CN106837608A - Fire change propulsive solid-liquid rocket structure in a kind of decking end - Google Patents
Fire change propulsive solid-liquid rocket structure in a kind of decking end Download PDFInfo
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- CN106837608A CN106837608A CN201710214237.3A CN201710214237A CN106837608A CN 106837608 A CN106837608 A CN 106837608A CN 201710214237 A CN201710214237 A CN 201710214237A CN 106837608 A CN106837608 A CN 106837608A
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- Prior art keywords
- powder column
- burning
- liquid rocket
- spray orifice
- combustion
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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
- F02K9/72—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)
- Nozzles (AREA)
Abstract
The present invention discloses a kind of decking end combustion change propulsive solid-liquid rocket structure, including engine skull, burning chamber shell and the jet pipe housing being sequentially coaxially connected from front to back.Oxidant enters combustion chamber by the inlet channel of engine skull front end, and segmentation end-burning grain is filled with combustion chamber, and the spray orifice of certain amount is all set on each section of powder column, and the equal coaxial design of corresponding spray orifice, spray bore dia is different.Oxidant carries out cigarette burning by the rear end face that spray orifice reaches segmentation end-burning grain, and powder column rear end face is integrally retired.High-temperature high-pressure fuel gas after burning are expanded by Laval nozzle and accelerate to spray, and produce reaction thrust.In the case where oxidizer flow rate is constant, as long as the diameter of the length and spray orifice for controlling different sections of powder columns can just accomplish stabilization, accurate change propulsive.
Description
Technical field
Invention belongs to rocket engine technical field, and in particular to a kind of decking end combustion change propulsive solid-liquid fire
Arrow engine structure.
Background technology
Solid-liquid rocket uses liquid oxidizer and solid fuel, liquid-propellant rocket engine has been had both in structure and has been consolidated
The common feature of body rocket engine, with security it is good, easily to carry out thrust regulation, powder column good stability, the feature of environmental protection good, easy
The advantages of shutdown and restarting, good economy performance, can be used for the fields such as sounding rocket, rail control engine, Variable Thrust Engine.
Meanwhile, solid-liquid rocket there is also that loading density is low, efficiency of combustion is low, oxygen combustion is than lacking for changing
Point.
According to the operation principle of rocket engine, the thrust of engine can be by changing propellant combination, propellant stream
The parameters such as amount, nozzle exit area and nozzle throat area are adjusted.But due to physical limit, propellant is combined and is sprayed
Pipe discharge area is controlled and adjusts extremely difficult, and because hot-fluid is very high, nozzle throat area is also difficult to change.Cause
This, the flow for changing propellant is regulation rocket engine thrust most common method.
Existing change propulsive solid-liquid rocket is mainly carries out thrust regulation by adjusting the flow of oxidant.This
The regulative mode of sample needs to set extra flow regulator in systems, increased the complexity of system.And change propulsive
Solid-liquid rocket during thrust regulation, when oxidizer flow rate occurs wide variation, in order to by injection pressure drop control
In the reasonable scope, in addition it is also necessary to which, using unique injection technique, this can also increase the complexity of system, while reducing reliability.
The content of the invention
In order to solve the above problems, patent of the present invention proposes a kind of decking end combustion change propulsive solid-liquid rocket knot
Structure, can accomplish stabilization, accurate change propulsive.
Change propulsive solid-liquid rocket structure is fired at decking end of the present invention, including be sequentially coaxially connected from front to back
Engine skull, burning chamber shell and jet pipe housing；Powder column is installed in combustion chamber shell body.Powder column is segmentation end-burning grain, by
At least n sections of powder column composition, n is positive integer, n ＞ 1；The interconnected spray orifice being related to vertically is provided with each section of powder column.
Thus, control oxygen to fire ratio by changing each section of spray orifice aperture of powder column, and then control thrust；And by changing
Each section of length of powder column provides the working time under thrust controlling every section of powder column.
