CN106134388B - A kind of monopropellant engine of nontoxic monopropellant - Google Patents
A kind of monopropellant engine of nontoxic monopropellantInfo
- Publication number
- CN106134388B CN106134388B CN201010052277.0A CN201010052277A CN106134388B CN 106134388 B CN106134388 B CN 106134388B CN 201010052277 A CN201010052277 A CN 201010052277A CN 106134388 B CN106134388 B CN 106134388B
- Authority
- CN
- China
- Prior art keywords
- monopropellant
- catalytic bed
- engine
- nontoxic
- catalyst
- 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.)
- Active
Links
Abstract
The present invention proposes a kind of monopropellant engine of nontoxic monopropellant, and this engine is made up of thrust chamber and magnetic valve, and thrust chamber is made up of ejector filler and body portion. Body portion comprises two-layer catalytic bed and combustion chamber, catalytic bed, and the external crucible of catalytic bed adopts finely grained catalyst, and rear bed adopts coarse granule catalyst. The active component of the catalyst adopting is metal iridium, contains iridium amount between 5%-35%. After catalytic bed, there is a combustion chamber. Before and after between catalytic bed, there is the refractory metal porous plate that adds the refractory metal net of coating and add coating between catalytic bed and combustion chamber. Magnetic valve is opened, and nontoxic monopropellant sprays from ejector filler, and by catalytic bed catalytic decomposition, the fuel of catabolite and propellant, after combustion chambers burn, enters jet pipe, produces thrust. Solve nontoxic monopropellant in monopropellant engine propellant combustion temperature and engine structure location problem, obtained the reliablely and stablely decomposition combustion Expected Results of propellant of nontoxic cellular construction.
Description
Technical field
The present invention relates to rocket engine technical field, be specifically related to single group of a kind of nontoxic monopropellantUnit's engine, be applicable to spacecraft attitude control system, fighter plane emergency power unit or diveThe emergency ascent device of ship.
Background technology
Since the sixties, Shell company developed Auto-decomposition hydrazine (N2H4) catalyst S hell-405,Hydrazine class unit engine becomes most widely used unit engine in spacecraft. But hydrazine is analogizedEnter agent toxicity large, in production, test and use procedure, not only can be to personnel's life and healthCause serious harm, and can, to environment, also increase production, transmitting and working serviceCost. In fighter plane and submarine, also run into identical problem.
In order to overcome above-mentioned shortcoming, developing various nontoxic monopropellants both at home and abroad, as HAN(HAN) base propellant, ADN (ADN) base propellant, hydrazine nitroform (HNF) base propellant.
This SP has the advantages such as freezing point is stable, clean, steam is nontoxic, and deposits under normal pressureStorage safety, without catching fire and the danger of exploding, can reduce the security management requirement of propellant transport and storage.
At present, hydrazine class unit engine only has cartalytic decomposition effect, without combustion process, there is no combustion chamber,Decomposition temperature, lower than 1000 DEG C, only adopts filter, between catalytic bed and jet pipe between two-layer catalytic bed completelyAdopt baffle plate, and filter and baffle plate employing high temperature alloy.
Nontoxic monopropellant comprises oxidant, fuel, additive, water composition, in engine not onlyThere is cartalytic decomposition effect to also have combustion process, in order to meet or exceed the specific impulse of hydrazine class unit engine, combustionBurn temperature and conventionally exceed 1200 DEG C, high temperature alloy net and high temperature alloy porous plate that the past adopts can not be expiredFoot requirement etc.
Summary of the invention
The present invention is the specific impulse that improves hydrazine class unit engine, and ignition temperature exceedes 1200 DEG C conventionally, thisThe monopropellant engine of a kind of nontoxic monopropellant of bright proposition, this engine is by thrust chamber and magnetic valve (1)Composition, magnetic valve (1) and thrust chamber are bolted; Thrust chamber is by ejector filler (2) and body portion groupBecome; Ejector filler one end is connected with magnetic valve (1) by bolt, and one end is passed through bolt or welding and body portion and connectedConnect; Body portion comprises catalyst external crucible, filter (4), and dividing plate (5), bed (6) after catalyst, backstop (7),Baffle plate (8), combustion chamber (9), jet pipe (10) etc., the outside metalwork that adopts forms a whole, and urgesAgent external crucible (3) is ejector filler (2) and then, bed (6) and catalyst external crucible (3), combustion after catalystBurn chamber and be connected (9), filter (4), dividing plate (5) is mainly used to cut apart catalyst external crucible (3) and catalysisBed (6) after agent; Backstop (7), baffle plate (8) is mainly used to cut apart bed (6) and combustion chamber after catalyst(9); In combustion chamber, there is a jet pipe (10) in (9) downstream.
