CN212535956U - Coaxial segmented anode type laser-electromagnetic field coupling thruster and electromagnetic accelerating electrode - Google Patents
Coaxial segmented anode type laser-electromagnetic field coupling thruster and electromagnetic accelerating electrode Download PDFInfo
- Publication number
- CN212535956U CN212535956U CN202021157097.4U CN202021157097U CN212535956U CN 212535956 U CN212535956 U CN 212535956U CN 202021157097 U CN202021157097 U CN 202021157097U CN 212535956 U CN212535956 U CN 212535956U
- Authority
- CN
- China
- Prior art keywords
- electromagnetic
- laser
- anode
- accelerating
- cathode
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Landscapes
- Plasma Technology (AREA)
Abstract
A coaxial segmented anode type laser-electromagnetic field coupling thruster and an electromagnetic accelerating electrode comprise a laser system, an electromagnetic accelerating electrode, a magnetic field coil and a solid working medium, wherein the electromagnetic accelerating electrode is a coaxial electromagnetic accelerating electrode which comprises an electromagnetic accelerating anode and an electromagnetic accelerating cathode, the electromagnetic accelerating anode is integrally cylindrical, the electromagnetic accelerating anode consists of a front-section anode cylinder, an insulating ceramic ring and a rear-section anode cylinder, and the insulating ceramic ring is arranged between the front-section anode cylinder and the rear-section anode cylinder; the electromagnetic accelerating cathode is arranged in the electromagnetic accelerating anode and the electromagnetic accelerating anode are coaxially arranged; the magnetic field coil is coated on the outer wall of the electromagnetic accelerating anode, and an external magnetic field is generated between the electromagnetic accelerating anode and the electromagnetic accelerating cathode. The arrangement of the insulating ceramic ring can enhance the current density of the discharge arc, thereby enhancing the ionization rate of the laser plasma and further improving the working medium utilization rate and the thrust of the thruster.
Description
Technical Field
The utility model relates to a for the novel thrustor that provides accurate thrust such as microsatellite orbit promotion, position hold, attitude control and network deployment flight, especially relate to an utilize laser ablation solid working medium to produce laser ablation plasma, then utilize the thrustor of electromagnetic field acceleration.
Background
The microsatellite has the advantages of small volume, light weight, low cost, high functional density, short development period, flexible emission, faster networking, strong viability and the like, and plays an important role in the fields of communication, navigation, reconnaissance, environmental monitoring and forecasting, emergency rescue, surveying and mapping, scientific research and the like. The micro satellite is composed of two parts, namely an effective load and a satellite platform, and the propulsion system is used as an important component of the satellite platform and can provide services such as attitude control, orbit maintenance, orbit maneuvering and position maintenance for the satellite, so that the satellite can complete more and more complex tasks and the service life of the satellite is prolonged. Therefore, the development of space propulsion systems with advanced performance is of paramount importance.
However, the traditional chemical propulsion has the problems of low specific impulse, heavy mass, low control precision and the like, so that people urgently need to find a novel small-thrust non-chemical propulsion system to meet the requirement of microsatellites on thrusters. The electric propulsion system is favored by the aerospace industry because of its characteristics of high specific impulse, low thrust, light weight, small volume, low working medium consumption, etc.
The solid ablation type pulse Plasma Thruster (APPT) has the advantages of simple structure, high specific impulse, light weight and the like, and is a preferred object of a microsatellite propulsion system, so that various aerospace major countries carry out long-term intensive research on the Thruster. The working process is as follows: igniting the spark plug to induce short pulse discharge lasting for several milliseconds on the surface of the propellant exposed between the two electrodes, so that the propellant is evaporated and ionized to form plasma; then the plasma is accelerated and sprayed out under the combined action of Lorentz force and aerodynamic force, so that thrust is generated.
The existing solid ablation type pulse plasma thruster has the problems that the diffusion of a discharge arc between electromagnetic accelerating electrodes exists, the current density of the discharge arc is reduced, the ionization rate of laser plasma is influenced, and the working medium utilization rate and the thrust of the thruster are damaged. Therefore, how to effectively prevent the arc diffusion between the electromagnetic accelerating electrodes is a technical problem that needs to be solved by those skilled in the art.
SUMMERY OF THE UTILITY MODEL
Aiming at the problem that the ionization rate of laser plasma is influenced by arc diffusion between electromagnetic accelerating electrodes in the conventional APPT, a coaxial segmented anode type laser-electromagnetic field coupling thruster and an electromagnetic accelerating electrode are provided.
In order to realize the purpose of the utility model, the following technical scheme is adopted to realize:
the coaxial segmented anode type laser-electromagnetic field coupling thruster comprises a laser system, an electromagnetic accelerating electrode, a magnetic field coil and a solid working medium, wherein laser beams emitted by the laser system ablate the solid working medium to generate laser plasma, the laser plasma enters a space between the electromagnetic accelerating cathode and the electromagnetic accelerating anode and is induced to generate short pulse discharge arcs, the short pulse discharge arcs enable the laser plasma to be heated and further ionized, and the plasma is accelerated and ejected under the combined action of Lorentz force and aerodynamic force, so that thrust is generated. The utility model discloses a create the part and lie in: the electromagnetic accelerating electrode is a coaxial electromagnetic accelerating electrode, the coaxial electromagnetic accelerating electrode comprises an electromagnetic accelerating anode and an electromagnetic accelerating cathode, the electromagnetic accelerating anode is integrally cylindrical, the electromagnetic accelerating anode consists of a front-section anode cylinder, an insulating ceramic ring and a rear-section anode cylinder, and the insulating ceramic ring is arranged between the front-section anode cylinder and the rear-section anode cylinder; the electromagnetic accelerating cathode is arranged in the electromagnetic accelerating anode and the electromagnetic accelerating anode are coaxially arranged; the magnetic field coil is coated on the outer wall of the electromagnetic accelerating anode, and an external magnetic field is generated between the electromagnetic accelerating anode and the electromagnetic accelerating cathode.
