CN114593029A - Coaxial cylindrical reflection type laser and electromagnetic field coupling thruster - Google Patents
Coaxial cylindrical reflection type laser and electromagnetic field coupling thruster Download PDFInfo
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- CN114593029A CN114593029A CN202011437692.8A CN202011437692A CN114593029A CN 114593029 A CN114593029 A CN 114593029A CN 202011437692 A CN202011437692 A CN 202011437692A CN 114593029 A CN114593029 A CN 114593029A
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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
- F03H3/00—Use of photons to produce a reactive propulsive thrust
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Abstract
The invention relates to a coaxial cylindrical reflecting laser and electromagnetic field coupling thruster, wherein a pulse plasma thruster comprises a coaxial flange outer electrode, a coaxial flange inner electrode, a hollow cylindrical working medium and an insulating flange, the front end of the coaxial flange outer electrode is opened, the rear end of the coaxial flange internal electrode is fixedly connected with the insulating flange in a sealing mode, the coaxial flange internal electrode is arranged at the axle center of the coaxial flange external electrode, the hollow cylindrical working medium is arranged between the coaxial flange external electrode and the coaxial flange internal electrode, the laser preionization system comprises a solid cylindrical working medium, a cylindrical insulator and a pulse laser, the cylindrical insulator is arranged at the rear end of the coaxial flange internal electrode, a light spring is arranged on the front side of the cylindrical insulator and connected with the solid cylindrical working medium, the pulse laser is aligned with the solid cylindrical working medium and connected with a trigger device, and the pulse power supply system is connected with the coaxial flange external electrode and the coaxial flange internal electrode in a connecting mode and triggers power supply through the trigger device. The invention has the advantages of high specific impulse, wide thrust dynamic range, no carbon deposit and plume pollution, and the like.
Description
Technical Field
The invention relates to a propelling device for providing power for a micro-nano satellite, in particular to a coaxial cylindrical reflecting type laser and electromagnetic field coupling thruster.
Background
Since the 21 st century, the world space activity has been in a vigorous development. With the rising of space tasks such as deep space exploration, interstellar navigation and the like by using the small satellites and the micro satellites, higher index requirements are provided for the maneuvering capability, the effective load capability and the task coverage capability of the spacecraft. The development of aerospace is advanced, and the development requirements under new potentials are met, so that higher requirements are firstly put forward on an aerospace propulsion system. The propulsion system with high specific impulse, compact structure, less working medium consumption and low cost is an urgent need for the development of the aerospace technology.
A Pulsed Plasma Thruster (PPT) is a power device that generates a micro-newton thrust by ablating a solid, and is also a Thruster developed and shaped gradually in recent years to meet the characteristics of a microsatellite, such as small volume and light weight. The thruster has the advantages of simple structure, low power, high specific impulse and the like, can meet various operations with high technical performance such as attitude adjustment, orbit change and the like in the process of executing tasks by the microsatellite, and can also meet the strict requirements of the microsatellite on power size, angle and direction control, so that the thruster has wide attention in the field of aerospace.
The main working principle of PPT is that energy is stored first by a capacitor, then ignited by an ignition plug and a micro-discharge is generated between an electrode and the surface of the propellant, and the electrons generated by the micro-discharge are accelerated towards the anode under the action of the electric field force between the electrodes and obtain energy. These electrons with considerable energy continuously collide with the propellant surface, generating more electrons, the newly generated electrons are accelerated and collide … … with the working substance, and in doing so, an "electron avalanche" process is presented, so that the energy storage capacitor forms a large current (10) between the two electrodes along the working substance surface3-104A) And (4) arc discharge. The high temperature arc formed by the discharge ablates a very thin layer on the surface of the propellant and decomposes and ionizes it into plasma. Under the action of electromagnetic force generated by thermal power and self-induced magnetic field, the plasma is accelerated and jetted out along the track electrode to generate a pulse thrust.
However, despite the many advantages presented by the current PPT, there are inherent problems, namely that the system efficiency is low, and hysteresis ablation tends to occur, resulting in a high energy loss; secondly, PPT also has the problems of ignition failure caused by ignition carbon deposition, incomplete ionization of working medium, plume pollution and the like. In view of the above problems, there is a need to find a solution to solve the existing problems by starting with key factors such as the ablation sufficiency and the energy utilization rate of the working medium.
