CN109058661A - A kind of interlayer composite adiabatic layer structure and manufacturing method - Google Patents
A kind of interlayer composite adiabatic layer structure and manufacturing method Download PDFInfo
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- CN109058661A CN109058661A CN201810838680.2A CN201810838680A CN109058661A CN 109058661 A CN109058661 A CN 109058661A CN 201810838680 A CN201810838680 A CN 201810838680A CN 109058661 A CN109058661 A CN 109058661A
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- layer
- ablation
- insulation layer
- thermal insulation
- ablation layer
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
- F16L59/00—Thermal insulation in general
- F16L59/02—Shape or form of insulating materials, with or without coverings integral with the insulating materials
- F16L59/028—Composition or method of fixing a thermally insulating material
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B1/00—Layered products having a general shape other than plane
- B32B1/08—Tubular products
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B25/00—Layered products comprising a layer of natural or synthetic rubber
- B32B25/04—Layered products comprising a layer of natural or synthetic rubber comprising rubber as the main or only constituent of a layer, which is next to another layer of the same or of a different material
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B25/00—Layered products comprising a layer of natural or synthetic rubber
- B32B25/18—Layered products comprising a layer of natural or synthetic rubber comprising butyl or halobutyl rubber
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
- B32B37/06—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the heating method
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
- B32B37/10—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the pressing technique, e.g. using action of vacuum or fluid pressure
-
- 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
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
- F16L59/00—Thermal insulation in general
- F16L59/02—Shape or form of insulating materials, with or without coverings integral with the insulating materials
- F16L59/029—Shape or form of insulating materials, with or without coverings integral with the insulating materials layered
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Laminated Bodies (AREA)
Abstract
The present invention provides a kind of interlayer composite adiabatic layer structure and manufacturing methods, successively thermal insulation layer, anti-ablation layer and transition zone are pasted onto motor combustion chamber case, thermal insulation layer and transition zone select the insulation layer material of ethylene propylene diene rubber system, anti-ablation layer choosing carbon fiber phenolic aldehyde nitrile rubber film stock, anti-ablation layer circumferential direction along motor combustion chamber case are divided into several pieces；Hot pressing is carried out after every layer of stickup, anti-ablation layer material is using preceding progress preliminary drying processing, and ablation layer carbon hair plates is first fought before pasting transition zone and thermal insulation layer carries out curing process.The present invention can be improved the globality of composite adiabatic layer, enhance compound interface reliability.
Description
Technical field
The present invention relates to thermal protection struc ture and techniques in a kind of Solid Rocket Motor combustion chamber, are mainly used in pulse and start
The important anti-hot spot of machine, end-burning grain engine and high overload, ablation engine chamber.
Background technique
Heat insulation material generally uses the single insulation of ethylene propylene diene rubber, nitrile rubber in Solid Rocket Motor combustion chamber
Material and carbon fibre fabric/rubbery system composite adiabatic layer.
Single rubber heat-insulating material is primarily adapted for use in internal bore burning, low fever loses the engine washed away, and structure is simple, tradition
Slice bonding, be molded the preforming technique being bonded again and can be achieved, but Burning corrosion resistance can have some limitations, for anti-
The more demanding engine of ablation can only guarantee heat insulation layer thermal protective performance by heat insulation layer thickness is increased, reduce engine and push away
Into the explosive payload of agent.
