CN107795446B - Cooling device and cooling method for electrode for high-power electric propeller - Google Patents
Cooling device and cooling method for electrode for high-power electric propeller Download PDFInfo
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- CN107795446B CN107795446B CN201710860539.8A CN201710860539A CN107795446B CN 107795446 B CN107795446 B CN 107795446B CN 201710860539 A CN201710860539 A CN 201710860539A CN 107795446 B CN107795446 B CN 107795446B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H1/00—Using plasma to produce a reactive propulsive thrust
- F03H1/0081—Electromagnetic plasma thrusters
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H1/00—Using plasma to produce a reactive propulsive thrust
- F03H1/0006—Details applicable to different types of plasma thrusters
- F03H1/0031—Thermal management, heating or cooling parts of the thruster
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
- F25B—REFRIGERATION MACHINES, PLANTS OR SYSTEMS; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS
- F25B1/00—Compression machines, plants or systems with non-reversible cycle
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
- F25B—REFRIGERATION MACHINES, PLANTS OR SYSTEMS; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS
- F25B41/00—Fluid-circulation arrangements
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- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K7/00—Constructional details common to different types of electric apparatus
- H05K7/20—Modifications to facilitate cooling, ventilating, or heating
- H05K7/2029—Modifications to facilitate cooling, ventilating, or heating using a liquid coolant with phase change in electronic enclosures
Abstract
A cooling device and a cooling method of an electrode for a high-power electric propeller are disclosed, wherein the device comprises a refrigerating part, a medium circulating part and a control part; the control part adjusts and controls the refrigerating part according to the difference value between the sensed temperature and the set temperature, and the medium circulating part cools the electrode. The electrode cooling device changes a space inertia cooling mode, is combined with the high-power electric propeller and is installed, and a low-temperature coolant circulation active cooling mode is utilized, so that the problem of fusing of the original electrode caused by overhigh working temperature is solved, the working temperature of the electrode of the high-power electric propeller is effectively reduced, the service life of the electrode is effectively prolonged, the working life of the electric propeller is indirectly prolonged, and the use cost of the electric propeller is reduced.
Description
Technical Field
The invention relates to an electrode cooling method, in particular to an electrode cooling method for an electric thruster.
Background
Magnetic plasma is a physical state in which neutral gas molecules form a plasma state under external discharge conditions and form under the action of an additional electromagnetic field. At present, thrusters used for a large space aircraft platform are all low-power types, and attitude maneuver and orbital transfer of the large space aircraft platform (such as a space station) are difficult to realize by low-power electric thrusters, so that a high-power electric thruster represented by a magnetic plasma electric thruster is the first choice of a future deep space exploration aircraft propulsion system, and the propulsion performance of high thrust and high specific impulse is easier to realize on the basis of meeting the external high-power supply condition. The high-power electric propeller can ionize the propellant through large-current discharge between electrodes in the working process, so that required ions are generated, and the ions are sprayed out under the action of an additional electromagnetic field to generate required thrust. The high-power electric thruster mostly realizes propellant ionization through electrode discharge, the working life of the electric thruster mainly depends on the life of an electrode, and under the high-power condition, the main factors influencing the life of the electrode are high temperature generated by discharge and the ablation effect of ion motion on the electrode. During the discharge process, a large amount of heat will be generated, which is mainly concentrated at the position of the discharge electrode and can seriously affect the working life of the electrode.
The electric propulsion device applied to the space at present is a low-power type, the heat generated by the electric propulsion device can meet the requirement only through traditional radiation heat dissipation, but after the power of the electric propulsion device is increased, the traditional air cooling, air cooling and radiation heat dissipation can not meet the high-temperature cooling requirement generated at the electrode of the high-power electric propulsion device, and if an effective electrode cooling device is lacked, the electrode is fused and ablated at high temperature, and the electrode can be replaced almost impossible in the space environment, so that a new effective cooling device is needed to be adopted to solve the problem.
