An aircraft electric drive and an eddy current integrated structure thereof

Abstract

The utility model relates to an aircraft electric drive and electric eddy current integrated structure, including outer rotor subassembly, stator subassembly, electric eddy current induction circuit board subassembly and electric eddy current rotor, outer rotor subassembly is rotatably connected with stator subassembly through bearing, and outer rotor subassembly includes rotor casing and the magnet steel fixed in rotor casing inner wall, electric eddy current rotor is fixed in rotor casing end face lower part, and stator subassembly includes stator casing and sets up stator winding on stator casing lateral wall, electric eddy current induction circuit board subassembly is fixed in stator casing's end face, and electric eddy current induction circuit board subassembly with electric eddy current rotor's position corresponds, and axial gap is left. The utility model will drive motor and electric eddy current function depth fusion in a physical unit, compact structure, has promoted power density, in addition electric eddy current effect response speed is extremely fast, can realize millisecond level's brake or high frequency's speed signal acquisition, has promoted system's dynamic response performance and control precision greatly.

Description

Technical Field

[0001] This utility model relates to the field of aircraft electric drive structure technology, specifically an aircraft electric drive and its integrated eddy current structure. Background Technology

[0002] With the rapid development of electric aircraft and drone technology, higher requirements are being placed on the power density, integration, and multifunctionality of drive motors. Traditional aircraft electric drive systems typically use separate motors and sensing modules, such as motors and photoelectric encoders, which results in large axial dimensions, complex structures, and increased weight, making it difficult to meet the requirements for lightweighting and compactness.

[0003] Currently, external rotor permanent magnet synchronous motors are widely used in aircraft propulsion systems due to their advantages such as high torque density and fast dynamic response. However, existing external rotor motors typically only have a drive function. To achieve functions such as speed detection, additional devices are required. However, using separate sensors (such as photoelectric encoders or Hall sensors) for speed measurement not only occupies space but is also susceptible to electromagnetic interference affecting measurement accuracy. In addition, existing electric drive systems still have certain limitations in terms of bearing support structure, heat dissipation management, and controller integration. Most motors use single bearings or simple double bearings for support, resulting in insufficient rotor system rigidity, which can easily lead to vibration or wobbling at high speeds.

[0004] Therefore, there is an urgent need for a highly integrated, multifunctional electric drive structure that can organically combine drive and sensing functions, while optimizing support rigidity, heat dissipation performance and installation structure, in order to meet the urgent needs of modern aircraft for efficient, compact and reliable electric drive systems. Utility Model Content

[0005] To solve the above-mentioned technical problems, the first objective of this utility model is to provide an integrated eddy current structure for aircraft electric drive, which has a fast response speed and occupies little space; the second objective of this utility model is to provide an aircraft electric drive.

[0006] To achieve the first objective of the above-mentioned utility model, the present utility model adopts the following technical solution:

[0007] An integrated eddy current structure for an aircraft's electric drive includes an outer rotor assembly, a stator assembly, an eddy current induction circuit board assembly, and an eddy current rotor. The outer rotor assembly is rotatably connected to the stator assembly via bearings. The outer rotor assembly includes a rotor housing and magnets fixed to the inner wall of the rotor housing. The eddy current rotor is fixed to the lower part of the end face of the rotor housing. The stator assembly includes a stator housing and stator windings disposed on the side wall of the stator housing. The eddy current induction circuit board assembly is fixed to the end face of the stator housing. The eddy current induction circuit board assembly corresponds to the position of the eddy current rotor and has an axial gap.

[0008] As a preferred embodiment, the upper part of the stator housing is provided with a raised edge, the middle part of the rotor housing is provided with a through hole, the edge of the through hole is folded inward and extended downward to form a bearing mounting opening, the bearing is sandwiched between the bearing mounting opening and the raised edge, and the eddy current rotor is fixed on the outside of the bearing mounting opening.

[0009] As a preferred embodiment, the end face of the stator housing is further provided with a mounting groove, the eddy current induction circuit board assembly is fixed in the mounting groove, and the eddy current rotor cooperates with the eddy current induction circuit board assembly.

[0010] As a preferred embodiment, the depth of the mounting groove is greater than or equal to the thickness of the eddy current induction circuit board assembly.

