CN116717398A - Rocket engine plasma igniter - Google Patents
Rocket engine plasma igniter Download PDFInfo
- Publication number
- CN116717398A CN116717398A CN202310529269.8A CN202310529269A CN116717398A CN 116717398 A CN116717398 A CN 116717398A CN 202310529269 A CN202310529269 A CN 202310529269A CN 116717398 A CN116717398 A CN 116717398A
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- Prior art keywords
- layer
- cathode
- anode
- igniter
- power supply
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- 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.)
- Pending
Links
- 239000002184 metal Substances 0.000 claims abstract description 23
- 229910052751 metal Inorganic materials 0.000 claims abstract description 23
- 239000007788 liquid Substances 0.000 claims abstract description 14
- 239000000446 fuel Substances 0.000 claims abstract description 11
- 239000000203 mixture Substances 0.000 claims abstract description 7
- 239000000919 ceramic Substances 0.000 claims description 23
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 7
- 239000000956 alloy Substances 0.000 claims description 7
- 229910045601 alloy Inorganic materials 0.000 claims description 7
- 229910052802 copper Inorganic materials 0.000 claims description 7
- 239000010949 copper Substances 0.000 claims description 7
- 229910000833 kovar Inorganic materials 0.000 claims description 7
- 239000000463 material Substances 0.000 claims description 5
- 239000012212 insulator Substances 0.000 claims description 4
- 238000007789 sealing Methods 0.000 claims description 4
- 238000002955 isolation Methods 0.000 claims description 3
- 238000009422 external insulation Methods 0.000 claims description 2
- 238000009434 installation Methods 0.000 abstract 1
- 239000002360 explosive Substances 0.000 description 6
- 230000000977 initiatory effect Effects 0.000 description 6
- 238000002485 combustion reaction Methods 0.000 description 5
- 230000007423 decrease Effects 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- 238000003466 welding Methods 0.000 description 3
- 239000003990 capacitor Substances 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 125000006850 spacer group Chemical group 0.000 description 2
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 description 1
- 150000001335 aliphatic alkanes Chemical class 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 230000020169 heat generation Effects 0.000 description 1
- 239000001257 hydrogen Substances 0.000 description 1
- 229910052739 hydrogen Inorganic materials 0.000 description 1
- 125000004435 hydrogen atom Chemical class [H]* 0.000 description 1
- 150000002739 metals Chemical class 0.000 description 1
- 239000007800 oxidant agent Substances 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 239000003380 propellant Substances 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 239000000758 substrate Substances 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/95—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by starting or ignition means or arrangements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Ignition Installations For Internal Combustion Engines (AREA)
- Spark Plugs (AREA)
Abstract
The application provides a rocket engine plasma igniter, comprising: the igniter head, the back pressure adapter and the power supply connector are connected in sequence; the power supply connector is connected with an external power supply, and responds to the current pulse input of the external power supply, and the current pulse is transmitted to the igniter head through the back pressure adapter; the igniter head comprises a cathode layer, a dielectric layer and an anode layer which are annularly and sequentially arranged; the cathode layer and the anode layer generate potential difference after receiving current pulse, and discharge occurs under the action of the medium layer, and joule energy generated by the discharge is used for guiding the fuel mixture of gas and liquid. The application has simple installation, no need of manual filling before emission, and the generated Joule energy can not be changed along with the atmospheric density by adding a metal layer to the medium layer of the igniter head.
Description
Technical Field
The application relates to the technical field of rocket engines, in particular to a rocket engine plasma igniter.
Background
Ground test systems such as liquid rocket engines and combustion type heaters typically employ liquid oxidants and fuels with relatively high combustion chamber pressures. The novel liquid rocket engine mostly adopts low-temperature propellants such as liquid oxygen, liquid hydrogen, liquid alkane and the like, has a severe ignition environment and has higher ignition energy and safety requirements. In addition, multiple start and reusable liquid rocket engines also place demands on the ignition technology for quick, reliable and reusable. The safe and reliable high-energy ignition technology is important to the liquid rocket engine and the ground test system thereof.
The existing ignition modes of rocket engines at present mainly comprise: and igniting the initiating explosive device by using a cartridge type ignition and the like. However, the current ignition mode has obvious defects generally.
Specifically, the main problems with initiating explosive device grain ignition include:
1) The manual filling is carried out before and after the fuel filling, so the requirement on personnel is very high, the environment for filling the fuel is generally at ultralow temperature, the environment is very severe, and the environmental risk coefficient of manual filling of operators is high.