Carbon fibre fabric/rubbery system composite adiabatic layer anti-ablation, heat-proof quality are better than traditional single rubber, pass through
It is as shown in Figure 1 that the solar heat protection mechanism of heat insulation layer is classified as thermal insulation layer, anti-ablation layer and transition zone, structure.Carbon fibre fabric is general
It chooses carbon cloth to use as anti-ablation layer, rubber heat-insulating layer is used as thermal insulation layer and transition zone.It is viscous in order to improve compound interface
Connect reliability, carbon cloth with rubber heat-insulating layer it is compound before must carry out surface treatment and dipping process, the carbon cloth single monolayer thick after impregnation
Degree is 0.3mm~0.4mm, and the general method using multiple-layer stacked meets the thickness requirement of anti-ablation layer, then by the multilayer of superposition
Carbon cloth is bonded in thermal insulation layer inner surface, and after preforming, in carbon cloth surfaces adhesive transition layer, last entirety is solidified.Due to carbon
Cloth superposition interface is more, and high pressure-temperature combustion gas when the engine is working is washed away the middle and later periods, and impregnation easily releases small molecule in carbon cloth,
The interlayer of superposition is fled, cause carbon cloth respectively layer by layer between unsticking, composite adiabatic layer anti-ablation performance of flushing reduce, anti-thermal failure.For
The lamination problem in the carbon cloth composite adiabatic layer course of work is solved, using carbon fiber tri-dimensional fabric (carbon net) as anti-ablation layer, warp
The carbon net for crossing impregnation has certain thickness, and single layer can reach the thickness requirement of composite adiabatic layer anti-ablation layer, does not have to superposition, carbon
Net has stronger structural integrity as anti-ablation layer.In engine working process, the three-dimensional overall structure of carbon net is improved
The anti-ablation performance of flushing of composite adiabatic layer, but as engine operation heat insulation layer temperature increases, the inside impregnation of carbon net and
The micro-molecular gas that thermal insulation layer surface discharges when being carbonized can flee at the interface between carbon net and thermal insulation layer, carbon net and heat-insulated stratum boundary
Emaciated face influences the reliability of carbon net anti-ablation from fault of construction is caused.
Summary of the invention
For overcome the deficiencies in the prior art, the present invention provides a kind of thermal protection struc ture material, can be improved composite adiabatic layer
Globality, enhance compound interface reliability.
The technical solution adopted by the present invention to solve the technical problems is: a kind of interlayer composite adiabatic layer structure is being started
In machine combustion chamber shell body, ecto-entad is followed successively by thermal insulation layer, anti-ablation layer and transition zone；The thermal insulation layer and transition zone are selected
The insulation layer material of ethylene propylene diene rubber system, anti-ablation layer choosing carbon fiber phenolic aldehyde nitrile rubber film stock；Described is anti-
Ablation layer circumferential direction along motor combustion chamber case is divided into several pieces.
Every piece of width of the anti-ablation layer circumferential direction segmentation is 100~200mm.
The present invention also provides the manufacturing methods of above-mentioned interlayer composite adiabatic layer structure, comprising the following steps:
A) thermal insulation layer of raw rubber state is pasted onto motor combustion chamber case inner wall bonding plane, is pressurizeed using air bag punching press
Mode carries out the hot-pressing processing that pressure is 0.6MPa~0.7MPa under the conditions of 80 DEG C~120 DEG C of temperature；
B) confrontation ablation layer material carries out the preliminary drying processing of 50 DEG C~70 DEG C, 1h~2h, is cut out according still further to split dimension
It cuts；
C) the anti-ablation layer material after cutting is pasted onto thermal insulation layer surface, using air bag punching press pressuring method, at 80 DEG C
The hot-pressing processing that pressure is 0.6MPa~0.7MPa is carried out under the conditions of~120 DEG C of temperature；
D) curing process is carried out to thermal insulation layer and anti-ablation layer, solidification initial pressure is 0.6MPa~0.65MPa, from room temperature
110 DEG C~130 DEG C are warming up to, 1h~2h is kept the temperature；155 DEG C~160 DEG C are warming up to, 1h~2h is kept the temperature；Then it is down to room temperature naturally；
E) transition zone is pasted onto anti-ablation layer surface.
The beneficial effects of the present invention are: anti-ablation layer is changed to circumferential decomposition texture from tube structure, as shown in Fig. 2, very
Good solves the problems, such as anti-ablation layer and thermal insulation layer interfacial detachment when engine operation, in engine working process, anti-burning
The discharge that erosion layer circumferential direction divides formal similarity that can accelerate bonding interface small molecule.Transition zone is carbonized punching completely after engine test
Brush, anti-ablation layer structural integrity, thickness and preceding almost the same, the no layering chip off-falling phenomenon that works, thermal insulation layer surface carbonization, carbonization are thick
Degree is 0.2mm~0.5mm.
