CN119261233A - A method for preparing a thermal insulation layer structure of a solid rocket engine - Google Patents
A method for preparing a thermal insulation layer structure of a solid rocket engine Download PDFInfo
- Publication number
- CN119261233A CN119261233A CN202411786266.3A CN202411786266A CN119261233A CN 119261233 A CN119261233 A CN 119261233A CN 202411786266 A CN202411786266 A CN 202411786266A CN 119261233 A CN119261233 A CN 119261233A
- Authority
- CN
- China
- Prior art keywords
- layer
- heat insulation
- insulation layer
- heat
- bottom layer
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Landscapes
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
Abstract
本发明提供一种固体火箭发动机绝热层结构的制备方法，包括如下步骤：S1：采用模压法预制第一绝热层底层预制件；将第一绝热层底层预制件的外侧与金属接头连接；S2：采用模压法预制第二绝热层底层预制件；S3：将第一绝热层底层预制件、抗烧蚀层、第二绝热层底层预制件粘接，然后于模具中，通过热压罐硫化工艺制备得到绝热层底层；S4：采用整体一步硫化工艺成型绝热层盖层预制件；S5：在模具中放入绝热层底层和绝热层盖层预制件，通过热压罐硫化工艺成型，得到所述固体火箭发动机绝热层结构。该方法制得的绝热层结构，可保证各绝热层厚度要求，尺寸精确，产品质量显著提高。
The present invention provides a method for preparing a solid rocket engine thermal insulation layer structure, comprising the following steps: S1: prefabricate a first thermal insulation layer bottom layer prefabricated part by a molding method; connect the outer side of the first thermal insulation layer bottom layer prefabricated part with a metal joint; S2: prefabricate a second thermal insulation layer bottom layer prefabricated part by a molding method; S3: bond the first thermal insulation layer bottom layer prefabricated part, the anti-ablation layer, and the second thermal insulation layer bottom layer prefabricated part, and then prepare the thermal insulation layer bottom layer in a mold by a hot-press vulcanization process; S4: form a thermal insulation layer cover layer prefabricated part by an overall one-step vulcanization process; S5: place the thermal insulation layer bottom layer and the thermal insulation layer cover layer prefabricated part in the mold, and form them by a hot-press vulcanization process to obtain the thermal insulation layer structure of the solid rocket engine. The thermal insulation layer structure prepared by the method can ensure the thickness requirements of each thermal insulation layer, the size is accurate, and the product quality is significantly improved.
Description
Technical Field
The invention belongs to the technical field of solid rocket engine manufacturing, and particularly relates to a preparation method of a solid rocket engine heat insulation layer structure.
Background
When the rocket engine works, the combustion chamber needs to bear the scouring of high-temperature and high-pressure air flow with the temperature of more than 3000 ℃, so that a heat insulation layer needs to be arranged on the inner wall of the combustion chamber to protect the combustion chamber shell. Currently, to further enhance the anti-scour properties of the insulation, an anti-ablative layer is provided adjacent to the location of connection with the nozzle.
The molding method of the heat insulating layer of the solid rocket engine mainly comprises compression molding and manual patch molding, and Chinese patent CN112223781A discloses a molding process of a manual patch molding heat insulating bottom layer, wherein the manual patch molding product has poor surface quality, is easy to have defects of pits, bulges, air inclusion and the like, is easy to be corroded by hot air flow, and thus influences the heat protection performance.
The compression molding process is widely applied in the field of heat insulation layer preparation, at present, due to strategic requirements, the performances of different weaponry are higher and higher, higher and higher requirements are put forward on an engine, the engine structure is more and more complex, the compression molding process is limited by the size and the profile complexity of the heat insulation layer, and the traditional compression molding process can not meet the current heat insulation layer molding requirements. In order to prevent burning-through of the ablation-resistant layer upon ignition of the engine, it is necessary to coat the ablation-resistant layer within the insulating layer, and the thickness position of the ablation layer within the insulating layer also needs to be precisely controlled, because if the ablation layer is close to the inside or outside of the engine, the ablation-resistant layer may be burned-through in advance upon ignition, resulting in burning-through of the insulating layer structure. The existing preparation method of the heat insulating layer cannot ensure the accuracy of the depth of the ablation-resistant layer in the heat insulating layer after molding and the bonding reliability, and secondly, the compression molding process is limited by the matching degree of the size of the heat insulating layer and the size of a mold cavity, for example, the arrangement of a flash channel is unreasonable, and the quality of the opening of a molding part cannot be ensured.
Therefore, there is a need to provide a method for preparing a solid rocket motor insulation layer structure with excellent thermal protection performance.
Disclosure of Invention
The invention solves the technical problem of providing a preparation method of a solid rocket engine heat insulation layer structure, and aims to solve the problem of poor heat protection performance of the existing solid rocket engine heat insulation layer.
