High-temperature-resistant rotating magnetic field assembly for aerospace and assembling test method thereof

Abstract

The application discloses a high-temperature-resistant rotating magnetic field assembly for aerospace and an assembling test method thereof, and relates to the technical field of rotating magnetic field equipment, which comprises a coil support, the coil support is installed on a magnetic conductor stator, a wire package conductor is wound on the coil support, and a wire high-temperature-resistant sleeve is arranged on the outer side of the wire package conductor. The wire high-temperature-resistant sleeve arranged on the outer side of the wire package conductor can effectively enhance the high-temperature resistance of the wire package conductor, so that the wire package conductor can work in a high-temperature environment below 500 DEG C.

Description

Technical Field

[0001] This invention relates to the field of rotating magnetic field equipment technology, and in particular to a high-temperature resistant rotating magnetic field component for aerospace applications and its assembly and testing method. Background Technology

[0002] In the preparation of high-temperature materials, rotating magnetic fields are widely used to assist in the regulation of material properties. Rotating magnetic fields are beneficial for improving the microstructure of high-temperature liquid alloys after solidification. During crystal growth, rotating magnetic fields can reduce some impurities and defects in the crystal, thus purifying the crystal and improving its quality. Under microgravity conditions, rotating magnetic fields have a stirring effect on the melt during the floating zone crystal growth process, reducing defects during solidification, enhancing solute transport, and regulating the solid-liquid interface, all of which contribute to improving crystal quality.

[0003] Currently, there are many methods to generate rotating magnetic fields. For example, at low frequencies, a rotating magnetic field can be generated by driving a permanent magnet to rotate through a transmission structure. This rotating field is two-dimensional, and its magnitude can be adjusted by changing the distance between the permanent magnets. The advantage of this type of rotating magnetic field is that it does not generate heat. The disadvantage is that it is difficult to dynamically adjust the magnetic field magnitude, and it cannot achieve higher frequency rotating magnetic fields. Therefore, the rotating magnetic field commonly used in laboratories is generated by an energized coil. This method has a simple structure, the magnetic field magnitude is easy to adjust, and it can also achieve high-frequency rotating magnetic fields, as well as multi-dimensional rotating magnetic fields.

[0004] Rotating magnetic fields used for the preparation of high-temperature materials in a microgravity environment can operate at temperatures up to 500°C. Conventional insulating coatings on the coil surface cannot meet the requirement of a maximum operating temperature of 500°C.

[0005] Therefore, there is an urgent need in this field for a novel high-temperature resistant rotating magnetic field assembly for aerospace applications and its assembly and testing method to solve the above problems. Summary of the Invention

[0006] The purpose of this invention is to provide a high-temperature resistant rotating magnetic field component for aerospace applications and its assembly and testing method, so as to solve the problems existing in the prior art and enhance the high-temperature resistance of the equipment.

[0007] To achieve the above objectives, the present invention provides the following solution: This invention discloses a high-temperature resistant rotating magnetic field assembly for aerospace applications, including a coil support mounted on a magnetically conductive stator. A coil wire is wound around the coil support, and a high-temperature resistant sheath is provided on the outside of the coil wire.

[0008] Preferably, the material of the coil conductor is pure copper or pure silver; The high-temperature resistant sleeve for the conductor is made of alumina or quartz. The coil support is made of aluminum alloy; The magnetically conductive stator is made of silicon steel sheet, and the surface of the magnetically conductive stator is provided with a stator insulating coating. The magnetically conductive stator has a circular ring structure, and a plurality of magnetic pole portions are provided on the inner side of the magnetically conductive stator. The magnetically conductive stator is provided in multiple layers, which are stacked sequentially and fixed by stator fasteners.

[0009] Preferably, the coil support includes two end panels, at least one isolation panel, and a central connecting tube. The central connecting tube passes through the center of the end panels and the isolation panel. The two end panels are located at both ends of the central connecting tube, and the isolation panel is located between the two end panels. The coil conductor is wound around the central connecting tube.

[0010] Preferably, the outer surface of the central connecting tube is wrapped with a wear-resistant layer.

[0011] Preferably, the outer side of the coil conductor is wrapped with a coil fixing layer, and the outer side of the coil fixing layer is fixed by a fixing layer binding member.

[0012] Preferably, the sidewall of the central connecting pipe is provided with multiple vortex isolation grooves.

