CN109605776A - Fiber wound and solidified rocket engine multiphase heat insulation layer forming method - Google Patents
Fiber wound and solidified rocket engine multiphase heat insulation layer forming method Download PDFInfo
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- CN109605776A CN109605776A CN201811360257.2A CN201811360257A CN109605776A CN 109605776 A CN109605776 A CN 109605776A CN 201811360257 A CN201811360257 A CN 201811360257A CN 109605776 A CN109605776 A CN 109605776A
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- insulation layer
- epdm
- heat insulation
- film
- phenolic resin
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/06—Fibrous reinforcements only
- B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
- B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
- B29C70/24—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
- B29C70/545—Perforating, cutting or machining during or after moulding
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3097—Cosmonautical vehicles; Rockets
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/748—Machines or parts thereof not otherwise provided for
- B29L2031/749—Motors
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Textile Engineering (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The invention discloses a kind of fiber wound and solidified rocket engine multiphase heat insulation layer forming methods, the multiphase heat insulation layer is collectively constituted by the EPDM and phenolic resin impregnation of carbon fibers 3 D weaving body of resistance to ablation, on the one hand the Burning corrosion resistance of heat-insulating material can be improved in the case where not increasing heat insulation layer thickness, the passive quality for reducing motor body, improves the mass ratio of engine；Another aspect is by the way of multiple-layered patches and the design of sandwich, molding multiphase heat-insulating material have preferable craftsmanship；Precompressed twice, on the one hand the gas between two kinds of heat-insulating materials and between EPDM film layers is discharged, on the other hand the insulation bed boundary good fit for guaranteeing phenolic resin impregnation of carbon fibers 3 D weaving body and upper and lower position, prevents the defects of bulge, gas enclosure, unsticking occur between EPDM and phenolic resin impregnation of carbon fibers 3 D weaving body multiphase heat-insulating material.
Description
Technical field
The invention belongs to heat-insulating material production fields in fiber winding solid propellant rocket, twine in particular to a kind of fiber
Around solidification rocket engine multiphase heat insulation layer forming method.
Background technique
Protective layer of the internal insulation material as Solid Rocket Motor combustion chamber has high temperature resistant ablation, anti-Gao Sure
Stream washes away and good mechanical property, prevents high temperature, high-pressure gas from reducing casing rigidity and jeopardizing its structural intergrity, fires to it
It burns room housing and plays heat-insulated and thermal protection, be the key components for guaranteeing rocket engine and working normally.
In recent years, with the new demand of high-performance rocket engine, becoming high-performance tactics with high overload at a high speed and leading
The important trend of bullet requires the long-time, resistance to oxidation and scour resistance of heat-insulating material more harsh；If raising is started
The ablation resistance of machine can carry out in terms of two, on the one hand can be by the thickness of increase heat-insulating material, but thickness increase can improve
Engine passiveness quality, so as to cause engine quality reduction；On the other hand it can be carried out by using the material more resistant to ablation exhausted
The preparation of thermosphere.
Summary of the invention
Present invention aim to deficiencies in view of the above technology, and providing one kind not only can guarantee heat insulation layer thickness but also energy
Improve the fiber wound and solidified rocket engine multiphase heat insulation layer forming method of ablation resistance.
To achieve the above object, the fiber wound and solidified rocket engine multiphase designed by the present invention is insulated formable layer side
Method, the multiphase heat insulation layer are collectively constituted by the EPDM and phenolic resin impregnation of carbon fibers 3 D weaving body of resistance to ablation, at
Type method the following steps are included:
1) mandrel surface is handled
Cleaning is used for the dust of the molding mandrel surface of motor body, in its surface wrap or puts up one layer of polytetrafluoroethyl-ne
Alkene layer；
2) it pre-processes for the first time
2a) preliminary drying: the good phenolic resin impregnation of carbon fibers 3 D weaving body of precuring is put into baking oven and carries out preliminary drying, in advance
Baking process is 80~100 DEG C/2~4h；
2b) preheat: adjustment heating platform temperature will take multiple EPDM films and one pre-baked to 5 ± 10 DEG C
Phenolic resin impregnation of carbon fibers 3 D weaving body is placed to being preheated on heating platform；
3) first time patch
3a) brush coating: in the polytetrafluoroethylene (PTFE) layer surface and step 3b of core model) in multiple EPDM films a surface it is each
The adhesive for brushing one layer of corresponding interface in advance, dries in the air to tack-free state；
3b) EPDM film patch: the brush coating face paste of first EPDM film in step 3a) is poly- to core model
The brush coating face of tetrafluoroethene layer；In the another side brush coating stick of first EPDM film, by the second Zhang San in step 3a)
In the brush coating face paste to the brush coating face of second EPDM film of first the third film of second；Successively put up until step 3a) in most
In the brush coating face paste of latter EPDM film to the brush coating face of second from the bottom EPDM film；
3c) brush coating: another surface of outermost layer EPDM film and phenolic resin leaching on being posted in mandrel surface
Stain carbon fiber 3 D weaving body surface face carries out the brushing of corresponding adhesive；It is hung after brushing to tack-free state；
3d) phenolic resin impregnation of carbon fibers 3 D weaving body is fixed: using polytetrafluoroethylene (PTFE) adhesive tape by phenolic resin first
The width position of impregnation of carbon fibers 3 D weaving body is fixed to mandrel surface outermost layer EPDM film surface of position to be puted up；
