CN109555619A - A kind of no-load voltage ratio single group member liquid rocket engine thrust chamber - Google Patents
A kind of no-load voltage ratio single group member liquid rocket engine thrust chamber Download PDFInfo
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- CN109555619A CN109555619A CN201811649555.3A CN201811649555A CN109555619A CN 109555619 A CN109555619 A CN 109555619A CN 201811649555 A CN201811649555 A CN 201811649555A CN 109555619 A CN109555619 A CN 109555619A
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- China
- Prior art keywords
- group member
- single group
- load voltage
- voltage ratio
- rocket engine
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Catalysts (AREA)
Abstract
The present invention provides a kind of no-load voltage ratio single group member liquid rocket engine thrust chamber, including sequentially connected: multitube radial direction injection into orbit pipe 1, variable cross-section flow distributor 2, hard sifter injector 3, multi-cavity reaction chamber 4, combustion gas collecting chamber 5 and De Laval noz(zle) 6.The present invention solves in the conventional single group member liquid-propellant rocket engine big flow no-load voltage ratio course of work, the output oscillation of engine operation thrust；The miniaturization of engine structure under reasonable catalyst bed bed load-up condition；Engine is achieved to work long hours the beneficial effects such as reliable.
Description
Technical field
The present invention relates to rocket-powered apparatus fields, and in particular, to a kind of no-load voltage ratio single group member liquid-propellant rocket engine pushes away
Power room.
Background technique
Monopropellant engine has the characteristics that structure is simple, high reliablity, is widely used in satellite, delivery, guided missile at present
The fields such as weapon and deep space control survey.In Push Technology, monopropellant propulsion is suitble to the propulsion system of ox grade and the above magnitude, and ties
Structure is simple, high reliablity.Conventional single group member thrust chamber is catalyzed bed structure using axial flowing, due to bed load limitation, with pushing away
Power increases, and catalytic bed diameter sharply increases, and structure efficiency reduces, therefore single group member thrust chamber is not suitable for high thrust motor.
Normal thrust range is 1N~1000N.
The explanation or report without finding technology similar to the present invention domestic at present, is also not yet collected into similar both at home and abroad
Data.
Summary of the invention
For the defects in the prior art, the object of the present invention is to provide a kind of no-load voltage ratio single group member liquid-propellant rocket engines to push away
Power room.
A kind of no-load voltage ratio single group member liquid rocket engine thrust chamber provided according to the present invention, including sequentially connected: it is more
Caliber is to injection into orbit pipe 1, variable cross-section flow distributor 2, hard sifter injector 3, multi-cavity reaction chamber 4, combustion gas collecting chamber 5 and draws
Cut down your jet pipe 6；
Wherein, according to the variation of Propellant Supply flow, propellant enters variable cross-section flow by multitube radial direction injection into orbit pipe 1
Distributor 2 guarantees that realizing in flow process for different flow propellant evenly distributes, then is pushed away by the realization of hard sifter injector 3
High-temperature high-pressure fuel gas is formed into the catalyst reaction in the uniform spray of agent and multi-cavity reaction chamber 4, multi-cavity reaction chamber 4 is by multiple anti-
Chamber is answered to form, each chamber can work independently, and rectified action of the high-temperature high-pressure fuel gas through combustion gas collecting chamber 5 passes through Laval
Jet pipe 6 forms the gas with high speed kinetic energy, to generate deboost.
Preferably, the propellant includes Hydrazine fuel.
Preferably, the multitube radial direction injection into orbit pipe 1 is a supervisor and more spray branch pipe compositions.
Preferably, the variable cross-section flow distributor 2 is variable section runner.
Preferably, the hard sifter injector 3 is made of multi-layer sintering net.
Preferably, the multi-cavity reaction chamber 4 is radial collet form, be divided into two layers, every layer inside and outside have it is independent multiple
Independent reaction member.
Preferably, the combustion gas collecting chamber 5 is variable cross-section chamber.
Preferably, the energy conversion device 6 is De Laval noz(zle).
Compared with prior art, the present invention have it is following the utility model has the advantages that
The present invention is using set catalytic bed and radial spray and radial catalysis bed structure radial direction collet engine structure identical
Structure size under can effectively reduce the bed load of single group member liquid-propellant rocket engine, reduce catalyst breakage rate, improve hair
Motivation overall work thermal environment improves engine performance.By flow regulative mode, thrust chamber is suitable for big flow no-load voltage ratio, real
The existing electrodeless output of motor power.
Detailed description of the invention
Upon reading the detailed description of non-limiting embodiments with reference to the following drawings, other feature of the invention,
Objects and advantages will become more apparent upon:
Fig. 1 is sectional view of the invention；
Appended drawing reference:
1: multitube radial direction injection into orbit pipe；2: variable cross-section flow distributor；3: hard sifter injector；4: multi-cavity reaction chamber；5:
Combustion gas collecting chamber；6: De Laval noz(zle).
