CN109236500A - A kind of Status of Low Cost Solid Rocket Motors powder charge combustion chamber unit and its processing method - Google Patents
A kind of Status of Low Cost Solid Rocket Motors powder charge combustion chamber unit and its processing method Download PDFInfo
- Publication number
- CN109236500A CN109236500A CN201810961272.6A CN201810961272A CN109236500A CN 109236500 A CN109236500 A CN 109236500A CN 201810961272 A CN201810961272 A CN 201810961272A CN 109236500 A CN109236500 A CN 109236500A
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- Prior art keywords
- fuel
- powder column
- oxidant
- lining
- heat insulation
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- 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.)
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Classifications
-
- 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
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
- F02K9/34—Casings; Combustion chambers; Liners thereof
-
- 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
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
- F02K9/34—Casings; Combustion chambers; Liners thereof
- F02K9/346—Liners, e.g. inhibitors
-
- 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
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
- F02K9/36—Propellant charge supports
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Testing Of Engines (AREA)
Abstract
The present invention provides the solid propellant rocket motor charge combustion chamber unit and its processing method of a kind of low cost, by in traditional powder column oxidant and fuel separation, the manufacturing of non-priming system in motor charge combustion chamber unit manufacturing process is set to produce in non-priming system manufacturer, to reduce its manufacturing cost.It include: shell and heat insulation layer, fuel lining, oxidant lining, fuel powder column and oxidant powder column positioned at enclosure interior；The heat insulation layer, fuel lining, oxidant lining, fuel powder column are non-priming system, and the oxidant powder column is priming system；Heat insulation layer is bonded on the shell inner peripheral surface, the fuel lining is bonded on the heat insulation layer inner peripheral surface, oxidant powder column and fuel powder column is respectively set along axial direction in the enclosure interior, the fuel powder column and oxidant powder column outer circumference surface are Nian Jie with the fuel lining inner peripheral surface respectively；It is isolated between the oxidant powder column and fuel powder column by the oxidant lining.
Description
Technical field
The present invention relates to a kind of motor charge combustion chamber units, belong to Solid Rocket Motor Technology field.
Background technique
Currently, solid propellant rocket is widely used in guided missile because of the features such as its structure is simple, non-maintaining, fast response time
Weapon and carrying space.With flourishing for business space flight market, solid propellant rocket research and development, manufacturing cost are reduced
Demand is more more and more urgent, and powder charge forms most important link as cost in each component of solid propellant rocket, and cost declining is latent
Power is maximum.
Conventional solid projectile charge combustion chamber unit is as shown in Figure 1, by shell 1, heat insulation layer 2, lining 3, powder column 4
Composition.Wherein heat insulation layer 2 is bonded on shell 1, and 3 outside of lining is Nian Jie with heat insulation layer 2, and inside is Nian Jie with powder column 4.It was manufactured
Journey are as follows: shell 1 is transferred to the powder charge producer for having priming system production qualification after manufacturing, made by powder charge producer according to heat insulation layer 2
Make and bonding with shell 1 → the series production cast of 3 coatings of lining → powder charge 4.Only powder charge 4 is priming system in each component part,
It is cast and is solidified by the medicine slurry that the components such as oxidant, fuel and adhesive are mixed into.Now widely used fourth hydroxyl three
The oxidant of constituent element propellant is AP (ammonium perchlorate), fuel is Al (aluminium powder), and adhesive is HTPB (end hydroxy butadiene).
Conventional solid projectile charge combustion chamber unit is disadvantageous in that in drop low cost aspect:
(1) oxidant, fuel and adhesive are uniformly mixed to form propellant, and integral cast is powder column 4, entire powder charge mixing
Process can only be produced in the producer for having priming system production qualification, and priming system production line is due to security requirement, to list
Position qualification and manpower, place, equipment requirement are very high, are unfavorable for cost reduction.
(2) manufacturing of the non-priming system such as heat insulation layer 2, lining 3 is unfavorable also in the manufacturer for having priming system qualification
It is reduced in cost.
Summary of the invention
In view of this, the present invention provides a kind of Status of Low Cost Solid Rocket Motors powder charge combustion chamber unit, pushed away not changing
Under the premise of agent component, oxidant and fuel are separated, non-priming system in motor charge combustion chamber unit manufacturing process is made
The manufacturing can be produced in non-priming system manufacturer, to reduce its manufacturing cost.
