Aircraft electric drive cooling oil hydraulic control structure

Abstract

The utility model relates to an aircraft electric drive cooling oil hydraulic control structure, including rotor subassembly and stator subassembly through bearing rotation connection, the bottom fixed heat dissipation piece and oil pump of stator subassembly, stator subassembly includes stator casing, winding and seal cover, still be equipped with controller assembly in stator casing, winding is fixed in the outside wall of stator casing, seal cover buckles in winding outside, make the cooling cavity between stator casing and seal cover, still be equipped with the oil return pipeline assembly between heat dissipation piece and cooling cavity, and still be equipped with check valve assembly in one end of oil return pipeline assembly, the top of stator casing still is equipped with oil storage component, and oil storage component communicates with cooling cavity through the integrated pipeline of setting in stator casing, and is equipped with the pressure component of control on -off in oil storage component. The utility model's structure can play to balance pressure, automatic regulation system oil pressure, keep system pressure stable, prevent cooling oil leakage.

Description

Technical Field

[0001] This utility model relates to the field of aircraft electric drive structure technology, and in particular to an aircraft electric drive cooling oil hydraulic control structure. Background Technology

[0002] With the rapid development of advanced aircraft such as electric vertical takeoff and landing (eVTOL) aircraft and unmanned aerial vehicles (UAVs), extremely stringent requirements have been placed on the power density, reliability, and thermal management performance of their drive systems. Direct-drive motors, due to their advantages such as high torque, high efficiency, and simplified transmission structure, have been widely used in the propulsion systems of these aircraft. However, integrating the motor, controller, and necessary cooling and hydraulic control functions into a compact space while meeting aerospace-grade safety and reliability standards remains a significant technical challenge.

[0003] The common oil channel scheme in the existing system uses an electronic oil pump to draw oil from the cooling chamber of the electric drive stator. The electronic oil pump generates high-pressure oil, which enters the radiator. After the radiator dissipates the oil temperature, it enters the IGBT module of the controller component through pipelines to cool the IGBT module. After exiting the IGBT module, the cooling oil enters the cooling chamber of the electric drive stator through pipelines. The coolant flows in the cooling chamber of the electric drive stator and exchanges heat with the winding coil. The cooled oil, after exchanging heat, re-enters the oil pump to complete the next cycle.

[0004] During the oil circulation process described above, according to the characteristic curve of the oil pump, when the pressure increases, the flow rate decreases, and the amount of oil participating in cooling decreases. The heat generated by the electric drive remains unchanged, and as the electric drive operates, the overall oil temperature will rise, leading to thermal runaway. Therefore, it is necessary to control the pipeline pressure to ensure that sufficient oil participates in lubrication.

[0005] Meanwhile, in a conventional oil circuit, the entire oil circuit is in series. The stator cooling chamber at the end of the oil circuit can be regarded as the oil pan, where the oil pressure is the lowest. When the amount of cooling oil increases or the flow rate of cooling oil increases, the flow resistance of each component increases accordingly, and the internal pressure of each part of the pipeline increases. When the internal oil pressure rises, it will exert huge pressure on the seals in the pipeline, especially the seals at the IGBT module. Failure of the seals will cause oil to leak into the electronic control module. Therefore, it is necessary to strictly control the pressure at the IGBT module.

[0006] In addition, when the electric drive is running, the power devices generate a lot of heat, which is immersed in the cooling oil. The flowing cooling oil carries away a lot of heat, causing the temperature of the coolant itself to rise. The coolant expands when heated. Because the oil passage is a closed space, the expansion of the liquid will cause the internal pressure to increase sharply. When the internal pressure reaches a certain threshold, the seal at a certain point will fail, causing the coolant to leak. It is necessary to control the internal pressure of the oil passage to not exceed the sealing threshold.

[0007] In summary, in terms of hydraulic control, it is crucial to ensure that the cooling circuit maintains appropriate oil pressure and flow rate under various operating conditions (such as static ground or high altitude and low temperature). Utility Model Content

[0008] In order to solve the above-mentioned technical problems, the purpose of this utility model is to provide a hydraulic control structure for aircraft electric drive cooling oil. This structure can balance pressure, automatically adjust system oil pressure, maintain system pressure stability, and prevent cooling oil leakage.