[0011] To achieve the second objective of the above-mentioned utility model, the present utility model adopts the following technical solution:

[0012] An electric drive for an aircraft employs an integrated eddy current structure for an aircraft electric drive as described in any of the above descriptions.

[0013] As a preferred embodiment, the bearings are multiple and arranged side by side along the axial direction. The end faces of the rotor housing and the stator housing are respectively provided with bearing outer ring pressure plates and bearing inner ring pressure plates. The outermost bearing inner and outer rings abut against the bearing inner ring pressure plates and bearing outer ring pressure plates, respectively. The inner wall of the rotor housing is provided with a support ring, and the outer wall of the stator housing is provided with a support step. The inner and outer rings of the bearing inner and outer rings abut against the support step and support ring, respectively. A preload pressure ring is also provided between adjacent bearings.

[0014] As a preferred embodiment, the magnet is glued and fixed to the inner wall of the rotor housing, and a fixing ring is also fixed to the lower end of the rotor housing, the fixing ring abutting against one end of the magnet.

[0015] As a preferred embodiment, the bottom of the stator housing is further provided with a cover plate, and a controller assembly is provided in the accommodating space formed by the cover plate and the stator housing. The winding is connected to the controller assembly, and a heat sink assembly is also provided at the bottom of the cover plate.

[0016] As a preferred embodiment, the stator housing sidewall is further provided with a plurality of fixing posts at intervals at the lower part of the winding for connection with the mounting bracket.

[0017] Compared with the prior art, the beneficial effects of this utility model are as follows:

[0018] This invention deeply integrates the drive motor and eddy current function into a single physical unit, eliminating the need for additional space and connecting components required for installing separate mechanical sensors. The structure is compact and avoids the redundancy and weight associated with traditional discrete structures, greatly optimizing the weight and volume of the aircraft drive system and improving power density. In addition, the eddy current effect has an extremely fast response speed, enabling millisecond-level braking or high-frequency speed signal acquisition, which greatly improves the dynamic response performance and control accuracy of the system. Attached Figure Description

[0019] 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.

[0020] Figure 1 This is a schematic diagram of the overall structure of the aircraft electric drive system according to this utility model;

[0021] Figure 2 This is a schematic diagram of a partial explosion of the electric drive system for an aircraft according to this utility model;

[0022] Figure 3 This is a schematic diagram of the structure of the external rotor assembly of the aircraft electric drive according to this utility model;

[0023] Figure 4 This is a structural schematic diagram of the stator assembly of this utility model;

[0024] Figure 5 This is a schematic diagram of the stator housing of this utility model.

[0025] Figure 6 This is a partially enlarged cross-sectional structural diagram of the electric drive system for aircraft according to this utility model.

[0026] The reference numerals in the accompanying drawings are as follows: 1. Outer rotor assembly; 11. Rotor housing; 12. Magnet; 13. Retaining ring; 110. Bearing outer ring pressure plate; 2. Stator assembly; 21. Stator housing; 210. Bearing inner ring pressure plate; 211. Lug; 212. Mounting groove; 219. Fixing post; 22. Stator winding; 23. Eddy current induction circuit board assembly; 24. Eddy current rotor; 3. Heat sink assembly; 6. Bearing. Detailed Implementation

[0027] 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.

[0028] 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.

[0029] 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.

[0030] 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.

[0031] 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.

[0032] 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.

[0033] The present invention will be further described below with reference to the accompanying drawings and embodiments:

[0034] like Figures 1 to 6 The electric drive for an aircraft shown includes an outer rotor assembly 1, a stator assembly 2, an eddy current induction circuit board assembly 23, and an eddy current rotor 24. The outer rotor assembly 1 is rotatably connected to the stator assembly 2 via a bearing 6. The outer rotor assembly 1 includes a rotor housing 11 and a magnet 12 fixed to the inner wall of the rotor housing 11. The eddy current rotor 24 is fixed to the lower part of the end face of the rotor housing 11. The stator assembly 2 includes a stator housing 21 and a stator winding 22 disposed on the side wall of the stator housing 21. The eddy current induction circuit board assembly 23 is fixed to the end face of the stator housing 21. The eddy current induction circuit board assembly 23 is positioned corresponding to the eddy current rotor 24, and there is an axial gap.