In order to solve the problems, the invention provides a preparation method of a solid rocket engine heat insulation layer structure, which comprises the following steps:
the solid rocket engine heat insulation layer structure comprises:
a first insulating layer bottom layer, the outer wall of the first insulating layer bottom layer being adapted to be connected to an engine housing;
The second heat insulation layer bottom layer is arranged on the inner side of the first heat insulation layer bottom layer and is connected with the first heat insulation layer bottom layer;
The anti-ablation layer is arranged between the first heat insulation layer bottom layer and the second heat insulation layer bottom layer and is positioned at one end of the first heat insulation layer bottom layer connected with the spray pipe;
the heat insulation layer cover layer is arranged on the inner side of the second heat insulation layer bottom layer and is connected with the second heat insulation layer bottom layer;
the metal joint is arranged on the outer side of the first heat insulation layer bottom layer and is positioned at one end of the first heat insulation layer bottom layer connected with the spray pipe;
the preparation method comprises the following steps:
s1, prefabricating a first heat insulation layer bottom layer by adopting a compression molding method according to the thickness of the selected first heat insulation layer bottom layer by using a film stock to obtain a first heat insulation layer bottom layer prefabricating member;
S2, prefabricating the bottom layer of the second heat insulation layer by adopting a compression molding method according to the thickness of the bottom layer of the selected second heat insulation layer by using a film stock to obtain a prefabricated part of the bottom layer of the second heat insulation layer;
S3, bonding the first heat-insulating layer bottom prefabricated member, the ablation-resistant layer and the second heat-insulating layer bottom prefabricated member, and then preparing the heat-insulating layer bottom layer in a mold through an autoclave vulcanization process;
S4, forming a prefabricated part of the heat insulation layer cover layer by adopting an integral one-step vulcanization process according to the thickness of the selected heat insulation layer cover layer by utilizing a film stock;
s5, placing a heat insulation layer bottom layer and a heat insulation layer cover layer prefabricated member in a die, and forming through an autoclave vulcanization process to obtain the solid rocket engine heat insulation layer structure.
Preferably, a joint protection layer is further arranged on the outer side of the metal joint, and the joint protection layer is connected with the metal joint.
The first heat insulation layer bottom layer, the second heat insulation layer bottom layer and the heat insulation layer cover layer are preferably made of heat insulation materials, wherein the heat insulation materials comprise a filler and a matrix, the filler is at least one of asbestos and silicon dioxide, and the matrix is at least one of nitrile rubber, styrene-butadiene rubber, ethylene propylene diene monomer rubber and silicone rubber.
Preferably, in the step S1, when the bottom layer of the first heat insulation layer is prefabricated by adopting a compression molding method, the vulcanization temperature is 85-95 ℃, and the heat is preserved for 110-130 min;
In the step S2, when the bottom layer of the second heat insulation layer is prefabricated by adopting a mould pressing method, the vulcanization temperature is 85-95 ℃, and the temperature is kept for 110-130 min;
Preferably, in the step S3, when the bottom layer of the heat insulation layer is prepared through an autoclave vulcanization process, the vulcanization temperature is 145-155 ℃, and the heat preservation is carried out for 110-130 min.
Preferably, in the step S4, when the heat insulation layer cover layer is prepared through an autoclave vulcanization process, the vulcanization temperature is 85-95 ℃, and the heat preservation is carried out for 110-130 min;
in the step S5, when the heat insulation layer structure is prepared through an autoclave vulcanization process, the vulcanization temperature is 145-155 ℃, and the heat is preserved for 110-130 min.
Preferably, step S3 further includes polishing the upper surface of the first thermal insulation bottom preform and the lower surface of the second thermal insulation bottom preform, and cleaning the surfaces with ethyl acetate before bonding the first thermal insulation bottom preform, the ablation-resistant layer, and the second thermal insulation bottom preform.
Preferably, step S5 further comprises, before the autoclave vulcanization process is performed, adhering a polytetrafluoroethylene tape to the position of the bonding edge between the second heat insulation layer and the heat insulation layer bottom layer connecting metal piece, so as to form an artificial debonding region.
Preferably, step S5 further comprises disposing a green sheet in the bonding region between the insulating layer bottom layer and the insulating layer cover layer prior to the autoclave curing process.
The method comprises the steps of carrying out sand blasting on the bonding surface of the metal joint, polishing the joint protection layer prefabricated member, coating an adhesive on the bonding surface of the metal joint and the bonding surface of the joint protection layer prefabricated member, and bonding the metal joint and the joint protection layer prefabricated member.
Compared with the prior art, the invention has the following beneficial effects:
According to the preparation method of the solid rocket engine heat insulation layer structure, the first heat insulation layer bottom layer and the second heat insulation layer bottom layer are prefabricated, the ablation-resistant layer is coated between the first heat insulation layer bottom layer and the second heat insulation layer bottom layer through the adhesive, the position fixing of the ablation-resistant layer is guaranteed, and meanwhile the bonding performance of the ablation-resistant layer and other interfaces is enhanced. The autoclave press vulcanization process can solve the problem that multiple vertical planes cannot be pressurized in the compression molding process, ensure the bonding quality, apply pressure perpendicular to the bonding surface to the bonding area in the compression molding process, and simultaneously prevent the heat insulation layer at the connecting metal part of the heat insulation layer bottom layer and the cover layer from being damaged due to overlarge pressure in the integral compression molding and compression process. The autoclave molding process can save the cost of a die male die, can mold a plurality of heat insulation layers at one time, can avoid energy loss caused by heat transfer of the die, shortens molding time and improves production efficiency.