The composite adiabatic layer manufacturing process that the present invention describes passes through the various small molecules discharge that will affect compound interface in advance,
Guarantee interface bond quality of the composite adiabatic layer in forming process.When anti-ablation layer makes, glue will carry out solvent dilution,
To improve wettability when carbon fiber impregnation, after the completion of molding, in material internal, there are also residual solvents, must carry out preliminary drying using preceding
Accelerate solvent volatilization, in addition, preliminary drying the hydrone of the anti-ablation layer moisture absorption during storage can be discharged.Anti-ablation layer is consolidated
Change is to solidify to realize by itself impregnation, and impregnation solidification crosslinks reaction, and the macromolecule end of the chain or functional group's polymerization are released small
Molecule, therefore before anti-ablation layer surface pastes transition zone, confrontation ablation layer is solidified, and reaction small molecule is discharged in advance.?
When anti-ablation layer and bottom thermal insulation layer solidify, must the two optimal flow temperature for a period of time, both make interface abundant
Mutually melt, improves interface bond quality.The anti-ablation layer carbon hair plates and thermal insulation layer ethylene propylene diene rubber of composite adiabatic layer of the invention
Adhesive strength level between heat insulation layer reaches 2.5~3.0MPa, the mature and stable reliable in quality of method of manufacturing technology of the invention.
Detailed description of the invention
Fig. 1 is carbon fibre fabric/rubber composite adiabatic layer schematic diagram；
Fig. 2 is carbon hair plates/rubber composite adiabatic schematic diagram of a layer structure；
Fig. 3 is composite adiabatic layer manufacturing process flow diagram.
Specific embodiment
Present invention will be further explained below with reference to the attached drawings and examples, and the present invention includes but are not limited to following implementations
Example.
The present invention improves the globality of composite adiabatic layer from configuration aspects, enhances compound boundary when designing composite adiabatic layer
Face reliability；In manufacturing process research process, raising compound interface is Nian Jie in terms of compound interface processing and material and processing
Reliability.
Thermal insulation layer of the invention and transition zone select the insulation layer material of ethylene propylene diene rubber system, anti-ablation layer choosing carbon
Fiber phenolic nitrile rubber film stock (popular name: carbon hair plates GJB2909-97), this film belongs to a kind of felt class material, thickness
Molding setting can be carried out according to design size, there is very high Burning corrosion resistance energy, linear ablative rate≤0.06mm/s.Composite adiabatic layer
Configuration aspects use anti-ablation layer circumferential direction separate structure, and the anti-ablation layer of original tube structure has been carried out circumferential point by this structure
Solution, during storage, can be such that the stress of bonding interface between anti-ablation layer and ethylene propylene diene rubber is sufficiently discharged；Hair
In the motivation course of work, carbon hair plates and thermal insulation layer can be discharged by thermogenetic small molecule gas in the structure gap that anti-ablation layer decomposes
Body.Anti-ablation layer when decomposing, every piece of width of decomposition according to engine heat insulation layer diameter control 100~200mm it
Between, the excessive exhaust effect that will affect course of work median surface of width, width is too small to reduce monolithic anti-ablation layer and thermal insulation layer
Bonded area, reduce thermal protective performance.
