CN114571649B - Method for rapidly pressing heat-proof product formed by integrally forming heat-proof layer with metal piece and large length-diameter ratio for aerospace vehicle and heat-proof product formed by integrally forming heat-proof layer with metal piece - Google Patents
Method for rapidly pressing heat-proof product formed by integrally forming heat-proof layer with metal piece and large length-diameter ratio for aerospace vehicle and heat-proof product formed by integrally forming heat-proof layer with metal piece Download PDFInfo
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- CN114571649B CN114571649B CN202210237608.0A CN202210237608A CN114571649B CN 114571649 B CN114571649 B CN 114571649B CN 202210237608 A CN202210237608 A CN 202210237608A CN 114571649 B CN114571649 B CN 114571649B
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- heat
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- proof
- premix
- pressing
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- 229910052751 metal Inorganic materials 0.000 title claims abstract description 111
- 239000002184 metal Substances 0.000 title claims abstract description 111
- 238000003825 pressing Methods 0.000 title claims abstract description 49
- 238000000034 method Methods 0.000 title claims abstract description 26
- 238000001816 cooling Methods 0.000 claims abstract description 50
- 238000005192 partition Methods 0.000 claims abstract description 8
- 238000000638 solvent extraction Methods 0.000 claims abstract description 4
- KXGFMDJXCMQABM-UHFFFAOYSA-N 2-methoxy-6-methylphenol Chemical compound [CH]OC1=CC=CC([CH])=C1O KXGFMDJXCMQABM-UHFFFAOYSA-N 0.000 claims description 26
- 239000005011 phenolic resin Substances 0.000 claims description 26
- 229920001568 phenolic resin Polymers 0.000 claims description 26
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 20
- QGZKDVFQNNGYKY-UHFFFAOYSA-N Ammonia Chemical compound N QGZKDVFQNNGYKY-UHFFFAOYSA-N 0.000 claims description 14
- 238000002360 preparation method Methods 0.000 claims description 12
- 238000005488 sandblasting Methods 0.000 claims description 12
- 239000012779 reinforcing material Substances 0.000 claims description 10
- 239000000835 fiber Substances 0.000 claims description 9
- 229910021529 ammonia Inorganic materials 0.000 claims description 7
- 239000006004 Quartz sand Substances 0.000 claims description 6
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 claims description 5
- 229910052749 magnesium Inorganic materials 0.000 claims description 5
- 239000011777 magnesium Substances 0.000 claims description 5
- 239000000377 silicon dioxide Substances 0.000 claims description 5
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 claims description 4
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 4
- 229910052796 boron Inorganic materials 0.000 claims description 4
- 239000004917 carbon fiber Substances 0.000 claims description 4
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 4
- 239000010453 quartz Substances 0.000 claims description 4
- 239000003365 glass fiber Substances 0.000 claims description 3
- 238000004321 preservation Methods 0.000 claims description 3
- 230000006835 compression Effects 0.000 claims 1
- 238000007906 compression Methods 0.000 claims 1
- 238000004519 manufacturing process Methods 0.000 abstract description 6
- 239000000047 product Substances 0.000 description 43
- 238000001514 detection method Methods 0.000 description 7
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 7
- 239000000203 mixture Substances 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 2
- 238000007723 die pressing method Methods 0.000 description 2
- 239000012467 final product Substances 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 1
- 238000000354 decomposition reaction Methods 0.000 description 1
- 238000001704 evaporation Methods 0.000 description 1
- 230000008020 evaporation Effects 0.000 description 1
- 239000003779 heat-resistant material Substances 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- ISWSIDIOOBJBQZ-UHFFFAOYSA-N phenol group Chemical group C1(=CC=CC=C1)O ISWSIDIOOBJBQZ-UHFFFAOYSA-N 0.000 description 1
- 238000009991 scouring Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- 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
- B29C43/00—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor
- B29C43/003—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor characterised by the choice of material
-
- 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
- B29C43/00—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor
- B29C43/02—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor of articles of definite length, i.e. discrete articles
- B29C43/18—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor of articles of definite length, i.e. discrete articles incorporating preformed parts or layers, e.g. compression moulding around inserts or for coating articles
-
- 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
- B29C43/00—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor
- B29C43/32—Component parts, details or accessories; Auxiliary operations
-
- 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
- B29C43/00—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor
- B29C43/32—Component parts, details or accessories; Auxiliary operations
- B29C43/52—Heating or cooling
