Non-contact electric energy transmission device for aircraft rotating part

Abstract

The invention discloses a non-contact electric energy transmission device for an aircraft rotating part. The non-contact electric energy transmission device comprises a fixed support, a mounting cylinder, a rotating shaft, a basic cylindrical fixed magnet assembly and a basic cylindrical movable magnet assembly. The mounting cylinder is fixedly connected to the fixing support, the fixing support is fixedly connected with a static part such as a fuselage of the aircraft, and the rotating shaft is connected to a rotating part of the aircraft. In the electric energy transmission process, a power supply transmits high-frequency alternating-current electric energy to the basic primary winding, an alternating magnetic field is generated in the primary winding, and according to the electromagnetic induction principle, the alternating magnetic field passes through the basic primary magnetic core, the basic secondary magnetic core and the basic secondary winding, so that induced electromotive force is generated in the basic secondary winding; and non-contact transmission of electric energy from the basic cylindrical fixed magnet assembly to the basic cylindrical movable magnet assembly is realized. Wires and electric brushes are not arranged in the whole electric energy transmission process, so that various defects caused by poor mechanical friction and electromagnetic property in the prior art are overcome.

Description

Technical Field

[0001] This application relates to the field of power transmission technology, and in particular to a non-contact power transmission device for rotating components of an aircraft. Background Technology

[0002] In the field of power transmission, traditional contact-type power transmission devices are widely used. Contact-type power transmission transfers power by directly connecting the power source and the power-consuming equipment with a wire. This method can reliably transmit power in a stable and fixed environment and has advantages such as mature technology and relatively low cost.

[0003] However, in scenarios involving the power supply of rotating components, especially those in aircraft, contact-based power transmission has significant drawbacks. During flight, the rotating components operate at high speeds, and the constant friction between brushes and slip rings in contact-based transmission devices accelerates wear, shortens service life, and increases maintenance costs and downtime. Furthermore, frictional heat can pose safety hazards, and energy loss due to friction reduces power transmission efficiency, wasting energy. Additionally, the physical connections of contact-based transmission limit the structural design and spatial layout of aircraft rotating components, making it difficult to meet the design requirements of lightweight, compact design, and complex spatial environments. Moreover, in special flight environments such as high humidity, high dust, and high vibration, the reliability of contact-based transmission devices is affected, making them prone to poor contact, short circuits, and other faults, impacting the normal operation of the aircraft.

[0004] Therefore, researchers have conducted extensive studies on contactless power transmission. Existing contactless power transmission methods include inductive and magnetic resonance methods. Inductive contactless power transmission is based on the principle of electromagnetic induction, generating an alternating magnetic field through a primary coil, which induces an electromotive force in a secondary coil, thus achieving power transmission. However, inductive transmission has a short transmission distance and is generally suitable for scenarios where the primary and secondary coils are in fixed relative positions and close to each other. The motion characteristics of rotating components in aircraft cause the distance and angle between the primary and secondary coils to constantly change, making it difficult for inductive transmission to stably power rotating components. Moreover, inductive transmission is inefficient when transmitting high-power electrical energy, making it difficult to meet the power requirements of rotating components in aircraft, such as high-power propeller motors.

[0005] Magnetic resonance non-contact power transfer utilizes the principle of magnetic resonance to achieve efficient power transfer in the near field through two resonant coils. In some small electronic devices, such as wirelessly charged earphones and smartwatches, magnetic resonance non-contact power transfer demonstrates convenience, eliminating the constraints of cables. However, when applied to powering rotating components of aircraft, this method also presents several challenges. First, the transmission efficiency of magnetic resonance transfer drops sharply when the distance and angle change significantly. During operation, the relative position and angle of rotating components in an aircraft constantly change, making it difficult to guarantee stable transmission efficiency. Second, the size and weight of magnetic resonance equipment are substantial, adding an extra burden to aircraft that are highly sensitive to weight, thus negatively impacting flight performance. Furthermore, magnetic resonance transfer suffers from poor electromagnetic compatibility, easily causing electromagnetic interference to other precision electronic devices on the aircraft, affecting the overall stability of the aircraft's electronic systems.