The utility model discloses well insulating ceramic ring's effect prevents the electric arc diffusion, can strengthen the current density of electric arc that discharges to strengthen laser plasma's ionization rate, and then further improve the working medium utilization ratio and the thrust of thrustor.
The front section anode cylinder and the rear section anode cylinder of the electromagnetic accelerating anode are made of metal with ablation resistance and good electric conductivity. The electromagnetic accelerating anode is cylindrical as a whole. The electromagnetic accelerating cathode is made of metal with ablation resistance and good electric conductivity. The electromagnetic accelerating anode and the electromagnetic accelerating cathode are connected with an electromagnetic accelerating electrode power supply to obtain a working power supply, and the magnetic field coil is connected with a magnetic field coil power supply to obtain the working power supply.
As a preferred scheme of the utility model, the one end opening of electrode is accelerated to the electromagnetism, and the other end of electrode is accelerated to the electromagnetism is sealed by the division board, sets up the mounting hole of fixed electromagnetism negative pole with higher speed on the division board, and the electromagnetism negative pole is solid cylindrical structure with higher speed, and the electromagnetism is fixed on the division board with higher speed the one end of negative pole, and the other end stretches into in the electromagnetism positive pole with higher speed. A plurality of through holes are uniformly formed in a separating plate between the electromagnetic accelerating anode and the electromagnetic accelerating cathode and on a circumference which takes the center of the electromagnetic accelerating cathode on the separating plate as the center of a circle, each through hole is respectively communicated with a ceramic tube, the other end of each ceramic tube is far away from the electromagnetic accelerating electrode and extends outwards, and a solid working medium is arranged at the port of each ceramic tube; laser beams emitted by a laser system ablate solid working media on the outer port of the ceramic tube to generate laser plasma, the laser plasma sequentially passes through holes on the ceramic tube and the isolation plate and then enters between the electromagnetic acceleration cathode and the electromagnetic acceleration anode to induce short pulse discharge arcs, the short pulse discharge arcs enable the laser plasma to be heated and further ionized, and the plasma is accelerated and sprayed out under the combined action of Lorentz force and aerodynamic force, so that thrust is generated.
The method is divided into a reflection type mode and a transmission type mode according to the fact that whether the incident direction of a laser beam is the same as the moving direction of laser plasma generated by ablating a solid working medium by the laser beam.
A reflection type: the laser system is arranged at the outer side of one end of the opening of the electromagnetic accelerating electrode, and laser beams emitted by the laser system are incident from one end of the opening of the electromagnetic accelerating electrode, penetrate through a through hole in the isolating plate and the ceramic tube communicated with the through hole, and ablate solid working media on the outer port of the ceramic tube.
A transmission type: the outer side surface of the solid working medium is pasted with a transparent substrate layer, the laser system is arranged on the outer side of the solid working medium, a laser beam emitted by the laser system is incident on the transparent substrate layer, and the laser beam ablates the solid working medium after penetrating through the transparent substrate layer to generate laser plasma.
As another technical solution of the present invention, the present invention also belongs to a reflective asymmetric laser-electromagnetic field coupling thruster based on a coaxial polar plate, and the difference is: the electromagnetic accelerating cathode is of a hollow cylinder structure, a hollow ceramic tube is coaxially sleeved in an inner cavity of the electromagnetic accelerating cathode, and a cylindrical solid working medium is coaxially sleeved in the hollow ceramic tube. The laser system is arranged on the outer side of one end of the opening of the electromagnetic accelerating electrode, laser beams emitted by the laser system are incident from one end of the opening of the electromagnetic accelerating electrode to ablate solid working media in the ceramic tube to generate laser plasma, the laser plasma enters the space between the electromagnetic accelerating cathode and the electromagnetic accelerating anode and induces to generate short pulse discharge arcs, the short pulse discharge arcs enable the laser plasma to be heated and further ionized, and the plasma is accelerated and ejected under the combined action of Lorentz force and aerodynamic force, so that thrust is generated.
No matter be reflective or transmission-type asymmetric laser-electromagnetic field coupling thrustor based on coaxial polar plate, solid working medium all is connected with solid working medium feeding device, and solid working medium feeding device provides solid working medium for the thrustor to update ablation position, guarantee to have comparatively the same ablation condition under the same laser ablation condition, thereby ensure comparatively the same ablation result, and then ensure to provide accurate thrust.
Solid working medium can be metal such as copper and aluminium, polymer such as polytetrafluoroethylene and polyvinyl chloride and other can easily save and can be by the solid material of laser ablation production plasma in the space environment, so need propellant storage tank, system such as valve and pipeline as the thrustor that adopts gas, liquid as working medium like, consequently, the thrustor can be very simple and compact.
The utility model discloses in ceramic pipe's effect is with separating one section distance between solid working medium and the electromagnetism accelerating electrode for the thruster during operation, the discharge arc that produces between the electromagnetism accelerating electrode can not ablate solid working medium, thereby ensures that the solid working medium that the thruster consumed at every turn during operation all produces by laser ablation, has consequently avoided the production of hysteresis ablation, and this utilization efficiency and the propulsive efficiency that is favorable to improving solid working medium.
The utility model discloses well division board's effect blocks laser plasma backward flow, avoids causing thrust loss. Because the discharge arc is generated near the separation plate when the thruster works, the separation plate must have the characteristic of high-temperature ablation resistance so as to ensure that the solid working medium consumed by the thruster during each work is generated by laser ablation. Meanwhile, the isolation plate is made of insulating materials, so that the electromagnetic acceleration anode and the electromagnetic acceleration cathode can be prevented from being conducted. Therefore, the insulation board needs to be made of an insulating material resistant to high temperature ablation, such as ceramic, high silica glass fiber, etc.