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
- B29K2061/00—Use of condensation polymers of aldehydes or ketones or derivatives thereof, as moulding material
- B29K2061/04—Phenoplasts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
- B29K2505/00—Use of metals, their alloys or their compounds, as filler
-
- 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
Abstract
The invention relates to a rapid pressing method of a heat-proof product formed by integrating a heat-proof layer with a large length-diameter ratio and a metal piece for an aerospace vehicle; partitioning according to the preset thickness of the heat-resistant layer, and calculating the weight of premix charges in different partitions of the heat-resistant layer; after the front surface of the metal piece is sandblasted, the metal piece is placed into a lower die, the lower die and the metal piece are preheated, a filling tool is used for filling premix, the premix is filled in different partitions corresponding to the filling tool and preheated, the preheated premix is filled into the lower die, and a preheated upper die is used for pressing and demolding to obtain a prefabricated member; placing the prefabricated member in an oven, preserving heat, and cooling to room temperature in a step manner to obtain a heat-proof product formed by integrating the heat-proof layer and the metal piece; the steps can solve the technical problems that the heat-proof layer and the metal piece in the prior art are independently formed and then are adhered to the metal piece, the process is complicated, and the production efficiency is low.
Description
Technical Field
The invention relates to the technical field of preparation of heat-resistant products, in particular to a rapid pressing method of a heat-resistant product formed by integrally forming a large-length-diameter-ratio heat-resistant layer and a metal piece for an aerospace vehicle and the product.
Background
When the aerospace vehicle reenters the atmosphere, the aerospace vehicle can generate sharp friction with air, the surface is required to bear the scouring of high-temperature and high-speed airflow at thousands of degrees, and in order to protect the aerospace vehicle from being burnt, a layer of special heat-resistant material is required to be used for protecting the surface.
In order to alleviate the high temperature transmission damage components generated by the severe friction between the aircraft and the air during the rapid flight, a heat-proof layer needs to be prepared on the surface of the aircraft. Phenolic material is a common heat-proof material, and under the action of heat flow, various heat-absorbing and heat-dissipating physical and chemical changes such as decomposition, melting, evaporation and the like occur, so that a large amount of heat energy is taken away by self mass consumption, and the heat is prevented from being transferred into metal pieces, thereby ensuring the normal work of the metal pieces. The heat-proof layer and the metal piece are prepared in a mode that the heat-proof layer is formed independently and then is bonded with the metal piece, the process is complex, labor and time are wasted, and production efficiency is low.
Therefore, in order to solve the above-mentioned problems, the present invention is needed to provide a method for rapidly pressing a heat-resistant product formed by integrally forming a heat-resistant layer with a metal member for an aerospace vehicle and a product thereof.
Disclosure of Invention
The invention aims to provide a rapid pressing method for a heat-proof product formed by integrating a heat-proof layer with a metal piece with a large length-diameter ratio and a product thereof, which are used for solving the technical problems of complicated process, labor and time consumption and lower production efficiency in the prior art that the heat-proof layer of an aerospace vehicle and the metal piece are independently formed by adopting the heat-proof layer and then are adhered to the metal piece.
The invention provides a rapid pressing method of a heat-proof product formed by integrating a heat-proof layer with a large length-diameter ratio and a metal piece for an aerospace vehicle, which comprises the following preparation steps:
preparing a pressing die, wherein the pressing die comprises an upper die and a lower die, the upper surface of the lower die is consistent with the appearance surface of a metal piece, and the cambered surface radius of the lower surface of the upper die is 92mm-96mm;
partitioning according to the preset thickness of the heat-resistant layer, and calculating the weight of premix charges in different partitions of the heat-resistant layer;
after the front surface of the metal piece is sandblasted, the front surface of the metal piece is placed into a lower die, the lower die and the metal piece are preheated, a filling tool is used for filling premix, the premix is filled in different partitions corresponding to the filling tool and preheated, the preheated premix is filled into the lower die, and a preheated upper die is used for pressing and demolding to obtain a prefabricated member;
and placing the prefabricated part in an oven, preserving heat, and cooling to room temperature in a step manner to obtain the heat-proof product formed by the heat-proof layer and the metal piece in an integrated manner.
