CN110792529B - Solid rocket engine front head inner heat insulation layer and forming method thereof - Google Patents
Solid rocket engine front head inner heat insulation layer and forming method thereof Download PDFInfo
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—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
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- C—CHEMISTRY; METALLURGY
- C09—DYES; PAINTS; POLISHES; NATURAL RESINS; ADHESIVES; COMPOSITIONS NOT OTHERWISE PROVIDED FOR; APPLICATIONS OF MATERIALS NOT OTHERWISE PROVIDED FOR
- C09D—COATING COMPOSITIONS, e.g. PAINTS, VARNISHES OR LACQUERS; FILLING PASTES; CHEMICAL PAINT OR INK REMOVERS; INKS; CORRECTING FLUIDS; WOODSTAINS; PASTES OR SOLIDS FOR COLOURING OR PRINTING; USE OF MATERIALS THEREFOR
- C09D161/00—Coating compositions based on condensation polymers of aldehydes or ketones; Coating compositions based on derivatives of such polymers
- C09D161/04—Condensation polymers of aldehydes or ketones with phenols only
- C09D161/06—Condensation polymers of aldehydes or ketones with phenols only of aldehydes with phenols
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- C—CHEMISTRY; METALLURGY
- C09—DYES; PAINTS; POLISHES; NATURAL RESINS; ADHESIVES; COMPOSITIONS NOT OTHERWISE PROVIDED FOR; APPLICATIONS OF MATERIALS NOT OTHERWISE PROVIDED FOR
- C09D—COATING COMPOSITIONS, e.g. PAINTS, VARNISHES OR LACQUERS; FILLING PASTES; CHEMICAL PAINT OR INK REMOVERS; INKS; CORRECTING FLUIDS; WOODSTAINS; PASTES OR SOLIDS FOR COLOURING OR PRINTING; USE OF MATERIALS THEREFOR
- C09D7/00—Features of coating compositions, not provided for in group C09D5/00; Processes for incorporating ingredients in coating compositions
- C09D7/40—Additives
- C09D7/60—Additives non-macromolecular
- C09D7/61—Additives non-macromolecular inorganic
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- C—CHEMISTRY; METALLURGY
- C09—DYES; PAINTS; POLISHES; NATURAL RESINS; ADHESIVES; COMPOSITIONS NOT OTHERWISE PROVIDED FOR; APPLICATIONS OF MATERIALS NOT OTHERWISE PROVIDED FOR
- C09D—COATING COMPOSITIONS, e.g. PAINTS, VARNISHES OR LACQUERS; FILLING PASTES; CHEMICAL PAINT OR INK REMOVERS; INKS; CORRECTING FLUIDS; WOODSTAINS; PASTES OR SOLIDS FOR COLOURING OR PRINTING; USE OF MATERIALS THEREFOR
- C09D7/00—Features of coating compositions, not provided for in group C09D5/00; Processes for incorporating ingredients in coating compositions
- C09D7/40—Additives
- C09D7/60—Additives non-macromolecular
- C09D7/63—Additives non-macromolecular organic
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- C—CHEMISTRY; METALLURGY
- C09—DYES; PAINTS; POLISHES; NATURAL RESINS; ADHESIVES; COMPOSITIONS NOT OTHERWISE PROVIDED FOR; APPLICATIONS OF MATERIALS NOT OTHERWISE PROVIDED FOR
- C09D—COATING COMPOSITIONS, e.g. PAINTS, VARNISHES OR LACQUERS; FILLING PASTES; CHEMICAL PAINT OR INK REMOVERS; INKS; CORRECTING FLUIDS; WOODSTAINS; PASTES OR SOLIDS FOR COLOURING OR PRINTING; USE OF MATERIALS THEREFOR
- C09D7/00—Features of coating compositions, not provided for in group C09D5/00; Processes for incorporating ingredients in coating compositions
- C09D7/40—Additives
- C09D7/70—Additives characterised by shape, e.g. fibres, flakes or microspheres
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/20—Manufacture essentially without removing material
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Abstract
The invention discloses a solid rocket engine front head inner heat insulation layer structure and a forming method thereof, which realize an inner profile multi-step structure of an inner heat insulation layer, wherein the inner heat insulation layer is manufactured by the following method: the method comprises the following steps: manufacturing a mould according to the inner heat insulation layer structure; step two: carrying out sand blasting treatment on the inner wall surface of the front end socket; step three: configuring a liquid heat insulating layer; pouring a liquid heat insulation layer with set mass into the front end socket; assembling the die and the front end enclosure to a set position to ensure the design thickness of the heat insulation layer; step six: putting the product into an oven for curing; step seven: and after the curing time is met, taking out the product, cooling to normal temperature, taking out the mold, and shaping and cutting the heat insulation layer to obtain the designed heat insulation layer. The heat insulating layer has high size control precision, good quality consistency and simple process, and can meet the molding requirements of various irregular inner heat insulating layers.