The advantage of the invention is that：
1st, combustion change propulsive solid-liquid rocket structure in decking end of the present invention, the dress of a change solid-liquid rocket
Medicine form, it is not necessary to which the structure to solid-liquid rocket is redesigned；
2nd, combustion change propulsive solid-liquid rocket structure in decking end of the present invention, sends out with traditional change propulsive solid-liquid rocket
Motivation is compared, it is not necessary to is changed the flow of oxidant in the course of the work, is reduced the complexity of induction system, improves reliability
Property；
3rd, decking end of the present invention combustion change propulsive solid-liquid rocket structure, end burn engine is in the course of the work
, than keeping constant, grainend is integrally retired for burning area and oxygen combustion；In the case where oxidizer flow rate is constant, as long as controlling
The length of different section powder columns and the diameter of spray orifice can just accomplish stabilization, accurate change propulsive；
4th, combustion change propulsive solid-liquid rocket structure in decking end of the present invention, in powder charge design, is fired using end face
Powder charge medicine shape is burnt, oxygen fires the steady of ratio in can improving filling fraction, the slenderness ratio of reduction engine, the maintenance combustion process of powder column
It is fixed, and the remaining medicine quality of engine can be reduced；
5th, combustion change propulsive solid-liquid rocket structure in decking end of the present invention, in engine working process, keeps
The state of cigarette burning, because combustion zone is away from engine head and valve, thermal protection is easily realized.
Brief description of the drawings
Fig. 1 is that change propulsive solid-liquid rocket structural representation is fired at decking end of the present invention；
Fig. 2 is that powder column spray orifice arrangement mode shows during change propulsive solid-liquid rocket structure is fired at decking end of the present invention
It is intended to.
In figure：
1- engine skull 2- combustion chambers forward flange 3- burning chamber shells
4- powder column heat insulation layers 5- segmentation end-burning grain 6- combustion chambers rear flange
7- jet pipe housing 8- jet pipe heat insulation layer 9- spray orifices
Specific embodiment
Patent of the present invention is described further below in conjunction with the accompanying drawings.
Patent of the present invention proposes a kind of decking end combustion change propulsive solid-liquid rocket scheme, and its structure includes starting
Nose cover 1, combustion chamber forward flange 2, burning chamber shell 3, powder column heat insulation layer 4, segmentation end-burning grain 5, combustion chamber rear flange 6, spray
Tube shell 7 and jet pipe heat insulation layer 8, as shown in Figure 1.
The burning chamber shell 3 is columnar structured, and its front end face is threadably secured and is provided with combustion respectively with rear end face
Burn room forward flange 2 and combustion chamber rear flange 6.The front end of engine skull 1 has inlet channel, for the supply of oxidant, oxidation
Agent can select O2、N2The gaseous oxidants such as O.Be designed with annular boss on the rear end face of engine skull 1, for combustion chamber shell
The front end face of body 3 coordinates, and realizes the radial positioning between engine skull 1 and burning chamber shell 3.Engine skull 1 and burning
It is coaxially connected by stay bolt between room forward flange 2；It is simultaneously close by mounting O-shaped in the groove that designs in the annular boss circumference
Seal, realizes the sealing of chamber front end.
Powder column heat insulation layer 4 is installed in above-mentioned burning chamber shell 3.The material of powder column heat insulation layer 4 is the silica high of resistance to ablation, its
By being adhesively fixed between the internal face of outside wall surface and burning chamber shell 3.Powder column heat insulation layer 4 is used for hindering heat to burning chamber shell
3 transmission, so that burning chamber shell 3-dimensional is held in relatively low temperature.
It is coaxially connected using stay bolt between the front end of jet pipe housing 7 and combustion chamber rear flange 6.Jet pipe heat insulation layer 8 is adopted
It is made of the heat-insulating material of resistance to ablation and antiscour, its outside wall surface passes through to be adhesively fixed with the internal face of jet pipe housing 7.Jet pipe is exhausted
Thermosphere 8 is used for ensureing that jet pipe housing 7, from the invasion and attack of heat and washing away for particle, has jet pipe housing 7 effect of protection.Spray
Pipe heat insulation layer 8 using leading portion convergence, back segment expansion Laval nozzle in the form of, it is ensured that engine high-temperature combustion gas it is swollen
Swollen and acceleration sprays, to produce ideal thrust.
