CN102192046A - Thruster of hydrogen-oxygen catalytic ignition mini rocket - Google Patents
Thruster of hydrogen-oxygen catalytic ignition mini rocket Download PDFInfo
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- CN102192046A CN102192046A CN2011101027328A CN201110102732A CN102192046A CN 102192046 A CN102192046 A CN 102192046A CN 2011101027328 A CN2011101027328 A CN 2011101027328A CN 201110102732 A CN201110102732 A CN 201110102732A CN 102192046 A CN102192046 A CN 102192046A
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Abstract
The invention provides a thruster of a hydrogen-oxygen catalytic ignition mini rocket, comprising a catalytic ignition device and a combustor device, wherein the catalytic ignition device comprises an end socket, a catalytic cylinder and a catalytic cylinder baseplate; and the combustor device comprises a graphite lining, a graphite precombustion chamber, a precombustion chamber sleeve, a nozzle steel jacket and a tungsten-doped copper nozzle. The thruster is used for realizing hydrogen-oxygen catalytic ignition which can be used for realizing the purpose of repeated ignition. Hydrogen inlets are uniformly distributed at the back semi-section of the combustor in the thruster in the circumferential direction, thus adjusting the hydrogen-oxygen mixing ratio and achieving an afterburning effect. The thruster is simple in structure and ensures that parts can be disassembled and replaced easily.
Description
Technical field
The invention belongs to astrovehicle spaces such as satellite and use the propulsion system field, be specifically related to the small-sized thruster of a kind of gas hydrogen oxygen catalytic ignition.
Background technique
Thruster on the satellite mostly is cold air and hydrazine catalytic decomposition at present, and specific impulse is lower, and is toxic, and gas hydrogen oxygen propellant agent theoretical specific impulse is far longer than hydrazine class propellant agent, can improve the space propulsion system performance greatly.Yet all the time, the space storage problem of high pressure hydrogen has restricted the space application of gas hydrogen oxygen thruster.Water base rocket space propulsion system can utilize the real-time electrolysis of low-pressure water to go out high pressure hydrogen, has solved the space storage problem of hydrogen, and schedule has been put in the development of space gas hydrogen oxygen thruster.
The high vacuum that use in the space, low energy consumption, small volume and the requirement of repeatedly lighting a fire make catalytic ignition become the first-selected firing mode of space gas hydrogen oxygen thruster.The U.S., states such as Japan successively Design and Machining multiple catalytic site internal heat hydrogen oxygen thruster, carried out series of experimental research in the many aspects such as selection, catalytic ignition structure Design, catalytic ignition response time and repeatability of catalytic media.
Summary of the invention
At problems of the prior art, the invention provides the small-sized thruster of a kind of gas hydrogen oxygen catalytic ignition, be used to realize the catalytic ignition of gas hydrogen oxygen, and catalytic ignition can reach the repeatedly purpose of igniting, the firing chamber second half section is circumferentially evenly arranged hydrogen inlet in this device, can regulate the hydrogen-oxygen proportions of ingredients, plays the effect of afterburning, and this apparatus structure is simple, is easy to dismounting and changes parts.
The present invention proposes the small-sized thruster of a kind of gas hydrogen oxygen catalytic ignition, and this thruster comprises catalytic ignition device and combusting room device.
Described catalytic ignition device is by end socket, catalysis tube and catalysis tube end plate are formed, the end socket front end has the gas via-hole that vertically passes this end socket axis, the two ends of gas via-hole are respectively applied for and are communicated with hydrogen and oxygen, form the gas hydrogen gentle oxygen inlet that enters the mouth, the end socket rear end has axial blind hole along axial direction, the bottom of this blind hole is connected with the side opening wall of gas via-hole central segment, the catalysis tube is arranged in this axial blind hole, and catalysis tube top does not contact this bottom, blind hole hole fully, and then the formation cavity is the premixing chamber between at the bottom of catalysis tube top and the blind hole hole, be connected between this premixing chamber and the catalysis tube top, connection place has the catalysis tube end plate by bolt, and the catalysis tube bottom also has the catalysis tube end plate by bolt, and then the platinum filament catalyzer is placed in the catalysis tube, hydrogen and oxygen mix earlier in the premixing chamber after gas hydrogen enters the mouth the inflow of gentle oxygen inlet, carry out catalysis in the catalysis tube that arrives soon after.The catalysis tube is a field-replaceable unit, and the demountable structure of catalysis tube and catalysis base plate has made things convenient for the replacing of catalyzer.The rear end of end socket is a flange plate structure, and the front end flange dish of the precombustion chamber sleeve by bolt and combusting room device is connected.