In recent years, with the significant progress in miniaturization technology of lasers, it has become possible to use compact lasers as energy sources for space micro-propulsion systems. The laser plasma micro thruster provides another mechanism for controlling micro mass and generating micro thrust through the ablation effect of irradiating the solid working medium by the laser beam, and has the advantages of simple structure, high specific impulse, wide thrust dynamic range, no carbon deposit and plume pollution and finer control. Therefore, the application of laser plasma micro-propulsion technology as micro-satellite attitude control is receiving attention from the industry. However, the working medium utilization rate and the system efficiency of the current laser plasma micro thruster are still low, and some new methods are still needed to be adopted to further improve the working medium utilization rate and the system efficiency so as to meet the real demand for the practicability of the micro satellite.
Disclosure of Invention
The invention aims to provide a coaxial cylindrical reflecting type thruster for coupling action of laser and an electromagnetic field, which has the advantages of high specific impulse, wide thrust dynamic range, no carbon deposit, no plume pollution and the like.
The purpose of the invention is realized by the following technical scheme:
a coaxial cylindrical reflective laser and electromagnetic field coupling action thruster is characterized in that: the pulse plasma thruster comprises a pulse plasma thruster, a pulse power supply system and a laser preionization system, wherein the pulse plasma thruster comprises a coaxial flange outer electrode, a coaxial flange inner electrode, a hollow cylindrical working medium and an insulating flange, the front end opening and the rear end of the coaxial flange outer electrode are fixedly connected with the insulating flange in a sealing way, the coaxial flange inner electrode is arranged along the axis of the coaxial flange outer electrode, the front end opening and the rear end are arranged in the middle of the insulating flange, the hollow cylindrical working medium is arranged between the coaxial flange outer electrode and the coaxial flange inner electrode, the laser preionization system comprises the solid cylindrical working medium, a cylindrical insulator and a pulse laser, the cylindrical insulator is arranged at the rear end of the coaxial flange inner electrode, a light spring is arranged at the front side of the cylindrical insulator and connected with the solid cylindrical working medium arranged in the coaxial flange inner electrode, and the laser output end of the pulse laser is aligned with the solid cylindrical working medium, and the pulse laser is connected with a trigger device, and the pulse power supply system is connected with the coaxial flange outer electrode and the coaxial flange inner electrode and is triggered and supplied with power through the trigger device.
Pulse power supply system includes DC power supply, controller, electric capacity, the switch that charges and spark switch, and wherein controller, DC power supply and the switch that charges establish ties in proper order, electric capacity with controller, DC power supply, the switch that charges establish ties, just electric capacity one side through first wire with the coaxial flange outer electrode links to each other, the opposite side through the second wire with coaxial flange inner electrode links to each other be equipped with the spark switch on the first wire, just the spark switch with trigger device links to each other be equipped with the ground wire on the second wire.
The insulating flange is fixedly connected with the coaxial flange outer electrode through a plurality of first bolts, the first lead is connected with any first bolt, a connecting plate is arranged in the middle of one side, away from the coaxial flange outer electrode, of the insulating flange, the rear end of the coaxial flange inner electrode is in contact with the connecting plate, and the second lead is connected with the connecting plate.
And a middle bolt is arranged in the middle of the connecting plate, penetrates through the insulating flange and then is fixedly connected with the cylindrical insulator, and the second lead is connected with the middle bolt.
The outer edge of the insulating flange is fixedly connected with the outer electrode of the coaxial flange through a plurality of first bolts uniformly distributed along the circumferential direction.
The outer edge of the connecting plate is fixedly connected with the insulating flange through a plurality of second bolts uniformly distributed along the circumferential direction.
The direct current power supply is a constant current source with adjustable voltage, and the capacitor is a capacitor with the capacitance of mF-muF magnitude.
The invention has the advantages and positive effects that:
the invention can make the capacitor instantly release electric quantity under the induction of laser plasma and generate large-current arc discharge on the surface of the hollow cylindrical working medium, the high-temperature arc formed by the discharge can ablate a thin layer of surface of the hollow cylindrical working medium and decompose and ionize the surface into high-density plasma, and under the thermal expansion force and the electromagnetic force generated by electromagnetic induction, the plasma between the outer electrode of the coaxial flange and the inner electrode of the coaxial flange is accelerated to be sprayed out to generate a pulse thrust.
Drawings
FIG. 1 is a schematic structural diagram of the present invention.
Wherein, 1-a direct current power supply; 2-a charge switch; 3-a controller; 4-capacitance; 5-a first wire; 6-spark switch; 7-ground wire; 8-a trigger device; 9-coaxial flange external electrode; 10-coaxial flange inner electrode; 11-middle bolt; 12-an insulating flange; 13-hollow cylindrical working medium; 14-solid column working medium; 15-light weight springs; 16-cylindrical insulator; 17-a pulsed laser; 18-a laser beam; 19-a first bolt; 20-a connecting plate; 21-second bolt.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings.
As shown in fig. 1, the present invention includes a pulse plasma thruster, a pulse power supply system and a laser preionization system, wherein the pulse plasma thruster is of a coaxial cylindrical structure, and includes a coaxial flange outer electrode 9, a coaxial flange inner electrode 10, a hollow cylindrical working medium 13 and an insulating flange 12, the coaxial flange outer electrode 9 has an opening at the front end and a rear end hermetically fixed to the insulating flange 12, the coaxial flange inner electrode 10 is disposed along the axis of the coaxial flange outer electrode 9, the coaxial flange inner electrode 10 has an opening at the front end and a rear end disposed in the middle of the insulating flange 12, the hollow cylindrical working medium 13 is disposed between the coaxial flange outer electrode 9 and the coaxial flange inner electrode 10, the laser preionization system includes a solid cylindrical working medium 14, a cylindrical insulator 16 and a pulse laser 17, wherein the solid cylindrical working medium 14 and the cylindrical insulator 16 are both disposed in the coaxial flange inner electrode 10, the cylindrical insulator 16 is arranged at the rear end of the coaxial flange inner electrode 10, a light spring 15 is arranged on the front side of the cylindrical insulator 16, the pulse laser 17 is arranged on the front side of the pulse plasma thruster, the laser output end of the pulse laser is aligned with the solid cylindrical working medium 14, the pulse laser 17 is connected with a trigger device 8 through a circuit, and the pulse power supply system is triggered by the trigger device 8 to supply power to the pulse plasma thruster.
As shown in fig. 1, the pulse power supply system includes a dc power supply 1, a controller 3, a capacitor 4, a charging switch 2, and a spark switch 6, wherein the controller 3, the dc power supply 1, and the charging switch 2 are sequentially connected in series, the capacitor 4 is connected in series with the controller 3, the dc power supply 1, and the charging switch 2, and one side of the capacitor 4 is connected to the pulse plasma thruster through a first wire 5, and the other side is connected to the pulse plasma thruster through a second wire, the spark switch 6 is provided on the first wire 5 and connected to a trigger device 8, and the second wire is provided with a ground wire 7.
In this embodiment, the dc power supply 1 is a constant current source with adjustable voltage, the capacitor 4 is a capacitor with capacitance in the mF-muf order, the dc power supply 1 is connected with the capacitor 4 through the charging switch 2 and the controller 3 and charges the capacitor, the charging switch 2 is a common push type switch, the charging loop of the capacitor 4 can be switched on and off through the on-off of the switch, the controller 3 is in a voltage regulation control mode, the charging electric quantity of the capacitor 4 can be controlled through the external voltage regulation of the controller 3, the spark switch 6 on the first lead 5 is an external trigger type switch, and the trigger device 8 can control the spark switch 6 to be closed and supply the charged electric quantity of the capacitor 4 to the pulse plasma thruster. The controller 3, the charging switch 2, the spark switch 6, the trigger device 8 and the capacitor 4 are all well known in the art and are commercially available products.
As shown in fig. 1, the outer edge of the insulating flange 12 is fixedly connected with the coaxial flange outer electrode 9 through a plurality of first bolts 19 uniformly distributed along the circumferential direction, the first lead 5 is connected with any one of the first bolts 19, and then the coaxial flange outer electrode 9 is electrified, a connecting plate 20 made of a metal material is arranged in the middle of one side of the insulating flange 12, which is far away from the coaxial flange outer electrode 9, the outer edge of the connecting plate 20 is fixedly connected with the insulating flange 12 through a plurality of second bolts 21 uniformly distributed along the circumferential direction, the rear end of the coaxial flange inner electrode 10 is in contact with the connecting plate 20, and the second lead is connected with the connecting plate 20.
As shown in fig. 1, a middle bolt 11 is disposed in the middle of the connecting plate 20, and the middle bolt 11 passes through the insulating flange 12 and is fixedly connected to a cylindrical insulator 16 disposed at the rear end of the coaxial flange inner electrode 10, so as to fix the cylindrical insulator 16, while the second lead is connected to the middle bolt 11, so as to be electrically connected to the coaxial flange inner electrode 10 via the middle bolt 11 and the connecting plate 20.
In this embodiment, the coaxial flange outer electrode 9 and the coaxial flange inner electrode 10 are both hollow metal cylinders, the insulating flange 12 is made of solid insulating materials such as polytetrafluoroethylene or nylon, and the hollow cylindrical working medium 13 is made of insulating solid materials such as polytetrafluoroethylene or teflon and is embedded between the coaxial flange outer electrode 9 and the coaxial flange inner electrode 10.
In this embodiment, the solid cylindrical working medium 14 is made of insulating solid materials such as polytetrafluoroethylene and teflon, and is integrally embedded into the coaxial flange inner electrode 10, one end of the solid cylindrical working medium 14 is connected with the light spring 15 with a high elastic coefficient, the other end of the light spring 15 is fixed on the cylindrical insulator 16, the center of the light spring 15 and the center of the solid cylindrical working medium 14 are all on the same straight line, and the straight line coincides with the central axis of the coaxial flange inner electrode 10.
In this embodiment, the pulse laser 17 may generate a laser beam 18 with adjustable pulse width and energy, and the laser beam 18 may directly interact with the solid cylindrical working medium 14 in the coaxial flange inner electrode 10. The pulse laser 17 and the pulse power supply system can realize synchronization and time delay adjustment through the trigger device 8. The pulsed laser 17 is well known in the art and is a commercially available product.
The working principle of the invention is as follows:
when a charging switch 2 in the pulse power supply system is closed, a direct current power supply 1 charges a capacitor 4, a first lead 5 on one side of the capacitor 4 is connected with an outer electrode 9 of a coaxial flange, a second lead on the other side of the capacitor 4 is connected with an inner electrode 10 of the coaxial flange through a connecting plate 20, and when a spark switch 6 is closed, the charged capacitor 4 can enable the two electrodes to instantly release electric quantity under a certain condition.
When the plasma discharge device works, a laser beam 18 generated by a pulse laser 17 and a solid cylindrical working medium 14 act to generate a trace plasma, a trigger device 8 enables a spark switch 6 in a pulse power supply system to be closed under the control of an external trigger signal of the pulse laser 17, a capacitor 4 supplies power to a pulse plasma thruster, the capacitor 4 instantly releases electric quantity under the induction of the laser plasma to generate large-current arc discharge on the surface of a hollow cylindrical working medium 13, high-temperature electric arcs formed by the discharge can ablate a thin layer of the surface of the hollow cylindrical working medium 13 and decompose and ionize the thin layer of the surface into high-density plasma, and under the electromagnetic force generated by thermal expansion force and electromagnetic induction, the plasma between an external electrode 9 of the coaxial flange and an internal electrode 10 of the coaxial flange is accelerated to be sprayed out to generate pulse thrust.
Claims (7)
1. A coaxial cylindrical reflective laser and electromagnetic field coupling action thruster is characterized in that: including pulse plasma thrustor, pulse power supply system and laser preionization system, wherein pulse plasma thrustor includes coaxial flange outer electrode (9), coaxial flange inner electrode (10), hollow cylindricality working medium (13) and insulating flange (12), coaxial flange outer electrode (9) front end opening, rear end with insulating flange (12) are sealed to be linked firmly, coaxial flange inner electrode (10) along coaxial flange outer electrode (9) axle center sets up and front end opening, rear end locates insulating flange (12) middle part, hollow cylindricality working medium (13) are located between coaxial flange outer electrode (9) and coaxial flange inner electrode (10), laser preionization system includes solid cylindricality working medium (14), cylindricality insulator (16) and pulse laser (17), wherein cylindricality insulator (16) are located coaxial flange inner electrode (10) rear end and front side are equipped with light spring (15) and locate The coaxial flange internal electrode structure is characterized in that solid cylindrical working media (14) in the coaxial flange internal electrode (10) are connected, the laser output end of the pulse laser (17) is aligned to the solid cylindrical working media (14), the pulse laser (17) is connected with a trigger device (8), and the pulse power supply system, the coaxial flange external electrode (9) and the coaxial flange internal electrode (10) are connected with each other and trigger power supply through the trigger device (8).
2. The thruster for coupling action of coaxial cylindrical reflection type laser and electromagnetic field according to claim 1, wherein: pulse power supply system includes DC power supply (1), controller (3), electric capacity (4), charge switch (2) and spark switch (6), and wherein controller (3), DC power supply (1) and charge switch (2) establish ties in proper order, electric capacity (4) with controller (3), DC power supply (1), charge switch (2) establish ties, just electric capacity (4) one side through first wire (5) with coaxial flange outer electrode (9) link to each other, the opposite side through the second wire with coaxial flange inner electrode (10) link to each other be equipped with spark switch (6) on first wire (5), just spark switch (6) with trigger device (8) link to each other be equipped with ground wire (7) on the second wire.
3. The thruster for coupling action of coaxial cylindrical reflection type laser and electromagnetic field according to claim 2, wherein: insulating flange (12) through a plurality of first bolt (19) with coaxial flange outer electrode (9) link firmly, just first wire (5) are connected with arbitrary first bolt (19), insulating flange (12) are kept away from coaxial flange outer electrode (9) one side middle part is equipped with a connecting plate (20), just coaxial flange inner electrode (10) rear end with connecting plate (20) contact, the second wire with connecting plate (20) link to each other.
4. The thruster for coupling action of coaxial cylindrical reflection type laser and electromagnetic field according to claim 3, wherein: and a middle bolt (11) is arranged in the middle of the connecting plate (20), penetrates through the insulating flange (12) and then is fixedly connected with the cylindrical insulator (16), and the second lead is connected with the middle bolt (11).
5. The thruster for coupling action of coaxial cylindrical reflection type laser and electromagnetic field according to claim 2, wherein: the outer edge of the insulating flange (12) is fixedly connected with the coaxial flange outer electrode (9) through a plurality of first bolts (19) uniformly distributed along the circumferential direction.
6. The thruster for coupling action of coaxial cylindrical reflection type laser and electromagnetic field according to claim 2, wherein: the outer edge of the connecting plate (20) is fixedly connected with the insulating flange (12) through a plurality of second bolts (21) uniformly distributed along the circumferential direction.
7. The thruster for coupling action of coaxial cylindrical reflection type laser and electromagnetic field according to claim 2, wherein: the direct current power supply (1) is a constant current source with adjustable voltage, and the capacitor (4) is a capacitor with the capacitance of mF-muF magnitude.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011437692.8A CN114593029A (en) | 2020-12-07 | 2020-12-07 | Coaxial cylindrical reflection type laser and electromagnetic field coupling thruster |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011437692.8A CN114593029A (en) | 2020-12-07 | 2020-12-07 | Coaxial cylindrical reflection type laser and electromagnetic field coupling thruster |
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| Publication Number | Publication Date |
|---|---|
| CN114593029A true CN114593029A (en) | 2022-06-07 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011437692.8A Pending CN114593029A (en) | 2020-12-07 | 2020-12-07 | Coaxial cylindrical reflection type laser and electromagnetic field coupling thruster |
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| CN (1) | CN114593029A (en) |
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2020
- 2020-12-07 CN CN202011437692.8A patent/CN114593029A/en active Pending
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