A base plate for aircraft motors with cooling channels

Abstract

This utility model relates to an aircraft motor base plate with cooling channels, comprising a base plate body, on which oil channels A and B are formed. Short oil pipes A and B, respectively, are formed on the side of oil channels A and B facing the stator housing, communicating with the oil inlet and outlet holes of the cooling channels on the stator housing. A radiator interface B and an oil pump interface A are provided on the other side of oil channels A and B. This utility model directly integrates the coolant distribution function, which originally required external pipes and joints, into the base plate as a structural component. This greatly simplifies the structure of the entire motor cooling system and reduces the number of parts. The flow channels inside the base plate body make full use of the structural space of the base plate, avoiding the occupation of valuable airborne space by external pipes, making the entire propulsion unit structure more compact. At the same time, reducing external pipes, joints, and their supporting structures helps to achieve overall system lightweighting.

Description

Technical Field

[0001] This utility model relates to the field of aircraft motor structure technology, and in particular to an aircraft motor base plate with a cooling channel. Background Technology

[0002] Aircraft, especially advanced aircraft such as electric vertical takeoff and landing (EVTOL) aircraft, face extremely stringent requirements regarding the power density, reliability, and lightweight design of their drive systems. As a core drive component, the motor generates a significant amount of heat during operation, primarily from its stator windings and core. If this heat cannot be dissipated promptly and effectively, the motor temperature will rise sharply, leading to a series of serious problems such as magnet demagnetization, insulation material aging, and reduced efficiency, directly threatening flight safety.

[0003] Currently, liquid cooling, especially oil cooling, has become the mainstream technology for cooling high power density motors due to its high specific heat capacity and thermal conductivity. A common approach is to machine or cast complex spiral cooling channels into the inner wall of the motor stator housing. Cooling oil flows through these channels, carrying away the heat generated inside the motor through the inner wall of the housing.

[0004] However, introducing and removing cooling oil into and out of the high-speed rotating motor stator housing is a technical challenge. Existing solutions typically rely on complex external piping systems. These external pipes need to connect from fixed components such as oil pumps and radiators to the rotating motor housing, often requiring dynamic sealing structures such as rotary joints. This approach has several significant drawbacks: 1. System complexity and reliability issues: The additional rotary joints and external piping increase the system's complexity and the number of components. Rotary joints are potential leak points and single-point failure sources, and their dynamic sealing structures are at risk of wear and failure under long-term high-speed operation, reducing the reliability of the entire drive system. This is unacceptable for aviation applications that pursue the highest safety standards. 2. Conflict between space layout and lightweight design: External piping occupies valuable airborne space, resulting in inflexible layout. Furthermore, to meet strength requirements, the piping and its supporting structures add extra weight, which is detrimental to the lightweight design of the aircraft. 3. Poor assembly and maintainability: Complex piping connections increase the difficulty of motor manufacturing and assembly, and also cause inconvenience for later maintenance and repair.

[0005] Furthermore, motors typically need to be integrated with components such as oil pumps and radiators to form a compact propulsion unit. This necessitates a robust base plate (or mounting plate) to support the motor stator, connect other components, and bear the overall load. In existing technologies, the motor base plate is usually considered merely a structural component and mounting interface, with a single function, and its integrated role in the thermal management system is not fully considered. Utility Model Content

[0006] To address the aforementioned technical problems, the present invention aims to provide an aircraft motor base plate with a cooling channel. This base plate can highly integrate the structural support function of the motor with the efficient coolant distribution function, thereby simplifying the system, improving reliability, saving space, and reducing weight.

[0007] To achieve the above-mentioned objectives, this utility model adopts the following technical solution: A base plate for an aircraft motor with a cooling channel includes a base plate body. Oil channels A and B are provided on the base plate body. Short oil pipes A and B, which communicate with the oil inlet and outlet holes of the cooling channel on the stator housing, are respectively provided on the side of oil channels A and B facing the stator housing. A radiator interface B and an oil pump interface A are provided on the other side of oil channels A and B.

[0008] As a preferred embodiment, a hollow support column is provided in the center of the base plate body. The hollow support column is fixed to the upper end face of the stator housing, and the base plate body is fixed to the lower end face of the stator housing, so that an installation cavity is formed inside the stator housing.

[0009] As a preferred embodiment, the oil passage A is an elongated arc shape that spans the entire base plate body.

[0010] As a preferred embodiment, the oil passage B is located at the edge of the bottom plate body, and short oil pipes B are respectively provided at both ends. A cavity A is also provided inside the oil passage B. The oil passage B is connected to the cavity A, and the oil pump interface A is located at the cavity A.