3e) phenolic resin impregnation of carbon fibers 3 D weaving shows consideration for piece: by phenolic resin impregnation of carbon fibers 3 D weaving body edge
It is circumferentially puted up, carries out catching up with gas when putting up, guarantee phenolic resin impregnation of carbon fibers 3 D weaving body and lower section ethylene-propylene diene copolymer
Piece fitting, it is finally that phenolic resin impregnation of carbon fibers 3 D weaving body is end to end, fixed phenolic resin impregnated carbon is removed at this time
The polytetrafluoroethylene (PTFE) adhesive tape of fibre three-dimensional knitted body, and used at the end to end place of phenolic resin impregnation of carbon fibers 3 D weaving body
Polytetrafluoroethylene (PTFE) adhesive tape is pasted, is fixed；
4) first time precompressed and preliminary drying
4a) first time precompressed: phenolic resin impregnation of carbon fibers 3 D weaving body surface face ring in step 3e) is to winding one
Layer polytetrafluoroethylene film, reuses wrapping machine for step 3e) middle gained multiphase heat insulation layer intermediate outside progress glass fibre
Layer winding；
4b) first time preliminary drying: the multiphase heat insulation layer of step 4a) being placed in baking oven and is heat-treated, temperature be 80~
100 DEG C/2~4h；
5) first dressing
6) second of patch
6a) preheat: adjustment heating platform temperature takes multiple EPDM films to place to heating platform to 55 ± 10 DEG C
It is preheated；
6b) brush coating: in phenolic resin impregnation of carbon fibers 3 D weaving external surface and step 6a) in multiple ethylene-propylene diene copolymers
Each pre- adhesive for brushing one layer of corresponding interface in one surface of piece；It is hung, is dried in the air to tack-free state after brushing；
6c) EPDM film patch: it on the basis of phenolic resin impregnation of carbon fibers 3 D weaving body axial position, will walk
Rapid 6b) in first EPDM film brush coating face paste to the brush coating face of phenolic resin impregnation of carbon fibers 3 D weaving body,
And first EPDM film requires the overlap edge of covering phenolic resin impregnation of carbon fibers 3 D weaving body；In the first Zhang San member
The another side brush coating stick of the third film of second, by the brush coating face paste of second EPDM film in step 6b) to the second Zhang San
On the brush coating face of first the third film of second；Successively put up until step 6a) in last EPDM film brush coating face paste extremely
On the brush coating face of second from the bottom EPDM film；
7) second of precompressed and preliminary drying
7a) second of precompressed: in step 6c) last EPDM film surface loop to winding one layer of polytetrafluoroethyl-ne
Alkene film reuses wrapping machine for step 7c) the progress glass layer winding of gained multiphase heat insulation layer intermediate outside；
7b) preliminary drying: the multiphase heat insulation layer of step 7a) is placed into 4~8h and carries out precompressed or be placed in baking oven to carry out hot place
Reason, heat treatment temperature are 80~100 DEG C/2~4h；
8) it clears up for second
9) it corrects, pressurize, solidification.
Further, the environment temperature of the forming method is 25 ± 10 DEG C, relative humidity≤75%.
Further, the EPDM film preparation process specifically:
Slice: the roller spacing of rubber mixing machine is first adjusted to 2~3mm, EPDM heat-insulating material is located in advance by rubber mixing machine
Manage and mixing 3~4 times back and forth, then adjust roller spacing, by the thickness of 0.5 ± 0.1mm, 2 ± 0.1mm be made several three
First the third film of second；
It cuts: determining the overall developed dimension of EPDM film by the outer diameter and length of core model, and taken by circumferencial direction
4~20, EPDM film, every EPDM film for needing to paste is cut by the requirement of 300~500mm of width, and thick
All ethylene-propylene diene copolymer on pieces of degree≤1.5mm reserve the overlapping part of 10~15mm, all EPDM of thickness >=1.5mm
Groove is reserved on film makes position；
Cleaning: all EPDM films after cutting are cleaned and is dried in the air using ethyl acetate and clean hairless paper
It is dry, it dries and is isolated between rear every adjacent two EPDM films with clean isolation cloth, prevent adjacent two Zhang San member second
Third cohesion of film.
Further, the step 2a) in, preceding 0.3~0.5h is used in phenolic resin impregnation of carbon fibers 3 D weaving body
It is taken out from baking oven.
Further, the step 4a) in, the tension of one-ply yarn is 15~30N when winding.
Further, in the step 5), the detailed process of first dressing are as follows: glass layer cleaning: multiphase is exhausted
The fiber on thermosphere surface is cut and is cleaned out, while cleaning up at phenolic resin impregnation of carbon fibers 3 D weaving body lap position
Polytetrafluoroethylene (PTFE) adhesive tape, reuse ethyl acetate and entire multiphase insulation layer surface cleared up, dried.
Further, the step 7a) in, the tension of one-ply yarn is 15~30N when winding.
Further, in the step 8), the detailed process of second of cleaning are as follows: cut the fiber of multiphase insulation layer surface
Break and clean out, while cleaning up polytetrafluoroethylene film outside multiphase heat insulation layer；Ethyl acetate is reused to entire multiphase
Insulation layer surface is cleared up, is dried.
Further, in the step 9), amendment, pressurization, solidification detailed process are as follows:
9a) multiphase heat insulation layer is modified: multiphase heat insulation layer boss being polished flat with sanding machine, to pit ternary
The third heat-insulating material of second is repaired, and is connected with adhesive；
9b) multiphase heat insulation layer pressurizes: carbon fiber being immersed in resin material, the multiphase obtained by step 10a) is insulated layer surface
Winding has the carbon fiber of resin material；
9c) multiphase heat insulation layer solidifies: multiphase heat insulation layer obtained by step 9b) being placed 1~3h at room temperature, is then placed in roasting
It is finally down in 50~90 DEG C of 2~4h of solidification, 100~130 DEG C of 2~4h of solidification, 140~170 DEG C of 4~10h of solidification respectively in case
Room temperature, and mandrel and core model are removed, required fiber wound and solidified rocket engine multiphase heat insulation layer is made.
