A high temperature superconducting magnet magnetic confinement plasma thruster device

Abstract

The application provides a high-temperature superconducting magnet magnetic confinement plasma thrust device, belonging to the technical field of space electric propulsion, and using a superconducting magnet to replace a conventional magnet, which is compact in structure and high in reliability. In the application, a vacuum ceramic tube is inserted at a center axis, a spiral antenna with different sizes is sleeved on different functional areas of the vacuum ceramic tube, a Dewar No.1 is sleeved on the right side of the ceramic tube, a radio frequency hole is opened on the upper part of the Dewar No.1 to connect a radio frequency flange, a refrigeration hole is opened on the lower part of the Dewar No.1 to connect a refrigeration flange, a Dewar No.2 is sleeved on the left side of the ceramic tube, a radio frequency hole is opened on the upper part of the Dewar No.2, the Dewar No.1 and the Dewar No.2 are connected through flanges, a main framework with a flange is sleeved on an inner barrel of the Dewar No.1, a superconducting magnet assembly is placed on the main framework, a split magnet is compressed through an epoxy compression end cover and a screw rod, insulation is performed through alternately inserting insulating epoxy plates and insulating aluminum plates between the split magnets, and a shell wiring assembly is inserted into a flange opening of the Dewar No.2. The application realizes conduction cooling of a superconducting magnet assembly.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of space electric propulsion, and particularly relates to a high-temperature superconducting magnet magnetic confinement plasma thruster device. BACKGROUND

[0002] Electric thrusters are widely used in spacecraft and satellite propulsion. At present, with the deepening of deep space exploration, high-efficiency space electric propulsion devices have become a research hotspot to replace traditional chemical thrusters. Electric propulsion devices use high-purity working gas as propellant, which can effectively reduce the system mass, effectively ionize the gas by electromagnetic control to generate thrust, and effectively change the thrust and specific impulse by controlling the mass flow of the gas. Compared with chemical thrusters, electric thrusters can achieve higher specific impulse and higher propellant utilization efficiency, allowing the system to operate more persistently under high specific impulse conditions. For satellite attitude control, the thrust generated by the electric thruster is more accurate and controllable, and the system wear is small, and the equipment life is longer.

[0003] At present, in the electric propulsion device, such as variable ratio pulse magnetic confinement plasma rocket, helicon thruster, etc., a conventional magnet is generally used to generate the required static magnetic field. However, for high magnetic field environment, the conventional magnet cannot stably operate in high magnetic field environment, which will cause the electric thruster device to directly fail. With the development of low-temperature and refrigeration technology, using a high-temperature superconducting magnet to replace the conventional magnet to generate the required static magnetic field for ground experiments can make the device structure more compact, lighter in weight, stronger and more stable in magnetic field, and without resistance loss, which provides a more ideal environment for the experiment and a better solution for deep space exploration missions.

[0004] At present, the conventional magnet of the magnetic confinement plasma electric propulsion device has the problems of performance degradation with the increase of magnetic field, serious heat loss, heavy weight, and unstable magnetic field. The structure of the current high-temperature superconducting magnet magnetic confinement plasma thruster device is not compact, and the superconducting magnet is easily affected by antenna heating and loses superconductivity. Therefore, it is urgent to design a compact high-temperature superconducting magnet magnetic confinement plasma thruster device to realize the combination of high-temperature superconducting magnet and electric thruster device, so as to realize further equipment optimization on the basis of the current electric thruster device, maintain long-term operation of the high-temperature superconducting magnet, and improve the reliability of the equipment. SUMMARY

[0005] In order to solve the problems of the conventional magnet of the magnetic confinement plasma electric propulsion device, such as performance decline with the increase of the magnetic field, serious heat loss, heavy weight and unstable magnetic field, and the problems of the high-temperature superconducting magnet magnetic confinement plasma thruster device, such as non-compact structure and easy loss of the magnet, the application provides a high-temperature superconducting magnet magnetic confinement plasma thruster device with compact structure, which uses a superconducting magnet to replace the conventional magnet, inserts a vacuum ceramic tube at a central axis, uses a spiral antenna with different sizes in different functional zones of the vacuum ceramic tube, sets a Dewar on the right side of the ceramic tube, opens a radio frequency hole at the upper part of the Dewar to connect a radio frequency flange, opens a refrigeration hole at the lower part of the Dewar to connect a refrigeration flange, sets another Dewar on the left side of the ceramic tube, opens a radio frequency hole at the upper part of the Dewar, connects the Dewar 1 and the Dewar 2 through the flanges, sets a main framework with a flange on the inner barrel of the Dewar 1, places a superconducting magnet assembly on the main framework, presses the split magnet through an epoxy end cover and a screw rod, inserts an insulating epoxy plate and an insulating aluminum plate alternately between the magnets for insulation, inserts a shell wiring assembly into a flange hole of the Dewar 2, connects a current lead to supply power to the superconducting magnet group, sets a cold screen on the outer layer of the magnet, seals the high-temperature superconducting magnet inside, connects a runway pull rod group to the flange of the main framework and the Dewar pull rod fixing ring, and fixes the magnet device, inserts a cold head cold lead copper column at the corresponding position of the refrigeration hole, and places a coil inter-supporting cold lead copper between the No. 1 high-temperature superconducting magnet and the No. 2 high-temperature superconducting magnet to conductively cool the superconducting magnet group.