Due in some occasions, the response characteristic of engine is had relatively high expectations, and adds in engine body portionHot charging is put, and internal heater and external heat device is set thus, internal heater: open magnetic valve (1) nontoxicMonopropellant, from ejector filler (2) ejection, heats the propellant spraying from ejector filler with interior heater,Ensure that propellant fast and stable in catalytic bed decomposes; External heat device: with external heater by catalystExternal crucible is heated to predetermined temperature, opens the nontoxic monopropellant of magnetic valve (1) from ejector filler (2) ejection,Ensure that propellant fast and stable in the catalytic bed of preheating decomposes.
Propellant select nontoxic can the storage of raw materials: as HAN (HAN) base propellant, two nitrylsAmine ammonium (ADN) base propellant, hydrazine nitroform (HNF) base propellant.
Employing the invention solves the material that nontoxic monopropellant exists in monopropellant engine application aspectThe problem such as propellant combustion temperature and engine structure layout be can not meet, reliable in structure, expection obtainedEffect.
Brief description of the drawings
Fig. 1 is the not engine structure schematic diagram with heater of the present invention
Fig. 2 is the engine structure schematic diagram of band external heat device of the present invention
Fig. 3 is the engine structure schematic diagram of band internal heater of the present invention
Detailed description of the invention
Below in conjunction with accompanying drawing and example, the present invention is further detailed explanation.
Fig. 1 is the not engine structure schematic diagram with heater of the present invention, by magnetic valve (1), ejector filler(2), catalysis external crucible (3), filter (4), dividing plate (5), after catalyst bed (6), backstop (7),Baffle plate (8), combustion chamber (9), jet pipe (10) composition.
The startup of magnetic valve (1) control engine and closing, non-toxic aq propellant is by magnetic valve (1)Enter ejector filler (2) atomization, ejector filler (2) adopts many capillaries to suppress body portion high temperature to magnetic valveHeat return and soak, after catalyst external crucible (3) and catalyst, bed (6) is mainly used to decompose propellant after atomizationIn oxidant, the active component of catalytic bed is metal iridium, containing iridium amount between 5%-35%, before catalystBed adopts fine grained 20 order～30 order catalyst, ensures propellant fast decoupled, and after catalyst, bed adoptsCoarse granule catalyst (Φ 1.7X2.0 or Φ 3.3X3.8), reduces catalytic bed flow resistance, the propellant of atomizationFirst enter catalyst external crucible (3), carry out decomposed, then gas-liquid mixture enters bed after catalyst(6) continue to decompose, filter adopts the molybdenum net and the dividing plate that add coating to adopt the refractory metal porous that adds coatingPlate; Backstop adopts the molybdenum net and the baffle plate that add coating to adopt the refractory metal porous plate that adds coating; In catalytic bedCombustion chamber below, allows fuel mix burning in catabolite and propellant in catalytic bed, produces high temperatureHigh-pressure gas. In jet pipe, high-temperature high-pressure fuel gas heat energy in jet pipe transforms kinetic energy, forms high velocity air,Thereby generation thrust.
Fig. 2 is the engine structure schematic diagram of band external heat device of the present invention, by magnetic valve (1), ejector filler(2), catalysis external crucible (3), filter (4), dividing plate (5), after catalyst bed (6), backstop (7),Baffle plate (8), combustion chamber (9), jet pipe (10), external heat device (11) composition.
Fig. 3 is the engine structure schematic diagram of band internal heater of the present invention,
By magnetic valve (1), ejector filler (2), catalysis external crucible (3), filter (4), dividing plate (5), urgesBed (6) after agent, backstop (7), baffle plate (8), combustion chamber (9), jet pipe (10), internal heater (11)Composition.
Adopt HAN base SP, HAN as oxidant, methyl alcohol as fuel, waterAs solvent, organic additive is as igniting agent. Catalyst is a kind of porosity of attachment activity metal iridiumMatter, carrier is Al2O3, catalyst is 30% containing iridium amount, external crucible granularity 20-30 order, rear bed sizeFor Φ 1.3X1.5. The chamber length that this example adopts is 20mm. Dividing plate and baffle plate employing add coatingNiobium tungsten alloy, filter, backstop adopt molybdenum net.
As shown in Figure 4 first, magnetic valve opens 0.1s and cuts out 0.3s totally four times, HAN base propellant fromUnoccupied place ejection in the middle of ejector filler, a small amount of propellant catalyzed N that resolves in catalyst bed2O、N2、H2Deng product, and emit heat make catalytic bed temperature increase, then magnetic valve is opened 10s continuously, pushes away in a large numberEnter agent and decompose in catalytic bed, and emit more heat, make catalytic bed temperature higher, decomposition gas andIn propellant, methyl alcohol burns after by catalytic bed in combustion chamber, and the high temperature and high pressure gas of generation passes throughJet pipe produces thrust.