Compared with prior art, the present invention having the advantage that
1, the multiphase prepared is used cooperatively by using phenolic resin impregnation of carbon fibers 3 D weaving body and EPDM
On the one hand the Burning corrosion resistance of heat-insulating material can be improved in the case where not increasing heat insulation layer thickness, reduce and start for heat-insulating material
The passive quality of casing body, improves the mass ratio of engine；On the other hand by the way of multiple-layered patches and sandwich
Design, molding multiphase heat-insulating material have preferable craftsmanship；
2) on the one hand the gas between two kinds of heat-insulating materials and between EPDM film layers is discharged in precompressed twice, another
Aspect guarantees the insulation bed boundary good fit of phenolic resin impregnation of carbon fibers 3 D weaving body and upper and lower position, prevents ternary
There is the defects of bulge, gas enclosure, unsticking between second third and phenolic resin impregnation of carbon fibers 3 D weaving body multiphase heat-insulating material.
Detailed description of the invention
Fig. 1 is to put up state photo figure after phenolic resin impregnation of carbon fibers 3 D weaving body in embodiment；
Fig. 2 is state photo figure after the completion of multiphase heat insulation layer preparation in embodiment.
Specific embodiment
The following further describes the present invention in detail with reference to the accompanying drawings and specific embodiments, convenient for more clearly understanding this
Invention, but they limiting the invention.
Fiber wound and solidified rocket engine multiphase heat insulation layer forming method, the multiphase heat insulation layer by resistance to ablation ternary second
Third and phenolic resin impregnation of carbon fibers 3 D weaving body collectively constitute, forming method the following steps are included:
1) ambient temperature and humidity control and mandrel surface processing
Using air-conditioning or dehumidifier, the environment temperature for adjusting the production of multiphase heat insulation layer is 25 ± 10 DEG C, relative humidity≤
75%；And the dust for being used for the molding mandrel surface of motor body is cleared up, in its surface wrap or put up one layer of polytetrafluoroethyl-ne
Alkene layer, for being isolated for multiphase heat insulation layer and core model；
2) prepared by EPDM film
2a) slice: the roller spacing of rubber mixing machine is first adjusted to 2~3mm, it is pre- that EPDM heat-insulating material is passed through into rubber mixing machine
It handles and is kneaded 3~4 times back and forth, then adjust roller spacing, several are made by the thickness of 0.5 ± 0.1mm, 2 ± 0.1mm
EPDM film；
It 2b) cuts: determining the overall developed dimension of EPDM film by the outer diameter and length of core model, and press circumferencial direction
4~20, EPDM film are taken, cuts every EPDM film for needing to paste by the requirement of 300~500mm of width, and
All ethylene-propylene diene copolymer on pieces of thickness≤1.5mm reserve all ternary second of overlapping part, thickness >=1.5mm of 10~15mm
Groove is reserved on third film makes position；
It 2c) cleans: all EPDM films after cutting being cleaned using ethyl acetate and clean hairless paper
And dry, it dries and is isolated between rear every adjacent two EPDM films with clean isolation cloth, prevent adjacent two Zhang San
First the third cohesion of film of second；
3) it pre-processes for the first time
3a) preliminary drying: the good phenolic resin impregnation of carbon fibers 3 D weaving body of precuring is put into baking oven and carries out preliminary drying, in advance
Baking process is 80~100 DEG C/2~4h, to guarantee that material has preferable craftsmanship, 0.3~0.5h can be incited somebody to action before use of the material
It takes out from baking oven；Preliminary drying process does not have phenolic resin impregnation of carbon fibers 3 D weaving body soft if temperature is lower than 80 DEG C
Change effect, material is still harder, cannot improve the craftsmanship of the material, if temperature is higher than 100 DEG C and the time is greater than 4h, phenolic aldehyde tree
Small molecule release is had in phenolic resin in rouge impregnation of carbon fibers 3 D weaving body, material inactive influences material bonding quality；
3b) preheat: adjustment heating platform temperature is to 55 ± 10 DEG C, the ethylene-propylene diene copolymer that will have been cleaned up in step 2c)
Multiple EPDM films and pre-baked phenolic resin impregnation of carbon fibers 3 D weaving body are taken to place to heated flat in piece
It is preheated on platform；
4) first time patch
4a) brush coating: in the polytetrafluoroethylene (PTFE) layer surface and step 3b of core model) in multiple EPDM films a surface it is each
The adhesive for brushing one layer of corresponding interface in advance, dries in the air to 8~10min to tack-free state；
4b) EPDM film patch: the brush coating face paste of first EPDM film in step 4a) is poly- to core model
The brush coating face of tetrafluoroethene layer, uses laser-projector as axial position benchmark when putting up；In first EPDM film
Another side brush coating stick, by the brush coating face paste of second EPDM film in step 4a) to second ethylene-propylene diene copolymer
On the brush coating face of piece, use laser-projector as axial position benchmark when putting up；It successively puts up up to last in step 4a)
In the brush coating face paste of one EPDM film to the brush coating face of second from the bottom EPDM film, thrown when putting up using laser
Shadow instrument is as axial position benchmark；
4c) brush coating: another surface of outermost layer EPDM film and phenolic resin leaching on being posted in mandrel surface