Described combusting room device oozes the copper jet pipe by graphite back boxing, graphite precombustion chamber, precombustion chamber sleeve, jet pipe steel sleeve and tungsten to be formed.Combusting room device be gas hydrogen oxygen through the place of platinum filament catalytic ignition after-combustion, and in the graphite precombustion chamber, can carry out further afterburning, to improve fuel gas temperature and thruster specific impulse, satisfy overall objective.Described precombustion chamber sleeve is by the front end flange dish that links to each other in turn, the shoulder hole structure that rear end flange plate and connection front end flange dish and rear end flange plate form is formed, this shoulder hole structure is formed by being positioned on the smaller shoulder hole of front end flange dish internal orifice dimension the hole and being positioned on the bigger shoulder hole of rear end flange plate internal orifice dimension the hole, the flange plate structure of end socket rear end is connected by bolt with the front end flange dish of sleeve, on shoulder hole, be provided with the graphite back boxing in the hole, graphite back boxing front-end face is concordant with catalysis tube end plate ear end face, and the gas hydrogen oxygen behind the platinum filament catalytic ignition at first enters in the graphite back boxing.And hole place also is provided with red copper pad B on graphite back boxing and the shoulder hole and since this moment gas hydrogen oxygen proportions of ingredients to depart from optimum mixture ratio more, therefore temperature herein is not very high, adopts graphite material can realize reusable purpose yet.Have temperature measuring hole and pressure tap on the sidewall of graphite back boxing, conveniently detect and gather the temperature and the pressure at this graphite back boxing place, also can prevent to meet accident when temperature from surpassing limit value.On shoulder hole, be positioned at place, graphite back boxing lower end surface in the hole and also be provided with the graphite precombustion chamber, the centre of graphite precombustion chamber is the cylindrical section structure, its central position circumferentially has 6 equably with coconnected vent, be communicated with the second road hydrogen by vent, the second road hydrogen enters in the graphite precombustion chamber through this, makes this second road hydrogen and unnecessary oxygen further burn.The two ends of cylinder end are nozzle structure, one end is communicated with the graphite back boxing, make gas enter cylindrical section by nozzle structure, the other end oozes the copper jet pipe with tungsten and is connected, making gas ooze the copper jet pipe through tungsten flows out, this tungsten oozes the copper jet pipe and places under the shoulder hole in the hole, dock with the bottom of graphite precombustion chamber at the top that tungsten oozes the copper jet pipe, the bottom that tungsten oozes the copper jet pipe is connected with the jet pipe steel sleeve, central through bore fixed tungsten by the jet pipe steel sleeve is oozed the copper jet pipe, and the outer rim of jet pipe steel sleeve is connected with the flange in the bottom dish of precombustion chamber.
The invention has the advantages that:
(1) the invention provides the small-sized thruster of a kind of gas hydrogen oxygen catalytic ignition, simple in structure, be easy to dismounting and change parts;
(2) the invention provides the small-sized thruster of a kind of gas hydrogen oxygen catalytic ignition, gas hydrogen oxygen is in the air inlet of thruster head two-way, and mixes at head;
(3) the invention provides the small-sized thruster of a kind of gas hydrogen oxygen catalytic ignition, the orifice plate of catalysis tube head not only can play the effect of rectification but also can prevent tempering;
(4) the invention provides the small-sized thruster of a kind of gas hydrogen oxygen catalytic ignition, the firing chamber second half section is circumferentially evenly arranged hydrogen inlet, can regulate the hydrogen-oxygen proportions of ingredients, plays the effect of afterburning.
