Water-cooling radiator for electric aircraft

Abstract

The utility model relates to the technical field of airplanes, and discloses a water-cooling radiator for an electric aircraft, which comprises confluence bodies arranged on two sides, and is characterized in that a radiating body is arranged between the confluence bodies on the two sides, a polygon is formed between the confluence bodies on the two sides and the radiating body, a water inlet and a water outlet are respectively formed in the confluence bodies on the two sides, and the water inlet and the water outlet are communicated with the radiating body. A water flow channel is formed between the water inlet and the radiator and between the water outlet and the radiator. A water-cooling radiator for an electric aircraft has the advantages of being capable of achieving shape following arrangement and saving space through polygonal structural design so as to be convenient to install, meeting the heat dissipation requirements of a motor and a speed reducer and the like, and solves the problems that an existing radiator is too large in size, limited by the size of an assembling space and inconvenient to install.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft, in particular to a water-cooled radiator for an electric aircraft. Background Art

[0002] In recent years, with the rapid development of cities and the rapid increase in the population of large cities, existing passenger transportation can no longer meet people's needs. In daily life, short-distance transportation or passenger transport often uses ground transportation such as buses, cars, and trucks. These modes of transportation are often restricted by ground roads and often experience traffic congestion. In terms of aircraft, manned aircraft are suitable for short-distance transportation and will be widely used and developed now and in the future.

[0003] During the use of an aircraft, some equipment will need to be cooled to improve the aircraft's endurance. However, existing radiators are too large and limited by the size of the transfer space, making them inconvenient to install and affecting the cooling effect of the motor and reducer.

[0004] Therefore, we propose a water-cooled radiator for electric aircraft to solve the above problems. Utility Model Content

[0005] (1) Technical problems solved

[0006] In response to the shortcomings of the existing technology, the utility model provides a water-cooled radiator for electric aircraft. Through the polygonal structure design, it can be arranged in a flexible manner, saving space, facilitating installation, and solving the heat dissipation needs of the motor and reducer. It solves the problem that the existing radiator is too large and is limited by the size of the transfer space, making it inconvenient to install.

[0007] (2) Technical solution

[0008] In order to achieve the above-mentioned purpose of easy installation and solving heat dissipation needs, the present invention provides the following technical solutions: A water-cooled radiator for an electric aircraft, comprising a confluence body arranged on both sides, a heat sink arranged between the confluence bodies on both sides, and a polygon formed between the confluence bodies on both sides and the heat sink. The polygon can be adapted according to the body shape and is not limited to a quadrilateral, hexagon, octagon, etc. A water inlet and a water outlet are respectively provided on the confluence bodies on both sides, which are used for water intake and water outlet respectively. Hot water enters from the water inlet, exchanges heat with the air, and flows out from the water outlet. A water flow path is formed between the water inlet and the water outlet and the heat dissipation flat tube to ensure that the water can flow.

[0009] As a further optimization of the present invention, the heat sink includes heat dissipation flat tubes and heat dissipation fins. The heat dissipation flat tubes are distributed horizontally or vertically between the converging bodies. Multiple groups of heat dissipation fins are distributed between the heat dissipation flat tubes and brazed on the heat dissipation flat tubes. The heat dissipation fins are closely arranged.

[0010] As a further optimization of the present invention, an inner annular fluid is also provided in the middle of the heat sink, and the inner annular fluid is provided with a mounting hole, through which the radiator can be set on the equipment, and the inner annular fluid is connected to the heat sink to form a water flow path.

[0011] As a further optimization of the present invention, the typical application scenario also includes a motor and a fan, the motor is coaxially connected to the fan, the radiator is placed between the fan and the motor, or on the side of the fan away from the motor, to achieve rapid air flow in the equipment space, thereby achieving the purpose of rapid heat dissipation of the equipment, and the inner annular fluid sleeve is arranged on the rotating shaft of the motor and does not rotate together with the rotating shaft.

[0012] As a further optimization of the present invention, a bearing is further provided between the inner annular fluid and the motor rotating shaft, and the stability of the radiator can be improved by installing the bearing.

[0013] As a further optimization of the present invention, the heat sink is made of metal, which can quickly absorb and dissipate heat to achieve a cooling effect.

[0014] (3) Beneficial effects

[0015] Compared with the prior art, the present invention provides a water-cooled radiator for electric aircraft, which has the following beneficial effects:

[0016] This technical solution uses a converging body to form a polygonal structure with the radiator, enabling space-saving layout of the body. The inner ring body allows for installation alongside devices requiring heat dissipation. The distributed heat dissipation flat tubes and fins allow for rapid heat dissipation, thus resolving the problem of existing radiators being too large and inconvenient to install due to limited space. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 This is a schematic diagram of the heat sink structure of the utility model;

[0018] Figure 2 This is a structural diagram of a first embodiment of the heat sink of the utility model;

[0019] Figure 3 This is a structural diagram of the second embodiment of the heat sink of the utility model.