Description
Technical Field
The invention relates to an inner heat insulation layer structure of a front head of a solid rocket engine and a forming method thereof, belonging to the technical field of the inner heat insulation layer structure of the front head of the solid rocket engine.
Background
The inner heat insulation layer is one of important parts in a solid rocket engine heat protection structure, and plays roles of heat insulation and protection in the working process of the engine so as to ensure that the metal shell is not ablated by high-temperature gas. Along with the higher and higher requirements of tactical missiles on the performance of solid rocket engines, the charging structures of the engines are diversified, so that the structures of the inner heat insulation layers are more and more complicated. The inner heat insulation layer is used as the passive quality of the engine, and the designed inner heat insulation layer is guaranteed to be as thin as possible on the premise of guaranteeing safe and reliable performance.
At present, the method for manufacturing the inner heat insulation layer mainly comprises two processes of hot pressing or compression molding after the ethylene propylene diene monomer rubber sheet rubber is pasted. The heat insulating layer in the front end enclosure of the engine is generally formed by sticking raw rubber sheets and then pressing, and the requirements of producing the heat insulating layer with ultrathin and complicated inner profile are difficult to realize by the thickness limitation of the raw rubber sheets and the forming process. Therefore, a stable and reliable molding process is needed to fulfill this need.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the defects of the prior art are overcome, the inner heat insulation layer structure of the front end socket of the solid rocket motor and the forming method thereof are provided, the conventional heat insulation layer design and forming process means are broken through, the production forming of the ultrathin and complex inner molded surface of the inner heat insulation layer of the front end socket is realized, the quality of the inner heat insulation layer can be reduced, and the efficiency of the motor is improved.
The technical solution of the invention is as follows:
the utility model provides an interior heat insulation layer structure of solid rocket engine front head, interior heat insulation layer is the hollow solid of revolution structure of curved cross-section for the inside heat insulation of solid rocket engine front head, and there is round platform form arch at the interior profile bottom center of interior heat insulation layer, and there are three fan ring form arch of evenly distributed at the interior profile middle part of interior heat insulation layer, and there are three fan ring form arch of evenly distributed at the interior profile edge of interior heat insulation layer, and the three fan ring form arch at middle part and edge crisscross distribution each other.
Further, the arc-shaped cross section of the inner insulating layer may be expressed as: the arc-shaped section is formed by tangency of three sections of surfaces, the central surface is a spherical surface of SR150mm, the transition surface is an arc surface of R30mm, and the outer side is a cylindrical surface with the diameter of 180 mm.
Furthermore, the thickness of the circular truncated cone-shaped bulge at the center of the bottom of the inner molded surface, the thickness of the three fan-shaped bulges at the middle part and the thickness of the three fan-shaped bulges at the edge are the same.
Furthermore, the edges of the circular truncated cone-shaped bulge at the center of the bottom of the inner molded surface, the three fan-shaped bulges at the middle part and the three fan-shaped bulges at the edges are all rounded, and the numerical value is R1.5mm.
Furthermore, the central angle of the middle fan-shaped annular bulge is 60 degrees, and the difference between the radiuses of the two arcs is 19 mm; the central angle of the edge fan-shaped annular bulge is 60 degrees; the size of the truncated cone-shaped bulge at the center of the bottom is 50mm in diameter and 1.5mm in height.