The prior technical scheme is mainly designed aiming at the ablation effect of ion motion on an electrode, the motion characteristic of ions is obtained through the test and calculation of the motion state of the ions, the research on the electrode structure, the electromagnetic field configuration and the magnetic field strength is developed on the basis, and aiming at the problem of influence of high temperature on the service life of the electrode, an inertial radiation heat dissipation mode is mainly adopted at the present stage, the effect of the passive heat dissipation mode in a vacuum environment is not obvious, the service life of the electrode of the high-power electric propeller is severely limited, and a cooling device special for the electrode is not provided for a long time.
Disclosure of Invention
In view of the above analysis, the invention provides a method for cooling an electrode of a high-power electric propeller and a cooling device for implementing the method, aiming at the problem that the service life of the electrode of the high-power electric propeller is influenced by the working temperature.
The purpose of the invention is mainly realized by the following technical scheme:
a cooling method of electrode for high-power electric propeller is applied to magnetic plasma high-power electric propeller of deep space exploration aircraft propulsion system, and two groups of cooling devices are used for separately cooling cathode and anode; in the cooling process, the difference value between the temperature of the coolant in the cooling device and the preset temperature is compared with the preset temperature difference for judgment, the rotating speed of the cooling device is controlled and adjusted according to the judgment result, the dynamic balance of the electrode temperature is kept, the anode is of a hollow structure, a coolant circulation channel which is attached to the anode in shape is arranged in the anode, the cathode comprises a cathode cooling heat conduction block with a hollow structure, and the outer wall of the cathode cooling heat conduction block is tightly contacted with the cathode.
The anode is designed into a hollow structure, a coolant circulation channel which is consistent with the anode structure and is attached to the anode structure as far as possible is arranged in the anode, so that the coolant can conveniently circulate from the inside of the anode, the area of the coolant circulation channel attached to the anode is increased, the cooling effect is maximized, the purpose of directly performing heat exchange with the anode structure body is realized, and the cooling effect on the anode is achieved.
Further, in the refrigerant cycle circuit: the low-temperature low-pressure refrigerant is changed into a high-temperature high-pressure refrigerant under the action of the compressor, the high-temperature high-pressure refrigerant is cooled by the fan and the condenser, and the cooled refrigerant enters the titanium tube type heat exchanger to cool the coolant;
in the coolant circulation circuit: the coolant in the coolant storage tank enters the titanium tube heat exchanger through the titanium tube heat exchange medium pump, is cooled through heat exchange with the refrigerant, and the cooled refrigerant flows back to the coolant storage tank.
Further, when the coolant is cooling oil, the coolant in the coolant storage tank enters the coolant flow passage of the anode through the cooling pump or the cathode is cooled and conducted heat quickly, the electrode is cooled through heat exchange with the electrode, and the cooled coolant flows back into the coolant storage tank and exchanges heat with the coolant again in the coolant circulation loop.
Further, when the coolant is cooling water, the device further comprises a water treatment device and an ion exchange resin water supply pump, wherein the coolant storage tank, the ion exchange resin water supply pump, the water treatment device, the cooling pump and the electrodes are sequentially connected to form an electrode cooling loop;
the coolant in the coolant storage tank enters the water treatment equipment through the ion exchange resin water supply pump to be deionized and processed into deionized water, the deionized water enters the anode coolant circulation channel through the cooling pump or the cathode cooling heat conduction speed, the electrode is cooled through heat exchange with the electrode, the cooled coolant flows back to the coolant storage tank, and heat exchange is carried out with the refrigerant in the coolant circulation loop again.
The coolant adopts liquid water, the ion exchange resin water supply pump conveys the cooling water in the coolant storage tank to the water treatment equipment, and the water treatment equipment carries out deionization treatment on the cooling water, thereby achieving the purpose of insulation.