According to the preparation method of the solid rocket engine heat insulation layer structure, the strip-shaped polytetrafluoroethylene tape (film) is found after the common high-temperature tape, the deglued cloth, the release paper and the polytetrafluoroethylene tape are compared, the film has good ductility and good viscosity, the operability in the sticking process is strong, unbalance phenomena such as wrinkles and air inclusion cannot occur, and the surface of the cover layer is prevented from being damaged by the pressed wrinkles in the integral forming process.
Drawings
FIG. 1 is a schematic illustration of a solid rocket motor insulation layer according to an embodiment of the present invention;
wherein the heat insulation layer comprises a first heat insulation layer bottom layer, a second heat insulation layer bottom layer, a 3-heat insulation layer cover layer, a 4-ablation resistant layer, a 5-joint protection layer, a 6-heat insulation layer bottom layer and a 7-metal joint.
Detailed Description
The technical solutions of the present invention will be clearly and completely described in conjunction with the embodiments of the present invention, and it is apparent that the described embodiments are only some embodiments of the present invention, not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
Example 1
As shown in fig. 1, a solid rocket engine insulation layer structure according to an embodiment of the present invention includes:
The first heat insulation layer bottom layer 1, the outer wall of the first heat insulation layer bottom layer 1 is suitable for being connected with the engine shell;
The second heat insulation layer bottom layer 2 is arranged on the inner side of the first heat insulation layer bottom layer 1 and is connected with the first heat insulation layer bottom layer 1;
The ablation resistant layer 4 is arranged between the first heat insulation layer bottom layer 1 and the second heat insulation layer bottom layer 2 and is positioned at one end of the first heat insulation layer bottom layer 1 connected with the spray pipe;
A heat insulating layer cover layer 3, wherein the heat insulating layer cover layer 3 is arranged on the inner side of the second heat insulating layer bottom layer 2 and is connected with the second heat insulating layer bottom layer 2;
And the metal joint 7 is arranged on the outer side of the first heat insulation layer bottom layer 1 and is positioned at one end of the first heat insulation layer bottom layer 1 connected with the spray pipe.
According to the solid rocket engine heat insulation layer structure, the heat insulation layer cover layer is arranged on the inner side and is contacted with the grain in operation, and is ablated firstly in the working process of the engine. The ablation resistant layer is arranged in the bottom layer near the spray pipe. The metal joint protection layer is adhered to the outer side of the metal piece. The heat insulating bottom layer is adhered to the shell material, and the heat insulating bottom layer and the heat insulating cover layer play a role in heat protection to protect the combustion chamber shell. The metal joint is arranged on the outer side of the bottom layer and used for reinforcing the opening of the sealing head, and the ignition device and the spray pipe assembly are installed.
The solid rocket engine heat insulation layer structure is prepared by a method combining a compression molding process and autoclave molding, and the molded bottom layer and the molded cover layer are stable in process, good in apparent quality and internal quality, can ensure the thickness requirement of each heat insulation layer, is accurate in size and remarkably improves the product quality.
In some embodiments, the outer side of the metal joint 7 is further provided with a joint protection layer 5, and the joint protection layer 5 is connected with the metal joint 7.
In some embodiments, the first heat insulating layer bottom layer, the second heat insulating layer bottom layer and the heat insulating layer cover layer are made of heat insulating materials, wherein the heat insulating materials comprise a filler and a matrix, the filler is at least one of asbestos and silicon dioxide, and the matrix is at least one of nitrile rubber, styrene-butadiene rubber, ethylene propylene diene monomer rubber and silicone rubber. The engine can also be made by adding carbon fiber or aramid fiber and other materials into epoxy resin or phenolic resin, has good heat insulation, ablation resistance, scouring resistance and other performances, and ensures that the engine can still reliably work for a long time after being ablated and scoured under high temperature and high pressure.
Example 2
The solid rocket engine heat insulation layer structure of the invention comprises:
The first heat insulation layer bottom layer 1, the outer wall of the first heat insulation layer bottom layer 1 is suitable for being connected with the engine shell;
The second heat insulation layer bottom layer 2 is arranged on the inner side of the first heat insulation layer bottom layer 1 and is connected with the first heat insulation layer bottom layer 1;
The ablation resistant layer 4 is arranged between the first heat insulation layer bottom layer 1 and the second heat insulation layer bottom layer 2 and is positioned at one end of the first heat insulation layer bottom layer 1 connected with the spray pipe;
A heat insulating layer cover layer 3, wherein the heat insulating layer cover layer 3 is arranged on the inner side of the second heat insulating layer bottom layer 2 and is connected with the second heat insulating layer bottom layer 2;
The metal joint 7 is arranged on the outer side of the first heat insulation layer bottom layer 1 and is positioned at one end of the first heat insulation layer bottom layer 1 connected with the spray pipe;
And the joint protection layer 5 is arranged outside the metal joint 7, and the joint protection layer 5 is connected with the metal joint 7.
