CN111468618B - Preparation method of airplane sheet metal stretching die - Google Patents
Preparation method of airplane sheet metal stretching die Download PDFInfo
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- CN111468618B CN111468618B CN202010273702.2A CN202010273702A CN111468618B CN 111468618 B CN111468618 B CN 111468618B CN 202010273702 A CN202010273702 A CN 202010273702A CN 111468618 B CN111468618 B CN 111468618B
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- 229910052751 metal Inorganic materials 0.000 title claims abstract description 30
- 239000002184 metal Substances 0.000 title claims abstract description 30
- 238000002360 preparation method Methods 0.000 title claims abstract description 16
- 239000000463 material Substances 0.000 claims abstract description 57
- 238000004519 manufacturing process Methods 0.000 claims abstract description 31
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 25
- 239000002131 composite material Substances 0.000 claims abstract description 21
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 19
- 238000000034 method Methods 0.000 claims abstract description 18
- 238000001723 curing Methods 0.000 claims abstract description 8
- 238000001029 thermal curing Methods 0.000 claims abstract description 8
- 238000003756 stirring Methods 0.000 claims description 31
- 239000003822 epoxy resin Substances 0.000 claims description 19
- 229920000647 polyepoxide Polymers 0.000 claims description 19
- 239000000203 mixture Substances 0.000 claims description 13
- 229920001187 thermosetting polymer Polymers 0.000 claims description 13
- 239000002023 wood Substances 0.000 claims description 13
- 239000000843 powder Substances 0.000 claims description 12
- 229920005989 resin Polymers 0.000 claims description 12
- 239000011347 resin Substances 0.000 claims description 12
- -1 aluminum compound Chemical class 0.000 claims description 10
- 239000011159 matrix material Substances 0.000 claims description 10
- 238000002156 mixing Methods 0.000 claims description 9
- MXRIRQGCELJRSN-UHFFFAOYSA-N O.O.O.[Al] Chemical compound O.O.O.[Al] MXRIRQGCELJRSN-UHFFFAOYSA-N 0.000 claims description 8
- 238000005266 casting Methods 0.000 claims description 8
- 229920000642 polymer Polymers 0.000 claims description 6
- 238000013007 heat curing Methods 0.000 claims description 4
- 238000007711 solidification Methods 0.000 claims 1
- 230000008023 solidification Effects 0.000 claims 1
- 230000007547 defect Effects 0.000 abstract description 11
- 238000005461 lubrication Methods 0.000 abstract description 3
- 239000000758 substrate Substances 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 3
- 238000003754 machining Methods 0.000 description 3
- 238000007493 shaping process Methods 0.000 description 3
- 229910000831 Steel Inorganic materials 0.000 description 2
- 150000001875 compounds Chemical class 0.000 description 2
- 238000012938 design process Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 229910052755 nonmetal Inorganic materials 0.000 description 2
- 238000012827 research and development Methods 0.000 description 2
- 239000010959 steel Substances 0.000 description 2
- 239000004925 Acrylic resin Substances 0.000 description 1
- 229920000178 Acrylic resin Polymers 0.000 description 1
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 229910001208 Crucible steel Inorganic materials 0.000 description 1
- 238000002679 ablation Methods 0.000 description 1
- NIXOWILDQLNWCW-UHFFFAOYSA-N acrylic acid group Chemical group C(C=C)(=O)O NIXOWILDQLNWCW-UHFFFAOYSA-N 0.000 description 1
- AZDRQVAHHNSJOQ-UHFFFAOYSA-N alumane Chemical class [AlH3] AZDRQVAHHNSJOQ-UHFFFAOYSA-N 0.000 description 1
- 238000010009 beating Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000009172 bursting Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- JEIPFZHSYJVQDO-UHFFFAOYSA-N iron(III) oxide Inorganic materials O=[Fe]O[Fe]=O JEIPFZHSYJVQDO-UHFFFAOYSA-N 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000002861 polymer material Substances 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- GOLXNESZZPUPJE-UHFFFAOYSA-N spiromesifen Chemical compound CC1=CC(C)=CC(C)=C1C(C(O1)=O)=C(OC(=O)CC(C)(C)C)C11CCCC1 GOLXNESZZPUPJE-UHFFFAOYSA-N 0.000 description 1
- 239000012257 stirred material Substances 0.000 description 1
- 230000003746 surface roughness Effects 0.000 description 1
- 230000002194 synthesizing effect Effects 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D37/00—Tools as parts of machines covered by this subclass
