Aviation motor with double-fan cooperative heat dissipation structure

Abstract

The utility model provides a kind of aviation motor with double-fan collaborative heat dissipation structure, including aviation motor base, aviation main motor and base support plate, the slot opening outward is equipped in the aviation motor base, the aviation main motor is located in the aviation motor base, two the base support plate fixedly arranged in the aviation motor base top end two sides, the base support plate position symmetrical arrangement of two sides, the base support plate of one side is installed and connected with annular support plate in one side face.This scheme is directly linked by transmission shaft and main motor shaft, inner ring fan blade generates high-strength axial airflow, accurately acts on motor end and core heating area, realizes heat rapid export, while outer ring fan blade revolves along annular track, forms large-flow annular airflow, expands heat dissipation coverage, and forms airflow superposition effect with inner ring airflow, significantly enhances overall heat dissipation capacity.

Description

Technical Field

[0001] This utility model relates to the field of aviation battery technology, specifically to an aviation motor with a dual-fan cooperative heat dissipation structure. Background Technology

[0002] As a core component of aircraft power systems, the performance stability and reliability of avionics directly affect flight safety and mission efficiency. With the rapid development of aviation technology, avionics are gradually moving towards higher power density, lighter weight, and more compact designs. However, the resulting thermal management issues have become a key bottleneck restricting their performance improvement.

[0003] Traditional aircraft motor cooling solutions mainly include natural convection cooling, single-fan forced air cooling, or liquid cooling systems. Natural convection cooling is inefficient and unsuitable for high-power applications. While liquid cooling systems offer strong cooling capabilities, they suffer from complex structures, heavy weight, and a high risk of leakage, limiting their application in the aerospace field. Single-fan forced air cooling, although simple in structure, is prone to heat dissipation blind spots under high-load conditions and lacks sufficient ability to optimize airflow organization. Utility Model Content

[0004] (a) Technical problems to be solved

[0005] To address the shortcomings of existing technologies, this invention provides an aircraft motor with a dual-fan collaborative heat dissipation structure, which solves the problems mentioned in the background technology, such as the tendency of single-fan forced air cooling to create heat dissipation blind spots under high load conditions and insufficient ability to optimize airflow organization.

[0006] (II) Technical Solution

[0007] To achieve the above objectives, this utility model provides the following technical solution: an aircraft motor with a dual-fan collaborative heat dissipation structure, comprising an aircraft motor base, an aircraft main motor, and a base support plate. The aircraft motor base has an outward-facing slot. The aircraft main motor is located within the aircraft motor base. Two base support plates are fixedly mounted on both sides of the top of the aircraft motor base, with the base support plates on both sides symmetrically arranged. One side of one base support plate is connected to an annular support plate. The annular support plate has an outward-facing heat dissipation cavity. A circular rotating slide rail is fixedly mounted on one side of the heat dissipation cavity. A plurality of annular arrayed outer ring fan blades are provided on one side of the rotating slide rail. The outer ring fan blades are movably connected to the rotating slide rail. An inner ring fan blade is rotatably mounted within the heat dissipation cavity. The inner ring fan blades are located within the inner ring of the heat dissipation cavity, and the outer ring fan blades are located within the outer ring of the heat dissipation cavity.

[0008] Preferably, a connecting base is provided at the connection position between the annular support plate and the base support plate. The connecting base is circular and has inwardly opening heat dissipation holes.

[0009] Preferably, the connecting base has a plurality of arrayed connecting through holes, with openings on both sides of the connecting through holes communicating through each other.

[0010] Preferably, a drive shaft is rotatably provided inside the heat dissipation hole, the drive shaft is installed and connected to the main motor shaft inside the aircraft main motor, and the drive shaft is installed and connected to the inner ring fan blade.

[0011] Preferably, a motor output module is installed on the base support plate on the other side, and the motor output module is connected to the main motor of the aircraft to achieve the effect of power output.