The first heat insulating layer bottom layer, the second heat insulating layer bottom layer and the heat insulating layer cover layer are made of heat insulating materials, wherein the heat insulating materials comprise filler and a matrix, the filler is silicon dioxide, and the matrix is nitrile rubber.
The preparation method of the solid rocket engine heat insulation layer structure of the embodiment comprises the following steps:
1. According to the thickness requirements of all parts of the heat insulation layer, an open mill is used for grinding incoming materials into films with different thicknesses, in the grinding process, thin-pass and triangular packing operations are required to be carried out on raw materials, the uniformity and the compactness of the incoming materials are improved, and the calendaring effect of ethylene propylene diene monomer rubber is reduced through the triangular packing operations;
2. designing a cutting template according to the thickness and the size requirements of different parts of the heat insulation layer, and cutting raw material sheets with different specifications according to the cutting template;
3. In order to enhance the bonding performance between metal and heat insulating materials, sand blasting the bonding surface of a metal joint, polishing the joint protection layer prefabricated member, coating an adhesive on the bonding surface of a metal joint 7 and the bonding surface of the joint protection layer prefabricated member, bonding the metal joint 7 and the joint protection layer prefabricated member, and fixing the metal joint protection layer prefabricated member and the metal joint by using a holding ring and a clamp to form a metal joint assembly;
4. Laying heat-insulating raw films with different specifications on the metal joint according to the design of the laying material until the required thickness and weight are reached;
5. Prefabricating the first heat insulation layer bottom layer 1 by a compression molding method according to the thickness of the selected first heat insulation layer bottom layer 1, wherein the vulcanizing temperature is 90 ℃, and preserving heat for 120min to obtain a first heat insulation layer bottom layer prefabricated member;
6. prefabricating the second heat insulation layer bottom layer 2 by a compression molding method according to the thickness of the selected second heat insulation layer bottom layer 2, wherein the vulcanizing temperature is 90 ℃, and preserving heat for 120min to obtain a second heat insulation layer bottom layer prefabricated member;
7. Polishing the upper surface of the first heat-insulating bottom layer prefabricated member and the lower surface of the second heat-insulating bottom layer prefabricated member, cleaning the surfaces by ethyl acetate, enhancing the reliability of an adhesive interface, then brushing an adhesive, airing for 20min, arranging the adhesive on the surface of the ablation-resistant layer 4, the contact position of the upper surface of the first heat-insulating bottom layer prefabricated member and the ablation-resistant layer, and the contact position of the lower surface of the second heat-insulating bottom layer prefabricated member and the ablation-resistant layer 4, arranging the first heat-insulating bottom layer prefabricated member, the ablation-resistant layer 4 and the second heat-insulating bottom layer prefabricated member in a die in sequence, preparing the heat-insulating bottom layer 6 through an autoclave vulcanizing process, and keeping the temperature for 120min at 150 ℃;
8. according to the thickness of the selected heat-insulating layer cover layer 3, molding a heat-insulating layer cover layer prefabricated member by using a film stock and adopting an integral one-step vulcanization process, wherein the vulcanization temperature is 90 ℃, and the heat preservation is carried out for 120min;
9. A polytetrafluoroethylene tape is stuck at the position of the joint metal part of the second heat insulating layer bottom layer 2 to the joint edge of the heat insulating layer cover layer 3 to form an artificial debonding area, raw rubber sheets with the thickness of 0.4mm are stuck at the joint positions of the heat insulating layer bottom layer and the heat insulating layer cover layer to align the concentric circles of the heat insulating layer bottom layer and the heat insulating layer cover layer, the heat insulating layer bottom layer 6 and the heat insulating layer cover layer prefabricated parts are sequentially put into a mould, the heat insulating layer structure of the solid rocket engine is obtained through vulcanization molding by an autoclave, the vulcanization temperature is 150 ℃ and the heat insulating layer structure is preserved for 120min, in the pressurizing process, the pressure vertical to the joint surface can be applied to the joint area, meanwhile, the heat insulating layer at the joint metal part of the second heat insulating layer bottom layer and the cover layer in the whole mould pressing and pressurizing process can be prevented from being damaged due to overlarge pressure, the cost of a mould male mould can be saved, and a plurality of heat insulating layers can be molded at one time by the autoclave process, and the production efficiency is improved.
