CN115214206A - Preparation method of composite material sandwich board - Google Patents

Preparation method of composite material sandwich board Download PDF

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Publication number
CN115214206A
CN115214206A CN202110430734.3A CN202110430734A CN115214206A CN 115214206 A CN115214206 A CN 115214206A CN 202110430734 A CN202110430734 A CN 202110430734A CN 115214206 A CN115214206 A CN 115214206A
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CN
China
Prior art keywords
skin
prepreg
honeycomb core
adhesive film
sandwich panel
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CN202110430734.3A
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Chinese (zh)
Inventor
杨维学
卫平
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Shanghai Teyi Silk Road Vehicle Equipment Co ltd
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Shanghai Teyi Silk Road Vehicle Equipment Co ltd
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Priority to CN202110430734.3A priority Critical patent/CN115214206A/en
Publication of CN115214206A publication Critical patent/CN115214206A/en
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B27/00—Layered products comprising a layer of synthetic resin
    • B32B27/06—Layered products comprising a layer of synthetic resin as the main or only constituent of a layer, which is next to another layer of the same or of a different material
    • B32B27/10—Layered products comprising a layer of synthetic resin as the main or only constituent of a layer, which is next to another layer of the same or of a different material of paper or cardboard
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B27/00—Layered products comprising a layer of synthetic resin
    • B32B27/12—Layered products comprising a layer of synthetic resin next to a fibrous or filamentary layer
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B27/00—Layered products comprising a layer of synthetic resin
    • B32B27/38—Layered products comprising a layer of synthetic resin comprising epoxy resins
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B29/00—Layered products comprising a layer of paper or cardboard
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
    • B32B3/10—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material
    • B32B3/12—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material characterised by a layer of regularly- arranged cells, e.g. a honeycomb structure
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
    • B32B37/06—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the heating method
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
    • B32B37/10—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the pressing technique, e.g. using action of vacuum or fluid pressure
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
    • B32B37/12—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by using adhesives
    • B32B37/1207—Heat-activated adhesive
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/22—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed
    • B32B5/24—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer
    • B32B5/26—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer another layer next to it also being fibrous or filamentary
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B7/00—Layered products characterised by the relation between layers; Layered products characterised by the relative orientation of features between layers, or by the relative values of a measurable parameter between layers, i.e. products comprising layers having different physical, chemical or physicochemical properties; Layered products characterised by the interconnection of layers
    • B32B7/04—Interconnection of layers
    • B32B7/12—Interconnection of layers using interposed adhesives or interposed materials with bonding properties
    • 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
    • B64C1/18—Floors
    • B64C1/20—Floors specially adapted for freight
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
    • B32B37/12—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by using adhesives
    • B32B37/1207—Heat-activated adhesive
    • B32B2037/1215—Hot-melt adhesive
    • B32B2037/1223—Hot-melt adhesive film-shaped
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
    • B32B2262/10—Inorganic fibres
    • B32B2262/101—Glass fibres
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/50—Properties of the layers or laminate having particular mechanical properties
    • B32B2307/558—Impact strength, toughness
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/70—Other properties
    • B32B2307/714—Inert, i.e. inert to chemical degradation, corrosion
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/70—Other properties
    • B32B2307/718—Weight, e.g. weight per square meter
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2605/00—Vehicles
    • B32B2605/18—Aircraft
    • 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

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  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Laminated Bodies (AREA)

Abstract

The invention provides a preparation method of a composite sandwich plate, which comprises the steps of unfreezing prepreg, preparing honeycomb, blanking, grouping prepreg, laying, curing and inspecting, wherein a first skin and a second skin are obtained by stacking multiple layers of prepreg, the prepreg is made of phenolic resin impregnated glass fiber materials, the first skin and the second skin form the surface of the composite sandwich plate, an aramid paper honeycomb core forms the inner layer of the composite sandwich plate, and the thickness of the first skin is larger than that of the second skin. Compared with the prior art, the invention enhances the electrochemical corrosion resistance of the composite sandwich panel, improves the impact resistance of the composite sandwich panel and reduces the weight of the composite sandwich panel through the setting.