[0011] As a preferred embodiment, the oil passage B and the cavity A are further provided with a plurality of support protrusions at intervals.

[0012] As a preferred embodiment, a cavity B is also provided on one side of the cavity A, and the cavity B is provided with an oil pump interface B and a radiator interface A.

[0013] As a preferred embodiment, the base plate body is also provided with an elongated clearance groove, and at least a portion of the bridging oil pipe in the stator assembly is disposed in the elongated clearance groove.

[0014] Compared with the prior art, the beneficial effects of this utility model are as follows: This invention integrates the coolant distribution function, which originally required external pipes and connectors, directly into the base plate, which is a structural component. This greatly simplifies the structure of the entire motor cooling system and reduces the number of parts. The flow channels inside the base plate make full use of the structural space, avoiding the occupation of valuable onboard space by external pipes, making the entire propulsion unit structure more compact. At the same time, reducing external pipes, connectors, and their supporting structures helps to achieve overall system weight reduction. Attached Figure Description

[0015] The accompanying drawings, which form part of this application, are used to provide a further understanding of this application. The illustrative embodiments of this application and their descriptions are used to explain this application and do not constitute a limitation thereof.

[0016] Figure 1 This is a schematic diagram of the structure of the motor base plate of this utility model; Figure 2 This is a cross-sectional structural diagram of the motor base plate of this utility model; Figure 3 This is a schematic diagram of the installation structure of the motor base plate, stator housing, controller assembly, and other components of this utility model.

[0017] The reference numerals in the accompanying drawings are as follows: 21, stator housing; 20, base plate body; 201, hollow support column; 202, oil passage A; 203, short oil pipe A; 204, short oil pipe B; 205, oil passage B; 2051, support protrusion; 206, radiator interface A; 207, radiator interface B; 208, oil pump interface A; 209, oil pump interface B; 230, cavity A; 240, cavity B; 250, elongated clearance groove; 220, power connector; 25, circuit board; 251, IGBT module; 26, cooling plate; 27, terminal block; 28, mounting bracket; 29, transition oil pipe. Detailed Implementation

[0018] It should be noted that the following detailed descriptions are illustrative and intended to provide further explanation of this application. Unless otherwise specified, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application pertains.

[0019] It should be noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the exemplary embodiments according to this application. As used herein, the singular form is intended to include the plural form as well, unless the context clearly indicates otherwise. Furthermore, it should be understood that when the terms "comprising" and / or "including" are used in this specification, they indicate the presence of features, steps, operations, devices, components, and / or combinations thereof.

[0020] Furthermore, in the description of this utility model, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "clockwise," and "counterclockwise," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model.

[0021] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this utility model, unless otherwise stated, "a plurality of" means two or more, unless otherwise expressly defined.

[0022] In this utility model, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0023] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0024] The present invention will be further described below with reference to the accompanying drawings and embodiments: like Figures 1 to 3The diagram shows an aircraft motor base plate with cooling channels, comprising a base plate body 20. Oil channels A202 and B205 are provided on the base plate body 20. Short oil pipes A203 and B204, respectively, are provided on the side of oil channels A202 and B205 facing the stator housing 21, communicating with the oil inlet and outlet holes of the cooling channels on the stator housing 21. A radiator interface B207 and an oil pump interface A208 are provided on the other side of oil channels A202 and B205. This base plate structure, by solidifying the main coolant flow channels inside the base plate, eliminates a large number of external pipe connection points, fundamentally reducing the risk of coolant leakage and improving the operational reliability of the system in high-speed, vibration environments.

[0025] A hollow support column 201 is also provided in the center of the base plate body 20. The hollow support column 201 is fixed to the upper end face of the stator housing 21, and the base plate body 20 is fixed to the lower end face of the stator housing 21, thus forming an installation cavity inside the stator housing 21. By fixing the stator housing at both the upper (hollow support column) and lower (base plate body) ends, a stable "double support" structure is formed, which significantly enhances the motor's ability to withstand complex loads (such as vibration and torque reaction force) during aircraft operation and prevents housing deformation. The base plate and stator housing together form a closed installation cavity, providing a stable and protected operating environment for the motor rotor, stator, and other core components.

[0026] The oil passage A202 is an elongated arc shape that spans the entire base plate body 20. Compared to a right-angle bend, the arc-shaped flow channel significantly reduces coolant flow resistance and local pressure loss, resulting in smoother fluid flow. This helps reduce oil pump power consumption and improve the overall efficiency of the cooling system. Simultaneously, the design spanning the entire base plate provides a large flow channel coverage area, facilitating more even distribution of coolant to the corresponding areas of the stator housing, or collecting heat from these areas, preventing localized overheating and promoting balanced overall thermal management.