[0006] In order to achieve the above-mentioned purposes, the application adopts the following technical solutions:

[0007] A high-temperature superconducting magnet magnetic confinement plasma thruster device, comprising a vacuum ceramic tube, a first spiral antenna, a second spiral antenna, a dewar one, a dewar two, a wiring assembly, a radio frequency flange, a radio frequency hole, a refrigeration flange, a cold head copper column, a cold shield, a first high-temperature superconducting magnet group, a second high-temperature superconducting magnet group, a first flange main skeleton, a second flange main skeleton, an epoxy compression end cover, a stainless steel compression end cover, an insulating aluminum plate, an insulating epoxy plate, a skeleton, a support cold copper, a screw, a runway pull rod group, a dewar pull rod fixing ring, the vacuum ceramic tube is placed in the center, the vacuum ceramic tube is inserted into the center hole of the right end cover of the dewar one and the center hole of the left end cover of the dewar two at both ends, the dewar one and the dewar two are butt jointed through the same size flange, the first flange main skeleton and the second flange main skeleton are sleeved on the inner barrel of the dewar one, the cold shield is connected to the flange outer diameter surface of the flange main skeleton, and the vacuum ceramic tube, the dewar one, the dewar two, the first flange main skeleton, the second flange main skeleton and the cold shield are coaxially arranged, the first flange main skeleton and the second flange main skeleton are packaged with the first high-temperature superconducting magnet group and the second high-temperature superconducting magnet group, the first flange main skeleton and the second flange main skeleton pass through the circumferential hole, and the clamping screw is installed to connect the first flange main skeleton and the second flange main skeleton, the first high-temperature superconducting magnet group and the second high-temperature superconducting magnet group are provided with epoxy compression end covers at both ends, the magnet groups are fastened, when the system is running, the refrigerator conducts refrigeration through the cold head copper column to the support cold copper column through the refrigeration flange, the support cold copper conducts cold to the first flange main skeleton, the second flange main skeleton, the first high-temperature superconducting magnet group and the second high-temperature superconducting magnet group, the first high-temperature superconducting magnet group and the second high-temperature superconducting magnet group are powered through the current lead transmission hole of the dewar two end surface, and the first spiral antenna and the second spiral antenna are coaxially fed through the radio frequency flange and the radio frequency hole respectively.

[0008] Further, the vacuum ceramic tube is inserted into the center hole of the right end cover of the dewar one and the center hole of the left end cover of the dewar two at both ends, the dewar is provided with a groove in the axial direction, and the rubber sealing ring is installed to seal the two parts respectively, the right end cover of the dewar one is threaded, and the vacuum ceramic tube can be screwed tightly, the left end of the vacuum ceramic tube is connected to the gas source, the right end is connected to the vacuum chamber, and a sealed cavity is formed.

[0009] Further, the wall thickness of the vacuum ceramic tube is 3.5mm, and the ceramic material is used.

[0010] Further, the dewar one is composed of an inner barrel, an outer barrel, a first butt joint flange and a second butt joint flange, the dewar two is composed of an outer barrel and a flange, the first butt joint flange is used for butt jointing the vacuum chamber, the second butt joint flange is butt jointed with the flange of the dewar two, and the whole structure is supported.

[0011] The radio frequency flange and the refrigeration flange are connected to the outer barrel, the radio frequency hole of the radio frequency flange penetrates the inner barrel and the outer barrel, the radio frequency hole penetrates one side of the outer barrel of the dewar two, and the radio frequency flange and the radio frequency hole are arranged on the same plane.

[0012] Further, the radio frequency flange is opposite the center of the first helical antenna, and the radio frequency hole is opposite the center of the second helical antenna, and the coaxial transmission line is passed through the radio frequency flange and the radio frequency hole to the helical antenna arm, and power is continuously supplied, and the power frequency is in the MHz level.

[0013] Further, the two Dewar rod fixing rings are connected to the left end cover and the right end cover of the Dewar, and the other side is connected to the runway pull rod group.

