CN112297401A - Hot bending forming method for PMI foam of aviation interlayer composite material - Google Patents
Hot bending forming method for PMI foam of aviation interlayer composite material Download PDFInfo
- Publication number
- CN112297401A CN112297401A CN202011076057.1A CN202011076057A CN112297401A CN 112297401 A CN112297401 A CN 112297401A CN 202011076057 A CN202011076057 A CN 202011076057A CN 112297401 A CN112297401 A CN 112297401A
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- China
- Prior art keywords
- pmi foam
- composite material
- pmi
- rubber film
- mould
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- 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
- B29C51/00—Shaping by thermoforming, i.e. shaping sheets or sheet like preforms after heating, e.g. shaping sheets in matched moulds or by deep-drawing; Apparatus therefor
- B29C51/10—Forming by pressure difference, e.g. vacuum
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- 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
- B29C51/00—Shaping by thermoforming, i.e. shaping sheets or sheet like preforms after heating, e.g. shaping sheets in matched moulds or by deep-drawing; Apparatus therefor
- B29C51/26—Component parts, details or accessories; Auxiliary operations
- B29C51/30—Moulds
- B29C51/36—Moulds specially adapted for vacuum forming, Manufacture thereof
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
- Blow-Moulding Or Thermoforming Of Plastics Or The Like (AREA)
Abstract
The invention relates to a hot bending forming method of PMI foam of an aviation interlayer composite material, realizes integral forming of multi-curved-surface PMI foam, and belongs to the field of manufacturing of aviation interlayer composite materials. The method comprises the following steps: (1) manufacturing a forming platform and a mould; (2) cutting the PMI foam board according to the size of the die; (3) cutting the rubber film according to the size of the die and the size of the PMI foam board; (4) placing the PMI foam plate on a mold, then covering the PMI foam plate and the mold with a rubber film, fixedly sealing the rubber film on a forming platform by using a high-temperature-resistant sealing rubber strip, and connecting the rubber film with a vacuum system through a vacuum nozzle; (5) and in the molding process, when the PMI foam board is heated to a softening point, the rubber film is attached to the PMI foam board and the mold through a vacuum pumping system.
Description
Technical Field
The invention relates to a hot bending forming method of PMI foam of an aviation interlayer composite material, realizes integral forming of multi-curved-surface PMI foam, and belongs to the field of manufacturing of aviation interlayer composite materials.
Background
The sandwich composite structural member has excellent performances of stable structure, high bearing capacity, light weight resistance, high bending rigidity and the like, and is widely applied to the field of aviation. PMI foam is the foam material with the highest specific strength and specific modulus under the condition of the same density, has excellent performances of high temperature resistance, isotropy, creep resistance and the like, and has become the main filling material of the aviation sandwich composite material structural member.
In order to meet the requirement of the shape of airplane gas, most aviation sandwich composite structural members are multi-curvature members, and PMI foams used by the members are mainly manufactured by numerical control machining or block splicing at present. However, numerical control machining is adopted, so that the manufacturing cost is high, the material utilization rate is low, and the problems of easy cracking, surface slag falling, difficult machining of thin-wall parts and the like exist; by adopting the block splicing, obvious splicing seams appear in the composite material, the quality and the overall strength of parts are influenced, and the use advantage of the PMI foam is reduced.
Disclosure of Invention
The invention aims to provide a hot bending forming method of PMI foam of an aviation interlayer composite material, which adopts a vacuum adsorption hot bending method to realize the integral rapid forming of a multi-curvature PMI foam structure and has the characteristics of simple operation, low cost and high forming quality.
In order to achieve the purpose, the invention adopts the following technical scheme: a hot bending forming method of PMI foam of an aviation interlayer composite material comprises the following steps:
(1) manufacturing a forming platform and a mould;
(2) cutting the PMI foam board according to the size of the die;
(3) cutting the rubber film according to the size of the die and the size of the PMI foam board;
(4) placing the PMI foam plate on a mold, then covering the PMI foam plate and the mold with a rubber film, fixedly sealing the rubber film on a forming platform by using a high-temperature-resistant sealing rubber strip, and connecting the rubber film with a vacuum system through a vacuum nozzle;
(5) and in the molding process, when the PMI foam board is heated to a softening point, the rubber film is attached to the PMI foam board and the mold through a vacuum pumping system.