Example 3
The preparation method of the solid rocket engine heat insulation layer structure of the embodiment comprises the following steps:
1. According to the thickness requirements of all parts of the heat insulation layer, an open mill is used for grinding incoming materials into films with different thicknesses, in the grinding process, thin-pass and triangular packing operations are required to be carried out on raw materials, the uniformity and the compactness of the incoming materials are improved, and the calendaring effect of ethylene propylene diene monomer rubber is reduced through the triangular packing operations;
2. designing a cutting template according to the thickness and the size requirements of different parts of the heat insulation layer, and cutting raw material sheets with different specifications according to the cutting template;
3. In order to enhance the bonding performance between metal and heat insulating materials, sand blasting the bonding surface of a metal joint, polishing the joint protection layer prefabricated member, coating an adhesive on the bonding surface of a metal joint 7 and the bonding surface of the joint protection layer prefabricated member, bonding the metal joint 7 and the joint protection layer prefabricated member, and fixing the metal joint protection layer prefabricated member and the metal joint by using a holding ring and a clamp to form a metal joint assembly;
4. Laying heat-insulating raw films with different specifications on the metal joint according to the design of the laying material until the required thickness and weight are reached;
5. prefabricating the first heat insulation layer 1 by a compression molding method according to the thickness of the selected first heat insulation layer 1, wherein the vulcanizing temperature is 85 ℃, and the temperature is kept for 110 minutes to obtain a first heat insulation layer prefabrication member;
6. Prefabricating the second heat insulation layer bottom layer 2 by a compression molding method according to the thickness of the selected second heat insulation layer bottom layer 2, wherein the vulcanizing temperature is 85 ℃, and preserving heat for 110min to obtain a second heat insulation layer bottom layer prefabricated member;
7. Polishing the upper surface of the first heat-insulating bottom layer prefabricated member and the lower surface of the second heat-insulating bottom layer prefabricated member, cleaning the surfaces by ethyl acetate, enhancing the reliability of an adhesive interface, then brushing an adhesive, airing for 20min, arranging the adhesive on the surface of the ablation-resistant layer 4, the contact position of the upper surface of the first heat-insulating bottom layer prefabricated member and the ablation-resistant layer, and the contact position of the lower surface of the second heat-insulating bottom layer prefabricated member and the ablation-resistant layer 4, arranging the first heat-insulating bottom layer prefabricated member, the ablation-resistant layer 4 and the second heat-insulating bottom layer prefabricated member in a die in sequence, preparing the heat-insulating bottom layer 6 through an autoclave vulcanizing process, and keeping the temperature at 145 ℃ for 110min;
8. according to the thickness of the selected heat-insulating layer cover layer 3, molding a heat-insulating layer cover layer prefabricated member by using a film stock and adopting an integral one-step vulcanization process, wherein the vulcanization temperature is 85 ℃, and the heat preservation is carried out for 110 minutes;
9. And (3) sticking polytetrafluoroethylene adhesive tapes to the bonding edge position of the heat insulating layer cover layer 3 at the position of the connecting metal piece of the second heat insulating layer bottom layer 2 to form an artificial debonding area, sticking raw rubber sheets with the thickness of 0.3mm to the bonding position of the heat insulating layer bottom layer and the heat insulating layer, aligning the concentric circles of the heat insulating layer bottom layer and the heat insulating layer, sequentially putting the heat insulating layer bottom layer 6 and the heat insulating layer cover layer prefabricated member into a mould, vulcanizing and forming by an autoclave, keeping the vulcanizing temperature at 145 ℃ and preserving heat for 110min to obtain the heat insulating layer structure of the solid rocket engine.
Example 4
The preparation method of the solid rocket engine heat insulation layer structure of the embodiment comprises the following steps:
1. According to the thickness requirements of all parts of the heat insulation layer, an open mill is used for grinding incoming materials into films with different thicknesses, in the grinding process, thin-pass and triangular packing operations are required to be carried out on raw materials, the uniformity and the compactness of the incoming materials are improved, and the calendaring effect of ethylene propylene diene monomer rubber is reduced through the triangular packing operations;
2. designing a cutting template according to the thickness and the size requirements of different parts of the heat insulation layer, and cutting raw material sheets with different specifications according to the cutting template;
3. In order to enhance the bonding performance between metal and heat insulating materials, sand blasting the bonding surface of a metal joint, polishing the joint protection layer prefabricated member, coating an adhesive on the bonding surface of a metal joint 7 and the bonding surface of the joint protection layer prefabricated member, bonding the metal joint 7 and the joint protection layer prefabricated member, and fixing the metal joint protection layer prefabricated member and the metal joint by using a holding ring and a clamp to form a metal joint assembly;
