阅读说明：本技术 一种超导型磁等离子体推进器 (Superconducting magnetic plasma propeller ) 是由 宋云涛 郑金星 刘菲 刘海洋 李永 周成 王戈 李明 朱小亮 吴友军 马林森 于 2020-10-29 设计创作，主要内容包括：本发明公开了一种超导型磁等离子体推进器,包括推进器阴极和推进器阳极,所述推进器阴极包括阴极进气管、固定环件、内腔体、外腔体、喷管固定座和阴极喷管,所述阴极进气管固定连接在所述内腔体前端,所述内腔体后端通过螺纹连接喷管固定座,所述喷管固定座与所述阴极喷管固定连接；所述内腔体、喷管固定座和阴极喷管均为中空结构,共同构成阴极进气通道；所述固定环件和外腔体固定嵌套在所述内腔体外侧；所述推进器阳极一端固定连接绝缘管件,所述绝缘管件和推进器阳极均嵌套在所述外腔体外侧。本发明推进器阳极通过螺旋式换热单元和多通道换热单元进行降温,实现阳极端部的均匀冷却。(The invention discloses a superconducting magnetic plasma propeller, which comprises a propeller cathode and a propeller anode, wherein the propeller cathode comprises a cathode air inlet pipe, a fixed ring piece, an inner cavity, an outer cavity, a spray pipe fixing seat and a cathode spray pipe; the inner cavity, the spray pipe fixing seat and the cathode spray pipe are all of hollow structures and jointly form a cathode air inlet channel; the fixed ring piece and the outer cavity are fixedly nested outside the inner cavity; one end of the propeller anode is fixedly connected with an insulating pipe fitting, and the insulating pipe fitting and the propeller anode are both nested outside the outer cavity. The propeller anode is cooled through the spiral heat exchange unit and the multi-channel heat exchange unit, so that the end part of the anode is uniformly cooled.)

1. A superconducting magnetic plasma propeller is characterized by comprising a propeller cathode and a propeller anode, wherein the propeller cathode comprises a cathode air inlet pipe, a fixed ring piece, an inner cavity, an outer cavity, a spray pipe fixing seat and a cathode spray pipe; the inner cavity, the spray pipe fixing seat and the cathode spray pipe are all of hollow structures and jointly form a cathode air inlet channel; the fixed ring piece and the outer cavity are fixedly nested outside the inner cavity;

one end of the propeller anode is fixedly connected with an insulating pipe fitting, and the insulating pipe fitting and the propeller anode are both nested outside the outer cavity.

2. A superconducting magnetic plasma thruster according to claim 1 wherein a coolant passage is provided between the stationary ring and the outer and inner cavities; the liquid inlet and the liquid outlet of the cooling liquid channel are positioned at the front end of the outer cavity.

3. A superconducting magnetic plasma thruster according to claim 1, wherein the cathode gas inlet pipe is perpendicular to the inner cavity, and one end of the inner cavity is sealed while the other end is connected to the nozzle holder.

4. A superconducting magnetic plasma thruster as claimed in claim 1 wherein an insulating layer is provided between the insulating pipe and the thruster anode and the thruster cathode.

5. A superconducting magnetic plasma thruster as claimed in claim 1 wherein the cathode nozzle is a multi-hole cathode nozzle.

6. A superconducting magnetic plasma thruster according to claim 1 wherein the thruster anode comprises an anode body and a helical heat exchange unit nested outside the thruster anode.

7. A superconducting magnetic plasma propeller according to claim 6, wherein the spiral heat exchange unit comprises a heat exchange shell, a heat exchange lining, a first liquid inlet pipe, a first liquid outlet pipe and a spiral channel located between the heat exchange shell and the heat exchange lining, the heat exchange lining is fixed on the outer side of the anode body for a circle, and the spiral channel is located in the heat exchange lining and surrounds the anode body for a circle.