[0009] To achieve the above-mentioned objectives, this utility model adopts the following technical solution: A hydraulic control structure for cooling oil in an aircraft electric drive system includes a rotor assembly and a stator assembly rotatably connected by bearings. A radiator and an oil pump are fixed to the bottom of the stator assembly. The stator assembly includes a stator housing, windings, and a sealing cover. A controller assembly is also provided inside the stator housing. The windings are fixed to the outer wall of the stator housing, and the sealing cover is fastened to the outside of the windings, forming a cooling chamber between the stator housing and the sealing cover. An oil inlet and an oil outlet are provided inside the cooling chamber. A return oil pipeline assembly is provided between the radiator and the cooling chamber, and a one-way valve assembly is provided at one end of the return oil pipeline assembly. An oil storage assembly is provided at the top of the stator housing. The oil storage assembly is connected to the cooling chamber through an integrated pipeline provided in the stator housing, and a pressure component for controlling the on / off state is provided in the oil storage assembly.

[0010] As a preferred embodiment, the return oil pipeline assembly includes a connecting pipe and joints fixed at both ends of the connecting pipe, one of which is also connected to a one-way connector.

[0011] As a preferred embodiment, the connector includes a ball joint rod and a connecting rod inserted and fixed inside the ball joint rod, with the connecting rod extending out of the ball joint rod. The connecting rod is hollow inside and open at one end, and the connecting rod communicates with the ball joint rod.

[0012] As a preferred embodiment, the one-way connector includes a connector housing and a one-way valve assembly. One end of the connector housing is fixed to and connected to the connector. The one-way valve assembly includes a one-way valve housing, a cover, a steel ball, and a spring. The one-way valve housing is fixed inside the connector housing. A pressure relief port is provided at the end of the one-way valve housing away from the connector. The cover is fixed inside the one-way valve housing and covers the pressure relief port. The steel ball is located in the cover. The spring is disposed between the steel ball and the cover, so that the steel ball blocks the pressure relief port under the action of elasticity. A side through hole is also provided on the side wall of the cover. After the steel ball compresses the spring, the side through hole communicates with the pressure relief port.

[0013] As a preferred embodiment, gaskets are provided on both sides of the through hole of the ball joint rod, and gaskets are also provided on the side of the connector housing away from the ball joint rod.

[0014] As a preferred embodiment, the oil storage assembly includes an oil storage valve seat and a cover plate. The cover plate is fixed to the top of the oil storage valve seat, and a connection hole is provided at the bottom of the oil storage valve seat. A valve core is also provided inside the oil storage valve seat, and a wave spring is provided between the valve core and the cover plate. The valve core seals the connection hole under the action of the wave spring.

[0015] As a preferred embodiment, O-rings are provided between the inner and outer walls of the valve core and the inner wall of the oil reservoir valve seat.

[0016] As a preferred embodiment, the connection hole is connected to one end of the integrated pipeline, and the bottom of the oil storage valve seat is provided with a sealing ring around the connection hole.

[0017] As a preferred embodiment, the stator housing is located at the lower part of the winding and has an outer edge, and the upper and lower ends of the sealing cover are respectively fixed to the top of the stator housing and the outer edge.

[0018] As a preferred embodiment, the sealing cover is made of carbon fiber and has a raised ring on the top to avoid the winding.

[0019] Compared with the prior art, the beneficial effects of this utility model are as follows: The stator assembly of this invention includes a stator housing, windings, and a sealing cover. The windings are fixed to the outer wall of the stator housing, and the sealing cover is fastened to the outside of the windings to form a cooling chamber. This structure allows cooling oil to directly contact the windings for heat exchange, greatly improving cooling efficiency, preventing overheating of the windings, and extending the motor's lifespan. Simultaneously, a return oil pipeline assembly is provided between the cooling chamber and the radiator, which balances the pressure at both locations. A one-way valve assembly is installed on the return oil pipeline, ensuring that it is normally closed. When the internal pressure does not exceed the one-way valve's opening value, the cooling oil operates along the normal path. However, when the internal pressure of the radiator exceeds the one-way valve's opening value, the return oil pipeline directly connects the radiator and the stator oil chamber, draining the cooling oil from the high-pressure area (radiator) into the low-pressure area (stator cooling chamber). This ensures that the pressure in the high-pressure area does not continue to rise, thereby protecting the IGBT module of the controller assembly at the rear of the radiator from pressure exceeding its safe value.

[0020] In addition, this invention also includes an oil storage assembly, which is connected to the cooling chamber via an integrated pipeline in the stator housing and its on / off state is controlled by a pressure assembly. This design can automatically adjust the system oil pressure, compensate for changes in oil volume caused by temperature variations, maintain stable system pressure, and prevent leakage caused by excessive pressure. Attached Figure Description

[0021] 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.