[0035] The stator housing 21 has a raised edge 211 on its upper part, and the rotor housing 11 has a through hole in its middle. The edge of the through hole is folded inward and extends downward to form a bearing mounting opening. The bearing 6 is sandwiched between the bearing mounting opening and the raised edge 211, and the eddy current rotor 24 is fixed to the outside of the bearing mounting opening. The bearing housing and the eddy current rotor mounting position are integrated into the rotor housing, which further saves axial space and makes the structure more compact.

[0036] The aforementioned structure also provides a stable and reliable mounting base for the bearing, enhances the radial and axial support rigidity of the rotor system, helps to suppress vibration and deformation during high-speed operation, and ensures smooth operation. At the same time, by directly fixing the eddy current rotor to the precise bearing mounting port, the coaxiality of the eddy current rotor and the main shaft is ensured, as well as the uniformity of the gap between the rotor and the eddy current induction circuit board assembly 23, thereby improving the efficiency of the eddy current effect and the accuracy of the signal.

[0037] The stator housing 21 has a mounting groove 212 on its end face. The eddy current induction circuit board assembly 23 is fixed in the mounting groove 212, and the eddy current rotor 24 cooperates with the eddy current induction circuit board assembly 23. The mounting groove ensures that the eddy current induction circuit board assembly can be accurately positioned and fixed, maintaining precise parallelism and a constant axial clearance with the rotating eddy current rotor, thus ensuring that the eddy current effect works effectively and stably.

[0038] Meanwhile, embedding the precision circuit board into the mounting slot protects it from damage during assembly or transportation, and prevents cables and other debris from interfering with its working area. Furthermore, the above structure provides a clear mounting reference, simplifies the assembly process, and improves production efficiency and product consistency.

[0039] As a preferred embodiment, the depth of the mounting groove 212 is greater than or equal to the thickness of the eddy current induction circuit board assembly 23. This ensures that the surface of the installed circuit board assembly does not protrude from the end face of the stator housing, completely avoiding the risk of accidental mechanical interference with the rotating eddy current rotor or other adjacent components, thus ensuring high safety. Furthermore, the flat or embedded structure facilitates the flow of surrounding airflow, reduces wind resistance loss, and also provides some benefits for heat dissipation of the circuit board.

[0040] Multiple bearings 6 are arranged side-by-side between the outer rotor assembly and the stator assembly along the axial direction. The end faces of the rotor housing 11 and the stator housing 21 are respectively provided with bearing outer ring pressure plates 110 and bearing inner ring pressure plates 210. The outermost bearing inner and outer rings abut against the bearing inner ring pressure plates 210 and the bearing outer ring pressure plates 110, respectively. The inner wall of the rotor housing 11 is provided with a support ring, and the outer wall of the stator housing 21 is provided with a support step. The innermost bearing inner and outer rings abut against the support step and the support ring, respectively. A preload pressure ring is also provided between adjacent bearings.

[0041] The electric drive of this utility model adopts a multi-bearing configuration, which greatly enhances the support stiffness of the rotor and can effectively suppress shaft deflection and vibration under high speed and high load. It ensures uniform air gap and stable eddy current gap of the motor. At the same time, through the pre-tightening ring and each stage of pressure plate and support structure, a precise pre-tightening force can be applied to the bearing assembly to eliminate bearing clearance and further improve rotational accuracy, stiffness and dynamic response characteristics. It also suppresses the adverse effects of thermal deformation caused by temperature rise at high speed.

[0042] In the outer rotor assembly, the magnet 12 is attached and fixed to the inner wall of the rotor housing 11, and a fixing ring 13 is also fixed to the lower end of the rotor housing 11, with the fixing ring 13 abutting against one end of the magnet 12.

[0043] Under the immense centrifugal force generated by high-speed rotation, relying solely on adhesive to fix the magnets poses a risk. Adding a mechanical retaining ring provides an extremely reliable mechanical lock to the magnets, completely preventing them from falling off and ensuring exceptional safety. Simultaneously, this structure enables the electric drive to withstand higher speeds, overloads, and vibration shocks, meeting the demanding flight conditions required by aircraft.

[0044] The stator housing 21 also has a cover plate at its bottom. The controller assembly is housed within the space formed by the cover plate and the stator housing 21. The winding 22 is connected to the controller assembly. A heat sink assembly 3 is also located at the bottom of the cover plate. Integrating the drive motor stator, eddy current function, and controller into one unit greatly simplifies external wiring, reduces connector failure points, and improves system reliability. The controller is one of the main heat sources; integrating it with the motor housing and sharing the bottom heat sink achieves efficient thermal management. The motor housing and heat sink provide a large heat dissipation area for the controller, ensuring the thermal stability of the controller and motor under continuous high load operation and preventing performance degradation due to overheating.