In composite adiabatic layer manufacturing process of the invention, points three layers are bonded in motor combustion chamber case, be followed successively by every
Thermosphere, anti-ablation layer and transition zone, every layer paste after carry out hot pressing with guarantee interface bond quality layer by layer and every layer material at
Type quality.Anti-ablation material carbon hair plates is carrying out preliminary drying processing using palpus, to discharge small point of residual solvent of carbon hair plates dipping solution
Son；In addition, first fighting ablation layer carbon hair plates and thermal insulation layer progress curing process before pasting transition zone, then transition zone is pasted, made
The small molecule that chemical reaction generates when carbon hair plates solidifies is discharged in advance, prevents small molecule from converging at transition zone bonding interface and causes to rouse
Packet debonding defect.Entire hot pressing, vulcanization use air bag punching press pressuring method, in carbon hair plates and thermal insulation layer composite curing, Ying
The optimal temperature setting step of insulating layer material mobility, to promote interface fusion and carbon hair plates to uniformly transfer pressure to thermal insulation layer
Power.Concrete technology method is as follows:
A) the thermal insulation layer ethylene propylene diene rubber of raw rubber state is pasted onto motor combustion chamber case inner wall bonding plane, used
Air bag punching press pressuring method carries out 80 DEG C~120 DEG C of temperature, the hot-pressing processing of pressure 0.6MPa~0.7MPa；
B) confrontation ablation layer material carbon hair plates carries out the preliminary drying processing of 50 DEG C~70 DEG C, 1h~2h, according still further to decomposition size
It is cut；
C) the carbon hair plates of cutting is successively pasted onto thermal insulation layer surface, carries out 80 DEG C of temperature using air bag punching press pressuring method
~120 DEG C, the hot-pressing processing of pressure 0.6MPa~0.7MPa；
D) thermal insulation layer to hot pressing in c) and anti-ablation layer carry out curing process.Solidification initial pressure 0.6MPa~
Temperature increasing schedule: 0.65MPa is warming up to 110 DEG C~130 DEG C from room temperature one way, keeps the temperature 1h~2h；One way is warming up to 155 DEG C~160
DEG C, keep the temperature 1h~2h；Naturally it is down to room temperature.
E) transition zone is pasted.
In the embodiment of the present invention, anti-ablation layer material carbon hair plates preliminary drying condition: 55 DEG C, time 1.5h, before preliminary drying processing
After weigh, electronic scale sensibility reciprocal be not more than 0.1g, calculate weight-loss ratio answer >=3%, weight-loss ratio calculation formula: (dry before quality-baking
Quality before quality/baking afterwards) × 100%；It reduces width and number calculating is decomposed according to heat insulation layer internal diameter perimeter and anti-ablation layer.Every block of carbon
Hair plates is successively pasted onto thermal insulation layer inner mold face according to design drawing, after hot-pressing processing, is thermally shielded layer/carbon hair plates composite curing,
Condition of cure: solidification initial pressure 0.6MPa~0.65MPa is warming up to 120 DEG C from room temperature one way, keeps the temperature 2h；One way is warming up to
160 DEG C, keep the temperature 2h；Naturally it is down to room temperature.The composite adiabatic layer product of completion meets engine design requirement.
Claims (3)
1. a kind of interlayer composite adiabatic layer structure, it is characterised in that: in motor combustion chamber case, ecto-entad be followed successively by every
Thermosphere, anti-ablation layer and transition zone；The thermal insulation layer and transition zone select the insulation layer material of ethylene propylene diene rubber system, resist
Ablation layer selects carbon fiber phenolic aldehyde nitrile rubber film stock；The anti-ablation layer is circumferential point along motor combustion chamber case
It is segmented into several pieces.
2. interlayer composite adiabatic layer structure according to claim 1, it is characterised in that: the anti-ablation layer circumferential direction segmentation
Every piece of width be 100~200mm.
3. the manufacturing method of interlayer composite adiabatic layer structure described in a kind of claim 1, it is characterised in that include the following steps:
A) thermal insulation layer of raw rubber state is pasted onto motor combustion chamber case inner wall bonding plane, using air bag punching press pressurization side
Formula carries out the hot-pressing processing that pressure is 0.6MPa~0.7MPa under the conditions of 80 DEG C~120 DEG C of temperature；
B) confrontation ablation layer material carries out the preliminary drying processing of 50 DEG C~70 DEG C, 1h~2h, is cut according still further to split dimension；
C) the anti-ablation layer material after cutting is pasted onto thermal insulation layer surface, using air bag punching press pressuring method, 80 DEG C~120
The hot-pressing processing that pressure is 0.6MPa~0.7MPa is carried out under the conditions of DEG C temperature；
D) curing process is carried out to thermal insulation layer and anti-ablation layer, solidification initial pressure is 0.6MPa~0.65MPa, from room temperature
To 110 DEG C~130 DEG C, 1h~2h is kept the temperature；155 DEG C~160 DEG C are warming up to, 1h~2h is kept the temperature；Then it is down to room temperature naturally；
E) transition zone is pasted onto anti-ablation layer surface.