Further, in step (1): the tolerance of the mould is +/-0.1 mm.
Further, in the step (2): the thickness of the PMI flat plate is not more than 10 mm.
Further, the PMI foam sheet size is smaller than the size of the mold.
Further, in step (3): the area of the rubber membrane is 1.5-2 times of the area of the mould.
Further, the temperature of the softening point in the step (5) is 160-190 ℃.
Further, the specific parameters in step (5) are as follows: vacuumizing to-0.02-0.04 MPa and keeping for 3-5min, vacuumizing to-0.05-0.07 MPa and keeping for 3-5min, vacuumizing to-0.09-0.1 MPa to attach the PMI foam plate to the mold, keeping the temperature and pressure for 5-10min, cooling and releasing the pressure, and taking out the finished piece.
Further, the mold is a male mold.
Manufacturing a corresponding forming die according to the overall dimension of PMI foam in the sandwich component, adopting a rubber film (the thickness of the rubber film is 0.5-2 mm) with high temperature resistance, high elasticity and reusability, and constructing a closed cavity through a forming platform. And then, heating the PMI foam plate to a softening temperature by utilizing the plasticity of the PMI foam at a high temperature, and applying vacuum pressure step by step to ensure that the PMI foam plate is gradually attached to the forming mold. And finally, maintaining the pressure for a certain time, and cooling to obtain the PMI foam multi-curvature structure in the required shape.
The invention has the advantages of
Compared with the prior art, the PMI foam hot bending forming method for the aviation interlayer composite material member provided by the invention has the advantages of simple operation process and high forming efficiency, can realize integral forming of multi-curved-surface PMI foam, and avoids the problems of high cost of numerical control processing and uncontrollable quality of block splicing.
Drawings
FIG. 1 is a schematic view of step (4) of the present invention;
FIG. 2 is a schematic view of step (5) of the present invention.
In the figure: 1-a rubber membrane; 2-PMI foam board; 3-molding; 4-a forming platform; 5-sealing adhesive tape; 6-vacuum nozzle.
Detailed Description
The technical solution in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention; it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments, and all other embodiments obtained by those skilled in the art without any inventive work are within the scope of the present invention.
A hot bending forming method of PMI foam of an aviation interlayer composite material comprises the following steps:
(1) manufacturing a forming platform 4 and a mould 3;
(2) cutting the PMI foam plate 2 according to the size of the die 3;
(3) cutting the rubber film 1 according to the size of the die 3 and the size of the PMI foam plate 2;
(4) the PMI foam plate 2 is placed on a mould 3, then the PMI foam plate 2 and the mould 3 are covered by a rubber film 1, the rubber film 1 is fixedly sealed on a forming platform 4 by a high-temperature resistant sealing rubber strip 5, and the rubber film is connected with a vacuum system through a vacuum nozzle 6;
(5) and in the molding process, when the PMI foam board 2 is heated to the softening point, the rubber film 1 is attached to the PMI foam board 2 and the mold 3 through a vacuum pumping system.
Further, in step (1): the tolerance of the mould 3 is +/-0.1 mm.
Further, in the step (2): the thickness of the PMI flat plate 2 is not more than 10 mm.
Further, the PMI foam sheet (2) size is smaller than the size of the mold 3.
Further, in step (3): the area of the rubber film 1 is 1.5-2 times of the area of the mould 3.
Further, the temperature of the softening point in the step (5) is 160-190 ℃.
Further, the specific parameters in step (5) are as follows: vacuumizing to-0.02-0.04 MPa and keeping for 3-5min, vacuumizing to-0.05-0.07 MPa and keeping for 3-5min, vacuumizing to-0.09-0.1 MPa to enable the PMI foam plate 2 and the die 3 to be attached, finally preserving heat and pressure for 5-10min, cooling and releasing pressure, and taking out the finished piece.
Further, the mold 3 is a male mold.
The foregoing is only a preferred embodiment of the present invention; the scope of the invention is not limited thereto. Any person skilled in the art should be able to cover the technical scope of the present invention by equivalent or modified solutions and modifications within the technical scope of the present invention.
Claims (8)
1. A hot bending forming method of PMI foam of an aviation interlayer composite material is characterized by comprising the following steps:
(1) manufacturing a forming platform (4) and a mould (3);
(2) cutting the PMI foam board (2) according to the size of the die (3);
(3) cutting the rubber film (1) according to the size of the die (3) and the size of the PMI foam plate (2);
(4) the PMI foam plate (2) is placed on a mould (3), then the PMI foam plate (2) and the mould (3) are covered by a rubber film (1), the rubber film (1) is fixedly sealed on a forming platform (4) by a high-temperature resistant sealing rubber strip (5), and the PMI foam plate is connected with a vacuum system through a vacuum nozzle (6);
(5) and in the molding process, when the PMI foam plate (2) is heated to the softening point, the rubber film (1) is attached to the PMI foam plate (2) and the mold (3) through a vacuum pumping system.
2. The method for hot roll forming of the PMI foam of an aerospace sandwich composite material according to claim 1, wherein: in step (1): the tolerance of the die (3) is +/-0.1 mm.
3. The method for hot roll forming of the PMI foam of an aerospace sandwich composite material according to claim 1, wherein: in step (2): the thickness of the PMI flat plate (2) is not more than 10 mm.
4. The method for hot roll forming of the PMI foam of an aerospace sandwich composite material according to claim 1, wherein: the PMI foam plate (2) has a size smaller than that of the mold (3).
5. The method for hot roll forming of the PMI foam of an aerospace sandwich composite material according to claim 1, wherein: in step (3): the area of the rubber film (1) is 1.5-2 times of the area of the mould (3).
6. The method for hot roll forming of the PMI foam of an aerospace sandwich composite material according to claim 1, wherein: the temperature of the softening point in the step (5) is 160-190 ℃.
7. The method for hot roll forming of the PMI foam of an aerospace sandwich composite material according to claim 1, wherein: the specific parameters in the step (5) are as follows: vacuumizing to-0.02-0.04 MPa and keeping for 3-5min, vacuumizing to-0.05-0.07 MPa and keeping for 3-5min, vacuumizing to-0.09-0.1 MPa to enable the PMI foam plate (2) and the mould (3) to be attached, finally preserving heat and pressure for 5-10min, cooling and releasing pressure, and taking out a finished piece.
8. The method for hot roll forming of the PMI foam of an aerospace sandwich composite material according to claim 1, wherein: the mould (3) is a male mould.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011076057.1A CN112297401A (en) | 2020-10-10 | 2020-10-10 | Hot bending forming method for PMI foam of aviation interlayer composite material |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011076057.1A CN112297401A (en) | 2020-10-10 | 2020-10-10 | Hot bending forming method for PMI foam of aviation interlayer composite material |
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| CN112297401A true CN112297401A (en) | 2021-02-02 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202011076057.1A Pending CN112297401A (en) | 2020-10-10 | 2020-10-10 | Hot bending forming method for PMI foam of aviation interlayer composite material |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1775507A (en) * | 2005-10-18 | 2006-05-24 | 成都飞机工业（集团）有限责任公司 | Thermal forming method for PMI foam laminated structure |
| CN102951371A (en) * | 2011-08-26 | 2013-03-06 | 波音公司 | Integrally stiffened, reusable vacuum bag and method of making the same |
| SG11201500518PA (en) * | 2012-07-24 | 2015-03-30 | Evonik Industries Ag | Novel shaping process for pmi foam materials and/or composite components produced therefrom |
| CN106738815A (en) * | 2016-11-30 | 2017-05-31 | 江西洪都航空工业集团有限责任公司 | A kind of rigid foam core thermoforming process |
-
2020
- 2020-10-10 CN CN202011076057.1A patent/CN112297401A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1775507A (en) * | 2005-10-18 | 2006-05-24 | 成都飞机工业（集团）有限责任公司 | Thermal forming method for PMI foam laminated structure |
| CN102951371A (en) * | 2011-08-26 | 2013-03-06 | 波音公司 | Integrally stiffened, reusable vacuum bag and method of making the same |
| SG11201500518PA (en) * | 2012-07-24 | 2015-03-30 | Evonik Industries Ag | Novel shaping process for pmi foam materials and/or composite components produced therefrom |
| CN106738815A (en) * | 2016-11-30 | 2017-05-31 | 江西洪都航空工业集团有限责任公司 | A kind of rigid foam core thermoforming process |
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Application publication date: 20210202 |
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