[0014] Further, the runway pull rod group includes a bolt, a runway pull rod, a ball pad, a room temperature end, and a pin, the pin connects the two ends of the runway pull rod to the room temperature end and the bolt to form a whole, the room temperature end is fixed to the Dewar rod fixing ring, and the bolt rod passes through the magnet pull rod seat head, the ball pad, and the magnet pull rod seat is fixed on the flange end face of the first flange main framework and the flange end face of the second flange main framework, and is uniformly distributed in three sets of runway pull rod groups to fix the magnet device.

[0015] Further, the first high-temperature superconducting magnet group and the second high-temperature superconducting magnet group form a split magnet, which is composed of a single-pie structure and a double-pie structure, and the double-pie structure uses an insulating epoxy plate for insulation, and the single-pie structure uses an insulating aluminum plate for insulation, and a double-pie structure and an insulating aluminum plate are placed together on a framework, and the framework is placed on the first flange main framework and the second flange main framework.

[0016] Further, the first high-temperature superconducting magnet group and the second high-temperature superconducting magnet group are wound from high-temperature superconducting tapes with different numbers of turns, the magnet groups have the same inner diameter and different outer diameters, and the magnet frameworks have the same size and the same inner diameter as the outer diameter of the flange main framework.

[0017] Further, the first high-temperature superconducting magnet group and the second high-temperature superconducting magnet group are turn-to-turn non-insulated magnet coils made of YBCO, and have E-J power law resistance characteristics. The magnetic field in the vacuum ceramic tube is adjusted by adjusting the current value on the current lead, and the current value does not exceed the critical current of the high-temperature superconducting tape.

[0018] Further, the Dewar No. 2 flange end face opening nests four wiring assemblies, one end of the current lead is connected to the high-temperature superconducting magnet group, the other end is connected to the wiring assembly, and the current source continuously passes low-frequency electricity to the wiring assembly.

[0019] Further, the epoxy compression end cover is installed between the magnet and the flange of the first flange main framework and the flange of the second flange main framework for insulation, and the epoxy compression end cover is installed on the other side of the superconducting magnet group before the stainless steel compression end cover is installed, and the screw rod passes through the flange of the first flange main framework, the flange of the second flange main framework, the epoxy compression end cover, and the stainless steel compression end cover to clamp the magnet device, ensuring that the axial distance between the single-pie structures remains unchanged.

[0020] The screw rod is divided into a long screw rod and a short screw rod, the long screw rod fixes two magnet group magnet devices into one, and the short screw rod is used for pressing a single magnet group magnet device.

[0021] Further, the first helical antenna and the second helical antenna are made of copper material and are designed as hollow, the inner diameter of the antenna is the same as the outer diameter of the vacuum ceramic tube, the first helical antenna is 4 cm long, and the second helical antenna is 10 cm long.

[0022] Beneficial effects:

[0023] Compared with a conventional magnet magnetic confinement plasma thruster device, a complete high-temperature superconducting magnet application structure is designed, a refrigerator at a refrigeration flange is started, a cold head copper column and a support cold copper conduct cold, and then refrigeration of the high-temperature superconducting magnet to a working temperature is realized, magnet current leads are led out from a through hole on a flange end cover surface of Dewar I and Dewar II to supply power to the magnet, and a power supply current is less than a critical current of the high-temperature superconducting magnet at different critical temperatures. The structure has good sealing performance, the effective distance between the inner barrel of Dewar I and the flange main skeleton is 88 mm, the magnet region and the warm hole region are separated, and it is ensured that the high-temperature superconducting magnet does not exceed the critical temperature and loses superconductivity in the running process. The use of the high-temperature superconducting magnet ensures that the magnetic field generated in the vacuum ceramic tube is stronger and more stable. For the plasma thruster, a stable magnetic field can ensure long-term effective ionization and plasma motion of the gas, and the result is more reliable. Since the plasma motion is more sensitive to temperature, the zero-resistance characteristic of the superconducting magnet, the high-temperature superconducting magnet does not heat in the running process, compared with the conventional magnet relying on water cooling to reduce temperature, the use of the high-temperature superconducting magnet eliminates the influence of the magnet heating problem on the result in the experiment. BRIEF DESCRIPTION OF DRAWINGS

[0024] Figure 1 It is a structure schematic view of the high-temperature superconducting magnet magnetic confinement plasma thruster device of the application;

[0025] Figure 2 It is a magnet structure schematic view of the application;

[0026] Figure 3 It is a structure schematic view of the pull rod device of the application;

[0027] Figure 4 It is a helical antenna schematic view of the application;

[0028] Figure 5 It is a vacuum ceramic tube center magnetic field schematic view of the application;

[0029] Figure 6 It is an antenna heating loss influence simulation schematic view of the application.