Further, the invention also provides a method for forming the internal heat insulation layer structure of the front head of the solid rocket motor, which comprises the following steps:
the method comprises the following steps: manufacturing an alloy aluminum mould according to the inner molded surface structure of the inner heat insulation layer, and spraying polytetrafluoroethylene on the surface of the mould;
step two: carrying out sand blasting treatment on the inner wall surface of the front end enclosure of the solid rocket engine to roughen the inner surface so as to improve the bonding property of the inner heat insulation layer and the metal front end enclosure;
step three: preparing a liquid heat insulating layer;
weighing the thermal insulation layer with a set mass in a liquid state, and pouring the thermal insulation layer into the front end enclosure;
assembling the die and the front end enclosure to the designed thickness position of the inner heat insulation layer, and fixing the die;
step six: putting the fixed product into an oven for curing;
step seven: after the curing time is met, the product is taken out, the temperature is reduced to the normal temperature, the mold is taken out, then the edge of the heat insulation layer in the front end socket is subjected to shaping cutting, the end face of the heat insulation layer is enabled to be flush with the metal surface, and the forming of the heat insulation layer structure in the front end socket is completed.
Further, in the step one, the outer surface of the alloy aluminum mould is the same as the inner surface of the heat insulation layer to be formed, the alloy aluminum mould is of a solid structure, and the outer surface is sprayed with an anti-sticking agent to ensure that the mould is not bonded with the heat insulation layer.
Further, the basic formula of the liquid heat insulating layer in the third step is as follows: 100 parts of base rubber, 3-5 parts of fiber filler, 50-55 parts of powder filler, 5-10 parts of plasticizer, 12-15 parts of crosslinking curing agent, 4-5 parts of functional assistant and 0.08-0.12 part of accelerator.
Further, the weight of the liquid heat insulating layer poured into the front end socket in the fourth step is 1.3-1.5 times of the design weight of the inner heat insulating layer.
Further, the curing conditions in the sixth step are as follows: the temperature of the oven is +60 ℃, and the curing is carried out for 5 to 7 days in the oven.
Compared with the prior art, the invention has the beneficial effects that:
(1) the design thickness of the heat insulation layer in the front seal head can be reduced, the passive quality of an engine is reduced, and the missile range is increased;
(2) the invention can meet the forming of various inner heat insulation layer structures with variable thickness, irregular shape and complex and changeable molded surfaces through the die and the liquid heat insulation layer, thereby realizing the diversity of charging design;
(3) the invention provides a method for forming an inner heat insulation layer of a complex structure, which has the advantages of simple product forming process, high size control precision and good product quality consistency.
Drawings
Fig. 1 is a schematic view 1 of an inner thermal insulation layer structure of a front head according to an embodiment of the present invention;
fig. 2 is a schematic diagram 2 of an inner thermal insulation layer structure of a front head according to an embodiment of the present invention.
Detailed Description
The invention provides a solution provided by the invention, which provides a front head inner heat insulation layer structure of a solid rocket motor and a forming method thereof, and the front head inner heat insulation layer structure comprises a front head 1 and an inner heat insulation layer 2 as shown in figures 1 and 2.
The inner heat insulation layer is of a hollow revolving body structure with an arc-shaped cross section and is used for internal heat insulation of a front head of the solid rocket engine, the center of the bottom of the inner molded surface of the inner heat insulation layer is provided with a circular truncated cone-shaped bulge, the middle of the inner molded surface of the inner heat insulation layer is provided with three fan-shaped bulges which are uniformly distributed, the edge of the inner molded surface of the inner heat insulation layer is provided with three fan-shaped bulges which are uniformly distributed, and the three fan-shaped bulges at the middle part and the three fan-shaped bulges at the edge are.
Interior heat insulation layer bulge just in time corresponds the fast grain of high combustion in the combustion chamber, and engine during operation, the fast grain of high combustion has burnt out fast, and heat insulation layer position can expose in advance in high temperature high pressure gas in its correspondence, and the heat preservation safe and reliable in engine course of the work of heat insulation layer in the bulge thickening can be guaranteed, prevents that metal casing from appearing overheated phenomenon.
The thickness of the circular truncated cone-shaped bulge at the center of the bottom of the inner molded surface, the thickness of the three fan-shaped bulges at the middle part and the thickness of the three fan-shaped bulges at the edge are the same.