The segmentation end-burning grain 5 is cylindrical structural, and the fuel commonly used using solid-liquid rocket is made, such as HTPB
(holding alkyl polybutadiene), PE (polyethylene) and PMMA (polymethyl methacrylate) etc., are co-axially located at powder column heat insulation layer 4
It is interior.Thrust as needed and working time, segmentation end-burning grain 5 are divided into multistage filling, are offered along powder column on each section of powder column
The spray orifice 9 of axial direction, spray orifice 9 radially divides multi-tier arrangement in powder column, as shown in Fig. 2 every layer of spray orifice 9 is circumferential uniform；And
Spray orifice 9 on each section of powder column makes spray orifice 9 corresponding on each segmentation right powder column 5 in end in the circumferential position correspondence of powder column
Connection and coaxial, formation spray passage.Oxygen is controlled to fire ratio by changing each section of aperture of the spray orifice of powder column 9；Simultaneously by changing
Become every section of length of powder column to control the working time under every section of thrust.Powder column is given in Fig. 1 and is divided into two sections of signals of filling
Figure, thrust as needed is more than the aperture of back segment powder column spray orifice 9 determining the aperture of spray orifice 9 of leading portion powder column.In powder column dress
In filling out, the thrust that the aperture of every section of powder column will be as needed determines that not necessarily the aperture of leading portion powder column is more than back segment medicine
The aperture of post.
When the decking end combustion change propulsive solid-liquid rocket works, oxidant passes through the front end of engine skull 1
Inlet channel enter burning chamber shell 3 in, be segmented end-burning grain 5 front end face and engine skull 1 rear end face between have
Certain cavity volume, is that oxidant is shunted and provided buffering into each spray orifice 9 of segmentation end-burning grain 5.Oxidant leads to
The rear end face that spray passage reaches segmentation end-burning grain 5 is crossed, when oxidant flow velocity exceedes critical flow velocity, engine only occurs end
Face is burnt, and powder column rear end face is integrally retired.Because powder column is divided into multistage filling, each section of footpath of the spray orifice of powder column 9 is different, therefore often
After section powder column has burnt, oxygen combustion ratio can change, so as to change thrust.In the case where oxidizer flow rate is constant, spray
Oxygen of the diameter in hole 9 according to obtained by being calculated as thrust fires ratio to determine, every section of length of powder column is according to burn rate and every section of thrust
Under working time determine, as long as the diameter of the length and spray orifice 9 for controlling different sections of powder columns can just accomplish stabilization, accurate become
Thrust.High-temperature high-pressure fuel gas after burning are expanded and are added by the Lavalle shape nozzle structure in engine jet pipe heat insulation layer 8
Speed sprays, and produces reaction thrust.
Claims (3)
1. a kind of decking end combustion change propulsive solid-liquid rocket structure, including sequentially coaxially connected from front to back start
Nose cover, burning chamber shell and jet pipe housing；Powder column is installed in combustion chamber shell body；It is characterized in that：Powder column is the combustion of segmentation end
Powder column, is made up of at least n sections of powder column, and n is positive integer, n ＞ 1；The interconnected spray for designing vertically is provided with each section of powder column
Orifice.
2. change propulsive solid-liquid rocket structure is fired at a kind of decking end as claimed in claim 1, it is characterised in that：Pass through
Change each section of spray orifice aperture of powder column to control oxygen to fire ratio, and then control thrust.
3. change propulsive solid-liquid rocket structure is fired at a kind of decking end as claimed in claim 1, it is characterised in that：Pass through
