Radial halbach configuration electromagnetic damping shimmy damper for aircraft nose landing gear

Abstract

This invention provides a radial Halbach configuration electromagnetic damper for aircraft nose landing gear, comprising a housing, a base, a rotating shaft, a first fixed disk, a second fixed disk, multiple permanent magnets, and bearings. The housing and base are fixedly connected to form a mounting cavity. The rotating shaft is rotatably mounted in the mounting cavity via the bearings. The first and second fixed disks are spaced apart along the axial direction of the rotating shaft and fixedly connected to it. The multiple permanent magnets are arranged circumferentially between the first and second fixed disks in a radial Halbach array. A working air gap is formed between the permanent magnets and the inner wall of the housing. Compared with the prior art, this invention can improve the magnetic field utilization rate on the working air gap side within the limited installation space of the nose landing gear, increase the damping torque and equivalent damping output, and is suitable for reducing yaw in aircraft nose landing gear.

Description

Technical Field

[0001] This invention relates to the field of aircraft landing gear damping technology, specifically a radial Halbach configuration electromagnetic damping damper for aircraft nose landing gear. Background Technology

[0002] The nose landing gear of an aircraft is prone to shimmy during taxiing, takeoff, and landing. Nose landing gear shimmy reduces the aircraft's directional stability during taxiing and may seriously affect flight safety. Therefore, shimmy dampers are usually installed to suppress shimmy.

[0003] Existing nose landing gear dampers mostly employ hydraulic damping. While hydraulic dampers are a mature technology, they typically suffer from complex structures, high maintenance requirements for the hydraulic system, stringent sealing reliability requirements, and significant weight. With the advancement of aircraft electromechanicalization and full electrification, adopting non-hydraulic methods for nose landing gear damping is of great importance.

[0004] Electromagnetic damping technology utilizes the relative motion between a conductor and a magnetic field to generate eddy currents, which in turn create a damping torque that opposes the relative motion. It offers advantages such as non-contact operation, fast response, low wear, and easy maintenance. However, in nose landing gear applications, the installation space and weight of the damper are strictly limited. Conventional permanent magnet arrangements result in limited utilization of the magnetic field on the working air gap side, easily leading to insufficient damping output per unit volume. Simultaneously, improving damping capacity usually accompanies increased eddy current losses in the outer shell, leading to higher thermal loads. Therefore, further improvements to the structural layout and heat dissipation conditions are needed to meet engineering application requirements.

[0005] Therefore, it is necessary to propose an electromagnetic damping sway reducer that is suitable for the limited installation space of the nose landing gear and takes into account both high damping output and engineering feasibility. Summary of the Invention

[0006] To address the issues of complex hydraulic systems and inconvenient maintenance associated with nose landing gear dampers, as well as the insufficient damping density of conventional electromagnetic damping structures within limited installation space, this invention provides a radial Halbach configuration electromagnetic damping damper for aircraft nose landing gear. This damper enhances the magnetic field strength near the working air gap side and reduces magnetic leakage on the back side, thereby improving magnetic field utilization. It is suitable for aircraft nose landing gear damping scenarios where high requirements are placed on volume, mass, and damping performance.

[0007] This invention provides a radial Halbach configuration electromagnetic damping damper for aircraft nose landing gear, comprising a mounting cavity, a rotating shaft, a first fixed disk, a second fixed disk, multiple permanent magnets, and bearings. The rotating shaft is mounted in the mounting cavity via bearings and rotates around its own axis via bearings. The first and second fixed disks are spaced apart along the axial direction of the rotating shaft and are fixedly connected to the rotating shaft. The multiple permanent magnets are arranged circumferentially between the first and second fixed disks, and the multiple permanent magnets are arranged in a radial Halbach array. A working air gap is formed between the permanent magnets and the inner wall of the mounting cavity. The mounting cavity is a conductive component. When the permanent magnets rotate relative to the inner wall of the mounting cavity, eddy currents are generated, forming an electromagnetic damping torque that hinders relative motion.