(5) the invention provides the small-sized thruster of a kind of gas hydrogen oxygen catalytic ignition, it is bigger that the preceding half section hydrogen-oxygen proportions of ingredients in firing chamber departs from optimum mixture ratio, combustion temperature is lower, reduced the preceding half section thermal protection requirement in firing chamber, second half section has been improved fuel gas temperature and specific impulse through afterburning, can satisfy the index on the engineering.
Description of drawings
Fig. 1: the invention provides the small-sized thruster structural representation of a kind of gas hydrogen oxygen catalytic ignition;
Fig. 2: the end socket sectional drawing that the invention provides the small-sized thruster of a kind of gas hydrogen oxygen catalytic ignition;
Fig. 3: the invention provides the small-sized thruster graphite of a kind of gas hydrogen oxygen catalytic ignition pre-combustion chamber schematic representation;
Fig. 4: the invention provides the small-sized thruster precombustion chamber of a kind of gas hydrogen oxygen catalytic ignition tube-in-tube structure schematic representation.
Among the figure:
1-catalytic ignition device 2-combusting room device 101-end socket base plate 102-catalysis tube
103-catalysis tube end plate 201-graphite back boxing 202-graphite precombustion chamber 203-precombustion chamber sleeve
204-jet pipe steel sleeve 205-tungsten oozes copper jet pipe 206-red copper pad A 207-red copper pad B
The 1011-gas hydrogen inlet 1012-gas oxygen inlet 1013-2021-of premixing chamber vent
Embodiment
The present invention is described in further detail below in conjunction with accompanying drawing.
The present invention proposes the small-sized thruster of a kind of gas hydrogen oxygen catalytic ignition, and as shown in Figure 1, this thruster comprises catalytic ignition device 1 and combusting room device 2.
Described catalytic ignition device 1 is by end socket 101, catalysis tube 102 and catalysis tube end plate 103 are formed, end socket 101 front ends have the gas via-hole that vertically passes this end socket axis, the two ends of gas via-hole are respectively applied for and are communicated with hydrogen and oxygen, form the gas hydrogen 1011 gentle oxygen inlets 1012 that enter the mouth, as Fig. 2, end socket 101 rear ends have axial blind hole along axial direction, the bottom of this blind hole is connected with the side opening wall of gas via-hole central segment, the catalysis tube is arranged in this axial blind hole, and catalysis tube top does not contact this bottom, blind hole hole fully, and then the formation cavity is premixing chamber 1013 between at the bottom of catalysis tube top and the blind hole hole, be connected between this premixing chamber and the catalysis tube top, connection place has catalysis tube end plate 103 by bolt, and the catalysis tube bottom also has catalysis tube end plate 103 by bolt, and then the platinum filament catalyzer is placed in the catalysis tube 102, hydrogen and oxygen are after gas hydrogen enters the mouth 1011 gentle oxygen inlet 1012 inflows, in premixing chamber 1013, mix earlier, carry out catalysis in the catalysis tube 102 that arrives soon after.Catalysis tube 102 is field-replaceable units, and the demountable structure of catalysis tube 102 and catalysis base plate 103 has made things convenient for the replacing of catalyzer.The rear end of end socket 101 is a flange plate structure, and the front end flange dish of the precombustion chamber sleeve 203 by bolt and combusting room device 2 is connected.