The utility model provides a laser system includes laser instrument and beam governing system. The laser is used for outputting pulse laser to the thruster, and laser parameters (such as laser energy, pulse width, wavelength, working frequency and the like) output by the laser can be adjusted through the control system, so that the propelling performance is controlled, and different task requirements are met. The beam adjusting system is positioned a short distance right in front of the laser and is used for focusing laser emitted by the laser according to requirements to ablate the solid working medium. For the reflective thruster, the laser system of the reflective thruster also comprises a plume protection device which is positioned right in front of the light beam regulation system and the laser and is used for blocking the plume generated by the thruster and preventing the light beam regulation system and the laser from being polluted by particles, gas, plasma and the like in the plume so as to influence the working state of the light beam regulation system and the laser.
The utility model discloses still include control system and power processing system. The control system is connected with the power supply processing system, the laser and the light beam adjusting system, and adjusts the output voltage and the laser parameters of each power consumption component and the size and the position of a focused light spot according to the requirements of space tasks, so that the related propulsion performance of the thruster is changed. The power supply processing system is connected with the electromagnetic accelerating electrode power supply and the magnetic field coil power supply and provides required electric energy for each power consumption component according to the instruction of the control system. The electromagnetic acceleration electrode power supply comprises a capacitor charging power supply and a capacitor unit, the capacitor charging power supply is connected with the capacitor unit through a lead and charges the capacitor unit, and the positive end and the negative end of the capacitor unit are respectively connected with the electromagnetic acceleration anode and the electromagnetic acceleration cathode through leads, so that a potential difference exists between the electromagnetic acceleration anode and the electromagnetic acceleration cathode. The control system can control the voltage output by the capacitor charging power supply through controlling the power supply processing system, so that the charging size of the capacitor unit is changed, namely the voltage between the electromagnetic acceleration anode and the electromagnetic acceleration cathode is changed, the discharging current is changed, and the effect of adjusting the propulsion performance is finally achieved. The control system can control the power supply voltage provided by the power supply processing system to the magnetic field coil power supply, and change the voltage output by the magnetic field coil power supply, so that the current of the magnetic field coil is changed, the magnitude of an external magnetic field is changed, and the propulsion performance of the thruster is improved.
The electromagnetic accelerating pole is connected with the capacitor unit and has the functions of: when a certain potential difference exists between the electromagnetic accelerating anode and the electromagnetic accelerating cathode, laser plasma generated by laser ablation can induce discharge when moving to a position between the electromagnetic accelerating anode and the electromagnetic accelerating cathode, and the plasma can be heated and further ionized by joule heat along with the increase of current between the two electrodes. Then, the electromagnetic force (lorentz force) generated by the discharge current and the self-induced magnetic field acts on the plasma, and the plasma beam is discharged, thereby generating thrust. The voltage between the electromagnetic accelerating anode and the electromagnetic accelerating cathode can be controlled by the control system to the power processing system to adjust the voltage output by the capacitor charging power supply, so that the input of discharging energy is changed, the accelerating effect on the plasma is further changed, and the propelling performance of the thruster is finally changed.
The utility model provides an electrode is accelerated to coaxial-type electromagnetism, including electromagnetism positive pole and electromagnetism negative pole with higher speed, the whole tube-shape that is of electromagnetism positive pole with higher speed, the electromagnetism positive pole comprises anterior segment positive pole barrel, insulating ceramic ring and back end positive pole barrel with higher speed, and insulating ceramic ring sets up between anterior segment positive pole barrel and back end positive pole barrel.
Compared with the prior art, the utility model discloses following beneficial technological effect has been produced:
1. the utility model provides a coaxial-type electromagnetism accelerating electrode, its electromagnetism is anodal with higher speed has asymmetric piecemeal positive pole structure, even use insulating ceramic ring to set up between anterior segment positive pole barrel and back end positive pole barrel, utilize ceramic insulating ring to fall into two sections around with the positive pole. The utility model discloses use this kind of coaxial-type electromagnetism accelerating electrode in the thrustor, this is exactly the utility model provides a coaxial segmentation anode type laser-electromagnetic field coupling thrustor. Because the insulating ceramic ring is arranged between the front section anode cylinder and the rear section anode cylinder, the divergence of the main discharge arc is limited, and the discharge arc is concentrated at the ceramic tube outlet at the corner of the anode, so that the current density and the discharge current of the discharge arc at the ceramic tube outlet position (namely the laser plasma outlet position) are improved, the ionization rate of the laser plasma is further increased, and the improvement of thrust and specific impulse is finally realized.
2. Because the ceramic tube avoids the generation of hysteresis ablation, the solid working medium consumed by the thruster during each working is generated by laser ablation, and the quality of the single-ablation solid working medium can be accurately controlled by controlling the laser. Compared with the APPT, the method improves the propelling efficiency and the utilization rate of the solid working medium.
3. Because the short pulse laser is used for ablating the solid working medium to generate plasma, short-time conductive plasma is generated between the electromagnetic accelerating electrodes, and short pulse discharge shorter than that of the traditional PPT is further obtained. Larger currents are expected because shorter pulsed plasma durations are obtained with short pulsed discharge energies. Since the force induced by the thruster depends on the square of the current, it is expected to improve the propulsion performance.
4. Laser ablation can induce a plasma with an initial velocity of many thousands of meters per second, which also improves propulsion performance relative to conventional PPT. In addition, the plasma having the initial velocity is further accelerated by the electromagnetic force formed between the electromagnetic accelerating poles, and the propulsion performance is expected to be greatly improved.
5. Because many solid materials can be used as the working medium, the range of the available solid working medium is enlarged, and systems such as a propellant storage tank, a valve, a pipeline and the like are not needed. Meanwhile, the thruster has fewer movable parts, so that the thruster has a very simple structure, high reliability and high response speed.
6. Because the adjustment of the laser energy and the voltage of each power supply (a capacitor charging power supply and a magnetic field coil power supply) can be realized through the control system, the power consumption, the thrust and the specific impulse adjustability of the thruster are higher.
7. The laser ignition is used for replacing the ignition of the traditional PPT spark plug, and the problems of carbon deposition and ignition failure of the spark plug are solved.
