CN113357109A - Ignition device of radio frequency ion thruster - Google Patents
Ignition device of radio frequency ion thruster Download PDFInfo
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- CN113357109A CN113357109A CN202110734035.8A CN202110734035A CN113357109A CN 113357109 A CN113357109 A CN 113357109A CN 202110734035 A CN202110734035 A CN 202110734035A CN 113357109 A CN113357109 A CN 113357109A
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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
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Abstract
The invention provides a radio frequency ion thruster ignition device, and relates to the technical field of radio frequency ion thrusters. Under the working state, the screen grid is connected with a direct-current high-voltage power supply, the main coil wound on the main ionization chamber is connected with a radio-frequency power supply, the additional coil wound on the auxiliary ionization chamber induces a sine high voltage, and a strong electric field between the screen grid and the metal air inlet pipe is enhanced at half probability because the metal air inlet pipe is connected with one end of the additional coil in an equipotential manner; the strengthened electric field breaks down more working media to form plasma, the high-density plasma is diffused to the main ionization chamber to collide with the non-ionized working media in an accelerating way, so that the working media in the main ionization chamber are completely ionized, the input power of a radio frequency power source on the main coil is reduced, and low-power ignition operation is realized.
Description
Technical Field
The invention relates to the technical field of radio frequency ion thrusters, in particular to an ignition device of a radio frequency ion thruster.
Background
The radio frequency ion thruster is a device which ionizes working media by using electromagnetic waves with frequency of about 1-10MHz and accelerates ions in an ion extraction system so as to generate thrust, and is one of aerospace electric thrusters. The direct current ion thruster has the characteristics of simple structure, high specific impulse, high efficiency, long service life and the like, is suitable for attitude adjustment, orbit maintenance, orbital transfer and even deep space exploration of various spacecrafts, and has the advantages of simpler structure and longer service life compared with the conventional direct current ion thruster.
The main structure of the radio frequency ion thruster comprises an ionization chamber capable of smoothly transmitting electromagnetic waves, a gas distributor, a coil wound outside the ionization chamber, an ion leading-out system and a neutralizer; the coil is connected with the radio frequency source through the impedance matching network, after the radio frequency source provides power, the coil induces a magnetic field in the ionization chamber, the alternating magnetic field induces a vortex electric field again, and the vortex electric field can accelerate a working medium to come out of the gas distributor and fill the whole ionization chamber to obtain plasma; after the plasma is transported to the ion extraction system, ions in the plasma are extracted and accelerated under the action of the ion extraction system to generate thrust, and ejected deionized water is finally neutralized under the action of electrons ejected by the neutralizer.
In the conventional radio frequency plasma thruster, high-flow and high-power impact is generally adopted during ignition, or radio frequency high voltage is connected between a screen grid and an accelerating grid to break down gas between the screen grid and the accelerating grid so as to generate electrons, or a neutralizer is adopted to generate electrons, and the electrons are introduced into an ionization chamber by a grid system. For the first case, the impedance change is obvious before and after ignition, the impact is large, working medium and energy are wasted, the second case damages the accelerating grid to shorten the service life of the system, and for the third case, the problems of the first point and the second point still cannot be avoided for the radio frequency ion thruster using the radio frequency neutralizer as an electron source or the self-neutralizing radio frequency ion thruster without the neutralizer.
Disclosure of Invention
The invention aims to provide an ignition device of a radio frequency ion thruster, which can realize ignition operation in a low-power state.
In order to achieve the purpose, the invention provides the following scheme:
a radio frequency ion thruster ignition device comprises a metal air inlet pipe, an ionization chamber, a main coil, an additional coil and a screen grid;
the ionization chamber comprises a main ionization chamber and an auxiliary ionization chamber, and the main ionization chamber is fixedly connected with the auxiliary ionization chamber;
the metal air inlet pipe is fixedly connected with the auxiliary ionization chamber;
the screen grid electrode is fixedly connected with the main ionization chamber and is externally connected with a direct-current high-voltage power supply;
the additional coil is wound on the auxiliary ionization chamber, one end of the additional coil is electrically connected with the metal air inlet pipe, and the other end of the additional coil is grounded;
the main coil is wound on the main ionization chamber and is used for being connected into a radio frequency power source;
when the metal air inlet pipe works, the additional coil is mutually coupled with the main coil through electromagnetic induction to generate sine high voltage, and the potential of the metal air inlet pipe is the same as that of one end of the additional coil.
Optionally, the ionization chamber is an integrally formed structure, and the main ionization chamber and the auxiliary ionization chamber are both tubular structures.
Optionally, the inner diameter of the main ionization chamber has a value greater than the inner diameter of the secondary ionization chamber, and the length of the secondary ionization chamber has a value greater than or equal to the length of the main ionization chamber.
Optionally, the aperture value of the air inlet hole of the metal air inlet pipe is smaller than the inner diameter value of the auxiliary ionization chamber.
Optionally, a plurality of needle point structures are arranged inside the metal air inlet pipe;
in operation, the tip structure is used to generate a tip discharge.
Optionally, the secondary coil is of a multi-turn coreless structure; the secondary coil is made by winding a litz wire in multiple turns and layers.
Optionally, the inductance of the additional coil is greater than the inductance of the main coil.
Optionally, the material of the ionization chamber is double-stage quartz or alumina ceramic.
According to the specific embodiment provided by the invention, the invention discloses the following technical effects:
the invention provides an ignition device of a radio frequency ion thruster; when the screen grid is externally connected with a direct-current high-voltage power supply, a strong electric field formed between the metal air inlet pipe and the screen grid can puncture working media entering the metal air inlet pipe, so that the working media become plasma. Meanwhile, the radio frequency power source is connected with the main coil, so that the additional coil is mutually coupled with the main coil through electromagnetic induction and generates sine high voltage, and the potential of the metal air inlet pipe and the potential of one end of the additional coil are equal to each other, so that half of the probability of an electric field between the metal air inlet pipe and the screen grid is enhanced, and the direct current high voltage required by breakdown can be reduced; and the enhanced electric field can break down more working media to generate more plasmas, after the more plasmas are diffused to the main ionization chamber, the plasmas are accelerated to collide with the working media in the main ionization chamber under the action of the magnetic field of the main ionization chamber, and the collision of the plasmas helps the non-ionized working media to complete ionization, so that the working media in the main ionization chamber are completely ionized under the lower input power of the main coil, and the low-power ignition operation is realized.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without inventive exercise.
FIG. 1 is a diagram of the structural design of an apparatus according to an embodiment of the present invention;
FIG. 2 is a block diagram of an ionization chamber according to an embodiment of the present invention;
FIG. 3 is a side view of an ionization chamber configuration of an embodiment of the present invention;
FIG. 4 is a tip structure view of a metal intake tube according to an embodiment of the present invention;
FIG. 5 is a side view of a tip structure of a metal air inlet tube according to an embodiment of the present invention;
FIG. 6 is a circuit diagram of an apparatus according to an embodiment of the present invention;
FIG. 7 is a schematic diagram of the circuit connection and ignition process of the device according to the embodiment of the present invention.
Description of the symbols:
1-metal air inlet pipe, 2-additional coil, 3-main coil, 4-screen grid, 5-main ionization chamber, 6-auxiliary ionization chamber and 7-needle point structure.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The invention aims to provide an ignition device of a radio frequency ion thruster, which can realize ignition operation in a low-power state.
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in further detail below.
Examples
As shown in fig. 1, the ignition device of the rf ion thruster of the present invention includes a metal air inlet pipe 1, an ionization chamber, a main coil 3, an additional coil 2, and a screen grid 4.
Furthermore, the ionization chamber can be divided into a main ionization chamber 5 and an auxiliary ionization chamber 6, and the main ionization chamber 5 is fixedly connected with the auxiliary ionization chamber 6.
The metal air inlet pipe 1 is fixedly connected with the auxiliary ionization chamber 6.
The screen grid 4 is fixedly connected with the main ionization chamber 5, and the screen grid 4 is externally connected with a direct-current high-voltage power supply.
The additional coil 2 is wound on the auxiliary ionization chamber 6, one end of the additional coil 2 is electrically connected with the metal air inlet pipe 1, and the other end of the additional coil 2 is grounded, which can be seen from the circuit connection diagram 6.
The main coil 3 is wound on the main ionization chamber 5, and the main coil 3 is used for connecting a radio frequency power source.
When the metal air inlet pipe works, the additional coil 2 is mutually coupled with the main coil 3 through electromagnetic induction to generate sine high voltage, and further the electric potential of the metal air inlet pipe 1 is the same as that of one end of the additional coil 2.