[0013] Preferably, both the end panel and the isolation panel are provided with lead wire guide grooves, and the lead wire portion of the coil conductor passes through the lead wire guide grooves; The outer side of the lead portion of the wire coil is provided with two layers of high-temperature resistant sheathing.

[0014] Preferably, the coil bracket is mounted on a bracket mounting base, and the bracket mounting base is provided with a mounting base through hole.

[0015] Preferably, the bracket mounting base has a mounting cavity, the coil bracket is located in the mounting cavity, the mounting cavity is provided with a positioning beam, the end panel and the isolation panel are both provided with positioning grooves, and the positioning beam is installed on the positioning grooves.

[0016] This invention discloses an assembly and testing method for a high-temperature resistant rotating magnetic field assembly for aerospace applications, comprising the following steps: S1. A high-temperature resistant sleeve is installed on the outside of the conductor in the online package; S2. Clean the coil support and wrap a wear-resistant layer on the coil support; S3. Wrap the wire coil around the coil support; S4. Wrap a coil fixing layer around the outside of the wound wire coil and secure the coil fixing layer with the fixing layer binding piece; S5. Clean the magnetically conductive stator, then stack several layers of magnetically conductive stator and fix them with stator fasteners; S6. Install the coil bracket onto the magnetic stator; S7. Install the coil bracket on the bracket mounting base, and then fix the magnetic stator and the bracket mounting base on the heating furnace mounting surface; S8. Provide the same current to the coil conductors on phase A or phase B magnetic poles, measure the magnetic field strength at the center of the magnetic gap and the distribution of the magnetic field strength along the central axis, thereby determining the spatial distribution of the rotating magnetic field; then change the current in the coil conductors, measure the magnetic field strength at the center of the magnetic gap, thereby obtaining the correspondence between the magnetic field strength at the center of the magnetic gap and the current in the coil conductors.

[0017] The present invention achieves the following technical effects compared to the prior art: The present invention provides a high-temperature resistant sheath for the outer side of the coiled conductor. The high-temperature resistant sheath can effectively prevent short circuits between the coiled conductors under aerospace mechanical conditions and can maintain insulation at high temperatures. Attached Figure Description

[0018] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the 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.

[0019] Figure 1 This is a schematic diagram of the structure of a high-temperature resistant rotating magnetic field assembly for aerospace applications, as shown in Example 1. Figure 2 This is a schematic diagram of the coil support structure in the high-temperature resistant rotating magnetic field assembly for aerospace applications, as shown in Example 1. Figure 3 This is a schematic diagram of the support mounting base in the high-temperature resistant rotating magnetic field assembly for aerospace applications, as shown in Example 1. In the diagram: 1-Coil bracket; 101-End panel; 102-Isolation panel; 103-Center connecting pipe; 104-Positioning groove; 105-Lead guide groove; 106-Eddy current isolation groove; 2-Magnetic stator; 201-Magnetic pole part; 202-Stator fastener; 3-Bracket mounting base; 301-Mounting base through hole; 302-Mounting cavity; 303-Positioning beam. Detailed Implementation

[0020] 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.

[0021] The purpose of this invention is to provide a high-temperature resistant rotating magnetic field component for aerospace applications and its assembly and testing method, so as to solve the problems existing in the prior art and enhance the high-temperature resistance of the equipment.

[0022] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0023] Example 1 like Figures 1-3 As shown, this embodiment provides a high-temperature resistant rotating magnetic field assembly for aerospace applications, capable of operating in environments up to 500°C. It includes a coil support 1, which is mounted on a magnetically conductive stator 2. A coiled wire is wound around the coil support 1, and a high-temperature resistant sheath is provided on the outside of the coiled wire. The aperture of the high-temperature resistant sheath matches the diameter of the coiled wire, and the thickness of the high-temperature resistant sheath is typically 0.05mm-0.2mm.

[0024] In practical use, the coil conductor is connected to the driving power supply (including but not limited to AC power). When the coil conductor is energized, a rotating magnetic field is generated. The high-temperature resistant sheath of the conductor can effectively prevent short circuits caused by the coil conductor being exposed and conducting to each other under aerospace mechanical environment, and can maintain insulation at high temperatures.

[0025] In this embodiment, the coil conductor is made of pure copper or pure silver. Specifically, the coil conductor can be bare copper or silver wire without surface insulation treatment to prevent the release of harmful gases at high temperatures. Silver wire is preferred because its low resistance helps reduce the temperature rise of the equipment during operation. The diameter, length, and number of turns of the coil conductor need to be determined based on parameters such as the driving power supply parameters of the rotating magnetic field, the frequency of the rotating magnetic field, the size of the coil, and the temperature coefficient of the coil conductor resistance within the operating temperature range.