2) The initiating explosive device grain is disposable, namely when the rocket engine ignition test is carried out on the ground, the initiating explosive device grain needs to be replaced once every time, each cost of the initiating explosive device grain is thousands of yuan, the purchase difficulty coefficient is large, the rocket engine ground test generally passes through the last ten tests, and therefore the comprehensive cost is very high.
3) The mounting structure of the initiating explosive device grain is very complex, and the filling accuracy requirement is very high.
The main problems with spark plug ignition are:
1) As the vacuum level decreases, the joule energy generated by the spark plug decreases. Therefore, if the spark plug type ignition is used after the secondary or tertiary rocket reaches a certain height, the failure of the rocket ignition due to insufficient joule energy generated is likely to occur, and finally the failure of the launching task is caused.
2) The common spark plug type ignition is serious in heating of the power supply module due to hundreds of ampere current discharge, and the temperature can rise by 60 ℃ generally for about 5 seconds, so that the loss of components is aggravated, and the reliability of products is not guaranteed.
Disclosure of Invention
The technical problem to be solved by the application is how to design an ignition device capable of effectively avoiding the problems; in view of this, the present application provides a rocket engine plasma igniter.
The technical scheme adopted by the application is that the rocket engine plasma igniter is arranged in a closed environment filled with a gas-liquid fuel mixture. Comprises an igniter head, a back pressure adapter and a power supply connector which are connected in sequence;
the power supply connector is connected with an external power supply, and responds to current pulse input of the external power supply to transmit the current pulse to the igniter head through the back pressure adapter;
the igniter head comprises a cathode layer, a dielectric layer and an anode layer which are annularly and sequentially arranged; the cathode layer and the anode layer generate potential difference after receiving the current pulse, and discharge occurs under the action of the medium layer, and joule energy generated by the discharge is used for igniting the gas-liquid fuel mixture.
In one embodiment, the anode layer and the cathode layer are made of metal, and the dielectric layer is made of ceramic.
In one embodiment, the surface of the dielectric layer is plated with a metal layer.
In one embodiment, the igniter head further comprises:
the igniter head insulating layer is wrapped outside the cathode layer and is made of ceramics;
and the igniter protecting shell is used for protecting other parts of the igniter head, and a thread structure is arranged on the outer side of the tail end and is used for being connected with an external structure to realize sealing.
In one embodiment, the backpressure adapter comprises: the cathode contact electrode, the inner insulating layer and the anode contact electrode are welded into a whole in an annular mode.
In one embodiment, the material of the cathode contact electrode comprises kovar alloy or oxygen-free copper, and is used for supplying power to the cathode layer;
the material of the inner insulating layer comprises ceramics, and is used for isolating the cathode contact electrode from the anode contact electrode;
the anode contact electrode is made of kovar alloy or oxygen-free copper and supplies power to the anode layer.
In one embodiment, the back pressure adapter further comprises:
the back pressure adapter housing is made of metal, is used for connecting the igniter head with the power supply connector and protecting the internal structure of the back pressure adapter;
the external insulation layer is made of ceramics, welded outside the cathode contact electrode and used for separating the back pressure adapter shell from the cathode contact electrode;
the isolation pad is made of ceramics, is arranged between the back pressure adapter and the igniter head along the radial direction, and is used for filling gaps and avoiding discharge of the cathode and the anode inside.
In one embodiment, the power connector includes: a cathode supply electrode, a power supply insulating layer and an anode supply electrode which are arranged in turn in a ring shape.
In one embodiment, the cathode supply electrode comprises a metal, and is in conduction with the cathode contact electrode;
the power supply insulating layer is made of an insulator and is used for isolating the cathode supply electrode and the anode supply electrode;
the anode supply electrode is made of metal and is communicated with the anode contact electrode.
By adopting the technical scheme, the embodiment provided by the application is simple to install and does not need manual filling before emission; the Joule energy cannot be changed along with the change of the external environment; can be used in high-pressure high-temperature combustion; the isolated high voltage does not break down with other components.
Drawings
FIG. 1 is a schematic view of the overall structure of a rocket engine plasma igniter according to an embodiment of the application;
FIG. 2 is a schematic cross-sectional view of a rocket engine plasma igniter according to an embodiment of the application;
FIG. 3 is a schematic cross-sectional view of an igniter protective housing according to an embodiment of the application;
FIG. 4 is a schematic cross-sectional view of an outer insulating layer according to an embodiment of the present application;
fig. 5 is a schematic cross-sectional view of a cathode contact according to an embodiment of the application.
