Unmanned aerial vehicle power supply module

Abstract

The utility model relates to the technical field of power sources, and discloses an unmanned aerial vehicle power source module which comprises a fuselage and a battery, the battery abuts against the bottom of the fuselage, a cover shell is installed on the lower side of the fuselage through a connecting structure, a partition plate is fixedly installed in the cover shell, first through holes are evenly formed in the partition plate, and abutting structures are installed in the first through holes. The lower surface of the battery abuts against the corresponding abutting structure below, an air inlet is formed in one end of the housing and located below the partition plate, and an exhaust port is formed in the other end of the housing and located above the partition plate. According to the utility model, the plurality of abutting structures are arranged in the housing, so that the batteries with different sizes can be abutted against the lower side of the machine body, the adaptation range is large, the use is flexible, and the abutting structures which do not abut against the batteries are located at the initial positions, so that the side walls of the batteries can be shielded, and the movement is avoided; in addition, air near the battery can circulate, and the heat exchange effect is good.

Description

Technical Field

[0001] This utility model relates to the field of power supply technology, specifically a power supply module for unmanned aerial vehicles (UAVs). Background Technology

[0002] The structure of a drone includes a fuselage, a power system (mainly consisting of an electric motor, propellers, batteries, and electronic speed controllers), and a flight control system (mainly consisting of sensors, controllers, and algorithms).

[0003] Batteries for drone applications need to have high energy density to provide enough power within a limited weight and volume, which helps drones achieve longer flight times and greater flight distances.

[0004] The batteries currently in use are embedded and installed in the device body using a snap-fit ​​structure, which also completes the electrical connection. However, for applications that require a wide range of adaptability, this installation structure limits the replaceability of batteries of different sizes and results in poor flexibility of use.

[0005] Therefore, in order to solve the above problems, a drone power supply module is proposed. Utility Model Content

[0006] The purpose of this invention is to provide a power module for drones that can replace batteries of different sizes, thereby solving the problems mentioned in the background art.

[0007] To achieve the above objectives, this utility model provides the following technical solution: a drone power module, comprising a fuselage and a battery, the battery being abutted against the bottom of the fuselage, a cover being installed on the lower side of the fuselage via a connecting structure, a partition being fixedly installed inside the cover, the partition having evenly spaced first through holes, each of the first through holes having a clamping structure installed inside, the lower surface of the battery abutting against the corresponding clamping structure below, an air inlet being provided at one end of the cover located below the partition, and an exhaust port being provided at the other end of the cover located above the partition.

[0008] Specifically, the clamping structure includes a through tube, a spring, and a bottom ring. The through tube is slidably assembled in the first through hole. A bottom ring is fixedly installed on the bottom outer side of the through tube. The through tube is fitted with a spring. The upper end of the spring is fixedly assembled with a partition plate, and the lower end of the spring is fixedly assembled with the bottom ring.

[0009] Optionally, an air guide head is installed at the upper end of the conduit.

[0010] Specifically, the air guide head includes a sealing head and a second through hole. The sealing head is fixedly installed at the upper end of the through pipe, and the sealing head has a second through hole opened radially.

[0011] Furthermore, the end cap is a blind tube made of ceramic material.

[0012] Furthermore, the second through hole consists of 2 to 3 holes evenly distributed around the circumference.

[0013] Specifically, the connection structure includes connecting ears and screws. At least three connecting ears are evenly fixed around the perimeter of the cover, and screws for connecting the body are installed inside the connecting ears.

[0014] Compared with the prior art, the beneficial effects of this utility model are: through the multiple clamping structures installed inside the casing, batteries of different sizes can be clamped to the lower side of the body, which has a wide range of compatibility and is flexible in use. The clamping structures that do not clamp the battery are in the initial position, which can block the side wall of the battery and prevent it from moving.

[0015] In addition, air can enter the chamber below the separator through the air inlet, and then enter the chamber above the separator through various sealing structures and air guides. After exchanging heat with the battery, it is finally discharged from the exhaust port, resulting in high heat exchange efficiency. Attached Figure Description

[0016] Figure 1 This is a schematic cross-sectional view of the internal structure of the casing of this utility model;

[0017] Figure 2 This is a partial sectional view of the structure of the clamping structure of this utility model;

[0018] Figure 3 This is a schematic cross-sectional view of the connection structure of this utility model.

[0019] In the diagram: 1. Body, 2. Battery, 3. Connecting structure, 31. Connecting ear, 32. Screw, 4. Exhaust port, 5. Clamping structure, 51. Through pipe, 52. Spring, 53. Bottom ring, 6. Cover, 7. Partition, 8. Air inlet, 9. Air guide head, 91. End cap, 92. Second through hole. Detailed Implementation

[0020] 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.

[0021] Please see Figure 1This utility model provides a power module for a drone, including a fuselage 1 and a battery 2. The battery 2 is abutted against the bottom of the fuselage 1. The fuselage 1 and the battery 2 are existing devices. A first connector extends from the lower side of the fuselage 1, and a second connector extends from the battery 2. By plugging in the first connector and the second connector, an electrical connection can be completed, thereby supplying power to the various electrical components of the fuselage 1.

[0022] A cover 6 is installed on the lower side of the body 1 via a connecting structure 3. A partition 7 is fixedly installed inside the cover 6. The partition 7 has evenly spaced first through holes, and a clamping structure 5 is installed in each of the first through holes. The lower surface of the battery 2 abuts against the corresponding clamping structure 5 below. One end of the cover 6 has an air inlet 8 located below the partition 7, and the other end of the cover 6 has an exhaust port 4 located above the partition 7. The clamping structure 5 has the ability to return to its original position. After the cover 6 is installed, the clamping structure 5 located below the battery 2 can press the battery 2 firmly against the lower part of the body 1, while the other clamping structures 5 remain in their original positions, covering the battery 2 around its perimeter, thus providing a limiting function.

