CN114718765A - Arc igniter for micro-nano satellite - Google Patents
Arc igniter for micro-nano satellite Download PDFInfo
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- CN114718765A CN114718765A CN202210412267.6A CN202210412267A CN114718765A CN 114718765 A CN114718765 A CN 114718765A CN 202210412267 A CN202210412267 A CN 202210412267A CN 114718765 A CN114718765 A CN 114718765A
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- 239000000843 powder Substances 0.000 claims abstract description 29
- 238000002485 combustion reaction Methods 0.000 claims abstract description 26
- 230000001590 oxidative effect Effects 0.000 claims abstract description 24
- 239000007800 oxidant agent Substances 0.000 claims abstract description 23
- 238000010891 electric arc Methods 0.000 claims abstract description 18
- 239000007788 liquid Substances 0.000 claims abstract description 10
- 238000003825 pressing Methods 0.000 claims abstract description 6
- 239000003721 gunpowder Substances 0.000 claims abstract description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 14
- 229910052799 carbon Inorganic materials 0.000 claims description 10
- 239000000463 material Substances 0.000 claims description 9
- 239000004215 Carbon black (E152) Substances 0.000 claims description 7
- 229930195733 hydrocarbon Natural products 0.000 claims description 7
- 150000002430 hydrocarbons Chemical class 0.000 claims description 7
- 230000015556 catabolic process Effects 0.000 claims description 6
- 238000000197 pyrolysis Methods 0.000 claims description 6
- 239000000446 fuel Substances 0.000 claims description 5
- 230000006698 induction Effects 0.000 claims description 5
- 238000007789 sealing Methods 0.000 claims description 5
- 239000002360 explosive Substances 0.000 claims description 4
- 229920001169 thermoplastic Polymers 0.000 claims description 4
- 238000004891 communication Methods 0.000 claims description 3
- 238000009792 diffusion process Methods 0.000 claims description 3
- 239000000126 substance Substances 0.000 claims description 3
- 238000011144 upstream manufacturing Methods 0.000 claims description 3
- 230000001939 inductive effect Effects 0.000 claims description 2
- 230000001737 promoting effect Effects 0.000 claims description 2
- 239000007789 gas Substances 0.000 description 8
- 238000000034 method Methods 0.000 description 7
- XECAHXYUAAWDEL-UHFFFAOYSA-N acrylonitrile butadiene styrene Chemical compound C=CC=C.C=CC#N.C=CC1=CC=CC=C1 XECAHXYUAAWDEL-UHFFFAOYSA-N 0.000 description 5
- 229920000122 acrylonitrile butadiene styrene Polymers 0.000 description 5
- 239000004676 acrylonitrile butadiene styrene Substances 0.000 description 5
- 238000005516 engineering process Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 239000003795 chemical substances by application Substances 0.000 description 2
- 229910002804 graphite Inorganic materials 0.000 description 2
- 239000010439 graphite Substances 0.000 description 2
- 229920000642 polymer Polymers 0.000 description 2
- 239000002861 polymer material Substances 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 238000010146 3D printing Methods 0.000 description 1
- 229910018487 Ni—Cr Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 230000003197 catalytic effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- VNNRSPGTAMTISX-UHFFFAOYSA-N chromium nickel Chemical compound [Cr].[Ni] VNNRSPGTAMTISX-UHFFFAOYSA-N 0.000 description 1
- 230000008094 contradictory effect Effects 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
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- 238000002474 experimental method Methods 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 231100000252 nontoxic Toxicity 0.000 description 1
- 230000003000 nontoxic effect Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 229920001568 phenolic resin Polymers 0.000 description 1
- 239000004033 plastic Substances 0.000 description 1
- 229920003023 plastic Polymers 0.000 description 1
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- 230000003068 static effect Effects 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
- 239000002023 wood Substances 0.000 description 1
Images
Classifications
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- 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
- F02K9/72—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid and solid propellants, i.e. hybrid rocket-engine plants
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
Abstract
The invention discloses an electric arc igniter for a micro-nano satellite, which comprises an igniter shell, an ignition powder column, a liquid oxidant, a nozzle fixing piece, a nozzle, an end cover, a conductive channel, two electrode pressing blocks, two insulating sleeves and two electrodes, wherein the ignition powder column is arranged on the igniter shell; the head part of the igniter shell is fixed with a nozzle through a nozzle fixing piece, the tail part of the igniter shell is fixed with an end cover, the ignition powder column is fixed in the igniter shell, a circular groove is formed in the center of the head part of the ignition powder column to serve as a pre-combustion chamber, and an arc-shaped groove directly communicated with the circular groove is formed in one side of the circular groove; open on the end cover has central through-hole to set up two electrodes, the electrode is kept apart through insulating boot outward, and two electrodes stretch into again after the both ends of the arc wall of point gunpowder column respectively and meander to its center along the arc wall, fix through the electrode briquetting respectively, and two electrode tip that meander realize the intercommunication through electrically conductive passageway. The invention has low ignition instantaneous power, can realize multiple start and stop of the solid-liquid mixed engine, and is suitable for a micro/nano satellite platform with multiple maneuvering requirements.