Reference numerals
1-igniter protecting shell, 2-back pressure adapter shell, 3-outer insulating layer, 4-cathode contact electrode, 5-inner insulating layer, 6-anode contact electrode, 7-cathode supply electrode, 8-power supply insulating layer, 9-anode supply electrode, 10-isolation pad, 11-cathode layer, 12-dielectric layer, 13-anode layer and 14-igniter head insulating layer.
Detailed Description
In order to further describe the technical means and effects adopted by the present application for achieving the intended purpose, the following detailed description of the present application is given with reference to the accompanying drawings and preferred embodiments.
In the drawings, the thickness, size and shape of the object have been slightly exaggerated for convenience of explanation. The figures are merely examples and are not drawn to scale.
It will be further understood that the terms "comprises," "comprising," "includes," "including," "having," "containing," and/or "including," when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and/or groups thereof. Furthermore, when a statement such as "at least one of the following" appears after a list of features that are listed, the entire listed feature is modified instead of modifying a separate element in the list. Furthermore, when describing embodiments of the present application, the use of "may" means "one or more embodiments of the present application. Also, the term "exemplary" is intended to refer to an example or illustration.
As used herein, the terms "substantially," "about," and the like are used as terms of a table approximation, not as terms of a table level, and are intended to illustrate inherent deviations in measured or calculated values that would be recognized by one of ordinary skill in the art.
Unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. It will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the relevant art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein.
It should be noted that, without conflict, the embodiments of the present application and features of the embodiments may be combined with each other. The application will be described in detail below with reference to the drawings in connection with embodiments.
The embodiment of the application discloses a rocket engine plasma igniter, which is arranged in a closed environment filled with a gas-liquid fuel mixture as shown in fig. 1 to 5, and comprises an igniter head, a back pressure adapter and a power supply connector which are connected in sequence;
the power supply connector is connected with an external power supply, and responds to the current pulse input of the external power supply, and current pulses are transmitted to the igniter head through the back pressure adapter;
the igniter head comprises a cathode layer 11, a dielectric layer 12 and an anode layer 13 which are annularly and sequentially arranged; the cathode layer 11 and the anode layer 13 generate potential differences after receiving current pulses, and discharge occurs under the action of the medium layer 12, and joule energy generated by the discharge is used for igniting the gas-liquid fuel mixture.
In this embodiment, the igniter head is the means for generating a plasma arc and is the means for generating joule energy for igniting the fuel in the rocket engine. The components are an igniter protecting shell 1, a cathode layer 11, a dielectric layer 12, an anode layer 13 and an igniter head insulating layer 14.
Specifically, the igniter protecting shell 1 is made of metal, and is used for protecting the internal structure and connecting the tail threads with a torch chamber or a precombustion chamber of the rocket engine, so that the integral sealing performance is ensured.
The cathode layer 11 is made of metal, and serves to supply electrons during discharge, and is consumed to generate a large amount of plasma.
The dielectric layer 12 is made of ceramic, and the dielectric layer 12 of the traditional spark igniter is an insulator for isolating the cathode and the anode. This method requires a medium for discharge, and has a problem that the joule energy generated decreases as the air density decreases. The dielectric layer 12 of the present application is coated with a metal layer on the basis of a ceramic substrate, and the specific design ensures that the joule energy generated by the dielectric layer is not changed along with the change of the air density, and the dielectric layer is successfully realized and verified in actual engineering.
The anode layer 13 is made of metal and serves to provide a conductive circuit for the arc. And the metal used for the igniter head is the same as the metal of the panel in the combustion chamber, so that the condition of being melted at high temperature does not exist.
The igniter head insulating layer 14 is made of ceramic, and has the main function of wrapping the cathode inside the igniter head, so that the problem of common ground interference of the igniter head is conveniently solved on a power supply.
In this embodiment, the backpressure adapter provides power to the igniter head and seals the rocket engine flare chamber or precombustor from the outside. Because of the high pressure of 20MPa or more in the torch chamber or the precombustion chamber of the rocket engine, the igniter head needs a back pressure adapter to seal the rocket engine. The back pressure adapter is characterized in that annular ceramics are wrapped with annular metals with better ductility such as kovar alloy or oxygen-free copper and the like, and then the annular ceramics are wrapped, the back pressure adapter adopts a metal-ceramic welding process,
the assembly gaps of the annular parts of the cathode contact electrode 4, the inner insulating layer 5 and the anode contact electrode 6 are all welded by metal-ceramic, so that the high-voltage-resistant cathode contact electrode is ensured to have good conduction power supply capacity, the cathode and the anode are separated, and the internal discharge of the cathode and the anode is effectively avoided. The components are a back pressure adapter housing 2, an outer insulating layer 3, a cathode contact electrode 4, an inner insulating layer 5, an anode contact electrode 6 and a spacer 10.