[0008] In a further improvement, the permanent magnets are uniformly distributed along the circumference and form a Halbach array by combining radial polarization and tangential polarization. The permanent magnets enhance the magnetic field on the side close to the inner wall of the mounting cavity and reduce the leakage magnetic field on the side away from the inner wall of the mounting cavity.

[0009] In a further improvement, a total of 12 permanent magnets are provided, divided into three groups of four permanent magnets each, arranged sequentially along the circumference.

[0010] In a further improvement, the permanent magnet is a sector-shaped permanent magnet.

[0011] In a further improvement, the mounting cavity is formed by a fixed connection between the outer shell and the base, and the base is provided with a mounting structure fixedly connected to the aircraft's nose landing gear anti-sway mechanism; the outer circumference of the outer shell is integrally formed with a heat dissipation structure, which is used to increase the heat dissipation area of ​​the outer shell and improve the heat dissipation conditions of the outer shell.

[0012] In a further improvement, the heat dissipation structure consists of multiple annular heat dissipation fins spaced apart along the axial direction of the outer casing.

[0013] In a further improvement, the heat dissipation structure is located on the outside of the outer casing corresponding to the eddy current heating area.

[0014] In a further improvement, the rotating shaft is provided with a connection structure that connects to the reducer in the anti-sway mechanism.

[0015] In a further improvement, the bearing includes a first bearing and a second bearing spaced apart along the axial direction of the shaft.

[0016] As a further improvement, the wall thickness of the outer casing is set to match the operating speed range and the skin effect.

[0017] The beneficial effects of this invention are as follows: 1. The present invention adopts a radial Halbach array arrangement, which can enhance the magnetic field strength near the working air gap side and reduce the back side leakage magnetic field, thereby improving the magnetic field utilization rate. It is suitable for aircraft nose landing gear sway reduction scenarios with high requirements for volume, mass and damping performance.

[0018] 2. The rotor structure consists of a first fixed disk, a second fixed disk, and multiple permanent magnets, with the permanent magnets arranged radially opposite to the conductive outer shell. This increases the effective electromagnetic area and improves the dynamic response capability of the sway reducer.

[0019] 3. The outer circumference of the shell is integrally formed with a heat dissipation structure. By increasing the heat exchange area, the heat dissipation conditions during operation are improved, which helps to reduce the heat accumulation in the heat-generating area of ​​the shell and improves the engineering applicability of the device.

[0020] 4. Within the limited installation space of the front landing gear, the present invention can output a larger damping torque and a higher equivalent damping coefficient, which is beneficial to improving the damping capacity per unit volume. Attached Figure Description

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

[0022] Figure 1 This is a schematic diagram of the overall structure of the electromagnetic damping oscillation reducer of the present invention; Figure 2 This is a schematic diagram of the internal structure of the anti-sway device of the present invention after the outer shell is removed; Figure 3 This is a schematic diagram of the exploded structure of the oscillation damper of the present invention; Figure 4 This is a schematic diagram of the integrated heat dissipation shell structure of the present invention; Figure 5 This is a schematic diagram of the radial Halbach array arrangement of the permanent magnets in this invention; Figure 6 This is a comparison diagram of the damping torque of the radial electromagnetic damper of this invention and the conventional axial electromagnetic damper.

[0023] Figure 7 The graph shows a comparison of the damping torque curves of the radial electromagnetic damper of this invention and the conventional axial electromagnetic damper at 100 rad / s.

[0024] Wherein: 1-outer shell; 2-base; 3-rotating shaft; 4-first fixed plate; 5-second fixed plate; 6-permanent magnet; 7-first bearing; 8-second bearing; 9-mounting structure; 10-connection structure; 11-heat dissipation structure. Detailed Implementation

[0025] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0026] like Figures 1 to 3 As shown, the present invention provides a radial Halbach configuration electromagnetic damping damper for aircraft nose landing gear, including a housing 1, a base 2, a rotating shaft 3, a first fixed plate 4, a second fixed plate 5, multiple permanent magnets 6, a first bearing 7, a second bearing 8, a mounting structure 9, a connecting structure 10, and a heat dissipation structure 11.