[0027] The oil passage B205 is located at the edge of the base plate body 20, and short oil pipes B204 are provided at both ends. The inner side of the oil passage B205 is also provided with a cavity A230. The oil passage B205 is connected to the cavity A230, and the oil pump interface A208 is located at the cavity A230.

[0028] Oil passage B is located at the edge, corresponding to the surrounding cooling channel on the stator housing. Short oil pipes at both ends allow coolant to flow out from both sides of the housing, ensuring uniform cooling. Cavity A, acting as a collector or distributor, combines two flow paths into one, which is then connected to an external system via an oil pump interface, achieving efficient fluid collection and distribution. Furthermore, placing the oil pump interface in cavity A provides a centralized and structurally robust connection point, facilitating connection to external oil pump piping and avoiding direct interface openings in weak areas, thus improving structural rationality and sealing reliability.

[0029] Multiple support protrusions 2051 are also provided at intervals at the connection between the oil passage B205 and the cavity A230. After the oil passage B205 connects with the cavity A230, a large cavity is formed, whose top or bottom wall may easily deform or vibrate under system pressure. The support protrusions act as "internal ribs," enhancing the mechanical strength and rigidity of this area and preventing deformation caused by pressure or external forces.

[0030] A cavity B240 is also provided on one side of cavity A230. Cavity B240 is equipped with an oil pump interface B209 and a radiator interface A206. The arrangement of cavity B makes the base plate a cooling distribution center. Cavity B connects the oil pump and the radiator, allowing the interfaces of key external components such as the oil pump and radiator to be centrally and rationally arranged on the base plate. Furthermore, the cooperation of the two cavities allows for more flexible design of internal flow channels, enabling complex fluid flow logic (such as series and parallel cooling), further optimizing the cooling effect and system efficiency.

[0031] The base plate body 20 is also provided with an elongated clearance groove 250, in which at least a portion of the bridging oil pipes within the stator assembly are disposed. The motor contains necessary internal connecting oil pipes, and the clearance groove provides dedicated space for these pipes, preventing interference with the base plate structure and ensuring assembly feasibility. Simultaneously, placing the bridging oil pipes in the clearance groove provides positioning and protection, preventing damage due to compression or friction during assembly or operation. This "embedded" design also avoids increasing the overall size of the assembly due to internal pipelines, maintaining the high compactness of the propulsion unit.

[0032] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0033] Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of the present invention without departing from the principles and spirit of the present invention. Any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention shall still fall within the scope of the technical solution of the present invention.

Claims

1. A base plate for an aircraft motor with a cooling channel, characterized in that: Includes a base plate body (20), on which oil passages A (202) and B (205) are provided. On the side of oil passages A (202) and B (205) facing the stator housing (21), short oil pipes A (203) and B (204) are respectively provided, which are connected to the oil inlet and outlet holes of the cooling channel on the stator housing (21). On the other side of oil passages A (202) and B (205), radiator interface B (207) and oil pump interface A (208) are provided.

2. The aircraft motor base plate with cooling channel according to claim 1, characterized in that, The base plate body (20) is also provided with a hollow support column (201) in the center. The hollow support column (201) is fixed to the upper end face of the stator housing (21), and the base plate body (20) is fixed to the lower end face of the stator housing (21), so that an installation cavity is formed inside the stator housing (21).

3. The aircraft motor base plate with cooling channels according to claim 1, characterized in that, The oil passage A (202) is an elongated arc shape and spans the entire bottom plate body (20).

4. The aircraft motor base plate with cooling channels according to claim 1, characterized in that, The oil passage B (205) is located on the edge of the base plate body (20), and short oil pipes B (204) are provided at both ends. The inner side of the oil passage B (205) is also provided with cavity A (230). The oil passage B (205) is connected to cavity A (230), and the oil pump interface A (208) is located at cavity A (230).

5. The aircraft motor base plate with cooling channels according to claim 4, characterized in that, Multiple support protrusions (2051) are also provided at intervals at the connection between the oil passage B (205) and the cavity A (230).

6. The aircraft motor base plate with cooling channels according to claim 4, characterized in that, A cavity B (240) is also provided on one side of cavity A (230), and cavity B (240) is provided with oil pump interface B (209) and radiator interface A (206).

7. The aircraft motor base plate with cooling channel according to claim 1, characterized in that, The base plate body (20) is also provided with a long strip-shaped clearance groove (250), and at least part of the cross-connecting oil pipe in the stator assembly is disposed in the long strip-shaped clearance groove (250).

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