Preferably, the metal piece is a flat plate, a strip-shaped arc plate or a profiled plate.
Preferably, 50-80 mesh quartz sand is adopted for sand blasting; the sand blasting pressure is 0.6+/-0.2 MPa.
Preferably, the preheating temperature of the upper die and the lower die is 175+/-10 ℃, and the heat preservation time is more than or equal to 30 minutes.
Preferably, the preheating temperature of the metal piece is 175+/-10 ℃ and the preheating time is 20-30min.
Preferably, the premix is phenolic resin and reinforcing material, the preheating temperature of the premix is 90+/-5 ℃, and the premix is preheated for 20-30min.
Preferably, the phenolic resin is one or two of ammonia phenolic resin, magnesium phenolic resin and boron phenolic resin; the reinforcing material is one of high silica fiber, quartz fiber, alkali-free glass fiber or carbon fiber.
Preferably, the upper die pressing pressure is 10-15MPa/m 2 Pressing at 175+ -10deg.C, maintaining the temperature for 20-35min, and demoulding at 175+ -10deg.C to obtain the final product.
Preferably, the prefabricated part is placed in an oven, and the temperature is kept for 120-240min at 175+/-10 ℃; cooling to 120 ℃, preserving heat for 60-120min, wherein the cooling speed is 20-40 ℃/h; cooling to 80 ℃, preserving heat for 60min, wherein the cooling speed is 20-40 ℃/h; cooling to room temperature.
The invention also provides a product obtained by the rapid pressing method of the integrated heat-proof product based on the large-length-diameter-ratio heat-proof layer and the metal piece for the aerospace vehicle, which comprises the metal piece, and the heat-proof layer is added on the metal piece.
Compared with the prior art, the rapid pressing method of the integrated heat-proof product of the large-length-diameter-ratio heat-proof layer and the metal piece for the aerospace vehicle has the following steps:
1. the rapid pressing method for the integrated heat-proof product of the large-length-diameter-ratio heat-proof layer and the metal piece of the aerospace vehicle can realize the integrated formation of the heat-proof layer and the metal piece and ensure the thickness uniformity of the partitioned heat-proof layer.
2. According to the rapid pressing method for the integrated heat-resistant product of the large-length-diameter-ratio heat-resistant layer and the metal piece for the aerospace vehicle, which is provided by the invention, the influence of the difference of the linear expansion coefficients of the heat-resistant layer and the metal piece is weakened by adopting a gradient cooling mode, and the phenomenon of interface debonding caused by the fact that the cooling rate is too high is avoided.
3. The rapid pressing method for the integrated heat-proof product of the large-length-diameter-ratio heat-proof layer and the metal piece of the aerospace vehicle improves the production efficiency of the product, has strong binding force between the heat-proof layer and the metal piece, good interface bonding quality and high internal quality of the heat-proof layer, does not need to increase too much cost, has good application prospect, and is beneficial to popularization and implementation.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are needed in the description of the embodiments or the prior art will be briefly described, and it is obvious that the drawings in the description below are some embodiments of the present invention, and other drawings can be obtained according to the drawings without inventive effort for a person skilled in the art.
Fig. 1 is a schematic structural view (perspective view) of the metal member and the heat-resistant layer according to the present invention.
Reference numerals illustrate:
1. a metal piece; 2. and a heat-resistant layer.
Detailed Description
The following description of the embodiments of the present invention will be made apparent and fully in view of the accompanying drawings, in which some, but not all embodiments of the invention are shown. 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.