[0030] The attached diagram is labeled as follows: 1-Vacuum ceramic tube, 2-No. 1 helical antenna, 3-No. 2 helical antenna, 4-Dewar 1, 5-Dewar 2, 6-Wiring assembly, 7-RF flange, 8-RF hole, 9-Refrigeration flange, 10-Cold head cooling copper column, 11-Cold shield, 12-No. 1 high-temperature superconducting magnet assembly, 13-No. 2 high-temperature superconducting magnet assembly, 14-No. 1 main frame with flange, 15-No. 2 main frame with flange, 16-Epoxy compression end cap, 17-Stainless steel compression end cap, 18-Insulating aluminum plate, 19-Insulating epoxy board, 20-Frame, 21-Supporting cooling copper, 22-Screw, 23-Runway tie rod assembly, 24-Dewar tie rod fixing ring, 31-Ball pad, 35-Bolt, 33-Pin, 34-Runway tie rod, 35-Room temperature end, 36-Magnet tie rod seat. Detailed Implementation

[0031] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the invention. Furthermore, the technical features involved in the various embodiments of this invention described below can be combined with each other as long as they do not conflict with each other.

[0032] Example 1:

[0033] like Figures 1 to 4 As shown, the high-temperature superconducting magnet magnetic confinement plasma thruster device of this invention includes a vacuum ceramic tube 1, a first spiral antenna 2, a second spiral antenna 3, a Dewar 1 4, a Dewar 2 5, a wiring assembly 6, a radio frequency flange 7, a radio frequency port 8, a cooling flange 9, a cold head cooling copper column 10, a cold shield 11, a first high-temperature superconducting magnet assembly 12, a second high-temperature superconducting magnet assembly 13, a first flanged main frame 14, a second flanged main frame 15, an epoxy compression end cap 16, a stainless steel compression end cap 17, an insulating aluminum plate 18, an insulating epoxy plate 19, a frame 20, a supporting cooling copper 21, a screw 22, a runway tie rod assembly 23, and a Dewar tie rod fixing ring 24.

[0034] Vacuum ceramic tube 1 is placed in the center of high temperature superconducting magnet magnetic confinement plasma thruster device, vacuum ceramic tube 1 is inserted in the center hole of the right end cover of Dewar 4 and the center hole of the left end cover of Dewar 5, the same shape and inner diameter, different length No. 1 spiral antenna 2, No. 2 spiral antenna 3 are sleeved on the different positions of vacuum ceramic tube 1 as different function areas, Dewar 4 and Dewar 5 are connected through the same size flange, No. 1 flange main skeleton 14, No. 2 flange main skeleton 15 are sleeved on the inner barrel of Dewar 4, cold shield 11 is connected to the flange outer diameter surface of the flange main skeleton, and vacuum ceramic tube 1, Dewar 4, Dewar 5, No. 1 flange main skeleton 14, No. 2 flange main skeleton 15, cold shield 11 are coaxially arranged, No. 1 flange main skeleton 14 and No. 2 flange main skeleton 15 are packaged with cold shield 11 to form No. 1 high temperature superconducting magnet group 12 and No. 2 high temperature superconducting magnet group 13, the high temperature superconducting tapes of No. 1 high temperature superconducting magnet group 12 and No. 2 high temperature superconducting magnet group 13 are wound on skeleton 20 to fix the inner diameter, skeleton 20 is sleeved on the main skeleton surface of No. 1 flange main skeleton 14 and No. 2 flange main skeleton 15, insulation is interrupted by alternately using insulating aluminum plate 18 and insulating epoxy plate 19, No. 1 flange main skeleton 14 and No. 2 flange main skeleton 15 pass through the circumferential hole, clamp screw 22 is added to connect No. 1 flange main skeleton 14 and No. 2 flange main skeleton 15, epoxy compression end cover 16 is added to the two ends of No. 1 high temperature superconducting magnet group 12 and No. 2 high temperature superconducting magnet group 13, stainless steel compression end cover 17 is additionally added to the flange one end of No. 1 flange main skeleton 14 and No. 2 flange main skeleton 15, the magnet group is fastened, Dewar rod fixing ring 24 is installed on the inner side of the two flanges of Dewar 5, Dewar rod fixing ring 24 is connected with the flange surface of No. 1 flange main skeleton 14 and No. 2 flange main skeleton 15 through runway pull rod group 23, the magnet is fixed, when the system runs, the refrigerator conducts refrigeration through cold head guide cold copper column 10, support guide cold copper 21, No. 1 flange main skeleton 14, No. 2 flange main skeleton 15, No. 1 high temperature superconducting magnet group 12 and No. 2 high temperature superconducting magnet group 13, No. 1 high temperature superconducting magnet group 12 and No. 2 high temperature superconducting magnet group 13 are powered through the current lead transmission hole of the end surface of Dewar 5, No. 1 spiral antenna 2 and No. 2 spiral antenna 3 are coaxially fed through radio frequency flange 7 and radio frequency hole 8 respectively.

