Unmanned aerial vehicle airborne power supply with air cooling heat dissipation function
By designing the inner casing, fan mechanism, heat dissipation fins, heat conduction strips, and heat dissipation mesh, combined with alumina ceramic heat conduction strips and auxiliary heat dissipation structures, dual air-cooling heat dissipation of the drone power supply is achieved, solving the heat dissipation requirements and moisture prevention issues in high-temperature and high-altitude environments, and ensuring stable operation of the power supply.
Patent Information
- Application Number
- CN202421245476.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-06-03
- Publication Date
- 2025-01-10
- Estimated Expiration
- 2034-06-03
AI Technical Summary
Drones have high heat dissipation requirements in environments such as high temperature and high altitude, but existing heat dissipation technologies are insufficient, and the high humidity during high-altitude flight may cause the power system to become damp.
It adopts an internal casing, fan mechanism, heat dissipation fins, heat conduction strips and heat dissipation mesh design, combined with alumina ceramic heat conduction strips and auxiliary heat dissipation structure, to achieve dual heat dissipation through air cooling and heat conduction, and utilizes the fan to drive air circulation and heat conduction pipes to dissipate heat.
It significantly improves the heat dissipation efficiency of the drone power supply in high-temperature and high-altitude environments, prevents the power supply from getting damp, and ensures stable operation.
Smart Images
Figure CN222330027U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of unmanned aerial vehicle power supplies, in particular to an unmanned aerial vehicle airborne power supply with an air cooling and heat dissipation function. Background Art
[0002] A drone is an aircraft that does not require an operator and is usually controlled by a remote control, a pre-set autonomous flight program, a ground control station or other autonomous control methods. During the use of a drone, the onboard power supply plays a vital role. It provides a stable and reliable power supply for the flight control system, navigation system, communication equipment, load sensors and other electronic equipment.
[0003] When a drone is flying at high altitude, it needs to be stably powered to ensure its normal operation. However, long-term high-load operation can cause the drone power supply to overheat, which may cause a series of problems, such as power system performance degradation and equipment damage. To solve this problem, drone manufacturers usually use heat dissipation technology to maintain stable power supply operation.
[0004] However, in actual applications, the heat dissipation technology of drones needs to be optimized according to their flight conditions and usage environment. For example, in high temperature and high altitude environments, drones need a more powerful heat dissipation system to maintain stable operation, and during high-altitude flight, sufficient water vapor may cause conventional non-sealed power systems to become damp.
[0005] In view of the above problems, it is urgent to carry out innovative design based on the original onboard power supply. Utility Model Content
[0006] The technical solution of the utility model is aimed at the technical problem that the existing technical solutions are too single, and provides a UAV airborne power supply with air cooling and heat dissipation function, which is significantly different from the existing technology, so as to solve the problems raised in the above background technology.
[0007] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: an airborne power supply for a drone with air-cooling and heat dissipation function, comprising a shell, an inner box for separating two spaces is provided in the shell, and a fan mechanism is installed between the inner box and the top of the shell, a plurality of heat dissipation fins for heat conduction are installed on the top of the inner box, and each end of the heat dissipation fin is bonded and connected to the electronic components in the inner box with a thermal conductive strip, first heat dissipation mesh holes are respectively provided on both sides of the shell, an auxiliary heat dissipation structure is installed between one side of the inner wall of the shell and the outer wall of the inner box, and second heat dissipation mesh holes are respectively provided on the other two sides of the shell.
[0008] Preferably, the thermally conductive strip is made of alumina ceramic material.
[0009] Preferably, the auxiliary heat dissipation structure includes a box body, a connecting shaft, a first fan, a second fan, and a heat pipe. The box body is arranged between the inner wall of the shell and the outer wall of the inner box, and a connecting shaft is rotatably connected to the top of the box body. The upper end of the connecting shaft is connected to the first fan, and the lower end of the connecting shaft is connected to the second fan. The bottom of the box body is connected to the heat pipe, and the other end of the heat pipe is connected to the inner box.
[0010] Preferably, the heat-conducting pipe is spirally wound on the outer wall of the inner box, and the box body is connected with the inner box.