Stain carbon fiber 3 D weaving body surface face carries out the brushing of corresponding adhesive, and adhesive requires to brush uniformly, no leakage brush；It brushes laggard
Row is hung, and is dried in the air to 8~10min to tack-free state；
4d) phenolic resin impregnation of carbon fibers 3 D weaving body is fixed: using polytetrafluoroethylene (PTFE) adhesive tape by phenolic resin first
The width position of impregnation of carbon fibers 3 D weaving body is fixed to mandrel surface outermost layer EPDM film surface of position to be puted up,
Laser-projector can be borrowed when putting up as benchmark；
4e) phenolic resin impregnation of carbon fibers 3 D weaving shows consideration for piece: according to the reference line of laser-projector, by phenolic resin
Impregnation of carbon fibers 3 D weaving body is circumferentially puted up, and carries out catching up with gas when putting up, and guarantees that phenolic resin impregnation of carbon fibers is three-dimensional
Knitted body is bonded with lower section EPDM film, finally that phenolic resin impregnation of carbon fibers 3 D weaving body is end to end, at this time
The polytetrafluoroethylene (PTFE) adhesive tape of fixed phenolic resin impregnation of carbon fibers 3 D weaving body is removed, and in phenolic resin impregnation of carbon fibers three
The dimension end to end place of knitted body is pasted using polytetrafluoroethylene (PTFE) adhesive tape, is fixed；
5) first time precompressed and preliminary drying
5a) first time precompressed: phenolic resin impregnation of carbon fibers 3 D weaving body surface face ring in step 4e) is to winding one
Layer polytetrafluoroethylene film, reuses wrapping machine for step 4e) middle gained multiphase heat insulation layer intermediate outside progress glass fibre
Layer winding, the tension of one-ply yarn is 15~30N when winding；
5b) first time preliminary drying: the multiphase heat insulation layer of step 5a) being placed in baking oven and is heat-treated, temperature be 80~
100 DEG C/2~4h, 50 DEG C or less then are cooled to furnace and is come out of the stove；
6) first dressing
Glass layer cleaning: the fiber of multiphase insulation layer surface is cut and is cleaned out, while cleaning up phenolic aldehyde tree
Polytetrafluoroethylene (PTFE) adhesive tape at rouge impregnation of carbon fibers 3 D weaving body lap position, reuses ethyl acetate and is insulated to entire multiphase
Layer surface is cleared up, is dried；
7) second of patch
It 7a) preheats: adjusting heating platform temperature to 5 ± 10 DEG C, the EPDM film that will have been cleaned up in step 2c)
In take multiple EPDM films to place to being preheated on heating platform；
7b) brush coating: in phenolic resin impregnation of carbon fibers 3 D weaving external surface and step 7a) in multiple ethylene-propylene diene copolymers
Each pre- adhesive for brushing one layer of corresponding interface in one surface of piece, adhesive require to brush uniformly, no leakage brush；It dries in the air after brushing
It sets, dries in the air to 8~10min to tack-free state；
7c) EPDM film patch: it on the basis of phenolic resin impregnation of carbon fibers 3 D weaving body axial position, will walk
Rapid 7b) in first EPDM film brush coating face paste to the brush coating face of phenolic resin impregnation of carbon fibers 3 D weaving body,
And first EPDM film requires the overlap edge of covering phenolic resin impregnation of carbon fibers 3 D weaving body；In the first Zhang San member
The another side brush coating stick of the third film of second, by the brush coating face paste of second EPDM film in step 7b) to the second Zhang San
On the brush coating face of first the third film of second；Successively put up until step 7a) in last EPDM film brush coating face paste extremely
On the brush coating face of second from the bottom EPDM film；
8) second of precompressed and preliminary drying
8a) second of precompressed: in step 7c) last EPDM film surface loop to winding one layer of polytetrafluoroethyl-ne
Alkene film reuses wrapping machine for step 7c) carry out glass layer winding outside gained multiphase heat insulation layer intermediate, when winding
The tension of one-ply yarn is 15~30N；
8b) preliminary drying: the multiphase heat insulation layer of step 8a) is placed into 4~8h and carries out precompressed or be placed in baking oven to carry out hot place
Reason, heat treatment temperature are 80~100 DEG C/2~4h, are cooled to 50 DEG C or less with furnace and come out of the stove；
9) it clears up for second
The fiber of multiphase insulation layer surface is cut and cleaned out, while cleaning up polytetrafluoroethyl-ne outside multiphase heat insulation layer
Alkene film；Ethyl acetate is reused to clear up entire multiphase insulation layer surface, dry；
10) it corrects, pressurize, solidification
10a) multiphase heat insulation layer is modified: multiphase heat insulation layer boss being polished flat with sanding machine, to pit with three
First the third heat-insulating material of second is repaired, and is connected with adhesive；
10b) multiphase heat insulation layer pressurizes: carbon fiber being immersed in resin material, the multiphase heat insulation layer table obtained by step 10a)
Face winding has the carbon fiber of resin material；
10c) multiphase heat insulation layer solidifies: multiphase heat insulation layer obtained by step 10b) being placed 1~3h at room temperature, is then placed in
It is finally dropped in 50~90 DEG C of 2~4h of solidification, 100~130 DEG C of 2~4h of solidification, 140~170 DEG C of 4~10h of solidification respectively in oven
To room temperature, and mandrel and core model are removed, required fiber wound and solidified rocket engine multiphase heat insulation layer is made.