Furthermore, the device also comprises a control cabinet which is respectively connected with the temperature sensor, the compressor, the fan and the condenser in the coolant storage tank; the control part senses the temperature of the returned coolant in the electrode cooling loop through a temperature sensor in the coolant storage tank, and the control cabinet judges the difference value between the temperature and the preset temperature; when the difference value is larger than the preset temperature difference, the control part controls the compressor, the fan and the condenser to increase the rotating speed and accelerate the heat exchange speed; when the difference is smaller than the preset temperature difference, the control part controls the compressor, the fan and the condenser to reduce the rotating speed, the heat exchange speed is reduced, and the dynamic balance of the electrode temperature is kept.
The temperature sensor in the coolant storage tank senses the temperature of the returned coolant, and the control cabinet can adjust and control the motion state of each component of the cooling device according to the difference between the sensed temperature and the set temperature, so that the purpose of cooling the electrode is achieved.
The invention also provides a cooling device of the cooling method of the electrode for the high-power electric propeller, which comprises the following steps: compressor, fan and condenser, titanium tubular heat exchanger, cooling pump, titanium tubular heat transfer medium pump and coolant storage case, wherein: the compressor, the fan, the condenser and the titanium tube type heat exchanger form a refrigerant circulation loop; the titanium tube type heat exchange medium pump, the coolant storage tank and the titanium tube type heat exchanger form a coolant circulation loop; the coolant storage tank, the cooling pump, and the electrode form an electrode cooling circuit.
Further, the cooling device is divided into two groups, one group cools the anode separately, the other group cools the cathode separately, the anode is arranged at a position close to the outside of the propeller, and the cathode is arranged at a position close to the inside of the propeller.
Further, the anode has a hollow structure, and a coolant flow passage conforming to the shape of the anode is provided inside the anode.
Furthermore, the cathode comprises a cathode cooling heat-conducting block with a hollow structure, the outer wall of the cathode cooling heat-conducting block is in close contact with the cathode, and the cathode cooling heat-conducting block is made of red copper.
The cathode cooling heat-conducting block is made of red copper, has better heat conductivity, is in close contact with the cathode, is of an internal hollow structure, and is convenient for the circulation of coolant, so that the heat exchange area is increased to the maximum extent, and the cooling effect on the cathode is achieved.
Further, the condenser is in the form of red copper pipe sleeve aluminum fins.
The condenser is in a high-efficiency red copper pipe sleeve aluminum fin heat dissipation mode, and provides safe and reliable cooling guarantee for cooling high-temperature and high-pressure refrigerant gas. The red copper pipe is matched with an aluminum fin, and a steel plate is used on the surface. The hot refrigerant flows through the copper pipe, so that the aluminum fins generate heat and radiate the heat, and the purpose of large-area heat radiation is achieved.
Further, the control part is a control cabinet, and the control cabinet is respectively connected with the temperature sensor, the compressor, the fan and the condenser in the coolant storage tank and controls the working states of the compressor, the fan and the condenser. The control part senses the temperature of the returned coolant in the electrode cooling loop through a temperature sensor in the coolant storage tank, and the control cabinet judges the difference value between the temperature and the preset temperature; when the difference value is larger than the preset temperature difference, the control part controls the compressor, the fan and the condenser to increase the rotating speed and accelerate the heat exchange speed; when the difference is smaller than the preset temperature difference, the control part controls the compressor, the fan and the condenser to reduce the rotating speed, the heat exchange speed is reduced, and the electrode temperature is kept in dynamic balance.
The invention has the following beneficial effects:
the invention is mainly applied to high-power electric propellers, is suitable for attitude maneuver and orbital transfer of a large space aircraft platform, and is difficult to realize by low-power electric propellers. For a high-power electric propeller, due to environmental limitation, the traditional air cooling cannot be applied, the air cooling and radiation heat dissipation cannot meet the high-temperature cooling requirement generated at an electrode, in addition, the electrode is hardly replaced in a space environment, and active cooling protection measures for the electrode are lacked in the working process of the high-power electric propeller at present, so the invention provides the electrode cooling device and the cooling method for the high-power electric propeller. The electrode cooling device is added to change a space inertia cooling mode, an active cooling mode is adopted to replace a traditional passive heat dissipation mode, the cooling device is combined with the electrode of the high-power electric propeller, and a low-temperature coolant circulation active cooling mode is utilized, so that the problem of fusing of the original electrode caused by overhigh working temperature is solved, and the working temperature of the electrode of the high-power electric propeller is effectively reduced.