Description

Preparation method of composite material sandwich board
Technical Field
The invention relates to the technical field of composite materials and aerospace, in particular to a preparation method of a composite material sandwich panel.
Background
Air transportation is one of the central links of logistics and is also one of the most important functions of modern logistics activities. With the development of the aviation industry, particularly the rise of the industry of large airplanes made in China, the demand of the industry for matching airplane parts is gradually increased, and the cargo compartment floor is an important part. The aviation cargo compartment floor firstly meets the performance requirements of aviation airworthiness regulations, such as flame retardance, low smoke, low toxicity, flame burnthrough resistance, flame spread resistance and the like. Secondly, excellent mechanical properties and durability should be satisfied, including: compressive strength, bending strength and deformation, insert shear strength, impact strength, performance stability in hot and humid environments. Again, it should meet the weight requirements to minimize the weight per unit area of the floor.
The existing aircraft cargo compartment floor is mostly of an aluminum alloy metal structure, has large area weight and poor sound insulation performance, has potential difference with an aircraft fuselage metal structure, and is easy to generate the phenomenon of corrosion of a contact surface after long-term use, so the improvement is needed urgently.
Disclosure of Invention
The invention mainly aims to provide a preparation method of a composite sandwich panel, aiming at enhancing the electrochemical corrosion resistance of the composite sandwich panel, improving the impact resistance of the composite sandwich panel and reducing the weight of the composite sandwich panel.
In order to achieve the above object, the present invention provides a method for preparing a composite material sandwich panel, wherein the method for preparing the composite material sandwich panel comprises:
step one, thawing a prepreg: taking out the prepreg from a refrigeration house with the temperature lower than-18 ℃ and standing in an environment with the temperature of 18-26 ℃ for more than 8 hours, wherein the prepreg is prepared by impregnating glass fiber with phenolic resin;
step two, cellular preparation: cleaning and drying the aramid fiber paper honeycomb core to obtain a clean and dry aramid fiber paper honeycomb core;
step three, blanking: respectively cutting the multiple layers of the prepreg, the first adhesive film, the second adhesive film and the aramid fiber paper honeycomb core to preset sizes so as to enable the lengths and the widths of the prepreg, the first adhesive film, the second adhesive film and the aramid fiber paper honeycomb core to be the same;
step four, grouping the prepregs: stacking a plurality of layers of the prepreg to obtain a first skin and a second skin, wherein the number of layers of the prepreg of the first skin is larger than that of the prepreg of the second skin;
step five, paving: sequentially overlapping the first skin, the first adhesive film, the aramid paper honeycomb core, the second adhesive film and the second skin;
step six, curing: placing the laid first skin, the laid first adhesive film, the laid aramid paper honeycomb core, the laid second adhesive film and the laid second skin into a hot press for curing to obtain a composite material sandwich plate, wherein the temperature range of the hot press is 120-50 ℃, and the pressure range of the hot press is 0.2-0.35Mpa;
step seven, checking: and (5) checking whether the surface of the composite sandwich plate is bulged, debonded and scratched.
In an embodiment of the present invention, between the step four and the step five, the method further includes: and placing the first skin and the second skin into a hot press for curing, wherein the temperature range of the hot press is 120-50 ℃, and the pressure range of the hot press is 0.2-0.35Mpa.
In an embodiment of the present invention, the fourth step includes: stacking a plurality of layers of the prepregs one by one to obtain the first skin and the second skin, a portion of one prepreg being superimposed on the other prepreg in two adjacent layers.
In an embodiment of the present invention, the second step includes:
compressing and drying air, and then blowing the air to the surface and the cells of the aramid fiber paper honeycomb core to obtain a clean aramid fiber paper honeycomb core;
and (3) drying the clean aramid fiber paper honeycomb core in an oven, wherein the drying time is within the range of 1-1.5 hours, and the drying temperature is within the range of 100-120 ℃, so as to obtain the clean and dry aramid fiber paper honeycomb core.
In an embodiment of the present invention, the third step, the fourth step and the fifth step are performed in a clean room, the temperature of the clean room is in a range of 18 to 24 ℃, and the humidity of the clean room is in a range of 0 to 60%.
In an embodiment of the present invention, the sixth step further includes: first covering with the looks dorsal part of second covering all covers from type paper, and the edge of first covering and the edge of second covering are located corresponding edge from type paper respectively inside, first covering with arbitrary position in the edge of arbitrary one in the second covering with correspond the interval between the corresponding position in the edge of type paper is more than 100 mm.
In one embodiment of the invention, the aramid fiber paper honeycomb core is composed of aramid fiber paper and phenolic resin, and the compression strength of the aramid fiber paper honeycomb core is greater than or equal to 10Mpa.
In an embodiment of the invention, the first adhesive film and the second adhesive film are made of flame-retardant epoxy resin, and the gram weights of the first adhesive film and the second adhesive film are both less than 200g/m 2 。
In one embodiment of the present invention, the grammage of the glass fibers in the prepreg is 300g/m 2 The tensile modulus of the glass fiber in the prepreg is greater than 2890000psi, and the volume content of the phenolic resin in the prepreg is 40-45%.
In an embodiment of the present invention, between the sixth step and the seventh step, further comprising: and cutting the composite material sandwich board to a preset size.
According to the technical scheme, a first skin and a second skin are obtained by stacking a plurality of layers of prepreg, the prepreg is made of phenolic resin impregnated glass fibers, the first skin and the second skin form the surface of the composite sandwich plate, and the aramid paper honeycomb core forms the inner layer of the composite sandwich plate. Compared with the prior art, the conductive performance of the composite material sandwich panel is weakened, the electrochemical corrosion resistance of the composite material sandwich panel is enhanced, the impact resistance of the composite material sandwich panel is improved, and the weight of the composite material sandwich panel is reduced through the setting.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.
FIG. 1 is a flow chart of a method of making a composite sandwich panel according to the present invention;
FIG. 2 is a schematic structural view of an embodiment of the composite sandwich panel of the present invention;
FIG. 3 is a schematic structural view of an embodiment of an aramid paper honeycomb core of the present invention;
fig. 4 is a schematic view of a structure in which a plurality of prepregs are stacked according to the present invention.
The reference numbers illustrate:
Figure BDA0003031261200000031
Figure BDA0003031261200000041
the implementation, functional features and advantages of the objects of the present invention will be further explained with reference to the accompanying drawings.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the 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.
It should be noted that all the directional indicators (such as upper, lower, left, right, front, and rear … …) in the embodiment of the present invention are only used to explain the relative position relationship between the components, the motion situation, and the like in a specific posture (as shown in the drawing), and if the specific posture is changed, the directional indicator is changed accordingly.
In addition, the descriptions related to "first", "second", etc. in the present invention are for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In addition, technical solutions between various embodiments may be combined with each other, but must be realized by a person skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination should not be considered to exist, and is not within the protection scope of the present invention.
Referring to fig. 1 to 4, the present invention provides a method for manufacturing a composite material sandwich panel, which includes:
step one, thawing the prepreg 100 a: the prepreg 100a is taken out from a freezer at a temperature of less than-18 ℃ and left standing in an environment at a temperature of 18-26 ℃ for 8 hours or more so that the temperature of the prepreg 100a is the same as the operating environment temperature.
The prepreg 100a is made of glass fibers impregnated with phenolic resin, and in the prepreg 100a, the weight of the glass fibers is about 300g/m < 2 >, the tensile modulus of the glass fibers is greater than 2890000psi, and the volume content of the phenolic resin is about 40% -45%.
Prepreg 100a is a composition of a resin matrix and reinforcement made by impregnating continuous fibers or fabrics with the resin matrix under strictly controlled conditions.
Specifically, this prepreg 100a is for 8 hours from the time of stewing after the freezer is taken out, so set up, can guarantee that the temperature of prepreg 100a can rise to with the operating environment temperature the same, prevent because the temperature difference leads to the prepreg surface to appear the steam condensation. The standing time after the prepreg 100a is taken out from the freezer may be 8.5 hours, 9.0 hours, 9.5 hours, or the like.
When the prepreg 100a is left to stand, the temperature in the environment is set according to the temperature of a refrigerator, and the lower the temperature of the refrigerator, the higher the temperature in the environment, for example: the freezer temperature is-18 ℃, the temperature in the environment is 18 ℃, and the other conditions are as follows: the freezer temperature is-25 deg.C and the ambient temperature is 23 deg.C, not to mention here.
Step two, cellular preparation: the aramid paper honeycomb core 130 is cleaned and dried to obtain a clean and dry aramid paper honeycomb core 130.
Specifically, air is compressed and dried and then blown to the surface and the cells of the aramid paper honeycomb core 130, and impurities and dust on the surface and in the cells of the aramid paper honeycomb core 130 are cleaned up to obtain a clean aramid paper honeycomb core 130; and (3) drying the clean aramid fiber paper honeycomb core 130 in an oven for 1-1.5 hours at the drying temperature of 100-120 ℃ to evaporate water in the aramid fiber paper honeycomb core 130 so as to obtain the clean and dry aramid fiber paper honeycomb core 130. Specifically, the drying time of clean aramid fiber paper honeycomb core 130 is 1.0 hour, so set up, can guarantee aramid fiber paper honeycomb core 130's stoving degree, can shorten drying time again.
The drying temperature is selected according to the humidity of the aramid paper honeycomb core 130, if the humidity of the aramid paper honeycomb core 130 is high, the drying temperature can be selected to be 118 ℃, 119 ℃ and the like, and if the humidity of the aramid paper honeycomb core 130 is low, the drying temperature can be selected to be 111 ℃, 112 ℃ and the like. The drying time is also selected according to the humidity of the aramid paper honeycomb core 130, and the larger the humidity of the aramid paper honeycomb core 130 is, the longer the drying time is.
Wherein, the air drying can be realized by an adsorption type compressed air dryer, and the moisture is adsorbed when the wet air passes through the adsorbent by utilizing the principle of pressure swing adsorption, so that the dry air without water vapor is obtained; the air drying may be performed by condensing moisture in the wet air and then separating out the condensed moisture from the air by using a principle of cooling the air and reducing the temperature of the air in a refrigeration type compressed air dryer to obtain dry air without water vapor.
The aramid fiber paper honeycomb core 130 is composed of aramid fiber paper and phenolic resin, the density of the aramid fiber paper honeycomb is larger than 100, and the compression strength of the aramid fiber paper honeycomb is larger than 10Mpa. The aramid paper honeycomb core 130 may be a meta-aramid paper honeycomb core 130, and the aramid paper honeycomb core 130 may also be a para-aramid paper honeycomb core 130, which is not specifically limited herein.
The cross section of the cells of the aramid paper honeycomb core 130 is regular hexagon, the diameter range of the inscribed circle of the regular hexagon is 0-4.8mm, and the structural strength of the aramid paper honeycomb core 130 is enhanced by the arrangement. Specifically, the diameter of the inscribed circle of the regular hexagon may be 3.2mm or 4.8mm, so that the cells on the aramid paper honeycomb core 130 are conveniently formed. In addition, the diameter of the regular hexagon inscribed circle can be any other value from 0mm to 4.8 mm. In addition, the cross section of the cells of the aramid paper honeycomb core 130 may also be rectangular.
The thickness of the aramid paper honeycomb core 130 is 5-25mm, and by the arrangement, the structural strength of the composite material sandwich plate 100 can be guaranteed, and the thickness of the composite material sandwich plate 100 can be reduced. Specifically, the thickness of the aramid paper honeycomb core 130 may be any length value between 5mm, 25mm, and 5-25mm, and in the actual use process, the thickness of the aramid paper honeycomb core 130 is selected according to the application environment of the composite sandwich panel 100.
Step three, blanking: the multilayer prepreg 100a, the first adhesive film 120, the second adhesive film 140 and the aramid paper honeycomb core 130 are respectively cut to preset sizes so that the lengths and the widths of the prepregs are the same.
Specifically, the multilayer prepreg 100a, the first adhesive film 120, the second adhesive film 140, and the aramid paper honeycomb core 130 may be cut by a cutting machine, or the multilayer prepreg 100a, the first adhesive film 120, the second adhesive film 140, and the aramid paper honeycomb core 130 may be cut by a pair of scissors manually, which is not listed here.
Step four, grouping the prepregs 100 a: the multiple layers of prepreg 100a are stacked to obtain a first skin 110 and a second skin 150.
Specifically, the multilayer prepreg 100a is divided into two parts to be stacked, the two parts are correspondingly formed into the first skin 110 and the second skin 150, the number of layers of the prepreg 100a of the first skin 110 is greater than that of the prepreg 100a of the second skin 150, and therefore, after the first skin 110 and the second skin 150 are processed through the same process, the thickness of the first skin 110 can be greater than that of the second skin 150.
The first skin 110 serves as a bearing surface for the composite sandwich panel 100, which enhances the impact resistance of the composite sandwich panel 100. Moreover, compared with the traditional sandwich panel in which the same surface layers are adopted on the two sides, the thickness of the second skin 150 is smaller than that of the first skin 110, so that the weight of the second skin 150 is smaller than that of the first skin 110, and the weight of the composite sandwich panel 100 is further reduced.
Specifically, the first skin 110 includes 4-5 plies of prepreg 100a and the second skin 150 includes 2-3 plies of prepreg 100a. The first skin 110 may include 4 layers of prepregs 100a, the first skin 110 may also include 5 layers of prepregs 100a, the second skin 150 may include 2 layers of prepregs 100a, and the second skin 150 may include 3 layers of prepregs 100a. In the actual processing process, the number of layers of the prepreg 100a in the first skin 110 and the number of layers of the prepreg 100a in the second skin 150 both depend on the preset strength of the composite sandwich panel 100, and the higher the preset strength of the composite sandwich panel 100 is, the higher the number of layers of the prepreg 100a in the first skin 110 and the number of layers of the prepreg 100a in the second skin 150 are.
Step five, paving: the first skin 110, the first adhesive film 120, the aramid paper honeycomb core 130, the second adhesive film 140 and the second skin 150 are sequentially stacked.
Specifically, the first adhesive film 120 and the second adhesive film 140 are epoxy adhesive films, have good, consistent and uniform adhesion, can be cut into precise shapes and sizes, are suitable for purely manual or automatic application, and are widely used for bonding various fabrics, paper, high polymer materials and metals.
Specifically, first covering 110, first glued membrane 120, aramid paper honeycomb core 130, second glued membrane 140 and second covering 150 all are the rectangle setting, and five length, width homoenergetic equal, and five length direction's both ends flush mutually, and five width direction's both ends flush mutually, so set up, not only can conveniently process preparation combined material sandwich panel 100, but also can conveniently splice polylith combined material sandwich panel 100 together.
In addition, the first skin 110, the first adhesive film 120, the aramid paper honeycomb core 130, the second adhesive film 140, and the second skin 150 may be arranged in regular shapes such as a circle, a trapezoid, a diamond, an ellipse, and a circular ring, and the first skin 110, the first adhesive film 120, the aramid paper honeycomb core 130, the second adhesive film 140, and the second skin 150 may be arranged in irregular shapes such as a circle with a notch at the edge.
Further, the third step, the fourth step and the fifth step are carried out in a clean room, the temperature range of the clean room is 18-24 ℃, and the humidity range of the clean room is 0-60%, so that on one hand, the cleanliness of the external environment in the laying process of the first skin 110, the aramid paper honeycomb core 130 and the second skin 150 can be ensured, and further, impurities such as dust in the external environment can be prevented from entering between the first skin 110 and the aramid paper honeycomb core 130 and between the second skin 150 and the aramid paper honeycomb core 130, on the other hand, the humidity of the external environment in the laying process of the first skin 110, the aramid paper honeycomb core 130 and the second skin 150 can be ensured to be lower, and further, the aramid paper honeycomb core 130 can be kept dry.
Step six, curing: and (3) placing the laid first skin 110, the first adhesive film 120, the aramid paper honeycomb core 130, the second adhesive film 140 and the second skin 150 into a hot press for curing to obtain the composite material sandwich plate 100, wherein the temperature range of the hot press is 120-150 ℃, the heat preservation time is 60-90 minutes, the pressure range of the hot press is 0.2-0.35Mpa, and the hot press is a flat plate hot press.
The temperature and the heat preservation time of the hot press are opposite in trend and depend on the curing performance of resin in the laid prepreg and the adhesive film, and generally, the curing time is shorter as the curing temperature is higher.
It should be noted that, both the first skin 110 and the second skin 150 may be uncured, and both the first skin 110 and the second skin 150 may also be cured, which is not limited herein.
Step seven, checking: the surface of the composite sandwich panel 100 was examined for bulges, debonding, and scratching.
The inspection can be manually completed, or the inspection can be completed by photographing and contrasting by a camera, which is not listed here.
Through the technical scheme, the first skin 110 and the second skin 150 are obtained by stacking the plurality of layers of prepregs 100a, the prepregs 100a are made of phenolic resin impregnated glass fibers, the first skin 110 and the second skin 150 form the surface of the composite sandwich panel 100, and the aramid paper honeycomb core 130 forms the inner layer of the composite sandwich panel 100. Compared with the prior art, the conductive performance of the composite material sandwich plate 100 is weakened through the setting, and the electrochemical corrosion resistance of the composite material sandwich plate 100 is further enhanced.
In view of the fact that the strength of the composite sandwich panel 100 can be enhanced by enhancing the strength of the first skin 110 and the strength of the second skin 150, in some embodiments of the invention, between step four and step five, the method further includes: and (3) placing the first skin 110 and the second skin 150 into a hot press for curing, wherein the temperature range of the hot press is 120-150 ℃, the pressure range of the hot press is 0.2-0.35Mpa, and the hot press is a flat plate hot press.
Through the technical scheme, on one hand, before the composite sandwich panel is laid, the first skin 110 and the second skin 150 are cured, and after the composite sandwich panel is laid, the first skin 110, the first adhesive film 120, the aramid paper honeycomb core 130, the second adhesive film 140 and the second skin 150 are cured, so that the strength of the first skin 110 and the strength of the second skin 150 can be enhanced through twice curing of the first skin 110 and the second skin 150, and further the strength of the composite sandwich panel 100 is enhanced.
Compared with the mode that the first skin 110 and the second skin 150 are cured once after being laid, the first skin 110 and the second skin 150 can be separately produced and processed by adopting the mode that the first skin 110 and the second skin 150 are cured once before and after being laid, and the first skin 110 and the second skin 150 can be conveniently organized and produced and processed.
Compared with the first skin 110 and the second skin 150 which are cured once before and after being laid, the first skin 110 and the second skin 150 are cured once after being laid, so that the curing process is simple and efficient.
To facilitate the fabrication of larger sized composite sandwich panels 100, in some embodiments of the present invention, referring to fig. 1-4, step four includes: multiple layers of prepregs 100a are stacked one on top of the other to obtain a first skin 100 and a second skin 150, with a portion of one prepreg 100a being superimposed over the other prepreg 100a in two adjacent layers of prepregs 100a.
Specifically, two ends of the two adjacent layers of prepregs 100a in the width direction may be flush with each other, and at this time, the length of the overlapped part of the two adjacent layers of prepregs 100a in the length direction of the prepreg 100a is more than 20 mm; the two adjacent layers of prepregs 100a may have both ends in the longitudinal direction aligned, and in this case, the length of the portion where the two adjacent layers of prepregs 100a overlap in the width direction of the prepreg 100a is 20mm or more.
It should be noted that when two ends of the two adjacent layers of prepregs 100a in the width direction are flush, the lengths of the two adjacent layers of prepregs 100a may be equal or unequal; when the two ends of the two adjacent layers of prepregs 100a in the length direction are flush, the widths of the two adjacent layers of prepregs 100a may be equal or unequal.
Through the technical scheme, one part of one prepreg 100a in two adjacent layers of prepregs 100a is overlapped on the other prepreg 100a, so that the composite material sandwich panel 100 with a larger size is conveniently manufactured.
Considering that during the curing process, if the first skin 110 and the second skin 150 are both directly contacted with the flat plate of the hot press, it is easy to generate the situation that the first skin 110 and the second skin 150 are both bonded with the flat plate of the hot press, in one embodiment of the present invention, referring to fig. 1 to 4, step six further includes: the release paper covers opposite sides of the first skin 110 and the second skin 150, edges of the first skin 110 and edges of the second skin 150 are respectively located inside corresponding edges of the release paper, an edge of one release paper exceeds an edge of the first skin 110, an edge of the other release paper exceeds an edge of the second skin 150, the release paper is release paper which prevents the prepreg 100a from being adhered and can also protect the prepreg 100a from being polluted, and the distance between any position of any one of the edges of the first skin 110 and the second skin 150 and the corresponding position of the corresponding edge of the corresponding release paper is more than 100 mm.
Specifically, the distance between the corresponding position at the edge of the corresponding release paper and the arbitrary position at the edge of any one of the first skin 110 and the second skin 150 is 100mm, so that the size of the release paper can be reduced on the premise of ensuring that the flat plates of the first skin 110 and the hot press are bonded together and the flat plates of the second skin 150 and the hot press are bonded together, and the cost is saved. In addition, the distance between any position at the edge of any one of the first skin 110 and the second skin 150 and the corresponding position at the edge of the corresponding release paper may also be 150mm, 200mm, and the like.
It should be noted that the number of the release paper covered by the opposite back sides of the first skin 110 and the second skin 150 may be 1, 2, 3, 4, … … N, and N +1 … …, where N is a positive integer greater than zero, and is not limited specifically herein.
In addition, a release agent is sprayed on the surfaces of the first skin 110 and the second skin 150, so that at least one of the first skin 110 and the second skin 150 is prevented from being bonded with a flat plate of a hot press.
It should be noted that, when the first skin 110 and the second skin 150 are cured once before being laid, release paper may cover both sides of the first skin 110 in the thickness direction, and release paper covers both sides of the second skin 150 in the thickness direction, so that the first skin 110 and the flat plate of the hot press can be prevented from being bonded together, and the second skin 150 and the flat plate of the hot press can be prevented from being bonded together.
In order to enhance the flame retardancy of the composite sandwich panel 100, in some embodiments of the present invention, the materials of the first adhesive film 120 and the second adhesive film 140 are both flame retardant epoxy resin, and the grammage of each of the first adhesive film 120 and the second adhesive film 140 is less than 200.
The flame-retardant epoxy resin, also called self-extinguishing epoxy resin, is an epoxy resin containing a flame-retardant group or woollen with a flame retardant. The materials of the first adhesive film 120 and the second adhesive film 140 may only contain flame retardant epoxy resin, and the materials of the first adhesive film 120 and the second adhesive film 140 may also be a mixture of flame retardant epoxy resin and other substrates, which is not limited herein.
By the technical scheme, the composite sandwich plate 100 has the characteristics of flame retardance, low smoke fog, low toxicity, flame burnthrough resistance, flame spread resistance, light weight and environmental friendliness.
In view of the fact that the properties of the prepreg 100a will affect the structural strength of the first and second skins 110, 150, in some embodiments of the present invention, the grammage of the glass fibers in the prepreg 100a is 300, the tensile modulus of the glass fibers in the prepreg 100a is greater than 2890000psi, and the volume of the phenolic resin in the prepreg 100a is 40% -45%, so configured to ensure the structural strength of the first and second skins 110, 150.
Considering that the outer contour of the composite sandwich panel 100 changes in size after the composite sandwich panel 100 is cured, in order to machine the composite sandwich panel 100 to a predetermined size, in some embodiments of the invention, between step six and step seven, the method further includes: the composite sandwich panel 100 is cut to a predetermined size.
Specifically, a diamond saw blade with the diameter of 200mm is selected by using a sawing machine, and the composite material sandwich plate 100 is cut at the rotating speed of 2000 rpm. Further, the cured composite material sandwich panel 100 may be cut using a machining device such as a milling machine or a machining center.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention, and all equivalent structural changes made by using the contents of the present specification and the drawings, or any other related technical fields, which are directly or indirectly applied to the present invention, are included in the scope of the present invention.

Claims (10)

1. A method for preparing a composite material sandwich panel is characterized by comprising the following steps:
step one, thawing a prepreg: taking out the prepreg from a refrigeration house with the temperature lower than-18 ℃ and standing in an environment with the temperature of 18-26 ℃ for more than 8 hours, wherein the prepreg is prepared by impregnating glass fiber with phenolic resin;
step two, cellular preparation: cleaning and drying the aramid fiber paper honeycomb core to obtain a clean and dry aramid fiber paper honeycomb core;
step three, blanking: respectively cutting the multiple layers of the prepreg, the first adhesive film, the second adhesive film and the aramid fiber paper honeycomb core to preset sizes so as to enable the lengths and the widths of the prepreg, the first adhesive film, the second adhesive film and the aramid fiber paper honeycomb core to be the same;
step four, grouping the prepregs: stacking a plurality of layers of the prepreg to obtain a first skin and a second skin, wherein the number of layers of the prepreg of the first skin is larger than that of the prepreg of the second skin;
step five, paving: sequentially overlapping the first skin, the first adhesive film, the aramid paper honeycomb core, the second adhesive film and the second skin;
step six, curing: placing the first skin, the first adhesive film, the aramid paper honeycomb core, the second adhesive film and the second skin which are laid into a hot press for curing to obtain a composite material sandwich board, wherein the temperature range of the hot press is 120-50 ℃, and the pressure range of the hot press is 0.2-0.35Mpa;
step seven, checking: and (4) detecting whether the surface of the composite sandwich panel has bulges, debonding and scratches.
2. The method of making a composite sandwich panel according to claim 1, further comprising, between said step four and said step five: and placing the first skin and the second skin into a hot press for curing, wherein the temperature range of the hot press is 120-50 ℃, and the pressure range of the hot press is 0.2-0.35Mpa.
3. The method of making a composite sandwich panel according to claim 1, wherein said step four comprises: stacking a plurality of layers of the prepregs one by one to obtain the first skin and the second skin, wherein a part of one prepreg is overlapped on the other prepreg in two adjacent layers of the prepregs.
4. The method of making a composite sandwich panel according to claim 1 wherein step two comprises:
compressing and drying air, and then blowing the air to the surface and the cells of the aramid fiber paper honeycomb core to obtain a clean aramid fiber paper honeycomb core;
and (3) drying the clean aramid fiber paper honeycomb core in an oven, wherein the drying time is within the range of 1-1.5 hours, and the drying temperature is within the range of 100-120 ℃, so as to obtain the clean and dry aramid fiber paper honeycomb core.
5. The method of making a composite sandwich panel according to claim 1 wherein steps three, four and five are performed in a cleanroom having a temperature in the range of 18-24 ℃ and a humidity in the range of 0-60%.
6. The method of making a composite sandwich panel according to claim 1 wherein said sixth step further comprises: first covering with the looks dorsal part of second covering all covers from type paper, and the edge of first covering and the edge of second covering are located corresponding edge from type paper respectively inside, first covering with arbitrary position in the edge of arbitrary one in the second covering with correspond the interval between the corresponding position in the edge of type paper is more than 100 mm.
7. The method for preparing the composite sandwich panel according to claim 1, wherein the aramid paper honeycomb core is composed of aramid fiber paper and phenolic resin, and the compressive strength of the aramid paper honeycomb core is greater than or equal to 10Mpa.
8. The method for manufacturing the composite sandwich panel according to claim 1, wherein the first adhesive film and the second adhesive film are made of flame-retardant epoxy resin, and the gram weights of the first adhesive film and the second adhesive film are less than 200g/m 2 。
9. A method of making a composite sandwich panel according to claim 1 wherein the glass fibres in the prepreg have a grammage of 300g/m 2 The tensile modulus of the glass fiber in the prepreg is greater than 2890000psi, and the volume content of the phenolic resin in the prepreg is 40-45%.
10. The method of making a composite sandwich panel according to claim 1 further comprising, between said sixth step and said seventh step: and cutting the composite material sandwich board to a preset size.
CN202110430734.3A 2021-04-21 2021-04-21 Preparation method of composite material sandwich board Pending CN115214206A (en)

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