The solid propellant rocket motor charge combustion chamber unit of the described low cost includes: shell and positioned at enclosure interior
Heat insulation layer, fuel lining, oxidant lining, fuel powder column and oxidant powder column；The heat insulation layer, fuel lining, oxidant lining
Layer, fuel powder column are non-priming system, and the oxidant powder column is priming system；
The heat insulation layer is bonded on the shell inner peripheral surface, and oxidant is respectively set along axial direction in the enclosure interior
Powder column and fuel powder column are provided with fuel lining between the fuel powder column and the heat insulation layer inner peripheral surface, in the oxygen
Oxidant lining is provided between agent powder column and the heat insulation layer inner peripheral surface；The oxidant powder column and fuel powder column are axial
It is isolated between interface by the oxidant lining.
Its processing sequence are as follows: the manufacture of the heat insulation layer and with the fuel of case bonding → on the heat insulation layer inner peripheral surface
The corresponding region coating fuel lining of powder column → manufacture fuel powder column, and it is bonded fuel powder column and fuel lining → in the insulation
Oxidation is coated on the end face that the corresponding region of oxidant powder column and fuel powder column are docked with oxidant powder column on layer inner peripheral surface
Agent lining → manufacture oxidant powder column, and it is bonded oxidant powder column and oxidant lining.
When the solid propellant rocket motor charge combustion chamber unit is segmentation structure, the solid-rocket of the described low cost
Motor charge combustion chamber unit includes: the fuel bay section of more than one oxidant bay section and same number；The oxidizer compartment
Section and fuel bay section interval are to being connected in an entirety；
The oxidant bay section includes: shell and the heat insulation layer for being bonded in shell inner peripheral surface, is bonded in heat insulation layer
The oxidant powder column that periphery lining and setting bond together with lining inner peripheral surface inside housings；
The fuel bay section includes: shell and the heat insulation layer for being bonded in shell inner peripheral surface, is bonded in heat insulation layer inner circle
The fuel powder column that circumferential surface lining and setting bond together with lining inner peripheral surface inside housings.
Its processing sequence are as follows: first process oxidant bay section and fuel bay section respectively, then by complete the process more than one
Oxidant bay section and more than one fuel bay section interval are to being connected in an entirety.
The utility model has the advantages that
(1) traditional powder column is divided into oxidant powder column and fuel powder column by the present invention, thus by conventional solid rocket motor
The oxidant of priming system and fuel isolation, enable the fuel powder column as non-priming system non-in machine powder charge combustion chamber unit
The production of priming system manufacturer, is greatly lowered the requirement to producer, place, equipment, personnel, reduces costs.
(2) heat insulation layer and fuel lining are non-priming system, produce, reduce costs in non-priming system manufacturer.
Detailed description of the invention
The structural schematic diagram of Fig. 1 conventional solid projectile charge combustion chamber unit；
Fig. 2 is the Status of Low Cost Solid Rocket Motors powder charge combustion chamber unit structural schematic diagram in embodiment 1；
The structural schematic diagram of Fig. 3 conventional segmental solid propellant rocket motor charge combustion chamber unit；
Fig. 4 is the inexpensive segmented rocket engine powder charge combustion chamber unit structural schematic diagram in embodiment 2；
Wherein: 1- shell；2- heat insulation layer；3- lining；4- powder column；31- fuel lining, 32- oxidant lining, 41- fuel
Powder column, 42- oxidant powder column.
Specific embodiment
The present invention will now be described in detail with reference to the accompanying drawings and examples.
Embodiment 1:
To solve the problems, such as that solid propellant rocket motor charge is at high cost, the present embodiment provides a kind of solid-rockets of low cost
Motor charge combustion chamber unit and its processing method.
As shown in Fig. 2, the solid propellant rocket motor charge combustion chamber unit includes: shell 1 and inside shell 1
Heat insulation layer 2, fuel lining 31, oxidant lining 32, fuel powder column 41 and oxidant powder column 42.By traditional medicine i.e. in this programme
Column 4 is divided into 42 two parts of fuel agent powder column 41 and oxidant powder column.Wherein heat insulation layer 2, fuel lining 31, fuel powder column 41 are non-
Priming system manufactures in non-priming system manufacturer, is wherein divided into Al aluminium powder and HTPB end hydroxy butadiene for 41 groups of fuel powder column.