[0035] A complete high-temperature superconducting magnet application structure is designed in this embodiment. The cryocooler at the flange end is started to conduct cold to the cold head copper column and the support copper column, and then the high-temperature superconducting magnet is cooled to the working temperature. The magnet current lead is drawn from the through hole in the flange end cover of Dowa I and Dowa II to supply power to the magnet. The supply current is less than the critical current of the high-temperature superconducting magnet at different critical temperatures. The structure has good sealing performance. The effective distance between the inner barrel of Dowa I and the main skeleton with flange is 88 mm, which separates the magnet area and the warm hole area, ensuring that the high-temperature superconducting magnet will not exceed the critical temperature during operation. The use of high-temperature superconducting magnet ensures that the magnetic field generated in the vacuum ceramic tube is stronger and more stable. For the plasma thruster, a stable magnetic field can ensure long-term effective ionization of the gas and plasma movement, and the results are more reliable. Since plasma movement is more sensitive to temperature, and the zero-resistance characteristic of superconducting magnet, the high-temperature superconducting magnet will not heat up during operation. Compared with the use of conventional magnets relying on water cooling to reduce temperature, the use of high-temperature superconducting magnet eliminates the impact of magnet heating problems on the results during the experiment.

[0036] Example 2

[0037] In combination Figure 1 This embodiment is different from Example 1 in that the vacuum ceramic tube is inserted into the center hole of the right end cover of Dowa I 4 and the center hole of the left end cover of Dowa II 5. The Dowa has a groove in the axial direction, and a rubber sealing ring is added to seal the two parts. The right end cover of Dowa I 4 has threads to tighten the vacuum ceramic tube 1. The left end of the vacuum ceramic tube is connected to the gas source, and the right end is connected to the vacuum chamber to form a sealed cavity. The other components and connection methods are the same as in Example 1.

[0038] Example 3

[0039] In combination Figure 1 This embodiment is different from Example 2 in that the vacuum ceramic tube has a wall thickness of 3.5 mm and is made of ceramic material. The other components and connection methods are the same as in Example 2.

[0040] Example 4

[0041] In combination Figure 1 This embodiment is different from Example 3 in that Dowa I is composed of an inner barrel, an outer barrel, a first butt flange, and a second butt flange. Dowa II is composed of an outer barrel and a flange. The first butt flange is used to butt joint the vacuum chamber, and the second butt flange is used to butt joint the flange of Dowa II to support the entire structure. The radio frequency flange and the refrigeration flange are connected to the outer barrel. The radio frequency hole of the radio frequency flange penetrates the inner barrel and the outer barrel. The radio frequency hole penetrates one side of the outer barrel of Dowa II, and the radio frequency flange and the radio frequency hole are arranged in the same plane. The other components and connection methods are the same as in Example 3.

[0042] Example 5:

[0043] Combination Figure 1 , Figure 4 This embodiment differs from Embodiment 4 in that the RF flange faces the center of the first helical antenna, and the RF aperture faces the center of the second helical antenna. Coaxial transmission lines run from the RF flange and the RF aperture to the helical antenna arms for continuous power supply, with power frequencies in the MHz range. Other components and connections are the same as in Embodiment 4.

[0044] Example 6:

[0045] Combination Figure 1 , Figure 3 This embodiment differs from Embodiment 5 in that the two Dewar tie rod fixing rings are respectively connected to the left and right end caps of the Dewar, and the other side is connected to the runway tie rod assembly. Other components and connection methods are the same as in Embodiment 5.

[0046] Example 7:

[0047] Combination Figure 3 This embodiment differs from Embodiment 6 in that the runway tie rod assembly 23 includes bolts 32, runway tie rods 34, ball pads 31, room temperature end 35, and pins 33. Pins 33 connect both ends of the runway tie rod 34 to the room temperature end 35 and bolts 35 respectively, forming a whole. The room temperature end 35 is fixed to the Dewar tie rod fixing ring 24. The bolt rod passes through the ball pad on the end of the magnet tie rod seat 36 to prevent it from falling off. Magnet tie rod seats 36 are fixed to the flange end faces of the first flanged main frame 14 and the second flanged main frame 15, with three seats evenly distributed circumferentially, connecting three sets of runway tie rod assemblies 23 to fix the magnet device. Other components and connection methods are the same as in Embodiment 6.