[0023] When installing the cover 6, ensure that the air inlet 8 is located on the front of the drone. In this way, when the drone is flying, air will enter the chamber below the partition 7 through the air inlet 8 due to pressure, and then enter the chamber above the partition 7 through each clamping structure 5. After exchanging heat with the battery 2, it will finally be discharged from the exhaust port 4.

[0024] For details, please refer to Figure 2 The clamping structure 5 includes a through pipe 51, a spring 52, and a bottom ring 53. The through pipe 51 is slidably assembled in the first through hole. The bottom of the outer side of the through pipe 51 is fixedly installed with a bottom ring 53. The through pipe 51 is fitted with a spring 52. The upper end of the spring 52 is fixedly assembled with the partition 7, and the lower end of the spring 52 is fixedly assembled with the bottom ring 53. The spring 52 can slide the through pipe 51 upward along the first through hole through the bottom ring 53 until it returns to its original position. When the top of the through pipe 51 is subjected to pressure, it can move downward. The through pipe 51 can connect the upper and lower chambers of the partition 7 to ensure that the air near the battery 2 can circulate.

[0025] Furthermore, an air guide head 9 is installed at the upper end of the through pipe 51. The air guide head 9 includes a cap 91 and a second through hole 92. The cap 91 is fixedly installed at the upper end of the through pipe 51, and the cap 91 has a second through hole 92 opened radially. The air transported upward through the through pipe 51 can be output to the side through the second through hole 92, which plays the role of air guide. The cap 91 is preferably a blind tube made of ceramic material, which has insulation and heat conduction properties, ensuring heat exchange efficiency while also providing insulation protection, making it safer to use.

[0026] In addition, there are 2 to 3 second through holes 92 evenly distributed around the circumference to ensure the output volume and uniformity of air output.

[0027] For details, please refer to Figure 3 The connecting structure 3 includes connecting ears 31 and screws 32. At least three connecting ears 31 are evenly fixedly installed around the perimeter of the cover 6. Screws 32 for connecting the body 1 are installed inside the connecting ears 31. The method of connecting the connecting ears 31 with screws 32 can ensure the connection strength, prevent the cover 6 from falling off, and facilitate disassembly.

[0028] The working principle of this embodiment:

[0029] In use, the battery 2 to be installed is connected to the body 1 by plugging in the first and second connectors. If the voltage of the battery 2 is not compatible, an adapter can be installed between the first and second connectors for conversion. After the cover 6 is fastened, the battery 2 is pressed against the bottom of the body 1 by the corresponding clamping structure 5. The other clamping structures 5 that are not pressed against the battery 2 are in the initial position, which can block the side wall of the battery 2 and prevent the battery 2 from moving. Then the cover 6 is fixedly installed by the connecting structure 3.

[0030] When the drone is flying, air enters the chamber below the partition 7 through the air inlet 8, and then enters the chamber above the partition 7 through various clamping structures 5 and air guides 9. After exchanging heat with the battery 2, it is finally discharged from the exhaust port 4.

[0031] It will be apparent to those skilled in the art that this invention is not limited to the details of the exemplary embodiments described above, and that it can be implemented in other specific forms without departing from the spirit or essential characteristics of this invention. Therefore, the embodiments should be considered illustrative and non-limiting, and the scope of this invention is defined by the appended claims rather than the foregoing description. Thus, all variations falling within the meaning and scope of equivalents of the claims are intended to be included within this invention. No reference numerals in the claims should be construed as limiting the scope of the claims.

[0032] Furthermore, it should be understood that although this specification describes embodiments, not every embodiment contains only one independent technical solution. This narrative style is merely for clarity. Those skilled in the art should consider the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. An unmanned aerial vehicle power module, comprising a fuselage (1) and a battery (2), the battery (2) being located against the bottom of the fuselage (1), characterized in that: The lower side of the fuselage (1) is provided with a cover (6) through a connecting structure (3), the inside of the cover (6) is fixedly provided with a partition plate (7), the first through hole is uniformly arranged on the partition plate (7), the first through hole is provided with a abutting structure (5), the lower surface of the battery (2) is abutted with the corresponding abutting structure (5), one end of the cover (6) is provided with an air inlet (8), the air inlet (8) is located below the partition plate (7), the other end of the cover (6) is provided with an air outlet (4), the air outlet (4) is located above the partition plate (7). 2.The power module of claim 1, wherein: The abutting structure (5) comprises a pipe (51), a spring (52) and a bottom ring (53), the pipe (51) is slidingly assembled in the first through hole, the bottom of the outer side of the pipe (51) is fixedly provided with a bottom ring (53), the pipe (51) is provided with a spring (52), the upper end of the spring (52) is fixedly assembled with the partition plate (7), and the lower end of the spring (52) is fixedly assembled with the bottom ring (53). 3.The power module of claim 2, wherein: The upper end of the pipe (51) is provided with a gas guide head (9).

4. The power module of claim 3, wherein: The gas guide head (9) comprises a head (91) and a second through hole (92), the head (91) is fixedly installed on the upper end of the pipe (51), and the head (91) is provided with a second through hole (92) along the radial direction.

5. The power module of claim 4, wherein: The head (91) is a blind pipe made of ceramic material.

6. The power module of claim 4, wherein: The second through hole (92) is 2-3 circularly and uniformly distributed.

7. The power module of claim 1, wherein: The connecting structure (3) comprises a connecting lug (31) and a screw (32), at least three connecting lugs (31) are uniformly fixedly arranged on the periphery of the cover (6), and the connecting lug (31) is provided with a screw (32) for connecting the fuselage (1).

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