Oxidant powder column 42 is priming system, and group is divided into AP ammonium perchlorate and HTPB end hydroxy butadiene.
Oxidant powder column 42 and fuel powder column 41 is axially inside respectively set in shell 1, and 1 inner peripheral surface of shell is bonded with absolutely
Thermosphere 2 carries out radial isolation and bonding, oxidant powder column 42 by fuel lining 31 between fuel powder column 41 and heat insulation layer 2
Radial isolation and bonding is carried out by oxidant lining 32 between heat insulation layer 2, between oxidant powder column 42 and fuel powder column 41
Axial isolation and bonding are carried out by oxidant lining 32.Specifically: 2 outer circumference surface of heat insulation layer is Nian Jie with 1 inner peripheral surface of shell
Together, 2 inner peripheral surface of heat insulation layer in 41 region of fuel investment powder column is coated with fuel lining 31, in filling oxidant powder column
2 inner peripheral surface of heat insulation layer in 42 regions is coated with oxidant lining 32,41 outer circumference surface of fuel powder column and 31 inner circle of fuel lining
Circumferential surface bonding, 42 outer circumference surface of oxidant powder column is Nian Jie with 32 inner peripheral surface of oxidant lining, and oxidant powder column 42 and fuel
Oxidant lining 32 is also equipped between 41 interface of powder column.It thus will be in conventional solid projectile charge combustion chamber unit
The oxidant and fuel of priming system are isolated, in processing by shell 1, heat insulation layer 2, fuel lining 31 and fuel powder column 41 are non-
After the completion of priming system manufacturer, it is transferred to the production that priming system powder charge factory carries out oxidant lining 32 and oxidant powder column 42, into
And it is assembled into entire powder charge combustion chamber unit.
Fuel powder column 41 is unable to self-sustaining burning in the course of work, under the oxygen-enriched environment that the burning of oxidant powder column 42 generates
It can be with sustained combustion.
Embodiment 2:
For segmented solid rocket charge combustion chamber unit, conventional segmental solid propellant rocket motor charge combustion chamber is single
Member as shown in figure 3, its combustion chamber by A, B, C, D bay section sequence to being connected in an entirety.By taking A bay section as an example, by shell 1, absolutely
Thermosphere 2, lining 3 and powder column 4 are constituted, and wherein powder column 4 is three constituent element HTPB propellants, by the AP of 69% mass fraction, 18% matter
The HTPB of the Al and 13% mass fraction that measure score are constituted, other three bay section sections are identical as A cargo tank structure, and the dress of each bay section
Medicine is identical in quality.
Low cost segmented solid rocket charge combustion chamber unit provided by the present embodiment is as shown in figure 4, its combustion chamber
Equally by tetra- bay sections of A, B, C, D sequence to being connected in an entirety, but wherein A bay section and C bay section are oxidant bay section, B bay section
It is fuel bay section with D bay section, i.e. oxidant bay section and fuel bay section interval is docked, specifically:
A bay section is identical with the structure type of C bay section, including shell 1, heat insulation layer 2, lining 3 and oxidant powder column 42, wherein
2 outer circumference surface of heat insulation layer bonds together with 1 inner peripheral surface of shell, and 3 outer circumference surface of lining is bonded in 2 inner peripheral surface of heat insulation layer
Together, 42 outer circumference surface of oxidant powder column bonds together with 3 inner peripheral surface of lining.42 groups of oxidant powder column are divided into 87% mass
The HTPB of the AP of score and 13% mass fraction.
B bay section is identical with the structure type of D bay section, including shell 1, heat insulation layer 2, lining 3 and fuel powder column 41, wherein absolutely
2 outer circumference surface of thermosphere bonds together with 1 inner peripheral surface of shell, and 3 outer circumference surface of lining and 2 inner peripheral surface of heat insulation layer are bonded in one
It rises, 41 outer circumference surface of fuel powder column bonds together with 3 inner peripheral surface of lining.41 groups of fuel powder column are divided into 87% mass fraction
The HTPB of Al and 13% mass fraction.
The mass ratio of the fuel powder column in oxidant powder column and B bay section in A bay section is 69:18；Oxidant in C bay section
The mass ratio of fuel powder column in powder column and D bay section is 69:18.The oxidant medicine in oxidant powder column and C bay section in A bay section
Column is identical in quality, and the fuel powder column in B bay section and the fuel powder column in D bay section are identical in quality.