4. Laying heat-insulating raw films with different specifications on the metal joint according to the design of the laying material until the required thickness and weight are reached;
5. prefabricating the first heat insulation layer 1 by a compression molding method according to the thickness of the selected first heat insulation layer 1, wherein the vulcanizing temperature is 95 ℃, and preserving heat for 130min to obtain a first heat insulation layer prefabrication member;
6. prefabricating the second heat insulation layer bottom layer 2 by a compression molding method according to the thickness of the selected second heat insulation layer bottom layer 2, wherein the vulcanizing temperature is 95 ℃, and the heat preservation is carried out for 130min to obtain a second heat insulation layer bottom layer prefabricated member;
7. Polishing the upper surface of the first heat-insulating bottom layer prefabricated member and the lower surface of the second heat-insulating bottom layer prefabricated member, cleaning the surfaces by ethyl acetate, enhancing the reliability of an adhesive interface, then brushing an adhesive, airing for 20min, arranging the adhesive on the surface of the ablation-resistant layer 4, the contact position of the upper surface of the first heat-insulating bottom layer prefabricated member and the ablation-resistant layer, and the contact position of the lower surface of the second heat-insulating bottom layer prefabricated member and the ablation-resistant layer 4, arranging the first heat-insulating bottom layer prefabricated member, the ablation-resistant layer 4 and the second heat-insulating bottom layer prefabricated member in a die in sequence, preparing the heat-insulating bottom layer 6 through an autoclave vulcanizing process, and keeping the temperature at 155 ℃ for 130min;
8. according to the thickness of the selected heat-insulating layer cover layer 3, molding a heat-insulating layer cover layer prefabricated member by using a film stock and adopting an integral one-step vulcanization process, wherein the vulcanization temperature is 95 ℃, and the heat preservation is carried out for 130min;
9. And (3) sticking polytetrafluoroethylene adhesive tapes to the bonding edge position of the heat insulating layer cover layer 3 at the position of the connecting metal piece of the second heat insulating layer bottom layer 2 to form an artificial debonding area, sticking raw rubber sheets with the thickness of 0.3mm to the bonding position of the heat insulating layer bottom layer and the heat insulating layer, aligning the concentric circles of the heat insulating layer bottom layer and the heat insulating layer, sequentially placing the heat insulating layer bottom layer 6 and the heat insulating layer cover layer prefabricated member in a mould, vulcanizing and forming by an autoclave, keeping the vulcanization temperature at 155 ℃ and preserving heat for 130min to obtain the heat insulating layer structure of the solid rocket engine.
Comparative example 1
The comparative example is different from example 2 in that a polytetrafluoroethylene tape is not stuck to the bonding edge of the artificial release layer at the position where the metal member is connected to the bottom layer of the second heat insulating layer, but a high-temperature tape is provided as the artificial release layer.
Comparative example 2
The difference between the comparative example and the example 2 is that the preparation of the bottom layer of the heat insulation layer is different, the bottom layer of the heat insulation layer is not divided into an upper layer and a lower layer which are respectively prefabricated, but directly paved, and the bottom layer of the heat insulation layer is formed in one step, namely, the preparation of the bottom layer of the heat insulation layer is realized by directly paving a raw rubber sheet in a mould until the thickness is set, then placing an anti-ablation layer, paving the raw rubber sheet on the anti-ablation layer until the thickness of the heat insulation layer is selected, and preparing the bottom layer of the heat insulation layer through an autoclave vulcanization process. The remaining steps were the same as in example 2.
The ablative properties and strength properties of the heat insulating layer structures obtained in examples 2, 3 and 4 and comparative examples 1 and 2 were measured, the positions of the ablative layers in the heat insulating layers were measured, and the deviation values of the positions from the predetermined positions were calculated. The test results are shown in table 1 below.
As can be seen from the data in table 1 below, compared with comparative example 2, the heat insulating layer prepared in each example of the present invention has significantly better ablation performance and strength performance, and more importantly, the position of the ablation resistant layer in the heat insulating layer after molding is more accurate and the position deviation is smaller. Compared with the comparative example 1, which adopts a high-temperature adhesive tape to make an artificial release layer, the invention adopts a polytetrafluoroethylene adhesive tape, and discovers that the strip polytetrafluoroethylene adhesive tape (film) has good ductility and good viscosity, has strong operability in the pasting process, does not have unbalance phenomena such as wrinkles, air inclusion and the like, and avoids the damage to the surface of the cover layer caused by the pressed wrinkles in the integral forming process;
TABLE 1
It is apparent that the above examples are given by way of illustration only and are not limiting of the embodiments. Other variations or modifications of the above teachings will be apparent to those of ordinary skill in the art. It is not necessary here nor is it exhaustive of all embodiments. While still being apparent from variations or modifications that may be made by those skilled in the art are within the scope of the invention.