- B21D37/20—Making tools by operations not covered by a single other subclass
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D37/00—Tools as parts of machines covered by this subclass
- B21D37/01—Selection of materials
-
- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08K—Use of inorganic or non-macromolecular organic substances as compounding ingredients
- C08K3/00—Use of inorganic substances as compounding ingredients
- C08K3/02—Elements
- C08K3/08—Metals
-
- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08K—Use of inorganic or non-macromolecular organic substances as compounding ingredients
- C08K3/00—Use of inorganic substances as compounding ingredients
- C08K3/18—Oxygen-containing compounds, e.g. metal carbonyls
- C08K3/20—Oxides; Hydroxides
- C08K3/22—Oxides; Hydroxides of metals
-
- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08K—Use of inorganic or non-macromolecular organic substances as compounding ingredients
- C08K3/00—Use of inorganic substances as compounding ingredients
- C08K3/02—Elements
- C08K3/08—Metals
- C08K2003/0812—Aluminium
-
- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08K—Use of inorganic or non-macromolecular organic substances as compounding ingredients
- C08K3/00—Use of inorganic substances as compounding ingredients
- C08K3/18—Oxygen-containing compounds, e.g. metal carbonyls
- C08K3/20—Oxides; Hydroxides
- C08K3/22—Oxides; Hydroxides of metals
- C08K2003/2227—Oxides; Hydroxides of metals of aluminium
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Health & Medical Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Medicinal Chemistry (AREA)
- Polymers & Plastics (AREA)
- Organic Chemistry (AREA)
- Mechanical Engineering (AREA)
- Materials Engineering (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The invention discloses a preparation method of an airplane sheet metal stretching die. The method comprises the following steps: preparing a base material and a surface-stretched material; bonding the base material and the surface stretching part material into a whole to form an integral composite material; placing the forming vessel filled with the integral composite material in a thermal curing furnace for curing and forming; and curing to form a blank manufacturing mold. The preparation method provided by the invention fully utilizes the properties of the multi-element aluminum composite material such as self-lubrication and the like, effectively makes up for the defects of the existing mold, and fully meets the requirements of the aircraft manufacturing industry on the products. The precision of the workpieces of the novel die product is greatly improved, the quantity of the workpieces is increased, and the quantity of the workpieces reaches more than 2000 workpieces. The invention well solves the difficult problem of troubles caused by various defects of the airplane sheet metal stretching die for many years.
Description
Technical Field
The invention belongs to the technical field of machining of airplane sheet metal parts, and relates to a manufacturing method of an airplane sheet metal stretching die.
Background
The stretching die for the plane sheet metal parts is key equipment for manufacturing the plane sheet metal parts, and the plane parts belong to small-batch workpieces with multiple varieties, small single parts and different shapes, so that the manufacturing cost is high, and the working efficiency is low, so that the problem which puzzles the whole plane manufacturing industry is solved.
The existing airplane sheet metal drawing die basically has two structural forms: the mold is composed of steel mold made of common cast steel and non-metal mold coated with epoxy resin composite material. The first steel die has the defects that the surface is easy to rust and friction residues (residues of aluminum alloy and oil left on the surface of the die during stretching) cause the deformation of a workpiece, and the die is scrapped after being used for 8-9 times under a common condition, so that a large amount of loss is caused. The second non-metal mold has the defects of high fracture rate (especially when the temperature difference is large) and high surface porosity. Due to insufficient wear resistance, after 9-10 parts are stretched, the surface of the part is scratched, and the surface needs to be machined again. And the mould is basically a non-renewable object, which affects the environmental protection, and some large aircraft manufacturing units in China definitely forbid the use of the product.
