CN116638790A - Forming method of epoxy flame-retardant sandwich structure composite material - Google Patents
Forming method of epoxy flame-retardant sandwich structure composite material Download PDFInfo
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- CN116638790A CN116638790A CN202310685144.4A CN202310685144A CN116638790A CN 116638790 A CN116638790 A CN 116638790A CN 202310685144 A CN202310685144 A CN 202310685144A CN 116638790 A CN116638790 A CN 116638790A
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- 239000002131 composite material Substances 0.000 title claims abstract description 49
- 238000000034 method Methods 0.000 title claims abstract description 35
- RNFJDJUURJAICM-UHFFFAOYSA-N 2,2,4,4,6,6-hexaphenoxy-1,3,5-triaza-2$l^{5},4$l^{5},6$l^{5}-triphosphacyclohexa-1,3,5-triene Chemical compound N=1P(OC=2C=CC=CC=2)(OC=2C=CC=CC=2)=NP(OC=2C=CC=CC=2)(OC=2C=CC=CC=2)=NP=1(OC=1C=CC=CC=1)OC1=CC=CC=C1 RNFJDJUURJAICM-UHFFFAOYSA-N 0.000 title claims abstract description 33
- 239000003063 flame retardant Substances 0.000 title claims abstract description 33
- 239000004593 Epoxy Substances 0.000 title claims abstract description 32
- 239000002313 adhesive film Substances 0.000 claims abstract description 29
- 238000003825 pressing Methods 0.000 claims abstract description 27
- 239000004760 aramid Substances 0.000 claims abstract description 26
- 229920003235 aromatic polyamide Polymers 0.000 claims abstract description 26
- 238000000465 moulding Methods 0.000 claims abstract description 12
- 229920005989 resin Polymers 0.000 claims description 25
- 239000011347 resin Substances 0.000 claims description 25
- 238000012546 transfer Methods 0.000 claims description 12
- 229920002620 polyvinyl fluoride Polymers 0.000 claims description 9
- 239000011159 matrix material Substances 0.000 claims description 7
- 239000004744 fabric Substances 0.000 claims description 6
- 239000012783 reinforcing fiber Substances 0.000 claims description 6
- 230000000630 rising effect Effects 0.000 claims description 6
- 239000003365 glass fiber Substances 0.000 claims description 5
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 3
- 239000004917 carbon fiber Substances 0.000 claims description 3
- 239000000835 fiber Substances 0.000 claims description 3
- 238000004519 manufacturing process Methods 0.000 abstract description 8
- 229920006231 aramid fiber Polymers 0.000 abstract description 5
- 238000005034 decoration Methods 0.000 abstract description 5
- 238000002360 preparation method Methods 0.000 abstract description 2
- 239000000463 material Substances 0.000 description 29
- 239000010410 layer Substances 0.000 description 15
- 238000002955 isolation Methods 0.000 description 11
- 230000008569 process Effects 0.000 description 11
- WSFSSNUMVMOOMR-UHFFFAOYSA-N Formaldehyde Chemical compound O=C WSFSSNUMVMOOMR-UHFFFAOYSA-N 0.000 description 6
- 238000013329 compounding Methods 0.000 description 6
- 238000001514 detection method Methods 0.000 description 6
- 238000010030 laminating Methods 0.000 description 5
- 239000002994 raw material Substances 0.000 description 4
- 238000005070 sampling Methods 0.000 description 4
- KXGFMDJXCMQABM-UHFFFAOYSA-N 2-methoxy-6-methylphenol Chemical compound [CH]OC1=CC=CC([CH])=C1O KXGFMDJXCMQABM-UHFFFAOYSA-N 0.000 description 3
- 208000034656 Contusions Diseases 0.000 description 3
- 238000000748 compression moulding Methods 0.000 description 3
- 230000007547 defect Effects 0.000 description 3
- 239000007789 gas Substances 0.000 description 3
- 239000005011 phenolic resin Substances 0.000 description 3
- 229920001568 phenolic resin Polymers 0.000 description 3
- 230000000903 blocking effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 239000003292 glue Substances 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 238000007689 inspection Methods 0.000 description 2
- 239000011229 interlayer Substances 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000011056 performance test Methods 0.000 description 2
- 238000004064 recycling Methods 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 238000005303 weighing Methods 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 239000011180 sandwich-structured composite Substances 0.000 description 1
- 239000002341 toxic gas Substances 0.000 description 1
- 238000009827 uniform distribution Methods 0.000 description 1