It is exhausted that the multiphase prepared is used cooperatively with EPDM by using phenolic resin impregnation of carbon fibers 3 D weaving body
On the one hand the Burning corrosion resistance of heat-insulating material can be improved in the case where not increasing heat insulation layer thickness, reduce engine for hot material
The passive quality of shell, improves the mass ratio of engine；On the other hand by the way of multiple-layered patches and sandwich is set
Meter, molding multiphase heat-insulating material have preferable craftsmanship；
The once precompressed later of phenolic resin impregnation of carbon fibers 3 D weaving body is puted up, its purpose is to phenolic aldehyde tree is discharged
Gas between rouge impregnation of carbon fibers 3 D weaving body and lower section EPDM film surface guarantees the fitting of the two interface；Complete
Portion's multiphase heat insulation layer completes the production and then carries out a precompressed, and its purpose is to phenolic resin impregnation of carbon fibers three is discharged
The gas between its top ethylene-propylene diene copolymer piece of knitted body is tieed up, guarantees phenolic resin impregnation of carbon fibers 3 D weaving body and upper and lower
The insulation bed boundary good fit of position.If an only precompressed, or without carry out precompressed, then the EPDM prepared with
The defects of will appear bulge, gas enclosure, unsticking between phenolic resin impregnation of carbon fibers 3 D weaving body multiphase heat-insulating material.
Fiber wound and solidified rocket engine multiphase of the present invention is elaborated with test result combined with specific embodiments below
Heat insulation layer forming method.
Embodiment
1) ambient temperature and humidity control and mandrel surface processing
Using air-conditioning or dehumidifier, the environment temperature for adjusting the production of multiphase heat insulation layer is 25 ± 3 DEG C, relative humidity≤
75%；And the dust for being used for the molding mandrel surface of motor body is cleared up, in its surface wrap or put up one layer of polytetrafluoroethyl-ne
Alkene layer；
2) prepared by EPDM film
2a) slice: the roller spacing of rubber mixing machine is first adjusted to 2.5mm, it is pre- that EPDM heat-insulating material is passed through into rubber mixing machine
It handles and is kneaded 3 times back and forth, then adjust roller spacing, several EPDM films are made by the thickness of 0.5mm, 2mm；
It 2b) cuts: determining the overall developed dimension of EPDM film by the outer diameter and length of core model, and press circumferencial direction
EPDM film 10 is taken to open, by every EPDM film that the requirement cutting of width 400mm needs to paste, and with a thickness of
All ethylene-propylene diene copolymer on pieces of 0.5mm reserve the overlapping part of 10mm, all ethylene-propylene diene copolymer on pieces of thickness 2mm reserve slope
Mouth production position；
It 2c) cleans: all EPDM films after cutting being cleaned using ethyl acetate and clean hairless paper
And dry, it dries and is isolated between rear every adjacent two EPDM films with clean isolation cloth；
3) it pre-processes for the first time
3a) preliminary drying: the good phenolic resin impregnation of carbon fibers 3 D weaving body of precuring is put into baking oven and carries out preliminary drying, in advance
Baking process is 90 DEG C/3h, to guarantee that material has preferable craftsmanship, 0.5h can be taken it from baking oven before use of the material
Out；
3b) preheat: adjustment heating platform temperature, will be in the EPDM film that cleaned up in step 2c) to 60 DEG C
5 EPDM films and pre-baked phenolic resin impregnation of carbon fibers 3 D weaving body are taken to place enterprising to heating platform
Row preheating；
4) first time patch
4a) brush coating: in the polytetrafluoroethylene (PTFE) layer surface and step 3b of core model) in 5 EPDM films a surface it is each
The adhesive for brushing one layer of corresponding interface in advance, dries in the air to 8~10min to tack-free state；
4b) EPDM film patch: the brush coating face paste of first EPDM film in step 4a) is poly- to core model
The brush coating face of tetrafluoroethene layer, uses laser-projector as axial position benchmark when putting up；In first EPDM film
Another side brush coating stick, by the brush coating face paste of second EPDM film in step 4a) to second ethylene-propylene diene copolymer
On the brush coating face of piece, use laser-projector as axial position benchmark when putting up；It successively puts up up to last in step 4a)
In the brush coating face paste of one EPDM film to the brush coating face of second from the bottom EPDM film, thrown when putting up using laser
Shadow instrument is as axial position benchmark；
4c) brush coating: another surface of outermost layer EPDM film and phenolic resin leaching on being posted in mandrel surface
Stain carbon fiber 3 D weaving body surface face carries out the brushing of corresponding adhesive, and adhesive requires to brush uniformly, no leakage brush；It brushes laggard
Row is hung, and is dried in the air to 8~10min to tack-free state；
4d) phenolic resin impregnation of carbon fibers 3 D weaving body is fixed: using polytetrafluoroethylene (PTFE) adhesive tape by phenolic resin first
The width position of impregnation of carbon fibers 3 D weaving body is fixed to mandrel surface outermost layer EPDM film surface of position to be puted up,
Laser-projector can be borrowed when putting up as benchmark；
4e) phenolic resin impregnation of carbon fibers 3 D weaving shows consideration for piece: according to the reference line of laser-projector, by phenolic resin