Conventional segmental solid propellant rocket motor charge fires in shell of each bay section in addition to powder column, heat insulation layer, lining and Fig. 3
It is consistent to burn chamber unit material.Thus when being processed to segmented solid rocket charge combustion chamber unit, A bay section and C bay section
It containing priming system, is produced in priming system producer, B bay section and C bay section are free of priming system, produce in non-priming system producer.
The inexpensive powder charge combustion chamber unit course of work in Fig. 4 are as follows: the oxygen after engine ignition, in A bay section and in C bay section
Agent powder column is first begin to burn, and generates oxygen rich fuel gas, and the fuel powder column in B bay section and C bay section is held under oxygen rich fuel gas environment
Afterflame is burnt, and is mixed to form high-temperature high-pressure fuel gas with the oxidant powder column combustion product in A bay section and in C bay section.High temperature and pressure combustion
Gas completes the conversion of thermal energy to mechanical energy as the working medium of solid propellant rocket in jet pipe, generates thrust.
Compared with conventional segmental solid engines powder charge combustion chamber unit, using Fig. 4 Status of Low Cost Solid Rocket Motors
The B bay section and D bay section of powder charge combustion chamber unit are produced in non-priming system manufacturer, and cost reduces.
To sum up, the above is merely preferred embodiments of the present invention, it is not intended to limit the scope of the present invention.It is all
Within the spirit and principles in the present invention, any modification, equivalent replacement, improvement and so on should be included in protection of the invention
Within the scope of.
Claims (6)
1. a kind of solid propellant rocket motor charge combustion chamber unit of low cost, it is characterised in that: include: shell and be located at shell
Heat insulation layer, fuel lining, oxidant lining, fuel powder column and the oxidant powder column in internal portion；The heat insulation layer, fuel lining,
Oxidant lining, fuel powder column are non-priming system, and the oxidant powder column is priming system；
The heat insulation layer is bonded on the shell inner peripheral surface, and oxidant powder column is respectively set along axial direction in the enclosure interior
With fuel powder column, it is provided with fuel lining between the fuel powder column and the heat insulation layer inner peripheral surface, in the oxidant
Oxidant lining is provided between powder column and the heat insulation layer inner peripheral surface；The oxidant powder column and fuel powder column axially dock
It is isolated between face by the oxidant lining.
2. a kind of solid propellant rocket motor charge combustion chamber unit of low cost, it is characterised in that: when the solid-rocket starts
Machine powder charge combustion chamber unit is segmentation structure, the fuel bay section including more than one oxidant bay section and same number；It is described
Oxidant bay section and fuel bay section interval are to being connected in an entirety；
The oxidant bay section includes: shell and the heat insulation layer for being bonded in shell inner peripheral surface, is bonded in heat insulation layer inner periphery
The oxidant powder column that face lining and setting bond together with lining inner peripheral surface inside housings；
The fuel bay section includes: shell and the heat insulation layer for being bonded in shell inner peripheral surface, is bonded in heat insulation layer inner peripheral surface
The fuel powder column that lining and setting bond together with lining inner peripheral surface inside housings.
3. the solid propellant rocket motor charge combustion chamber unit of low cost as claimed in claim 1 or 2, it is characterised in that: institute
It states fuel powder column group and is divided into Al aluminium powder and HTPB end hydroxy butadiene；The oxidant powder column group be divided into AP ammonium perchlorate and
HTPB end hydroxy butadiene.
4. the solid propellant rocket motor charge combustion chamber unit of low cost as claimed in claim 2, it is characterised in that: each oxidation
Oxidant powder column is identical in quality in agent bay section, and fuel powder column is identical in quality in each fuel bay section.
5. the processing method of the solid propellant rocket motor charge combustion chamber unit based on low cost described in claim 1, special
Sign is: its processing sequence are as follows: the manufacture of the heat insulation layer and with the fuel of case bonding → on the heat insulation layer inner peripheral surface
The corresponding region coating fuel lining of powder column → manufacture fuel powder column, and it is bonded fuel powder column and fuel lining → in the insulation
Oxidation is coated on the end face that the corresponding region of oxidant powder column and fuel powder column are docked with oxidant powder column on layer inner peripheral surface
Agent lining → manufacture oxidant powder column, and it is bonded oxidant powder column and oxidant lining.