8. A superconducting magnetic plasma thruster according to claim 6, wherein the thruster anode further comprises a multi-channel heat exchange unit, the multi-channel heat exchange unit comprises an end shell, an end cooling tank, a second liquid inlet pipe, a second liquid outlet pipe and an end cooling channel, the end shell is fixed at the rear end of the thruster anode, and the front end of the thruster anode is connected with an insulating pipe fitting; the outside of tip shell sets up the tip cooling bath, tip cooling channel sets up around the propeller positive pole, and the one end of tip cooling channel is connected the tip cooling bath, and the second feed liquor pipe or second drain pipe are connected to the other end.

9. A superconducting magnetic plasma thruster according to claim 8 wherein the second inlet pipes and the second outlet pipes are equal in number and symmetrically distributed outside the anode of the thruster.

10. A superconducting magnetic plasma thruster as claimed in claim 8 wherein the end housing, thruster anode and insulating pipe are nested together outside the outer cavity.

Technical Field

The invention relates to the field of propellers, in particular to a superconducting magnetic plasma propeller.

Background

Space tasks such as large-scale spacecraft orbit transfer, manned lunar landing, deep space exploration and the like put higher demands on the specific impulse, thrust, service life and the like of a propulsion system. The traditional chemical propulsion and Hall propulsion have large thrust, small specific impulse and low effective load, and the ion propulsion has high specific impulse and small thrust, so that the requirements of future space tasks cannot be met. The principle of the magnetic plasma thruster is that the plasma generated by ionizing a working medium by a high-temperature electric arc is accelerated under the comprehensive action of a magnetic field and an electric field so as to generate reverse thrust on the thruster, and the acceleration mechanism relates to four mutually coupled acceleration modes of self field acceleration, vortex acceleration, Hall acceleration and pneumatic acceleration and is known as the strongest electric propulsion technology by NASA. The method has a plurality of advantages in the aspects of large-scale spacecraft orbit transfer, manned lunar landing, deep space exploration and the like.

Generally, the ion propulsion is used to accelerate and eject ions generated by ionization of working media under the action of an electrostatic field to generate thrust. The additional magnetic field is provided by a superconducting magnet instead of a conventional copper coil, so that not only can a higher magnetic field strength be obtained, the size of the whole component is greatly reduced, but also the cathode plasma discharge is more uniform due to the uniform magnetic field of the superconducting magnet.

The main function of the anode of the space magnetic plasma dynamic thruster is to maintain the constant discharge balance of the anode and the cathode, and the structural form and the size of the anode directly play a vital role in the plasma ionization and energy injection efficiency of the thruster.

The power loss of the space superconducting magnetic plasma thruster is mainly at an anode, but the tip of a cathode needs to bear high temperature of about 2000-3000K, energy generated by the high temperature is finally converted into heat, the cathode is the worst working environment in all parts of the thruster, because the cathode is positioned in the center of a discharge area and needs to directly bear bombardment of ions, strong heat radiation and joule heat brought by discharge current, the anode of the space magnetic plasma thruster bears the bombardment of electrons and ions, 80% of heat loss of the thruster occurs at the anode, and the thermal environment of the anode is severe, so how to efficiently discharge the heat of the anode is particularly important. However, in a space environment, the cooling efficiency of the anode is seriously low due to the weight loss of cooling water, and the traditional heat exchange structure is difficult to meet the refrigeration requirement of the anode.

Disclosure of Invention

In view of the shortcomings of the prior art, the invention aims to provide a superconducting magnetic plasma thruster.

In order to achieve the purpose, the invention adopts the following technical scheme: a superconducting magnetic plasma propeller comprises a propeller cathode and a propeller anode, wherein the propeller cathode comprises a cathode air inlet pipe, a fixed ring piece, an inner cavity, an outer cavity, a spray pipe fixing seat and a cathode spray pipe; the inner cavity, the spray pipe fixing seat and the cathode spray pipe are all of hollow structures and jointly form a cathode air inlet channel; the fixed ring piece and the outer cavity are fixedly nested outside the inner cavity;

one end of the propeller anode is fixedly connected with an insulating pipe fitting, and the insulating pipe fitting and the propeller anode are both nested outside the outer cavity.