Claims (10)
1. A preparation method of a solid rocket engine heat insulation layer structure is characterized by comprising the following steps:
the solid rocket engine heat insulation layer structure comprises:
a first insulating layer bottom layer, the outer wall of the first insulating layer bottom layer being adapted to be connected to an engine housing;
The second heat insulation layer bottom layer is arranged on the inner side of the first heat insulation layer bottom layer and is connected with the first heat insulation layer bottom layer;
The anti-ablation layer is arranged between the first heat insulation layer bottom layer and the second heat insulation layer bottom layer and is positioned at one end of the first heat insulation layer bottom layer connected with the spray pipe;
the heat insulation layer cover layer is arranged on the inner side of the second heat insulation layer bottom layer and is connected with the second heat insulation layer bottom layer;
the metal joint is arranged on the outer side of the first heat insulation layer bottom layer and is positioned at one end of the first heat insulation layer bottom layer connected with the spray pipe;
the preparation method comprises the following steps:
s1, prefabricating a first heat insulation layer bottom layer by adopting a compression molding method according to the thickness of the selected first heat insulation layer bottom layer by using a film stock to obtain a first heat insulation layer bottom layer prefabricating member;
S2, prefabricating the bottom layer of the second heat insulation layer by adopting a compression molding method according to the thickness of the bottom layer of the selected second heat insulation layer by using a film stock to obtain a prefabricated part of the bottom layer of the second heat insulation layer;
S3, bonding the first heat-insulating layer bottom prefabricated member, the ablation-resistant layer and the second heat-insulating layer bottom prefabricated member, and then preparing the heat-insulating layer bottom layer in a mold through an autoclave vulcanization process;
S4, forming a prefabricated part of the heat insulation layer cover layer by adopting an integral one-step vulcanization process according to the thickness of the selected heat insulation layer cover layer by utilizing a film stock;
s5, placing a heat insulation layer bottom layer and a heat insulation layer cover layer prefabricated member in a die, and forming through an autoclave vulcanization process to obtain the solid rocket engine heat insulation layer structure.
2. The method for preparing a solid rocket engine insulating layer structure according to claim 1, wherein:
And the outer side of the metal joint is also provided with a joint protection layer, and the joint protection layer is connected with the metal joint.
3. The method for preparing a solid rocket engine insulating layer structure according to claim 1, wherein:
the first heat insulation layer bottom layer, the second heat insulation layer bottom layer and the heat insulation layer cover layer are made of heat insulation materials;
The heat insulation material comprises a filler and a matrix, wherein the filler is at least one of asbestos and silicon dioxide, and the matrix is at least one of nitrile rubber, styrene-butadiene rubber, ethylene propylene diene monomer rubber and silicone rubber.
4. The method for preparing a solid rocket engine insulating layer structure according to claim 1, wherein:
in the step S1, when the bottom layer of the first heat insulation layer is prefabricated by adopting a mould pressing method, the vulcanization temperature is 85-95 ℃, and the temperature is kept for 110-130 min;
in the step S2, when the bottom layer of the second heat insulation layer is prefabricated by adopting a mould pressing method, the vulcanization temperature is 85-95 ℃, and the temperature is kept for 110-130 min.
5. The method for preparing a solid rocket engine insulating layer structure according to claim 1, wherein:
In the step S3, when the bottom layer of the heat insulation layer is prepared through an autoclave vulcanization process, the vulcanization temperature is 145-155 ℃, and the heat is preserved for 110-130 min.
6. The method for preparing a solid rocket engine insulating layer structure according to claim 1, wherein:
In the step S4, when the heat insulation layer is prepared through an autoclave vulcanization process, the vulcanization temperature is 85-95 ℃, and the heat is preserved for 110-130 min;
in the step S5, when the heat insulation layer structure is prepared through an autoclave vulcanization process, the vulcanization temperature is 145-155 ℃, and the heat is preserved for 110-130 min.
7. The method for manufacturing a solid rocket engine insulating layer structure according to claim 1, wherein;
and step S3, before bonding the first heat-insulating layer bottom prefabricated member, the ablation-resistant layer and the second heat-insulating layer bottom prefabricated member, polishing the upper surface of the first heat-insulating layer bottom prefabricated member and the lower surface of the second heat-insulating layer bottom prefabricated member, and cleaning the surfaces by using ethyl acetate.
8. The method for preparing a solid rocket engine insulating layer structure according to claim 1, wherein:
And step S5, before the vulcanization process of the autoclave is carried out, a polytetrafluoroethylene tape is stuck to the position of the bonding edge of the second heat insulation layer bottom layer connecting metal piece and the heat insulation layer cover layer to form an artificial debonding area.
9. The method for preparing a solid rocket engine insulating layer structure according to claim 1, wherein:
Step S5 further includes disposing a green sheet in the bonding area between the bottom layer of the thermal insulation layer and the cover layer of the thermal insulation layer prior to shaping by the autoclave curing process.