Disclosure of Invention
In view of the above, the invention aims to provide a preparation method of an aircraft sheet metal stretching die, which can solve the problems of poor high temperature resistance, poor wear resistance and the like of the aircraft sheet metal stretching die;
in order to achieve the purpose, the invention provides the following technical scheme:
a preparation method of an airplane sheet metal drawing die comprises the following steps:
preparing a base material and a surface-stretched material;
bonding the base material and the surface stretching part material into a whole to form an integral composite material;
placing the forming vessel filled with the integral composite material in a thermal curing furnace for curing and forming;
and curing to form a blank manufacturing mold.
Further, the preparation method of the matrix material comprises the following steps:
a. stirring and mixing the aluminum compound powder and the high polymer thermosetting resin by using stirring equipment to obtain a daub-shaped mixture material;
b. the mixture material is placed in a matrix outer frame and tamped.
Further, the aluminum compound powder comprises: the high-molecular thermosetting resin is epoxy resin, wherein the epoxy resin comprises the following components in percentage by mass: 20%, aluminum hydroxide powder: 75 percent and 5 percent of pure aluminum powder.
Further, the stirring device adopts a 200L line quantity stirrer, and the stirring time is as follows: for 40 minutes.
Further, the tamping standing time is 8 hours, and the outer frame of the substrate is made of wood boards.
Further, a method for producing the surface-stretched material includes:
a. stirring and mixing the aluminum compound powder and the high polymer thermosetting resin by using stirring equipment to obtain a daub-shaped mixture material;
b. according to a digital model of the mold, adopting a wood plate outer frame, and casting the daub-shaped mixture material into the wood plate outer frame;
the casting was carried out in several passes with an interval of 4 hours.
Further, the aluminum compound powder comprises: the high-molecular thermosetting resin is epoxy resin, wherein the epoxy resin accounts for 40% by mass, the aluminum hydroxide powder accounts for 50% by mass, and the pure aluminum powder accounts for 10% by mass.
Further, the stirring device is a 300L line quantity stirrer, and the stirring time is as follows: for 25 minutes.
Further, the base material and the surface stretched portion material are bonded by YD-127 epoxy resin.
Further, the integral composite material is heated to 80 ℃ in a heat curing furnace and is stood for 72 hours; the size of the inner chamber of the thermocuring furnace is 2000x2000x1000mm, and the power is 30 KVA.
The invention has the beneficial effects that:
the preparation method provided by the invention fully utilizes the properties of the multi-element aluminum composite material such as self-lubrication and the like, effectively makes up for the defects of the existing mold, and fully meets the requirements of the aircraft manufacturing industry on the products. The precision of the workpieces of the novel die product is greatly improved, the quantity of the workpieces is increased, and the quantity of the workpieces reaches more than 2000 workpieces. The problem of puzzlement caused by various defects of the airplane sheet metal stretching die for many years is well solved.
Drawings
In order to facilitate understanding for those skilled in the art, the present invention will be further described with reference to the accompanying drawings.
FIG. 1 is a schematic flow chart of a manufacturing method of an aircraft sheet metal stretching mold according to the present invention;
FIG. 2 is a schematic diagram of the structure of the modified acrylic resin preparation process of the present invention.
Detailed Description
The invention discloses a preparation method of an airplane sheet metal stretching die, which fully utilizes the performance advantages of a novel composite material, overcomes the defects of the existing product, and provides a new implementation scheme and method in the aspects of materials, design and manufacturing process of the airplane sheet metal stretching die. The working precision of the product is obviously improved, the number of parts is effectively increased, the manufacturing cost is greatly reduced, and the working efficiency is improved.
The technical solutions in the embodiments of the present invention will be clearly and completely described below, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The prior art has the following two defects:
1: the high temperature resistance is poor. If the temperature for curing the product is controlled within 200 ℃, the technology cannot be applied to the product requiring higher temperature resistance.