[0048] Example 8:

[0049] Combination Figures 1 to 2 This embodiment differs from Embodiment 7 in that the No. 1 and No. 2 high-temperature superconducting magnet groups form a split magnet, consisting of single-pane and double-pane structures. The double-pane structures are insulated with insulating epoxy boards, while the single-pane structures are insulated with insulating aluminum plates. Each double-pane and insulating aluminum plate is placed on a frame, which is fitted onto the No. 1 and No. 2 flanged main frames. Other components and connections are the same as in Embodiment 7.

[0050] Example 9:

[0051] Combination Figures 1 to 2This embodiment is different from embodiment 8 in that the first high-temperature superconducting magnet group and the second high-temperature superconducting magnet group are wound by high-temperature superconducting tapes with different numbers of turns, the inner diameters of the magnet groups are the same, the outer diameters are different, the magnet skeleton sizes are the same, and the inner diameters of the magnet skeletons are equal to the outer diameters of the main skeletons with flanges. Other components and connection modes are the same as those of embodiment 8.

[0052] Embodiment 10:

[0053] In combination Figures 1 to 2 This embodiment is different from embodiment 10 in that the first high-temperature superconducting magnet group and the second high-temperature superconducting magnet group are inter-turn non-insulated magnet coils, the material is YBCO, and the resistance characteristic has E-J power law. The magnetic field in the vacuum ceramic tube is adjusted by adjusting the current value on the current lead, and the current value does not exceed the critical current of the high-temperature superconducting tape. Other components and connection modes are the same as those of embodiment 9.

[0054] Embodiment 11:

[0055] In combination Figures 1 to 2 This embodiment is different from embodiment 10 in that the flanges of the Dewar No. 1 and No. 2 are drilled to embed four wiring assemblies, one end of the current lead is connected to the high-temperature superconducting magnet group, the other end is connected to the wiring assembly, and the current source continuously passes low-frequency electricity to the wiring assembly. Other components and connection modes are the same as those of embodiment 10.

[0056] Embodiment 12:

[0057] In combination Figures 1 to 2 This embodiment is different from embodiment 11 in that the epoxy compression end cover is installed between the magnet and the flanges of the first and second main skeletons with flanges for insulation, and the epoxy compression end cover is installed on the other side of the superconducting magnet group before the stainless steel compression end cover is installed. The screw passes through the first and second main skeletons with flanges, the epoxy compression end cover, and the stainless steel compression end cover to clamp the magnet device, ensuring that the axial distance between the single pies is unchanged. The screw is divided into long and short screws, the long screw fixes the two magnet group magnet devices into one, and the short screw is used to compress the single magnet group magnet device. Other components and connection modes are the same as those of embodiment 11.

[0058] Embodiment 13: In combination Figure 4 This embodiment is different from embodiment 12 in that the first and second spiral antennas are made of copper and are designed as hollow, the inner diameter of the antenna is the same as the outer diameter of the vacuum ceramic tube, the first spiral antenna is 4 cm long, and the second spiral antenna is 10 cm long. Other components and connection modes are the same as those of embodiment 12.

[0059] Embodiment 14: In combination Figure 5The embodiment is described, and the difference between the embodiment and the embodiment 13 is that the magnetic field generated by the different current input to the first high-temperature superconducting magnet group and the second high-temperature superconducting magnet group is the field type required by the specific plasma electromagnetic propulsion device operation. The other components and connection modes are the same as those of the embodiment 13.

[0060] Embodiment 15: Combination Figure 6 The embodiment is described, and the difference between the embodiment and the embodiment 14 is that most of the loss generated by the first spiral antenna and the second spiral antenna is absorbed by the inner barrels of the Dewar 1 and the Dewar 2, and the influence on the superconducting magnet is small, which will not cause quenching during operation. The other components and connection modes are the same as those of the embodiment 14.

[0061] The high-temperature superconducting magnet magnetic confinement plasma thrust device provided by the application works as follows. First, the vacuum ceramic tube 1 is evacuated to remove the internal air, and then the vacuum ceramic tube 1 is washed with high-purity working gas from the gas source. The refrigerator at the refrigerator flange is opened, and the magnet is conducted to cool. When the magnet enters the working temperature range, the first high-temperature superconducting magnet group and the second high-temperature superconducting magnet group are powered by the current lead passing through the current lead hole of the flange of the Dewar 1 left end cover and the Dewar 2 right end cover. The current value of the current source is strictly less than the critical current value of the superconducting tape corresponding to the working temperature. The radio frequency antenna is fed by coaxial transmission through the radio frequency flange. With the increase of the feeding power, the gas is excited into high-energy particles-plasma, and the discharge process is completed. Under the action of the radio frequency wave and the magnetic field, the energy of the plasma is continuously improved, and the speed of the directional motion is continuously improved. When the plasma is discharged from the vacuum ceramic tube 1, the thrust is generated, and the whole process of the thruster is completed.