8. The solid working medium is partially ionized during laser ablation and is further ionized during discharge between the electromagnetic accelerating electrodes, so that the thruster can obtain higher ionization rate and the energy conversion efficiency is correspondingly improved.
To sum up, the utility model discloses have simple structure, impel efficient, than towards high, the reliability is high, thrust adjustability is high, the plume pollutes advantages such as little, the working medium selective surface is wide when can effectively restrict the divergence of main discharge arc, is expected to provide accurate thrust for microsatellite's track promotion, position holding, attitude control and network deployment flight etc. provides feasible thrustor for microsatellite's long-time position holding and maneuver flight etc..
Drawings
FIG. 1 is a schematic structural view of example 1;
FIG. 2 is a schematic structural view of example 2;
FIG. 3 is a schematic structural view of embodiment 3.
Reference numbers in the figures:
1. a control system; 2. a power supply processing system; 3. a magnetic field coil power supply; 4. a capacitor unit; 5. a capacitor charging power supply; 6. solid working medium; 7. a solid working medium supply device; 8. a ceramic tube; 9. a separator plate; 10. a magnetic field coil; 11. an electromagnetically accelerated anode; 12. an electromagnetically accelerated cathode; 13. a laser; 14. a beam conditioning system; 15. a plume protection device; 16. a transparent substrate layer; 17. an insulating ceramic ring.
Detailed Description
The technical solution in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the drawings of the embodiments of the present invention, and further detailed description will be made without limiting the scope of the present invention.
Example 1:
the coaxial segmented anode type laser-electromagnetic field coupling thruster shown in fig. 1 will be described first. The device comprises a control system 1, a power supply processing system 2, a magnetic field coil power supply 3, a capacitor unit 4, a capacitor charging power supply 5, a solid working medium 6, a solid working medium supply device 7, a ceramic tube 8, a separation plate 9, a magnetic field coil 10, an electromagnetic acceleration anode 11, an electromagnetic acceleration cathode 12, a laser 13, a light beam adjusting system 14, a plume protection device 15 and an insulating ceramic ring 17.
The electromagnetic accelerating electrode is a coaxial electromagnetic accelerating electrode, the coaxial electromagnetic accelerating electrode comprises an electromagnetic accelerating anode 11 and an electromagnetic accelerating cathode 12, the electromagnetic accelerating anode 11 is integrally cylindrical, and the electromagnetic accelerating anode 11 is composed of a front-section anode cylinder, an insulating ceramic ring 17 and a rear-section anode cylinder. The insulating ceramic ring 17 is arranged between the front section anode cylinder and the rear section anode cylinder, and the three are fixedly connected into a whole, namely the electromagnetic accelerating anode 11. The front section anode cylinder and the rear section anode cylinder of the electromagnetic accelerating anode are made of metal with ablation resistance and good electric conductivity. The electromagnetically accelerated cathode 12 is a solid cylindrical structure made of a metal having ablation resistance and good electrical conductivity. The electromagnetic accelerating cathode 12 is arranged in the electromagnetic accelerating anode 11 and the electromagnetic accelerating anode are coaxially arranged; the magnetic field coil 10 is coated on the outer wall of the electromagnetic accelerating anode 11, and generates an external magnetic field between the electromagnetic accelerating anode 11 and the electromagnetic accelerating cathode 12.
The electromagnetic accelerating anode 11 and the electromagnetic accelerating cathode 12 are connected to an electromagnetic accelerating electrode power supply to obtain an operating power supply, and the magnetic field coil 10 is connected to the magnetic field coil power supply 3 to obtain an operating power supply. In this embodiment, the electromagnetic acceleration electrode power supply includes a capacitor charging power supply 5 and a capacitor unit 4, the capacitor charging power supply 5 is connected to the capacitor unit 4 through a lead and charges the capacitor unit 4, and positive and negative ends of the capacitor unit 4 are respectively connected to the electromagnetic acceleration anode 11 and the electromagnetic acceleration cathode 12 through leads, so that a potential difference exists between the electromagnetic acceleration anode 11 and the electromagnetic acceleration cathode 12.
The control system 1 is connected with the power supply processing system 2, the laser 13 and the light beam adjusting system 14, and adjusts the output voltage and laser parameters of each power consumption component and the size and position of a focused light spot according to the requirements of space tasks, so that the related propulsion performance of the thruster is changed. The power supply processing system 2 is connected with the capacitor charging power supply 5 and the magnetic field coil power supply 3, and provides required electric energy for each power consumption component according to the instruction of the control system 1. The control system 1 can control the voltage output by the capacitor charging power supply 5 through controlling the power supply processing system 2, so that the charging size of the capacitor unit 4 is changed, namely the voltage between the electromagnetic acceleration anode 11 and the electromagnetic acceleration cathode 12 is changed, the discharging current is changed, and the propulsion performance is adjusted. The control system 1 can control the power supply voltage provided by the power supply processing system 2 to the field coil power supply 3, and change the voltage output by the field coil power supply 3, thereby changing the current of the field coil 10, further changing the magnitude of the applied magnetic field, and improving the propulsion performance of the thruster.
The laser 13 outputs pulse laser, the laser 13 is connected with the control system 1, and laser parameters (such as laser energy, pulse width, wavelength, working frequency and the like) output by the laser 13 can be adjusted through the control system 1, so that the propelling performance can be controlled, and different task requirements can be met. The light beam adjusting system 14 is located a short distance right in front of the laser 13, and the light beam adjusting system 14 is connected with the control system 1 and is used for focusing laser emitted by the laser 13 according to the requirements of the control system 1 to ablate the solid working medium. The plume protection device 15 is located right in front of the beam conditioning system 14 and the laser 13, and functions to block the plume generated by the thruster and prevent the beam conditioning system 14 and the laser 13 from being contaminated by particles, gases, plasma, etc. in the plume, thereby affecting the operating state thereof.