Impregnation of carbon fibers 3 D weaving body is circumferentially puted up, and carries out catching up with gas when putting up, and guarantees that phenolic resin impregnation of carbon fibers is three-dimensional
Knitted body is bonded with lower section EPDM film, finally that phenolic resin impregnation of carbon fibers 3 D weaving body is end to end, at this time
The polytetrafluoroethylene (PTFE) adhesive tape of fixed phenolic resin impregnation of carbon fibers 3 D weaving body is removed, and in phenolic resin impregnation of carbon fibers three
The dimension end to end place of knitted body is pasted using polytetrafluoroethylene (PTFE) adhesive tape, is fixed, as shown in Figure 1；
5) first time precompressed and preliminary drying
5a) first time precompressed: phenolic resin impregnation of carbon fibers 3 D weaving body surface face ring in step 4e) is to winding one
Layer polytetrafluoroethylene film, reuses wrapping machine for step 4e) middle gained multiphase heat insulation layer intermediate outside progress glass fibre
Layer winding, the tension of one-ply yarn is 20N when winding；
5b) first time preliminary drying: the multiphase heat insulation layer of step 5a) being placed in baking oven and is heat-treated, temperature be 90 DEG C/
Then 3h is cooled to 50 DEG C or less with furnace and comes out of the stove；
6) first dressing
Glass layer cleaning: the fiber of multiphase insulation layer surface is cut and is cleaned out, while cleaning up phenolic aldehyde tree
Polytetrafluoroethylene (PTFE) adhesive tape at rouge impregnation of carbon fibers 3 D weaving body lap position, reuses ethyl acetate and is insulated to entire multiphase
Layer surface is cleared up, is dried；
7) second of patch
7a) preheat: adjustment heating platform temperature, will be in the EPDM film that cleaned up in step 2c) to 10 DEG C
Last 5 EPDM films are taken to place to being preheated on heating platform；
7b) brush coating: in phenolic resin impregnation of carbon fibers 3 D weaving external surface and step 7a) in 5 ethylene-propylene diene copolymers
Each pre- adhesive for brushing one layer of corresponding interface in one surface of piece, adhesive require to brush uniformly, no leakage brush；It dries in the air after brushing
It sets, dries in the air to 8~10min to tack-free state；
7c) EPDM film patch: it on the basis of phenolic resin impregnation of carbon fibers 3 D weaving body axial position, will walk
Rapid 7b) in first EPDM film brush coating face paste to the brush coating face of phenolic resin impregnation of carbon fibers 3 D weaving body,
And first EPDM film requires the overlap edge of covering phenolic resin impregnation of carbon fibers 3 D weaving body；In the first Zhang San member
The another side brush coating stick of the third film of second, by the brush coating face paste of second EPDM film in step 7b) to the second Zhang San
On the brush coating face of first the third film of second；Successively put up until step 7a) in last EPDM film brush coating face paste extremely
On the brush coating face of second from the bottom EPDM film；
8) second of precompressed and preliminary drying
8a) second of precompressed: in step 7c) last EPDM film surface loop to winding one layer of polytetrafluoroethyl-ne
Alkene film reuses wrapping machine for step 7c) carry out glass layer winding outside gained multiphase heat insulation layer intermediate, when winding
The tension of one-ply yarn is 20N；
8b) preliminary drying: placing 6h for the multiphase heat insulation layer of step 8a) and carry out precompressed or be placed in baking oven to be heat-treated,
Heat treatment temperature is 90 DEG C/3h, is cooled to 50 DEG C or less with furnace and comes out of the stove；
9) it clears up for second
The fiber of multiphase insulation layer surface is cut and cleaned out, while cleaning up polytetrafluoroethyl-ne outside multiphase heat insulation layer
Alkene film；Ethyl acetate is reused to clear up entire multiphase insulation layer surface, dry；
10) it corrects, pressurize, solidification
10a) multiphase heat insulation layer is modified: multiphase heat insulation layer boss being polished flat with sanding machine, to pit with three
First the third heat-insulating material of second is repaired, and is connected with adhesive；
10b) multiphase heat insulation layer pressurizes: carbon fiber being immersed in resin material, the multiphase heat insulation layer table obtained by step 10a)
Face winding has the carbon fiber of resin material；
10c) multiphase heat insulation layer solidifies: multiphase heat insulation layer obtained by step 10b) being placed 1~3h at room temperature, is then placed in
It is finally down to room temperature, and remove mandrel and core model in 80 DEG C of solidification 3h, 120 DEG C of solidification 3h, 160 DEG C of solidification 6h respectively in oven,
Required fiber wound and solidified rocket engine multiphase heat insulation layer is made, as shown in Figure 2.
EPDM-phenolic aldehyde the tree prepared using this fiber wound and solidified rocket engine multiphase heat insulation layer forming method
Rouge impregnation of carbon fibers 3 D weaving body multiphase heat-insulating material, ablating rate are apparently higher than EPDM heat-insulating material, use
The detection of GJB323A progress oxy-acetylene linear ablative rate, it is known that, the linear ablative rate average value 0.087mm/ of EPDM heat-insulating material
S, and the linear ablative rate average value 0.052mm/s of the multiphase heat-insulating material of this programme preparation, decline about 40%；Meanwhile it examining
Bonding interface intensity between EPDM and phenolic resin impregnation of carbon fibers 3 D weaving body, respectively according to QJ2038.1A,
QJ2038.2 avulse, shear the preparation and performance test of sample, and testing result is shown in Table 1.