In the description of the present invention, it should be noted that the directions or positional relationships indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, are merely for convenience of describing the present invention and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should be noted that, unless explicitly specified and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be either fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
The invention provides a rapid pressing method of a heat-proof product formed by integrating a large-length-diameter-ratio heat-proof layer and a metal piece of an aerospace vehicle, which comprises the following preparation steps:
s1) preparing a pressing die, wherein the pressing die comprises an upper die and a lower die, the upper surface of the lower die is consistent with the appearance surface of a metal piece, and the radius of an arc surface of the lower surface of the upper die is 92mm-96mm;
s2) partitioning according to the preset thickness of the heat-resistant layer, and calculating the weight of premix charges in different partitions of the heat-resistant layer;
s3) after the front surface of the metal piece is sandblasted, the front surface of the metal piece is placed into a lower die, the lower die and the metal piece are preheated, a filling tool is used for filling premix, the premix is filled in different partitions corresponding to the filling tool and preheated, the preheated premix is filled into the lower die, and a preheated upper die is used for pressing and demolding to obtain a prefabricated member;
s4) placing the prefabricated member in an oven, preserving heat, and cooling to room temperature in a step manner to obtain the heat-proof product formed by the heat-proof layer and the metal piece in an integrated manner.
According to the rapid pressing method for the integrated heat-proof product of the large-length-diameter-ratio heat-proof layer and the metal piece of the aerospace vehicle, which is provided by the invention, through the steps, the integrated formation of the heat-proof layer and the metal piece can be realized, and the thickness uniformity of the partitioned heat-proof layer is ensured.
According to the rapid pressing method for the integrated heat-resistant product of the large-length-diameter-ratio heat-resistant layer and the metal piece for the aerospace vehicle, which is provided by the invention, the influence of the difference of the linear expansion coefficients of the heat-resistant layer and the metal piece is weakened by adopting a gradient cooling mode, and the phenomenon of interface debonding caused by the fact that the cooling rate is too high is avoided.
The rapid pressing method for the integrated heat-proof product of the large-length-diameter-ratio heat-proof layer and the metal piece of the aerospace vehicle improves the production efficiency of the product, has strong binding force between the heat-proof layer and the metal piece, good interface bonding quality and high internal quality of the heat-proof layer, does not need to increase too much cost, has good application prospect, and is beneficial to popularization and implementation.
Specifically, the metal piece is a flat plate, a strip-shaped arc plate or a special-shaped plate, and the method is not limited by the shape of the metal piece and improves the production efficiency.
Specifically, sand blasting is carried out by adopting 50-80 mesh quartz sand; the sand blasting pressure is 0.6+/-0.2 MPa.
Specifically, the preheating temperature of the upper die and the lower die is 175+/-10 ℃, and the heat preservation time is more than or equal to 30 minutes.
Specifically, the preheating temperature of the metal piece is 175+/-10 ℃ and the preheating time is 20-30min.
Specifically, the premix is phenolic resin and reinforcing material, the preheating temperature of the premix is 90+/-5 ℃, and the premix is preheated for 20-30min.
Specifically, the phenolic resin is one or two of ammonia phenolic resin, magnesium phenolic resin and boron phenolic resin; the reinforcing material is one of high silica fiber, quartz fiber, alkali-free glass fiber or carbon fiber.
Specifically, the upper die pressing pressure is 10-15MPa/m 2 Pressing at 175+ -10deg.C, maintaining the temperature for 20-35min, and demoulding at 175+ -10deg.C to obtain the final product.
Specifically, placing the prefabricated member in an oven, and preserving heat for 120-240min at 175+/-10 ℃; cooling to 120 ℃, preserving heat for 60-120min, wherein the cooling speed is 20-40 ℃/h; cooling to 80 ℃, preserving heat for 60min, wherein the cooling speed is 20-40 ℃/h; cooling to room temperature.
As shown in fig. 1, the present embodiment provides a product obtained by a method for rapidly pressing a heat-resistant product formed by integrally forming a heat-resistant layer with a metal piece on the basis of the large-length-diameter-ratio heat-resistant layer for an aerospace vehicle according to any one of the above embodiments, which comprises a metal piece 1, wherein the heat-resistant layer 2 is added on the metal piece 1.