- 238000011179 visual inspection Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 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
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
-
- 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
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
- Laminated Bodies (AREA)
Abstract
The application relates to the technical field of composite material preparation, in particular to a method for forming an epoxy flame-retardant sandwich structure composite material. The molding method comprises the following steps: the upper surface and the lower surface of the upper panel and the lower panel are respectively stuck with a piece of isolating paper/film; placing an aramid paper honeycomb on the adhesive film surface of the lower panel, and placing the adhesive film surface of the upper panel on the surface of the aramid paper honeycomb to form a sandwich structure; pre-pressing the mould with the sandwich structure under a first set condition; carrying out curing treatment on the pre-compacted die under a second set condition; and demolding the cured mold to obtain the epoxy flame-retardant sandwich structure composite material. The method for forming the epoxy flame-retardant sandwich structure composite material aims to solve the problems that the artificial and auxiliary consumables of the aramid fiber honeycomb sandwich structure composite material applied to aviation interior decoration at present are large in investment and low in production efficiency.
Description
Technical Field
The application relates to the technical field of composite material preparation, in particular to a method for forming an epoxy flame-retardant sandwich structure composite material.
Background
With further improvement of the requirements of the aircraft structure on safety, economy, comfort and the like, the aramid fiber honeycomb sandwich structure composite material has been widely applied to aviation internal decoration and secondary bearing structural members due to excellent characteristics of high specific strength, high specific modulus, fatigue resistance, corrosion resistance, sound insulation, flame retardance and the like. In order to ensure some key properties of the honeycomb sandwich structure, such as surface density, peel strength and the like, a phenolic resin system is generally selected as the panel prepreg, but the phenolic resin releases formaldehyde toxic gas in the manufacturing and using processes, so that the panel prepreg is not friendly to the environment.
The prior aramid fiber honeycomb sandwich structure composite material applied to aviation interior decoration is mainly a phenolic resin system, and gradually faces to be replaced due to formaldehyde gas release. The honeycomb sandwich structure compression molding mainly uses manual paving and vacuum bag compacting as main completion prefabricated body, and the manual and auxiliary consumable material investment is large, so that a large amount of auxiliary consumable material garbage is caused, and the production efficiency is low.
Accordingly, the inventors provide a method of forming an epoxy flame retardant sandwich structured composite.
Disclosure of Invention
(1) Technical problem to be solved
The embodiment of the application provides a molding method of an epoxy flame-retardant sandwich structure composite material, which solves the technical problems of large labor and auxiliary material investment and low production efficiency of the prior aramid honeycomb sandwich structure composite material applied to aviation interior decoration.
(2) Technical proposal
The application provides a molding method of an epoxy flame-retardant sandwich structure composite material, which comprises the following steps:
the upper surface and the lower surface of the upper panel and the lower panel are respectively stuck with a piece of isolating paper/film;
placing an aramid paper honeycomb on the adhesive film surface of the lower panel, and placing the adhesive film surface of the upper panel on the surface of the aramid paper honeycomb to form a sandwich structure;
pre-pressing the mould with the sandwich structure under a first set condition;
carrying out curing treatment on the pre-compacted die under a second set condition;
and demolding the cured mold to obtain the epoxy flame-retardant sandwich structure composite material.