Claims (9)
1. a kind of fiber wound and solidified rocket engine multiphase heat insulation layer forming method, it is characterised in that: the multiphase heat insulation layer
It is collectively constituted by the EPDM and phenolic resin impregnation of carbon fibers 3 D weaving body of resistance to ablation, forming method includes following step
It is rapid:
1) mandrel surface is handled
Cleaning is used for the dust of the molding mandrel surface of motor body, in its surface wrap or puts up a strata tetrafluoroethene
Layer；
2) it pre-processes for the first time
2a) preliminary drying: the good phenolic resin impregnation of carbon fibers 3 D weaving body of precuring being put into baking oven and carries out preliminary drying, preliminary drying mistake
Journey is 80~100 DEG C/2~4h；
2b) preheat: adjustment heating platform temperature will take multiple EPDM films and a pre-baked phenolic aldehyde to 55 ± 10 DEG C
Resin impregnated carbon fiber 3 D weaving body is placed to being preheated on heating platform；
3) first time patch
3a) brush coating: in the polytetrafluoroethylene (PTFE) layer surface and step 3b of core model) in multiple EPDM films a surface it is each pre-brush
The adhesive for applying one layer of corresponding interface, dries in the air to tack-free state；
3b) EPDM film patch: by the brush coating face paste of first EPDM film in step 3a) to core model polytetrafluoro
The brush coating face of pvdf layer；In the another side brush coating stick of first EPDM film, by second Zhang San's member second in step 3a)
In the brush coating face paste of third film to the brush coating face of second EPDM film；Successively put up until step 3a) in last
In the brush coating face paste to the brush coating face of second from the bottom EPDM film for opening EPDM film；
3c) brush coating: another surface of outermost layer EPDM film and phenolic resin impregnated carbon on being posted in mandrel surface
Fibre three-dimensional knitted body surface carries out the brushing of corresponding adhesive；It is hung after brushing to tack-free state；
3d) phenolic resin impregnation of carbon fibers 3 D weaving body is fixed: first being impregnated phenolic resin using polytetrafluoroethylene (PTFE) adhesive tape
The width position of carbon fiber 3 D weaving body is fixed to mandrel surface outermost layer EPDM film surface of position to be puted up；
3e) phenolic resin impregnation of carbon fibers 3 D weaving shows consideration for piece: circumferentially by phenolic resin impregnation of carbon fibers 3 D weaving body
It is puted up, carries out catching up with gas when putting up, guarantee that phenolic resin impregnation of carbon fibers 3 D weaving body and lower section EPDM film paste
It closes, it is finally that phenolic resin impregnation of carbon fibers 3 D weaving body is end to end, fixed phenolic resin impregnation of carbon fibers is removed at this time
The polytetrafluoroethylene (PTFE) adhesive tape of 3 D weaving body, and poly- four are used at the phenolic resin end to end place of impregnation of carbon fibers 3 D weaving body
Vinyl fluoride adhesive tape is pasted, is fixed；
4) first time precompressed and preliminary drying
4a) first time precompressed: phenolic resin impregnation of carbon fibers 3 D weaving body surface face ring in step 3e) is to winding a strata
Tetrafluoroethene film reuses wrapping machine for step 3e) in carry out glass layer outside gained multiphase heat insulation layer intermediate and twine
Around；
4b) first time preliminary drying: the multiphase heat insulation layer of step 4a) being placed in baking oven and is heat-treated, and temperature is 80~100
DEG C/2~4h；
5) first dressing
6) second of patch
6a) preheat: adjustment heating platform temperature takes multiple EPDM films to place to carrying out on heating platform to 5 ± 10 DEG C
Preheating；
6b) brush coating: in phenolic resin impregnation of carbon fibers 3 D weaving external surface and step 6a) in multiple EPDM films
Each pre- adhesive for brushing one layer of corresponding interface in one surface；It is hung, is dried in the air to tack-free state after brushing；
6c) EPDM film patch: on the basis of phenolic resin impregnation of carbon fibers 3 D weaving body axial position, by step
The brush coating face paste of first EPDM film in 6b) to the brush coating face of phenolic resin impregnation of carbon fibers 3 D weaving body, and
First EPDM film requires the overlap edge of covering phenolic resin impregnation of carbon fibers 3 D weaving body；In first Zhang San's member second
The another side brush coating stick of third film, by the brush coating face paste of second EPDM film in step 6b) to the second Zhang San member
On the brush coating face of the third film of second；The brush coating face paste up to last EPDM film in step 6a) is successively puted up to
Number second is opened on the brush coating face of EPDM film；
7) second of precompressed and preliminary drying
7a) second of precompressed: last EPDM film surface loop is thin to one strata tetrafluoroethene of winding in step 6c)
Film reuses wrapping machine for step 7c) the progress glass layer winding of gained multiphase heat insulation layer intermediate outside；
7b) preliminary drying: placing 4~8h for the multiphase heat insulation layer of step 7a) and carry out precompressed or be placed in baking oven to be heat-treated,
Heat treatment temperature is 80~100 DEG C/2~4h；
8) it clears up for second
9) it corrects, pressurize, solidification.
2. fiber wound and solidified rocket engine multiphase heat insulation layer forming method according to claim 1, it is characterised in that: institute
The environment temperature for stating forming method is 25 ± 10 DEG C, relative humidity≤75%.
3. fiber wound and solidified rocket engine multiphase heat insulation layer forming method according to claim 1, it is characterised in that: institute
State EPDM film preparation process specifically:
Slice: the roller spacing of rubber mixing machine is first adjusted to 2~3mm, EPDM heat-insulating material is pre-processed simultaneously by rubber mixing machine
It is kneaded 3~4 times back and forth, then adjusts roller spacing, several ternary second are made by the thickness of 0.5 ± 0.1mm, 2 ± 0.1mm
Third film；
It cuts: determining the overall developed dimension of EPDM film by the outer diameter and length of core model, and take ternary by circumferencial direction
4~20, the third film of second is cut by the requirement of 300~500mm of width and needs every EPDM film pasting, and thickness≤
All ethylene-propylene diene copolymer on pieces of 1.5mm reserve all EPDM films of overlapping part, thickness >=1.5mm of 10~15mm
Upper reserved groove makes position；
Cleaning: being cleaned and dried to all EPDM films after cutting using ethyl acetate and clean hairless paper,
It dries and is isolated between rear every adjacent two EPDM films with clean isolation cloth, prevent adjacent two ethylene-propylene diene copolymers
Piece adhesion.
4. fiber wound and solidified rocket engine multiphase heat insulation layer forming method according to claim 1, it is characterised in that: institute
State step 2a) in, it is taken out from baking oven using preceding 0.3~0.5h in phenolic resin impregnation of carbon fibers 3 D weaving body.