The arc-shaped cross section of the inner heat insulation layer can be expressed as: the arc-shaped section is formed by tangency of three sections of surfaces, the central surface is a spherical surface of SR150mm, the transition surface is an arc surface of R30mm, and the outer side is a cylindrical surface with the diameter of 180 mm. The arc-shaped section is matched with the inner molded surface of the metal shell, so that the quality of the inner heat insulation layer can be reduced on the premise of ensuring the safety and reliability of thermal protection, the passive quality of the engine is reduced, and the mass ratio of the engine is improved.
Preferably, the edges of the circular truncated cone-shaped bulge at the center of the bottom of the inner molded surface, the three fan-shaped bulges at the middle part and the three fan-shaped bulges at the edges are all rounded, and the numerical value is R1.5mm. The rounding can reduce the structural stress in the curing process of the inner heat insulating layer, ensure the structural integrity of the inner heat insulating layer and improve the forming reliability of the inner heat insulating layer.
Preferably, the central angle of the middle sector annular bulge is 60 degrees, and the difference between the radiuses of the two arcs is 19 mm; the central angle of the edge fan-shaped annular bulge is 60 degrees; the size of the truncated cone-shaped bulge at the center of the bottom is 50mm in diameter and 1.5mm in height.
Aiming at the inner heat insulation layer structure, the invention also provides a method for forming the inner heat insulation layer structure of the front head of the solid rocket motor, which comprises the following steps:
the method comprises the following steps: manufacturing an alloy aluminum mould according to the inner molded surface structure of the inner heat insulation layer, and spraying polytetrafluoroethylene on the surface of the mould; the outer surface of the alloy aluminum mould is the same as the inner surface of the heat insulation layer to be formed, the alloy aluminum mould is of a solid structure, and the outer surface is sprayed with an anti-sticking agent to ensure that the mould is not bonded with the heat insulation layer. The distance between the end face of the die and the inner molded surface of the front end socket is equal to the thickness of the inner heat insulation layer and is 0.5 mm;
step two: carrying out sand blasting treatment on the inner wall surface of the front end enclosure of the solid rocket engine to roughen the inner surface so as to improve the bonding property of the inner heat insulation layer and the metal front end enclosure;
step three: preparing a heat insulating layer in a liquid state, specifically: butylated Hydroxyl (HTPB) base: 100 parts of carbon fiber filler, 3-5 parts of boron phenolic resin filler, 50-55 parts of boron phenolic resin filler, 5-10 parts of DEHP plasticizer, 12-15 parts of HB cross-linking curing agent, 4-5 parts of KH-550 functional additive and 0.08-0.12 part of YX-KZ accelerator.
Weighing the thermal insulation layer with a set mass in a liquid state, and pouring the thermal insulation layer into the front end enclosure; the weight of the liquid heat insulation layer poured into the front end socket is 1.3-1.5 times of the design weight of the inner heat insulation layer, and is 52-60.
Assembling the die and the front end enclosure to the designed thickness position of the inner heat insulation layer, and fixing the die;
step six: putting the fixed product into an oven for curing; the curing conditions were: the temperature of the oven is +60 ℃, and the curing is carried out for 5 to 7 days in the oven.
Step seven: after the curing time is met, the product is taken out, the temperature is reduced to the normal temperature, the mold is taken out, then the edge of the heat insulation layer in the front end socket is subjected to shaping cutting, the end face of the heat insulation layer is enabled to be flush with the metal surface, and the forming of the heat insulation layer structure in the front end socket is completed.
The invention can meet the forming of various inner heat insulation layer structures with variable thickness, irregular shape and complex and changeable molded surfaces through the die and the liquid heat insulation layer, thereby realizing the diversity of charging design; and the product molding process is simple, the size control precision is high, and the product quality consistency is good.
Example 1 of the present invention is given below:
the front seal head 1 is made of high-strength steel 30CrMnSiA material and is machined according to design requirements.