Because the structures and the installation modes of the cathode and the anode are different in the high-power electric propeller, the invention adopts two sets of cooling devices to respectively cool the cathode and the anode, thereby improving the cooling effect, and simultaneously, the invention respectively sets different cooling modes for the cathode and the anode. The anode is designed into an anode with a hollow structure, a coolant flow channel which is consistent with the anode structure and is attached to the anode structure as far as possible is arranged in the anode, the area of the coolant flow channel attached to the anode is increased, and the cooling effect is maximized. The cathode cooling heat conduction block is arranged on the cathode for cathode cooling, so that the cooling rate is increased, and the cooling effect is optimal.
After the active cooling mode of the invention is adopted, the cooling time can be shortened by 50 percent under the condition of reaching the same cooling effect, the service life of the electrode can be prolonged to more than three times of that of the traditional passive cooling mode, the service life of the electrode is effectively prolonged, the working life of the electric propeller is indirectly prolonged, and the use cost of the electric propeller is reduced.
Additional features and advantages of the invention will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by the practice of the invention. The objectives and other advantages of the invention will be realized and attained by the structure particularly pointed out in the written description and claims hereof as well as the appended drawings.
Drawings
The drawings are only for purposes of illustrating particular embodiments and are not to be construed as limiting the invention, wherein like reference numerals are used to designate like parts throughout.
FIG. 1 is a schematic diagram showing the constitution of an anode cooling apparatus in example 1.
FIG. 2 is a schematic diagram showing the constitution of the cathode cooling device in example 1.
Detailed Description
The present invention is further described in the following description in conjunction with the following drawings, which form a part hereof, and which together with the embodiments of the invention serve to explain the principles of the invention.
The invention is mainly applied to high-power electric propellers, is suitable for attitude maneuver and orbital transfer of a large space aircraft platform, and is difficult to realize by low-power electric propellers. The active cooling mode suitable for the vacuum environment such as water cooling or oil cooling is adopted, so that the temperature of the electrode can be effectively reduced, and the service life of the electrode is prolonged.
Example 1
The coolant in this embodiment is liquid water.
An electrode cooling device for a high-power electric propeller, comprising: the device comprises a compressor, a fan, a condenser, a titanium tube type heat exchanger, a cooling pump, a titanium tube type heat exchange medium pump, an ion exchange resin water supply pump, water treatment equipment, a coolant storage tank, a control cabinet, a cathode cooling heat conduction block, a cathode and an anode.
The outlet of the compressor is connected with the inlet of the fan, the outlet of the fan is connected with the inlet of the condenser, the outlet of the condenser is connected with the inlet of the first channel in the titanium tube heat exchanger, and the outlet of the first channel in the titanium tube heat exchanger is connected with the inlet of the compressor, so that a circulation loop of the refrigerant is formed. One end of the titanium tube type heat exchange medium pump is connected with the coolant storage tank, the other end of the titanium tube type heat exchange medium pump is connected with an inlet of the second channel in the titanium tube type heat exchanger, and an outlet of the second channel in the titanium tube type heat exchanger is connected with the coolant storage tank through a conveying pipeline, so that a coolant circulation loop is formed. The inlet end of the ion exchange resin water supply pump is connected with the coolant storage tank, the outlet end of the ion exchange resin water supply pump is connected with the inlet end of the water treatment equipment, the inlet end of the cooling pump is connected with the outlet end of the water treatment equipment, the outlet end of the cooling pump is connected with an electrode to be cooled, and the electrode coolant outlet is connected with the coolant storage tank to form an electrode cooling loop. In the cathode cooling loop, the outlet end of the cooling pump is connected with the inlet end of the cathode cooling heat-conducting block, and the outlet end of the cathode cooling heat-conducting block is connected with the coolant