5. fiber wound and solidified rocket engine multiphase heat insulation layer forming method according to claim 1, it is characterised in that: institute
State step 4a) in, the tension of one-ply yarn is 15~30N when winding.
6. fiber wound and solidified rocket engine multiphase heat insulation layer forming method according to claim 1, it is characterised in that: institute
It states in step 5), the detailed process of first dressing are as follows: glass layer cleaning: the fiber of multiphase insulation layer surface is cut simultaneously
It cleans out, while cleaning up the polytetrafluoroethylene (PTFE) adhesive tape at phenolic resin impregnation of carbon fibers 3 D weaving body lap position, then
Entire multiphase insulation layer surface is cleared up using ethyl acetate, is dried.
7. fiber wound and solidified rocket engine multiphase heat insulation layer forming method according to claim 1, it is characterised in that: institute
State step 7a) in, the tension of one-ply yarn is 15~30N when winding.
8. fiber wound and solidified rocket engine multiphase heat insulation layer forming method according to claim 1, it is characterised in that: institute
It states in step 8), the detailed process of second of cleaning are as follows: the fiber of multiphase insulation layer surface is cut and cleaned out, while is clear
Reason falls polytetrafluoroethylene film outside multiphase heat insulation layer；Reuse ethyl acetate to entire multiphase insulation layer surface cleared up,
It dries.
9. fiber wound and solidified rocket engine multiphase heat insulation layer forming method according to claim 1, it is characterised in that: institute
It states in step 9), amendment, pressurization, solidification detailed process are as follows:
9a) multiphase heat insulation layer is modified: multiphase heat insulation layer boss being polished flat with sanding machine, to pit EPDM
Heat-insulating material is repaired, and is connected with adhesive；
9b) multiphase heat insulation layer pressurizes: carbon fiber being immersed in resin material, the multiphase heat insulation layer surface wrap obtained by step 10a)
Carbon fiber with resin material；
9c) multiphase heat insulation layer solidifies: multiphase heat insulation layer obtained by step 9b) being placed 1~3h at room temperature, is then placed in oven
Respectively in 50~90 DEG C of 2~4h of solidification, 100~130 DEG C of 2~4h of solidification, 140~170 DEG C of 4~10h of solidification, it is finally down to room
Temperature, and mandrel and core model are removed, required fiber wound and solidified rocket engine multiphase heat insulation layer is made.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111957901A (en) * | 2020-08-25 | 2020-11-20 | 湖北三江航天江北机械工程有限公司 | Large-diameter engine shell gypsum core mold forming method |
| CN115895130A (en) * | 2022-12-05 | 2023-04-04 | 湖北三江航天江河化工科技有限公司 | Three-dimensional carbon fiber woven body reinforced ethylene propylene diene monomer-phenolic aldehyde scouring-resistant composite material and preparation method thereof |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0552676A1 (en) * | 1992-01-22 | 1993-07-28 | Dornier Gmbh | Protection system for parts subjected to high thermal loads or the thermal loads and dynamic pressure loads |
| 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 |
| CN104354436A (en) * | 2014-11-07 | 2015-02-18 | 湖北三江航天江北机械工程有限公司 | Manufacturing method of composite material shell wound by high-temperature-resistant fiber |
| 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 |
| CN104875467A (en) * | 2014-02-28 | 2015-09-02 | 湖北航天化学技术研究所 | Resin-based premix and rocket engine housing synchronous thermal-curing and adhesion method |
| CN104943184A (en) * | 2015-05-15 | 2015-09-30 | 湖北三江航天江河化工科技有限公司 | Mounting forming method of heat insulating layer |
| CN107322951A (en) * | 2017-08-05 | 2017-11-07 | 湖北三江航天江北机械工程有限公司 | Solid propellant rocket internal insulation winding, molding method |
-
2018
- 2018-11-15 CN CN201811360257.2A patent/CN109605776B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0552676A1 (en) * | 1992-01-22 | 1993-07-28 | Dornier Gmbh | Protection system for parts subjected to high thermal loads or the thermal loads and dynamic pressure loads |
| 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 |
| CN104875467A (en) * | 2014-02-28 | 2015-09-02 | 湖北航天化学技术研究所 | Resin-based premix and rocket engine housing synchronous thermal-curing and adhesion method |
| CN104354436A (en) * | 2014-11-07 | 2015-02-18 | 湖北三江航天江北机械工程有限公司 | Manufacturing method of composite material shell wound by high-temperature-resistant fiber |
| 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 |
| CN104943184A (en) * | 2015-05-15 | 2015-09-30 | 湖北三江航天江河化工科技有限公司 | Mounting forming method of heat insulating layer |
| CN107322951A (en) * | 2017-08-05 | 2017-11-07 | 湖北三江航天江北机械工程有限公司 | Solid propellant rocket internal insulation winding, molding method |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111957901A (en) * | 2020-08-25 | 2020-11-20 | 湖北三江航天江北机械工程有限公司 | Large-diameter engine shell gypsum core mold forming method |
| CN115895130A (en) * | 2022-12-05 | 2023-04-04 | 湖北三江航天江河化工科技有限公司 | Three-dimensional carbon fiber woven body reinforced ethylene propylene diene monomer-phenolic aldehyde scouring-resistant composite material and preparation method thereof |
| CN115895130B (en) * | 2022-12-05 | 2024-03-22 | 湖北三江航天江河化工科技有限公司 | Three-dimensional carbon fiber woven body reinforced ethylene-propylene-diene monomer-phenolic anti-scouring composite material and preparation method thereof |
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