Example 1
The preparation process of the integrated heat-resistant product of the large length-diameter ratio heat-resistant layer and the metal piece for the aerospace vehicle comprises the following steps:
s1) preparing a pressing die, wherein the pressing die comprises an upper die and a lower die, the upper surface of the lower die is consistent with the appearance surface of a metal piece, and the radius of an arc surface of the lower surface of the upper die is 92mm;
s2) dividing into 4 areas according to the preset thickness of the heat-resistant layer, wherein the charging amount of the premix is respectively 37g, 53g, 30g and 87g;
s3) after the front surface of the metal piece is sandblasted, the front surface of the metal piece is placed into a lower die, the lower die and the metal piece are preheated, the preheating temperature is 175 ℃, the preheating is carried out for 20 minutes, a filling tool is used for filling premix, the premix is filled in different areas corresponding to the filling tool and is preheated, the preheated premix is filled into the lower die, the unit area of the preheated upper die is 10MPa, and the pressing pressure is 175 ℃. Preserving heat for 20min, and demolding to obtain a prefabricated member;
s4) placing the prefabricated member in an oven, preserving heat, and cooling to room temperature in a step manner to obtain the heat-proof product formed by the heat-proof layer and the metal piece in an integrated manner.
Wherein, 50-80 mesh quartz sand is used for sand blasting; the sand blasting pressure was 0.6MPa.
The preheating temperature of the premix is 90 ℃, and the premix is preheated for 20min;
placing the prefabricated part in an oven, and preserving heat for 240min at 175 ℃ in a step cooling process; cooling to 120 ℃, preserving heat for 60min, wherein the cooling speed is 20 ℃/h; cooling to 80 ℃, preserving heat for 60min, wherein the cooling speed is 40 ℃/h; cooling to room temperature;
specifically, the phenolic resin is a mixture of ammonia phenolic resin and magnesium phenolic resin; the reinforcing material is high silica fiber.
The method is used for carrying out water ultrasonic detection on the heat-proof product formed by the heat-proof layer with the large length-diameter ratio and the metal piece integrally, and the result shows that: the interface between the metal piece and the heat-proof layer has no debonding phenomenon.
Example two
The preparation process of the integrated heat-resistant product of the large length-diameter ratio heat-resistant layer and the metal piece for the aerospace vehicle comprises the following steps:
s1) preparing a pressing die, wherein the pressing die comprises an upper die and a lower die, the upper surface of the lower die is consistent with the appearance surface of a metal piece, and the radius of an arc surface of the lower surface of the upper die is 92mm;
s2) dividing into 4 areas according to the preset thickness of the heat-resistant layer, wherein the charging amount of the premix is respectively 37g, 53g, 30g and 87g;
s3) after the front surface of the metal piece is sandblasted, the front surface of the metal piece is placed into a lower die, the lower die and the metal piece are preheated, the preheating temperature is 175 ℃, the preheating is carried out for 20 minutes, a filling tool is used for filling premix, the premix is filled in different areas corresponding to the filling tool and is preheated, the preheated premix is filled into the lower die, the unit area of the preheated upper die is 10MPa, and the pressing pressure is 175 ℃. Preserving heat for 20min, and demolding to obtain a prefabricated member;
s4) placing the prefabricated member in an oven, preserving heat, and cooling to room temperature in a step manner to obtain the heat-proof product formed by the heat-proof layer and the metal piece in an integrated manner.
Wherein, 50-80 mesh quartz sand is used for sand blasting; the sand blasting pressure was 0.6MPa.
The preheating temperature of the premix is 90 ℃, and the premix is preheated for 20min;
placing the prefabricated part in an oven, and preserving heat for 200min at 175 ℃ in the step cooling process; cooling to 120 ℃, preserving heat for 120min, wherein the cooling speed is 40 ℃/h; cooling to 80 ℃, preserving heat for 60min, wherein the cooling speed is 20 ℃/h; cooling to room temperature;
specifically, the phenolic resin is a mixture of ammonia phenolic resin and magnesium phenolic resin; the reinforcing material is high silica fiber.
The method is used for carrying out water ultrasonic detection on the heat-proof product formed by the heat-proof layer with the large length-diameter ratio and the metal piece integrally, and the result shows that: the interface between the metal piece and the heat-proof layer has no debonding phenomenon.