[0062] The application has been disclosed as above with the preferred embodiment, however, it is not used to limit the application, any skilled person in the art can make some changes or modifications to the equivalent embodiments with the above disclosed structure and technical content without departing from the technical solution range of the application. However, any simple modification, equivalent change and modification made to the above embodiments according to the technical essence of the application are still within the technical solution range of the application.

Claims

1. A high-temperature superconducting magnet magnetic confinement plasma thruster device, characterized in that, Includes vacuum ceramic tube (1), No. 1 spiral antenna (2), No. 2 spiral antenna (3), Dewar 1 (4), Dewar 2 (5), wiring assembly (6), RF flange (7), RF port (8), cooling flange (9), cold head cooling copper column (10), cold shield (11), No. 1 high temperature superconducting magnet assembly (12), No. 2 high temperature superconducting magnet assembly (13), No. 1 flanged main frame (14), No. 2 flanged main frame (15), epoxy compression end cap (16), stainless steel compression end cap (17), insulating aluminum plate (18), insulating epoxy board (19), frame (20), supporting cooling copper (21). Screw (22), runway tie rod assembly (23), Dewar tie rod fixing ring (24); The vacuum ceramic tube (1) is placed in the center of the high-temperature superconducting magnet magnetic confinement plasma thruster device. The two ends of the vacuum ceramic tube (1) are inserted into the center hole of the right end cap of Dewar I (4) and the center hole of the left end cap of Dewar II (5). Dewar I (4) and Dewar II (5) are connected by flanges of the same size. The No. 1 flanged main frame (14) and the No. 2 flanged main frame (15) are fitted on the inner barrel of Dewar I (4). The cold shield is connected to the outer diameter surface of the flange of the flanged main frame. The vacuum ceramic tube (1), Dewar I (4), Dewar II (5), and the first The first flanged main frame (14), the second flanged main frame (15), and the cold shield (11) are coaxially arranged. The first flanged main frame (14), the second flanged main frame (15), and the cold shield (11) encapsulate the first high-temperature superconducting magnet group (12) and the second high-temperature superconducting magnet group (13). The first flanged main frame (14) and the second flanged main frame (15) have through circumferential holes, and clamping screws are installed to connect the first flanged main frame (14) and the second flanged main frame (15). Epoxy compression end caps (16) are installed at both ends of the first high-temperature superconducting magnet group (12) and the second high-temperature superconducting magnet group (13). When the system is running, the refrigerator conducts cooling through the cooling head copper column (10) of the cooling flange (9) to support the cooling copper (21). The cooling copper (21) conducts cooling through the main frame with flange (14), the main frame with flange (15), the first high temperature superconducting magnet group (12), and the second high temperature superconducting magnet group (13). The first high temperature superconducting magnet group (12) and the second high temperature superconducting magnet group (13) are powered by the current transmission lead through the Dewar 2 (5) end hole. The first spiral antenna (2) and the second spiral antenna (3) are coaxially fed through the radio frequency flange (7) and the radio frequency hole (8), respectively.

2. The high-temperature superconducting magnet magnetic confinement plasma thruster device according to claim 1, characterized in that: The vacuum ceramic tube (1) is inserted into the center hole of the right end cap of Dewar 1 (4) and the center hole of the left end cap of Dewar 2 (5). The right end cap of Dewar 1 (4) has threads for tightening the vacuum ceramic tube (1). The left end of the vacuum ceramic tube (1) is connected to the gas source and the right end is connected to the vacuum chamber to form a sealed cavity.

3. The high-temperature superconducting magnet magnetic confinement plasma thruster device according to claim 2, characterized in that: Vacuum ceramic tube (1) has a wall thickness of 3.5mm and is made of ceramic material.

4. The high-temperature superconducting magnet magnetic confinement plasma thruster device according to claim 2, characterized in that: Dewar 1 (4) consists of an inner barrel, an outer barrel, a No. 1 docking flange, and a No. 2 docking flange. Dewar 2 (5) consists of an outer barrel and a flange. The No. 1 docking flange is used to dock with the vacuum chamber. The No. 2 docking flange docks with the flange of Dewar 2 (5) to support the entire structure. The RF flange (7) and the cooling flange (9) are connected to the outer barrel of Dewar 1. The RF port of the RF flange (7) passes through the inner barrel and the outer barrel of Dewar 1. The RF port (8) passes through one side of the outer barrel of Dewar 2 (5). The RF flange (7) and the RF port are set on the same plane.