10. The method for preparing a solid rocket engine insulating layer structure according to claim 1, wherein:
The method comprises the steps of carrying out sand blasting on the bonding surface of the metal joint, polishing the joint protection layer prefabricated member, coating an adhesive on the bonding surface of the metal joint and the bonding surface of the joint protection layer prefabricated member, and bonding the metal joint and the joint protection layer prefabricated member.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202411786266.3A CN119261233A (en) | 2024-12-06 | 2024-12-06 | A method for preparing a thermal insulation layer structure of a solid rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202411786266.3A CN119261233A (en) | 2024-12-06 | 2024-12-06 | A method for preparing a thermal insulation layer structure of a solid rocket engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN119261233A true CN119261233A (en) | 2025-01-07 |
Family
ID=94125182
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202411786266.3A Pending CN119261233A (en) | 2024-12-06 | 2024-12-06 | A method for preparing a thermal insulation layer structure of a solid rocket engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN119261233A (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104703782A (en) * | 2012-10-04 | 2015-06-10 | 波音公司 | Method and apparatus for co-curing composite skins and stiffeners in an autoclave |
| CN111516196A (en) * | 2020-04-10 | 2020-08-11 | 北京玻钢院复合材料有限公司 | Composite material solid rocket engine heat insulation layer structure and preparation method thereof |
| CN114131802A (en) * | 2021-11-23 | 2022-03-04 | 中国直升机设计研究所 | Processing method of U-shaped thin-wall bonding structure |
| CN115384083A (en) * | 2022-09-13 | 2022-11-25 | 江苏新扬新材料股份有限公司 | Method for manufacturing full-opening composite material shell |
| CN115583057A (en) * | 2022-10-26 | 2023-01-10 | 江苏新扬新材料股份有限公司 | Method for forming heat-insulating end socket of scouring-resistant engine shell |
| CN118418477A (en) * | 2024-05-29 | 2024-08-02 | 北京玻钢院复合材料有限公司 | Composite forming method of fiber-wound engine seal head heat insulation layer |
| CN118438706A (en) * | 2024-04-30 | 2024-08-06 | 威海光晟航天航空科技有限公司 | Method for repairing R-angle defect of heat insulation structure of composite material engine shell |
-
2024
- 2024-12-06 CN CN202411786266.3A patent/CN119261233A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104703782A (en) * | 2012-10-04 | 2015-06-10 | 波音公司 | Method and apparatus for co-curing composite skins and stiffeners in an autoclave |
| CN111516196A (en) * | 2020-04-10 | 2020-08-11 | 北京玻钢院复合材料有限公司 | Composite material solid rocket engine heat insulation layer structure and preparation method thereof |
| CN114131802A (en) * | 2021-11-23 | 2022-03-04 | 中国直升机设计研究所 | Processing method of U-shaped thin-wall bonding structure |
| CN115384083A (en) * | 2022-09-13 | 2022-11-25 | 江苏新扬新材料股份有限公司 | Method for manufacturing full-opening composite material shell |
| CN115583057A (en) * | 2022-10-26 | 2023-01-10 | 江苏新扬新材料股份有限公司 | Method for forming heat-insulating end socket of scouring-resistant engine shell |
| CN118438706A (en) * | 2024-04-30 | 2024-08-06 | 威海光晟航天航空科技有限公司 | Method for repairing R-angle defect of heat insulation structure of composite material engine shell |
| CN118418477A (en) * | 2024-05-29 | 2024-08-02 | 北京玻钢院复合材料有限公司 | Composite forming method of fiber-wound engine seal head heat insulation layer |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111516196B (en) | Composite material solid rocket engine heat insulation layer structure and preparation method thereof | |
| CN112497587B (en) | Method for forming heat insulating layer of fiber-wound engine end socket | |
| CN110481059B (en) | A composite foam sandwich structure and its forming method | |
| CN105437521A (en) | Seal head heat insulating layer forming method and mold of filament winding engine heat insulating structure | |
| CN102285059B (en) | Molding method and mold used in resin transfer molding technology of cable rectifying cover | |
| CN112297462A (en) | Manufacturing method of rocket engine full composite material shell | |
| CN109605625B (en) | Method for forming heat insulation layer of solid rocket engine combustion chamber shell | |
| CN115898695B (en) | Heat insulation layer structure of combustion chamber of solid rocket engine and bonding method thereof | |
| CN116834395B (en) | Ablation-resistant heat-insulating composite heat-insulating layer structure and forming method | |
| CN115583057A (en) | Method for forming heat-insulating end socket of scouring-resistant engine shell | |
| CN119261233A (en) | A method for preparing a thermal insulation layer structure of a solid rocket engine | |
| CN112277209B (en) | Forming method for repairing process of fiber-wound engine shell body model | |
| CN215242964U (en) | Vacuum bonding solidification forming device | |
| CN112743880B (en) | Repairing method for large-area damage of honeycomb sandwich structural member | |
| CN113775437B (en) | Composite material solid rocket engine heat insulation structure and forming method | |
| CN114179392B (en) | Forming method of large-size seal head heat insulation layer | |
| CN112606380B (en) | Method for forming thermal protection layer of spray pipe | |
| CN112223781B (en) | Method for sticking heat-insulating layer of large-diameter and large-thickness end socket of fiber-wound shell of solid rocket engine | |
| CN112223793B (en) | Method for repairing delamination defect of fiber winding engine shell interface | |
| CN114179393B (en) | Forming method of filament wound engine seal head autoclave | |
| CN110228214B (en) | Rapid forming method of continuous fiber reinforced plastic automobile part | |
| CN114346396A (en) | A kind of double-layer flap wall plate superplastic forming diffusion connection die and method | |
| CN112659597A (en) | Material shortage repairing method for ethylene propylene diene monomer molded part | |
| CN115556386A (en) | Integral molding method for heat insulation layer of composite material engine shell | |
| CN117774377A (en) | Integrated forming method of heat-insulating seal head with cover layer |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |