CN108869222B - A kind of radio frequency-ion thruster ignition initiation devices - Google Patents
A kind of radio frequency-ion thruster ignition initiation devices Download PDFInfo
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- CN108869222B CN108869222B CN201810709475.6A CN201810709475A CN108869222B CN 108869222 B CN108869222 B CN 108869222B CN 201810709475 A CN201810709475 A CN 201810709475A CN 108869222 B CN108869222 B CN 108869222B
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- radio frequency
- ion thruster
- cold
- ignition
- ionisation chamber
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H1/00—Using plasma to produce a reactive propulsive thrust
- F03H1/0006—Details applicable to different types of plasma thrusters
-
- 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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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Electromagnetism (AREA)
- Plasma Technology (AREA)
Abstract
The invention proposes a kind of radio frequency-ion thruster ignition initiation devices, belong to radio frequency-ion thruster technical field, more particularly to a kind of radio frequency-ion thruster ignition initiation devices.It solves existing radio frequency-ion thruster igniting difficulty in starting, needs the higher gas pressure of ionisation chamber, the problem of ignition point consumes a large amount of Working medium gas.It includes cold-cathode electron source, emitter, cold cathode air supply pipe, current-limiting resistance, ignition switch, charging resistor, capacitor, accelerating power source, switching switch and ionisation chamber.It is mainly used for the igniting starting of radio frequency-ion thruster.
Description
Technical field
The invention belongs to radio frequency-ion thruster technical fields, light a fire and start more particularly to a kind of radio frequency-ion thruster
Device.
Background technique
Radio frequency-ion thruster be it is a kind of provide the energy conversion device of power for spacecraft, this thruster passes through
It is passed through radio-frequency current on coil, axial magnetic field is generated inside ionisation chamber, then generates eddy current field, this electromagnetic field pair
The effect of ion can be ignored, and electronics can obtain enough energy to hit neutral atom, its ionization is made to form self-maintained discharge,
Ion in ionisation chamber is accelerated to spray by ion-optic system, forms plume and generates thrust, is neutralized by averager launching electronics
Ion is to maintain external electroneutral.Radio frequency-ion thruster ionizes working medium by the way of inductively coupled discharge,
Have many advantages, such as that structure is simple, be easy to minimize；Acceleration to working medium is realized using electrostatic accelerated mode, therefore there is specific impulse
Advantage high, thrust noise is small；Thrust can be adjusted by changing RF input power, working medium flow, grid voltage, be had
Have the advantages that response is rapid, thrust range is big, high resolution.
Igniting starting is the key technical problem in radio frequency-ion thruster actual application, since radio frequency discharge is several
Gas density is higher in pa to the ionisation chamber of tens pa magnitudes, it is relatively easy to establish electric discharge, but in Miniature RF ion thruster
In, the usually only several sccm of gas flow, pressure only has 10 in ionisation chamber-1Magnitude is even lower, therefore it is lighted a fire
Starting is abnormal difficult, and the prior art usually carries out excitation igniting using the gas pressure that pulse pressure moment increases ionisation chamber, makes
It obtains ion thruster ignition point gas consumption to be significantly increased, reduces the sweay of propulsion system.
Summary of the invention
The present invention in order to solve the problems in the prior art, proposes a kind of radio frequency-ion thruster ignition initiation devices.
To achieve the above object, the invention adopts the following technical scheme: a kind of radio frequency-ion thruster ignition initiation devices,
It includes cold-cathode electron source, emitter, cold cathode air supply pipe, current-limiting resistance, ignition switch, charging resistor, capacitor, accelerates electricity
Source, switching switch and ionisation chamber, the ionisation chamber is interior to be equipped with cold-cathode electron source, before the emitter is located at cold cathode air supply pipe
End, the cold cathode air supply pipe after current-limiting resistance and ignition switch with one end of capacitor by being connected, the other end of the capacitor
It is connected with the cathode of accelerating power source, the cold cathode air supply pipe passes through one end after current-limiting resistance and ignition switch with charging resistor
It is connected, the other end of the charging resistor is connected with the anode of accelerating power source, and the cathode of the accelerating power source is connected with screen, institute
Accelerating power source is stated by being connected after switching switch with accelerating grid, before the igniting starting of radio frequency-ion thruster, accelerating power source is by filling
Resistance is capacitor charging, and Working medium gas, which enters after radio frequency thruster ionisation chamber to disconnect switching to switch by cold-cathode electron source, to be closed
Ignition switch is closed, breakdown Working medium gas produces between cold cathode air supply pipe and cold-cathode electron source shell after electric current passes through current-limiting resistance
The emitter of raw electric arc, the electric arc heated cold cathode air supply pipe front end of generation forms seed electrons, and seed electrons enter ionisation chamber
The interior ionization for Working medium gas in ionisation chamber provides seed, and disconnection igniting closes the switch switching switch, and ion is in screen and adds
It is accelerated to draw between fast grid and forms thrust.Further, the ignition switch and switching switch are that hilted broadsword pair sets switch.
Further, the resistance value of the charging resistor is 10 Ω or 15 Ω.