Example III
The preparation process of the integrated heat-resistant product of the large length-diameter ratio heat-resistant layer and the metal piece for the aerospace vehicle comprises the following steps:
s1) preparing a pressing die, wherein the pressing die comprises an upper die and a lower die, the upper surface of the lower die is consistent with the appearance surface of a metal piece, and the radius of an arc surface of the lower surface of the upper die is 92mm;
s2) dividing into 4 areas according to the preset thickness of the heat-resistant layer, wherein the charging amount of the premix is respectively 37g, 53g, 30g and 87g;
s3) after the front surface of the metal piece is sandblasted, the front surface of the metal piece is placed into a lower die, the lower die and the metal piece are preheated, the preheating temperature is 175 ℃, the preheating is carried out for 20 minutes, a filling tool is used for filling premix, the premix is filled in different areas corresponding to the filling tool and is preheated, the preheated premix is filled into the lower die, the unit area of the preheated upper die is 10MPa, and the pressing pressure is 175 ℃. Preserving heat for 20min, and demolding to obtain a prefabricated member;
s4) placing the prefabricated member in an oven, preserving heat, and cooling to room temperature in a step manner to obtain the heat-proof product formed by the heat-proof layer and the metal piece in an integrated manner.
Wherein, 50-80 mesh quartz sand is used for sand blasting; the sand blasting pressure was 0.6MPa.
The preheating temperature of the premix is 90 ℃, and the premix is preheated for 20min;
placing the prefabricated part in an oven, and preserving heat for 240min at 175 ℃ in a step cooling process; cooling to 120 ℃, preserving heat for 60min, wherein the cooling speed is 20 ℃/h; cooling to 80 ℃, preserving heat for 60min, wherein the cooling speed is 40 ℃/h; cooling to room temperature;
specifically, the phenolic resin is a mixture of ammonia phenolic resin and boron phenolic resin; the reinforcing material is quartz fiber.
The method is used for carrying out water ultrasonic detection on the heat-proof product formed by the heat-proof layer with the large length-diameter ratio and the metal piece integrally, and the result shows that: the interface between the metal piece and the heat-proof layer has no debonding phenomenon.
Example IV
The preparation process of the integrated heat-resistant product of the large-length-diameter-ratio heat-resistant layer and the metal piece for the aerospace vehicle is the same as that of the first embodiment, and the difference is that the cambered surface radius of the lower surface of the upper die prepared in the step 1 is 96mm.
The method is used for carrying out water ultrasonic detection on the heat-proof product formed by the heat-proof layer with the large length-diameter ratio and the metal piece integrally, and the result shows that: the interface between the metal piece and the heat-proof layer has no debonding phenomenon.
Example five
The preparation process of the integrated heat-resistant product of the large-length-diameter-ratio heat-resistant layer and the metal piece for the aerospace vehicle is the same as that of the first embodiment, and the difference is that the phenolic resin is ammonia phenolic resin and the reinforcing material is carbon fiber.
The method is used for carrying out water ultrasonic detection on the heat-proof product formed by the heat-proof layer with the large length-diameter ratio and the metal piece integrally, and the result shows that: the interface between the metal piece and the heat-proof layer has no debonding phenomenon.
Example six
The preparation process of the integrated heat-proof product of the large length-diameter ratio heat-proof layer and the metal piece for the aerospace vehicle is the same as that of the first embodiment, and the difference is that the prefabricated part is placed in an oven, and the step cooling process is to keep the temperature at 175 ℃ for 120min; cooling to 120 ℃, preserving heat for 120min, wherein the cooling speed is 40 ℃/h; cooling to 80 ℃, preserving heat for 60min, wherein the cooling speed is 20 ℃/h; cooling to room temperature;
the method is used for carrying out water ultrasonic detection on the heat-proof product formed by the heat-proof layer with the large length-diameter ratio and the metal piece integrally, and the result shows that: the interface between the metal piece and the heat-proof layer has no debonding phenomenon.
Example seven
The preparation process of the integrated heat-proof product of the large length-diameter ratio heat-proof layer and the metal piece for the aerospace vehicle is the same as that of the first embodiment, and the difference is that the preheated upper die is adopted for pressing, the pressing pressure is 15MPa in unit area, and the pressing temperature is 175 ℃. Preserving heat for 35min, and demolding to obtain a prefabricated member;
the method is used for carrying out water ultrasonic detection on the heat-proof product formed by the heat-proof layer with the large length-diameter ratio and the metal piece integrally, and the result shows that: the interface between the metal piece and the heat-proof layer has no debonding phenomenon.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention, and not for limiting the same; although the invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some or all of the technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit of the invention.