[0006] Currently, there is limited research on non-contact power transmission devices suitable for special scenarios such as rotating parts of aircraft. Existing related technologies have significant room for improvement in terms of power transmission power, stability, and adaptability to complex operating conditions of aircraft. Summary of the Invention

[0007] This application provides a non-contact power transmission device for rotating components of aircraft, which solves the technical problems of low power transmission efficiency and poor stability in existing non-contact power transmission technologies, making it difficult to meet the complex power demands of aircraft operating conditions. The technical solution is as follows:

[0008] A contactless power transfer device for rotating components of an aircraft, comprising:

[0009] A fixed bracket is used to fixably connect to the stationary part of the aircraft. The fixed bracket includes a mounting cylinder; a rotating shaft is used to fixably connect to the rotating parts of the aircraft; a basic cylindrical fixed magnet assembly is fixedly connected to the inner wall of the mounting cylinder; and a basic cylindrical moving magnet assembly is fixedly connected to the rotating shaft. The basic cylindrical moving magnet assembly is located inside the basic cylindrical fixed magnet assembly and is coaxial with the basic cylindrical fixed magnet assembly. There is a gap between the basic cylindrical moving magnet assembly and the basic cylindrical fixed magnet assembly.

[0010] Optionally, the basic cylindrical fixed magnet assembly includes: a basic primary magnetic core and a basic primary winding; the basic primary magnetic core is cylindrical and fixedly connected to the inner wall of the mounting cylinder, one end of the basic primary magnetic core is provided with an inner flange extending toward the center of the basic primary magnetic core, and the other end is detachably connected with a first retaining ring, and the basic primary winding is disposed in the annular groove formed by the inner flange and the first retaining ring; the basic cylindrical moving magnet assembly includes: a basic secondary magnetic core and a basic secondary winding; the basic secondary magnetic core is cylindrical and fixedly connected to the rotating shaft, one end of the basic secondary magnetic core is provided with an outer flange extending away from the center of the basic secondary magnetic core, and the other end is detachably connected with a second retaining ring, and the basic secondary winding is disposed in the annular groove formed by the outer flange and the second retaining ring.

[0011] Optionally, the non-contact power transmission device for the rotating components of an aircraft further includes at least one cascaded cylindrical fixed magnet assembly axially connected between the basic primary magnetic core and the first retaining ring, and at least one cascaded cylindrical moving magnet assembly axially connected between the basic secondary magnetic core and the second retaining ring, wherein the number of the cascaded cylindrical fixed magnet assemblies and the cascaded cylindrical moving magnet assemblies are equal; the cascaded cylindrical fixed magnet assembly includes a cascaded primary magnetic core and a cascaded primary winding; the cascaded primary magnetic core is cylindrical, and both ends of the cascaded primary magnetic core are provided with first pin holes, and the cascaded primary winding is sleeved outside the cascaded primary magnetic core; the cascaded cylindrical moving magnet assembly includes The system comprises: cascaded secondary magnetic cores and cascaded secondary windings; the cascaded secondary magnetic cores are cylindrical, with second pin holes at both ends, and the cascaded secondary windings are sleeved around the cascaded secondary magnetic cores; a third pin hole is provided at the end of the basic primary magnetic core near the cascaded primary magnetic core; a fourth pin hole is provided at the end face of the basic secondary magnetic core near the cascaded secondary magnetic core; the basic primary magnetic core and the cascaded primary magnetic cores are connected by pins; the basic secondary magnetic core and the cascaded secondary magnetic cores are connected by pins; the cascaded primary magnetic core near the first retaining ring is connected to the first retaining ring by screws; the cascaded secondary magnetic core near the second retaining ring is connected to the second retaining ring by screws.

[0012] Optionally, the output terminal of the basic secondary winding is connected in parallel with the output terminal of each of the cascaded secondary windings.

[0013] Optionally, the basic primary winding, the basic secondary winding, the cascaded primary winding, and the cascaded secondary winding are all wound with Litz wire, which is formed by twisting together multiple strands of fine wire.

[0014] Optionally, the basic primary magnetic core, the basic secondary magnetic core, the cascaded primary magnetic core, and the cascaded secondary magnetic core are all made of amorphous alloy material through processing and pressing.