[0026] The materials used for high-temperature resistant tubing for conductors have the characteristics of high temperature resistance and insulation. The materials used for high-temperature resistant tubing for conductors include, but are not limited to, existing alumina or quartz.

[0027] The coil support 1 is made of aluminum alloy, which can withstand temperatures up to 500°C and is a lightweight alloy, which helps to reduce weight.

[0028] The magnetically conductive stator 2 is made of silicon steel sheet; specifically, it uses existing high-frequency magnetically conductive silicon steel sheet. The surface of the magnetically conductive stator 2 is coated with a stator insulating coating, which also possesses high-temperature resistance and insulation properties. The material of the stator insulating coating includes, but is not limited to, magnesium oxide (MgO). Figure 1 It is not difficult to see that the magnetic stator 2 has a circular ring structure, and the inner side of the magnetic stator 2 is provided with several magnetic pole parts 201, specifically four magnetic pole parts 201. The included angle between two adjacent magnetic pole parts 201 is 90°. In actual use, the four magnetic pole parts 201 are divided into two A-phase magnetic poles and two B-phase magnetic poles. The two A-phase magnetic poles are arranged opposite each other, and the two B-phase magnetic poles are arranged opposite each other.

[0029] The optimal thickness of the single magnetic stator 2 is 0.1mm-0.5mm, and the higher the operating frequency, the smaller the thickness, which is beneficial to reducing the ferromagnetic eddy current loss in the magnetic stator 2.

[0030] Multiple magnetically conductive stators 2 are provided, with multiple layers of magnetically conductive stators 2 stacked sequentially and fixed by stator fasteners 202. Figure 1 As can be seen from the diagram, the magnetic stator 2 has connecting holes evenly distributed along its circumference. These connecting holes are divided into two parts: a first connecting hole and a second connecting hole, which are staggered. The corresponding first connecting holes in each magnetic stator 2 are fixed together by stator fasteners 202, which include, but are not limited to, bolts. The second connecting holes in each integrally fixed magnetic stator 2 can be bolted to the heating furnace mounting surface, thus preventing vibration during operation from damaging the magnetic stator 2 or reducing its performance.

[0031] In this embodiment, as Figure 2 As shown, the coil support 1 includes two end panels 101, at least one isolation panel 102, and a central connecting tube 103. The central connecting tube 103 passes through the center of the end panels 101 and the isolation panel 102. The two end panels 101 are located at both ends of the central connecting tube 103, and the isolation panel 102 is located between the two end panels 101. The coil wire is wound around the central connecting tube 103 between the isolation panel 102 and the end panels 101. Figure 2 An isolation panel 102 is provided, located in the middle of the central connecting tube 103, so two coil wires (i.e., coils) can be wound on each coil support 1. If a large magnetic field is required for operation, both coil wires on the coil support 1 can be powered simultaneously. If a smaller magnetic field is required, only one coil wire needs to be powered. Furthermore, if the coil wire fails, the other coil wire can be switched on in time, thereby improving the reliability of the rotating magnetic field for aerospace applications.

[0032] If it is necessary to wind more coil wires (i.e., coils) on a coil bracket 1, more isolation panels 102 can be set up. The central connecting tube 103 between two adjacent isolation panels 102 can also be used to wind coil wires.

[0033] The magnetic pole portion 201 of the magnetically conductive stator 2 passes through the central through hole of the central connecting tube 103, thereby connecting the magnetically conductive stator 2 with the coil support 1.

[0034] In this embodiment, the outer surface of the central connecting tube 103 is wrapped with a wear-resistant layer. The wear-resistant layer has the characteristics of high temperature resistance and insulation. Its material includes, but is not limited to, alumina or quartz, to prevent the high temperature resistant sleeve of the coil conductor from being worn through under aerospace mechanical environment (including vibration environment) and causing the coil to short circuit.

[0035] In this embodiment, the outer side of the coil conductor is wrapped with a coil fixing layer, which also has the characteristics of high temperature resistance and insulation. Its material includes, but is not limited to, alumina or quartz. After the coil conductor is wrapped with the coil fixing layer, the outer side of the coil fixing layer is bound and fixed by a fixing layer binding member. The fixing layer binding member can be a high temperature resistant sheath for the conductor. Of course, those skilled in the art can also replace it with binding wires of other materials, and it is not limited to this one.