Specifically, the back pressure adapter housing 2 is made of metal and is mainly used for connecting the igniter head with the power supply connector and protecting the internal structure of the back pressure adapter.
The outer insulating layer 3 is made of ceramics and mainly has the function of separating the shell from the cathode contact electrode 4, so that the problem of common ground interference of the igniter head is conveniently solved on a power supply.
The cathode contact electrode 4 is made of metal with better ductility such as kovar alloy or oxygen-free copper and can be welded with ceramics, and is mainly used for supplying power to the cathode.
The inner insulating layer 5 is made of ceramic, and has the main function of isolating the cathode and the anode, avoiding discharge in the inner part, and simultaneously welding the cathode and the anode together through a metal-ceramic welding process, thereby achieving the effect of back pressure sealing.
The anode contact electrode 6 is made of metal with better ductility such as kovar alloy or oxygen-free copper and can be welded with ceramics, and is mainly used for supplying power to the anode.
The spacer 10 is made of ceramic and is mainly used for filling gaps and preventing the internal discharge of the cathode and the anode.
In this embodiment, the main function of the power connector is to supply power to the igniter head by connecting with the back pressure adapter. The components are a cathode supply electrode 7, a power supply insulating layer 8 and an anode supply electrode 9.
The cathode supply electrode 7 is made of metal and mainly has the function of supplying power to the cathode of the igniter head through being pressed and conducted with the cathode contact electrode 4.
The power supply insulating layer 8 is made of an insulator such as plastic and is used for isolating the cathode and anode power supply electrodes and avoiding the discharge of the cathode and anode at the power supply joint.
The anode supply electrode 9 is made of metal and mainly has the function of supplying power to the anode of the igniter head through being pressed and conducted with the anode contact electrode 6.
In addition, in a preferred embodiment, the circuit boards used for the igniters in the prior art are all single circuit boards, and a single transformer, a triode and a capacitor are used for charging, discharging and supplying power to the igniters. Namely, the traditional mode has the problems that the circuit board is serious in heat generation and can not be used for a long time, and the high Wen Zaocheng component is serious in failure. This embodiment may employ split power supply.
Specifically, the split power type power supply is to divide a combined circuit of a transformer, a boosting module, a capacitor, a triode and the like into a plurality of circuit boards, the plurality of circuit boards are used for independently supplying power to a plasma igniter head, a singlechip is used for controlling output high-voltage pulses, the circuit boards are used for output synchronization by using a synchronization signal, and the high-voltage pulses output by different circuit boards are overlapped together, so that the high-voltage pulses meeting the use conditions are generated. The power device has the advantages that the use requirement is met, and meanwhile, the power is shared by the circuit boards, so that the heating value of the power device is greatly reduced, the high reliability of the circuit is effectively improved, the failure risk caused by the high temperature of the device is reduced, and the ignition time is prolonged.
In summary, compared with the prior art, the application has at least the following advantages:
1) The embodiment provides a novel rocket engine igniter which is simple to install and does not need to be manually filled before being emitted.
2) The embodiment provides a novel rocket engine igniter with Joule energy which is not changed along with the change of the external environment.
3) The embodiment provides a novel rocket engine igniter which can be used in high-pressure high-temperature combustion.
4) The embodiment provides a novel rocket engine igniter which is used for isolating high voltage and cannot break down other parts.
While the application has been described in connection with specific embodiments thereof, it is to be understood that these drawings are included in the spirit and scope of the application, it is not to be limited thereto.
Claims (9)
1. A rocket engine plasma igniter, wherein the igniter is disposed in a closed environment filled with a gas-liquid fuel mixture. Comprises an igniter head, a back pressure adapter and a power supply connector which are connected in sequence;
the power supply connector is connected with an external power supply, and responds to current pulse input of the external power supply to transmit the current pulse to the igniter head through the back pressure adapter;
the igniter head comprises a cathode layer, a dielectric layer and an anode layer which are annularly and sequentially arranged; the cathode layer and the anode layer generate potential difference after receiving the current pulse, and discharge occurs under the action of the medium layer, and joule energy generated by the discharge is used for igniting the gas-liquid fuel mixture.
2. A rocket engine plasma igniter according to claim 1 wherein the anode layer and cathode layer materials comprise metal and the dielectric layer materials comprise ceramic.
3. A rocket engine plasma igniter according to claim 2 wherein the surface of said dielectric layer is plated with a metal layer.