Claims (8)
1. A rapid pressing method for a heat-resistant product formed by integrally forming a heat-resistant layer with a large length-diameter ratio and a metal piece is characterized by comprising the following steps of: the preparation method comprises the following preparation steps:
preparing a pressing die, wherein the pressing die comprises an upper die and a lower die, the upper surface of the lower die is consistent with the appearance surface of a metal piece, and the cambered surface radius of the lower surface of the upper die is 92mm-96mm;
partitioning according to the preset thickness of the heat-resistant layer, and calculating the weight of premix charges in different partitions of the heat-resistant layer;
after the front surface of the metal piece is sandblasted, the front surface of the metal piece is placed into a lower die, the lower die and the metal piece are preheated, a filling tool is used for filling premix, the premix is filled in different partitions corresponding to the filling tool and preheated, the preheated premix is filled into the lower die, and a preheated upper die is used for pressing and demolding to obtain a prefabricated member;
placing the prefabricated member in an oven, preserving heat, and cooling to room temperature in a step manner to obtain a heat-proof product formed by integrating the heat-proof layer and the metal piece;
the pressure applied to the upper die is 10-15MPa/m 2 Pressing at 175+ -10deg.C, maintaining the temperature for 20-35min, and demolding at 175+ -10deg.C to obtain prefabricated member;
placing the prefabricated part in an oven, and preserving heat for 120-240min at 175+/-10 ℃; cooling to 120 ℃, preserving heat for 60-120min, wherein the cooling speed is 20-40 ℃/h; cooling to 80 ℃, preserving heat for 60min, wherein the cooling speed is 20-40 ℃/h; cooling to room temperature.
2. The method for rapidly pressing the heat-resistant product integrally formed by the heat-resistant layer with the large length-diameter ratio and the metal piece according to claim 1 is characterized in that: the metal piece is a flat plate, a strip-shaped arc plate or a special-shaped plate.
3. The method for rapidly pressing the heat-resistant product integrally formed by the heat-resistant layer with the large length-diameter ratio and the metal piece according to claim 1 is characterized in that: adopting 50-80 mesh quartz sand to carry out sand blasting; the sand blasting pressure is 0.6+/-0.2 MPa.
4. The method for rapidly pressing the heat-resistant product integrally formed by the heat-resistant layer with the large length-diameter ratio and the metal piece according to claim 1 is characterized in that: the preheating temperature of the upper die and the lower die is 175+/-10 ℃, and the heat preservation time is more than or equal to 30 minutes.
5. The method for rapidly pressing the heat-resistant product integrally formed by the heat-resistant layer with the large length-diameter ratio and the metal piece according to claim 1 is characterized in that: the preheating temperature of the metal piece is 175+/-10 ℃ and the preheating time is 20-30min.
6. The method for rapidly pressing the heat-resistant product integrally formed by the heat-resistant layer with the large length-diameter ratio and the metal piece according to claim 1 is characterized in that: the premix is prepared from phenolic resin and reinforcing material, and the preheating temperature of the premix is 90+/-5 ℃ and the preheating time is 20-30min.
7. The method for rapidly pressing the heat-resistant product integrally formed by the heat-resistant layer with the large length-diameter ratio and the metal piece according to claim 6 is characterized in that: the phenolic resin is one or two of ammonia phenolic resin, magnesium phenolic resin and boron phenolic resin; the reinforcing material is one of high silica fiber, quartz fiber, alkali-free glass fiber or carbon fiber.
8. A product obtained by a rapid compression method of a heat-resistant product formed by integrating a heat-resistant layer with a metal piece according to any one of claims 1 to 7, characterized in that: comprises a metal piece (1), wherein a heat-proof layer (2) is added on the metal piece (1).
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| WO2012108446A1 (en) * | 2011-02-07 | 2012-08-16 | 帝人株式会社 | Molded object with thickness gradient and process for producing same |
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| CN106628110A (en) * | 2016-11-28 | 2017-05-10 | 北京航天长征飞行器研究所 | Novel integral special-shaped heatproof structure with ablation and heat insulation function division |
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