[0012] (III) Beneficial Effects

[0013] This invention provides an aircraft motor with a dual-fan cooperative heat dissipation structure. It has the following beneficial effects:

[0014] 1. This solution directly links the drive shaft with the main motor shaft. The inner fan blades generate a high-intensity axial airflow, which is precisely applied to the motor end and the core heat-generating area to achieve rapid heat dissipation. At the same time, the outer fan blades revolve along the circular track, forming a large-volume annular airflow, expanding the heat dissipation coverage area, and creating an airflow superposition effect with the inner airflow, significantly enhancing the overall heat dissipation capacity.

[0015] 2. This solution uses an independent drive module to link the inner and outer fan blades with the main motor, achieving intelligent matching of airflow direction and flow rate, thus avoiding the local overheating problem of traditional single-fan cooling. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the external structure of the present utility model;

[0017] Figure 2 This is a schematic diagram of the main structure of this utility model;

[0018] Figure 3 This is a side view of the structure of this utility model;

[0019] Figure 4 This is a front view structural diagram of the present invention.

[0020] In the diagram: 101, aircraft motor base; 102, aircraft main motor; 103, base support plate; 104, annular support plate; 105, rotating slide rail; 106, heat dissipation cavity; 107, outer fan blades; 108, connecting through hole; 109, drive shaft; 110, inner fan blades; 111, connecting heat dissipation hole; 112, motor output module; 113, connecting base. Detailed Implementation

[0021] This utility model embodiment provides an aircraft motor with a dual-fan cooperative heat dissipation structure, such as Figure 1-4 As shown, the system includes an aircraft motor base 101, an aircraft main motor 102, and a base support plate 103. The aircraft motor base 101 has an outward-facing slot. The aircraft main motor 102 is located inside the aircraft motor base 101. Two base support plates 103 are fixedly mounted on both sides of the top of the aircraft motor base 101. The base support plates 103 on both sides are symmetrically arranged. An annular support plate 104 is installed and connected to one side of one of the base support plates 103. The support plate 104 has an outward-facing heat dissipation cavity 106. A circular rotating slide rail 105 is fixedly installed on one side of the heat dissipation cavity 106. A plurality of outer ring fan blades 107 in a circular array are provided on one side of the rotating slide rail 105. The outer ring fan blades 107 are movably connected to the rotating slide rail 105. An inner ring fan blade 110 is rotatably installed in the heat dissipation cavity 106. The inner ring fan blade 110 is located in the inner ring of the heat dissipation cavity 106, and the outer ring fan blades 107 are located in the outer ring of the heat dissipation cavity 106.

[0022] It should be further explained that the outer fan blade 107 is in the shape of a curved fan, and the inner fan blade 110 is in the shape of an arc blade, which promotes the flow of air.

[0023] It is worth further explaining that the rotating slide rail 105 is equipped with a drive module, which is used to drive the outer ring fan blades 107 on each side to move along the guide of the rotating slide rail 105, thereby achieving the effect of driving rotation.

[0024] Furthermore, a connecting base 113 is provided at the connection position between the annular support plate 104 and the base support plate 103. The connecting base 113 is annular and has inwardly opening heat dissipation holes 111 inside.

[0025] Furthermore, the connecting base 113 is provided with a plurality of arrayed connecting through holes 108, and the two sides of the connecting through holes 108 are open and connected.

[0026] Furthermore, a drive shaft 109 is rotatably provided inside the heat dissipation hole 111. The drive shaft 109 is installed and connected to the main motor shaft inside the aircraft main motor 102, and the drive shaft 109 is installed and connected to the inner fan blade 110.

[0027] It should be further explained that when the aircraft main motor 102 starts, it drives the transmission shaft 109 to rotate through the output of the main motor shaft, and then drives the inner fan blade 110 to rotate through the transmission shaft 109.

[0028] Furthermore, a motor output module 112 is installed on the base support plate 103 on the other side. The motor output module 112 is connected to the aircraft main motor 102 to achieve the effect of power output.