storage tank through a conveying pipeline; in the anode cooling loop, the anode is designed into a hollow structure, a coolant flow channel consistent with the anode structure is arranged in the anode cooling loop, the coolant flow channel is attached to the anode structure as far as possible, so that the area of the coolant flow channel attached to the anode can be maximized, the cooling effect is maximized, the anode in the embodiment is an expansion type annular structure with a narrow lower part and a wide upper part, the opening angle of the expansion type annular structure is 30 degrees, the anode is made of metal molybdenum, the anode designed in the manner can enable the propellant injection efficiency to be highest and has the high-temperature resistance characteristic, therefore, in the embodiment, the shape of the coolant flow channel in the anode is also an annular structure with a narrow lower part and a wide upper part, the anode is in a ring anode structure, and the shape of the anode is attached as far as possible. The outlet end of the cooling pump is connected with the inlet end of the anode coolant, and the outlet end of the anode coolant is connected with the coolant storage tank through a conveying pipeline. The different reasons for the arrangement of the cathode and the anode structure are that the anode is arranged at the position of the propeller close to the outside, and the anode is of a hollow structure, so that the volume of the anode can be reduced, the space is saved, and the assembling of the propeller is facilitated; the negative pole is close to the position of the inside at the propeller, the volume of negative pole itself is great, and the inside restriction that has space again of propeller, consequently set hollow structure to the negative pole, the volume of negative pole can be very big, inconvenient processing also makes things convenient for the equipment of propeller, consequently when for the negative pole cooling, the setting has hollow structure's negative pole cooling heat conduction piece for the negative pole cooling, red copper is chooseed for use to negative pole cooling piece material, the design is two annular channel structure, central passage is used for the propellant to flow in the negative pole, outer loop channel is used for the circulation and the circulation of coolant. The control cabinet is connected with the coolant storage tank sensor, the compressor, the fan and the condenser through signal lines respectively.
The working process of the device is as follows:
the low-temperature low-pressure refrigerant is changed into a high-temperature high-pressure refrigerant under the action of the compressor, and the high-temperature high-pressure refrigerant is cooled by the fan and the condenser; the coolant in the coolant storage tank completes the circulation in the coolant circulation loop through a titanium tube type heat exchange medium pump; the refrigerant and the coolant complete heat exchange in the titanium tube heat exchanger. Meanwhile, the ion exchange resin water supply pump conveys the cooling water to water treatment equipment (deionized water treatment equipment in the embodiment) to enable the cooling water to become deionized water, the deionized water is conveyed to a cooling channel corresponding to the electrode through the cooling pump to be subjected to heat exchange treatment, and after the heat exchange is finished, the deionized water flows back to the coolant storage tank to be subjected to another heat exchange with the refrigerant.
The compressor is used for compressing low-temperature low-pressure refrigerant gas to form high-temperature high-pressure refrigerant gas, and the refrigerant is Freon. The fan is used for accelerating high-temperature and high-pressure refrigerant gas, the working efficiency of the compressor can be improved, and the high-power axial flow fan is selected as the fan. The condenser is in a high-efficiency red copper pipe sleeve aluminum fin heat dissipation mode, and provides safe and reliable cooling guarantee for cooling high-temperature and high-pressure refrigerant gas. The titanium tube type heat exchanger is a place for heat exchange between a refrigerant and a coolant, two pipelines are arranged in the titanium tube type heat exchanger and are connected by a heat conducting plate, one pipeline is used for circulation of the refrigerant, and the other pipeline is used for circulation of the coolant. The titanium tubular heat exchange medium pump is used for conveying the coolant in the coolant storage tank to the titanium tubular heat exchanger, the coolant and a Freon refrigerant are subjected to heat exchange in the titanium tubular heat exchanger, the cooled coolant flows back to the coolant storage tank through a pipeline to be stored, and the titanium tubular heat exchange medium pump can stir the