2: the wear resistance is weak. The method is suitable for manufacturing various single small-batch products and is not suitable for manufacturing single products in large batch, such as dies with the number of the products exceeding 5000.
The invention relates to a process for synthesizing a multi-element aluminum composite material for an airplane sheet metal drawing die and forming a die blank. The multielement aluminum composite material is a novel composite material formed by mixing aluminum and aluminum compounds serving as matrixes with a thermosetting high polymer material, and has the advantages of high strength, high toughness, impact resistance, easiness in cutting and processing, reusability, abrasive resistance and the like. After years of practical exploration, the technology develops a plurality of subspecies materials and obtains better application in the fields of die manufacturing, mechanical manufacturing and the like.
A method for manufacturing an airplane sheet metal stretching mold, which is shown in fig. 1 as a schematic flow chart of the method for manufacturing the airplane sheet metal stretching mold; the method comprises the following steps:
preparing a base material and a surface stretching part material, wherein a structural schematic diagram of an airplane sheet metal stretching die is shown in FIG. 2, and the base material and the surface stretching part material comprise a base part 1 and a surface stretching part 2;
bonding the base material and the surface stretching part material into a whole to form an integral composite material;
placing the forming vessel filled with the integral composite material in a thermal curing furnace for curing and forming;
and curing to form a blank manufacturing mold.
Further, the preparation method of the matrix material comprises the following steps:
a. stirring and mixing the aluminum compound powder and the high polymer thermosetting resin by using stirring equipment to obtain a daub-shaped mixture material;
b. the mixture material is placed in a matrix outer frame and tamped.
Further, the aluminum-based compound powder includes: the high-molecular thermosetting resin is epoxy resin, wherein the epoxy resin comprises the following components in percentage by mass: 20%, aluminum hydroxide powder: 75 percent and 5 percent of pure aluminum powder.
Further, the stirring device adopts a 200L line quantity stirrer, and the stirring time is as follows: for 40 minutes.
And further, the tamping standing time is 8 hours, and the outer frame of the substrate is made of wood boards.
Further, a method for producing the surface stretched portion material:
a. stirring and mixing the aluminum compound powder and the high polymer thermosetting resin by using stirring equipment to obtain a daub-shaped mixture material;
b. according to a digital model of the mold, adopting a wood plate outer frame, and casting the daub-shaped mixture material into the wood plate outer frame;
the casting was carried out in several passes with an interval of 4 hours.
Further, the aluminum-based compound powder includes: the high-molecular thermosetting resin is epoxy resin, wherein the epoxy resin accounts for 40% by mass, the aluminum hydroxide powder accounts for 50% by mass, and the pure aluminum powder accounts for 10% by mass.
Specifically, the stirring device is a 300L line quantity stirrer, and the stirring time is as follows: for 25 minutes.
Further, the base material and the surface stretched portion material are bonded by YD-127 epoxy resin.
Further, the integral composite material is heated to 80 ℃ in a heat curing furnace and is stood for 72 hours; the size of the inner chamber of the thermocuring furnace is 2000x2000x1000mm, and the power is 30 KVA.
The product aims to fully utilize the performance advantages of the novel composite material, overcome the defects of the existing product and provide a new implementation scheme and method in the aspects of material, design and manufacturing process of the airplane sheet metal stretching die. The purposes of remarkably improving the working precision of products, effectively increasing the number of parts, greatly reducing the manufacturing cost and improving the working efficiency are achieved.
The invention fully utilizes the properties of the multi-element aluminum composite material such as self-lubrication and the like, effectively makes up the defects of the product and fully meets the requirements of the aircraft manufacturing industry on the product. The precision of the workpieces of the novel die product is greatly improved, the quantity of the workpieces is increased, and the quantity of the workpieces reaches more than 2000 workpieces. The problem of puzzlement caused by various defects of the airplane sheet metal stretching die for many years is well solved.