[0029] The usage method of this solution is as follows:

[0030] S1. During the operation of the aircraft main motor 102, the main motor shaft of the aircraft main motor 102 directly or indirectly drives the transmission shaft 109 installed and connected to it to rotate. The rotation of the transmission shaft 109 drives the inner ring fan blade 110 installed and connected to it to rotate at high speed in the inner ring area of ​​the heat dissipation cavity 106. When the inner ring fan blade 110, which is in the shape of an arc blade, rotates, it mainly generates airflow along the motor axis. This airflow directly acts on the end or adjacent area of ​​the aircraft main motor 102, and quickly blows the heat generated inside the motor to the heat dissipation cavity 106 and the external environment.

[0031] S2. At the same time, the drive module is activated, and the drive module drives the outer ring fan blades 107 on each side to move along the guide of the rotating slide rail 105. Since the rotating slide rail 105 is circular, the movement of the outer ring fan blades 107 is essentially a circular motion around the central axis of the annular support plate 104. During the rotation of the curved fan-shaped outer ring fan blades 107, several large-volume airflows are generated in the outer ring area of ​​the heat dissipation cavity 106. At this time, the airflow direction generated by the outer ring fan blades 107 and the airflow direction generated by the inner ring fan blades 110 can cooperate and enhance each other.

[0032] S3. The connection heat dissipation holes 111 and connection through holes 108 provided on the connection base 113 provide additional channels for airflow. The connection heat dissipation holes 111 help to introduce or export airflow into or near the motor or key heat-generating components. The array of connection through holes 108 effectively promotes airflow in the connection area between the annular support plate 104 and the base support plate 103, and even the entire mounting structure, preventing heat from accumulating in this area and assisting in the flow and pressure balance of the inner and outer rings of airflow.

[0033] S4. The other end of the aircraft main motor 102 outputs power through the motor output module 112, thus fulfilling its core function as an aircraft motor.

[0034] Although 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 alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. An aircraft motor with a dual-fan cooperative heat dissipation structure, comprising an aircraft motor base (101), an aircraft main motor (102), and a base support plate (103), characterized in that: The aircraft motor base (101) has an outward-facing slot. The aircraft main motor (102) is located inside the aircraft motor base (101). Two base support plates (103) are fixedly mounted on both sides of the top of the aircraft motor base (101). The base support plates (103) on both sides are symmetrically arranged. One side of the base support plate (103) is connected to an annular support plate (104). The annular support plate (104) has an outward-facing heat dissipation cavity (104). 06), a rotating slide rail (105) is fixedly provided on one side of the heat dissipation cavity (106), and a plurality of outer ring fan blades (107) in an annular array are provided on one side of the rotating slide rail (105). The outer ring fan blades (107) are movably connected to the rotating slide rail (105). An inner ring fan blade (110) is rotatably provided in the heat dissipation cavity (106). The inner ring fan blade (110) is located in the inner ring of the heat dissipation cavity (106), and the outer ring fan blades (107) are located in the outer ring of the heat dissipation cavity (106).

2. The aircraft motor with a dual-fan cooperative heat dissipation structure according to claim 1, characterized in that: A connecting base (113) is provided at the connection position between the annular support plate (104) and the base support plate (103), and the connecting base (113) is provided with an inwardly opening heat dissipation hole (111).

3. An aircraft motor with a dual-fan cooperative heat dissipation structure according to claim 2, characterized in that: The connecting base (113) has a plurality of arrayed connecting through holes (108), and the two sides of the connecting through holes (108) are open and connected.

4. An aircraft motor with a dual-fan cooperative heat dissipation structure according to claim 3, characterized in that: A drive shaft (109) is rotatably mounted inside the heat dissipation hole (111), and the drive shaft (109) is installed and connected to the main motor shaft inside the aircraft main motor (102).

5. An aircraft motor with a dual-fan cooperative heat dissipation structure according to claim 4, characterized in that: The drive shaft (109) is installed and connected to the inner fan blade (110).

6. An aircraft motor with a dual-fan cooperative heat dissipation structure according to claim 1, characterized in that: On the other side, the base support plate (103) is equipped with a motor output module (112), which is connected to the aircraft main motor (102) to achieve power output.

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