Described combusting room device 2 oozes copper jet pipe 205 by graphite back boxing 201, graphite precombustion chamber 202, precombustion chamber sleeve 203, jet pipe steel sleeve 204 and tungsten to be formed.Combusting room device 2 be gas hydrogen oxygen through the place of platinum filament catalytic ignition after-combustion, and in graphite precombustion chamber 202, can carry out further afterburning, to improve fuel gas temperature and thruster specific impulse, satisfy overall objective.Described precombustion chamber sleeve 203 is by the front end flange dish that links to each other in turn, the shoulder hole structure that rear end flange plate and connection front end flange dish and rear end flange plate form is formed, this shoulder hole structure is formed by being positioned on the smaller shoulder hole of front end flange dish internal orifice dimension the hole and being positioned on the bigger shoulder hole of rear end flange plate internal orifice dimension the hole, the flange plate structure of end socket 101 rear ends is connected by bolt with the front end flange dish of sleeve 203, on shoulder hole, be provided with graphite back boxing 201 in the hole, graphite back boxing 201 front-end faces are concordant with catalysis tube end plate 103 ear end faces, and the gas hydrogen oxygen behind the platinum filament catalytic ignition at first enters in the graphite back boxing 201.And the place, hole also is provided with red copper pad B207 on graphite back boxing 201 and the shoulder hole and since this moment gas hydrogen oxygen proportions of ingredients to depart from optimum mixture ratio more, therefore temperature herein is not very high, adopts graphite material can realize reusable purpose yet.Have temperature measuring hole and pressure tap on the sidewall of graphite back boxing 201, conveniently detect and gather the temperature and the pressure at these graphite back boxing 201 places, also can prevent to meet accident when temperature from surpassing limit value.On shoulder hole, be positioned at place, graphite back boxing lower end surface in the hole and also be provided with graphite precombustion chamber 202, the centre of graphite precombustion chamber 202 is the cylindrical section structure, its central position circumferentially has 6 equably with coconnected vent 2021, be communicated with the second road hydrogen by vent 2021, the second road hydrogen enters into 202 li of graphite precombustion chambers through this, makes this second road hydrogen and unnecessary oxygen further burn.The two ends of cylinder end are nozzle structure, one end is communicated with graphite back boxing 201, make gas enter cylindrical section by nozzle structure, the other end oozes copper jet pipe 205 with tungsten and is connected, making gas ooze copper jet pipe 205 through tungsten flows out, this tungsten oozes the copper jet pipe and places under the shoulder hole in the hole, dock with the bottom of graphite precombustion chamber 202 at the top that tungsten oozes copper jet pipe 205, the bottom that tungsten oozes copper jet pipe 205 is connected with jet pipe steel sleeve 204, central through bore fixed tungsten by jet pipe steel sleeve 204 is oozed copper jet pipe 205, and the outer rim of jet pipe steel sleeve 204 is connected with the flange in the bottom dish of precombustion chamber.
Described end socket 101, catalysis tube 102 and catalysis tube end plate 103 are made by stainless steel, and the one, because the stainless steel strength ratio is higher, good welding performance, the 2nd, because its anticorrosive property, can avoid material such as iron rust to pollute the platinum filament catalyzer.
Described graphite back boxing 201 and graphite precombustion chamber 202 all adopt the reasonable graphite material of thermal protective performance (TPP) to make.The all reasonable stainless steel of the material selection intensity of described precombustion chamber sleeve 203 and corrosion resistance.
The front end flange dish of described precombustion chamber sleeve 203 is provided with temperature measuring hole and pressure tap temperature measuring hole and the pressure tap corresponding to the same with graphite back boxing 201 sidewalls.Be provided with red copper pad B207 between the hole on described graphite back boxing 201 and precombustion chamber sleeve 203 shoulder holes, tungsten oozes the wall place that copper jet pipe 205 is connected with hole under the shoulder hole and is provided with red copper pad A206, by red copper pad A206 and red copper pad B207, realize the sealing of precombustion chamber sleeve 203.Described jet pipe steel sleeve 204 adopts stainless steel material.
Described tungsten oozes copper jet pipe 205 and oozes copper product by tungsten and make.Tungsten oozes the front half part of copper jet pipe 205 in precombustion chamber sleeve 203, fixes when latter half part is connected with precombustion chamber sleeve 203 by jet pipe steel sleeve 204.Fuel gas temperature behind afterburning is than higher, and the velocity ratio of combustion gas herein is very fast, therefore selects for use all reasonable tungsten of ablation property and mechanical property to ooze copper and satisfies the requirement that repeatability is used.