As a preferred embodiment, the main ionization chamber 5 and the auxiliary ionization chamber 6 in this embodiment are both tubular structures, and the main ionization chamber 5 and the auxiliary ionization chamber 6 are non-detachable integral structures, that is, the ionization chambers are integrally formed structures, please refer to fig. 2 and fig. 3.
In a preferred embodiment, the inner diameter of main ionization chamber 5 is greater than the inner diameter of secondary ionization chamber 6, and the length of secondary ionization chamber 6 is greater than or equal to the length of main ionization chamber 5.
In this embodiment, the inner diameter of main ionization chamber 5 is 10 times the inner diameter of sub ionization chamber 6, and the length of sub ionization chamber 6 is greater than or equal to the length of main ionization chamber 5. In the embodiment, the auxiliary ionization chamber 6 is designed into a long and narrow channel, so that the density and the air pressure of working media in the auxiliary ionization chamber 6 can be improved.
As a preferred embodiment, in this embodiment, the aperture value of the air inlet hole of the metal air inlet pipe 1 is smaller than the inner diameter value of the secondary ionization chamber 6, so that the density of the working medium near the air inlet pipe can be increased, the inner diameter value of the secondary ionization chamber 6 is smaller than the inner diameter value of the primary ionization chamber 5, and the length value of the secondary ionization chamber 6 is greater than or equal to the length value of the primary ionization chamber 5.
The metal gas inlet pipe 1 is provided with a small gas inlet hole, preferably, the diameter of the gas inlet hole of the metal gas inlet pipe 1 is 1/5-1/3 of the inner diameter of the auxiliary ionization chamber 6 in the embodiment, the structure is designed to improve the gas density near the metal gas inlet pipe 1, and in addition, the diameter of the gas inlet hole of the metal gas inlet pipe 1 can be designed to be different values according to the relation between the flow and the breakdown voltage.
As a preferred embodiment, the additional coil 2 has a multi-turn core-free structure, and is formed by tightly winding litz wire having a plurality of turns and layers and excellent insulation between wires.
In a preferred embodiment, the additional coil 2 can provide a large inductance, the inductance of the additional coil 2 is larger than that of the main coil 3, and the inductance of the additional coil 2 is 7-10 times that of the main coil 3 in this embodiment, or may be determined according to practical effects.
In a preferred embodiment, the metal inlet tube 1 is provided with a plurality of needle point structures 7 inside. The surface of the inner part of the metal air inlet pipe 1 can generate an etching effect due to high-voltage breakdown, so that the surface of the metal air inlet pipe 1 can be designed to be thicker, and the requirement on the service life of long-time work can be met; in order to improve the breakdown effect, the present embodiment provides a plurality of needle tips 7 near the air supply hole of the metal intake duct 1, as shown in fig. 4 and 5. In operation, the tip structure 7 is used to generate a tip discharge. The structure design can reduce the voltage of a direct-current high-voltage power supply used for breakdown of the working medium.
In a preferred embodiment, the ionization chamber is made of quartz or alumina ceramic.
In a working state, working media enter the auxiliary ionization chamber 6 from the metal air inlet pipe 1 with a narrow air inlet channel, the auxiliary ionization chamber 6 is a long and narrow channel, the inner diameter of the auxiliary ionization chamber 6 is 3-5 times of the inner diameter of the air inlet hole of the metal air inlet pipe 1, but the inner diameter of the auxiliary ionization chamber 6 is smaller than that of the main ionization chamber 5, the structural design is used for improving the air pressure in the auxiliary ionization chamber 6, the working media finally flow to the main ionization chamber 5, and the inner diameter of the main ionization chamber 5 is 10 times of the inner diameter of the auxiliary ionization chamber 6 in the embodiment. The screen grid 4 has a throttling function and is used for providing a direct-current high-voltage power supply. The additional coil 2 is wound on the auxiliary ionization chamber 6, the inductance of the additional coil 2 is 7-10 times of the inductance of the main coil 3 in the embodiment, and the inductance of the additional coil 2 and the main coil 3 can also be restricted according to the upper limit of the voltage of the direct-current voltage source applied on the screen grid 4. When the voltage of the dc voltage source is low, the additional coil 2 requires a large inductance.
In the working state, one end of the metal air inlet pipe 1 is connected with the additional coil 2, and the other end of the additional coil 2 is grounded. A strong electric field is formed between the metal air inlet pipe 1 and the screen grid 4 connected with the direct-current high-voltage power supply, a high-density gas working medium is arranged near an air inlet hole of the metal air inlet pipe 1, the gas working medium is punctured by the strong electric field under a proper voltage difference to generate plasma, and the gas working medium in the auxiliary ionization chamber 6 is also punctured by the strong electric field to generate plasma.