[0015] Optionally, when the non-contact power transmission device for the rotating components of an aircraft includes only a basic cylindrical fixed magnet assembly and a basic cylindrical moving magnet assembly, the basic primary magnetic core and the first retaining ring form a cylindrical shape; the basic secondary magnetic core and the second retaining ring form an H-shaped structure; when the non-contact power transmission device for the rotating components of an aircraft includes a basic cylindrical fixed magnet assembly and a cascaded cylindrical fixed magnet assembly, as well as a basic cylindrical moving magnet assembly and a cascaded cylindrical moving magnet assembly, the basic primary magnetic core, the cascaded primary magnetic core, and the first retaining ring form a cylindrical shape; the basic secondary magnetic core, the cascaded secondary magnetic core, and the second retaining ring form an H-shaped structure.

[0016] Optionally, an adhesive layer is provided between the basic primary winding and the basic primary magnetic core; a positioning frame is provided between the basic secondary winding and the basic secondary magnetic core; an adhesive layer is provided between the cascaded primary winding and the cascaded primary magnetic core; and a positioning frame is provided between the cascaded secondary winding and the cascaded secondary magnetic core.

[0017] The beneficial effects of the technical solutions provided in this application include:

[0018] A non-contact power transmission device for rotating components of an aircraft includes: a fixed bracket, a mounting cylinder, a rotating shaft, a basic cylindrical fixed magnet assembly, and a basic cylindrical moving magnet assembly.

[0019] The mounting cylinder is fixedly connected to a fixed bracket, which is fixedly connected to a stationary part of the aircraft, such as the fuselage. The rotating shaft is connected to a rotating part of the aircraft, such as the propeller shaft. During power transmission, the power source delivers high-frequency alternating current to the primary winding of the foundation, generating an alternating magnetic field in the primary winding. According to the principle of electromagnetic induction, the alternating magnetic field passes through the primary magnetic core, the secondary magnetic core, and the secondary winding, thereby inducing an electromotive force in the secondary winding, achieving non-contact power transmission from the basic cylindrical fixed magnet assembly to the basic cylindrical moving magnet assembly. Throughout the power transmission process, there are no wires or brushes, overcoming various drawbacks caused by mechanical friction and poor electromagnetic characteristics in existing technologies. This improves the stability, reliability, and efficiency of power transmission, meeting the power supply requirements of rotating components under complex operating conditions, and providing a more reliable power transmission solution for aircraft design and operation. The non-contact power transmission device for rotating components of aircraft proposed in this application also has the following technical advantages: First, it eliminates the traditional contact-type power transmission method, avoiding frictional losses caused by mechanical contact. This not only significantly extends the lifespan of the device and reduces maintenance costs, but also eliminates potential safety hazards caused by frictional heat. Second, the adoption of a cascadeable, rotary, and separable structure greatly enhances the device's adaptability to different power requirements. In aircraft, different rotating components, such as small servo motors and large propeller motors, have significantly different power demands. Flexible cascading allows for easy adjustment of power output. In contrast, traditional single-transformer structures struggle to meet diverse power requirements without altering the overall size and weight of the equipment. Third, the application of Litz wire and amorphous alloy cores significantly improves power transmission efficiency. Litz wire effectively reduces the skin effect and proximity effect under high-frequency currents, reducing conductor resistance loss; the amorphous alloy core, with its excellent soft magnetic properties, reduces hysteresis and eddy current losses. The synergistic effect of both significantly reduces energy loss during power transmission. Fourth, the device's non-contact design and optimized structural layout allow for more flexible structural design and spatial arrangement of the aircraft's rotating components. By eliminating the physical connections required for contact-based power transmission, aircraft design can more freely incorporate compact and lightweight designs for rotating components, contributing to improved flight performance and maneuverability. Furthermore, by reducing the risk of failure due to physical contact, this device can maintain stable and reliable power transmission in harsh flight environments such as high humidity, high dust, and high vibration, further enhancing the operational safety and stability of the aircraft under complex conditions.

[0020] Other features and advantages of this disclosure will be described in detail in the following detailed description section. Attached Figure Description

[0021] To more clearly illustrate the technical solutions in the embodiments of this application, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0022] Figure 1 This is a perspective view of a non-contact electrical power transmission device for a rotating component of an aircraft, provided in an embodiment of this application.

[0023] Figure 2 This is a cross-sectional view of a non-contact electrical power transmission device for a rotating component of an aircraft, provided in an embodiment of this application.