[0027] The outer shell 1 and the base 2 are fixedly connected to form a mounting cavity. The base 2 is fixedly connected to the outer cylinder of the aircraft's nose landing gear via a mounting structure 9. The rotating shaft 3 is mounted in the mounting cavity via a first bearing 7 and a second bearing 8 and can rotate relative to the base 2 and the outer shell 1. One end of the rotating shaft 3 is provided with a connecting structure 10 for connecting to the transmission component in the nose landing gear steering sleeve or steering mechanism, thereby transmitting the nose landing gear shimmy motion to the damper rotating shaft 3.

[0028] The first fixed disk 4 and the second fixed disk 5 are fixedly connected to the rotating shaft 3 and are spaced apart along the axial direction of the rotating shaft 3. A plurality of permanent magnets 6 are disposed between the first fixed disk 4 and the second fixed disk 5, and the plurality of permanent magnets 6 are evenly distributed along the circumferential direction to form a rotor assembly that rotates synchronously with the rotating shaft 3.

[0029] like Figure 5 As shown, multiple permanent magnets 6 are arranged in a radial Halbach array. Preferably, a total of 12 permanent magnets 6 are arranged in three groups of four, with adjacent permanent magnets arranged in a combination of radial and tangential polarization. This arrangement enhances the magnetic field on the side closer to the outer shell 1 and reduces leakage magnetic field on the side closer to the rotating shaft 3, thereby improving the utilization rate of the magnetic field on the working air gap side. Preferably, the permanent magnets 6 adopt a fan-shaped structure to increase their effective working area relative to the inner wall of the outer shell 1.

[0030] The outer shell 1 is made of a conductive material, preferably copper, aluminum, or other conductive metal suitable for forming eddy current damping. A working air gap is formed between the permanent magnet 6 and the inner wall of the outer shell 1. When the rotating shaft 3 drives the permanent magnet 6 to rotate relative to the outer shell 1, the changing magnetic field generated by the permanent magnet 6 cuts through the conductive areas in the outer shell 1, thereby inducing eddy currents within the outer shell 1. According to Lenz's law, these eddy currents will generate an electromagnetic damping torque that opposes relative motion, used to suppress the shimmy of the aircraft's nose landing gear.

[0031] like Figure 1 and Figure 4 As shown, a heat dissipation structure 11 is integrally formed on the outer circumference of the outer shell 1. Preferably, the heat dissipation structure 11 consists of a plurality of annular heat dissipation fins spaced apart along the axial direction of the outer shell 1. This heat dissipation structure 11 is an integral structure with the outer shell 1, which not only helps to increase the heat exchange area between the outer shell 1 and the outside air, but also avoids the structural complexity caused by additional assembled heat dissipation components.

[0032] During operation, eddy current losses in the outer casing 1 will generate a certain amount of heat. To improve the heat dissipation conditions of the heat-generating area, this embodiment provides a heat dissipation structure 11 integrally formed around the outer circumference of the outer casing 1, thereby improving the heat exchange capacity between the outer casing 1 and the external environment and thus enhancing the applicability of the oscillation damper in engineering applications.

[0033] Since the radial Halbach array enhances the magnetic field strength near the inner wall of the outer shell 1, the present invention can output a larger damping torque and improve the damping density of the yaw damper under the same installation space and mass constraints. Preferably, the external dimensions of the yaw damper meet the installation space requirements of the nose landing gear, and the overall yaw damper can be controlled within a small diameter and height range to adapt to the limited space arrangement of the nose landing gear.

[0034] like Figure 6 and Figure 7 As shown, compared with conventional axial electromagnetic dampers, the radial Halbach configuration of the present invention can achieve a larger damping torque and a higher equivalent damping coefficient under the same operating conditions, making it more suitable for sway reduction applications under limited installation space conditions of the nose landing gear.