coolant in the coolant storage tank at the same time, so that the temperature of the coolant is uniform. The coolant adopts liquid water, the ion exchange resin water supply pump conveys the cooling water in the coolant storage tank to the water treatment equipment, and the water treatment equipment carries out deionization treatment on the cooling water, thereby achieving the purpose of insulation. The cooling pump can convey the treated deionized cooling water to the electrode, so that the cooling water exchanges heat with the electrode and then flows back to the coolant storage tank through a pipeline, and the circulation movement is carried out. The cathode cooling heat-conducting block is made of red copper, has better heat conductivity, is in close contact with the cathode and is of an internal hollow structure, so that the circulation of a coolant is facilitated, the heat exchange area is increased to the maximum extent, and the cooling effect on the cathode is achieved; the anode is designed into a hollow structure, so that the coolant can conveniently circulate from the inside of the anode, the purpose of directly exchanging heat with the anode structure body is realized, and the cooling effect on the anode is achieved. The control cabinet can adjust and control the motion state of each component of the cooling device according to the difference value between the sensed temperature and the set temperature, and when the difference value is greater than the preset temperature difference value, the control part controls the compressor, the fan and the condenser to increase the rotating speed, so that the heat exchange speed is increased and the high-efficiency cooling is kept; when the difference is less than the preset temperature difference, the control part controls the compressor, the fan and the condenser to reduce the rotating speed, slow down the heat exchange speed, maintain the proper temperature required by the electrode work, ensure that the electrode temperature can keep a dynamic balance, and achieve the purpose of cooling the electrode, wherein the preset temperature difference in the embodiment is 300 ℃.
Example 2
The cooling water in the invention can also be replaced by cooling oil, if the cooling oil is adopted, the device does not adopt water treatment equipment and an ion exchange resin water supply pump, and other devices are the same.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention.
Claims (1)
1. A cooling method of an electrode for a high-power electric propeller is characterized in that the cooling method is applied to a magnetic plasma high-power electric propeller of a deep space exploration aircraft propulsion system, and two groups of cooling devices are used for separately cooling a cathode and an anode; in the cooling process, the difference value between the temperature of the coolant in the cooling device and the preset temperature is compared and judged with the preset temperature difference, the rotating speed of the cooling device is controlled and adjusted according to the judgment result, the dynamic balance of the electrode temperature is kept, the anode is of an expansion type annular structure with a narrow lower part and a wide upper part, and the opening angle is 30 degrees; the anode is of a hollow structure, a coolant flow channel which is attached to the anode in shape is arranged in the anode, and the coolant flow channel is of an annular structure with a narrow lower part and a wide upper part; the cathode comprises a cathode cooling heat-conducting block with a hollow structure, and the outer wall of the cathode cooling heat-conducting block is in close contact with the cathode; the cathode cooling block is made of red copper and is designed into a double-ring channel structure, a central channel is used for enabling a propellant to flow into the cathode, and an outer ring channel is used for circulating and circulating a coolant;
in the refrigerant circulation circuit: the low-temperature low-pressure refrigerant is changed into a high-temperature high-pressure refrigerant under the action of the compressor, the high-temperature high-pressure refrigerant is cooled by the fan and the condenser, and the cooled refrigerant enters the titanium tube type heat exchanger to cool the coolant;
in the coolant circulation circuit: the coolant in the coolant storage tank enters the titanium tube heat exchanger through the titanium tube heat exchange medium pump, is cooled through heat exchange with the refrigerant, and the cooled refrigerant flows back to the coolant storage tank;