6. the processing method of the solid propellant rocket motor charge combustion chamber unit based on low cost as claimed in claim 2, special
Sign is: its processing sequence are as follows: first processes oxidant bay section and fuel bay section, more than one oxygen that then will be completed the process respectively
Agent bay section and more than one fuel bay section interval are to being connected in an entirety.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810961272.6A CN109236500A (en) | 2018-08-22 | 2018-08-22 | A kind of Status of Low Cost Solid Rocket Motors powder charge combustion chamber unit and its processing method |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810961272.6A CN109236500A (en) | 2018-08-22 | 2018-08-22 | A kind of Status of Low Cost Solid Rocket Motors powder charge combustion chamber unit and its processing method |
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| CN109236500A true CN109236500A (en) | 2019-01-18 |
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| CN201810961272.6A Pending CN109236500A (en) | 2018-08-22 | 2018-08-22 | A kind of Status of Low Cost Solid Rocket Motors powder charge combustion chamber unit and its processing method |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109958548A (en) * | 2019-03-12 | 2019-07-02 | 湖北航天化学技术研究所 | A kind of rapid fire solid propellant rocket modularization charge process |
| CN109989851A (en) * | 2019-03-20 | 2019-07-09 | 湖北航天技术研究院总体设计所 | For the compound cutan of powder charge combustion chamber and powder charge combustion chamber and manufacturing method |
| CN114290662A (en) * | 2021-12-31 | 2022-04-08 | 西安交通大学 | Heat insulation/charge integrated additive manufacturing method for solid rocket engine |
| JP7067126B2 (en) | 2018-03-06 | 2022-05-16 | 日油株式会社 | Insulator attachment method and jig |
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| US3357187A (en) * | 1966-03-14 | 1967-12-12 | Thiokol Chemical Corp | Ducted rocket motor |
| RU2100064C1 (en) * | 1995-01-16 | 1997-12-27 | Научно-исследовательский институт прикладной математики и механики | Solid-reactant gas generator |
| CA2322069A1 (en) * | 1999-10-27 | 2001-04-27 | Anthony Joseph Cesaroni | Oxidizer package for propellant system for rockets |
| US6311479B1 (en) * | 1999-12-13 | 2001-11-06 | Roger E. Lo | Modular cryogenic solid fuel rocket drive sets |
| DE202013100254U1 (en) * | 2013-01-18 | 2013-02-11 | Hubertus Schulte | Combustion chamber for solid rockets |
| CN105003355A (en) * | 2015-07-27 | 2015-10-28 | 湖北三江航天江河化工科技有限公司 | Solid rocket engine with high thrust ratio and manufacturing method thereof |
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Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3357187A (en) * | 1966-03-14 | 1967-12-12 | Thiokol Chemical Corp | Ducted rocket motor |
| RU2100064C1 (en) * | 1995-01-16 | 1997-12-27 | Научно-исследовательский институт прикладной математики и механики | Solid-reactant gas generator |
| CA2322069A1 (en) * | 1999-10-27 | 2001-04-27 | Anthony Joseph Cesaroni | Oxidizer package for propellant system for rockets |
| US6311479B1 (en) * | 1999-12-13 | 2001-11-06 | Roger E. Lo | Modular cryogenic solid fuel rocket drive sets |
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| CN105003355A (en) * | 2015-07-27 | 2015-10-28 | 湖北三江航天江河化工科技有限公司 | Solid rocket engine with high thrust ratio and manufacturing method thereof |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP7067126B2 (en) | 2018-03-06 | 2022-05-16 | 日油株式会社 | Insulator attachment method and jig |
| CN109958548A (en) * | 2019-03-12 | 2019-07-02 | 湖北航天化学技术研究所 | A kind of rapid fire solid propellant rocket modularization charge process |
| CN109989851A (en) * | 2019-03-20 | 2019-07-09 | 湖北航天技术研究院总体设计所 | For the compound cutan of powder charge combustion chamber and powder charge combustion chamber and manufacturing method |
| CN114290662A (en) * | 2021-12-31 | 2022-04-08 | 西安交通大学 | Heat insulation/charge integrated additive manufacturing method for solid rocket engine |
| CN114290662B (en) * | 2021-12-31 | 2023-05-30 | 西安交通大学 | Heat insulation/charge integrated additive manufacturing method for solid rocket engine |
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