[0045] The stator housing 21 of this invention features multiple fixed posts 219 spaced apart on its side wall below the winding 22 for connection to a mounting bracket. The stator housing provides a robust and reliable mechanical interface, ensuring the electric drive unit can be securely mounted on the aircraft's support or fuselage and effectively transmit torque and withstand various flight loads. By placing the mounting point at the lower part of the housing, where structural rigidity is better, rather than at the end, and by distributing the multiple fixed posts at intervals, force flow is transmitted more directly, reducing cantilever effects, preventing housing deformation, and ensuring the accuracy of the core air gap and eddy current gap.

[0046] 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.

[0047] 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. An integrated eddy current structure for electric drive of aircraft, characterized in that: The device includes an outer rotor assembly (1), a stator assembly (2), an eddy current induction circuit board assembly (23), and an eddy current rotor (24). The outer rotor assembly (1) is rotatably connected to the stator assembly (2) via a bearing (6). The outer rotor assembly (1) includes a rotor housing (11) and a magnet (12) fixed to the inner wall of the rotor housing (11). The eddy current rotor (24) is fixed to the lower part of the end face of the rotor housing (11). The stator assembly (2) includes a stator housing (21) and a stator winding (22) disposed on the side wall of the stator housing (21). The eddy current induction circuit board assembly (23) is fixed to the end face of the stator housing (21). The eddy current induction circuit board assembly (23) is positioned corresponding to the eddy current rotor (24) and has an axial gap.

2. The integrated eddy current structure for aircraft electric drive according to claim 1, characterized in that, The upper part of the stator housing (21) is provided with a raised edge (211), the middle part of the rotor housing (11) is provided with a through hole, the edge of the through hole is folded inward and extended downward to form a bearing mounting port, the bearing (6) is sandwiched between the bearing mounting port and the raised edge (211), and the eddy current rotor (24) is fixed on the outside of the bearing mounting port.

3. The integrated eddy current structure for aircraft electric drive according to claim 2, characterized in that, The stator housing (21) is also provided with a mounting groove (212) on its end face. The eddy current induction circuit board assembly (23) is fixed in the mounting groove (212), and the eddy current rotor (24) cooperates with the eddy current induction circuit board assembly (23).

4. The integrated eddy current structure for aircraft electric drive according to claim 3, characterized in that, The depth of the mounting groove (212) is greater than or equal to the thickness of the eddy current induction circuit board assembly (23).

5. An electric drive for an aircraft, characterized in that: The electric eddy current integrated structure for aircraft electric drive is adopted as described in any one of claims 1 to 4.

6. An electric drive system for an aircraft according to claim 5, characterized in that, The bearings (6) are multiple and arranged side by side along the axial direction. The rotor housing (11) and stator housing (21) are respectively provided with bearing outer ring pressure plate (110) and bearing inner ring pressure plate (210) on their end faces. The outermost bearing inner and outer rings in the axial direction abut against the bearing inner ring pressure plate (210) and bearing outer ring pressure plate (110) respectively. The inner wall of the rotor housing (11) is provided with a support ring, and the outer wall of the stator housing (21) is provided with a support step. The innermost bearing inner and outer rings in the axial direction abut against the support step and support ring respectively. A pre-tightening pressure ring is also provided between adjacent bearings.

7. An electric drive system for an aircraft according to claim 5, characterized in that, The magnet (12) is attached and fixed to the inner wall of the rotor housing (11). A fixing ring (13) is also fixed at the lower end of the rotor housing (11), and the fixing ring (13) abuts against one end of the magnet (12).

8. An electric drive system for an aircraft according to claim 5, characterized in that, The bottom of the stator housing (21) is also provided with a cover plate, and the controller assembly is provided in the accommodating space formed by the cover plate and the stator housing (21). The winding (22) is connected to the controller assembly, and the bottom of the cover plate is also provided with a heat sink assembly (3).

9. An electric drive system for an aircraft according to claim 5, characterized in that, On the side wall of the stator housing (21), at the lower part of the winding (22), a plurality of fixing posts (219) for connecting with the mounting bracket are also provided at intervals.

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