4. A rocket engine plasma igniter according to claim 3, wherein said igniter head further comprises:
the igniter head insulating layer is wrapped outside the cathode layer and is made of ceramics;
and the igniter protecting shell is used for protecting other parts of the igniter head, and a thread structure is arranged on the outer side of the tail end and is used for being connected with an external structure to realize sealing.
5. A rocket engine plasma igniter according to claim 1, wherein said back pressure adapter comprises: the cathode contact electrode, the inner insulating layer and the anode contact electrode are welded into a whole in an annular mode.
6. A rocket engine plasma igniter according to claim 5 wherein,
the cathode contact electrode is made of kovar alloy or oxygen-free copper and is used for supplying power to the cathode layer;
the material of the inner insulating layer comprises ceramics, and is used for isolating the cathode contact electrode from the anode contact electrode;
the anode contact electrode is made of kovar alloy or oxygen-free copper and supplies power to the anode layer.
7. A rocket engine plasma igniter according to claim 6, wherein said back pressure adapter further comprises:
the back pressure adapter housing is made of metal, is used for connecting the igniter head with the power supply connector and protecting the internal structure of the back pressure adapter;
the external insulation layer is made of ceramics, welded outside the cathode contact electrode and used for separating the back pressure adapter shell from the cathode contact electrode;
the isolation pad is made of ceramics, is arranged between the back pressure adapter and the igniter head along the radial direction, and is used for filling gaps and avoiding discharge of the cathode and the anode inside.
8. A rocket engine plasma igniter according to claim 6, wherein said power connection comprises: a cathode supply electrode, a power supply insulating layer and an anode supply electrode which are arranged in turn in a ring shape.
9. A rocket engine plasma igniter according to claim 8 wherein,
the cathode supply electrode is made of metal and is communicated with the cathode contact electrode;
the power supply insulating layer is made of an insulator and is used for isolating the cathode supply electrode and the anode supply electrode;
the anode supply electrode is made of metal and is communicated with the anode contact electrode.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310529269.8A CN116717398A (en) | 2023-05-11 | 2023-05-11 | Rocket engine plasma igniter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310529269.8A CN116717398A (en) | 2023-05-11 | 2023-05-11 | Rocket engine plasma igniter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116717398A true CN116717398A (en) | 2023-09-08 |
Family
ID=87870510
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310529269.8A Pending CN116717398A (en) | 2023-05-11 | 2023-05-11 | Rocket engine plasma igniter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116717398A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101158321A (en) * | 2007-05-18 | 2008-04-09 | 清华大学 | Low-temperature plasma non-hot point fire steadying flame device |
| US20100212620A1 (en) * | 2009-02-26 | 2010-08-26 | Ngk Insulators, Ltd. | Plasma igniter and ignition device for internal combustion engine |
| CN202718760U (en) * | 2012-05-29 | 2013-02-06 | 哈尔滨工程大学 | Plasma ignitor with reusable cathode |
| CN104612879A (en) * | 2015-01-19 | 2015-05-13 | 西安航天动力研究所 | High-back-pressure plasma igniter |
| CN112443401A (en) * | 2020-11-17 | 2021-03-05 | 中国人民解放军空军工程大学 | Jet arc-striking type long-distance high-energy plasma igniter |
| CN114991966A (en) * | 2022-06-08 | 2022-09-02 | 中国人民解放军空军工程大学 | Preionization type plasma igniter |
-
2023
- 2023-05-11 CN CN202310529269.8A patent/CN116717398A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101158321A (en) * | 2007-05-18 | 2008-04-09 | 清华大学 | Low-temperature plasma non-hot point fire steadying flame device |
| US20100212620A1 (en) * | 2009-02-26 | 2010-08-26 | Ngk Insulators, Ltd. | Plasma igniter and ignition device for internal combustion engine |
| CN202718760U (en) * | 2012-05-29 | 2013-02-06 | 哈尔滨工程大学 | Plasma ignitor with reusable cathode |
| CN104612879A (en) * | 2015-01-19 | 2015-05-13 | 西安航天动力研究所 | High-back-pressure plasma igniter |
| CN112443401A (en) * | 2020-11-17 | 2021-03-05 | 中国人民解放军空军工程大学 | Jet arc-striking type long-distance high-energy plasma igniter |
| CN114991966A (en) * | 2022-06-08 | 2022-09-02 | 中国人民解放军空军工程大学 | Preionization type plasma igniter |
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Inventor after: Wang Hongxia Inventor after: Su Yehuan Inventor before: Wang Hongxia Inventor before: Su Yehuan Inventor before: Xie Kan |