[0011] Preferably, the first heat dissipation mesh hole and the first fan are in the same horizontal plane, and a guide plate for guiding airflow to drive the first fan to rotate is provided on the top of the inner box.
[0012] Compared with the prior art, the beneficial effect of the utility model is as follows: the UAV onboard power supply with air-cooling and heat dissipation function, through the arrangement of the inner box, the fan mechanism, the heat dissipation fins, the thermal conductive strips and the first heat dissipation mesh, and the thermal conductive strips made of alumina ceramic material, the alumina ceramic has excellent insulation properties and high thermal conductivity, so that the heat generated by the electronic components is transferred to the heat dissipation fins through the thermal conductive strips, and then the outside air is drawn into between the top of the shell and the inner box through the fan mechanism, and then the air flows to both sides, absorbs the heat on the heat dissipation fins when passing through the heat dissipation fins, and is discharged through the first heat dissipation mesh, thereby achieving the first heat dissipation effect.
[0013] By setting the auxiliary heat dissipation structure and the second heat dissipation mesh, when the air passes through the first heat dissipation mesh, the flow thrust of the air acts on the first fan through the guidance of the guide plate, and the second fan is driven to rotate through the connecting shaft, thereby driving the air flow in the box body and the inner box. After the air in the inner box enters the heat pipe, the heat can be discharged through the heat pipe and flow to the outside through the second heat dissipation mesh. The air cooled in the heat pipe flows back to the inner box again, and the second air-cooled heat dissipation effect is achieved in this cycle. The superposition of the two heat dissipation effects greatly improves the heat dissipation efficiency, and solves the problem that the drone needs a more powerful heat dissipation system to maintain stable operation in high temperature, high altitude and other environments. BRIEF DESCRIPTION OF THE DRAWINGS
[0014] Figure 1 This is a schematic diagram of the cross-sectional structure of the inner box of the utility model;
[0015] Figure 2 This is a schematic diagram of the cross-sectional structure of the housing of the utility model;
[0016] Figure 3 This is a schematic diagram of the front view structure of the utility model;
[0017] Figure 4 It is a schematic diagram of the three-dimensional structure of the utility model.
[0018] In the figure: 1. shell; 2. inner box; 3. fan mechanism; 4. heat dissipation fins; 5. thermal conductive strips; 6. first heat dissipation mesh; 7. auxiliary heat dissipation structure; 701. box body; 702. connecting shaft; 703. first fan; 704. second fan; 705. heat pipe; 8. second heat dissipation mesh. DETAILED DESCRIPTION
[0019] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.
[0020] See also Figure 1-4 The utility model provides a technical solution: an airborne power supply for a drone with air-cooling and heat dissipation function, comprising a shell 1, an inner box 2, a fan mechanism 3, heat dissipation fins 4, a thermal conductive strip 5, a first heat dissipation mesh 6, an auxiliary heat dissipation structure 7, a box body 701, a connecting shaft 702, a first fan 703, a second fan 704, a heat pipe 705, and a second heat dissipation mesh 8. The shell 1 is provided with an inner box 2 for separating two spaces, and a fan mechanism 3 is installed between the inner box 2 and the top of the shell 1, a plurality of heat dissipation fins 4 for heat conduction are installed on the top of the inner box 2, and the end of each heat dissipation fin 4 is connected with a thermal conductive strip 5 in contact with the electronic components in the inner box 2, first heat dissipation meshes 6 are respectively provided on both sides of the shell 1, an auxiliary heat dissipation structure 7 is installed between one side of the inner wall of the shell 1 and the outer wall of the inner box 2, and second heat dissipation meshes 8 are respectively provided on the other two sides of the shell 1.
[0021] The heat conducting strip 5 is made of alumina ceramic material.
[0022] The auxiliary heat dissipation structure 7 includes a box body 701, a connecting shaft 702, a first fan 703, a second fan 704, and a heat pipe 705. The box body 701 is arranged between the inner wall of the shell 1 and the outer wall of the inner box 2, and the connecting shaft 702 is rotatably connected to the top of the box body 701, the upper end of the connecting shaft 702 is connected to the first fan 703, and the lower end of the connecting shaft 702 is connected to the second fan 704, the bottom of the box body 701 is connected to the heat pipe 705, and the other end of the heat pipe 705 is connected to the inner box 2.