The inner heat insulating layer of the front end socket is manufactured according to the following steps:
the method comprises the following steps: manufacturing an alloy aluminum mould according to the inner molded surface structure of the inner heat insulation layer, and spraying polytetrafluoroethylene on the surface of the mould; the outer surface of the alloy aluminum mould is the same as the inner surface of the heat insulation layer to be formed;
step two: the inner wall surface of the front end enclosure is subjected to sand blasting treatment to make the inner surface rough so as to improve the bonding performance of the inner heat insulation layer and the metal front end enclosure and ensure reliable bonding and no debonding;
step three: preparing a liquid heat insulating layer;
butyl hydroxy agent: 100 parts of carbon fiber filler, 4 parts of boron phenolic resin filler, 8 parts of DEHP plasticizer, 15 parts of HB crosslinking curing agent, 5 parts of KH-550 functional auxiliary agent and 0.12 part of YX-KZ accelerator.
Weighing the liquid heat insulation layer with set mass, and pouring the liquid heat insulation layer into the front end enclosure; the weight of the liquid heat insulation layer poured into the front end socket is 52.9 g.
Step five: assembling the die and the front end enclosure to a set designed thickness position of the heat insulation layer, and fixing the die;
step six: the fixed product is put into an oven for curing, the temperature of the oven is +60 ℃, and the oven is kept still for curing for 5 days;
step seven: after the curing time is met, taking out the product, cooling to normal temperature, taking out the mold, then shaping and cutting the edge of the inner heat insulation layer of the front end socket, ensuring that the end face of the inner heat insulation layer is flush with the metal surface, and finally obtaining the designed inner heat insulation layer structure of the front end socket.
The surface of the heat insulation layer is smooth after molding, no bulge or pit exists, no bubble exists in the heat insulation layer, debonding between the heat insulation layer and the shell interface is detected by ultrasonic flaw detection, and the weight and the thickness of the heat insulation layer are shown in table 1. The performance of the heat insulating layer meets the index requirement.
Example 2 of the invention is given below:
the front seal head 1 is made of high-strength steel 30Cr3SiNiMoVA material and is machined according to design requirements.
The inner heat insulating layer of the front end socket is manufactured according to the following steps:
the method comprises the following steps: manufacturing an alloy aluminum mould according to the inner molded surface structure of the inner heat insulation layer, and spraying polytetrafluoroethylene on the surface of the mould; the outer surface of the alloy aluminum mould is the same as the inner surface of the heat insulation layer to be formed;
step two: the inner wall surface of the front end enclosure is subjected to sand blasting treatment to make the inner surface rough so as to improve the bonding performance of the inner heat insulation layer and the metal front end enclosure and ensure reliable bonding and no debonding;
step three: preparing a liquid heat insulating layer;
HTPB base: 100 parts of carbon fiber filler, 5 parts of boron phenolic resin filler, 8 parts of DEHP plasticizer, 14 parts of HB crosslinking curing agent, 4 parts of KH-550 functional auxiliary agent and 0.10 part of YX-KZ accelerator.
Weighing the liquid heat insulation layer with set mass, and pouring the liquid heat insulation layer into the front end enclosure; the weight of the liquid insulating layer poured into the front head was 56.7 g.
Step five: assembling the die and the front end enclosure to a set designed thickness position of the heat insulation layer, and fixing the die;
step six: the fixed product is put into an oven for curing, the temperature of the oven is plus 60 ℃, and the oven is kept still for curing for 7 days;
step seven: after the curing time is met, taking out the product, cooling to normal temperature, taking out the mold, then shaping and cutting the edge of the inner heat insulation layer of the front end socket, ensuring that the end face of the inner heat insulation layer is flush with the metal surface, and finally obtaining the designed inner heat insulation layer structure of the front end socket.
The surface of the heat insulation layer is smooth after molding, no bulge or pit exists, no bubble exists in the heat insulation layer, debonding between the heat insulation layer and the shell interface is detected by ultrasonic flaw detection, and the weight and the thickness of the heat insulation layer are shown in table 1. The performance of the heat insulating layer meets the index requirement.
TABLE 1 Heat-insulating layer Properties
The method of the invention realizes the high dimensional precision requirement and the precise molding of the inner heat insulation layer of the complex structure profile, and is suitable for the molding of the heat insulation layer of the solid rocket motor with special structural requirements.
While the embodiments of the present invention have been disclosed in the context of preferred embodiments, it will be apparent to those skilled in the art that the invention is not limited to the details of the foregoing illustrative embodiments, but is capable of numerous modifications and variations without departing from the spirit of the invention.