Further, a cooling liquid channel is arranged between the fixed ring piece and the inner cavity body as well as between the outer cavity body and the inner cavity body; the liquid inlet and the liquid outlet of the cooling liquid channel are positioned at the front end of the outer cavity.

Furthermore, the cathode air inlet pipe is perpendicular to the inner cavity, one end of the inner cavity is sealed, and the other end of the inner cavity is connected with the spray pipe fixing seat.

Further, an insulating layer is arranged between the insulating pipe fitting and the propeller anode and between the propeller cathode.

Further, the cathode nozzle is a porous cathode nozzle.

Further, the propeller anode comprises an anode body and a spiral heat exchange unit, and the spiral heat exchange unit is nested outside the propeller anode.

Further, spiral heat transfer unit includes heat transfer shell, heat transfer inside lining, first feed liquor pipe, first drain pipe and is located the spiral channel between heat transfer shell and the heat transfer inside lining, the heat transfer inside lining is fixed anode body outside a week, spiral channel is located in the heat transfer inside lining, and encircle anode body a week.

Furthermore, the propeller anode also comprises a multi-channel heat exchange unit, the multi-channel heat exchange unit comprises an end part shell, an end part cooling groove, a second liquid inlet pipe, a second liquid outlet pipe and an end part cooling channel, the end part shell is fixed at the rear end of the propeller anode, and the front end of the propeller anode is connected with an insulating pipe fitting; the outside of tip shell sets up the tip cooling bath, tip cooling channel sets up around the propeller positive pole, and the one end of tip cooling channel is connected the tip cooling bath, and the second feed liquor pipe or second drain pipe are connected to the other end.

Furthermore, the number of the second liquid inlet pipes is equal to that of the second liquid outlet pipes, and the second liquid inlet pipes and the second liquid outlet pipes are symmetrically distributed on the outer side of the anode of the propeller.

Further, the end shell, the propeller anode and the insulating pipe fitting are nested outside the outer cavity together.

The invention has the beneficial effects that: when the propeller works, the porous cathode spray pipe is higher in temperature and easy to generate corrosion loss, and is connected with the inner cavity through threads, so that the replacement efficiency is higher after the loss, and the replacement cost is lower. The liquid inlet and the liquid outlet of the cooling liquid channel in the cathode of the propeller are designed on the same side, so that more cooling liquid can be kept in the cooling liquid channel, the retention time of the cooling liquid in the channel is prolonged, a large amount of heat generated by the porous cathode spray pipe can be taken away, and the utilization efficiency of the cooling liquid is improved. The multi-position structure of the porous cathode spray pipe is connected in a welding mode, so that the cooling liquid leakage can be prevented more reliably and effectively. The cooling time of the cooling liquid in the heat exchange lining is effectively prolonged by the propeller anode through the spiral heat exchange unit, and the cooling efficiency is improved; the flow of the cooling liquid can be greatly increased through the multi-channel heat exchange unit, and the heat exchange speed is accelerated, so that the refrigerating capacity is improved; in addition, the uniform cooling of the end part of the anode is realized by the way that water inlets and water outlets are alternately arranged among the end part cooling channels of the multi-channel heat exchange unit.

Drawings

FIG. 1 is a schematic structural view of a propeller cathode according to the present invention;

FIG. 2 is a schematic structural view of a propeller according to the present invention;

FIG. 3 is a top view of the propeller of the present invention;

FIG. 4 is a schematic structural view of a propeller anode according to the present invention;

FIG. 5 is a schematic structural view of a spiral heat exchange unit according to the present invention;

FIG. 6 is a schematic structural diagram of a multi-channel heat exchange unit according to the present invention.