Description
Technical Field
The invention belongs to the ignition technology of an engine, and particularly relates to an electric arc igniter for a micro-nano satellite.
Background
In recent years, with the continuous progress of science and technology, the threshold of entering the air is continuously reduced, and the micro-nano satellite is continuously expanded in the civil and commercial fields. The material has already shown a tendency of 'explosive' growth due to low cost and short development period. In the orbit active micro-nano satellites, 46.6 percent of the orbit active micro-nano satellites are technical test satellites, and the space environments with different orbit heights have obvious difference, so that large-scale orbit maneuvering is realized, and the method has great significance for verifying that components and technologies correspond to different space environments.
The orbit transfer of the current satellite is mainly realized by a satellite-borne thruster, and common ignition modes of the thruster comprise catalytic ignition, plasma ignition, torch ignition and the like, but the modes have the problem of overhigh power and limit the application of the thruster to the micro-nano satellite.
CN201410599049.3 discloses a secondary insensitive electric igniter for direct current ignition, which adopts new ignition agent, new explosive head agent, improved charging space and optimized bridgewire structure to solve the technical requirements of resistance, insulation resistance, safe current, ignition current, instantaneous degree, static electricity prevention and the like and the energy output requirement of the electric igniter. However, the ignition process cannot be controllably stopped, all the ignition charges are completely combusted after one ignition, the second or more ignitions cannot be realized, and multiple reliable ignitions cannot be realized.
Wupeng, in the article "attitude control engine arc ignition system based on single chip microcomputer control", adopts a high-voltage pack to generate high-voltage breakdown air, and high-temperature electric arcs generated by breakdown directly ignite mixed gas of oxidant and fuel. However, the voltage is only determined to be unable to break down the air, when the air breaks down, the electric arc is determined to be the power of the electric arc, the power of the electric arc is derived from the power output by the electric arc discharge circuit, and the circuit is required to increase enough power for igniting the mixed gas. In the article, the instantaneous power of ignition reaches 24W, and if the ignition device is used for a micro-nano satellite platform, a great load is caused on a power supply system of a satellite.
Disclosure of Invention
The invention aims to provide an electric arc igniter for a micro-nano satellite, which is applied to a micro-nano satellite solid-liquid mixing thruster and aims to meet the requirement of multiple ignition in a large-range and multiple maneuvering process of the micro-nano satellite.