5. The high-temperature superconducting magnet magnetic confinement plasma thruster device according to claim 4, characterized in that: The RF flange (7) is directly opposite the center of the first spiral antenna (2), and the RF hole (8) is directly opposite the center of the second spiral antenna (3). Coaxial transmission lines are passed through the RF flange (7) and the RF hole (8) to the spiral antenna arm for continuous power supply. The power supply frequency is in the MHz range.

6. The high-temperature superconducting magnet magnetic confinement plasma thruster device according to claim 1, characterized in that: Two Dewar tie rod fixing rings (24) are connected to the left end cap and the right end cap of Dewar 1 (4) respectively, and the other side of the two Dewar tie rod fixing rings (24) is connected to the runway tie rod assembly (23).

7. The high-temperature superconducting magnet magnetic confinement plasma thruster device according to claim 6, characterized in that: The runway tie rod assembly (23) includes bolts, runway tie rods, ball pads, room temperature end, and pins. The pins connect the two ends of the runway tie rods to the room temperature end and bolts respectively to form a whole. The room temperature end is fixed to the Dewar tie rod fixing ring. The bolt rod passes through the ball pad of the magnet tie rod seat to prevent it from falling off. The magnet tie rod seat is fixed with three evenly distributed circumferentially on the flange end face of the No. 1 flanged main frame and the flange end face of the No. 2 flanged main frame, and connects three sets of runway tie rod assemblies (23) to fix the magnet device.

8. The high-temperature superconducting magnet magnetic confinement plasma thruster device according to claim 4, characterized in that: The No. 1 high-temperature superconducting magnet group (12) and the No. 2 high-temperature superconducting magnet group (13) form a split magnet, which consists of a single-pane structure and a double-pane structure. The double panes are insulated with an insulating epoxy board (19), and the single panes are insulated with an insulating aluminum plate (18). A double pane and an insulating aluminum plate (18) are placed on a frame (20). The frame (20) is fitted on the No. 1 flanged main frame (14) and the No. 2 flanged main frame (15).

9. A high-temperature superconducting magnet magnetic confinement plasma thruster device according to claim 8, characterized in that: The No. 1 high-temperature superconducting magnet group (12) and the No. 2 high-temperature superconducting magnet group (13) are made of high-temperature superconducting tape with different number of turns. The inner diameter of the magnet group is the same, but the outer diameter is different. The magnet skeleton (20) has the same size, and the inner diameter of the skeleton is equal to the outer diameter of the main skeleton with flange.

10. A high-temperature superconducting magnet magnetic confinement plasma thruster device according to claim 9, characterized in that: The No. 1 high-temperature superconducting magnet group (12) and the No. 2 high-temperature superconducting magnet group (13) are non-insulated magnet coils with YBCO material, and their resistance characteristics have EJ power law. The magnetic field in the vacuum ceramic tube (1) is adjusted by adjusting the current value on the current lead, and the current value does not exceed the critical current of the high-temperature superconducting tape.

11. A high-temperature superconducting magnet magnetic confinement plasma thruster device according to claim 10, characterized in that: The No. 4 and No. 2 flanges of Dewar 1 and Dewar 2 (5) have openings on their end faces, and four wiring components are nested therein. One end of the current lead is connected to the high-temperature superconducting magnet assembly, and the other end is connected to the wiring component. The current source continuously supplies low-frequency electricity to the wiring component.

12. The high-temperature superconducting magnet magnetic confinement plasma thruster device according to claim 8, characterized in that: Install the epoxy clamping end cap (16) to insulate between the magnet and the flange of the No. 1 flanged main frame (14) and the flange of the No. 2 flanged main frame (15). On the other side of the superconducting magnet assembly, first install the epoxy clamping end cap (16) and then install the stainless steel clamping end cap (17). The screw (22) passes through the flange of the No. 1 flanged main frame (14), the flange of the No. 2 flanged main frame (15), the epoxy clamping end cap (16), and the stainless steel clamping end cap (17) to clamp the magnet device and ensure that the axial distance between the single discs remains unchanged. The screw (22) is divided into a long screw and a short screw. The long screw fixes the two magnet groups into one unit, while the short screw is used to press the individual magnet group.

13. The high-temperature superconducting magnet magnetic confinement plasma thruster device according to claim 1, characterized in that: Both the No. 1 spiral antenna (2) and the No. 2 spiral antenna (3) are made of copper and have a hollow design. The inner diameter of the antenna is the same as the outer diameter of the vacuum ceramic tube (1). The No. 1 spiral antenna is 4cm long and the No. 2 spiral antenna is 10cm long.

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