One end of the electromagnetic accelerating electrode is opened, the other end of the electromagnetic accelerating electrode is sealed by a partition board 9, a mounting hole for fixing an electromagnetic accelerating cathode 12 is arranged at the center of the partition board 9, one end of the electromagnetic accelerating cathode 12 is fixed on the partition board 9, and the other end of the electromagnetic accelerating cathode extends into an electromagnetic accelerating anode 11. A plurality of through holes are uniformly formed in the partition plate 9 between the electromagnetic accelerating anode 11 and the electromagnetic accelerating cathode 12 and on a circumference which takes the center of the electromagnetic accelerating cathode 1 on the partition plate 9 as the circle center, each through hole is respectively communicated with a ceramic tube 8, the other end of the ceramic tube 8 is far away from the electromagnetic accelerating electrode and extends outwards, and a solid working medium 6 is arranged at the port of the ceramic tube 8. The solid working medium 6 is connected with a solid working medium supply device 7, the solid working medium supply device 7 provides the solid working medium 6 for the thruster so as to update the ablation position, guarantee the same ablation conditions under the same laser ablation conditions, guarantee the same ablation products and further guarantee the provision of accurate thrust.
The laser system is arranged at the outer side of one end of the opening of the electromagnetic accelerating electrode, a laser beam emitted by the laser system enters from one end of the opening of the electromagnetic accelerating electrode, passes through a through hole on the isolating plate 9 and the ceramic tube 8 communicated with the through hole, the solid working medium 6 on the outer port of the ceramic tube 8 is ablated to generate laser plasma, the laser plasma sequentially passes through the ceramic tube 8 and the through hole on the isolating plate 9 and enters between the electromagnetic accelerating anode 11 and the electromagnetic accelerating cathode 12 to be induced to generate short pulse discharge electric arcs, the short pulse discharge electric arcs enable the laser plasma to be heated and further ionized, and the plasma is accelerated and ejected under the combined action of Lorentz force and aerodynamic force, so that thrust is generated.
Example 2:
the coaxial segmented anode type laser-electromagnetic field coupling thruster shown in fig. 2 comprises a control system 1, a power supply processing system 2, a magnetic field coil power supply 3, a capacitor unit 4, a capacitor charging power supply 5, a solid working medium 6, a solid working medium supply device 7, a ceramic tube 8, a separation plate 9, a magnetic field coil 10, an electromagnetic acceleration anode 11, an electromagnetic acceleration cathode 12, a laser 13, a light beam adjusting system 14, a plume protection device 15 and an insulating ceramic ring 17.
The electromagnetic accelerating electrode is a coaxial electromagnetic accelerating electrode, the coaxial electromagnetic accelerating electrode comprises an electromagnetic accelerating anode 11 and an electromagnetic accelerating cathode 12, the electromagnetic accelerating anode 11 is integrally cylindrical, and the electromagnetic accelerating anode 11 is composed of a front-section anode cylinder, an insulating ceramic ring 17 and a rear-section anode cylinder. The insulating ceramic ring 17 is arranged between the front section anode cylinder and the rear section anode cylinder, and the three are fixedly connected into a whole, namely the electromagnetic accelerating anode 11. The front section anode cylinder and the rear section anode cylinder of the electromagnetic accelerating anode are made of metal with ablation resistance and good electric conductivity. The electromagnetically accelerated cathode 12 is a hollow cylindrical structure made of a metal having ablation resistance and good electrical conductivity. The electromagnetic accelerating cathode 12 is arranged in the electromagnetic accelerating anode 11 and the electromagnetic accelerating anode are coaxially arranged; the magnetic field coil 10 is coated on the outer wall of the electromagnetic accelerating anode 11, and generates an external magnetic field between the electromagnetic accelerating anode 11 and the electromagnetic accelerating cathode 12.
The electromagnetic accelerating anode 11 and the electromagnetic accelerating cathode 12 are connected to an electromagnetic accelerating electrode power supply to obtain an operating power supply, and the magnetic field coil 10 is connected to the magnetic field coil power supply 3 to obtain an operating power supply.
One end of the electromagnetic accelerating electrode is opened, the other end of the electromagnetic accelerating electrode is sealed by a partition plate 9, a mounting hole for fixing an electromagnetic accelerating cathode 12 is formed in the partition plate 9, one end of the electromagnetic accelerating cathode 12 is fixed on the partition plate 9, and the other end of the electromagnetic accelerating cathode extends into an electromagnetic accelerating anode 11. A hollow ceramic tube 8 is coaxially sleeved in an inner cavity of the electromagnetic accelerating cathode 12, and a cylindrical solid working medium 6 is coaxially sleeved in the hollow ceramic tube 8. The outer end of the solid working medium 6 is connected with a solid working medium supply device 7, the solid working medium supply device 7 provides the solid working medium 6 for the thruster so as to update the ablation position, guarantee the same ablation conditions under the same laser ablation conditions, guarantee the same ablation products and further guarantee the accurate thrust.
The laser system is arranged on the outer side of one end of the opening of the electromagnetic accelerating electrode, laser beams emitted by the laser system are incident from one end of the opening of the electromagnetic accelerating electrode, solid working media 6 in the ceramic tube 8 are ablated to generate laser plasma, the laser plasma enters between the electromagnetic accelerating anode 11 and the electromagnetic accelerating cathode 12 and is induced to generate short pulse discharge arcs, the short pulse discharge arcs enable the laser plasma to be heated and further ionized, and the plasma is accelerated and ejected under the combined action of Lorentz force and aerodynamic force, so that thrust is generated.
As in example 1, the laser system includes a laser, a beam conditioning system located directly in front of the laser, and a plume protection device located directly in front of the beam conditioning system and the laser. The control system is connected with the power supply processing system, the laser and the light beam adjusting system, and the power supply processing system is connected with the electromagnetic accelerating electrode power supply and the magnetic field coil power supply.
Example 3:
the coaxial segmented anode type laser-electromagnetic field coupling thruster shown in fig. 3 comprises a control system 1, a power supply processing system 2, a magnetic field coil power supply 3, a capacitor unit 4, a capacitor charging power supply 5, a solid working medium 6, a solid working medium supply device 7, a ceramic tube 8, an isolation plate 9, a magnetic field coil 10, an electromagnetic acceleration anode 11, an electromagnetic acceleration cathode 12, a laser 13, a light beam adjusting system 14, a transparent substrate layer 16 and an insulating ceramic ring 17.
The electromagnetic accelerating electrode is a coaxial electromagnetic accelerating electrode, the coaxial electromagnetic accelerating electrode comprises an electromagnetic accelerating anode 11 and an electromagnetic accelerating cathode 12, the electromagnetic accelerating anode 11 is integrally cylindrical, and the electromagnetic accelerating anode 11 is composed of a front-section anode cylinder, an insulating ceramic ring 17 and a rear-section anode cylinder. The insulating ceramic ring 17 is arranged between the front section anode cylinder and the rear section anode cylinder, and the three are fixedly connected into a whole, namely the electromagnetic accelerating anode 11. The front section anode cylinder and the rear section anode cylinder of the electromagnetic accelerating anode are made of metal with ablation resistance and good electric conductivity. The electromagnetically accelerated cathode 12 is a solid cylindrical structure made of a metal having ablation resistance and good electrical conductivity. The electromagnetic accelerating cathode 12 is arranged in the electromagnetic accelerating anode 11 and the electromagnetic accelerating anode are coaxially arranged; the magnetic field coil 10 is coated on the outer wall of the electromagnetic accelerating anode 11, and generates an external magnetic field between the electromagnetic accelerating anode 11 and the electromagnetic accelerating cathode 12.
The electromagnetic accelerating anode 11 and the electromagnetic accelerating cathode 12 are connected to an electromagnetic accelerating electrode power supply to obtain an operating power supply, and the magnetic field coil 10 is connected to the magnetic field coil power supply 3 to obtain an operating power supply.
In this embodiment, the electromagnetic acceleration electrode power supply includes a capacitor charging power supply 5 and a capacitor unit 4, the capacitor charging power supply 5 is connected to the capacitor unit 4 through a lead and charges the capacitor unit 4, and positive and negative ends of the capacitor unit 4 are respectively connected to the electromagnetic acceleration anode 11 and the electromagnetic acceleration cathode 12 through leads, so that a potential difference exists between the electromagnetic acceleration anode 11 and the electromagnetic acceleration cathode 12.
The control system 1 is connected with the power supply processing system 2, the laser 13 and the light beam adjusting system 14, and adjusts the output voltage and laser parameters of each power consumption component and the size and position of a focused light spot according to the requirements of space tasks, so that the related propulsion performance of the thruster is changed. The power supply processing system 2 is connected with the capacitor charging power supply 5 and the magnetic field coil power supply 3, and provides required electric energy for each power consumption component according to the instruction of the control system 1. The control system 1 can control the voltage output by the capacitor charging power supply 5 through controlling the power supply processing system 2, so that the charging size of the capacitor unit 4 is changed, namely the voltage between the electromagnetic acceleration anode 11 and the electromagnetic acceleration cathode 12 is changed, the discharging current is changed, and the propulsion performance is adjusted. The control system 1 can control the power supply voltage provided by the power supply processing system 2 to the field coil power supply 3, and change the voltage output by the field coil power supply 3, thereby changing the current of the field coil 10, further changing the magnitude of the applied magnetic field, and improving the propulsion performance of the thruster.
The laser 13 outputs pulse laser, the laser 13 is connected with the control system 1, and the laser parameters (such as laser energy, pulse width, wavelength, working frequency and the like) output by the laser can be adjusted by the control system, so that the propelling performance can be controlled, and different task requirements can be met. The light beam adjusting system 14 is located a short distance right in front of the laser 13, and the light beam adjusting system 14 is connected with the control system 1 and is used for focusing laser emitted by the laser 13 according to the requirements of the control system to ablate the solid working medium.
One end of the electromagnetic accelerating electrode is opened, the other end of the electromagnetic accelerating electrode is sealed by a partition board 9, a mounting hole for fixing an electromagnetic accelerating cathode 12 is arranged at the center of the partition board 9, one end of the electromagnetic accelerating cathode 12 is fixed on the partition board 9, and the other end of the electromagnetic accelerating cathode extends into an electromagnetic accelerating anode 11. A plurality of through holes are uniformly formed in the partition plate 9 between the electromagnetic accelerating anode 11 and the electromagnetic accelerating cathode 12 and on a circumference which takes the center of the electromagnetic accelerating cathode 1 on the partition plate 9 as the circle center, each through hole is respectively communicated with a ceramic tube 8, the other end of the ceramic tube 8 is far away from the electromagnetic accelerating electrode and extends outwards, and a solid working medium 6 is arranged at the port of the ceramic tube 8. The solid working medium 6 is connected with a solid working medium supply device 7, the solid working medium supply device 7 provides the solid working medium 6 for the thruster so as to update the ablation position, guarantee the same ablation conditions under the same laser ablation conditions, guarantee the same ablation products and further guarantee the provision of accurate thrust.
A transparent substrate layer 16 is attached to the outer side face of the solid working medium 6, the laser system is arranged on the outer side of the solid working medium 6, laser beams emitted by the laser system are incident on the transparent substrate layer 16, and the laser beams penetrate through the transparent substrate layer 16 to ablate the solid working medium 6 to generate laser plasma. The laser plasma sequentially passes through the through holes on the ceramic tube 8 and the partition plate 9 and then enters between the electromagnetic acceleration anode 11 and the electromagnetic acceleration cathode 12, short pulse discharge arcs are induced to be generated, the laser plasma is heated and further ionized through the short pulse discharge arcs, and the plasma is accelerated and sprayed out under the combined action of Lorentz force and aerodynamic force, so that thrust is generated.
The solid working medium 6 and the transparent substrate layer 16 are very thin, generally tens of microns, but the thicknesses of the solid working medium 6 and the transparent substrate layer 16 are different, the thickness of the transparent substrate layer 16 should be as small as possible on the basis of ensuring that the transparent substrate layer is not ablated by laser, the thickness of the solid working medium 6 should depend on the specific used solid working medium, the thicknesses of the solid working medium are different at different times, but the basic principle is to ensure that the transparent substrate layer can be ablated by the laser.