[0024] Figure 3 This is an exploded view of a non-contact electrical power transmission device for a rotating component of an aircraft, provided in an embodiment of this application.

[0025] Figure 4 This is a perspective view of another contactless power transmission device for rotating components of an aircraft provided in the embodiments of this application;

[0026] Figure 5 This is a cross-sectional view of another contactless power transmission device for a rotating component of an aircraft provided in this application embodiment;

[0027] Figure 6 This is an exploded view of another contactless power transmission device for rotating components of an aircraft, provided in an embodiment of this application.

[0028] Figure 7 This is an exploded view of a basic cylindrical fixed magnet assembly, a basic cylindrical moving magnet assembly, a cascaded cylindrical fixed magnet assembly, and a cascaded cylindrical moving magnet assembly in another contactless power transmission device for rotating components of an aircraft, provided in an embodiment of this application.

[0029] Explanation of reference numerals in the attached figures

[0030] 1-Fixed bracket; 2-Mounting cylinder; 3-Rotating shaft; 4-Basic cylindrical fixed magnet assembly; 41-Basic primary magnetic core; 411-Inner flange; 412-Third pin hole; 42-Basic primary winding; 43-First retaining ring; 5-Basic cylindrical moving magnet assembly; 51-Basic secondary magnetic core; 511-Outer flange; 512-Fourth pin hole; 52-Basic secondary winding; 53-Second retaining ring; 6-Cascaded cylindrical fixed magnet assembly; 61-Cascaded primary magnetic core; 611-First pin hole; 62-Cascaded primary winding; 7-Cascaded cylindrical moving magnet assembly; 71-Cascaded secondary magnetic core; 711-Second pin hole; 72-Cascaded secondary winding; 8-Pin; 9-Screw. Detailed Implementation

[0031] The specific embodiments of this disclosure will be described in detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are for illustration and explanation only and are not intended to limit this disclosure.

[0032] In this disclosure, unless otherwise stated, directional terms such as "upper" and "lower" generally refer to the relative positions of the corresponding components in the direction of gravity when they are in use, and "inner" and "outer" refer to their relative positions to the contours of the corresponding components themselves. Furthermore, the terms "first," "second," etc., used in this disclosure are for distinguishing one element from another and do not have sequential or importance implications. In the following description, when referring to the accompanying drawings, unless otherwise explained, the same reference numerals in different drawings denote the same or similar elements.

[0033] According to the embodiments of this application, refer to Figures 1 to 7 As shown, a non-contact power transmission device for rotating components of an aircraft includes: a fixed bracket 1, a mounting cylinder 2, a rotating shaft 3, a basic cylindrical fixed magnet assembly 4, and a basic cylindrical moving magnet assembly 5.

[0034] Among them, reference Figure 1 and Figure 2 A fixed bracket 1 is used to fix and connect to the stationary part of the aircraft. The fixed bracket 1 includes a mounting cylinder 2. The rotating shaft 3 is used to fix and connect to the rotating parts of the aircraft. A basic cylindrical fixed magnet assembly 4 is fixedly connected to the inner wall of the mounting cylinder 2. A basic cylindrical moving magnet assembly 5 is fixedly connected to the rotating shaft 3. The basic cylindrical moving magnet assembly 5 is located inside the basic cylindrical fixed magnet assembly 4 and is coaxial with the basic cylindrical fixed magnet assembly 4. There is a gap between the basic cylindrical moving magnet assembly 5 and the basic cylindrical fixed magnet assembly 4.

[0035] In the above embodiment, the mounting cylinder 2 is fixedly connected to the fixed bracket 1, which is fixedly connected to the stationary part of the aircraft, such as the fuselage. The rotating shaft 3 is connected to the rotating part of the aircraft, such as the propeller shaft. During the power transmission process, the power source delivers high-frequency AC power to the primary winding 42, generating an alternating magnetic field in the primary winding. According to the principle of electromagnetic induction, the alternating magnetic field passes through the primary magnetic core 41, the secondary magnetic core 51, and the secondary winding 52, thereby generating an induced electromotive force in the secondary winding 52. This achieves non-contact power transmission from the basic cylindrical fixed magnet assembly 4 to the basic cylindrical moving magnet assembly 5. Throughout the power transmission process, there are no wires or brushes, overcoming various drawbacks caused by mechanical friction and poor electromagnetic characteristics in the prior art. This improves the stability, reliability, and efficiency of power transmission, meeting the power supply requirements of rotating components under complex operating conditions, and providing a more reliable power transmission solution for aircraft design and operation.