For the sake of clarity, the following examples are provided to illustrate the invention in detail
Example 1:
a base portion
1: preparation of matrix materials
| Name of Material | Model number | Ratio (%) | Manufacturer of the product |
| Epoxy resin | YD-127 | 20 | Kyodita Mitsubishi corporation |
| Aluminum hydroxide powder | AH-2 | 75 | China Aluminum Co., Ltd. |
| Pure aluminum powder | FLQT-1 | 5 | China Aluminum Co., Ltd. |
2. Mixing of matrix materials
Stirring equipment: 200L line quantity stirrer
Stirring time: 40 minutes
3. Shaping of base material
And manufacturing a matrix outer frame by using a wood board according to a digital model of the mold, and then stirring. And after stirring is completed, moving the multi-element aluminum mixture into a wood frame for tamping. Standing for 8 hours.
(II) surface stretching part
1. Preparation of surface-stretched Material
| Name of Material | Model number | Ratio (%) | Manufacturer of the product |
| Epoxy resin | YD-128 | 40 | Kyodita Mitsubishi corporation |
| Aluminum hydroxide powder | AH-2 | 50 | China Aluminum Co., Ltd. |
| Pure aluminum powder | FLQT-1 | 10 | China Aluminum Co., Ltd. |
2. Blending of materials for surface-stretched parts
Stirring equipment: 300L displacement vacuum stirrer
Stirring time: 25 minutes
3. Shaping of blank for surface stretching part
According to the model of the mould, the outer frame is made of a wood plate, and then the stirred material is introduced into the wood frame. The casting is carried out for multiple times, and the operation interval is 4 hours, so that the ablation phenomenon caused by the reaction heat of the materials is prevented.
(III) shaping of the Integrated blank
After the (I) and (II) are finished, the substrate and the surface blank are stuck together by YD-127 epoxy resin, and the substrate and the surface blank are placed still for 8 hours, then sent into a thermocuring furnace to be heated to 80 ℃, and are placed still for 72 hours. The heat curing oven can be selected according to the size of the product,
the present embodiment selects an interior compartment size of 2000x2000x1000mm with a power of 30 KVA.
(IV) numerical control machining of die
And (5) after the mould blank is well solidified, machining to the required precision by adopting a numerical control machining center according to a design digital model.
Method for detecting blank
The hardness of the material of example 1 was measured by a durometer hardness tester to be 82D or more, and the material was a good product. The porosity of the surface stretching part is lower than 5 percent, and the product is qualified.
The preparation process provided by the embodiment of the invention successfully starts the research and development of the formula of the multi-element aluminum composite material and the research and development of the forming process. Different types of material combinations show different performance parameters, and the material ratio finally synthesized through a large number of experiments meets the expected index requirements through detection and actual product application. Meanwhile, the forming process of the material also needs to be carried out for a plurality of times, and the tamped matrix shows good heat resistance. When the temperature difference change is bigger, for example, still can keep its structural strength when being greater than 40 ℃, the phenomenon of bursting can not appear, and the tensile part in surface adopts the vacuum stirring casting mode, has greatly reduced the production of gas pocket, has guaranteed the surface roughness of product to make aircraft panel beating finished piece quality promote by a wide margin.
The invention firstly starts from product materials, develops brand-new airplane lead-aluminum die materials and forming process methods through a large amount of practices, and has the capability of replacing the existing product manufacturing technology without realizing the updating and upgrading of airplane sheet metal stretching products.
The comparison of the aircraft sheet metal drawing die prepared in this example with conventional products is shown in the following table:
the preferred embodiments of the invention disclosed above are intended to be illustrative only. The preferred embodiments are not intended to be exhaustive or to limit the invention to the precise embodiments disclosed. Obviously, many modifications and variations are possible in light of the above teaching. The embodiments were chosen and described in order to best explain the principles of the invention and the practical application, to thereby enable others skilled in the art to best utilize the invention. The invention is limited only by the claims and their full scope and equivalents.