[0035] The various embodiments in this specification are described in a progressive manner. Similar or identical parts between embodiments can be referred to interchangeably. Each embodiment focuses on its differences from other embodiments. In particular, for the device embodiments, the above descriptions are merely preferred embodiments of the present invention. Since they are fundamentally similar to the method embodiments, the descriptions are relatively simple, and relevant parts can be referred to the descriptions of the method embodiments. The above descriptions are merely specific embodiments of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention, without departing from the principle of the present invention, should be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A radial Halbach configuration electromagnetic damping damper for aircraft nose landing gear, characterized in that: It includes a mounting cavity, a rotating shaft (3), a first fixed plate (4), a second fixed plate (5), multiple permanent magnets (6), and bearings; The rotating shaft (3) is installed in the mounting cavity by bearings and rotates around its own axis by bearings; The first fixed disk (4) and the second fixed disk (5) are spaced apart along the axial direction of the rotating shaft (3) and are fixedly connected to the rotating shaft (3). A plurality of permanent magnets (6) are arranged between the first fixed disk (4) and the second fixed disk (5) along the circumferential direction, and the plurality of permanent magnets (6) are arranged in a radial Halbach array manner. A working air gap is formed between the permanent magnet (6) and the inner wall of the mounting cavity. The mounting cavity is a conductive component. When the permanent magnet (6) rotates relative to the inner wall of the mounting cavity, eddy currents are generated and an electromagnetic damping torque is formed to hinder the relative motion.

2. The radial Halbach configuration electromagnetic damping damper for aircraft nose landing gear according to claim 1, characterized in that: The permanent magnet (6) is uniformly distributed along the circumference and forms a Halbach array by combining radial polarization and tangential polarization. The permanent magnet (6) enhances the magnetic field on the side close to the inner wall of the mounting cavity and weakens the leakage magnetic field on the side away from the inner wall of the mounting cavity.

3. The radial Halbach configuration electromagnetic damping damper for aircraft nose landing gear according to claim 1 or 2, characterized in that: There are 12 permanent magnets (6) in total, which are divided into three groups of four permanent magnets in each group, arranged in sequence along the circumference.

4. The radial Halbach configuration electromagnetic damping damper for aircraft nose landing gear according to claim 1 or 2, characterized in that: The permanent magnet (6) is a sector-shaped permanent magnet.

5. The radial Halbach configuration electromagnetic damping damper for aircraft nose landing gear according to claim 1, characterized in that: The mounting cavity is formed by a fixed connection between the outer shell (1) and the base (2). The base (2) is provided with a mounting structure (9) fixedly connected to the aircraft nose landing gear anti-sway mechanism. The outer circumference of the outer shell (1) is integrally formed with a heat dissipation structure (11). The heat dissipation structure (11) is used to increase the heat dissipation area of ​​the outer shell (1) and improve the heat dissipation conditions of the outer shell (1).

6. The radial Halbach configuration electromagnetic damping damper for aircraft nose landing gear according to claim 5, characterized in that: The heat dissipation structure (11) consists of multiple annular heat dissipation fins spaced apart along the axial direction of the outer shell (1).

7. The radial Halbach configuration electromagnetic damping damper for aircraft nose landing gear according to claim 5, characterized in that: The heat dissipation structure (11) is located on the outside of the outer shell (1) corresponding to the eddy current heating area.

8. The radial Halbach configuration electromagnetic damping damper for aircraft nose landing gear according to claim 1 or 5, characterized in that: The rotating shaft (3) is provided with a connecting structure (10) that connects to the reducer in the swing reduction mechanism.

9. The radial Halbach configuration electromagnetic damping damper for aircraft nose landing gear according to claim 8, characterized in that: The bearing includes a first bearing (7) and a second bearing (8) spaced apart along the axial direction of the shaft (3).

10. The radial Halbach configuration electromagnetic damping damper for aircraft nose landing gear according to claim 5, characterized in that: The wall thickness of the outer shell (1) is set according to the operating speed range and skin effect.

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