Claims (7)
1. the small-sized thruster of gas hydrogen oxygen catalytic ignition is characterized in that: comprise catalytic ignition device and combusting room device;
Described catalytic ignition device is by end socket, catalysis tube and catalysis tube end plate are formed, the end socket front end has the gas via-hole that vertically passes this end socket axis, the two ends of gas via-hole are respectively applied for and are communicated with hydrogen and oxygen, form the gas hydrogen gentle oxygen inlet that enters the mouth, the end socket rear end has axial blind hole along axial direction, the bottom of this blind hole is connected with the side opening wall of gas via-hole central segment, the catalysis tube is arranged in this axial blind hole, and catalysis tube top does not contact this bottom, blind hole hole fully, and then the formation cavity is the premixing chamber between at the bottom of catalysis tube top and the blind hole hole, be connected between this premixing chamber and the catalysis tube top, connection place has the catalysis tube end plate by bolt, and the catalysis tube bottom also has the catalysis tube end plate by bolt, and then the platinum filament catalyzer is placed in the catalysis tube, hydrogen and oxygen mix earlier in the premixing chamber after gas hydrogen enters the mouth the inflow of gentle oxygen inlet, carry out catalysis in the catalysis tube that arrives soon after; The rear end of end socket is a flange plate structure;
Described combusting room device oozes the copper jet pipe by graphite back boxing, graphite precombustion chamber, precombustion chamber sleeve, jet pipe steel sleeve and tungsten to be formed; Described precombustion chamber sleeve is made up of the shoulder hole structure that the front end flange dish that links to each other in turn, rear end flange plate and connection front end flange dish and rear end flange plate form, this shoulder hole structure is by hole on the shoulder hole that is positioned at the front end flange dish and be positioned on the shoulder hole of rear end flange plate the hole and form, the flange plate structure of end socket rear end is connected by bolt with the front end flange dish of sleeve, be provided with the graphite back boxing on shoulder hole in the hole, graphite back boxing front-end face is concordant with catalysis tube end plate ear end face; On shoulder hole, be positioned at place, graphite back boxing lower end surface in the hole and also be provided with the graphite precombustion chamber, the centre of graphite precombustion chamber is the cylindrical section structure, the vent that its central position circumferentially has equably, be communicated with the second road hydrogen by vent, the second road hydrogen enters in the graphite precombustion chamber through this, further burns with unnecessary oxygen; The two ends of cylinder end are nozzle structure, one end is communicated with the graphite back boxing, the other end oozes the copper jet pipe with tungsten and is connected, this tungsten oozes the copper jet pipe and places under the shoulder hole in the hole, dock with the bottom of graphite precombustion chamber at the top that tungsten oozes the copper jet pipe, the bottom that tungsten oozes the copper jet pipe is connected with the jet pipe steel sleeve, oozes the copper jet pipe by the central through bore fixed tungsten of jet pipe steel sleeve, and the outer rim of jet pipe steel sleeve is connected with the flange in the bottom dish of precombustion chamber.
2. the small-sized thruster of a kind of gas hydrogen oxygen catalytic ignition according to claim 1 is characterized in that: the place, hole also is provided with red copper pad B on described graphite back boxing and the shoulder hole.
3. the small-sized thruster of a kind of gas hydrogen oxygen catalytic ignition according to claim 1 is characterized in that: described tungsten oozes the wall place that the copper jet pipe is connected with hole under the shoulder hole and is provided with red copper pad A.
4. the small-sized thruster of a kind of gas hydrogen oxygen catalytic ignition according to claim 1 is characterized in that: have temperature measuring hole and pressure tap on the sidewall of described graphite back boxing, be used to detect and gather the temperature and the pressure of graphite back boxing.
5. the small-sized thruster of a kind of gas hydrogen oxygen catalytic ignition according to claim 4 is characterized in that: the front end flange dish of described precombustion chamber sleeve is provided with temperature measuring hole and pressure tap temperature measuring hole and the pressure tap corresponding to the same with graphite back boxing sidewall.
