CN111690235B - Skin mold forming material and manufacturing and application thereof - Google Patents
Skin mold forming material and manufacturing and application thereof Download PDFInfo
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- CN111690235B CN111690235B CN202010606204.5A CN202010606204A CN111690235B CN 111690235 B CN111690235 B CN 111690235B CN 202010606204 A CN202010606204 A CN 202010606204A CN 111690235 B CN111690235 B CN 111690235B
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- parts
- skin
- mold
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- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08L—COMPOSITIONS OF MACROMOLECULAR COMPOUNDS
- C08L63/00—Compositions of epoxy resins; Compositions of derivatives of epoxy resins
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/12—Construction or attachment of skin panels
-
- 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
Abstract
The invention relates to the technical field of skin molding die composite materials, in particular to a skin molding die composite material and a preparation method and application thereof, wherein the skin molding die composite material comprises the following molding formula in parts by weight: 100 parts of epoxy resin, 50-70 parts of toughening material, 15-25 parts of curing agent, 12-17 parts of plasticizer, 8-15 parts of reinforcing material, 3-5 parts of lubricant and 20-30 parts of epoxy reactive diluent, uniformly mixing the materials in a formula to obtain a mixture, pouring the mixture into a mold cavity of a mold for casting molding, heating up the skin mold and the mold together for curing after molding, and demolding at room temperature after curing is completed to obtain the skin mold, wherein the performance index of the skin mold meets the requirements of missile skin molding technology.
Description
Technical Field
The invention relates to the technical field of skin molding die composite materials, in particular to a skin molding die composite material and a manufacturing method and application thereof.
Background
The main function of the elastomer skin is that the cabin bodies of the frame structure are connected by the skin, the skin structure is formed by covering a layer of metal plates on the longitudinal ribs and the transverse ribs of the space framework to form a combined action system, the skin can be subjected to internal tension, compression and shearing stress, the skin is equivalent to continuously distributed support, the effect of space stress is achieved, and the elastomer skin structure comprises a cabin body skin connecting structure, a main wing skin connecting riveting structure and a control surface skin riveting structure. The shape of the skin is special in the actual manufacturing process of the skin, the surface of the skin is a curved surface manufactured according to a certain curve equation, a mold is used as a tool for manually beating the skin into the shape in the manufacturing process of the traditional skin, the skin meeting the curve equation is manufactured and manually beaten (the skin is along the curved surface of the mold) for a plurality of times, the performance requirement on the mold is particularly high, the mold is required to have higher strength and toughness, the formula of the skin tire film is essentially different from that of the traditional glass fiber reinforced plastic, and the requirements of three aspects are mainly met: a) The film-forming resin system has higher epoxy equivalent, has enough strength after the mold is cured, and bears certain pneumatic load; b) The film-forming resin system has certain flexibility and meets the stress deformation of the mold; c) The film forming material has reinforcement material to ensure the strength and toughness of the mold.
As disclosed in patent No. CN201811586165.6, an autoclave molding process skin for a composite material workpiece comprises: resin: 20-80wt% of fiber: 20-60wt% of rubber: 20-60wt%; the resin is one or a combination of a plurality of thermosetting resins such as epoxy resin, bismaleimide resin, cyanate resin, polyimide resin and the like, or one or a combination of a plurality of thermoplastic resins such as polyethylene, polypropylene, polyurethane, polyphenylene sulfide, polyaryletherketone, polyether etherketone, polysulfone, polyether sulfone, thermoplastic polyimide, polycarbonate, polyamide, polyurea and the like.
As another example, patent No. CN201410752046.9 discloses a coating composition for rapid repair of damaged skin coating of an aircraft, wherein the component a comprises the following components in percentage by mass: 15-25% of medium-high molecular weight epoxy resin, 2-12% of modified resin, 15-30% of conventional pigment and filler, 15-30% of environment-friendly anti-corrosion pigment, 0.5-1% of auxiliary agent and the balance of solvent; the component B comprises the following components in percentage by mass: 60-90% of epoxy-amine adduct, 10-40% of epoxy-polyamino alkoxy silane adduct, and the sum of the epoxy-amine adduct and the epoxy-polyamino alkoxy silane adduct is 100%.
As another patent No. CN200510027442.6, a coating system suitable for the skin of large and medium civil airliners is disclosed, which consists of a primer and a top coat, characterized in that the primer is made of a medium molecular weight epoxy resin matched with a softer polyamide curing agent, and the top coat is made of a special hydroxyl polyester resin matched with an HDI biuret and an HDI trimer as a crosslinking agent.