[0022] Figure 1 and Figure 2 These are schematic diagrams of the overall structure of this utility model from two different angles; Figure 3 This is a cross-sectional structural diagram of the stator assembly and oil storage assembly of this utility model; Figure 4 This is a schematic diagram of the structure of the return oil pipeline assembly of this utility model; Figure 5 This is a cross-sectional structural diagram of the connector of this utility model; Figure 6 This is a cross-sectional structural diagram of the connector and unidirectional connector of this utility model; Figure 7 This is a cross-sectional structural diagram of the oil storage component of this utility model.

[0023] The reference numerals in the accompanying drawings are as follows: 1. Rotor assembly; 21. Stator housing; 211. Integrated piping; 22. Sealing cover; 23. Winding; 3. Radiator; 4. Oil return piping assembly; 41. Connecting pipe; 42. Joint; 420. Ball joint; 421. Connecting rod; 43. One-way joint; 430. Joint housing; 431. One-way valve housing; 4311. Pressure relief port; 432. Cover; 4321. Side through hole; 433. Steel ball; 434. Spring; 44. Gasket; 5. Oil reservoir assembly; 51. Oil reservoir valve seat; 52. Cover plate; 53. Wave spring; 54. Valve core; 542. O-ring; 55. Connecting hole; 551. Sealing ring. Detailed Implementation

[0024] 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.

[0025] 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.

[0026] 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.

[0027] 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.

[0028] 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.

[0029] 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.

[0030] The present invention will be further described below with reference to the accompanying drawings and embodiments: like Figure 1 and Figure 2The diagram illustrates a hydraulic control structure for an aircraft's electric drive cooling oil, comprising a rotor assembly 1 and a stator assembly rotatably connected by bearings. A radiator 3 and an oil pump are fixed to the bottom of the stator assembly. The stator assembly includes a stator housing 21, windings 23, and a sealing cover 22. A controller assembly is also housed within the stator housing 21. The windings 23 are fixed to the outer wall of the stator housing 21. The sealing cover 22 is fastened to the outer side of the windings 23. The stator housing 21 also has an outer edge located below the windings 23. The upper and lower ends of the sealing cover 22 are respectively connected to the top of the stator housing 21 and... The outer edge is fixed, forming a cooling cavity between the stator housing 21 and the sealing cover 22. The cooling cavity is also provided with an oil inlet and an oil outlet. The sealing cover 22 is made of carbon fiber and has a raised ring at the top to avoid the winding 23. An oil return pipeline assembly 4 is also provided between the radiator 3 and the cooling cavity. One end of the oil return pipeline assembly 4 is also provided with a one-way valve assembly. An oil storage assembly 5 is also provided at the top of the stator housing 21. The oil storage assembly 5 is connected to the cooling cavity through an integrated pipeline 211 provided in the stator housing 21. The oil storage assembly 5 is provided with a pressure component for controlling the on / off state.

[0031] The stator assembly of this invention features a bottom-mounted radiator and oil pump, forming a compact cooling system layout that facilitates installation and maintenance within the limited space of an aircraft. Simultaneously, the controller assembly is integrated within the stator housing, reducing external wiring and improving the system's anti-interference capability and reliability, making it suitable for the high-vibration environment of aircraft. This invention also includes an oil return pipeline assembly to balance the pressure between the radiator and the cooling chamber, and an oil reservoir assembly on the stator housing further adjusts the pressure within the cooling chamber.

[0032] like Figures 4 to 6 As shown, the return oil pipeline assembly 4 includes a connecting pipe 41 and connectors 42 fixed at both ends of the connecting pipe 41, one of which is also connected to a one-way connector 43. The connector 42 includes a ball-joint rod 420 and a connecting rod 421 inserted and fixed within the ball-joint rod 420, with the connecting rod 421 extending beyond the ball-joint rod 420. The connecting rod 421 is hollow inside and open at one end, communicating with the ball-joint rod 420. In the above structure, the connector uses a combination of a ball-joint rod and a connecting rod. The ball-joint rod allows for a certain angle adjustment, facilitating pipeline alignment during installation and adapting to the complex spatial layout inside the aircraft.

[0033] The one-way connector 43 includes a connector housing 430 and a one-way valve assembly. One end of the connector housing 430 is fixed to and communicates with the connector 42. The one-way valve assembly includes a one-way valve housing 431, a cover 432, a steel ball 433, and a spring 434. The one-way valve housing 431 is fixed inside the connector housing 430. A pressure relief port 4311 is provided at the end of the one-way valve housing 431 away from the connector 42. The cover 432 is fixed in the one-way valve housing 431 and covers the pressure relief port 4311. The steel ball 433 is located in the cover 432. The spring 434 is disposed between the steel ball 433 and the cover 432, so that the steel ball 433 blocks the pressure relief port 4311 under the action of elasticity. A side through hole 4321 is also provided on the side wall of the cover 432. After the steel ball 433 compresses the spring 434, the side through hole 4321 communicates with the pressure relief port 4311.