[0036] According to the embodiments of this application, refer to Figures 1 to 3 As shown, the basic cylindrical magnet assembly 4 may include: a basic primary magnetic core 41 and a basic primary winding 42. (Referring to...) Figure 2 and Figure 3 As shown, the basic primary magnetic core 41 is cylindrical and fixedly connected to the inner wall of the mounting cylinder 2. One end of the basic primary magnetic core 41 is provided with an inner flange 411 extending towards the center of the basic primary magnetic core 41, and the other end is detachably connected to a first retaining ring 43. The basic primary winding 42 is disposed in the annular groove formed by the inner flange 411 and the first retaining ring 43. This design ensures that the basic primary winding 42 is reliably located on the inner wall of the basic primary magnetic core 41.

[0037] refer to Figure 2 and Figure 3 As shown, the basic cylindrical moving magnet assembly 5 includes a basic secondary magnetic core 51 and a basic secondary winding 52. The basic secondary magnetic core 51 is cylindrical and fixedly connected to the rotating shaft 3. One end of the basic secondary magnetic core 51 has an outer flange 511 extending away from the center of the basic secondary magnetic core 51, and the other end is detachably connected to a second retaining ring 53. The basic secondary winding 52 is disposed within an annular groove formed by the outer flange 511 and the second retaining ring 53. This design ensures that the basic secondary winding 52 is reliably located on the outer wall of the basic secondary magnetic core 51.

[0038] According to the embodiments of this application, refer to Figures 4 to 7As shown, the non-contact power transmission device for the rotating components of an aircraft further includes at least one cascaded cylindrical fixed magnet assembly 6 connected axially between the basic primary magnetic core 41 and the first retaining ring 43, and at least one cascaded cylindrical moving magnet assembly 7 connected axially between the basic secondary magnetic core 51 and the second retaining ring 53, and the number of the cascaded cylindrical fixed magnet assembly 6 and the cascaded cylindrical moving magnet assembly 7 are equal.

[0039] For details, please refer to Figure 6 and Figure 7 As shown, the cascaded cylindrical magnet assembly 6 includes a cascaded primary magnetic core 61 and a cascaded primary winding 62; the cascaded primary magnetic core 61 is cylindrical, and both ends of the cascaded primary magnetic core 61 are provided with first pin holes 611, and the cascaded primary winding 62 is sleeved on the outside of the cascaded primary magnetic core 61.

[0040] refer to Figure 6 and Figure 7 As shown, the cascaded cylindrical moving magnet assembly 7 includes: a cascaded secondary magnetic core 71 and a cascaded secondary winding 72; the cascaded secondary magnetic core 71 is cylindrical, and a second pin hole 711 is provided at both ends of the cascaded secondary magnetic core 71; the cascaded secondary winding 72 is sleeved on the cascaded secondary magnetic core 71.

[0041] refer to Figure 6 and Figure 7 As shown, a third pin hole 412 is provided at the end of the base primary magnetic core 41 near the cascaded primary magnetic core 61. (Reference) Figure 7 As shown, a fourth pin hole 512 is provided on the end face of the basic secondary core 51 near the cascaded secondary core 71; the basic primary core 41 and the cascaded primary core 61 are connected by a pin 8; the basic secondary core 51 and the cascaded secondary core 71 are connected by a pin 8.

[0042] refer to Figure 7 As shown, the cascaded primary magnetic core 61 near the first retaining ring 43 is connected to the first retaining ring 43 by screw 9; the cascaded secondary magnetic core 71 near the second retaining ring 53 is connected to the second retaining ring 53 by screw 9.

[0043] In the above embodiments, to improve wireless power transmission efficiency, one or more cascaded cylindrical magnet assemblies 6 can be axially fixedly connected to one end of the basic cylindrical magnet assembly 4, while a corresponding number of cascaded cylindrical moving magnet assemblies 7 can be axially fixedly connected to the corresponding end of the basic cylindrical moving magnet assembly 5. This connection method enables the various contactless power transmission devices to work collaboratively, thereby effectively increasing the power output. For example, when the output power of a single contactless power transmission device is P1, after n units are cascaded, under ideal conditions, the overall output power can reach n*P1. Through this flexible cascading method, customized configurations can be made according to the power requirements of different rotating parts of the aircraft.