Specific embodiment
The present invention is described in detail combined with specific embodiments below.Following embodiment will be helpful to the technology of this field
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill of this field
For personnel, without departing from the inventive concept of the premise, several changes and improvements can also be made.These belong to the present invention
Protection scope.
As shown in Figure 1, a kind of no-load voltage ratio single group member liquid rocket engine thrust chamber provided by the invention, including be sequentially connected
: multitube radial direction injection into orbit pipe 1, variable cross-section flow distributor 2, hard sifter injector 3, multi-cavity reaction chamber 4, combustion gas collecting chamber 5
And De Laval noz(zle) 6.
Wherein, according to the variation of Propellant Supply flow, propellant enters variable cross-section flow by multitube radial direction injection into orbit pipe 1
Distributor 2 guarantees that realizing in flow process for different flow propellant evenly distributes, then is pushed away by the realization of hard sifter injector 3
High-temperature high-pressure fuel gas is formed into the catalyst reaction in the uniform spray of agent and multi-cavity reaction chamber 4, multi-cavity reaction chamber 4 is by multiple anti-
Chamber is answered to form, each chamber can work independently, and rectified action of the high-temperature high-pressure fuel gas through combustion gas collecting chamber 5 passes through Laval
Jet pipe 6 forms the gas with high speed kinetic energy, to generate deboost.
In the present embodiment, propellant includes Hydrazine fuel.Multitube radial direction injection into orbit pipe 1 is a supervisor and more spray branch
Pipe composition.Variable cross-section flow distributor 2 is variable section runner.Hard sifter injector 3 is made of multi-layer sintering net.Multi-cavity reaction
Room 4 is radial collet form, and being divided into two layers, every layer inside and outside has independent multiple independent reaction members.Combustion gas collecting chamber 5 is
Variable cross-section chamber.Energy conversion device 6 is De Laval noz(zle).
Propellant forms certain initial velocity after multitube radial direction injection into orbit pipe carries out flow just distribution under the effect of the pressure
Degree, into variable cross-section flow distributor, evenly distributes propellant again, guarantees that identical injection rate enters porous material spray
Device forms uniform drop spray, and injection direction is that engine is radial, and propellant is contacted with catalyst, and orderly catalysis occurs
Decomposition reaction.Cartalytic decomposition effect releases heat and accelerates reaction under the effect of liquid propellant thermal environment.In the extremely short time
Interior, high-temperature fuel gas establishes higher pressure in engine reaction unit, and high-temperature high-pressure fuel gas is through combustion gas collecting chamber, by radial flow
The dynamic fuel gas reforming combustion gas for axial flow, then acted on through De Laval noz(zle), it realizes that thermal energy is converted to kinetic energy, is sprayed by spout
Form thrust.Multi-cavity reaction chamber uses inside and outside absolute construction, can add spontaneous catalyst in internal chamber, help to improve hair
Spontaneous or non-spontaneous property catalyst is added in motivation resistant and oscillation resistant ability, the exterior chamber property of can choose, and steady operation is started in maintenance, drops
Low engine cost；Using independent multiple-cavity cell structure, can be effectively reduced in engine working process due to catalyst attrition band
The void effect come guarantees engine health reliably working；The radial jacket structured hot working environment of thrust chamber of the present invention simultaneously
More conventional monopropellant engine design is more friendly, and radial direction is jacket structured under identical structure size effectively reduces single group member
The catalyst bed bed load of liquid-propellant rocket engine facilitates the high thrustization design of single group member liquid-propellant rocket engine and flows greatly
Quantitative change is than steady operation in range.
Through overtesting, the present invention can be successfully applied on single group member 3000N thrust magnitude engine, and realizing engine can
By ignition operation；The single group member liquid-propellant rocket engine structure design scalability that the present invention plants adjustable thrust is strong, is applicable to ox
Grade, hundred Ns of grade change propulsive single group member liquid-propellant rocket engines.
A kind of single group member liquid rocket engine thrust chamber structure of big flow no-load voltage ratio of the present invention is radial vertical due to using
Body formula structure type effectively increases engine operation flow no-load voltage ratio under structure size permanence condition, realizes high thrust, big
The output of thrust no-load voltage ratio, while ensure that engine operational life；Radial collet design, engine center hollow out not only have simultaneously
Effect reduces engine weight, and improves the problems such as spray face temperature is excessively high in engine working process.Achieve single group member liquid
The beneficial effects such as rocket engine change propulsive operating mode.
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited to above-mentioned
Particular implementation, those skilled in the art can make a variety of changes or modify within the scope of the claims, this not shadow
Ring substantive content of the invention.In the absence of conflict, the feature in embodiments herein and embodiment can any phase
Mutually combination.
Claims (8)
1. a kind of no-load voltage ratio single group member liquid rocket engine thrust chamber, which is characterized in that including sequentially connected: multitube radially sprays
Note pipe (1), variable cross-section flow distributor (2), hard sifter injector (3), multi-cavity reaction chamber (4), combustion gas collecting chamber (5) and
De Laval noz(zle) (6)；
Wherein, according to the variation of Propellant Supply flow, propellant divides by multitube radial direction injection into orbit pipe (1) into variable cross-section flow
Orchestration (2) guarantees that realizing in flow process for different flow propellant evenly distributes, then is realized by hard sifter injector (3)
Catalyst reaction in the uniform spray of propellant and multi-cavity reaction chamber (4) forms high-temperature high-pressure fuel gas, multi-cavity reaction chamber (4) by
Multiple reaction chamber compositions, each chamber can work independently, and rectified action of the high-temperature high-pressure fuel gas through combustion gas collecting chamber (5) is led to
It crosses De Laval noz(zle) (6), the gas with high speed kinetic energy is formed, to generate deboost.
2. no-load voltage ratio single group member liquid rocket engine thrust chamber according to claim 1, which is characterized in that the propellant
Including Hydrazine fuel.
3. no-load voltage ratio single group member liquid rocket engine thrust chamber according to claim 1, which is characterized in that the multi-pipe-diameter
It is a supervisor and more spray branch pipe compositions to injection into orbit pipe (1).
4. no-load voltage ratio single group member liquid rocket engine thrust chamber according to claim 1, which is characterized in that the variable cross-section
Flow distributor (2) is variable section runner.
5. no-load voltage ratio single group member liquid rocket engine thrust chamber according to claim 1, which is characterized in that the porous material
Material ejector filler (3) is made of multi-layer sintering net.
6. no-load voltage ratio single group member liquid rocket engine thrust chamber according to claim 1, which is characterized in that the multi-cavity is anti-
Answer room (4) for radial collet form, being divided into two layers, every layer inside and outside there are independent multiple independent reaction members.
7. no-load voltage ratio single group member liquid rocket engine thrust chamber according to claim 1, which is characterized in that the combustion gas is received
Integrate room (5) as variable cross-section chamber.
8. no-load voltage ratio single group member liquid rocket engine thrust chamber according to claim 1, which is characterized in that the energy turns
It is De Laval noz(zle) that (6) are set in makeup.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811649555.3A CN109555619A (en) | 2018-12-30 | 2018-12-30 | A kind of no-load voltage ratio single group member liquid rocket engine thrust chamber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811649555.3A CN109555619A (en) | 2018-12-30 | 2018-12-30 | A kind of no-load voltage ratio single group member liquid rocket engine thrust chamber |
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| Publication Number | Publication Date |
|---|---|
| CN109555619A true CN109555619A (en) | 2019-04-02 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811649555.3A Pending CN109555619A (en) | 2018-12-30 | 2018-12-30 | A kind of no-load voltage ratio single group member liquid rocket engine thrust chamber |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114592989A (en) * | 2022-05-09 | 2022-06-07 | 西安航天动力研究所 | Liquid oxygen kerosene pintle injector thrust chamber and starting method thereof |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0829637A1 (en) * | 1995-06-13 | 1998-03-18 | Daimler-Benz Aerospace Aktiengesellschaft | Thruster |
| CN106134393B (en) * | 2010-12-15 | 2014-03-19 | 上海空间推进研究所 | Low thrust list constituent element peroxide rocket |
| CN104265507A (en) * | 2014-09-23 | 2015-01-07 | 贵州航天红光机械制造有限公司 | Thrust chamber injector of hydrazine type low-thrust single-unit engine |
| US20150121843A1 (en) * | 2012-05-09 | 2015-05-07 | Ecaps Ab | Reactor for ammonium dinitramide-based liquid mono-propellants, and thruster including the reactor |
| CN107143433A (en) * | 2017-05-17 | 2017-09-08 | 上海空间推进研究所 | Single group member liquid-propellant rocket engine radial direction chuck catalyst bed |
-
2018
- 2018-12-30 CN CN201811649555.3A patent/CN109555619A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0829637A1 (en) * | 1995-06-13 | 1998-03-18 | Daimler-Benz Aerospace Aktiengesellschaft | Thruster |
| CN106134393B (en) * | 2010-12-15 | 2014-03-19 | 上海空间推进研究所 | Low thrust list constituent element peroxide rocket |
| US20150121843A1 (en) * | 2012-05-09 | 2015-05-07 | Ecaps Ab | Reactor for ammonium dinitramide-based liquid mono-propellants, and thruster including the reactor |
| CN104265507A (en) * | 2014-09-23 | 2015-01-07 | 贵州航天红光机械制造有限公司 | Thrust chamber injector of hydrazine type low-thrust single-unit engine |
| CN107143433A (en) * | 2017-05-17 | 2017-09-08 | 上海空间推进研究所 | Single group member liquid-propellant rocket engine radial direction chuck catalyst bed |
Non-Patent Citations (1)
| Title |
|---|
| 周汉申: "单组元催化分解发动机喷注器的设计与研究", 《上海航天》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114592989A (en) * | 2022-05-09 | 2022-06-07 | 西安航天动力研究所 | Liquid oxygen kerosene pintle injector thrust chamber and starting method thereof |
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Application publication date: 20190402 |