The technical solution for realizing the invention is as follows: an electric arc igniter for a micro-nano satellite comprises an igniter shell, an ignition powder column, a liquid oxidant, a nozzle fixing piece, a nozzle, an end cover, a conductive channel, two electrode pressing blocks, two insulating sleeves and two electrodes; the igniter shell is cylindrical, the nozzle is fixed at the head of the igniter shell through the nozzle fixing piece, the end cover is fixed at the tail of the igniter shell, the ignition powder column is fixed in the igniter shell, the head of the ignition powder column is in contact with the tail of the end cover, and the tail of the ignition powder column is not in contact with the head of the nozzle to form a combustion cavity; the ignition powder column is provided with a second flow passage with a central through hole as an oxidant, the center of the head part of the ignition powder column is provided with a circular groove as a precombustion chamber, the circular groove is communicated with the second flow passage, the head part of the ignition powder column is also provided with an arc-shaped groove positioned on one side of the circular groove, and the arc-shaped groove and the circular groove are directly provided with a first passage for communication; the end cover is provided with a central through hole as a first flow channel of an oxidant, the end cover is also provided with two electrode mounting holes, the two electrode mounting holes are symmetrically distributed around the central through hole, an electrode is arranged in each electrode mounting hole, the electrodes and the electrode mounting holes are isolated by insulating sleeves, the two electrodes respectively extend into two ends of an arc-shaped groove of the gunpowder column and then meander to the center of the arc-shaped groove along the arc-shaped groove, the two electrodes are respectively fixed by electrode pressing blocks, and the end parts of the two meandering electrodes are communicated through a conductive channel;
applying voltage to the electrodes, when the voltage at two ends of a conductive channel at the tail end of each electrode exceeds a threshold value, generating electric breakdown between the two electrodes under the induction of the conductive channel to generate high-temperature electric arcs and further generate high-temperature hydrocarbon steam, starting for a period of time, enabling an oxidant flow to enter the precombustion chamber from a first flow channel at the upstream, enabling the oxidant flow to contact with the high-temperature hydrocarbon steam to start combustion to form a flame kernel, continuously pyrolyzing the flame kernel and igniting an ignition explosive column in downward propagation, forming a high-temperature and high-pressure environment in the combustion chamber, further promoting the pyrolysis of fuel, forming diffusion combustion after being mixed with oxidant gas, further improving the temperature of the flame and the pressure in the combustion chamber, and realizing reliable ignition of subsequent main charges after being sprayed out through the nozzle; in the event that the initial conductive path is depleted after multiple ignitions of the igniter, the burned mass of the ignition charge still acts to induce an arc between the two electrodes.
Compared with the prior art, the invention has the remarkable advantages that:
(1) according to the invention, the ignition principle of polymer low-voltage breakdown is adopted, compared with other ignition modes, the power consumption at the moment of ignition is reduced to 3w to the lowest extent, and the method is more suitable for a micro-nano satellite platform with the limited total power of a power supply.
(2) The invention utilizes the characteristic that the carbonizable polymer forms a carbon layer after burning, and uses the carbon layer to induce the generation of electric arc, thereby realizing the multiple starting ignition of the igniter.
(3) The ignition powder adopts thermoplastic polymer materials such as ABS and the like, can be manufactured into various ignition powder columns by FDM technology, is simple to manufacture, and is non-toxic and pollution-free to the environment.
Drawings
Fig. 1 is a schematic diagram of the overall structure of an arc igniter for a micro/nano satellite according to the invention.
Fig. 2 is a schematic diagram of an ignition charge column head of the electric arc igniter for the micro-nano satellite according to the invention.
Fig. 3 is a schematic diagram showing the relationship between the ignition charge and the electrodes of the arc igniter for the micro/nano satellite according to the invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely 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 inventive step, are within the scope of the present invention.
It should be noted that all the directional indicators (such as upper, lower, left, right, front and rear … …) in the embodiment of the present invention are only used to explain the relative position relationship between the components, the movement situation, etc. in a specific posture (as shown in the drawings), and if the specific posture is changed, the directional indicator is changed accordingly.
In addition, the descriptions related to "first", "second", etc. in the present invention are only for descriptive purposes and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of the feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless explicitly specifically defined otherwise.
In the present invention, unless otherwise expressly specified or limited, the terms "connected," "secured," and the like are to be construed broadly, e.g., "secured" may be fixedly connected, releasably connected, or integral; "connected" may be mechanically or electrically connected. The specific meanings of the above terms in the present invention can be understood according to specific situations by those of ordinary skill in the art.
In addition, the technical solutions in the embodiments of the present invention may be combined with each other, but it must be based on the realization of those skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination of technical solutions should not be considered to exist, and is not within the scope of the claimed invention.
The following further introduces specific embodiments, technical difficulties and inventions of the present invention with reference to the design examples.
With reference to fig. 1 to 3, the electric arc igniter for the micro-nano satellite comprises an igniter shell 1, an ignition powder column 2, a liquid oxidant, a nozzle fixing piece 3, a nozzle 4, an end cover 7, a conductive channel 9, two insulating sleeves 5, two electrodes 6 and two electrode pressing blocks 10. The igniter shell 1 is cylindrical, the nozzle 4 is fixed at the head of the igniter shell 1 through the nozzle fixing piece 3, and the nozzle fixing piece 3 is fixedly connected with the igniter shell 1 through threads. The end cover 7 is fixed at the tail part of the igniter shell 1 through a screw, the ignition charge column 2 is fixed in the igniter shell 1, the head part of the ignition charge column 2 is contacted with the tail part of the end cover 7, and a combustion cavity is formed between the tail part of the ignition charge column 2 and the head part of the nozzle 4 without contact. The ignition powder column 2 is provided with a second flow passage with a central through hole as an oxidant, the center of the head of the ignition powder column 2 is provided with a circular groove as a precombustion chamber, the circular groove is communicated with the second flow passage, the inner diameter of the circular groove is larger than that of the second flow passage, the head of the ignition powder column 2 is also provided with an arc-shaped groove positioned on one side of the circular groove, and the arc-shaped groove and the circular groove are directly provided with a first passage for communication. Open the first runner that has central through hole as the oxidant on the end cover 7, still be equipped with two electrode mounting holes on the end cover 7, two electrode mounting holes are about central through hole symmetric distribution, be equipped with an electrode 6 in every electrode mounting hole, keep apart through insulating boot 5 between electrode 6 and the electrode mounting hole, two electrodes stretch into again after the both ends of the arc wall of ignition charge post 2 along the arc wall meandering to its center respectively, fix through electrode briquetting 10 respectively, two meandering electrode tip realize the intercommunication through electrically conductive passageway 9. The electrode 6 is ignited, the ignition powder column 2 is pyrolyzed, meanwhile, the liquid oxidant enters through the first flow channel of the nozzle 4 and forms flame with the pyrolyzed ignition powder column 2, and the flame is sprayed out of the nozzle 4 after sequentially passing through the second flow channel and the combustion cavity.
The electric arc igniter for the micro-nano satellite further comprises a sealing ring 8, wherein the sealing ring 8 is arranged between the igniter shell 1 and the end cover 7, and a gap is formed between the igniter shell 1 and the end cover 7 in a sealing mode, so that high-temperature gas is prevented from being reversely sprayed out from the gap in the ignition process.
The nozzle 4 adopts a Laval nozzle, the front section is designed in a shrinkage mode to improve the pressure in a combustion chamber, so that the combustion temperature is higher and more sufficient, and the rear section is an expansion section to improve the flow rate of gas entering a main combustion chamber.
The conductive path 9 uses graphite powder as an arc-inducing path.
The inner wall of the igniter shell 1 is provided with a step surface for matching with the end cover 7 to realize the positioning and fixing of the ignition charge 2.
The igniter shell 1, the nozzle fixing piece 3 and the end cover 7 are made of 30CrMnSi materials, the electrode 6 is made of nickel-chromium high-temperature-resistant alloy, and the insulating sleeve 5 is made of phenolic plastics filled with wood. The ignition charge 2 and the electrode compact 10 are both ABS materials manufactured using a selected carbonizable thermoplastic polymer, such as 3D printing.
In the invention, the ignition powder column 2 adopts ABS (acrylonitrile-butadiene-styrene plastic), after receiving an ignition signal, a voltage of about 300V is applied to the electrode 6, when the voltage at two ends of the conductive channel 9 at the tail end of the electrode 6 exceeds a threshold value, under the induction of graphite, electric breakdown occurs between the two electrodes 6, high-temperature electric arc is generated, so that the ABS material is subjected to stable pyrolysis, and combustible gas and particles mainly comprising hydrocarbon are generated. The pyrolyzed fuel gas is mixed with the oxidizing gas entering the first flow channel to form a flame kernel, and the large amount of pyrolysis ignition powder columns 2 are propagated downstream along the way, so that sufficient supply of fuel and oxidant is ensured, and continuous and stable combustion is realized. A high-temperature and high-pressure environment is formed in the combustion cavity, so that pyrolysis of the fuel is further promoted, diffusion combustion is formed after the pyrolysis is mixed with oxidant gas, the temperature of flame and the pressure in the combustion cavity are further increased, and reliable ignition of subsequent main charge is realized after the flame is sprayed out through the nozzle 4. The thermoplastic polymer that can carbonize of ignition charge 2 material selection, this type of polymer material can form more carbon simple substance in the combustion process, covers and forms denser carbon layer at the internal surface of ignition charge 2, and this characteristic has guaranteed that under the condition that initial conducting channel 9 was consumed and is used up after the ignition many times of ignitor, still there is the material to play the effect of induced electric arc between two electrodes 6. The conductive channel 9 arranged on the surface of the ignition charge column 2 is far away from the second flow channel of the ignition charge column 2. The head of the ignition charge column 2 is designed with a precombustion chamber with a diameter far larger than that of the second flow passage, so that the temperature of the head of the whole ignition charge column 2 is relatively lower than that of the second flow passage, the speed of oxidation reaction of carbon simple substances is reduced, and the generated carbon layer can be fully reserved. The first passage is configured to enable propagation of an initial flame from the path downstream.
The working process of the electric arc igniter for the micro-nano satellite comprises the following steps: after the solid-liquid mixed engine is controlled to send out an ignition signal, 300V voltage is applied between the two electrodes 6, the two electrodes 6 are rapidly punctured through the conductive channel 9 to generate electric arcs, high-temperature hydrocarbon steam is generated, oxidant flow enters the precombustion chamber from the upstream first flow channel after being started for a period of time, contacts with the high-temperature hydrocarbon steam to start combustion, is continuously pyrolyzed and ignites the ignition charge 2 in downward propagation, continuously strengthens the combustion process, and is ejected into a main combustion cavity of the engine through the nozzle 4 after passing through the combustion cavity to ignite the main charge. By cutting off the supply of liquid oxidant when it is desired to stop operation. The electric arc igniter can spontaneously stop reaction, and the ignition of the igniter is realized. When subsequent re-ignition is required, the ignition process described above is repeated, with the structure acting to induce arc generation being changed from the conductive paths 9 to the residual carbon layer resulting from the previous ignition, again resulting in successful ignition of the igniter.
The igniter is low in ignition power, simple in structure and capable of realizing stable ignition for more than 10 times, and ignition delay time is less than 0.2s in a ground test.
Experiments prove that when the liquid oxidant adopts oxygen and the material of the induction path is graphite, the instantaneous power consumption of the ignition device is 3 w.
Claims (6)
1. An electric arc igniter for a micro-nano satellite comprises an igniter shell (1), an ignition powder column (2), a liquid oxidant, a nozzle fixing piece (3), a nozzle (4), an end cover (7), two insulating sleeves (5) and two electrodes (6); some firearm casing (1) are cylindric, and nozzle (4) are fixed at the head of some firearm casing (1) through nozzle mounting (3), and end cover (7) are fixed at the afterbody of some firearm casing (1), its characterized in that: the ignition powder ignition device is characterized by further comprising a conductive channel (9) and two electrode pressing blocks (10), the ignition powder column (2) is fixed in the igniter shell (1), the head of the ignition powder column (2) is in contact with the tail of the end cover (7), and a combustion cavity is formed between the tail of the ignition powder column (2) and the head of the nozzle (4) in a non-contact mode; the ignition powder column (2) is provided with a second flow passage with a central through hole as an oxidant, the center of the head part of the ignition powder column (2) is provided with a circular groove as a precombustion chamber, the circular groove is communicated with the second flow passage, the head part of the ignition powder column (2) is also provided with an arc-shaped groove positioned on one side of the circular groove, and the arc-shaped groove and the circular groove are directly provided with a first passage for communication; the end cover (7) is provided with a central through hole as a first flow channel of an oxidant, the end cover (7) is also provided with two electrode mounting holes, the two electrode mounting holes are symmetrically distributed around the central through hole, an electrode (6) is arranged in each electrode mounting hole, the electrodes (6) and the electrode mounting holes are isolated by an insulating sleeve (5), the two electrodes (6) respectively extend into two ends of an arc-shaped groove of the gunpowder column (2) and then meander towards the center of the arc-shaped groove along the arc-shaped groove and are respectively fixed by an electrode pressing block (10), and the end parts of the two meandering electrodes are communicated through a conductive channel (9);
applying voltage to the electrodes (6), when the voltage at two ends of a conductive channel (9) at the tail end of each electrode (6) exceeds a threshold value, generating electric breakdown between the two electrodes (6) under the induction of the conductive channel (9) to generate high-temperature electric arcs and further generate high-temperature hydrocarbon steam, enabling an oxidant flow to enter the precombustion chamber from a first flow channel at the upstream after starting for a period of time, enabling the oxidant flow to contact with the high-temperature hydrocarbon steam to start combustion to form flame nuclei, continuously pyrolyzing and igniting the ignition explosive columns (2) in downward propagation to form a high-temperature high-pressure environment in the combustion chamber, further promoting the pyrolysis of fuel, mixing with oxidant gas to form diffusion combustion, further improving the temperature of flame and the pressure in the combustion chamber, and realizing reliable ignition of subsequent main charges after being sprayed out through the nozzle (4); in the event that the initial conductive path (9) is depleted after multiple ignitions of the igniter, the burned material of the ignition charge (2) still acts to induce an arc between the two electrodes (6).
2. The arc igniter for the micro-nano satellite according to claim 1, wherein: the material of the ignition charge column (2) is selected from a carbonizable thermoplastic polymer, which can form a carbon simple substance in the combustion process, a compact carbon layer is formed on the inner surface of the ignition charge column (2) in a covering mode, and after the igniter ignites for multiple times, the initial conductive channel (9) is consumed completely, and the carbon layer after the ignition charge column (2) burns still plays a role in inducing electric arc between the two electrodes (6).
3. The arc igniter for the micro-nano satellite according to claim 1, wherein: the inner diameter of the circular groove is larger than that of the second flow passage.
4. The arc igniter for the micro-nano satellite according to claim 1, wherein: still include sealing washer (8), sealing washer (8) set up between ignitor casing (1) and end cover (7).
5. The arc igniter for the micro-nano satellite according to claim 1, wherein: the conductive channel (9) adopts graphite powder as an arc induction path.
6. The arc igniter for the micro-nano satellite according to claim 1, wherein: the diameter of the precombustion chamber at the head of the ignition charge column (2) is far larger than that of the second flow passage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210412267.6A CN114718765A (en) | 2022-04-19 | 2022-04-19 | Arc igniter for micro-nano satellite |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210412267.6A CN114718765A (en) | 2022-04-19 | 2022-04-19 | Arc igniter for micro-nano satellite |
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| Publication Number | Publication Date |
|---|---|
| CN114718765A true CN114718765A (en) | 2022-07-08 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210412267.6A Pending CN114718765A (en) | 2022-04-19 | 2022-04-19 | Arc igniter for micro-nano satellite |
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| Country | Link |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5485721A (en) * | 1993-06-30 | 1996-01-23 | Erno Raumfahrttechnik Gmbh | Arcjet for a space flying body |
| US20150322892A1 (en) * | 2012-07-30 | 2015-11-12 | Utah State University | Restartable Ignition Devices, Systems, and Methods Thereof |
| CN110714855A (en) * | 2018-07-12 | 2020-01-21 | 南京理工大学 | Electric control power device with real-time controllable thrust and capable of repeatedly igniting and extinguishing |
| US20200370513A1 (en) * | 2012-07-30 | 2020-11-26 | Utah State University | Thrust augmentation of an additively manufactured hybrid rocket system using secondary oxidizer injection |
-
2022
- 2022-04-19 CN CN202210412267.6A patent/CN114718765A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5485721A (en) * | 1993-06-30 | 1996-01-23 | Erno Raumfahrttechnik Gmbh | Arcjet for a space flying body |
| US20150322892A1 (en) * | 2012-07-30 | 2015-11-12 | Utah State University | Restartable Ignition Devices, Systems, and Methods Thereof |
| US20200370513A1 (en) * | 2012-07-30 | 2020-11-26 | Utah State University | Thrust augmentation of an additively manufactured hybrid rocket system using secondary oxidizer injection |
| CN110714855A (en) * | 2018-07-12 | 2020-01-21 | 南京理工大学 | Electric control power device with real-time controllable thrust and capable of repeatedly igniting and extinguishing |
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Application publication date: 20220708 |