6. the small-sized thruster of a kind of gas hydrogen oxygen catalytic ignition according to claim 1, it is characterized in that: the material of described end socket, catalysis tube, precombustion chamber sleeve, jet pipe steel sleeve and catalysis tube end plate is stainless steel.
7. the small-sized thruster of a kind of gas hydrogen oxygen catalytic ignition according to claim 1, it is characterized in that: the material of described graphite back boxing and graphite precombustion chamber is graphite material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110102732 CN102192046B (en) | 2011-04-22 | 2011-04-22 | Thruster of hydrogen-oxygen catalytic ignition mini rocket |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110102732 CN102192046B (en) | 2011-04-22 | 2011-04-22 | Thruster of hydrogen-oxygen catalytic ignition mini rocket |
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| CN102192046A true CN102192046A (en) | 2011-09-21 |
| CN102192046B CN102192046B (en) | 2013-09-18 |
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| CN 201110102732 Expired - Fee Related CN102192046B (en) | 2011-04-22 | 2011-04-22 | Thruster of hydrogen-oxygen catalytic ignition mini rocket |
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Cited By (9)
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| CN103398378A (en) * | 2013-07-26 | 2013-11-20 | 中国计量学院 | Spontaneous combustion type hydrogen-catalysis combustor |
| CN103644044A (en) * | 2013-11-26 | 2014-03-19 | 北京航空航天大学 | Multi-component simulative engine applied to vacuum plume effect experimental research and ignition scheme thereof |
| CN106194500A (en) * | 2016-08-26 | 2016-12-07 | 北京宇航系统工程研究所 | A kind of tridyne pressure charging system being applied to liquid rocket |
| EP3246559A1 (en) * | 2016-05-20 | 2017-11-22 | Airbus DS GmbH | Rocket propulsion system and method for operating the same |
| CN107725216A (en) * | 2017-08-30 | 2018-02-23 | 北京控制工程研究所 | One kind premix hydrogen-oxygen thruster |
| CN107798178A (en) * | 2017-10-16 | 2018-03-13 | 兰州空间技术物理研究所 | One kind mixing thruster performance optimization method |
| CN108999727A (en) * | 2018-10-15 | 2018-12-14 | 北京动力机械研究所 | Protection against erosion water cooling nozzle structure |
| CN109928858A (en) * | 2017-12-15 | 2019-06-25 | 中国科学院大连化学物理研究所 | A kind of H with modularization catalytic bed2O2Gas generator |
| CN113530709A (en) * | 2021-09-16 | 2021-10-22 | 西安空天引擎科技有限公司 | Bimodal hydrogen peroxide gas generator |
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Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103398378A (en) * | 2013-07-26 | 2013-11-20 | 中国计量学院 | Spontaneous combustion type hydrogen-catalysis combustor |
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| CN106194500B (en) * | 2016-08-26 | 2018-01-05 | 北京宇航系统工程研究所 | A kind of tridyne pressure charging system applied to liquid rocket |
| CN107725216A (en) * | 2017-08-30 | 2018-02-23 | 北京控制工程研究所 | One kind premix hydrogen-oxygen thruster |
| CN107798178A (en) * | 2017-10-16 | 2018-03-13 | 兰州空间技术物理研究所 | One kind mixing thruster performance optimization method |
| CN107798178B (en) * | 2017-10-16 | 2020-12-25 | 兰州空间技术物理研究所 | Hybrid thruster performance optimization method |
| CN109928858A (en) * | 2017-12-15 | 2019-06-25 | 中国科学院大连化学物理研究所 | A kind of H with modularization catalytic bed2O2Gas generator |
| CN108999727A (en) * | 2018-10-15 | 2018-12-14 | 北京动力机械研究所 | Protection against erosion water cooling nozzle structure |
| CN113530709A (en) * | 2021-09-16 | 2021-10-22 | 西安空天引擎科技有限公司 | Bimodal hydrogen peroxide gas generator |
| CN113530709B (en) * | 2021-09-16 | 2021-12-14 | 西安空天引擎科技有限公司 | Bimodal hydrogen peroxide gas generator |
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| CN102192046B (en) | 2013-09-18 |
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