However, the existing elastic skin material has the problem that the in-plane flexibility and the out-of-plane rigidity are difficult to be combined, namely, the in-plane deformation capability of the aircraft skin is strong, and the out-of-plane normal bearing capability of the aircraft skin is weak; and the plane skin with stronger out-of-plane normal bearing capacity has weaker in-plane deformation capacity. And the development of the skin mold is greatly restricted by the factors such as complex operation of the molding method.
Disclosure of Invention
The invention provides a skin mold material and a forming method thereof, aiming at the defects of the prior art.
The method is realized by the following technical scheme:
the first aim of the invention is to provide a skin mold molding material, which comprises the following molding formulation in parts by weight: 100 parts of epoxy resin, 50-70 parts of toughening material, 15-25 parts of curing agent, 12-17 parts of plasticizer, 8-15 parts of reinforcing material, 3-5 parts of lubricant and 20-30 parts of epoxy reactive diluent.
Further preferably, the skin mold molding material comprises the following molding formula in parts by weight: 100 parts of epoxy resin, 50-60 parts of toughening material, 15-20 parts of curing agent, 12-15 parts of plasticizer, 10-15 parts of reinforcing material, 3-5 parts of lubricant and 20-25 parts of epoxy reactive diluent.
Still further preferably, the skin mold molding material comprises the following molding formulation in parts by weight: 100 parts of epoxy resin, 55 parts of toughening material, 20 parts of curing agent, 13 parts of plasticizer, 15 parts of reinforcing material, 4 parts of lubricant and 23 parts of epoxy reactive diluent.
The toughening material is preferably a polyamide resin.
The curing agent is polyethylene polyamine or other amine curing agents; polyethylene polyamines are preferred.
The plasticizer is preferably dibutyl phthalate.
The reinforcing material is preferably aluminum powder with granularity more than or equal to 100 meshes.
The lubricant is preferably graphite powder.
The epoxy reactive diluent is any one of lipid, alcohol and ketone; acetone is preferred.
The second object of the present invention is to provide a method for manufacturing a skin mold from the molding material, which comprises the steps of: and weighing epoxy resin, a toughening material, a curing agent, a plasticizer, a reinforcing material, a lubricant and an epoxy reactive diluent according to a formula, uniformly mixing, pouring the mixture into a mold cavity for casting molding, performing heating-up type curing on the skin mold and the mold together after molding, and demolding at room temperature after curing is completed to obtain the skin mold.
The heating type curing is to cure for 6 hours under the condition of 20-30 ℃, then heat up to 50-60 ℃ and cure for 6 hours under constant temperature, and then heat up to 80-90 ℃ and cure for 24 hours under constant temperature.
The third object of the present invention is that the skin molding material is used for manufacturing cabin skin moldings, control surface skin moldings, main wing skin moldings and skin moldings with other special shapes.
The beneficial effects are that:
according to the application, the inventor selects dibutyl phthalate as a main plasticizing material and polyamide resin as a secondary plasticizing material to carry out modification treatment on epoxy resin through a large number of experimental researches and screens, and meanwhile, the polyamide resin as the secondary plasticizing material has a toughening effect, so that the strength and toughness of the skin mold material are effectively modified by utilizing the interaction relationship between the dibutyl phthalate and the polyamide resin, the high-toughness and high-strength functions of the mold are ensured, and the problem that the technological performance (toughness and impact resistance) of the mold formed and processed by single epoxy resin is poor is solved.
Compared with the prior art, the skin mold provided by the invention has the core technical indexes that the strength and toughness of the molded mold can be effectively adjusted under the condition of excellent conventional performance, so that the molded mold is matched with the skin of the cabin body during molding, and the required strength and toughness of the skin of the cabin body are ensured.
The skin mold disclosed by the invention is wide in application range, and can be used for not only cabin skin molds, but also control surface skin molds, main wing skin molds and skin molds with other special shapes.
The skin mold disclosed by the invention has excellent comprehensive performance, the tensile modulus is greater than 25Gpa, the tensile strength is greater than 160MPa, the specific strength is greater than 50MPa, the elongation at break is greater than 1.2%, and the performance index of the skin mold meets the requirements of missile skin molding technology.
Drawings
Fig. 1: a skin mold structure schematic diagram, wherein a layer A is a base material, and a layer B is a casting layer;
fig. 2: cabin skin part structure schematic diagram.
Detailed Description
The following detailed description of the invention is provided in further detail, but the invention is not limited to these embodiments, any modifications or substitutions in the basic spirit of the present examples, which still fall within the scope of the invention as claimed.
Example 1
Skin mold forming material formula
The formulation of the molding material of the cabin skin mold is shown in table 1:
TABLE 1
| Sequence number | Material name | Material brand | Classification | Parts by weight of |
| 1 | Bisphenol A epoxy resin | E51 | Main body resin | 50 |
| 2 | Polyamide resin | 650 | Toughened and cured resin | 25 |
| 3 | Polyethylene polyamine | Chemical purity | Curing agent | 9 |
| 4 | Epoxy reactive diluent | Acetone (Industrial grade) | Diluent agent | 6 |
| 5 | Dibutyl phthalate | Reagent grade | Plasticizer(s) | 3 |
| 6 | Aluminum powder | Greater than 100 meshes | Reinforcing material | 5 |
| 7 | GraphitePowder | Industrial grade | Lubricating filler material | 2 |
Examples 2 to 7
The formulation proportions were varied on the basis of example 1, as shown in Table 2;
TABLE 2
The sizing materials according to the formulations of examples 1-7 were molded into templates with mold cavity sizes of 200×200×5, cured and demolded to prepare standard samples, and the physical and chemical properties and static mechanical properties of the molding materials were tested by conventional methods, and the performance results of examples 1-7 are shown in tables 3 and 4:
a) Physical and chemical properties of the mold material are shown in Table 3;
TABLE 3 Table 3
| Project | Density (g/cm) 3 ) | Coefficient of thermal conductivity (W/m. Degree.C.) | Coefficient of thermal expansion |
| Example 1 | 1.78 | 0.48 | (1011./2℃) |
| Example 2 | 1.8875 | 01.2409 | 1201.29 |
| Example 3 | 1.73 | 0.50 | 11.3 |
| Example 4 | 1.76 | 0.48 | 10.6 |
| Example 5 | 1.78 | 0.45 | 10.4 |
| Example 6 | 1.54 | 0.72 | 12.1 |
| Example 7 | 1.62 | 0.66 | 11.9 |
b) The mechanical properties of the molding materials are shown in Table 4;
TABLE 4 Table 4
Example 8: cabin skin mold forming and manufacturing process
The manufacturing of the cabin skin molding die is completed by casting in a die, and the main process comprises the processes of releasing agent on an outer die of the die, glue preparation, casting, solidification and releasing, and specifically comprises the following steps:
1) And (3) installing a die: installing a die inner core according to the requirement of FIG. 1, and adjusting the gap between the inner core and the outer die;
2) And (3) upper release agent: uniformly waxing the inner surface of the inner cavity of the outer mold and uniformly sticking a layer of polyvinyl chloride film;
3) And (3) glue preparation: calculating the total amount of film forming materials according to the volume of a die cavity, weighing according to the formula of table 1 or table 2, and uniformly dispersing each component by using a dispersing tool;
4) Pouring: pouring the prepared sizing material into a mold cavity;
5) Curing: after casting molding, the skin mold and the mold are subjected to heating type solidification, specifically: curing for 6 hours at 20-30 ℃, heating to 50-60 ℃, preserving heat and curing for 6 hours, heating to 80-90 ℃, preserving heat and curing for 24 hours, and then, cooling to room temperature and preserving heat for more than 6 hours;
6) Demolding: after the molding is formed, the mold is demolded by a press-off tool, and the mold is not damaged by tapping and fine drawing, as shown in fig. 1.
Example 9
The molding skin for the cabin skin part shown in fig. 2 is formed by a mold, and the specific operation is as follows:
1) And (3) blanking: checking the blanking size and blanking according to the required size;
2) And (3) bench workers: pre-bending and preliminary stretch forming parts;
3) And (3) checking: the fitting clearance between the part and the mould is required to be not more than 0.5;
4) And (3) heat treatment: quenching;
5) And (3) bench workers: drawing, correcting, scribing, removing allowance and filing;
6) Milling: milling each hole and deburring;
7) And (3) checking: and checking according to a model curve equation and the sizes of all holes.
Claims (4)
1. The skin mold molding material is characterized by comprising the following molding formula in parts by weight: 100 parts of epoxy resin, 50-70 parts of toughening material, 15-25 parts of curing agent, 12-17 parts of plasticizer, 8-15 parts of reinforcing material, 3-5 parts of lubricant and 20-30 parts of acetone;
the toughening material is polyamide resin;
the plasticizer is dibutyl phthalate;
the curing agent is polyethylene polyamine;
the reinforcing material is aluminum powder with granularity more than or equal to 100 meshes;
the lubricant is graphite powder;
according to the method for manufacturing the skin mold by using the skin mold molding material, epoxy resin, toughening material, curing agent, plasticizer, reinforcing material, lubricant and acetone are measured according to the formula and mixed uniformly, then the mixture is poured into a mold cavity for casting molding, after molding, the skin mold and the mold are cured together at a temperature rising mode, and after curing is completed, demolding is carried out at room temperature, so that the skin mold is obtained;
the heating type curing is to cure for 6 hours under the condition of 20-30 ℃, then heat up to 50-60 ℃ and cure for 6 hours under constant temperature, and then heat up to 80-90 ℃ and cure for 24 hours under constant temperature.
2. The skin mold molding material according to claim 1, wherein the skin mold molding material comprises the following molding formulation in parts by weight: 100 parts of epoxy resin, 50-60 parts of toughening material, 15-20 parts of curing agent, 12-15 parts of plasticizer, 10-15 parts of reinforcing material, 3-5 parts of lubricant and 20-25 parts of acetone.
3. Skin mold molding material according to claim 1 or 2, characterized in that the skin mold molding material has the following molding formulation in parts by weight: 100 parts of epoxy resin, 55 parts of toughening material, 20 parts of curing agent, 13 parts of plasticizer, 15 parts of reinforcing material, 4 parts of lubricant and 23 parts of acetone.
4. Use of the skin molding material according to claim 1, 2 or 3 for the production of cabin skin moldings, control surface skin moldings and main wing skin moldings.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010606204.5A CN111690235B (en) | 2020-06-29 | 2020-06-29 | Skin mold forming material and manufacturing and application thereof |
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| CN202010606204.5A CN111690235B (en) | 2020-06-29 | 2020-06-29 | Skin mold forming material and manufacturing and application thereof |
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104259384A (en) * | 2014-07-30 | 2015-01-07 | 宁国市冠宇模具有限公司 | Resin mold and production method thereof |
| CN104387722A (en) * | 2014-10-21 | 2015-03-04 | 常熟市金成模具有限公司 | Compounding ratio of metal resin rapid die material and solidifying method thereof |
| CN104788791A (en) * | 2015-04-30 | 2015-07-22 | 青岛海蓝海洋复合功能材料科技有限公司 | High-stability low-temperature-resistant plastic |
| CN105111485A (en) * | 2015-09-09 | 2015-12-02 | 滁州迪蒙德模具制造有限公司 | Manufacturing method of mold |
| CN106273902A (en) * | 2016-08-05 | 2017-01-04 | 深圳航天科技创新研究院 | A kind of aluminium foam sandwich structural composite material and preparation method thereof |
| CN108274729A (en) * | 2017-12-26 | 2018-07-13 | 天津康普斯特科技发展有限公司 | A kind of high molecular material makes drawing die and its manufacturing method |
| CN111019293A (en) * | 2019-11-30 | 2020-04-17 | 无锡市明江保温材料有限公司 | Vacuum insulation material and preparation method thereof |
| CN111267327A (en) * | 2020-03-16 | 2020-06-12 | 沈阳飞机工业（集团）有限公司 | Skin stretch forming die and manufacturing method thereof |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7078451B2 (en) * | 2002-12-19 | 2006-07-18 | Owens Corning Fiberglas Technology, Inc. | Formulation and process for compression molded component parts |
| CN104781303B (en) * | 2012-11-13 | 2017-11-10 | 陶氏环球技术有限责任公司 | Epoxy-resin systems for the tetramine containing polyethylene of resin transfer moulding method |
-
2020
- 2020-06-29 CN CN202010606204.5A patent/CN111690235B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104259384A (en) * | 2014-07-30 | 2015-01-07 | 宁国市冠宇模具有限公司 | Resin mold and production method thereof |
| CN104387722A (en) * | 2014-10-21 | 2015-03-04 | 常熟市金成模具有限公司 | Compounding ratio of metal resin rapid die material and solidifying method thereof |
| CN104788791A (en) * | 2015-04-30 | 2015-07-22 | 青岛海蓝海洋复合功能材料科技有限公司 | High-stability low-temperature-resistant plastic |
| CN105111485A (en) * | 2015-09-09 | 2015-12-02 | 滁州迪蒙德模具制造有限公司 | Manufacturing method of mold |
| CN106273902A (en) * | 2016-08-05 | 2017-01-04 | 深圳航天科技创新研究院 | A kind of aluminium foam sandwich structural composite material and preparation method thereof |
| CN108274729A (en) * | 2017-12-26 | 2018-07-13 | 天津康普斯特科技发展有限公司 | A kind of high molecular material makes drawing die and its manufacturing method |
| CN111019293A (en) * | 2019-11-30 | 2020-04-17 | 无锡市明江保温材料有限公司 | Vacuum insulation material and preparation method thereof |
| CN111267327A (en) * | 2020-03-16 | 2020-06-12 | 沈阳飞机工业（集团）有限公司 | Skin stretch forming die and manufacturing method thereof |
Non-Patent Citations (1)
| Title |
|---|
| 新材料蒙皮拉形模具的制备工艺;王珏等;《合成树脂及塑料》;20180325(第02期);第79页左栏第2段，第1.1-1.2、2.1部分、表1 * |
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