As shown in Figure 5, this engine of constant pressure curve shows is successfully realized pulse enable, has reached expection order.
Its catalytic process is as follows:
First catalytic bed is heated to 120 DEG C, magnetic valve is opened 10s continuously, and HAN base propellant is from sprayIn device, spray, propellant is the catalyzed N that resolves in catalyst bed2The products such as O, N2, H2, and in combustionBurn in chamber and burn, emit heat body portion temperature is increased, and the stable rising of constant pressure, the HTHP of generationGas produces thrust by jet pipe,
The constant pressure curve starting after heating 120 DEG C as shown in Figure 6, illustrates that this engine successfully realizes startup,Reach expection object.
Claims (5)
1. a monopropellant engine for nontoxic monopropellant, this engine is by thrust chamber and magnetic valveComposition, thrust chamber is made up of ejector filler and body portion, and body portion comprises two-layer catalytic bed and combustion chamber, its featureBe that catalytic bed adopts double-layer structure, external crucible adopts fine grained 20 order～30 order catalyst, and rear bed adoptsCoarse granule catalyst, described coarse granule catalyst is the catalyst of Φ 1.7 × 2.0 or Φ 3.3 × 3.8, adoptsWith the active component of catalyst be metal iridium, between 5%-35%, have one after catalytic bed containing iridium amountCombustion chamber, between the catalytic bed of front and back, between catalytic bed and combustion chamber, exist add coating refractory metal net andAdd the refractory metal porous plate of coating.
2. according to the monopropellant engine of a kind of nontoxic monopropellant described in claims 1, itsBe characterised in that start mode, adopt engine prepulsing starting under room temperature condition, the width of prepulsing exists0.05-0.5s, pulse number is 2-10 time.
3. according to the monopropellant engine of the nontoxic monopropellant described in claims 1, its feature existsIn start mode, at the outside heater that increases of catalytic bed, make catalytic bed be heated to 100 DEG C and start aboveMachine starting.
4. according to the monopropellant engine of the nontoxic monopropellant described in claims 1, its feature existsAccording to the feature of propellant, between catalytic bed and ejector filler, increase inner heating device, catalytic bed is addedHeat is to more than 100 DEG C engine start.
5. according to the monopropellant engine of the nontoxic monopropellant described in claims 1, its feature existsBe HAN HAN base propellant or ADN ADN base propellant or nitroform in the propellant adoptingHydrazine HNF base propellant.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201010052277.0A CN106134388B (en) | 2010-12-10 | 2010-12-10 | A kind of monopropellant engine of nontoxic monopropellant |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201010052277.0A CN106134388B (en) | 2010-12-10 | 2010-12-10 | A kind of monopropellant engine of nontoxic monopropellant |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106134388B true CN106134388B (en) | 2013-12-11 |
Family
ID=57251098
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201010052277.0A Active CN106134388B (en) | 2010-12-10 | 2010-12-10 | A kind of monopropellant engine of nontoxic monopropellant |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106134388B (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106014688A (en) * | 2016-05-10 | 2016-10-12 | 北京控制工程研究所 | Flow control device and method |
| CN106194502A (en) * | 2016-07-15 | 2016-12-07 | 北京航空航天大学 | A kind of solid-liquid Attitude rocket engine |
| CN109882316A (en) * | 2019-02-20 | 2019-06-14 | 上海空间推进研究所 | Length adjustable catalytic bed for monopropellant rocket engine |
| CN110043391A (en) * | 2019-04-17 | 2019-07-23 | 上海空间推进研究所 | Cellular-type catalytic bed and engine propulsion method |
| CN110332059A (en) * | 2019-04-25 | 2019-10-15 | 北京控制工程研究所 | A kind of connection structure for single group member high temperature alloy ejector filler and ceramic spray pipe |
| CN110486190A (en) * | 2019-07-24 | 2019-11-22 | 北京控制工程研究所 | A kind of injection device of monopropellant engine |
| CN110500200A (en) * | 2019-05-28 | 2019-11-26 | 北京控制工程研究所 | A kind of micrometeor green high-capacity single group member thruster structure |
| CN110645117A (en) * | 2019-09-18 | 2020-01-03 | 北京控制工程研究所 | Ceramic thrust chamber for monopropellant hydroxyl nitrate amino thruster |
| CN111550328A (en) * | 2020-05-09 | 2020-08-18 | 北京控制工程研究所 | Ignition method for realizing rapid normal-temperature start of hydroxylamine nitrate engine |