[0036] The coil fixing layer is used to fix the coiled wire to prevent the wound wire from loosening under aerospace mechanical environment (including vibration environment) and thus affecting its performance.

[0037] The coil conductor, wear-resistant layer, coil fixing layer, and fixing layer binding components together form a complete coil structure.

[0038] In this embodiment, the sidewall of the central connecting pipe 103 is provided with a plurality of eddy current isolation grooves 106. Specifically, from Figure 2 As can be seen, four eddy current blocking grooves 106 are evenly distributed around the sidewall of the central connecting pipe 103, while the end panel 101 and the isolation panel 102 are provided with grooves (i.e., stepped grooves in the figure) corresponding to the eddy current blocking grooves 106. The advantage of this arrangement is that it avoids the formation of eddy currents on the coil support 1 when the rotating magnetic field is working, thereby reducing eddy current losses under AC working conditions. Of course, in addition to this, those skilled in the art can adjust the specific shape and number of the eddy current blocking grooves 106 and the corresponding grooves on the end panel 101 and the isolation panel 102 according to actual needs, but it is necessary to ensure that the central holes of the end panel 101 and the isolation panel 102 corresponding to the central connecting pipe 103 are non-circular in shape.

[0039] In this embodiment, both the end panel 101 and the isolation panel 102 are provided with oblique elongated lead guide grooves 105. The lead portion of the coil wire passes through the lead guide grooves 105, which limit and function the lead portion of the coil wire.

[0040] The lead section of the coil conductor is the part of the coil conductor that extends out of the coil fixing layer. The end of the lead section is used to connect to the drive power supply. The outer side of the lead section of the coil conductor has two layers of high-temperature resistant sheathing, while the remaining part of the coil conductor (i.e., the part inside the coil fixing layer) only needs one layer of high-temperature resistant sheathing. The reason for this design is that during actual wire handling, the lead section outside the coil fixing layer needs to be fixed by a clamp, resulting in higher wear on the lead section of the coil conductor. Therefore, two layers of high-temperature resistant sheathing are necessary to prevent the coil conductor from being exposed due to wear.

[0041] In this embodiment, the coil bracket 1 is mounted on the bracket mounting base 3. The bracket mounting base 3 has a mounting base through hole 301, which is fixed to the heating furnace mounting surface by screws, thereby improving the aerospace mechanical requirements of the rotating magnetic field. The bracket mounting base 3 is made of titanium alloy, which is a high-strength and lightweight alloy, which is beneficial for weight reduction; at the same time, it has low thermal conductivity, reducing the heat conduction from the heating furnace to the rotating magnetic field assembly.

[0042] In this embodiment, from Figure 3 As can be seen, the bracket mounting base 3 has a rectangular mounting cavity 302. The size of the coil bracket 1 matches the size of the mounting cavity 302, and the coil bracket 1 is located inside the mounting cavity 302. Positioning beams 303 are provided on both sides of the upper end of the mounting cavity 302. L-shaped positioning grooves 104 are provided on both sides of the upper end of the end panel 101 and the isolation panel 102. The positioning beams 303 are installed on the positioning grooves 104, thereby realizing the positioning of the coil bracket 1 and the bracket mounting base 3.

[0043] Example 2 This embodiment provides an assembly and testing method for a high-temperature resistant rotating magnetic field assembly for aerospace applications, used to assemble the high-temperature resistant rotating magnetic field assembly for aerospace applications disclosed in Embodiment 1, including the following steps: S1. Confirm that the conductors of each coil are intact, without weld joints or contamination, and then install a high-temperature resistant sleeve on the outside of the conductors in the coil.

[0044] S2. Round off all corners of coil bracket 1 and ultrasonically clean it in alcohol for 15 minutes. After drying, wrap a wear-resistant layer on coil bracket 1 (central connecting tube 103) to prevent the high-temperature resistant sheath of the outer layer of the coil conductor from being worn through under aerospace mechanical conditions, which could cause a short circuit between the coil conductor and coil bracket 1.

[0045] S3. Wrap the coil wire around the coil bracket 1. The number of turns of the coil wire is determined according to the design requirements. Reserve a 0.5-meter lead wire section for subsequent electrical assembly and connection to the drive power supply.