[0020] In the figure: 1. Converging body; 2. Heat dissipation flat tubes; 3. Heat dissipation fins; 4. Inner ring fluid; 5. Motor; 6. Fan. DETAILED DESCRIPTION

[0021] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0022] See also Figure 1-3 A water-cooled radiator for an electric aircraft includes a confluence body 1 arranged on both sides, a heat sink arranged between the confluence bodies 1 on both sides, and a polygon formed between the confluence bodies 1 on both sides and the heat sink. The polygon can be adapted according to the shape of the aircraft body and is not limited to a quadrilateral, hexagon, octagon, etc. A water inlet and a water outlet are respectively provided on the confluence bodies 1 on both sides, which are used for water inlet and water outlet respectively. Hot water enters from the water inlet, is dissipated, and flows out from the water outlet. A water flow path is formed between the water inlet and the water outlet and the heat sink to ensure that the water flow can flow.

[0023] The heat sink includes heat dissipation flat tubes 2 and heat dissipation fins 3. The heat dissipation flat tubes 2 are distributed horizontally or vertically between the converging bodies 1, and multiple groups of heat dissipation fins 3 are distributed between the heat dissipation flat tubes 2. An inner ring fluid 4 is also provided in the middle of the heat sink. The inner ring fluid 4 is provided with a mounting hole, through which the radiator can be installed on the equipment. The inner ring fluid 4 is connected to the heat sink to form a water flow path.

[0024] Typical application scenarios also include a motor 5 and a fan 6. The motor 5 is coaxially connected to the fan 6. The radiator is placed between the fan 6 and the motor 5, or on the other side of the fan 6, to achieve rapid airflow in the equipment space, thereby achieving the purpose of rapid heat dissipation of the equipment. The inner annular fluid 4 is sleeved on the rotating shaft of the motor 5 and rotates together with the rotating shaft.

[0025] A bearing is also provided between the inner annular fluid 4 and the rotating shaft of the motor 5. The stability of the radiator can be improved by installing the bearing; the radiator is made of metal, which can quickly absorb and dissipate heat, thereby achieving a cooling effect.

[0026] Working principle: First, place the radiator in the duct in the space where heat dissipation is required. The shape of the radiator can be determined according to the shape of the duct. The radiator can be installed between the fan 6 and the motor 5, or it can be installed on the side of the fan 6 away from the motor 5. When the radiator is installed between the fan 6 and the motor 5, the motor 5 drives the fan 6 to rotate, forcing air to blow to the surface of the radiator for heat dissipation; when the radiator is installed on the other side of the fan 6, the motor 5 drives the fan 6 to rotate, forcibly extracting air from the surface of the radiator, so that the air flows on the surface of the radiator, and heat is exchanged when passing through the radiator fins 3 and the heat dissipation flat tubes 2. During this process, the coolant will enter from the water inlet and flow out from the water outlet.

[0027] Although the embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and variations may be made to these embodiments without departing from the principles and spirit of the present invention, and the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A water-cooled radiator for an electric aircraft, comprising a converging body (1) arranged on both sides, characterized in that: A heat sink is provided between the converging bodies (1) on both sides, and a polygon is formed between the converging bodies (1) on both sides and the heat sink. A water inlet and a water outlet are respectively provided on the converging bodies (1) on both sides, and a water flow path is formed between the water inlet and the water outlet and the heat sink.

2. The water-cooled radiator for an electric aircraft according to claim 1, characterized in that: The heat sink comprises heat dissipation flat tubes (2) and heat dissipation fins (3); the heat dissipation flat tubes (2) are distributed horizontally or vertically between the converging bodies (1); and a plurality of groups of heat dissipation fins (3) are distributed between the heat dissipation flat tubes (2).

3. The water-cooled radiator for an electric aircraft according to claim 1, characterized in that: An inner annular fluid (4) is also provided in the middle of the heat sink, and the inner annular fluid (4) is provided with a mounting hole. The inner annular fluid (4) is connected to the heat dissipation flat tube to form a water flow path.

4. The water-cooled radiator for an electric aircraft according to claim 3, characterized in that: In a typical application scenario, a motor (5) and a fan (6) are also included. The motor (5) is coaxially connected to the fan (6). The radiator is placed between the fan (6) and the motor (5), or on the other side of the fan (6). The inner annular fluid (4) is sleeved on the rotating shaft of the motor (5).

5. The water-cooled radiator for an electric aircraft according to claim 4, characterized in that: A bearing is also provided between the mounting hole provided in the inner annular fluid (4) and the rotating shaft of the motor (5).

6. The water-cooled radiator for an electric aircraft according to claim 1, characterized in that: The heat sink is made of metal.

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