[0034] The aforementioned one-way valve assembly uses spring pressure to block the pressure relief port with a steel ball, achieving one-way closure. When the oil pressure is sufficient, the steel ball compresses the spring, opening the pressure relief port and allowing oil to flow through the side passage. This structure is simple, reliable, and responsive, ensuring one-way oil flow. The design of the pressure relief port and side passage allows for automatic pressure relief when the system pressure is too high, preventing damage to pipelines or components and improving safety.

[0035] Gaskets 44 are provided on both sides of the through hole of the ball joint rod 420, and gaskets 44 are also provided on the side of the connector housing 430 away from the ball joint rod 420. The gaskets on both sides of the through hole of the ball joint rod and on the side of the connector housing away from the ball joint rod provide an additional sealing layer, effectively preventing oil leakage from the connection. At the same time, the gaskets can absorb vibration and shock, reduce wear on the connector components, and extend their service life, making them particularly suitable for the high-vibration environment of aircraft.

[0036] Under normal conditions, to ensure the cooling effect of the IGBT module, the one-way connector in the oil return pipeline assembly prevents the radiator from being connected to the cooling chamber. When the internal pressure of the cooling system exceeds the pressure value that the IGBT module can withstand, the one-way valve assembly opens, the pressure relief circuit is opened, and the high-pressure cooling oil in the radiator is guided to the relatively low-pressure stator cooling chamber through the oil return pipeline assembly. After the pressure relief circuit is opened, the internal pressure of the oil passage is controlled, the cooling capacity of the oil pump is guaranteed, and all seals are within a safe range.

[0037] Once the pressure inside the stator's cooling chamber and the radiator is balanced, if the electric drive requires continuous high heat generation, the temperature of the cooling oil will also continue to rise. The heated cooling oil will expand further, and the internal pressure will continue to rise. Therefore, it is necessary to design an oil storage component, which is connected to the stator cooling chamber where the pressure is relatively low.

[0038] like Figure 3 and Figure 7As shown, the oil storage assembly 5 includes an oil storage valve seat 51 and a cover plate 52. The cover plate 52 is fixed to the top of the oil storage valve seat 51. A connection hole 55 is provided at the bottom of the oil storage valve seat 51. A valve core 54 is also provided inside the oil storage valve seat 51. A wave spring 53 is also provided between the valve core 54 and the cover plate 52. The valve core 54 blocks the connection hole 55 under the action of the wave spring 53. A vent plug assembly is also arranged on the cover plate to avoid additional resistance caused by spatial changes when the wave spring moves. The oil storage assembly is cylindrical in shape, and the middle area adopts a hollow structure to avoid the space of the aircraft's pitch motor.

[0039] O-rings 541 are provided between the inner and outer walls of the valve core 54 and the inner wall of the oil reservoir valve seat 51. The O-rings between the inner and outer walls of the valve core and the inner wall of the oil reservoir valve seat form a double sealing structure, effectively preventing oil leakage from around the valve core and ensuring pressure control accuracy. The connecting hole 55 is connected to one end of the integrated pipeline 211, and a sealing ring 551 is also provided at the bottom of the oil reservoir valve seat 51 around the connecting hole 55. The connection hole is connected to the integrated pipeline, ensuring smooth flow of oil from the oil reservoir assembly to the cooling chamber and reducing pressure loss; and the sealing ring around the connecting hole enhances the sealing performance at the connection between the oil reservoir valve seat and the stator housing, preventing oil leakage from the interface.

[0040] The aforementioned oil storage component is normally in a closed state. When the internal pressure of the oil passage in the electric drive cooling system continues to rise even with the one-way valve component of the return oil pipeline component open, the oil pressure exceeds the set threshold. The oil pressure pushes the valve core, and the rear wave spring is compressed. The volume of the sealing area between the valve core and the valve seat increases, and the cooling oil enters the newly added area. The pressure in the oil passage is released, preventing it from rising further and thus protecting the entire seal. When the oil temperature decreases, the pressure in the oil passage of the electric drive cooling system also decreases. Under the action of the wave spring, the valve core is pushed to reset, and the cooling oil in the oil storage chamber component returns to the circulation loop under the pressure of the valve core to participate in normal cooling. The above process completes one working stroke.