[0046] S4. Each coil support 1 has two independent coil structures, and a total of four coil supports 1 are provided. After the winding of each coil conductor is completed, a coil fixing layer is wrapped around the outside of the wound coil conductor to protect it. The lead wire of the coil conductor is led out along the lead wire guide groove 105 on the end panel 101 or the isolation panel 102. The coil fixing layer is bound and fixed by a fixing layer binding device. The fixing layer binding device uses binding wire with a diameter of 0.2mm-0.5mm to wrap around the coil fixing layer three times to prevent the coil fixing layer from loosening and being worn under aerospace mechanical environment.

[0047] S5. Clean the magnetically conductive stator 2, taking care to prevent damage to the stator insulation coating. After drying, determine the number of magnetically conductive stator 2 sheets according to the center through hole of the coil bracket 1 and the thickness of the single-layer magnetically conductive stator 2. Then stack several layers of magnetically conductive stator 2 and fix them with stator fasteners 202 to prevent the magnetically conductive stator 2 from vibrating during AC operation.

[0048] S6. Install the coil bracket 1 on the magnetic pole part 201 of the magnetic stator 2. There are four magnetic pole parts 201 and four coil brackets 1. Each magnetic pole part 201 is fitted with a coil bracket 1 containing a coil structure.

[0049] S7. Install the coil bracket 1 on the bracket mounting base 3, and then fix the magnetic stator 2 and the bracket mounting base 3 to the heating furnace mounting surface with corresponding bolts to prevent loosening under aerospace mechanical environment.

[0050] S8. Provide the same current to the coil conductors on the A-phase magnetic poles or the B-phase magnetic poles, measure the magnetic field strength at the center of the magnetic gap (i.e., the intersection of the line connecting the two A-phase magnetic poles and the line connecting the two B-phase magnetic poles) and the magnetic field strength distribution along the central axis (i.e., the straight line perpendicular to the center of the plane containing the two A-phase magnetic poles and the two B-phase magnetic poles), thereby determining the spatial distribution of the rotating magnetic field; then change the current in the coil conductors and measure the magnetic field strength at the center of the magnetic gap, thereby obtaining the correspondence between the magnetic field strength at the center of the magnetic gap and the current in the coil conductors.

[0051] In the description of this invention, it should be understood that the terms "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this invention, 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, and therefore should not be construed as a limitation of this invention. Furthermore, the terms "first," "second," "third," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance. Thus, a feature defined with "first," "second," etc., may explicitly or implicitly include one or more of that feature. In the description of this invention, unless otherwise stated, "a plurality of" means two or more.

[0052] In the description of this invention, unless otherwise expressly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to fixed connections, detachable connections, or integral connections; they can refer to mechanical connections or electrical connections; they can refer to direct connections or indirect connections through an intermediate medium; and they can refer to the internal communication between two components. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0053] If this invention discloses or relates to components or structural parts that are fixedly connected to each other, then, unless otherwise stated, a fixed connection can be understood as: a detachable fixed connection (e.g., using bolts or screws) or a non-detachable fixed connection (e.g., riveting, welding). Of course, a fixed connection can also be replaced by an integral structure (e.g., manufactured in one piece using a casting process) (except where it is obviously impossible to use an integral molding process).

[0054] In addition, unless otherwise stated, the terms used in any of the technical solutions disclosed in this invention to indicate positional relationships or shapes include states or shapes that are similar to, close to, or approximate with those states or shapes.

[0055] Any component provided by this invention can be assembled from multiple individual components or can be a single component manufactured by a one-piece molding process.

[0056] It should be noted that the structures, proportions, sizes, etc., depicted in the accompanying drawings of this specification are only used to complement the content disclosed in the specification, so as to enable those skilled in the art to understand and read them, and are not intended to limit the conditions under which the present invention can be implemented. Therefore, they have no substantial technical significance. Any modifications to the structure, changes in the proportions, or adjustments to the size, without affecting the effects and objectives that the present invention can produce, should still fall within the scope of the technical content disclosed in the present invention.

[0057] It should also be noted that in the embodiments of this application, the same reference numerals are used to denote the same component or the same part.

[0058] Any adaptive changes made according to actual needs are within the scope of protection of this invention.

[0059] Specific examples have been used to illustrate the principles and implementation methods of this invention. The descriptions of the above embodiments are only for the purpose of helping to understand the method and core ideas of this invention. Furthermore, those skilled in the art will recognize that, based on the ideas of this invention, there will be changes in the specific implementation methods and application scope. Therefore, the content of this specification should not be construed as a limitation of this invention.