Claims (5)
1. A method for forming an inner heat insulation layer structure of a front head of a solid rocket engine is characterized by comprising the following steps:
the inner heat insulation layer structure of the front head of the solid rocket engine is a hollow revolving body structure with an arc-shaped section and is used for internal heat insulation of the front head of the solid rocket engine, a circular truncated cone-shaped bulge is arranged at the center of the bottom of an inner molded surface of the inner heat insulation layer, three fan-shaped bulges are uniformly distributed in the middle of the inner molded surface of the inner heat insulation layer, the three fan-shaped bulges are uniformly distributed at the edge of the inner molded surface of the inner heat insulation layer, and the three fan-shaped bulges at the middle and the three fan-shaped bulges at the edge are distributed in a staggered manner;
the arc-shaped cross section of the inner heat insulation layer is represented as: the arc-shaped section is formed by tangency of three sections of surfaces, the central surface is a spherical surface with the radius SR150mm, the transition surface is an arc surface with the radius R30mm, and the outer side is a cylindrical surface with the diameter of 180 mm;
the thickness of the circular truncated cone-shaped bulge at the center of the bottom of the inner molded surface, the thickness of the three fan-shaped bulges at the middle part and the thickness of the three fan-shaped bulges at the edge are the same;
the edges of the circular truncated cone-shaped bulge at the center of the bottom of the inner molded surface, the three fan-shaped bulges at the middle part and the three fan-shaped bulges at the edges are all rounded, and the numerical value is the radius R1.5mm;
the central angle of the middle sector annular bulge is 60 degrees, and the difference of the radiuses of the two arcs is 19 mm; the central angle of the edge fan-shaped annular bulge is 60 degrees; the size of the circular truncated cone-shaped bulge at the center of the bottom is 50mm in diameter and 1.5mm in height;
the method for forming the internal heat insulation layer structure of the front head of the solid rocket engine comprises the following steps:
the method comprises the following steps: manufacturing an alloy aluminum mould according to the inner molded surface structure of the inner heat insulation layer, and spraying polytetrafluoroethylene on the surface of the mould;
step two: carrying out sand blasting treatment on the inner wall surface of the front end enclosure of the solid rocket engine to roughen the inner surface so as to improve the bonding property of the inner heat insulation layer and the metal front end enclosure;
step three: preparing a liquid heat insulating layer;
weighing the thermal insulation layer with a set mass in a liquid state, and pouring the thermal insulation layer into the front end enclosure;
assembling the die and the front end enclosure to the designed thickness position of the inner heat insulation layer, and fixing the die;
step six: putting the fixed product into an oven for curing;
step seven: after the curing time is met, the product is taken out, the temperature is reduced to the normal temperature, the mold is taken out, then the edge of the heat insulation layer in the front end socket is subjected to shaping cutting, the end face of the heat insulation layer is enabled to be flush with the metal surface, and the forming of the heat insulation layer structure in the front end socket is completed.
2. The method for forming an insulation layer structure in a front head of a solid rocket motor according to claim 1, wherein: in the first step, the outer surface of the alloy aluminum mould is the same as the inner surface of the heat insulation layer to be formed, the alloy aluminum mould is of a solid structure, and the outer surface is sprayed with an anti-sticking agent to ensure that the mould is not bonded with the heat insulation layer.
3. The method for forming an insulation layer structure in a front head of a solid rocket motor according to claim 1, wherein: the basic formula of the liquid heat insulating layer in the third step is as follows: 100 parts of base rubber, 3-5 parts of fiber filler, 50-55 parts of powder filler, 5-10 parts of plasticizer, 12-15 parts of crosslinking curing agent, 4-5 parts of functional assistant and 0.08-0.12 part of accelerator.
4. The method for forming an insulation layer structure in a front head of a solid rocket motor according to claim 1, wherein: and in the fourth step, the weight of the liquid heat insulating layer poured into the front end socket is 1.3-1.5 times of the design weight of the inner heat insulating layer.
5. The method for forming an insulation layer structure in a front head of a solid rocket motor according to claim 1, wherein: the curing conditions in the sixth step are as follows: the temperature of the oven is +60 ℃, and the curing is carried out for 5 to 7 days in the oven.
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