[0023] The heat conducting pipe 705 is spirally wound on the outer wall of the inner box 2 , and the box body 701 is connected to the inner box 2 .
[0024] The first heat dissipation mesh hole 6 and the first fan 703 are in the same horizontal plane, and a guide plate for guiding airflow to drive the first fan 703 to rotate is provided on the top of the inner box 2.
[0025] Working principle: According to Figure 1 As shown, the device is mounted on the drone. As the power supply continuously provides energy to the drone for flight, the generated heat is introduced into the heat dissipation fins 4 through the heat conduction strips 5. At this time, the fan mechanism 3 is started to introduce the outside air into the housing 1 from the top, and then flows along the top of the inner box 2 to both sides and is discharged from the first heat dissipation mesh 6. In this process, the air contacts the heat dissipation fins 4, absorbs the heat thereon, and is discharged from the first heat dissipation mesh 6, thereby achieving the first heat dissipation effect. In addition, the electronic components inside the power supply are sealed and protected, and are not easily affected by the erosion of high-altitude humidity.
[0026] In the process of air passing through the first heat dissipation mesh 6, the airflow is guided to the first fan 703 through the guide plate on the top of the inner box 2 to drive it to rotate, and the second fan 704 is driven to rotate through the connecting shaft 702. Due to the connection between the box body 701 and the inner box 2, the rotation of the second fan 704 drives the air flow in the inner box 2. The air in the inner box 2 carries the heat from the electronic components through the box body 701 and enters the heat pipe 705. After the heat is transferred to the outside through the heat pipe 705 and the second heat dissipation mesh 8, the cooled air in the heat pipe 705 flows back from the other end of the heat pipe 705 to the inner box 2 to complete the cycle, avoiding the entry of humid air from the outside to erode. Through the two heat dissipation methods, the timely heat dissipation efficiency of the power supply under high load can be effectively improved. This is the working principle of the UAV airborne power supply with air-cooled heat dissipation function.
[0027] Although the embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.
Claims
1. An airborne power supply for a drone with air cooling and heat dissipation function, comprising a housing (1), characterized in that: An inner box (2) for separating two spaces is provided inside the shell (1), and a fan mechanism (3) is installed between the inner box (2) and the top of the shell (1). A plurality of heat dissipation fins (4) for heat conduction are installed on the top of the inner box (2), and each end of the heat dissipation fin (4) is connected to the electronic component in the inner box (2) with a heat conducting strip (5). First heat dissipation mesh holes (6) are provided on both sides of the shell (1), an auxiliary heat dissipation structure (7) is installed between one side of the inner wall of the shell (1) and the outer wall of the inner box (2), and second heat dissipation mesh holes (8) are provided on the other two sides of the shell (1).
2. The UAV airborne power supply with air cooling and heat dissipation function according to claim 1 is characterized in that: The heat conducting strip (5) is made of alumina ceramic material.
3. The UAV airborne power supply with air cooling and heat dissipation function according to claim 1 is characterized in that: The auxiliary heat dissipation structure (7) comprises a box body (701), a connecting shaft (702), a first fan (703), a second fan (704), and a heat pipe (705); the box body (701) is arranged between the inner wall of the shell (1) and the outer wall of the inner box (2); a connecting shaft (702) is rotatably connected to the top of the box body (701); the upper end of the connecting shaft (702) is connected to the first fan (703), and the lower end of the connecting shaft (702) is connected to the second fan (704); the bottom of the box body (701) is connected to the heat pipe (705), and the other end of the heat pipe (705) is connected to the inner box (2).
4. The UAV airborne power supply with air cooling and heat dissipation function according to claim 3 is characterized in that: The heat conduction pipe (705) is spirally wound on the outer wall of the inner box (2), and the box body (701) is connected to the inner box (2).
5. The UAV airborne power supply with air cooling and heat dissipation function according to claim 1 is characterized in that: The first heat dissipation mesh hole (6) and the first fan (703) are in the same horizontal plane, and a guide plate for guiding airflow to drive the first fan (703) to rotate is provided on the top of the inner box (2).