[0041] 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.

[0042] 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 hydraulic control structure for an aircraft's electric drive cooling oil, characterized in that, The system includes a rotor assembly (1) and a stator assembly rotatably connected by bearings. A radiator (3) and an oil pump are fixed to the bottom of the stator assembly. The stator assembly includes a stator housing (21), windings (23), and a sealing cover (22). A controller assembly is also provided inside the stator housing (21). The windings (23) are fixed to the outer wall of the stator housing (21), and the sealing cover (22) is fastened to the outside of the windings (23), such that the stator housing (21) and the sealing cover (22) are connected. A cooling chamber is formed between the radiator (3) and the cooling chamber. An oil inlet and an oil outlet are provided in the cooling chamber. An oil return pipeline assembly (4) is provided between the radiator (3) and the cooling chamber. A one-way valve assembly is provided at one end of the oil return pipeline assembly (4). An oil storage assembly (5) is provided at the top of the stator housing (21). The oil storage assembly (5) is connected to the cooling chamber through an integrated pipeline (211) provided in the stator housing (21). A pressure assembly for controlling the on / off state is provided in the oil storage assembly (5).

2. The aircraft electric drive cooling oil hydraulic control structure according to claim 1, characterized in that, The return oil pipeline assembly (4) includes a connecting pipe (41) and joints (42) fixed at both ends of the connecting pipe (41), one of which is also connected to a one-way joint (43).

3. The aircraft electric drive cooling oil hydraulic control structure according to claim 2, characterized in that, The connector (42) includes a ball joint rod (420) and a connecting rod (421) inserted and fixed inside the ball joint rod (420), and the connecting rod (421) extends out of the ball joint rod (420). The connecting rod (421) is hollow inside and open at one end, and the connecting rod (421) is connected to the ball joint rod (420).

4. The aircraft electric drive cooling oil hydraulic control structure according to claim 3, characterized in that, The one-way connector (43) includes a connector housing (430) and a one-way valve assembly. One end of the connector housing (430) is fixed to and communicates with the connector (42). The one-way valve assembly includes a one-way valve housing (431), a cover (432), a steel ball (433), and a spring (434). The one-way valve housing (431) is fixed inside the connector housing (430). A pressure relief port (4311) is provided at the end of the one-way valve housing (431) away from the connector (42). The cover (432) is fixed to... In the one-way valve housing (431), the pressure relief port (4311) is covered. The steel ball (433) is located in the cover (432). The spring (434) is arranged between the steel ball (433) and the cover (432), so that the steel ball (433) blocks the pressure relief port (4311) under the action of elasticity. A side through hole (4321) is also provided on the side wall of the cover (432). After the steel ball (433) compresses the spring (434), the side through hole (4321) communicates with the pressure relief port (4311).

5. The aircraft electric drive cooling oil hydraulic control structure according to claim 4, characterized in that, Gaskets (44) are provided on both sides of the through hole of the ball joint rod (420), and gaskets (44) are also provided on the side of the connector housing (430) away from the ball joint rod (420).

6. The hydraulic control structure for aircraft electric drive cooling oil according to claim 1, characterized in that, The oil storage assembly (5) includes an oil storage valve seat (51) and a cover plate (52). The cover plate (52) is fixed on the top of the oil storage valve seat (51). A connection hole (55) is provided at the bottom of the oil storage valve seat (51). A valve core (54) is also provided inside the oil storage valve seat (51). A wave spring (53) is also provided between the valve core (54) and the cover plate (52). The valve core (54) seals the connection hole (55) under the action of the wave spring (53).

7. The aircraft electric drive cooling oil hydraulic control structure according to claim 6, characterized in that, O-rings (541) are provided between the inner and outer walls of the valve core (54) and the inner wall of the oil storage valve seat (51).

8. The aircraft electric drive cooling oil hydraulic control structure according to claim 6, characterized in that, The connecting hole (55) is connected to one end of the integrated pipeline (211), and the bottom of the oil storage valve seat (51) is provided with a sealing ring (551) around the connecting hole (55).

9. The hydraulic control structure for aircraft electric drive cooling oil according to claim 1, characterized in that, The stator housing (21) is located at the lower part of the winding (23) and has an outer edge. The upper and lower ends of the sealing cover (22) are fixed to the top and outer edge of the stator housing (21) respectively.

10. The aircraft electric drive cooling oil hydraulic control structure according to claim 1, characterized in that, The sealing cover (22) is made of carbon fiber and has a raised ring on the top to avoid the winding (23).

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