Change each section of length of powder column to control every section of powder column to provide the working time under thrust.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710214237.3A CN106837608A (en) | 2017-04-01 | 2017-04-01 | Fire change propulsive solid-liquid rocket structure in a kind of decking end |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710214237.3A CN106837608A (en) | 2017-04-01 | 2017-04-01 | Fire change propulsive solid-liquid rocket structure in a kind of decking end |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106837608A true CN106837608A (en) | 2017-06-13 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710214237.3A Pending CN106837608A (en) | 2017-04-01 | 2017-04-01 | Fire change propulsive solid-liquid rocket structure in a kind of decking end |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106837608A (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108569422A (en) * | 2018-02-11 | 2018-09-25 | 浙江兆华机械制造有限公司 | A kind of rocket segmental structure |
| CN109237517A (en) * | 2018-08-12 | 2019-01-18 | 梁智斌 | Annular jet propeller |
| CN112211749A (en) * | 2020-09-18 | 2021-01-12 | 西北工业大学 | Small solid rocket engine |
| CN112253330A (en) * | 2020-08-28 | 2021-01-22 | 上海航天化工应用研究所 | Forming device for freely filling silver-embedded wire into explosive column and using method thereof |
| CN112610359A (en) * | 2020-12-28 | 2021-04-06 | 中国航天空气动力技术研究院 | Solid rocket engine fixing device of embedded installation |
| CN112983676A (en) * | 2021-03-31 | 2021-06-18 | 西北工业大学 | Novel solid rocket engine combustion chamber grain |
| CN113357051A (en) * | 2021-06-25 | 2021-09-07 | 中国科学院力学研究所 | Internal spiral injection type solid-liquid engine explosive column |
| CN114856862A (en) * | 2022-06-14 | 2022-08-05 | 中国科学院力学研究所 | Spiral nested type explosive column of variable thrust solid-liquid rocket engine and manufacturing method |
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| US3789610A (en) * | 1967-06-21 | 1974-02-05 | Us Army | Tandem solid-hybrid rocket motor |
| US3807170A (en) * | 1967-03-16 | 1974-04-30 | Us Army | Fuel injection subsystem for supersonic combustion |
| US5404715A (en) * | 1992-12-09 | 1995-04-11 | Societe Europeenne De Propulsion | Liquid propellant rocket engine with parallel auxiliary flow, and an integrated gas generator |
| CN103967653A (en) * | 2014-04-28 | 2014-08-06 | 北京航空航天大学 | Axial injection end combustion solid-liquid rocket engine structure |
| RU150828U1 (en) * | 2014-04-16 | 2015-02-27 | Федеральное государственное казенное военное образовательное учреждение высшего профессионального образования "ВОЕННАЯ АКАДЕМИЯ МАТЕРИАЛЬНО-ТЕХНИЧЕСКОГО ОБЕСПЕЧЕНИЯ имени генерала армии А.В. Хрулева" | MOTOR UNIT WITH TANGENTIAL-SLOT TYPE Aperture Diaphragms |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| GB1074743A (en) * | 1963-07-11 | 1967-07-05 | Onera (Off Nat Aerospatiale) | Improvements in hot gas generators, and in particular rocket motors |
| US3807170A (en) * | 1967-03-16 | 1974-04-30 | Us Army | Fuel injection subsystem for supersonic combustion |
| US3789610A (en) * | 1967-06-21 | 1974-02-05 | Us Army | Tandem solid-hybrid rocket motor |
| US3715888A (en) * | 1969-11-26 | 1973-02-13 | Universal Oil Prod Co | Hybrid rocket |
| US5404715A (en) * | 1992-12-09 | 1995-04-11 | Societe Europeenne De Propulsion | Liquid propellant rocket engine with parallel auxiliary flow, and an integrated gas generator |
| RU150828U1 (en) * | 2014-04-16 | 2015-02-27 | Федеральное государственное казенное военное образовательное учреждение высшего профессионального образования "ВОЕННАЯ АКАДЕМИЯ МАТЕРИАЛЬНО-ТЕХНИЧЕСКОГО ОБЕСПЕЧЕНИЯ имени генерала армии А.В. Хрулева" | MOTOR UNIT WITH TANGENTIAL-SLOT TYPE Aperture Diaphragms |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108569422A (en) * | 2018-02-11 | 2018-09-25 | 浙江兆华机械制造有限公司 | A kind of rocket segmental structure |
| CN108569422B (en) * | 2018-02-11 | 2022-11-01 | 浙江兆华机械制造有限公司 | Rocket sectional structure |
| CN109237517A (en) * | 2018-08-12 | 2019-01-18 | 梁智斌 | Annular jet propeller |
| CN109237517B (en) * | 2018-08-12 | 2021-03-26 | 梁智斌 | Annular nozzle propeller |
| CN112253330A (en) * | 2020-08-28 | 2021-01-22 | 上海航天化工应用研究所 | Forming device for freely filling silver-embedded wire into explosive column and using method thereof |
| CN112211749A (en) * | 2020-09-18 | 2021-01-12 | 西北工业大学 | Small solid rocket engine |
| CN112610359A (en) * | 2020-12-28 | 2021-04-06 | 中国航天空气动力技术研究院 | Solid rocket engine fixing device of embedded installation |
| CN112610359B (en) * | 2020-12-28 | 2022-02-22 | 中国航天空气动力技术研究院 | Solid rocket engine fixing device of embedded installation |
| CN112983676A (en) * | 2021-03-31 | 2021-06-18 | 西北工业大学 | Novel solid rocket engine combustion chamber grain |
| CN113357051A (en) * | 2021-06-25 | 2021-09-07 | 中国科学院力学研究所 | Internal spiral injection type solid-liquid engine explosive column |
| CN114856862A (en) * | 2022-06-14 | 2022-08-05 | 中国科学院力学研究所 | Spiral nested type explosive column of variable thrust solid-liquid rocket engine and manufacturing method |
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| PB01 | Publication | ||
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Application publication date: 20170613 |