Further, the resistance value of the current-limiting resistance is 10K Ω or 20K Ω.
Further, the capacitance of the capacitor is 10 μ F or 20 μ F.
By the way that cold-cathode electron source is arranged in ionisation chamber, by cold-cathode electron source and inductively coupled radio frequency ion thruster
Air supply system carries out integrated design, generates electric arc, the cold yin of electric arc heated by high-voltage breakdown Working medium gas in ignition point
The emitter of pole air supply pipe front end realizes that electronics is drawn, and provides seed electrons for the igniting starting of radio frequency-ion thruster, reaches drop
The purpose of low radio frequency ion thruster igniting entry condition.
Compared with prior art, it is stranded the beneficial effects of the present invention are: solving existing radio frequency-ion thruster igniting starting
The problem of difficulty, needs ionisation chamber elevated pressures, and ignition point consumes a large amount of Working medium gas, the present invention in igniting start-up course,
It haves no need to change gas supply flow and moment consumes a large amount of Working medium gas, this method may be implemented within the scope of wider gas supply flow and penetrate
The igniting of frequency ion thruster starts.
Detailed description of the invention
Fig. 1 is a kind of radio frequency-ion thruster ignition initiation devices schematic diagram of the present invention
1- cold-cathode electron source, 2- emitter, 3- cold cathode air supply pipe, 4- Working medium gas, 5- current-limiting resistance, 6- igniting are opened
It closes, 7- charging resistor, 8- capacitor, 9- accelerating power source, 10- switching switch, 11- screen, 12- accelerating grid, 13- ionisation chamber
Specific embodiment
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation illustrates.
Illustrate present embodiment referring to Fig. 1, a kind of radio frequency-ion thruster ignition initiation devices, it includes cold cathode electron
Source 1, emitter 2, cold cathode air supply pipe 3, current-limiting resistance 5, ignition switch 6, charging resistor 7, capacitor 8, accelerating power source 9, switching
Switch 10 and ionisation chamber 13, the ionisation chamber 13 is interior to be equipped with cold-cathode electron source 1, and the emitter 2 is located at cold cathode air supply pipe 3
Front end, the cold cathode air supply pipe 3 are connected after passing through current-limiting resistance 5 and ignition switch 6 with one end of capacitor 8, the capacitor 8
The other end is connected with the cathode of accelerating power source 9, the cold cathode air supply pipe 3 by after current-limiting resistance 5 and ignition switch 6 with charging
One end of resistance 7 is connected, and the other end of the charging resistor 7 is connected with the anode of accelerating power source 9, and the accelerating power source 9 is born
Pole is connected with screen 11, and the accelerating power source 9 after switching switch 10 with accelerating grid 12 by being connected, the igniting of radio frequency-ion thruster
Before starting, accelerating power source 9 is the charging of capacitor 8 by charging resistor 7, and Working medium gas 4 is pushed away by cold-cathode electron source 1 into radio frequency
Switching switch 10 is disconnected after power device ionisation chamber 13 and is closed ignition switch 6, and breakdown Working medium gas 4 exists after electric current passes through current-limiting resistance 5
Electric arc is generated between 1 shell of cold cathode air supply pipe 3 and cold-cathode electron source, 3 front end of electric arc heated cold cathode air supply pipe of generation
Emitter 2 forms seed electrons, and seed electrons, which enter in ionisation chamber 13, provides kind for the ionization of Working medium gas 4 in ionisation chamber 13
Son disconnects the closure switching switch 10 of ignition switch 6, and ion, which is accelerated to draw between screen 11 and accelerating grid 12, forms thrust.
Seed electrons of the present invention are drawn out to ionisation chamber 13 under the action of electric field, exist inside ionisation chamber 13 by penetrating
The axial magnetic field generated under the frequency function of current, then generates eddy current field, and seed electrons obtain foot under eddy electric field effect
Enough energy impact neutral atoms, make its ionization form self-maintained discharge.
Ignition switch of the present invention 6 sets switch using hilted broadsword pair with switching switch 10, can control accelerating power source 9 to
Another access disconnects while two different direction output, an i.e. access closure.The resistance value of resistance and the capacitance of capacitor
Setting are as follows: charging resistor 7 is 10K Ω, current-limiting resistance 5 is 10 Ω, capacitor 8 is 10 μ F or charging resistor 7 is 10K Ω, current limliting electricity
Resistance 5 is 15 Ω, capacitor 8 is 10 μ F or charging resistor 7 is 20K Ω, current-limiting resistance 5 is 10 Ω, capacitor 8 is 20 μ F.
Above to a kind of radio frequency-ion thruster ignition initiation devices provided by the present invention, it is described in detail, this
Apply that a specific example illustrates the principle and implementation of the invention in text, the explanation of above example is only intended to
It facilitates the understanding of the method and its core concept of the invention；At the same time, for those skilled in the art, think of according to the present invention
Think, there will be changes in the specific implementation manner and application range, in conclusion the content of the present specification should not be construed as pair
Limitation of the invention.