Reference numerals: 11 cathode gas inlet pipes, 12 fixed ring parts, 13 inner cavities, 14 outer cavities, 15 spray pipe fixing seats, 16 cathode spray pipes, 17 liquid inlets, 18 liquid outlets, 21 insulating pipe fittings, 22 anode bodies, 23 spiral heat exchange units, 24 multi-channel heat exchange units, 231 heat exchange shells, 232 heat exchange linings, 233 first liquid inlet pipes, 234 first liquid outlet pipes, 235 spiral channels, 241 end shells, 242 end cooling grooves, 243 second liquid inlet pipes, 244 second liquid outlet pipes and 245 end cooling channels,

Detailed Description

The invention will be further described with reference to the accompanying drawings and the detailed description below:

referring to the attached drawings 1-2, the superconducting magnetic plasma propeller comprises a propeller cathode and a propeller anode, wherein the propeller cathode comprises a cathode air inlet pipe 11, a fixed ring member 12, an inner cavity 13, an outer cavity 14, a spray pipe fixing seat 15 and a cathode spray pipe 16, the cathode air inlet pipe 11 is fixedly connected to the front end of the inner cavity 13, the rear end of the inner cavity 13 is connected with the spray pipe fixing seat 15 through threads, and the spray pipe fixing seat 15 is fixedly connected with the cathode spray pipe 16; the inner cavity 13, the nozzle fixing seat 15 and the cathode nozzle 16 are all hollow structures and jointly form a cathode air inlet channel; the fixed ring member 12 and the outer cavity 14 are fixedly nested outside the inner cavity 13. The cathode nozzle in the invention is a porous cathode nozzle.

Preferably, as shown in fig. 1, the cathode gas inlet pipe is perpendicular to the inner cavity, one end of the inner cavity is sealed, and the other end of the inner cavity is connected with the nozzle fixing seat.

Specifically, the inner cavity 13 and the cathode gas inlet pipe 11 are fixed by welding and connected with the nozzle fixing seat 15 by threaded connection, the nozzle fixing seat 15 is fixed with the cathode nozzle 16 by high-temperature welding, and the two parts jointly form a gas inlet channel structure of the porous cathode nozzle of the space superconducting type magnetic plasma thruster, when the thruster works, propellant sprayed from the cathode nozzle 16 is ionized by arc discharge between the cathode nozzle 16 and the anode of the thruster to generate high-temperature plasma, and the high-temperature plasma is accelerated and sprayed out under the action of a magnetic field generated by a space superconducting magnet, so that required reaction force is generated to propel the space spacecraft, wherein the space superconducting magnet surrounds the periphery of the thruster.

With continued reference to fig. 1-2, the outer cavity 14, the fixed ring 12 and the inner cavity 13 are fixed by welding, a cooling liquid channel is left between the fixed ring 12 and the inner cavity 13, and cooling liquid flows through the liquid inlet 17 and the liquid outlet 18, which together form a cathode liquid cooling structure, and the liquid cooling structure of the porous cathode nozzle is sleeved as a whole into the insulating tube 21 to be connected and fixed with the propeller anode and insulated, so that no short circuit or breakdown occurs at other parts outside the ionization between the propeller anode and the cathode nozzle 16 during operation. Cathode spray tube 16 is because of the erosion of high temperature plasma discharge, sputter, produce a large amount of heats, heat conduction is to the lower interior cavity 13 of temperature on, the coolant liquid flows in cooling channel, the most heat that porous cathode spray tube during operation produced can be taken away in the circulation of coolant liquid, derive a large amount of heats through forced convection heat transfer, the life-span of extension space superconductive type magnetism plasma propeller negative pole, thereby guarantee that the propeller carries out stable discharge in 16 most advanced positions of cathode spray tube, guarantee overall structure's steady operation, and then improve the work life of propeller.