the cooling method adopts a control cabinet to realize temperature control, and the control cabinet is respectively connected with a temperature sensor, a compressor, a fan and a condenser in a coolant storage tank; the control cabinet senses the temperature of the returned coolant in the electrode cooling loop through a temperature sensor in the coolant storage tank, and judges the difference value between the temperature and the preset temperature; when the difference value is larger than the preset temperature difference, the control cabinet controls the compressor, the fan and the condenser to increase the rotating speed and accelerate the heat exchange speed; when the difference value is smaller than the preset temperature difference, the control cabinet controls the compressor, the fan and the condenser to reduce the rotating speed, slow down the heat exchange speed and keep the dynamic balance of the electrode temperature;
when the coolant is cooling oil, the coolant in the coolant storage tank enters a coolant circulation passage of the anode through a cooling pump or the cathode is cooled and conducted quickly, the electrode is cooled through heat exchange with the electrode, the cooled coolant flows back to the coolant storage tank, and heat exchange is carried out with the refrigerant in the coolant circulation loop again;
when the coolant is cooling water, the device also comprises a water treatment device and an ion exchange resin water supply pump, wherein the coolant storage tank, the ion exchange resin water supply pump, the water treatment device, the cooling pump and the electrode are sequentially connected to form an electrode cooling loop;
the coolant in the coolant storage tank enters water treatment equipment through the ion exchange resin water supply pump to be deionized and converted into deionized water, the deionized water enters a coolant flow passage of the anode through the cooling pump or the cathode is cooled and conducts heat quickly, the electrode is cooled through heat exchange with the electrode, the cooled coolant flows back to the coolant storage tank, and heat exchange is carried out with the refrigerant in the coolant circulation loop again;
the cooling device of the cooling method of the electrode for the high-power electric propeller comprises the following steps: compressor, fan and condenser, titanium tubular heat exchanger, cooling pump, titanium tubular heat transfer medium pump and coolant storage case, wherein: the compressor, the fan, the condenser and the titanium tube type heat exchanger form a refrigerant circulation loop; the titanium tube type heat exchange medium pump, the coolant storage tank and the titanium tube type heat exchanger form a coolant circulation loop; the coolant storage tank, the cooling pump and the electrode form an electrode cooling circuit;
the cooling devices are arranged in two groups separately, one group cools the anode separately, the other group cools the cathode separately, the anode is arranged at the position close to the outside of the propeller, and the cathode is arranged at the position close to the inside of the propeller;
the anode is of a hollow structure, and a coolant flow channel which is attached to the anode in shape is arranged in the anode;
the cathode comprises a cathode cooling heat-conducting block with a hollow structure, the outer wall of the cathode cooling heat-conducting block is in close contact with the cathode, and the cathode cooling heat-conducting block is made of red copper;
the condenser is in a form of red copper pipe sleeve aluminum fins.
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| EP3988784A1 (en) * | 2020-10-22 | 2022-04-27 | Cryogenic And Vacuum Systems, Sia | Electric rocket engine cooling system |
| CN114017275B (en) * | 2021-11-29 | 2022-05-17 | 中国科学院合肥物质科学研究院 | Superconducting magnetic plasma propeller heat pipe cooling structure |
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| GB897577A (en) * | 1959-07-15 | 1962-05-30 | Bristol Siddeley Engines Ltd | Improvements in or relating to apparatus for producing a jet consisting of a plasma of ions and electrons |
| DE3931740A1 (en) * | 1988-02-10 | 1991-04-04 | Olin Corp | ARC RAY DRIVER WITH IMPROVED LIFETIME |
| DE102007044074B4 (en) * | 2007-09-14 | 2011-05-26 | Thales Electron Devices Gmbh | Electrostatic ion accelerator arrangement |
| FR2950114B1 (en) * | 2009-09-17 | 2012-07-06 | Snecma | HALL EFFECT ENGINE WITH COOLING OF THE INTERNAL CERAMIC |
| UA101678C2 (en) * | 2011-04-08 | 2013-04-25 | Национальный Научный Центр "Харьковский Физико-Технический Институт" | Vacuum arc evaporator FOR GENERATING cathode plasma |
| CN103790794B (en) * | 2014-03-03 | 2016-06-01 | 哈尔滨工业大学 | Multistage cusped magnetic field plasma thruster heat loss through radiation device |
| US9963249B2 (en) * | 2015-06-29 | 2018-05-08 | The Boeing Company | Efficient stationkeeping design for mixed fuel systems in response to a failure of an electric thruster |
| CN107044396B (en) * | 2017-06-14 | 2019-06-04 | 北京航空航天大学 | A kind of water-cooling structure complementary field magnetic plasma propeller |
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