Claims (5)
1. a kind of radio frequency-ion thruster ignition initiation devices, it includes cold-cathode electron source (1), emitter (2), current-limiting resistance
(5), ignition switch (6), capacitor (8), accelerating power source (9) and ionisation chamber (13), it is characterised in that: it further includes cold cathode gas supply
(3), charging resistor (7) and switching switch (10) are managed, is equipped with cold-cathode electron source (1) in the ionisation chamber (13), the transmitting
Body (2) is located at cold cathode air supply pipe (3) front end, and the cold cathode air supply pipe (3) passes through current-limiting resistance (5) and ignition switch (6)
It is connected afterwards with one end of capacitor (8), the other end of the capacitor (8) is connected with the cathode of accelerating power source (9), and the cold cathode supplies
Tracheae (3) is connected with one end of charging resistor (7) afterwards by current-limiting resistance (5) and ignition switch (6), the charging resistor (7)
The other end be connected with the anode of accelerating power source (9), the cathode of the accelerating power source (9) is connected with screen (11), the acceleration
Power supply (9) is connected with accelerating grid (12) afterwards by switching switch (10), before the igniting starting of radio frequency-ion thruster, accelerating power source
It (9) is capacitor (8) charging by charging resistor (7), Working medium gas (4) enters radio frequency thruster by cold-cathode electron source (1)
Ionisation chamber (13) disconnects switching switch (10) closure ignition switch (6) afterwards, and electric current punctures Working medium gas by current-limiting resistance (5) afterwards
(4) electric arc, the electric arc heated cold cathode gas supply of generation are generated between cold cathode air supply pipe (3) and cold-cathode electron source (1) shell
The emitter (2) for managing (3) front end forms seed electrons, and seed electrons enter in ionisation chamber (13) for ionisation chamber (13) interior working medium gas
The ionization of body (4) provides seed, disconnects ignition switch (6) closure switching switch (10), ion is in screen (11) and accelerating grid
(12) it is accelerated to draw between and forms thrust.
2. a kind of radio frequency-ion thruster ignition initiation devices according to claim 1, it is characterised in that: the igniting is opened
It closes (6) and switching switch (10) and sets switch for hilted broadsword is double.
3. a kind of radio frequency-ion thruster ignition initiation devices according to claim 1, it is characterised in that: the charging electricity
The resistance value for hindering (7) is 10K Ω or 20K Ω.
4. a kind of radio frequency-ion thruster ignition initiation devices according to claim 1, it is characterised in that: the current limliting electricity
The resistance value for hindering (5) is 10 Ω or 15 Ω.
5. a kind of radio frequency-ion thruster ignition initiation devices according to claim 1, it is characterised in that: the capacitor
(8) capacitance is 10 μ F or 20 μ F.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810709475.6A CN108869222B (en) | 2018-07-02 | 2018-07-02 | A kind of radio frequency-ion thruster ignition initiation devices |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810709475.6A CN108869222B (en) | 2018-07-02 | 2018-07-02 | A kind of radio frequency-ion thruster ignition initiation devices |
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| CN108869222A CN108869222A (en) | 2018-11-23 |
| CN108869222B true CN108869222B (en) | 2019-09-10 |
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Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109630369B (en) * | 2019-01-11 | 2020-01-14 | 哈尔滨工业大学 | Radio frequency ion thruster and pulse generation method |
| CN110056491B (en) * | 2019-05-14 | 2020-07-14 | 大连理工大学 | Carbon nanotube array thruster |
| CN111287922A (en) * | 2020-02-13 | 2020-06-16 | 哈尔滨工业大学 | Dual-frequency dual-antenna small wave ionized ion propulsion device |
| CN111878337A (en) * | 2020-07-06 | 2020-11-03 | 安徽华东光电技术研究所有限公司 | Ion thruster |
| CN111852803B (en) * | 2020-07-27 | 2021-07-16 | 大连理工大学 | Mixed effect annular ion thruster based on segmented anode |
| CN114302548B (en) * | 2021-12-31 | 2023-07-25 | 中山市博顿光电科技有限公司 | Radio frequency ionization device, radio frequency neutralizer and control method thereof |
| CN114718830B (en) * | 2022-04-13 | 2024-05-10 | 哈尔滨工业大学 | Working medium-free annular hot wire cathode |
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| FR2897398A1 (en) * | 2006-02-14 | 2007-08-17 | Claude Poher | DEVICE THROUGH ACCELERATION OF PARTICLES AND APPLICATIONS OF SAID DEVICE |
| CN102493936A (en) * | 2011-12-15 | 2012-06-13 | 哈尔滨工业大学 | Hall thrustor based on magnetic focusing |
| US9086060B1 (en) * | 2012-10-31 | 2015-07-21 | The Boeing Company | Telemetry for testing switch configuration in ion propulsion system |
| CN103596348B (en) * | 2013-11-22 | 2016-09-14 | 哈尔滨工业大学 | A kind of plasma Hall effect thruster low-frequency oscillation suppression external loop |
| CN106640568B (en) * | 2015-10-30 | 2019-05-17 | 北京精密机电控制设备研究所 | A kind of dipolar solid ablative-type protective coating plasma accelerator |
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