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| CN201810838680.2A CN109058661B (en) | 2018-07-27 | 2018-07-27 | Interlayer composite heat insulation layer structure and manufacturing method |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109648887A (en) * | 2018-12-25 | 2019-04-19 | 内蒙古航天红峡化工有限公司 | A kind of solid propellant rocket half air bag cure under pressure heat insulation layer device and method |
| CN111561187A (en) * | 2020-05-25 | 2020-08-21 | 湖北三江航天万峰科技发展有限公司 | Heat-preservation, damage-resistance and ablation-resistance device for box type equipment and assembling method thereof |
| CN114407459A (en) * | 2022-01-28 | 2022-04-29 | 宁波天擎航天科技有限公司 | Solid rocket, engine and thermal protection structure at tail part of composite shell of solid rocket |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| AU4341396A (en) * | 1994-12-13 | 1996-07-03 | Hp-Chemie Pelzer Research And Development Ltd. | Reusable textile floor coverings |
| CN102632683A (en) * | 2012-03-30 | 2012-08-15 | 湖北三江航天江北机械工程有限公司 | Manufacturing method for manual patch of heat insulating layer of filament winding engine shell |
| CN104861884A (en) * | 2015-05-15 | 2015-08-26 | 湖北三江航天江河化工科技有限公司 | Method for bonding carbon fiber/phenolic-nitrile rubber materials |
| CN104924631A (en) * | 2015-05-15 | 2015-09-23 | 湖北三江航天江河化工科技有限公司 | Carbon fiber/phenol-butadiene-acrylonitrile rubber material integral prefabrication method |
| CN104960200A (en) * | 2015-05-15 | 2015-10-07 | 湖北三江航天江河化工科技有限公司 | Rubber-based thermal insulation layer patching method |
| CN104829857B (en) * | 2015-05-15 | 2017-11-28 | 湖北三江航天江河化工科技有限公司 | A kind of carbon fiber/phenolic aldehyde nitrile rubber bonding interface processing method |
-
2018
- 2018-07-27 CN CN201810838680.2A patent/CN109058661B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| AU4341396A (en) * | 1994-12-13 | 1996-07-03 | Hp-Chemie Pelzer Research And Development Ltd. | Reusable textile floor coverings |
| CN102632683A (en) * | 2012-03-30 | 2012-08-15 | 湖北三江航天江北机械工程有限公司 | Manufacturing method for manual patch of heat insulating layer of filament winding engine shell |
| CN104861884A (en) * | 2015-05-15 | 2015-08-26 | 湖北三江航天江河化工科技有限公司 | Method for bonding carbon fiber/phenolic-nitrile rubber materials |
| CN104924631A (en) * | 2015-05-15 | 2015-09-23 | 湖北三江航天江河化工科技有限公司 | Carbon fiber/phenol-butadiene-acrylonitrile rubber material integral prefabrication method |
| CN104960200A (en) * | 2015-05-15 | 2015-10-07 | 湖北三江航天江河化工科技有限公司 | Rubber-based thermal insulation layer patching method |
| CN104829857B (en) * | 2015-05-15 | 2017-11-28 | 湖北三江航天江河化工科技有限公司 | A kind of carbon fiber/phenolic aldehyde nitrile rubber bonding interface processing method |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109648887A (en) * | 2018-12-25 | 2019-04-19 | 内蒙古航天红峡化工有限公司 | A kind of solid propellant rocket half air bag cure under pressure heat insulation layer device and method |
| CN109648887B (en) * | 2018-12-25 | 2021-07-20 | 内蒙古航天红峡化工有限公司 | Device and method for pressurizing and curing heat insulation layer of half airbag of solid rocket engine |
| CN111561187A (en) * | 2020-05-25 | 2020-08-21 | 湖北三江航天万峰科技发展有限公司 | Heat-preservation, damage-resistance and ablation-resistance device for box type equipment and assembling method thereof |
| CN114407459A (en) * | 2022-01-28 | 2022-04-29 | 宁波天擎航天科技有限公司 | Solid rocket, engine and thermal protection structure at tail part of composite shell of solid rocket |
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