[0044] Specifically, the output terminal of the basic secondary winding 52 is connected in parallel with the output terminal of each of the cascaded secondary windings 72.

[0045] According to embodiments of this application, the basic primary winding 42, the basic secondary winding 52, the cascaded primary winding 62, and the cascaded secondary winding 72 are all wound with Litz wire, which is formed by twisting multiple strands of fine wire together. During power transmission, the performance of the wires and the magnetic core has a significant impact on energy loss. Litz wire, composed of multiple strands of fine wire, effectively reduces the skin effect and proximity effect under high-frequency currents compared to traditional single wires, reducing energy loss due to wire resistance and improving power transmission efficiency. The Litz wire is wound into winding coils using a winding frame or tooling according to the corresponding winding sequence, impregnated with enamel, and then fixed to the inside of the basic primary magnetic core 41 or the cascaded primary magnetic core 61 by adhesive. The Litz wire is then wound onto the outside of the basic secondary magnetic core 51 or the cascaded secondary magnetic core 71 manually or using automated equipment, according to the corresponding winding sequence.

[0046] According to embodiments of this application, the basic primary magnetic core 41, the basic secondary magnetic core 51, the cascaded primary magnetic core 61, and the cascaded secondary magnetic core 71 are all manufactured by pressing amorphous alloy materials. Amorphous alloy magnetic cores possess excellent soft magnetic properties, exhibiting high permeability and low coercivity, enabling them to generate high magnetic induction intensity under relatively low excitation current, while also exhibiting very low hysteresis and eddy current losses. This significantly reduces energy loss in the magnetic core portion during operation of the contactless power transmission device, further improving the overall power transmission efficiency of the device.

[0047] According to an embodiment of this application, when the non-contact power transmission device for the rotating components of an aircraft only includes a basic cylindrical fixed magnet assembly 4 and a basic cylindrical moving magnet assembly 5, the basic primary magnetic core 41 and the first retaining ring 43 form a cylindrical shape; the basic secondary magnetic core 51 and the second retaining ring 53 form an H-shaped structure.

[0048] When the non-contact power transmission device for the rotating components of an aircraft includes a basic cylindrical fixed magnet assembly 4 and a cascaded cylindrical fixed magnet assembly 6, as well as a basic cylindrical moving magnet assembly 5 and a cascaded cylindrical moving magnet assembly 7, the basic primary magnetic core 41, the cascaded primary magnetic core 61 and the first retaining ring 43 form a cylindrical shape; the basic secondary magnetic core 51, the cascaded secondary magnetic core and the second retaining ring 53 form an H-shaped structure.

[0049] In the above embodiments, it is necessary to ensure that the magnetic coupling between the basic primary winding 42 and the basic secondary winding 52, as well as the cascaded primary winding 62 and the cascaded secondary winding 72, can be stably maintained during relative rotation. The primary winding and the basic secondary winding 52 are designed as concentric rings, and the cascaded primary winding 62 and the cascaded secondary winding 72 are also designed as concentric rings. This ensures that the magnetic flux of their linkage is maximized. At the same time, the winding coils are precisely matched in terms of parameters such as the number of turns and wire diameter, and optimized according to factors such as the amount of electrical energy required by the rotating components of the aircraft and the transmission distance.

[0050] According to embodiments of this application, an adhesive layer is provided between the basic primary winding 42 and the basic primary magnetic core 41; a positioning frame is provided between the basic secondary winding 52 and the basic secondary magnetic core 51; an adhesive layer is provided between the cascaded primary winding 62 and the cascaded primary magnetic core 61; and a positioning frame is provided between the cascaded secondary winding 72 and the cascaded secondary magnetic core 71. By precisely positioning and fixing the windings and magnetic cores in this way, the magnetic core can be fully utilized to transmit magnetic flux to the maximum extent.