The transparent substrate layer 16 needs to be made of a transparent material which is resistant to laser ablation and has good light transmittance, such as polyethylene terephthalate (PET) film, cellulose acetate, polyimide and the like, in order to reduce the absorption of the transparent substrate layer 16 on laser energy to ensure that most of the laser energy is used for ablating solid working media and ensure that the transparent substrate layer is not ablated, so that on one hand, the pollution of laser ablation products on a focusing system and a pulse laser can be prevented, and the normal operation of the focusing system and the pulse laser can be influenced; on the other hand, the transparent substrate layer 16 can also generate a restraining effect on laser ablation, so that the propelling performance of the thruster can be further improved.
The solid working medium supply device 7 is used for supplying a solid working medium to the thruster so as to update the ablation position and ensure the same ablation condition under the same laser ablation condition, thereby ensuring the basically consistent ablation product and further ensuring the accurate thrust. Meanwhile, the solid working medium supply device 7 can update the transparent substrate layer 16 and the solid working medium 6 at the same time, so that the energy of the laser passing through the transparent substrate layer 16 is ensured to be the same each time, and the laser can be prevented from passing through the transparent substrate layer 16 for many times to cause ablation and perforation, thereby not playing the roles of preventing pollution and restricting the laser ablation.
In summary, although the present invention has been described with reference to the preferred embodiments, it should be understood that the present invention is not limited thereto, and those skilled in the art can make various changes and modifications without departing from the spirit and scope of the present invention.
Claims (10)
1. The utility model provides a coaxial segmentation anode type laser-electromagnetic field coupling thrustor, includes laser system, electromagnetism accelerating electrode, magnetic field coil, solid working medium, the laser beam ablation solid working medium that laser system launches produces laser plasma, laser plasma gets into between electromagnetism accelerating cathode, the electromagnetism accelerating anode and the induction produces short pulse discharge arc, short pulse discharge arc makes laser plasma heating and further ionization, plasma is spout with higher speed under the combined action of lorentz force and aerodynamic force to produce thrust, its characterized in that: the electromagnetic accelerating electrode is a coaxial electromagnetic accelerating electrode, the coaxial electromagnetic accelerating electrode comprises an electromagnetic accelerating anode and an electromagnetic accelerating cathode, the electromagnetic accelerating anode is integrally cylindrical, the electromagnetic accelerating anode consists of a front-section anode cylinder, an insulating ceramic ring and a rear-section anode cylinder, and the insulating ceramic ring is arranged between the front-section anode cylinder and the rear-section anode cylinder; the electromagnetic accelerating cathode is arranged in the electromagnetic accelerating anode and the electromagnetic accelerating anode are coaxially arranged; the magnetic field coil is coated on the outer wall of the electromagnetic accelerating anode, and an external magnetic field is generated between the electromagnetic accelerating anode and the electromagnetic accelerating cathode.
2. The coaxial segmented anode type laser-electromagnetic field coupling thruster of claim 1, wherein: the front section anode cylinder, the rear section anode cylinder and the electromagnetic acceleration cathode are all made of ablation-resistant metal, the electromagnetic acceleration anode and the electromagnetic acceleration cathode are connected with an electromagnetic acceleration electrode power supply to obtain a working power supply, and the magnetic field coil is connected with a magnetic field coil power supply to obtain the working power supply.
3. The coaxial segmented anode type laser-electromagnetic field coupling thruster of claim 1, wherein: one end of the electromagnetic accelerating electrode is opened, the other end of the electromagnetic accelerating electrode is sealed by a separation plate, a mounting hole for fixing the electromagnetic accelerating cathode is formed in the separation plate, the electromagnetic accelerating cathode is of a solid cylindrical structure, one end of the electromagnetic accelerating cathode is fixed on the separation plate, and the other end of the electromagnetic accelerating cathode extends into the electromagnetic accelerating anode; a plurality of through holes are uniformly formed in a separating plate between the electromagnetic accelerating anode and the electromagnetic accelerating cathode and on a circumference which takes the center of the electromagnetic accelerating cathode on the separating plate as the center of a circle, each through hole is respectively communicated with a ceramic tube, the other end of each ceramic tube is far away from the electromagnetic accelerating electrode and extends outwards, and a solid working medium is arranged at the port of each ceramic tube; laser beams emitted by a laser system ablate solid working media on the outer port of the ceramic tube to generate laser plasma, the laser plasma sequentially passes through holes on the ceramic tube and the isolation plate and then enters between the electromagnetic acceleration cathode and the electromagnetic acceleration anode to induce short pulse discharge arcs, the short pulse discharge arcs enable the laser plasma to be heated and further ionized, and the plasma is accelerated and sprayed out under the combined action of Lorentz force and aerodynamic force, so that thrust is generated.
4. The coaxial segmented anode type laser-electromagnetic field coupling thruster of claim 3, wherein: the laser system is arranged on the outer side of one end of the opening of the electromagnetic accelerating electrode, and laser beams emitted by the laser system are incident from one end of the opening of the electromagnetic accelerating electrode, penetrate through a through hole in the isolating plate and the ceramic tube communicated with the through hole, and ablate solid working media on the outer port of the ceramic tube.
5. The coaxial segmented anode type laser-electromagnetic field coupling thruster of claim 3, wherein: the outer side surface of the solid working medium is pasted with a transparent substrate layer, the laser system is arranged on the outer side of the solid working medium, a laser beam emitted by the laser system is incident on the transparent substrate layer, and the laser beam ablates the solid working medium after penetrating through the transparent substrate layer to generate laser plasma.