Claims (6)
1. A preparation method of an airplane sheet metal drawing die is characterized by comprising the following steps:
preparing a base material and a surface-stretched material;
bonding the base material and the surface stretching part material into a whole to form an integral composite material;
placing the forming vessel filled with the integral composite material in a thermal curing furnace for curing and forming;
forming a blank manufacturing die after solidification;
the preparation method of the matrix material comprises the following steps:
a. stirring and mixing the aluminum compound powder and the high polymer thermosetting resin by using stirring equipment to obtain a daub-shaped mixture material;
b. placing the mixture material in a matrix outer frame and tamping;
the aluminum compound powder comprises: the high-molecular thermosetting resin is epoxy resin, wherein the epoxy resin comprises the following components in percentage by mass: 20%, aluminum hydroxide powder: 75 percent of pure aluminum powder and 5 percent of pure aluminum powder;
the method for producing the surface-stretched material comprises the following steps:
a. stirring and mixing the aluminum compound powder and the high polymer thermosetting resin by using stirring equipment to obtain a daub-shaped mixture material;
b. according to a digital model of the mold, adopting a wood plate outer frame, and casting the daub-shaped mixture material into the wood plate outer frame;
the casting is carried out for multiple times, and the interval time is 4 hours;
the aluminum compound powder comprises: the high-molecular thermosetting resin is epoxy resin, wherein the epoxy resin accounts for 40% by mass, the aluminum hydroxide powder accounts for 50% by mass, and the pure aluminum powder accounts for 10% by mass.
2. The method for preparing the airplane sheet metal drawing die according to claim 1, wherein in the step a for preparing the base material, a 200L line quantity stirrer is adopted as the stirring equipment, and the stirring time is as follows: for 40 minutes.
3. The method for manufacturing the airplane sheet metal stretching die according to claim 1, wherein the tamping standing time is 8 hours, and the outer frame of the base body is made of a wood board.
4. The method for preparing the airplane sheet metal stretching mold according to claim 1, wherein in the step a for preparing the surface stretching part material, a 300L line quantity stirrer is adopted as stirring equipment, and the stirring time is as follows: for 25 minutes.
5. The method for manufacturing the airplane sheet metal drawing die according to claim 1,
the base material and the surface stretched material are bonded by YD-127 epoxy resin.
6. The method for preparing the airplane sheet metal drawing die as claimed in claim 1, wherein the integral composite material is heated to 80 ℃ in a heat curing furnace and stands for 72 hours; the size of the inner chamber of the thermocuring furnace is 2000x2000x1000mm, and the power is 30 KVA.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010273702.2A CN111468618B (en) | 2020-04-09 | 2020-04-09 | Preparation method of airplane sheet metal stretching die |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010273702.2A CN111468618B (en) | 2020-04-09 | 2020-04-09 | Preparation method of airplane sheet metal stretching die |
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| CN111468618A CN111468618A (en) | 2020-07-31 |
| CN111468618B true CN111468618B (en) | 2022-04-15 |
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| CN105945159B (en) * | 2016-05-05 | 2018-06-29 | 沈阳中航迈瑞特工业有限公司 | A kind of manufacturing method of the pull-shaped mold of polymer matrix composites airplane parts |
| CN108274729B (en) * | 2017-12-26 | 2020-05-05 | 天津康普斯特科技发展有限公司 | Stretching die made of high polymer material and manufacturing method thereof |
| CN108162260B (en) * | 2017-12-26 | 2020-09-04 | 天津康普斯特科技发展有限公司 | Mixed resin for manufacturing stretching die and method for manufacturing stretching die |
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Effective date of registration: 20240618 Address after: 110000 No.12, Shenbei Road, Shenbei New District, Shenyang City, Liaoning Province Patentee after: Shenyang Jinwei aviation parts manufacturing Co.,Ltd. Country or region after: China Address before: 110000 No. 1, Baihuashan Road, Huanggu District, Shenyang City, Liaoning Province Patentee before: Shenyang Shenfei machinery equipment factory Country or region before: China |
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