[0051] The non-contact power transmission device for rotating components of an aircraft according to the embodiments of this application has the following technical effects:

[0052] First, it abandons the traditional contact-based power transmission method, avoiding frictional losses caused by mechanical contact. This not only significantly extends the service life of the device and reduces maintenance costs, but also eliminates potential safety hazards caused by frictional heat. For example, traditional contact-based transmission devices may require replacement of worn brushes and slip rings every few hundred flight hours, while this non-contact device can extend the maintenance cycle several times, greatly improving the reliability and continuity of aircraft operation.

[0053] Second, the adoption of a cascadeable, rotary, and separable structure greatly enhances the device's adaptability to different power requirements. In aircraft, different rotating components, such as small servo motors and large propeller motors, have significantly different power demands. Through flexible cascading, the power output can be easily adjusted. In contrast, traditional single-transformer structures struggle to meet diverse power requirements without altering the overall size and weight of the equipment.

[0054] Third, the application of Litz wire and amorphous alloy cores significantly improves power transmission efficiency. Litz wire effectively reduces the skin effect and proximity effect under high-frequency current, thus reducing conductor resistance loss; amorphous alloy cores, with their excellent soft magnetic properties, reduce hysteresis loss and eddy current loss. The synergistic effect of these two technologies significantly reduces energy loss during the entire power transmission process.

[0055] Fourth, the non-contact design and optimized structural layout of this device allow for greater flexibility in the structural design and spatial arrangement of the aircraft's rotating components. By eliminating the physical connections required for contact-based power transmission, aircraft design can more freely pursue compact and lightweight designs for rotating components, contributing to improved flight performance and maneuverability. Furthermore, by reducing the risk of failure due to physical contact, this device can maintain stable and reliable power transmission even in harsh flight environments such as high humidity, high dust, and high vibration, further enhancing the aircraft's operational safety and stability under complex conditions.

[0056] The preferred embodiments of this disclosure have been described in detail above with reference to the accompanying drawings. However, this disclosure is not limited to the specific details of the above embodiments. Within the scope of the technical concept of this disclosure, various simple modifications can be made to the technical solutions of this disclosure, and these simple modifications all fall within the protection scope of this disclosure.

[0057] It should also be noted that the various specific technical features described in the above embodiments can be combined in any suitable manner without contradiction. To avoid unnecessary repetition, this disclosure will not describe the various possible combinations separately.

[0058] Furthermore, various different embodiments of this disclosure can be combined in any way, as long as they do not violate the spirit of this disclosure, they should also be regarded as the content disclosed in this disclosure.

Claims

1. A non-contact electrical power transmission device for rotating components of an aircraft, characterized in that, include: A fixed bracket (1) is used to fix the fixed connection to the stationary part of the aircraft, the fixed bracket (1) including a mounting cylinder (2); Rotary shaft (3) is used to fix and connect the rotating components of the aircraft; The basic cylindrical magnet assembly (4) is fixedly connected to the inner wall of the mounting cylinder (2); The basic cylindrical moving magnet assembly (5) is fixedly connected to the rotating shaft (3). The basic cylindrical moving magnet assembly (5) is located inside the basic cylindrical fixed magnet assembly (4) and is coaxial with the basic cylindrical fixed magnet assembly (4). There is a gap between the basic cylindrical moving magnet assembly (5) and the basic cylindrical fixed magnet assembly (4).

2. The non-contact electrical power transmission device for rotating components of an aircraft according to claim 1, characterized in that, The basic cylindrical magnet assembly (4) includes: a basic primary magnetic core (41) and a basic primary winding (42). The basic primary magnetic core (41) is cylindrical and fixedly connected to the inner wall of the mounting cylinder (2). One end of the basic primary magnetic core (41) is provided with an inner flange (411) extending toward the center of the basic primary magnetic core (41), and the other end is detachably connected with a first retaining ring (43). The basic primary winding (42) is disposed in the annular groove formed by the inner flange (411) and the first retaining ring (43). The basic cylindrical moving magnet assembly (5) includes: a basic secondary magnetic core (51) and a basic secondary winding (52). The basic secondary magnetic core (51) is cylindrical and fixedly connected to the rotating shaft (3). One end of the basic secondary magnetic core (51) is provided with an outer flange (511) extending away from the center of the basic secondary magnetic core (51), and the other end is detachably connected with a second retaining ring (53). The basic secondary winding (52) is disposed in the annular groove formed by the outer flange (511) and the second retaining ring (53).