The gas working medium is broken down by a strong electric field under proper high voltage, and plasma is generated after the breakdown. The appropriate high voltage can be obtained directly by increasing the dc high voltage power applied by the screen grid 4, or by the mutual induction of the additional coil 2 and the main coil 3, which puts higher demands on the dc high voltage power. When a radio frequency power source feeds power into the main coil 3 through the impedance matching network, the additional coil 2 generates sine high voltage due to electromagnetic induction, and the power of the main coil 3 is partially coupled to the additional coil 2; because the electric potential of the metal air inlet pipe 1 is equal to the electric potential of one end of the additional coil 2, the electric field between the metal air inlet pipe 1 and the screen grid 4 is enhanced by half, and the voltage of a direct-current high-voltage power supply required by breakdown of working media can be reduced. Meanwhile, the enhanced electric field can break down more working media to generate more plasmas, so that the density of the plasmas in the auxiliary ionization chamber 6 is increased, the more plasmas are diffused to the main ionization chamber 5 from the auxiliary ionization chamber 6, and are accelerated to collide with the working media in the main ionization chamber 5 under the action of the magnetic field of the main ionization chamber 5, the collision of the plasmas helps the unionized working media to complete ionization, so that the working media in the main ionization chamber 5 complete ionization under the lower input power of the main coil 3, the input power of the main coil 3 is reduced, and the purpose of low-power ignition is achieved. After the working medium in the main ionization chamber 5 is completely ionized, the grounding end of the additional coil is disconnected, and the ignition is finished. Fig. 7 is a schematic diagram of the circuit connection and ignition process of the device according to the embodiment of the present invention, and the ignition process of the device according to the embodiment of the present invention can be seen in fig. 5.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
The principles and embodiments of the present invention have been described herein using specific examples, which are provided only to help understand the method and the core concept of the present invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, the specific embodiments and the application range may be changed. In view of the above, the present disclosure should not be construed as limiting the invention.
Claims (8)
1. The ignition device of the radio frequency ion thruster is characterized by comprising a metal air inlet pipe, an ionization chamber, a main coil, an additional coil and a screen grid;
the ionization chamber comprises a main ionization chamber and an auxiliary ionization chamber, and the main ionization chamber is fixedly connected with the auxiliary ionization chamber;
the metal air inlet pipe is fixedly connected with the auxiliary ionization chamber;
the screen grid is fixedly connected with the main ionization chamber and is used for being connected with a direct-current high-voltage power supply;
the additional coil is wound on the auxiliary ionization chamber, one end of the additional coil is electrically connected with the metal air inlet pipe, and the other end of the additional coil is grounded;
the main coil is wound on the main ionization chamber and is used for being connected into a radio frequency power source;
when the metal air inlet pipe works, the additional coil is mutually coupled with the main coil through electromagnetic induction to generate sine high voltage, and the potential of the metal air inlet pipe is the same as that of one end of the additional coil.
2. The rf ion thruster ignition device of claim 1 wherein the ionization chamber is a one-piece structure and the primary ionization chamber and the secondary ionization chamber are both tubular structures.
3. The rf ion thruster ignition device of claim 1, wherein the primary ionization chamber has an inner diameter value greater than an inner diameter value of the secondary ionization chamber, and the secondary ionization chamber has a length value greater than or equal to a length value of the primary ionization chamber.
4. The rf ion thruster ignition device of claim 1, wherein an aperture value of the air intake hole of the metal air intake pipe is smaller than an inner diameter value of the secondary ionization chamber.
5. The rf ion thruster ignition device of claim 1, wherein the metal intake tube has a plurality of needle point structures disposed therein;
in operation, the tip structure is used to generate a tip discharge.
6. The rf ion thruster ignition device of claim 1 wherein the secondary coil is a multi-turn coreless structure; the secondary coil is made by winding a litz wire in multiple turns and layers.
7. The rf ion thruster ignition device of claim 1, wherein the inductance of the additional coil is greater than the inductance of the main coil.
8. The rf ion thruster ignition device of claim 1 wherein the material of the ionization chamber is double-stage quartz or alumina ceramic.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114922790A (en) * | 2022-05-19 | 2022-08-19 | 哈尔滨工业大学 | Radio frequency ion thruster based on ICP internal coupling discharge |
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