrated cooling structure for the unmanned aerial vehicle power compartment, the mounting bracket is fitted to the lower ventilation duct and is made of aluminum alloy.

[0016] Preferably, in the above-mentioned integrated cooling structure for the power compartment of a UAV, the front and rear walls of the UAV body are both double-layered structures, and the air inlet and outlet channels are formed by air inlet pipes and air outlet pipes, respectively.

[0017] Preferably, in the above-mentioned integrated cooling structure for a UAV power compartment, both the air inlet pipe and the air outlet pipe are arranged at an angle, such that the air inlet pipe and the air outlet pipe form a bending angle with the upper ventilation pipe and the lower ventilation pipe, respectively.

[0018] Preferably, in the above-mentioned integrated cooling structure for the power compartment of a UAV, both the air inlet pipe and the air outlet pipe are provided with mesh panels at their openings.

[0019] Preferably, in the above-mentioned integrated cooling structure for the unmanned aerial vehicle power compartment, air vents are provided on both the upper ventilation pipe and the lower ventilation pipe.

[0020] As can be seen from the above technical solution, compared with the prior art, the present invention discloses a heat dissipation structure for an integrated power compartment of a UAV, which has the following beneficial effects:

[0021] 1. High-efficiency heat dissipation: The design incorporates a continuous mounting cavity, air inlet and outlet channels, and ventilation ducts on the upper and lower heat dissipation mounting plates, creating a complete airflow path and significantly improving heat dissipation efficiency. The addition of upper and lower heat dissipation fins further expands the heat dissipation area and enhances heat dissipation capacity. The use of aluminum alloy material leverages its excellent thermal conductivity to quickly conduct heat, further improving the heat dissipation effect.

[0022] 2. Structural Optimization and Lightweight Design: The integrated design organically combines heat dissipation with the load-bearing function of the drone's power compartment, reducing the space occupied by the heat dissipation system and optimizing the overall structure of the drone. The use of aluminum alloy material ensures heat dissipation performance while reducing the weight of the drone and improving flight performance.

[0023] 3. Ease of Installation and Maintenance: The upper and lower heat dissipation mounting plates are connected to the mounting cavity by bolts, featuring a detachable design that facilitates the installation, maintenance, and replacement of the power mechanism, reducing maintenance costs and time. The integrated design of the mounting bracket and the lower heat dissipation mounting plate makes the installation of the power mechanism more stable and further optimizes the space layout.

[0024] 4. Optimized Airflow: The inclined arrangement of the air inlet and outlet ducts, and the bends they form with the ventilation ducts, guides airflow along a predetermined path, increasing the heat exchange efficiency between the air and the heat dissipation components, while also optimizing the aerodynamic performance of the drone. Air vents on the ventilation ducts further improve airflow efficiency and enhance heat dissipation.

[0025] 5. Reliability and Durability: Mesh panels are installed at the openings of the air inlet and outlet ducts to prevent dust and debris from entering the heat dissipation channels, avoiding blockages and extending the service life of the heat dissipation system. The overall structure is made of aluminum alloy, which has good mechanical properties and corrosion resistance, improving the reliability and durability of the drone.

[0026] 6. Improved overall performance: Through the above design optimization, this utility model not only solves the problems of low heat dissipation efficiency, large space occupation of heat dissipation system and complicated installation of traditional UAVs, but also improves the overall performance of UAVs, including flight performance, reliability and service life. Attached Figure Description

[0027] 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 embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.

[0028] Figure 1 The attached figure is a schematic diagram of the integrated load-bearing and heat dissipation structure for the UAV power compartment provided by this utility model.

[0029] Figure 2 The attached figure is a cross-sectional view of the integrated load-bearing and heat dissipation structure for the UAV power compartment provided by this utility model.

[0030] Figure 3 The attached figure is a structural schematic diagram of the UAV body provided by this utility model;

[0031] Figure 4 The attached figure is a structural schematic diagram of the upper heat dissipation mounting plate provided by this utility model;

[0032] Figure 5 The attached figure is a structural schematic diagram of the lower heat dissipation mounting plate provided by this utility model.

[0033] in:

[0034] 1- The drone itself;

[0035] 11-Installation cavity; 12-Air inlet channel; 13-Air outlet channel; 14-Air inlet pipe; 15-Air outlet pipe; 16-Mesh panel;

[0036] 2-Upper heat dissipation mounting plate;

[0037] 21-Upper ventilation duct; 211-Air outlet; 22-Upper heat dissipation fins;

[0038] 3-Lower heat dissipation mounting plate;

[0039] 31-Lower ventilation duct; 32-Lower heat dissipation fins; 33-Mounting bracket. Detailed Implementation

[0040] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0041] See appendix Figure 1 To be continued Figure 5 This utility model discloses a heat dissipation structure for an integrated load-bearing and heat dissipation system for a drone's power compartment, comprising:

[0042] The drone body 1 has a vertically penetrating mounting cavity 11 in the middle, and air inlet channel 12 and air outlet channel 13 are respectively opened on the front and rear walls of the drone body 1.