3. The non-contact electrical power transmission device for rotating components of an aircraft according to claim 2, characterized in that, The non-contact power transmission device for the rotating components of an aircraft further includes at least one cascaded cylindrical fixed magnet assembly (6) axially connected between the basic primary magnetic core (41) and the first retaining ring (43), and at least one cascaded cylindrical moving magnet assembly (7) axially connected between the basic secondary magnetic core (51) and the second retaining ring (53), and the number of the cascaded cylindrical fixed magnet assembly (6) and the cascaded cylindrical moving magnet assembly (7) is equal; The cascaded cylindrical magnet assembly (6) includes a cascaded primary magnetic core (61) and a cascaded primary winding (62). The cascaded primary magnetic core (61) is cylindrical, and both ends of the cascaded primary magnetic core (61) are provided with first pin holes (611). The cascaded primary winding (62) is sleeved on the outside of the cascaded primary magnetic core (61). The cascaded cylindrical moving magnet assembly (7) includes: a cascaded secondary magnetic core (71) and a cascaded secondary winding (72). The cascaded secondary magnetic core (71) is cylindrical, and a second pin hole (711) is provided at both ends of the cascaded secondary magnetic core (71). The cascaded secondary winding (72) is sleeved on the outside of the cascaded secondary magnetic core (71). A third pin hole (412) is provided at the end of the basic primary magnetic core (41) near the cascaded primary magnetic core (61). A fourth pin hole (512) is provided on the end face of the base secondary core (51) near the cascaded secondary core (71). The basic primary magnetic core (41) and the cascaded primary magnetic core (61) are connected by pins (8); the basic secondary magnetic core (51) and the cascaded secondary magnetic core (71) are connected by pins (8); The cascaded primary magnetic core (61) near the first retaining ring (43) is connected to the first retaining ring (43) by screws (9); The cascaded secondary magnetic core (71) near the second retaining ring (53) is connected to the second retaining ring (53) by screws (9).

4. The non-contact electrical power transmission device for rotating components of an aircraft according to claim 3, characterized in that, The output terminal of the basic secondary winding (52) is connected in parallel with the output terminal of each of the cascaded secondary windings (72).

5. The non-contact electrical power transmission device for rotating components of an aircraft according to claim 4, characterized in that, The basic primary winding (42), the basic secondary winding (52), the cascaded primary winding (62) and the cascaded secondary winding (72) are all wound with Litz wire, which is formed by twisting together multiple thin wires.

6. The non-contact electrical power transmission device for rotating components of an aircraft according to claim 5, characterized in that, The basic primary magnetic core (41), the basic secondary magnetic core (51), the cascaded primary magnetic core (61), and the cascaded secondary magnetic core (71) are all made of amorphous alloy material through processing and pressing.

7. The non-contact electrical power transmission device for rotating components of an aircraft according to claim 6, characterized in that, When the non-contact power transmission device for the rotating components of an aircraft only includes a basic cylindrical fixed magnet assembly (4) and a basic cylindrical moving magnet assembly (5), the basic primary magnetic core (41) and the first retaining ring (43) form a cylindrical shape; the basic secondary magnetic core (51) and the second retaining ring (53) form an H-shaped structure. When the non-contact power transmission device for the rotating components of an aircraft includes a basic cylindrical fixed magnet assembly (4) and a cascaded cylindrical fixed magnet assembly (6), as well as a basic cylindrical moving magnet assembly (5) and a cascaded cylindrical moving magnet assembly (7), the basic primary magnetic core (41), the cascaded primary magnetic core (61) and the first retaining ring (43) form a cylindrical shape; the basic secondary magnetic core (51), the cascaded secondary magnetic core and the second retaining ring (53) form an H-shaped structure.

8. The non-contact electrical power transmission device for a rotating component of an aircraft according to any one of claims 3 to 7, characterized in that, An adhesive layer is provided between the basic primary winding (42) and the basic primary magnetic core (41); a positioning frame is provided between the basic secondary winding (52) and the basic secondary magnetic core (51); an adhesive layer is provided between the cascaded primary winding (62) and the cascaded primary magnetic core (61); and a positioning frame is provided between the cascaded secondary winding (72) and the cascaded secondary magnetic core (71).

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