| CN114963238A (en) * | 2022-04-18 | 2022-08-30 | 北京控制工程研究所 | Non-toxic single-component engine reaction chamber and assembly method |
-
2010
- 2010-12-10 CN CN201010052277.0A patent/CN106134388B/en active Active
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106014688A (en) * | 2016-05-10 | 2016-10-12 | 北京控制工程研究所 | Flow control device and method |
| CN106014688B (en) * | 2016-05-10 | 2017-11-07 | 北京控制工程研究所 | A kind of volume control device and method |
| CN106194502A (en) * | 2016-07-15 | 2016-12-07 | 北京航空航天大学 | A kind of solid-liquid Attitude rocket engine |
| CN106194502B (en) * | 2016-07-15 | 2018-03-02 | 北京航空航天大学 | A kind of solid-liquid Attitude rocket engine |
| CN109882316A (en) * | 2019-02-20 | 2019-06-14 | 上海空间推进研究所 | Length adjustable catalytic bed for monopropellant rocket engine |
| CN110043391A (en) * | 2019-04-17 | 2019-07-23 | 上海空间推进研究所 | Cellular-type catalytic bed and engine propulsion method |
| CN110332059A (en) * | 2019-04-25 | 2019-10-15 | 北京控制工程研究所 | A kind of connection structure for single group member high temperature alloy ejector filler and ceramic spray pipe |
| CN110500200A (en) * | 2019-05-28 | 2019-11-26 | 北京控制工程研究所 | A kind of micrometeor green high-capacity single group member thruster structure |
| CN110500200B (en) * | 2019-05-28 | 2021-02-09 | 北京控制工程研究所 | Micro-flow green high-energy single-component thruster structure |
| CN110486190A (en) * | 2019-07-24 | 2019-11-22 | 北京控制工程研究所 | A kind of injection device of monopropellant engine |
| CN110645117A (en) * | 2019-09-18 | 2020-01-03 | 北京控制工程研究所 | Ceramic thrust chamber for monopropellant hydroxyl nitrate amino thruster |
| CN111550328A (en) * | 2020-05-09 | 2020-08-18 | 北京控制工程研究所 | Ignition method for realizing rapid normal-temperature start of hydroxylamine nitrate engine |
| CN114963238A (en) * | 2022-04-18 | 2022-08-30 | 北京控制工程研究所 | Non-toxic single-component engine reaction chamber and assembly method |
| CN114963238B (en) * | 2022-04-18 | 2023-07-14 | 北京控制工程研究所 | Non-toxic single-component engine reaction chamber and assembly method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106134388B (en) | A kind of monopropellant engine of nontoxic monopropellant | |
| Li et al. | Comparative investigation on combustion characteristics of ADN-based liquid propellants in inert gas and oxidizing gas atmospheres with resistive ignition method | |
| US8024918B2 (en) | Rocket motor having a catalytic hydroxylammonium (HAN) decomposer and method for combusting the decomposed HAN-based propellant | |
| JP4232820B2 (en) | Thruster device using nitrous oxide | |
| CN109595100B (en) | Electric ignition green unit liquid rocket engine structure | |
| CN106134417B (en) | Low-thrust rocket | |
| JP2003524096A (en) | Rocket motor assembly | |
| CN104632467A (en) | Rocket thrust chamber provided with acoustic cavity and applied to supersonic airliner and supply system thereof | |
| US6849247B1 (en) | Gas generating process for propulsion and hydrogen production | |
| EP2158395B1 (en) | Hydroxy amine based staged combustion hybrid rocket motor | |
| CN102175041B (en) | Dividing wall type regenerative cooling air oxygen alcohol torch type igniter | |
| KR20150008903A (en) | Improved reactor for ammonium dinitramide-based liquid monopropellants, and thruster including the reactor | |
| CN110645117B (en) | Ceramic thrust chamber for monopropellant hydroxyl nitrate amino thruster | |
| CN111173647A (en) | Two-component nitrous oxide engine | |
| KR101069553B1 (en) | Bipropellant rocket engine using Heat of hydrogen peroxide decomposition and propulsion method thereof | |
| CN106014688B (en) | A kind of volume control device and method | |
| JP4333943B2 (en) | High-temperature gas generation method using HAN / HN-based monopropellant | |
| JP2004257318A (en) | Propulsion apparatus and flying object including the same and method for igniting propulsion apparatus | |
| US3673801A (en) | Propulsion method using catalytic decomposition of hydrazine | |
| Peretz et al. | Development of a laboratory-scale system for hybrid rocket motor testing | |
| JP2009085155A (en) | Bi-propellant thruster | |
| Chehroudi et al. | Liquid propellants and combustion: fundamentals and classifications | |
| CN105715409A (en) | Annular solid-liquid catalytic ignition engine | |
| JP2010229853A (en) | Catalyst decomposition type thruster for space vehicle | |
| KR20150008902A (en) | Improved reactor for ammonium dinitramide-based liquid mono-propellants, and thruster including the reactor |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR03 | Grant of secret patent right | ||
| GRSP | Grant of secret patent right | ||
| DC01 | Secret patent status has been lifted | ||
| DCSP | Declassification of secret patent |