Further, the upper panel and the lower panel comprise Tedlar films, prepregs and adhesive films which are stacked in sequence.
Further, the reinforcing fiber of the prepreg is continuous, the reinforcing fiber is any one of glass fiber and carbon fiber, and the fiber cloth is a unidirectional tape or various fabrics.
Further, the matrix resin of the prepreg is a medium-temperature curing epoxy system and has flame-retardant property.
Further, the mass content of the matrix resin in the prepreg is 40±3%.
Further, the resin system of the adhesive film is the same as the resin system of the prepreg, and the surface density of the resin system of the adhesive film is 200-300 g/m 2 。
Further, the pre-pressing treatment is performed on the mold with the sandwich structure placed under a first set condition, specifically:
transferring the die to a pre-pressing machine by using a transfer platform, and placing one die on each layer; wherein the pre-pressing pressure is 0.3-0.8 Mpa, the temperature is 80+/-3 ℃, and the constant temperature time is 10-30 min.
Further, the maximum mold locking force of the pre-pressing machine is more than or equal to 250T, the temperature rising/reducing speed is 1-3 ℃/min, the temperature uniformity is +/-3 ℃, and the pressure uniformity is +/-1%.
Further, the pre-compacted die is cured under a second set condition, specifically:
transferring the pre-compacted die to a curing press by using a transfer platform, and placing one die on each layer; wherein the curing pressure is 0.8-1.8 Mpa, the temperature is 130+/-5 ℃, and the constant temperature time is 10-30 min.
Further, the maximum mold locking force of the curing press is more than or equal to 500T, the temperature rising/reducing speed is 1-3 ℃/min, the temperature uniformity is +/-3 ℃, and the pressure uniformity is +/-1%.
(3) Advantageous effects
In conclusion, the application replaces a large amount of manual work through equipment automation to form a high-efficiency circulating flow production line, the panel compounding process can continuously provide the composite panels with required layering structures and sizes, and the sandwich structure combining, pre-pressing, press curing, demolding and other processes form closed circulating operation, so that resources are effectively utilized, and the efficiency is improved.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the embodiments of the present application will be briefly described below, and it is obvious that the drawings described below are only some embodiments of the present application, and other drawings may be obtained according to these drawings without inventive effort to a person of ordinary skill in the art.
FIG. 1 is a schematic flow chart of a method for molding an epoxy flame retardant sandwich structure composite material according to an embodiment of the application;
FIG. 2 is a schematic diagram of an epoxy flame retardant sandwich structure provided by an embodiment of the present application;
fig. 3 is a schematic structural diagram of an upper panel/lower panel of an epoxy flame retardant sandwich structure according to an embodiment of the present application.
In the figure:
1-an upper panel; 101-Tedlar film; 102-prepreg; 103-an adhesive film; 2-a lower panel; 3-aramid paper honeycomb.
Detailed Description
Embodiments of the present application are described in further detail below with reference to the accompanying drawings and examples. The following detailed description of the embodiments and the accompanying drawings are provided to illustrate the principles of the application and are not intended to limit the scope of the application, i.e., the application is not limited to the embodiments described.
It should be noted that, without conflict, the embodiments of the present application and features of the embodiments may be combined with each other. The application will be described in detail below with reference to the drawings in connection with embodiments.
Fig. 1 is a schematic flow chart of a method for forming an epoxy flame retardant sandwich structure composite material according to an embodiment of the present application, as shown in fig. 1, the method may include the following steps:
s100, attaching isolation paper/films on the upper surface and the lower surface of the upper panel and the lower panel;
s200, placing an aramid paper honeycomb on the adhesive film surface of the lower panel, and placing the adhesive film surface of the upper panel on the surface of the aramid paper honeycomb to form a sandwich structure;
s300, pre-pressing the mold with the sandwich structure under a first set condition;
s400, curing the pre-compacted die under a second set condition;
s500, demolding the cured mold to obtain the epoxy flame-retardant sandwich structure composite material.