Please refer to the attached drawing, the cathode of the propeller ensures that the temperature is not too high during the operation of the propeller through the cooling channel reserved inside the cathode, and the reliability of the whole system is not affected. Two liquid inlets and two liquid outlets which are connected with the cooling liquid channels are evenly distributed at the upper part and the lower part of the end part of the outer cavity far away from the porous cathode spray pipe. During operation, cooling liquid enters from the liquid inlet, flows to the liquid outlet at the upper part of the outer cavity through the wall of the inner cavity and flows out from the liquid outlet, and the cooling liquid takes away overhigh heat generated by the cathode during operation of the propeller through heat exchange with the outer surface of the inner cavity, so that the stable operation of the propeller system is ensured.

Please refer to fig. 4-6, in which an insulating layer is disposed between the insulating pipe and the propeller anode and the propeller cathode. The propeller anode includes an anode body 222, a spiral heat exchange unit 23, and a multi-channel heat exchange unit 24.

The spiral heat exchange unit is nested outside the propeller anode. One end of the propeller anode is fixedly connected with an insulating pipe fitting, and the insulating pipe fitting and the propeller anode are both nested outside the outer cavity. Spiral heat transfer unit includes heat transfer shell 231, heat transfer inside lining 232, first feed liquor pipe 233, first drain pipe 234 and is located the spiral channel 235 between heat transfer shell and the heat transfer inside lining, and heat transfer inside lining 232 is fixed in anode body 222 outside a week, and spiral channel 235 is located the heat transfer inside lining, and encircles anode body a week.

Spiral channel 235 is machined from heat exchange liner 232 and the depth and width of the spiral channel are designed to closely match the cooling capacity required. The heat exchange shell 231 and the heat exchange lining 232 are assembled and welded to form a sealed cooling channel.

First feed liquor pipe 233 and first drain pipe 234 all weld with heat transfer shell 231, guarantee that the structure is sealed, and the cooling water does not reveal. The cooling water enters the spiral channel 235 through the first inlet pipe 233 and finally flows out through the first outlet pipe 234. The spiral channel obviously increases the flow path of the cooling water, has better heat conduction capability and improves the heat exchange capability of the anode. The first inlet pipe 233 and the first outlet pipe 234 are arranged at diagonal positions.

The propeller anode further comprises a multi-channel heat exchange unit, the multi-channel heat exchange unit comprises an end part shell 241, an end part cooling groove 242, a second liquid inlet pipe 243, a second liquid outlet pipe 244 and an end part cooling channel 245, the end part shell 241 is fixed at the rear end of the propeller anode, and the front end of the propeller anode is connected with the insulating pipe fitting 21; the outside of tip shell sets up the tip cooling bath, and tip cooling channel sets up around the propeller positive pole, and tip cooling channel's one end connects the tip cooling bath, and the second feed liquor pipe or second drain pipe are connected to the other end.

The number of the second liquid inlet pipes is equal to that of the second liquid outlet pipes, and the outer sides of the anodes of the thrusters are symmetrically distributed. The end part shell, the propeller anode and the insulating pipe fitting are nested outside the outer cavity together.

The end casing 241 and the anode body 22 are welded to form an end cooling groove 242. The second liquid inlet pipe 243 and the second liquid outlet pipe 243 are welded and sealed with the anode body 22, so that the cooling water is prevented from leaking. The coolant enters the end cooling channel 245 through the second liquid inlet pipe 243 and then flows into the end cooling bath 242; and exits the multi-channel heat exchange structure through second outlet 244 via end cooling channels 245. The second liquid inlet pipe 243 and the second liquid outlet pipe 243 in the multi-channel heat exchange structure are alternately arranged, so that uniform heat exchange at the end part of the anode is realized.

Various other modifications and changes may be made by those skilled in the art based on the above-described technical solutions and concepts, and all such modifications and changes should fall within the scope of the claims of the present invention.