Claims

1. A high-temperature resistant rotating magnetic field component for aerospace applications, characterized in that: It includes a coil support (1), which is mounted on a magnetic stator (2). A coil wire is wound on the coil support (1), and a high-temperature resistant sleeve is provided on the outside of the coil wire.

2. The high-temperature resistant rotating magnetic field assembly for aerospace applications according to claim 1, characterized in that: The material of the coil conductor is pure copper or pure silver; The high-temperature resistant sleeve for the conductor is made of alumina or quartz. The coil support (1) is made of aluminum alloy; The magnetic stator (2) is made of silicon steel sheet. The surface of the magnetic stator (2) is provided with a stator insulating coating. The magnetic stator (2) has a circular ring structure. Several magnetic poles (201) are provided on the inner side of the magnetic stator (2). The magnetically conductive stator (2) is provided in multiple layers, and the magnetically conductive stator (2) is stacked in sequence and fixed by stator fasteners (202).

3. The high-temperature resistant rotating magnetic field assembly for aerospace applications according to claim 1, characterized in that: The coil support (1) includes two end panels (101), at least one isolation panel (102), and a central connecting tube (103). The central connecting tube (103) passes through the center of the end panels (101) and the isolation panel (102). The two end panels (101) are located at both ends of the central connecting tube (103), and the isolation panel (102) is located between the two end panels (101). The coil wire is wound around the central connecting tube (103).

4. The high-temperature resistant rotating magnetic field assembly for aerospace applications according to claim 3, characterized in that: The outer surface of the central connecting pipe (103) is wrapped with a wear-resistant layer.

5. The high-temperature resistant rotating magnetic field assembly for aerospace applications according to claim 3, characterized in that: The outer side of the coil conductor is wrapped with a coil fixing layer, and the outer side of the coil fixing layer is fixed by a fixing layer binding member.

6. The high-temperature resistant rotating magnetic field assembly for aerospace applications according to claim 3, characterized in that: The central connecting pipe (103) has multiple vortex isolation grooves (106) on its side wall.

7. The high-temperature resistant rotating magnetic field assembly for aerospace applications according to claim 3, characterized in that: Both the end panel (101) and the isolation panel (102) are provided with lead wire grooves (105), and the lead wire portion of the coil conductor will pass through the lead wire grooves (105). The outer side of the lead portion of the wire coil is provided with two layers of high-temperature resistant sheathing.

8. The high-temperature resistant rotating magnetic field assembly for aerospace applications according to claim 3, characterized in that: The coil bracket (1) is mounted on the bracket mounting base (3), and the bracket mounting base (3) is provided with a mounting base through hole (301).

9. The high-temperature resistant rotating magnetic field assembly for aerospace applications according to claim 8, characterized in that: The bracket mounting base (3) is provided with a mounting cavity (302), the coil bracket (1) is located in the mounting cavity (302), the mounting cavity (302) is provided with a positioning beam (303), the end panel (101) and the isolation panel (102) are both provided with positioning grooves (104), and the positioning beam (303) is installed on the positioning grooves (104).

10. A method for assembling and testing a high-temperature resistant rotating magnetic field assembly for aerospace applications, characterized in that, The method for assembling the high-temperature resistant rotating magnetic field assembly for aerospace use as described in any one of claims 1-9 includes the following steps: S1. A high-temperature resistant sleeve is installed on the outside of the conductor in the online package; S2. The coil support (1) is cleaned and a wear-resistant layer is wrapped on the coil support (1); S3. Wrap the wire coil around the coil support (1); S4. Wrap a coil fixing layer around the outside of the wound wire coil and secure the coil fixing layer with the fixing layer binding piece; S5. Clean the magnetically conductive stator (2), and then stack several layers of magnetically conductive stator (2) and fix them with stator fasteners (202); S6. Install the coil support (1) onto the magnetic stator (2); S7. Install the coil bracket (1) on the bracket mounting base (3), and then fix the magnetic stator (2) and the bracket mounting base (3) on the heating furnace mounting surface; S8. Provide the same current to the coil conductors on phase A or phase B magnetic poles, measure the magnetic field strength at the center of the magnetic gap and the distribution of the magnetic field strength along the central axis, thereby determining the spatial distribution of the rotating magnetic field; then change the current in the coil conductors, measure the magnetic field strength at the center of the magnetic gap, thereby obtaining the correspondence between the magnetic field strength at the center of the magnetic gap and the current in the coil conductors.

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