CN106870205B - A kind of diplopore shape segmentation rotation powder charge solid-liquid rocket thrust chamber - Google Patents
A kind of diplopore shape segmentation rotation powder charge solid-liquid rocket thrust chamber Download PDFInfo
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- CN106870205B CN106870205B CN201710044584.6A CN201710044584A CN106870205B CN 106870205 B CN106870205 B CN 106870205B CN 201710044584 A CN201710044584 A CN 201710044584A CN 106870205 B CN106870205 B CN 106870205B
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- powder column
- component
- solid fuel
- powder
- intermediate cavity
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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
- F02K9/72—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid and solid propellants, i.e. hybrid rocket-engine plants
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Solid Fuels And Fuel-Associated Substances (AREA)
Abstract
A kind of diplopore shape segmentation rotation powder charge solid-liquid rocket thrust chamber scheme, including preceding combustion chamber component, leading portion solid fuel powder column, intermediate cavity component, back segment solid fuel powder column, after-burning chamber component, nozzle component, burning chamber shell are disclosed in the present invention.The fuel powder column is the identical diplopore shape powder column of two sections of geometric shapes, and two sections of powder columns rotate 30 ° -60 ° of angle filling.Intermediate cavity is set between two sections of powder columns, the material used is the high silicon oxygen of resistance to ablation, and intermediate cavity outside wall surface is Nian Jie with motor combustion chamber case inner wall.When engine operation, due to two sections of powder column rotation fillings, the stroke of oxidant and fuel in the combustion chamber is extended, simultaneously because the presence of intermediate cavity and the inhibition of back segment grainend, oxidant and fuel can be more fully mixed and burned, to effectively improve the burn rate and efficiency of combustion of solid-liquid rocket.
Description
Technical field
The present invention relates to solid-liquid rocket technical fields, are that a kind of diplopore shape segmentation rotation powder charge is solid specifically
Liquid thrust chamber.
Background technique
Solid-liquid rocket is a kind of new rocket combined using liquid oxidizer and solid fuel as propellant
Propulsion system.Since the fuel and oxidant of solid-liquid engine are stored respectively, start so it has different from solid or liquid
Unique feature of machine has the advantages that good economy performance, safety is good, the feature of environmental protection is good, is easy to thrust is adjusted.It is contemplated that space flight
Field, especially middle-size and small-size sounding rocket, inferior orbital vehicle and high-altitude high speed cruise flight device etc. have wide hair
Exhibition prospect.
But the oxidant and fuel due to solid-liquid rocket are out-phase, non-premix, are burnt indoor
Burning is a kind of typical diffusive combustion process, has thereby resulted in the solid fuel grain burning rate of solid-liquid rocket relatively
Low disadvantage.Further, since oxidant and fuel mixability are poor, therefore efficiency of combustion is generally sent out than liquid and solid-rocket
Motivation is all low.The burn rate and efficiency of combustion for improving solid-liquid rocket must be solved in the development process of solid-liquid rocket
Certainly the problem of.
Summary of the invention
The purpose of the present invention is to solve the above problems, propose a kind of diplopore shape segmentation rotation powder charge solid-liquid rocket hair
Motivation thrust chamber.After powder column segmentation rotation filling, the flow field of engine is greatly affected, the joining section meeting between powder column
Whirlpool is generated, it can extend the residence time of oxidant and fuel in the combustion chamber, enhance blending between the two, promote burning,
And then improve the burn rate of fuel and the efficiency of combustion of engine.
A kind of diplopore shape segmentation rotation powder charge solid-liquid rocket thrust chamber scheme, including preceding combustion chamber component, leading portion are double
Hole shape solid fuel powder column, intermediate cavity component, back segment diplopore shape solid fuel powder column, after-burning chamber component, nozzle component and burning
Room housing.
Radially load the solid fuel powder column of two sections of identical geometric shapes in the motor combustion chamber case, two sections
Powder column rotates 30 ° -60 ° of angle filling.All there are two perforative hole, the positional relationships in two holes on every section of solid fuel powder column
Can guarantee under identical burn rate with geometric dimension, combustion face retire intermediate cavity internal diameter boundary time and two holes burn when
Between it is identical.One section of intermediate cavity is set between two sections of powder columns, and the material used is the high silicon oxygen of resistance to ablation, not through leading portion powder column
The oxidant and leading portion powder column for participating in reaction are pyrolyzed but unburned fuel be relatively adequately mixed and burned in intermediate cavity.
Chamber component is fired before engine is assembled in the front end of motor combustion chamber case, the effect of preceding combustion chamber component mainly generates here
Reflux, promotes the gasification of liquid oxidizer, and the blending of enhancing engine oxidant and fuel here is started so as to improve
The burn rate of machine leading portion powder column and the combustion stability of engine.Assemble engine afterburner group in the rear end of motor combustion chamber case
The afterburner main function of part, engine is the blending further promoted between unreacted oxidant and fuel, and raising is started
The efficiency of combustion of machine.Engine jet pipe component is assembled in the rear end of after-burning chamber component.
The present invention has the advantages that
(1) present invention is prolonged after two sections of powder columns rotate 30 ° of -60 ° of angles fillings using diplopore shape segmentation rotation charge structure
The stroke of oxidant and fuel in the combustion chamber has been grown, fuel burn rate can be increased, has improved the efficiency of combustion of engine；
(2) intermediate cavity is arranged between two sections of powder columns in the present invention, is conducive to further promote unreacted fuel and oxidation
Blending between agent improves the efficiency of combustion of engine；
(3) present invention is using diplopore shape segmentation rotation charge structure, after two sections of powder columns rotate 30 ° of -60 ° of angles fillings, after
Section grainend has inhibition to upstream combustion gas, and the oxidant and fuel that upstream can be made not sufficiently combusted are diffused into back segment
Powder column channel center is sufficiently carried out mixed firinor fuel burning.This increases the burn rate of back segment powder column, and the efficiency of combustion of engine mentions
It is high；
(4) design of diplopore shape solid fuel grain configuration is utilized in the present invention, filling rate is higher, in combustion medicine
It is also not easy to fall off because of ablation among column, and the shape without changing engine chamber, with general solid-liquid rocket
Being replaced mutually property is good.
Detailed description of the invention
Fig. 1 is a kind of diplopore shape segmentation rotation powder charge solid-liquid rocket thrust chamber schematic diagram；
Fig. 2 is diplopore shape powder column geometry profile schematic diagram；
Fig. 3 is two sections of powder column rotation powder charge schematic diagrames.
In figure:
1-preceding combustion chamber component 2-leading portion solid fuel powder column 3-intermediate cavity component
4-back segment solid fuel powder column 5-after-burning, 6-nozzle components of chamber component
7-burning chamber shells
Specific embodiment
Below in conjunction with drawings and examples, the present invention is described in further detail.
The present invention is a kind of diplopore shape segmentation rotation powder charge solid-liquid rocket thrust chamber, as shown in Figure 1 and Figure 2, including
Preceding combustion chamber component 1, leading portion solid fuel powder column 2, intermediate cavity component 3, back segment solid fuel powder column 4, after-burning chamber component 5, jet pipe
Component 6, burning chamber shell 7.
The solid fuel powder column is packed into motor combustion chamber case, intermediate cavity outside wall surface and engine chamber shell
Internal wall surface passes through bonding cooperation.The rear end of engine jet pipe component, after-burning chamber component and burning chamber shell is connected using stay bolt
It connects, and airtight using O-ring seal guarantee.
The leading portion solid fuel powder column 2 and back segment solid fuel powder column 4 are the identical diplopore shape medicine of two sections of geometric shapes
Column, two sections of powder columns rotate 30 ° -60 ° of angle filling, and powder charge schematic diagram is as shown in Figure 3 (by two holes of diplopore shape powder column
Center of circle phase continuous cropping straight line, the line on the basis of the line of front end solid fuel powder column 2, on back segment solid fuel powder column 4
Need to rotate 30 ° -60 °, i.e. angle A in Figure of description 3), the outside wall surface of powder column and the inner wall of motor combustion chamber case 7
Face passes through bonding cooperation.The positional relationship and geometric dimension in two holes can guarantee that under identical burn rate, combustion face is moved back on powder column
The time for moving on to 3 internal diameter boundary of intermediate cavity is identical as the time that two holes are burnt.It is fired in leading portion solid fuel powder column 2 and back segment solid
Expect that intermediate cavity 3 is arranged between powder column 4, the material used is the high silicon oxygen of resistance to ablation, and the oxygen of reaction is had neither part nor lot in through leading portion powder column
Agent and leading portion powder column are pyrolyzed but unburned fuel be relatively adequately mixed and burned in intermediate cavity.
At the preceding combustion chamber component 1 and after-burning chamber component 5 of thrust chamber, the indoor fuel gas temperature that burns is very high, in its inner wall
The heat insulation layer that face bonding heat insulation composite material is made into, to form good thermal protection effect to it.The core of engine jet pipe component 6
Center portion part is the Laval nozzle of leading portion convergence, back segment expansion, it is ensured that the expansion and acceleration of engine high-temperature combustion gas spray,
To generate ideal thrust.
Engine jet pipe component 6, after-burning chamber component 5 and the rear end of burning chamber shell 7 are connected using stay bolt, and use O
Type sealing ring guarantees airtight.
When hybrid rocket engine works, the heat that combustion zone releases heats solid fuel, when solid fuel table
When face reaches certain temperature, solid fuel begins to gasify.Before liquid oxidizer is sprayed by ejector filler after combustion chamber component 1,
By being atomized and evaporating, and and influenced to gasify by combustion zone is exothermic, subsequently into leading portion solid fuel powder column 2 with it is solid
Gasification fuel is reacted.The effect of preceding combustion chamber component 1 mainly generates reflux here, promotes the gas of liquid oxidizer
Change, the blending of enhancing engine oxidant and fuel here, so as to improve the burn rate of engine leading portion powder column and start
The combustion stability of machine.
Had neither part nor lot in through leading portion solid fuel powder column 2 reaction oxidant and leading portion solid fuel powder column 2 pyrolysis but it is unburned
After the fuel of burning enters intermediate cavity 3, can more fully it be mixed.4 end face of back segment solid fuel powder column is to upstream combustion gas
With inhibition, the oxidant and fuel that upstream can be made not sufficiently combusted are diffused into back segment powder column channel center, fully
It is mixed and burned.This increases the burn rate of back segment solid fuel powder column 4, and the efficiency of combustion of engine improves.
Engine after-burning chamber component 5 is assembled in 7 rear end of motor combustion chamber case, and the after-burning chamber component 5 of engine is mainly made
With being the blending further promoted between unreacted oxidant and fuel, the efficiency of combustion of engine is improved.After burning
High-temperature high-pressure fuel gas expands by the Laval nozzle in engine jet pipe component 6 and accelerates to spray, and generates reaction thrust.
The present invention utilizes the design of diplopore shape solid fuel grain configuration, and filling rate is higher, in combustion in powder column
Between be also not easy to fall off because of ablation.And it is mutual with general solid-liquid rocket without the shape for changing engine chamber
Replaceability is good.
The present invention is rotated 30 ° of -60 ° of angles fillings, can be extended using diplopore shape segmentation rotation charge structure, two sections of powder columns
The stroke of oxidant and fuel in the combustion chamber, and back segment grainend has inhibition to upstream combustion gas, can make upstream
Not sufficiently combusted oxidant and fuel is diffused into back segment powder column channel center, is sufficiently carried out mixed firinor fuel burning, to increase combustion
Expect burn rate, improves the efficiency of combustion of engine.
Intermediate cavity is arranged between leading portion solid fuel powder column and back segment solid fuel powder column in the present invention, and the material used is
The high silicon oxygen of resistance to ablation, the oxidant and the pyrolysis of leading portion powder column but unburned fuel that reaction is had neither part nor lot in through leading portion powder column can be with
Relatively adequately be mixed and burned in intermediate cavity.
Claims (1)
1. a kind of diplopore shape segmentation rotation powder charge solid-liquid rocket thrust chamber, including preceding combustion chamber component, leading portion solid fuel
Powder column, intermediate cavity component, back segment solid fuel powder column, after-burning chamber component, nozzle component, burning chamber shell；
Preceding combustion chamber component is connected with the front end of burning chamber shell using stay bolt, engine jet pipe component, after-burning chamber component and combustion
The rear end for burning room housing is connected using stay bolt, and guarantees airtight, the front end solid fuel medicine of junction using O-ring seal
Column, intermediate cavity component, rear end solid fuel powder column are bonded on the inner wall of burning chamber shell, and all parts are coaxially set
It sets；
Leading portion solid fuel powder column and back segment solid fuel powder column are the identical diplopore shape powder column of two sections of geometric shapes, two sections of powder columns
The angle filling of 30 ° -60 ° of rotation；
Intermediate cavity is set between leading portion solid fuel powder column and back segment solid fuel powder column, the material used is the height of resistance to ablation
Silicon oxygen, had neither part nor lot in through leading portion powder column reaction oxidant and leading portion powder column pyrolysis but unburned fuel can intermediate cavity into
Row is relatively adequately mixed and burned.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710044584.6A CN106870205B (en) | 2017-01-19 | 2017-01-19 | A kind of diplopore shape segmentation rotation powder charge solid-liquid rocket thrust chamber |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710044584.6A CN106870205B (en) | 2017-01-19 | 2017-01-19 | A kind of diplopore shape segmentation rotation powder charge solid-liquid rocket thrust chamber |
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| CN106870205A CN106870205A (en) | 2017-06-20 |
| CN106870205B true CN106870205B (en) | 2019-04-05 |
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| CN108104942A (en) * | 2016-10-29 | 2018-06-01 | 熵零技术逻辑工程院集团股份有限公司 | A kind of solid fuel rotary power engine |
| CN112983676B (en) * | 2021-03-31 | 2023-06-13 | 西北工业大学 | Solid rocket engine combustion chamber grain |
| CN114251196B (en) * | 2021-09-26 | 2023-02-07 | 北京中科宇航技术有限公司 | Variable expansion ratio spray pipe of single-chamber double-thrust solid rocket engine |
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| JP4183475B2 (en) * | 2002-10-17 | 2008-11-19 | 株式会社Ｉｈｉエアロスペース | Solid rocket engine solid motor and its combustion method |
| US7921638B2 (en) * | 2006-04-20 | 2011-04-12 | Combustion Propulsion & Ballistic Technology Corp. | Bi-propellant rocket motor having controlled thermal management |
| CN103016208B (en) * | 2012-12-12 | 2015-02-11 | 北京航空航天大学 | Wheel-shaped charging device for hybrid 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 |
| CN106121864A (en) * | 2016-07-22 | 2016-11-16 | 北京航空航天大学 | A kind of head body portion combines multizone and is centrifuged spray solid-liquid rocket |
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