In the above embodiment, in step S200, the sandwich structure includes the upper/lower composite panel and the aramid paper honeycomb. Removing the isolation paper/film on the surface of the lower panel, grabbing the adhesive film face upwards by a mechanical arm into a lower die cavity, placing aramid paper honeycomb on the adhesive film face upwards, removing the isolation paper/film on the surface of the upper panel, grabbing the adhesive film face downwards by the mechanical arm to the honeycomb surface, and finishing the combination of the sandwich structure, namely attaching the aramid paper honeycomb to the lower surface of the upper panel and the upper surface of the lower panel; the upper die and the lower die of the die are assembled.
The thickness of the aramid paper honeycomb has a certain relation with the thickness of the sandwich structure, and the honeycomb grid can be embedded into the panel material in the pressurizing and curing process of the honeycomb sandwich structure to be effectively combined, so that the thickness of the honeycomb is increased by 0.5-1 mm compared with the theoretical estimated thickness.
In step S500, the cured mold is transferred to the demolding area by using the transfer platform, and after the temperature of the mold is reduced to below 80 ℃, the upper mold is removed, the product is taken out, and the upper/lower surfaces of the product are protected from scratches, bruises, and the like. The mold is cycled back to the sandwich assembly process.
The environment-friendly epoxy flame-retardant resin system prepreg is selected, optimized technological parameters are adopted, an automatic and efficient circulating flow water production line is utilized, the flame retardance of the honeycomb sandwich structure is rapidly molded by compression molding, and the requirements on navigability and key performance meet the index are met. The molding cycle of the honeycomb sandwich structure can be further shortened and the productivity can be improved by selecting quick curing and epoxy flame-retardant prepreg molding.
The upper/lower panels of the composite honeycomb sandwich structure of the laminating machine are utilized, the manipulator is used for completing honeycomb sandwich structure combination, die/product transfer, the prepressing press and the curing press are set to be constant in temperature and constant in pressure, the equipment state is unchanged, the products flow orderly, resources are effectively utilized, annular circulation is formed, automation and mass production industrialization are realized, and the production efficiency is further improved.
The flame retardant property of the aramid fiber honeycomb sandwich structure composite material meets the relevant requirements of seaworthiness 25.853 a), 25.853d and annex F.
As an alternative embodiment, the upper and lower panels each comprise Tedlar film, prepreg and adhesive film stacked in sequence. The prepreg and the adhesive film are generally required to be used in an environment with the temperature of 15-27 ℃ and the humidity of less than or equal to 80%, the whole material is arranged on a material frame in a material frame area of a laminating machine according to the panel layering sequence, and the width of raw materials can be widened by 10-20 mm compared with the width of products, so that the raw materials are used as the process allowance; the material rack area is also provided with an auxiliary material rack of the isolating paper/film, the rotation direction of the auxiliary material rack is opposite to that of the material rack, the isolating paper/film on the upper/lower surface of the material is recovered, the isolating paper/film on the upper/lower surface of the composite panel is reserved, the panel can be protected, and the composite panel is stored more conveniently; the multi-layer materials are conveyed to a roller nip with adjustable temperature for compounding after being overlapped, the speed of the roller is controlled to be 2-4 m/min according to the temperature sticking performance of a resin system of different prepregs, the temperature can be adjusted within the range of room temperature to 60 ℃, and the proper temperature is provided to be beneficial to improving the interlayer laminating performance of the materials; conveying the composite panel to a slitting area, and slitting according to the length of the product; by analogy, the same lay-up structure may be continuously compounded.
The Tedlar polyvinyl fluoride film as the appearance layer is compounded on the surface of the upper/lower panel of the sandwich structure composite material, and the Tedlar film is white (can be adjusted according to the product requirement) and has the thickness of about 25 mu m and can be produced and imported in China.
As an alternative embodiment, the reinforcing fiber of the prepreg is continuous, the reinforcing fiber is any one of glass fiber and carbon fiber, and the fiber cloth is unidirectional tape or various fabrics; the matrix resin of the prepreg is a medium-temperature curing epoxy system and has flame-retardant property. The specific material of the prepreg is not limited, and the prepreg can meet the corresponding performance requirements of the composite material.
As an alternative embodiment, the mass content of the matrix resin in the prepreg is 40+/-3%, the resin system of the adhesive film is the same as that of the prepreg, and the surface density of the resin system of the adhesive film is 200-300 g/m 2 。
Specifically, the mass ratio of the matrix resin and the surface density of the resin system of the adhesive film are not limited, and are selected according to the relevant properties of the composite material to be actually molded.
As an alternative embodiment, the mold with the sandwich structure placed thereon is subjected to a pre-pressing treatment under a first set condition, specifically: transferring the mold to a pre-pressing machine by using a transfer platform, and placing one mold on each layer; wherein the pre-pressing pressure is 0.3-0.8 Mpa, the temperature is 80+/-3 ℃, and the constant temperature time is 10-30 min.
In the above embodiment, the pre-pressing pressure selection requirement can properly improve interlayer bonding property, and a certain space is reserved to facilitate resin flow so as to drive internal gas to flow out; the prepressing temperature selects a period with better resin fluidity, the viscosity of the fast curing resin is reduced to a platform at about 80 ℃, the resin is basically unchanged after being kept at the constant temperature for 60 minutes, the resin does not react, the product is heated uniformly along with the prolongation of the constant temperature time, and the gas in the product is discharged easily. The pressure, temperature and time of the pre-pressing machine are set unchanged, and the mold circularly flows.
Wherein, the die is preferably made of metal, and the surface finish of the upper die and the lower die is as follows: ra is less than or equal to 0.8 mu m, parallelism is less than or equal to 0.1mm, die stop strip movable blocks with different heights are arranged around the lower die, the height of each die stop strip movable block is set to be the lower limit of the thickness requirement of a product, the dual-function type die stop strip movable block has the dual functions of effectively controlling the thickness of the product and avoiding the product from collapsing when the pressure is overlarge.
As an alternative implementation mode, the maximum mold locking force of the pre-pressing machine is more than or equal to 250T, the rising/reducing speed is 1-3 ℃/min, the temperature uniformity is +/-3 ℃, and the pressure uniformity is +/-1%; the maximum mold locking force of the curing press is more than or equal to 500T, the temperature rising/reducing speed is 1-3 ℃/min, the temperature uniformity is +/-3 ℃, and the pressure uniformity is +/-1%. The number of layers in the pre-pressing and curing processes is not less than 3, and the size of the workbench surface is not less than 1300 x 2600mm.
As an alternative embodiment, the pre-compacted die is subjected to a curing treatment under a second set condition, specifically: transferring the pre-compacted die to a curing press by using a transfer platform, and placing one die on each layer; wherein the curing pressure is 0.8-1.8 Mpa, the temperature is 130+/-5 ℃, and the constant temperature time is 10-30 min.
In the above embodiment, the curing pressure is selected not to be higher than the steady-state compression strength of the aramid paper honeycomb, and the flatness of the honeycomb sandwich structure cannot be out of tolerance; the curing temperature is selected to be suitable for the reaction period of the fast curing resin, and the resin is fully reacted along with the prolongation of the constant temperature time. The mould is transferred from the pre-pressing press to the curing press, and the pressure relief process is the air release and exhaust process. The pressure, temperature and time setting of the curing press are unchanged, and the mold circularly flows.
After step S500, further step S600, checking/detecting: visual inspection of the outer surface for defects such as cracks, scratches, etc. are not allowed; detecting the thickness of the product by uniformly distributing the sampling points by using a height ruler or a caliper with the tolerance of +/-0.15 mm; the flatness of the product is detected by the detection platform, and the requirement is less than or equal to 2mm/m; the performance of the furnace samples was tested and the requirements are shown in Table 1.
TABLE 1 aramid honeycomb sandwich structural performance index requirement
The compression molding of the aramid fiber honeycomb sandwich structure composite material for the interior decoration of the aircraft toilet of a certain model is further described in detail.
Example 1
11mm aramid honeycomb sandwich structure composite material
1. Upper/lower panel composite: the concrete structure of the panel layer is 1 layer of Tedlar film and 2 layers of prepreg1201FR epoxy flame retardant system, glass fiber surface density 200g/m 2 /100g/m 2 ) +glue film (LWF-2C, areal density 240 g/m) 2 ) Compounding under the environment that the temperature is 15-27 ℃ and the humidity is less than or equal to 80%, mounting the whole material on a material frame in a material frame area of a laminating machine according to the panel layering sequence, wherein the width of the raw material is 1250mm; recycling the upper/lower isolation paper/film of the material by using an auxiliary material frame in the material frame area, and reserving the isolation paper/film on the upper/lower surface of the composite panel; after being overlapped, the multi-layer materials are conveyed to a roller press area for compounding, the speed of a roller is 2-4 m/min, and the temperature of the roller is set to be 35+/-2 ℃; conveying the composite panel to a slitting area, wherein the slitting length is 2500mm; similarly, the same ply structure is continuously compounded.
2. Sandwich structure combination: the sandwich structure comprises upper/lower composite panels, aramid paper honeycomb (ACCH-II-1.83-48, thickness 10.8 mm). Removing the isolation paper/film on the surface of the lower panel, grabbing the adhesive film face upwards by a mechanical arm into a lower die cavity, placing aramid paper honeycomb on the adhesive film face upwards, removing the isolation paper/film on the surface of the upper panel, grabbing the adhesive film face downwards by the mechanical arm to the honeycomb surface, and finishing the combination of the sandwich structure, namely attaching the aramid paper honeycomb to the lower surface of the upper panel and the upper surface of the lower panel; the upper die and the lower die of the die are assembled, and the height of the blocking strip movable block of the die is 10.85mm.
3. Prepressing: transferring the die onto a pre-pressing machine by using a transferring platform, and setting pre-pressing pressure, temperature and time: the pressure is set to be 0.5-0.6 Mpa, the temperature is set to be 80+/-3 ℃, and the constant temperature time is set to be 30min. The pressure, temperature and time of the pre-pressing machine are set unchanged, and the mold circularly flows.
4. And (3) curing by a press: the pre-compacted die is immediately transferred to a curing press by utilizing a transfer platform, and the curing pressure, temperature and time are set: the pressure was set at 1.2MPa, the temperature was set at 130.+ -. 5 ℃ and the holding time was 30min. The mold is transferred from the pre-press to the curing press. The pressure, temperature and time setting of the curing press are unchanged, and the mold circularly flows.
5. Demolding: and transferring the cured mold to a demolding area by using a transfer platform, removing the upper mold after the temperature of the mold is reduced to below 80 ℃, and taking out the product to protect the upper/lower surface of the product from scratches, bruises and the like. The mold is cycled back to the sandwich assembly process.
6. Inspection/detection: visually checking that the outer surface has no defects such as cracks, scratches and the like; the thickness of the product is 10.96-11.12 mm by using caliper uniform distribution point taking detection, so that the tolerance requirement is met; the flatness of the product detected by the detection platform is less than or equal to 1.2mm/m, so that the requirement is met; the performance of the as-furnace samples was measured and shown in Table 2.
Table 2 11mm aramid honeycomb sandwich structure Performance test
| Index item | Test standard | Unit (B) | Index requirements | Actual measurement value |
| Tensile strength in plane | GB/T1452-2005 | Mpa | ≥2.3 | 2.46 |
| Shear strength | GB/T1455-2005 | Mpa | ≥1.31 | 1.57 |
| Roller peel strength | GB/T1457-2005 | N·mm/mm | ≥36 | 41.5 |
| Areal density of | Sampling weighing calculation | Kg/m 2 | ≤2.18 | 2.06 |
Example 2
19mm aramid honeycomb sandwich structure composite material
1. Upper/lower panel composite: the concrete structure of the panel layer is 1 layer of Tedlar film and 2 layers of prepreg1212FR epoxy flame retardant system, glass fibre surface density 200g/m 2 /100g/m 2 ) +glue film (LWF-2C, areal density 240 g/m) 2 ) Compounding under the environment that the temperature is 15-27 ℃ and the humidity is less than or equal to 80%, mounting the whole material on a material frame in a material frame area of a laminating machine according to the panel layering sequence, wherein the width of the raw material is 1250mm; recycling the upper/lower isolation paper/film of the material by using an auxiliary material frame in the material frame area, and reserving the isolation paper/film on the upper/lower surface of the composite panel; after being overlapped, the multi-layer materials are conveyed to a roller press area for compounding, the speed of a roller is 2-4 m/min, and the temperature of the roller is set to be 35+/-2 ℃; conveying the composite panel to a slitting area, wherein the slitting length is 2500mm; similarly, the same ply structure is continuously compounded.
2. Sandwich structure combination: the sandwich structure comprises upper/lower composite panels, aramid paper honeycomb (NH-I-1.83-48, thickness 18.8 mm). Removing the isolation paper/film on the surface of the lower panel, grabbing the adhesive film face upwards by a mechanical arm into a lower die cavity, placing aramid paper honeycomb on the adhesive film face upwards, removing the isolation paper/film on the surface of the upper panel, grabbing the adhesive film face downwards by the mechanical arm to the honeycomb surface, and finishing the combination of the sandwich structure, namely attaching the aramid paper honeycomb to the lower surface of the upper panel and the upper surface of the lower panel; the upper die and the lower die of the die are assembled, and the height of the blocking strip movable block of the die is 18.85mm.
3. Prepressing: transferring the die onto a pre-pressing machine by using a transferring platform, and setting pre-pressing pressure, temperature and time: the pressure is set to be 0.6-0.7 Mpa, the temperature is set to be 80+/-3 ℃, and the constant temperature time is set to be 30min. The pressure, temperature and time of the pre-pressing machine are set unchanged, and the mold circularly flows.
4. And (3) curing by a press: the pre-compacted die is immediately transferred to a curing press by utilizing a transfer platform, and the curing pressure, temperature and time are set: the pressure was set at 1.4MPa, the temperature was set at 130.+ -. 5 ℃ and the holding time was 120min. The mold is transferred from the pre-press to the curing press. The pressure, temperature and time setting of the curing press are unchanged, and the mold circularly flows.
5. Demolding: and transferring the cured mold to a demolding area by using a transfer platform, removing the upper mold after the temperature of the mold is reduced to below 80 ℃, and taking out the product to protect the upper/lower surface of the product from scratches, bruises and the like. The mold is cycled back to the sandwich assembly process.
6. Inspection/detection: visually checking that the outer surface has no defects such as cracks, scratches and the like; the caliper is used for uniformly distributing the sampling points to detect the thickness of the product to be 18.91-19.05 mm, so that the tolerance requirement is met; the flatness of the product detected by the detection platform is less than or equal to 1.5mm/m, so that the requirement is met; the performance of the as-furnace samples was measured and shown in Table 3.
TABLE 3 19mm aramid honeycomb sandwich structure Performance test
| Index item | Test standard | Unit (B) | Index requirements | Actual measurement value |
| Tensile strength in plane | GB/T1452-2005 | Mpa | ≥2.3 | 2.34 |
| Shear strength | GB/T1455-2005 | Mpa | ≥1.17 | 1.25 |
| Roller peel strength | GB/T1457-2005 | N·mm/mm | ≥36 | 47.8 |
| Areal density of | Sampling weighing calculation | Kg/m 2 | ≤2.55 | 2.47 |
It should be understood that, in the present specification, each embodiment is described in an incremental manner, and the same or similar parts between the embodiments are all referred to each other, and each embodiment is mainly described in a different point from other embodiments. The application is not limited to the specific steps and structures described above and shown in the drawings. Also, a detailed description of known method techniques is omitted here for the sake of brevity.
The above is only an example of the present application and is not limited to the present application. Various modifications and alterations of this application will become apparent to those skilled in the art without departing from the scope of this application. Any modification, equivalent replacement, improvement, etc. which come within the spirit and principles of the application are to be included in the scope of the claims of the present application.
Claims (10)
1. The method for forming the epoxy flame-retardant sandwich structure composite material is characterized by comprising the following steps of:
the upper surface and the lower surface of the upper panel and the lower panel are respectively stuck with a piece of isolating paper/film;
placing an aramid paper honeycomb on the adhesive film surface of the lower panel, and placing the adhesive film surface of the upper panel on the surface of the aramid paper honeycomb to form a sandwich structure;
pre-pressing the mould with the sandwich structure under a first set condition;
carrying out curing treatment on the pre-compacted die under a second set condition;
and demolding the cured mold to obtain the epoxy flame-retardant sandwich structure composite material.
2. The method of claim 1, wherein the upper and lower panels each comprise Tedlar film, prepreg, and adhesive film stacked in sequence.
3. The method for forming the epoxy flame-retardant sandwich structure composite material according to claim 2, wherein the reinforcing fibers of the prepreg are continuous, the reinforcing fibers are any one of glass fibers and carbon fibers, and the fiber cloth is a unidirectional tape or various fabrics.
4. The method for molding an epoxy flame-retardant sandwich structure composite material according to claim 2, wherein the matrix resin of the prepreg is a medium-temperature cured epoxy system and has flame-retardant property.
5. The method for molding an epoxy flame retardant sandwich structure composite material according to claim 4, wherein the mass content of the matrix resin in the prepreg is 40±3%.
6. The method for molding an epoxy flame-retardant sandwich structure composite material according to claim 2, wherein the resin system of the adhesive film is the same as the resin system of the prepreg, and the areal density of the resin system of the adhesive film is 200-300 g/m 2 。
7. The method for molding an epoxy flame retardant sandwich structure composite material according to claim 1, wherein the pre-pressing treatment is performed on the mold with the sandwich structure placed under a first set condition, specifically:
transferring the die to a pre-pressing machine by using a transfer platform, and placing one die on each layer; wherein the pre-pressing pressure is 0.3-0.8 Mpa, the temperature is 80+/-3 ℃, and the constant temperature time is 10-30 min.
8. The method for molding the epoxy flame-retardant sandwich structure composite material according to claim 7, wherein the maximum mold locking force of the pre-pressing machine is more than or equal to 250T, the temperature rising/reducing speed is 1-3 ℃/min, the temperature uniformity is +/-3 ℃, and the pressure uniformity is +/-1%.
9. The method for forming an epoxy flame retardant sandwich structure composite material according to claim 1, wherein the pre-compacted mold is cured under a second set condition, specifically:
transferring the pre-compacted die to a curing press by using a transfer platform, and placing one die on each layer; wherein the curing pressure is 0.8-1.8 Mpa, the temperature is 130+/-5 ℃, and the constant temperature time is 10-30 min.
10. The method for molding the epoxy flame-retardant sandwich structure composite material according to claim 9, wherein the maximum mold locking force of the curing press is not less than 500T, the temperature rising/reducing speed is 1-3 ℃/min, the temperature uniformity is +/-3 ℃, and the pressure uniformity is +/-1%.
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