[0043] The upper heat dissipation mounting plate 2 and the lower heat dissipation mounting plate 3 are detachably connected to the upper and lower openings of the mounting cavity 11, respectively. The bottom wall of the upper heat dissipation mounting plate 2 has multiple upper ventilation pipes 21, and the bottom wall of the lower heat dissipation mounting plate 3 has multiple lower ventilation pipes 31. The two ends of the upper ventilation pipes 21 and the lower ventilation pipes 31 are respectively connected to the air inlet channel 12 and the air outlet channel 13. The cavity formed by the upper heat dissipation mounting plate 2, the lower heat dissipation mounting plate 3 and the mounting cavity 11 is used to install the power mechanism.

[0044] To further optimize the above technical solution, the exposed surfaces of the upper heat dissipation mounting plate 2 and the lower heat dissipation mounting plate 3 are provided with upper heat dissipation fins 22 and lower heat dissipation fins 32, respectively, which correspond to the sidewalls of the upper ventilation duct 21 and the lower ventilation duct 31. The placement of heat dissipation fins on the exposed surfaces of the upper heat dissipation mounting plate 2 and the lower heat dissipation mounting plate 3 increases the heat dissipation area and further improves heat dissipation efficiency. The correspondence between the heat dissipation fins and the sidewalls of the ventilation ducts allows heat to be dissipated more quickly through airflow, enhancing the heat dissipation effect and helping to better control the temperature of the power system.

[0045] To further optimize the above technical solution, the upper heat dissipation mounting plate 2, lower heat dissipation mounting plate 3, upper ventilation duct 21, lower ventilation duct 31, upper heat dissipation fin 22, and lower heat dissipation fin 32 are all made of aluminum alloy. Using aluminum alloy to manufacture the heat dissipation mounting plate, ventilation duct, and heat dissipation fins is advantageous because aluminum alloy has excellent thermal conductivity, enabling rapid heat transfer and thus improving heat dissipation efficiency. Simultaneously, aluminum alloy is lightweight, minimizing the added weight of the drone and contributing to its lightweight design, thereby enhancing its flight performance.

[0046] To further optimize the above technical solution, both the upper heat dissipation mounting plate 2 and the lower heat dissipation mounting plate 3 are connected to the opening of the mounting cavity 11 by bolts. This detachable connection method facilitates the installation and removal of the heat dissipation mounting plates, making the installation, maintenance, and replacement of the power mechanism more convenient and faster, improving the maintainability of the UAV, and reducing maintenance costs and time.

[0047] To further optimize the above technical solution, a mounting bracket 33 spanning the lower ventilation duct 31 is fixed to the top surface of the lower heat dissipation mounting plate 3. The power mechanism is mounted on the mounting bracket 33. This design makes the installation of the power mechanism more stable, while making full use of the space of the heat dissipation mounting plate, further optimizing the internal spatial layout of the UAV, and improving the compactness of the structure.

[0048] To further optimize the above technical solution, the mounting bracket 33 is fitted to the lower ventilation pipe 31 and is made of aluminum alloy. On the one hand, this ensures the structural strength of the mounting bracket 33, which can reliably support the power mechanism; on the other hand, the aluminum alloy mounting bracket 33, together with the heat dissipation mounting plate and the ventilation pipe, forms an integrated heat dissipation structure, which further enhances the heat dissipation effect and ensures that the heat generated by the power mechanism during operation can be dissipated in a timely manner.

[0049] To further optimize the above technical solution, the front and rear walls of the UAV body 1 are both double-layered structures, and the interior is formed by air inlet pipe 14 and air outlet pipe 15 to form air inlet channel 12 and air outlet channel 13, respectively. This design makes air intake and exhaust smoother, improves airflow efficiency, thereby enhancing the overall performance of the heat dissipation system and providing more effective airflow support for the heat dissipation of the power system.

[0050] To further optimize the above technical solution, both the air inlet duct 14 and the air outlet duct 15 are arranged at an angle, so that the air inlet duct 14 and the air outlet duct 15 form a bending angle with the upper ventilation duct 21 and the lower ventilation duct 31, respectively. This structure can guide the air to flow along a predetermined path, increase the residence time of the air in the heat dissipation structure, improve the heat exchange efficiency between the air and the heat dissipation components, further enhance the heat dissipation effect, and also help optimize the aerodynamic performance of the UAV.

[0051] To further optimize the above technical solution, mesh plates 16 are provided at the openings of the air inlet pipe 14 and the air outlet pipe 15. This can prevent dust, debris and other objects from entering the heat dissipation channel, avoid blockage of the heat dissipation channel, ensure the normal operation of the heat dissipation system, extend the service life of the heat dissipation system, and also help improve heat dissipation efficiency and the reliability of the UAV.

[0052] To further optimize the above technical solution, air vents 211 are provided on both the upper ventilation pipe 21 and the lower ventilation pipe 31, which increases the airflow channel and area, further improves the airflow efficiency and heat dissipation effect, and enables heat to be dissipated more quickly, thereby enhancing the performance of the heat dissipation structure and better meeting the high heat dissipation requirements of high-performance UAVs.

[0053] The various embodiments in this specification are described in a progressive manner, with each embodiment focusing on its differences from other embodiments. Similar or identical parts between embodiments can be referred to interchangeably. For the apparatus disclosed in the embodiments, since they correspond to the methods disclosed in the embodiments, the description is relatively simple; relevant parts can be referred to the method section.

[0054] The above description of the disclosed embodiments enables those skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present invention. Therefore, the present invention is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A heat dissipation structure for an unmanned aerial vehicle (UAV) power compartment that integrates load-bearing and heat dissipation functions, characterized in that: include: The drone body (1) has a vertically penetrating mounting cavity (11) in the middle, and air inlet channel (12) and air outlet channel (13) are respectively opened on the front and rear walls of the drone body (1). The upper heat dissipation mounting plate (2) and the lower heat dissipation mounting plate (3) are detachably connected to the upper and lower openings of the mounting cavity (11). The bottom wall of the upper heat dissipation mounting plate (2) has multiple upper ventilation pipes (21), and the bottom wall of the lower heat dissipation mounting plate (3) has multiple lower ventilation pipes (31). The two ends of the upper ventilation pipes (21) and the lower ventilation pipes (31) are respectively connected to the air inlet channel (12) and the air outlet channel (13). The cavity formed by the upper heat dissipation mounting plate (2) and the lower heat dissipation mounting plate (3) and the mounting cavity (11) is used to install the power mechanism.

2. The integrated heat dissipation structure for a UAV power compartment according to claim 1, characterized in that, The exposed side surfaces of the upper heat dissipation mounting plate (2) and the lower heat dissipation mounting plate (3) have an upper heat dissipation fin (22) and a lower heat dissipation fin (32), respectively, which correspond to the side walls of the upper ventilation pipe (21) and the lower ventilation pipe (31).

3. The integrated heat dissipation structure for a UAV power compartment according to claim 2, characterized in that, The upper heat dissipation mounting plate (2), the lower heat dissipation mounting plate (3), the upper ventilation pipe (21), the lower ventilation pipe (31), the upper heat dissipation fin (22), and the lower heat dissipation fin (32) are all made of aluminum alloy.

4. The integrated heat dissipation structure for a UAV power compartment according to claim 1, characterized in that, Both the upper heat dissipation mounting plate (2) and the lower heat dissipation mounting plate (3) are connected to the opening of the mounting cavity (11) by bolts.

5. The integrated heat dissipation structure for a UAV power compartment according to claim 1, characterized in that, The top surface of the lower heat dissipation mounting plate (3) is fixed with a mounting bracket (33) that spans the lower ventilation pipe (31), and the power mechanism is mounted on the mounting bracket (33).

6. The integrated heat dissipation structure for a UAV power compartment according to claim 5, characterized in that, The mounting bracket (33) is attached to the lower ventilation pipe (31) and is made of aluminum alloy.

7. The integrated heat dissipation structure for a UAV power compartment according to claim 1, characterized in that, The front and rear walls of the UAV body (1) are both double-layered structures, and the air inlet pipe (14) and air outlet pipe (15) form the air inlet channel (12) and air outlet channel (13) respectively.

8. The integrated heat dissipation structure for a UAV power compartment according to claim 7, characterized in that, The air inlet pipe (14) and the air outlet pipe (15) are both arranged at an angle, so that the air inlet pipe (14) and the air outlet pipe (15) form a bending angle with the upper ventilation pipe (21) and the lower ventilation pipe (31), respectively.

9. The integrated heat dissipation structure for a UAV power compartment according to claim 8, characterized in that, Both the air inlet pipe (14) and the air outlet pipe (15) are provided with mesh plates (16).

10. The integrated heat dissipation structure for a UAV power compartment according to claim 1, characterized in that, Both the upper ventilation pipe (21) and the lower ventilation pipe (31) are provided with air vents (211).

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