6. The coaxial segmented anode type laser-electromagnetic field coupling thruster of claim 1, wherein: the electromagnetic accelerating cathode is of a hollow cylinder structure, a hollow ceramic tube is coaxially sleeved in an inner cavity of the electromagnetic accelerating cathode, and a cylindrical solid working medium is coaxially sleeved in the hollow ceramic tube; the laser system is arranged on the outer side of one end of the opening of the electromagnetic accelerating electrode, laser beams emitted by the laser system are incident from one end of the opening of the electromagnetic accelerating electrode, and solid working media in the ceramic tube are ablated to generate laser plasma.
7. The coaxial segmented anode type laser-electromagnetic field coupling thruster of any one of claims 1 to 6, wherein: the solid working medium is connected with a solid working medium supply device, and the solid working medium supply device provides the solid working medium for the thruster.
8. The coaxial segmented anode type laser-electromagnetic field coupling thruster of claim 1, wherein: the laser system comprises a laser, a light beam adjusting system and a plume protection device, wherein the light beam adjusting system is positioned right in front of the laser, and the plume protection device is positioned right in front of the light beam adjusting system and the laser.
9. The coaxial segmented anode type laser-electromagnetic field coupling thruster of claim 7, wherein: the control system is connected with the power supply processing system, the laser and the light beam adjusting system, and the power supply processing system is connected with the electromagnetic accelerating electrode power supply and the magnetic field coil power supply;
the electromagnetic acceleration electrode power supply comprises a capacitor charging power supply and a capacitor unit, the capacitor charging power supply is connected with the capacitor unit through a lead and charges the capacitor unit, and the positive end and the negative end of the capacitor unit are respectively connected with the electromagnetic acceleration anode and the electromagnetic acceleration cathode through leads so that a potential difference exists between the electromagnetic acceleration anode and the electromagnetic acceleration cathode;
the control system can control the voltage output by the capacitor charging power supply through controlling the power supply processing system, so that the charging size of the capacitor unit is changed, namely the voltage between the electromagnetic acceleration anode and the electromagnetic acceleration cathode is changed, and the discharging current is changed;
the control system can control the power supply voltage provided by the power supply processing system to the magnetic field coil power supply, and change the voltage output by the magnetic field coil power supply, so that the current of the magnetic field coil is changed, and the magnitude of an external magnetic field is changed.
10. Electromagnetism accelerating electrode, including electromagnetism accelerating anode and electromagnetism accelerating cathode, its characterized in that: the whole electromagnetic accelerating anode is in a cylindrical shape and comprises a front-section anode cylinder, an insulating ceramic ring and a rear-section anode cylinder, wherein the insulating ceramic ring is arranged between the front-section anode cylinder and the rear-section anode cylinder.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021157097.4U CN212535956U (en) | 2020-06-19 | 2020-06-19 | Coaxial segmented anode type laser-electromagnetic field coupling thruster and electromagnetic accelerating electrode |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021157097.4U CN212535956U (en) | 2020-06-19 | 2020-06-19 | Coaxial segmented anode type laser-electromagnetic field coupling thruster and electromagnetic accelerating electrode |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212535956U true CN212535956U (en) | 2021-02-12 |
Family
ID=74545073
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202021157097.4U Active CN212535956U (en) | 2020-06-19 | 2020-06-19 | Coaxial segmented anode type laser-electromagnetic field coupling thruster and electromagnetic accelerating electrode |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN212535956U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112014660A (en) * | 2020-07-10 | 2020-12-01 | 西安交通大学 | Electromagnetic pulse excitation-based space equipment electrostatic discharge method and device |
-
2020
- 2020-06-19 CN CN202021157097.4U patent/CN212535956U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112014660A (en) * | 2020-07-10 | 2020-12-01 | 西安交通大学 | Electromagnetic pulse excitation-based space equipment electrostatic discharge method and device |
| CN112014660B (en) * | 2020-07-10 | 2022-04-01 | 西安交通大学 | Electromagnetic pulse excitation-based space equipment electrostatic discharge method and device |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107939625B (en) | Reflection type laser-electromagnetic field coupling thruster | |
| CN208221007U (en) | Parallel polar plate type laser supported pulse plasma thruster | |
| CN107842478B (en) | Transmission type laser-electromagnetic field coupling thruster | |
| CN201162635Y (en) | Dual-electrode solid pulsed plasma thruster | |
| CN102374146B (en) | Pulse laser plasma electricity hybrid micro-propulsion unit and method | |
| Rafalskyi et al. | Brief review on plasma propulsion with neutralizer-free systems | |
| CN105952603B (en) | Laser ablation pulses plasma thruster | |
| CN110439771A (en) | A kind of air-breathing pulse plasma thruster | |
| CN212535956U (en) | Coaxial segmented anode type laser-electromagnetic field coupling thruster and electromagnetic accelerating electrode | |
| CN107061210B (en) | A kind of pulsed plasma thruster accelerated based on electrothermal and electromagnetic mixing | |
| CN212615195U (en) | Parallel segmented anode type laser-electromagnetic field coupling thruster and electromagnetic accelerating electrode | |
| US3308623A (en) | Electro-thermic ejectors | |
| CN106438251A (en) | Novel hollow cathode thruster | |
| CN109737023A (en) | A kind of self breakdown type pulsed plasma thruster of annular vertebral body structure anode | |
| CN110056491A (en) | A kind of carbon nano pipe array thruster | |
| US20200332780A1 (en) | Thruster device | |
| CN111173698B (en) | Liquid working medium plasma thruster based on microwave enhancement | |
| CN206592256U (en) | A kind of triggerless micro-vacuum arc propeller of use gas storage electrode | |
| CN111365207A (en) | Sectional pulse plasma thruster | |
| CN111997853A (en) | Near space environment air suction type radio frequency plasma propeller | |
| CN208221008U (en) | Coaxial polar plate type laser supported pulse plasma thruster | |
| JP6632114B2 (en) | Vacuum arc thruster | |
| CN105201769A (en) | Laser plasma combined propelling system | |
| TW202302993A (en) | Vacuum cathode arc-induced pulsed thruster | |
| HORISAWA et al. | Laser-electric hybrid acceleration system for space propulsion applications |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |