CN110259605A - A kind of ADN base single group member thruster of low-temperature plasma synergistic catalysis - Google Patents
A kind of ADN base single group member thruster of low-temperature plasma synergistic catalysis Download PDFInfo
- Publication number
- CN110259605A CN110259605A CN201910513121.9A CN201910513121A CN110259605A CN 110259605 A CN110259605 A CN 110259605A CN 201910513121 A CN201910513121 A CN 201910513121A CN 110259605 A CN110259605 A CN 110259605A
- Authority
- CN
- China
- Prior art keywords
- section
- anode
- adn
- insulator
- group member
- Prior art date
- 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.)
- Granted
Links
- 238000006555 catalytic reaction Methods 0.000 title claims abstract description 25
- 230000002195 synergetic effect Effects 0.000 title claims abstract description 17
- 239000012212 insulator Substances 0.000 claims abstract description 48
- 230000003197 catalytic effect Effects 0.000 claims abstract description 36
- 238000002485 combustion reaction Methods 0.000 claims abstract description 28
- 239000007788 liquid Substances 0.000 claims abstract description 27
- 239000003380 propellant Substances 0.000 claims abstract description 25
- 238000012360 testing method Methods 0.000 claims abstract description 17
- 239000007921 spray Substances 0.000 claims abstract description 14
- 239000000463 material Substances 0.000 claims description 15
- 239000003054 catalyst Substances 0.000 claims description 14
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 12
- 229910002804 graphite Inorganic materials 0.000 claims description 12
- 239000010439 graphite Substances 0.000 claims description 12
- 239000010453 quartz Substances 0.000 claims description 12
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N silicon dioxide Inorganic materials O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 12
- OKKJLVBELUTLKV-UHFFFAOYSA-N Methanol Chemical compound OC OKKJLVBELUTLKV-UHFFFAOYSA-N 0.000 claims description 9
- 210000004907 gland Anatomy 0.000 claims description 9
- 239000003708 ampul Substances 0.000 claims description 8
- 238000007789 sealing Methods 0.000 claims description 7
- 239000012530 fluid Substances 0.000 claims description 6
- 239000000446 fuel Substances 0.000 claims description 6
- 239000008187 granular material Substances 0.000 claims description 6
- 239000007800 oxidant agent Substances 0.000 claims description 5
- 230000001590 oxidative effect Effects 0.000 claims description 5
- 229910001369 Brass Inorganic materials 0.000 claims description 4
- 230000004888 barrier function Effects 0.000 claims description 4
- 239000010951 brass Substances 0.000 claims description 4
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 4
- 239000010963 304 stainless steel Substances 0.000 claims description 3
- 229910000589 SAE 304 stainless steel Inorganic materials 0.000 claims description 3
- 229910045601 alloy Inorganic materials 0.000 claims description 3
- 239000000956 alloy Substances 0.000 claims description 3
- 238000009413 insulation Methods 0.000 claims description 3
- 239000002608 ionic liquid Substances 0.000 claims description 3
- 229910052741 iridium Inorganic materials 0.000 claims description 3
- GKOZUEZYRPOHIO-UHFFFAOYSA-N iridium atom Chemical compound [Ir] GKOZUEZYRPOHIO-UHFFFAOYSA-N 0.000 claims description 3
- 229910052751 metal Inorganic materials 0.000 claims description 3
- 239000002184 metal Substances 0.000 claims description 3
- 229910000510 noble metal Inorganic materials 0.000 claims description 3
- 239000002904 solvent Substances 0.000 claims description 3
- 229910001220 stainless steel Inorganic materials 0.000 claims description 3
- 239000004575 stone Substances 0.000 claims description 2
- 239000003795 chemical substances by application Substances 0.000 claims 1
- 230000006835 compression Effects 0.000 abstract description 4
- 238000007906 compression Methods 0.000 abstract description 4
- 238000010494 dissociation reaction Methods 0.000 abstract description 4
- 230000005593 dissociations Effects 0.000 abstract description 4
- 239000007789 gas Substances 0.000 description 25
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 14
- 238000013461 design Methods 0.000 description 11
- 229910052786 argon Inorganic materials 0.000 description 7
- 230000000694 effects Effects 0.000 description 6
- 238000000034 method Methods 0.000 description 6
- OAKJQQAXSVQMHS-UHFFFAOYSA-N Hydrazine Chemical compound NN OAKJQQAXSVQMHS-UHFFFAOYSA-N 0.000 description 4
- 230000008901 benefit Effects 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 238000010438 heat treatment Methods 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 239000000243 solution Substances 0.000 description 3
- QGZKDVFQNNGYKY-UHFFFAOYSA-O Ammonium Chemical compound [NH4+] QGZKDVFQNNGYKY-UHFFFAOYSA-O 0.000 description 2
- 238000007664 blowing Methods 0.000 description 2
- 229910010293 ceramic material Inorganic materials 0.000 description 2
- 239000000470 constituent Substances 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 230000008014 freezing Effects 0.000 description 2
- 238000007710 freezing Methods 0.000 description 2
- 230000002779 inactivation Effects 0.000 description 2
- 239000013067 intermediate product Substances 0.000 description 2
- 230000003287 optical effect Effects 0.000 description 2
- 238000005245 sintering Methods 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- BRUFJXUJQKYQHA-UHFFFAOYSA-O ammonium dinitramide Chemical compound [NH4+].[O-][N+](=O)[N-][N+]([O-])=O BRUFJXUJQKYQHA-UHFFFAOYSA-O 0.000 description 1
- 210000000988 bone and bone Anatomy 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 239000003638 chemical reducing agent Substances 0.000 description 1
- 230000002153 concerted effect Effects 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 239000000945 filler Substances 0.000 description 1
- 230000008570 general process Effects 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 231100000614 poison Toxicity 0.000 description 1
- 230000007096 poisonous effect Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000012797 qualification Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 229910052594 sapphire Inorganic materials 0.000 description 1
- 239000010980 sapphire Substances 0.000 description 1
- 239000010935 stainless steel Substances 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000005979 thermal decomposition reaction Methods 0.000 description 1
- 230000001988 toxicity Effects 0.000 description 1
- 231100000419 toxicity Toxicity 0.000 description 1
- 230000009466 transformation Effects 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
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
-
- 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
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Plasma Technology (AREA)
Abstract
The embodiment of the invention discloses a kind of ADN base single group member thrusters of low-temperature plasma synergistic catalysis, including the coaxial sequentially connected spray section of one, ionization section, catalytic section, combustion chamber；The both ends of spray section and ionization section are compressed by forward flange disk and middle ring flange；The integral structure and ionization section that catalytic section and combustion chamber are formed are compressed by middle ring flange and rear stub；Spray section includes forward flange disk, preceding insulator and anode chassis and the gas supply liquid supply pipe for being respectively configured to provide ADN liquid propellant and gas；Ionization section include with the sequentially connected cylindric anode in anode chassis, middle insulator, tubular cathode, rear insulator and middle ring flange, between middle ring flange and forward flange disk by lock-screw cooperation compression；Catalytic section includes rear stub and catalytic bed；Combustion chamber includes optic test window and the sensor joint chair that one side is reserved, and the present invention has diversified sparking mode, significant to the sparking mode for changing existing catalysis dissociation completely.
Description
Technical field
The present embodiments relate to space chemical propulsion technologies and electric thruster design field, and in particular to a kind of low
The ADN base single group member thruster of isothermal plasma concerted catalysis.
Background technique
Diamide ammonium (Ammonium Dinitramide, be abbreviated as ADN) thruster is that a kind of development potentiality is huge
Push Technology, ADN base propellant are made of diamide ammonium, fuel and water, and with small toxicity, pollution-free, freezing point is low, stability
High, the advantages that volatility is small, it is new a developing direction and research hotspot of space technology, is with a wide range of applications.
For conventional propellant anhydrous hydrazine, ADN base propellant unique advantage prevents it in R&D process without special
Shield measure, and can be realized the pre-packaged of space power system, the capability of fast response and mobility of system is substantially improved.
ADN base single group member thruster has had certain space-orbit flight experience at present, but is all logical without exception
Cross the mode of catalysis dissociation.Its development bottleneck be high temperature when propellant combustion will lead to catalysis bed structure collapsing sintering with
And the inactivation of active constituent, the normal work of thruster is directly affected, needs additional input to heat function to light a fire with pre-heating system
Rate, sparking mode is single, and developing new sparking mode is the effective means to solve the above problems.
Summary of the invention
For this purpose, the embodiment of the present invention provides a kind of ADN base single group member thruster of low-temperature plasma synergistic catalysis, with solution
The certainly single problem of thruster sparking mode in the prior art.
To achieve the goals above, the embodiment of the present invention provides the following technical solutions:
A kind of ADN base single group member thruster of low-temperature plasma synergistic catalysis, including the coaxial sequentially connected spray of one
Section, ionization section, catalytic section, four segment structure of combustion chamber are infused, the spray section and the both ends for ionizing section pass through forward flange disk and middle method
Blue disk compresses；The integral structure and ionization section that the catalytic section and combustion chamber are formed are compressed by middle ring flange and rear stub；
The spray section include sequentially connected forward flange disk, preceding insulator and anode chassis and sequentially pass through it is described before
Ring flange, preceding insulator and anode chassis are respectively configured to provide the gas supply liquid supply pipe of ADN liquid propellant and gas, the gas supply
The through-hole cooperation conveying propellant and gas of the tail end of liquid supply pipe and the setting of anode chassis；
The ionization section includes and the sequentially connected cylindric anode in anode chassis, middle insulator, tubular cathode, rear insulation
Body and middle ring flange are cooperated by lock-screw between the middle ring flange and forward flange disk and are compressed, and in the tubular yin
Pole inner surface is equipped with dielectric；Ionization section is additionally provided with electrode terminal；
The catalytic section includes rear stub and catalytic bed, and the rear stub, catalytic bed and combustion chamber are structure as a whole,
Cooperate between middle ring flange and rear stub also through lock-screw and compresses；
The combustion chamber includes the optic test window and sensor joint chair reserved on one side for being opened in three faces respectively.
The embodiment of the present invention is further characterized in that the ADN liquid propellant is monopropellant, including oxidant
(ADN), ionic liquid fuel (methanol) and solvent (water).
The embodiment of the present invention is further characterized in that the inside groove and preceding insulator of the forward flange disk inner side end cooperate；Circle
Column anode, middle insulator and tubular cathode are around the mutually matched ladder shaft like parts of central axis；Tubular cathode and anode
Radial positioning is realized by insulator in ladder shaft-like between chassis.
The embodiment of the present invention is further characterized in that each component end face is designed with the internal annular for being equipped with soft graphite washer
Slot realizes the sealing between axially position and anode and cathode and insulator by soft graphite washer.
The embodiment of the present invention is further characterized in that the cylindric anode and anode chassis are designed for integral type, anode bottom
The gas supply of the inside nozzle of connection gas supply liquid supply pipe is provided on disk for fluid through-hole, the gas supply is that annular array is double for fluid through-hole
Layer structure, 6 through-holes of internal layer, 8 through-holes of outer layer, diameter is 1.5mm.
The embodiment of the present invention is further characterized in that the dielectric is quartz ampoule, quartzy tube outer surface and tubular cathode
Inner surface cooperation, realization is quartz ampoule radial positioning；The quartz ampoule is realized by the clearance fit of middle insulator, rear stub
Axially position, quartzy pipe outside diameter are 12mm, and internal diameter is adjustable.
The embodiment of the present invention is further characterized in that the catalytic bed includes catalyst granules, and the catalyst granules is iridium
Base catalyst and other kinds of noble metal-based catalysts；The length of the catalytic bed is 0~33mm.
The embodiment of the present invention is further characterized in that, except the gas supply liquid supply pipe, middle ring flange and sensor joint chair use 304
Stainless steel material, for electrode terminal using outside brass material, remaining metal parts is all made of high temperature alloy GH2520 material.
The embodiment of the present invention is further characterized in that the ionization section uses the mode of DBD (dielectric barrier discharge).
The embodiment of the present invention is further characterized in that the optic test window is by quartz material, optic test window
It is equipped with the gland for being closed its opening.By the fastening that is spirally connected, gland and sensor joint chair are 304 for gland and optic test window
Stainless steel material.
The embodiment of the present invention has the advantages that
(1) present invention uses argon gas as electric discharge working medium, is conducive to independent observation ionization effect, while also can be used as blowing
Pipeline plays the effect for removing residual propellant；
(2) present invention designs insulating cylinder in ionization section, guarantees to carry out insulation connection between cathode and anode, be made pottery using high temperature
Ceramic material has the characteristics that resistant to high temperature；And cathode and anode insulating reliability is guaranteed by the suitable axial dimension of design insulator；
(3) anode and cathode of the present invention, insulator are both designed as ladder shaft-like, by multi-diameter shaft and interior bone, guarantee above-mentioned
Partial alignment；
(4) present invention realizes sealing, Graphite pad high temperature resistant, sealing by installing flexible graphite gasket in key position
The good, high reliablity of property prevents simultaneously because the protection to collets with preferable compression ratio and rebound degree, may be implemented in it
It is subject to crushing, improves the reliability of insulating Design；
(5) present invention realizes the axially position of ionization section using ring flange and lock-screw, repeats disassembled and assembled freely, passes through
The axial dimension of processing component is adjusted to adjust the length of effectively ionization section, provides convenience for experimental study, guarantees that thruster is whole
Body is beautiful and clean；
(6) present invention generates nonequilibrium plasma by way of dielectric barrier discharge, retains catalysis segment structure and guarantees
Can be with successful ignition, while valid data can be collected by optical window, joint chair etc., it verifies the structure design and whether can
Enough effectively improve the utilization efficiency of propellant and the performance of thruster；
(7) catalytic section of the present invention is detachable, the length of catalytic bed can be freely adjusted, to the later period only with non-equilibrium plasma
The experimental study of body igniting provides convenience, while significant to the sparking mode for changing existing catalysis dissociation completely.
Detailed description of the invention
It, below will be to embodiment party in order to illustrate more clearly of embodiments of the present invention or technical solution in the prior art
Formula or attached drawing needed to be used in the description of the prior art are briefly described.It should be evident that the accompanying drawings in the following description is only
It is merely exemplary, it for those of ordinary skill in the art, without creative efforts, can also basis
The attached drawing of offer, which is extended, obtains other implementation attached drawings.
Structure depicted in this specification, ratio, size etc., only to cooperate the revealed content of specification, for
Those skilled in the art understands and reads, and is not intended to limit the invention enforceable qualifications, therefore does not have technical
Essential meaning, the modification of any structure, the change of proportionate relationship or the adjustment of size are not influencing the function of the invention that can be generated
Under effect and the purpose that can reach, should all still it fall in the range of disclosed technology contents obtain and can cover.
Fig. 1 is integrally-built cross-sectional view of the invention；
Fig. 2 is integrally-built side view of the invention；
Fig. 3 is the structural schematic diagram of cylindric anode of the invention；
Fig. 4 is the side view on anode chassis of the invention；
Fig. 5 is the structural schematic diagram of catalytic section of the invention and combustion chamber；
Fig. 6 is the side structure schematic diagram of combustion chamber of the invention；
In figure:
1- spray section；2- ionizes section；3- catalytic section；The combustion chamber 4-；6- soft graphite washer；7- lock-screw；
101- supplies liquid supply pipe；102- forward flange disk；Insulator before 103-；
201- anode chassis；202- dielectric；203- tubular cathode；Ring flange in 204-；205- electrode terminal；
Insulator in 206-；Insulator after 207-；The cylindric anode of 208-；
301- catalytic bed；302- rear stub；
401- optic test window；402- sensor joint chair.
Specific embodiment
Embodiments of the present invention are illustrated by particular specific embodiment below, those skilled in the art can be by this explanation
Content disclosed by book is understood other advantages and efficacy of the present invention easily, it is clear that described embodiment is the present invention one
Section Example, instead of all the embodiments.Based on the embodiments of the present invention, those of ordinary skill in the art are not doing
Every other embodiment obtained under the premise of creative work out, shall fall within the protection scope of the present invention.
High temperature when propellant combustion will lead to collapsing sintering and the inactivation of active constituent of catalysis bed structure, direct shadow
The normal work of thruster is rung, it is common to light a fire by pre-heating system, need additional input heating power, therefore igniting side
Formula is more single.
To solve the above-mentioned problems, the present invention provides a kind of ADN base single group member thrust of low-temperature plasma synergistic catalysis
Device, general process the same with the course of work of common thruster are as follows: first inject gas, electric discharge generates plasma, is then injected into
Propellant realizes plasma igniting, so that propellant combustion generates bulk gas, sprays from jet pipe and generates thrust.Without pre-
Hot systems igniting, uses argon gas as electric discharge working medium, generates the igniting that nonequilibrium plasma realizes propellant by DBD, has
Effect improves the single disadvantage of current ADN base single group member thruster sparking mode.It is specific:
As shown in the integrally-built cross-sectional view of the thruster of Fig. 1 and Fig. 2 and side view: the generally coaxial circles of the thruster
Column structure, thruster include the coaxial sequentially connected spray section 1 of one, electricity from ejector filler to jet pipe direction (from left to right)
From section 2, catalytic section 3,4 four segment structure of combustion chamber.The both ends of spray section 1 and ionization section 2 pass through forward flange disk 102 and middle ring flange
204 compress；The integral structure and ionization section 2 that catalytic section 3 and combustion chamber 4 are formed are pressed by middle ring flange 204 and rear stub 302
Tightly.Thruster compact overall structure of the present invention saves space, and can satisfy design needs.Wherein:
Spray section 1 includes gas supply liquid supply pipe 101, the forward flange disk for being respectively configured to provide ADN liquid propellant and gas
102, preceding insulator 103, anode chassis 201；Gas supply liquid supply pipe 101 sequentially passes through forward flange disk 102, preceding insulator 103 and sun
Gas supply on pole chassis 201 is for fluid through-hole.The through-hole that the tail end and anode chassis 201 for supplying liquid supply pipe 101 are arranged, which cooperates, to be conveyed
Propellant and gas.
ADN liquid propellant is monopropellant, including oxidant (ADN), ionic liquid fuel (methanol) and solvent
(water) has the characteristics that low freezing point, low-steam pressure, green non-poisonous.The preferred argon gas of gas is as electric discharge working medium.Be conducive to independence
Ionization effect is observed, while also can be used as blowing pipeline, plays the effect for removing residual propellant.
Liquid supply pipe 1 is supplied by argon arc welding in the end face outside of forward flange disk 102,102 inner side end of forward flange disk
Inside groove and preceding insulator 103 cooperate, and realize radial positioning.
Preferably, the inside of preceding insulator 103 is equipped with the through-hole of variable cross-section design, provides buffering to propellant injection
Space.
Gas supply on anode chassis 201 is annular array double-layer structure for fluid through-hole, it is preferred that 6 through-holes of internal layer, outer layer
8 through-holes, diameter are 1.5mm.The inside nozzle of gas supply liquid supply pipe 101 is connected on the through-hole on anode chassis 201.
As shown in Figures 1 to 4, ionization section 2 uses the mode of DBD (dielectric barrier discharge).Ionizing section 2 includes and anode bottom
The sequentially connected cylindric anode 208 of disk 201, middle insulator 206, tubular cathode 203, rear insulator 207 and middle ring flange
204, it is compressed between middle ring flange 204 and forward flange disk 102 by the cooperation of lock-screw 7, and in 203 inner surface of tubular cathode
It is equipped with dielectric 202；Ionization section 2 is additionally provided with electrode terminal 205.Preferably, the diameter of cylindric anode 208
For 2mm.
Ionize section 2 from inside to outside successively are as follows: cylindric anode 208, dielectric 202, tubular cathode 203, middle ring flange
204, electrode terminal 205；
Ionize 2 outer layer of section (from left to right) successively are as follows: cylindric anode 208, middle insulator 206, tubular cathode 203, after
Insulator 207；Cylindric anode 208 and the inside for being connected to anode chassis 201, and be integral type mechanism.Cylindric anode
208, middle insulator 206 and tubular cathode 203 are around the mutually matched ladder shaft like parts of central axis.Middle insulator 206
Center is equipped with the through-hole for the insertion of cylindric anode 208.
Sequentially pacify by preceding insulator 103, cylindric anode 208, middle insulator 206, tubular cathode 203, rear insulator 207
Dress, and given as security tightly by forward flange disk 102 and middle ring flange 204 from both ends cooperation, it is realized by the cooperation between each section variable cross-section
Radial positioning, while compressing end face Graphite pad and realizing axially position, and guaranteeing the sealing between each section.It is specific: each portion
Part end face is designed with the internal annular groove for being equipped with soft graphite washer 6, by soft graphite washer 6 realize axially position and
Sealing between anode and cathode and insulator.Soft graphite washer 6 is installed in key position, realizes sealing, soft graphite washer 6 is resistance to
High temperature, good airproof performance, high reliablity, simultaneously because it may be implemented with preferable compression ratio and rebound degree to collets
Protection, prevents from being subject to crushing, improves the reliability of insulating Design.
Radial positioning is realized by insulator 206 in ladder shaft-like between tubular cathode 203 and anode chassis 201.Middle method
Between blue disk 204 and rear insulator 207 also similarly.
Dielectric 202 is preferably quartz ampoule, and quartzy tube outer surface and 203 inner surface of tubular cathode cooperate, and realization is stone
English pipe radial positioning；Quartz ampoule realizes axially position by the clearance fit of middle insulator 206, rear stub 302, outside quartz ampoule
Diameter is 12mm, and internal diameter is adjustable.
As shown in Figure 1, Figure 2, shown in Fig. 5 and Fig. 6, catalytic section 3 includes by round honeycomb baffle, catalyst granules and wire
The catalytic bed 301 of netted baffle plate composition and the rear stub 302 being connect with ionization section 2.Rear stub 302,301 and of catalytic bed
Combustion chamber 4 is structure as a whole.Middle ring flange 204 and rear stub 302 are compressed by lock-screw 7 realizes catalytic bed 301 and combustion
Burn the positioning of room 4.The length of catalytic bed 301 is adjusted by adjusting the length of loading catalyst particle, it is preferred that catalytic bed
301 length range is 0~33mm.Preferably 19mm, design thrust 1N.
Due to uncertain success igniting, retain catalytic section 3 to improve the reliability of igniting, dismountable catalytic section 3
Convenience is provided for transformation sparking mode completely later, solving the unbearable long-time high temperature of existing catalyst granules causes thruster
The problem of can not work normally.Catalytic section 3 is detachable, the length of catalytic bed 301 can be freely adjusted, to the later period only with non-equilibrium
The experimental study of plasma igniting provides convenience, while having important meaning to the sparking mode for changing existing catalysis dissociation completely
Justice.
The catalyst of catalytic section 3 is preferably iridium based catalyst and other kinds of noble metal-based catalysts etc..
Combustion chamber 4 includes reserving positioned at the optic test window 401 for being opened in three faces respectively and positioned at remaining one side
Sensor joint chair 402.Sensor joint chair 402 is preferably cylindric.Convenient for the access of the sensor devices such as pressure, temperature.Pass through
Optical measurement window 401 can study the efficiency of combustion etc. of ADN base single group member thruster, convenient for the size tune of thruster after guidance
It is whole.The collected valid data of sensor connected by optic test window 401 and sensor joint chair 402, verify the knot
Whether structure design can effectively improve the utilization efficiency of propellant and the performance of thruster.Preferably, optic test window
401 use argon arc welding with 4 inner cavity of combustion chamber.
The opening diameter of optic test window 401 is preferably 3.5mm, and optic test window 401 is excellent by quartz material
It is selected as sapphire material, thickness 6mm, diameter 13mm.Optic test window 401 is equipped with the gland for being closed its opening.Gland
Pass through the fastening that is spirally connected with optic test window 401.Gland and sensor joint chair 402 are preferably 304 stainless steel materials.Combustion chamber 4
It is followed by jet pipe, the throat diameter of jet pipe is 1.12mm.
To use 304 stainless steels in addition to supplying liquid supply pipe 101, middle ring flange 204 and sensor joint chair 402 in upper member
Material, using brass material, (brass has good electric conductivity, and high temperature resistant, fusing point to the electrode terminal 205 being spirally connected with power supply line
It is high) outside, remaining metal parts is all made of high temperature alloy GH2520 material.Preceding insulator 103, middle insulator 206 and rear insulator
207 use high-temperature ceramic materials, have the characteristics that resistant to high temperature；And yin, yang is guaranteed by the suitable axial dimension of design insulator
Pole insulating reliability.
Meanwhile forward flange disk 102, middle ring flange 204 by lock-screw 7 by component according to preceding insulator 103, cylindric
The sequence compression of anode 208, middle insulator 206, tubular cathode 203 and rear insulator 207.It, can be with by unclamping lock-screw 7
Each component of repeated removal, and appropriate adjustment its relative axial position, advantageously adjust the dimensional parameters of thruster, and experiment is ground
Offer convenience is provided, guarantees that thruster is overall beautiful clean and tidy.
The combustion reaction process of ADN can substantially be divided into two stages.First stage is the thermal decomposition stage of ADN, at this
One stage, ADN are decomposed into the group with relatively small molecular weight, and some of them have oxidisability, some to have reproducibility, according to
Stoichiometric ratio calculates, and the oxidant of intermediate product is more than reducing agent.Second stage is combustion phases, in this stage, ADN points
The fuel for solving these intermediate products and addition for generating reacts jointly, highly exothermic, completes the whole process of burning.
The ADN base single group member thruster course of work of low-temperature plasma synergistic catalysis of the present invention are as follows:
Cylindric anode 208 is connected high-tension ignition power supply with tubular cathode 203 by electrode terminal 205, is supplied by gas supply
The air supply pipe of liquid pipe 101 is put to argon gas discharging working medium is passed through inside cylindric anode 208 and tubular cathode 203 in argon gas arrival
Breakdown generation electric discharge, forms non-flat when electric room (cavity area of cylindric anode 208 and 203 edge medium of tubular cathode besieged city)
Weigh plasma；It is passed through ADN base liquid propellant by supplying the liquid supply pipe of liquid supply pipe 101 again later, in plasma
High energy electron bombards propellant, so that it is decomposed into oxidant, fuel element and is reacted, thus realize igniting, propellant combustion
It burns and generates bulk gas from the ejection of tail portion jet pipe, generate thrust.
Although above having used general explanation and specific embodiment, the present invention is described in detail, at this
On the basis of invention, it can be made some modifications or improvements, this will be apparent to those skilled in the art.Therefore,
These modifications or improvements without departing from theon the basis of the spirit of the present invention are fallen within the scope of the claimed invention.
Claims (10)
1. a kind of ADN base single group member thruster of low-temperature plasma synergistic catalysis, it is characterised in that: coaxial sequentially including one
The spray section (1) of connection, ionization section (2), catalytic section (3), (4) four segment structure of combustion chamber, the spray section (1) and ionization section
(2) both ends are compressed by forward flange disk (102) and middle ring flange (204)；What the catalytic section (3) and combustion chamber (4) were formed
Integral structure and ionization section (2) are compressed by middle ring flange (204) and rear stub (302)；
The spray section (1) include sequentially connected forward flange disk (102), preceding insulator (103) and anode chassis (201) and
It sequentially passes through the forward flange disk (102), preceding insulator (103) and anode chassis (201) and is respectively configured to provide the propulsion of ADN liquid
The gas supply liquid supply pipe (101) of agent and gas, the tail end of gas supply liquid supply pipe (101) and the through-hole of anode chassis (201) setting
Cooperation conveying propellant and gas；
The ionization section (2) include with anode chassis (201) sequentially connected cylindric anode (208), middle insulator (206),
Tubular cathode (203), rear insulator (207) and middle ring flange (204), the middle ring flange (204) and forward flange disk (102) it
Between compressed by lock-screw (7) cooperation, and be equipped with dielectric in tubular cathode (203) inner surface
(202)；Ionization section (2) is additionally provided with electrode terminal (205)；
The catalytic section (3) includes rear stub (302) and catalytic bed (301), the rear stub (302), catalytic bed (301)
It is structure as a whole with combustion chamber (4), matches combined pressure also through lock-screw (7) between middle ring flange (204) and rear stub (302)
Tightly；
The combustion chamber (4) includes that the optic test window (401) for being opened in three faces respectively and sensor reserved on one side connect
Seat (402).
2. a kind of ADN base single group member thruster of low-temperature plasma synergistic catalysis according to claim 1, feature exist
In: the ADN liquid propellant is monopropellant, including oxidant (ADN), ionic liquid fuel (methanol) and solvent
(water).
3. a kind of ADN base single group member thruster of low-temperature plasma synergistic catalysis according to claim 1, feature exist
In: the inside groove of forward flange disk (102) inner side end and preceding insulator (103) cooperate；Cylindric anode (208), middle insulation
Body (206) and tubular cathode (203) are around the mutually matched ladder shaft like parts of central axis；Tubular cathode (203) and anode
Radial positioning is realized by insulator (206) in ladder shaft-like between chassis (201).
4. a kind of ADN base single group member thruster of low-temperature plasma synergistic catalysis according to claim 1, feature exist
In: each component end face is designed with the internal annular groove for being equipped with soft graphite washer (6), is realized by soft graphite washer (6)
Sealing between axially position and anode and cathode and insulator.
5. a kind of ADN base single group member thruster of low-temperature plasma synergistic catalysis according to claim 1, feature exist
In: the cylindric anode (208) is designed with anode chassis (201) for integral type, and connection is provided on anode chassis (201) and is supplied
The gas supply of the inside nozzle of gas liquid supply pipe (101) is annular array double-layer structure, internal layer for fluid through-hole for fluid through-hole, the gas supply
6 through-holes, 8 through-holes of outer layer, diameter is 1.5mm.
6. a kind of ADN base single group member thruster of low-temperature plasma synergistic catalysis according to claim 1, feature exist
In: the dielectric (202) is quartz ampoule, and quartzy tube outer surface and tubular cathode (203) inner surface cooperate, and realization is quartz
Pipe radial positioning；The quartz ampoule realizes axially position, stone by the clearance fit of middle insulator (206), rear stub (302)
English pipe outside diameter is 12mm, and internal diameter is adjustable.
7. a kind of ADN base single group member thruster of low-temperature plasma synergistic catalysis according to claim 1, feature exist
In: the catalytic bed (301) includes catalyst granules, and the catalyst granules is iridium based catalyst and other kinds of noble metal
Base catalyst；The length of the catalytic bed (301) is 0~33mm.
8. a kind of ADN base single group member thruster of low-temperature plasma synergistic catalysis according to claim 1, feature exist
In: except the gas supply liquid supply pipe (101), middle ring flange (204) and sensor joint chair (402) use 304 stainless steel materials, electrode
For binding post (205) using outside brass material, remaining metal parts is all made of high temperature alloy GH2520 material.
9. a kind of ADN base single group member thruster of low-temperature plasma synergistic catalysis according to claim 1, feature exist
In: ionization section (2) uses the mode of DBD (dielectric barrier discharge).
10. a kind of ADN base single group member thruster of low-temperature plasma synergistic catalysis according to claim 1, feature
Be: for the optic test window (401) by quartz material, optic test window (401), which is equipped with, is closed its opening
Gland.By the fastening that is spirally connected, gland and sensor joint chair (402) are 304 stainless steels for gland and optic test window (401)
Matter.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910513121.9A CN110259605B (en) | 2019-06-14 | 2019-06-14 | ADN-based single-component thruster for low-temperature plasma concerted catalysis |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910513121.9A CN110259605B (en) | 2019-06-14 | 2019-06-14 | ADN-based single-component thruster for low-temperature plasma concerted catalysis |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110259605A true CN110259605A (en) | 2019-09-20 |
| CN110259605B CN110259605B (en) | 2020-04-07 |
Family
ID=67918105
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910513121.9A Active CN110259605B (en) | 2019-06-14 | 2019-06-14 | ADN-based single-component thruster for low-temperature plasma concerted catalysis |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110259605B (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110954576A (en) * | 2019-12-11 | 2020-04-03 | 中国科学院力学研究所 | Plasma ignition experimental device and method |
| CN110954794A (en) * | 2019-12-11 | 2020-04-03 | 中国科学院力学研究所 | Liquid propellant constant-pressure discharge characteristic parameter measuring device |
| CN113123901A (en) * | 2021-05-08 | 2021-07-16 | 北京交通大学 | Ionic propellant electric ignition method based on resistance heating and high-temperature ignition of combustion chamber |
| CN113137318A (en) * | 2021-05-08 | 2021-07-20 | 北京交通大学 | Electric ignition method of ionic propellant based on resistance heating mode |
| CN113446129A (en) * | 2021-07-26 | 2021-09-28 | 中国人民解放军战略支援部队航天工程大学 | High-efficiency stable combustion injector of medium-small thrust rocket engine |
| CN114324708A (en) * | 2021-12-20 | 2022-04-12 | 杭州谱育科技发展有限公司 | FID detector and method based on catalytic ignition technology |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1477663A2 (en) * | 2003-05-13 | 2004-11-17 | United Technologies Corporation | Monopropellant reactor system and operating method for a reactor system |
| JP2006037824A (en) * | 2004-07-27 | 2006-02-09 | Japan Aerospace Exploration Agency | Discharge plasma reaction type thruster |
| US20140290212A1 (en) * | 2013-03-27 | 2014-10-02 | Lockheed Martin Corporation | Reactants sprayed into plasma flow for rocket propulsion |
| CN108482711A (en) * | 2012-12-04 | 2018-09-04 | 波音公司 | The method and apparatus for executing forward operation using the system that is electrically propelled |
| CN108612599A (en) * | 2016-12-10 | 2018-10-02 | 中国科学院大连化学物理研究所 | A kind of liquid-electricity interblock space thruster |
-
2019
- 2019-06-14 CN CN201910513121.9A patent/CN110259605B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1477663A2 (en) * | 2003-05-13 | 2004-11-17 | United Technologies Corporation | Monopropellant reactor system and operating method for a reactor system |
| JP2006037824A (en) * | 2004-07-27 | 2006-02-09 | Japan Aerospace Exploration Agency | Discharge plasma reaction type thruster |
| CN108482711A (en) * | 2012-12-04 | 2018-09-04 | 波音公司 | The method and apparatus for executing forward operation using the system that is electrically propelled |
| US20140290212A1 (en) * | 2013-03-27 | 2014-10-02 | Lockheed Martin Corporation | Reactants sprayed into plasma flow for rocket propulsion |
| CN108612599A (en) * | 2016-12-10 | 2018-10-02 | 中国科学院大连化学物理研究所 | A kind of liquid-electricity interblock space thruster |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110954576A (en) * | 2019-12-11 | 2020-04-03 | 中国科学院力学研究所 | Plasma ignition experimental device and method |
| CN110954794A (en) * | 2019-12-11 | 2020-04-03 | 中国科学院力学研究所 | Liquid propellant constant-pressure discharge characteristic parameter measuring device |
| CN110954794B (en) * | 2019-12-11 | 2022-04-12 | 中国科学院力学研究所 | Liquid propellant constant-pressure discharge characteristic parameter measuring device |
| CN113123901A (en) * | 2021-05-08 | 2021-07-16 | 北京交通大学 | Ionic propellant electric ignition method based on resistance heating and high-temperature ignition of combustion chamber |
| CN113137318A (en) * | 2021-05-08 | 2021-07-20 | 北京交通大学 | Electric ignition method of ionic propellant based on resistance heating mode |
| CN113446129A (en) * | 2021-07-26 | 2021-09-28 | 中国人民解放军战略支援部队航天工程大学 | High-efficiency stable combustion injector of medium-small thrust rocket engine |
| CN114324708A (en) * | 2021-12-20 | 2022-04-12 | 杭州谱育科技发展有限公司 | FID detector and method based on catalytic ignition technology |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110259605B (en) | 2020-04-07 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110259605A (en) | A kind of ADN base single group member thruster of low-temperature plasma synergistic catalysis | |
| JP4908629B2 (en) | Electrolytic igniter for rocket engines using monopropellant | |
| US8375697B2 (en) | Electrolytic igniter for rocket engines using liquid propellants | |
| US5485721A (en) | Arcjet for a space flying body | |
| US5767439A (en) | Annular plasma injector | |
| US4322946A (en) | Thermal thruster with superheater | |
| JP2010523877A5 (en) | ||
| CN113123901A (en) | Ionic propellant electric ignition method based on resistance heating and high-temperature ignition of combustion chamber | |
| JP2007298031A (en) | Bipropellent injector, rocket thruster assembly and injector assembly | |
| JPH08320197A (en) | Method and equipment for generating high-pressure gas-pulse by using comparatively inactive fuel and oxidizer under peripheral condition | |
| US5185541A (en) | Gas turbine for converting fuel to electrical and mechanical energy | |
| US5319926A (en) | Thruster for spacecraft | |
| CN116771548A (en) | Chemical-electric arc combined power thruster for space and application method thereof | |
| US20080173270A1 (en) | Fuel injection device including plasma-inducing electrode arrays | |
| US20090114178A1 (en) | Fuel injection device including plasma-inducing electrode arrays | |
| EP3500545B1 (en) | Microwave ignition of electrically operated propellants | |
| ZA200109302B (en) | Plasma torch comprising electrodes separated by an air gap and igniter incorporating same. | |
| WO1992020913A1 (en) | Plasma ignition apparatus and method for enhanced combustion and flameholding in engine combustion chambers | |
| US4027187A (en) | Supersonic spark gap switch | |
| CN113137318A (en) | Electric ignition method of ionic propellant based on resistance heating mode | |
| US4047880A (en) | Fluids distributor for energized-fluid systems | |
| CN114962077A (en) | Dinitramide ammonium-based liquid single-component engine based on electric ignition mode | |
| CN207083268U (en) | A kind of plasma producing apparatus based on hot cathode | |
| US20070082237A1 (en) | Fuel reforming apparatus and fuel cell system with the same | |
| Russell et al. | Inert gas metallic vapor laser |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20231116 Address after: 511458 Room 501, building 1, 1119 Haibin Road, Nansha District, Guangzhou City, Guangdong Province Patentee after: Guangdong Aerospace Science and Technology Research Institute (Nansha) Address before: 100190, No. 15 West Fourth Ring Road, Beijing, Haidian District Patentee before: INSTITUTE OF MECHANICS, CHINESE ACADEMY OF SCIENCES |
|
| TR01 | Transfer of patent right |