CN115157819A - Honeycomb wave-absorbing composite material and preparation method and application thereof - Google Patents

Honeycomb wave-absorbing composite material and preparation method and application thereof Download PDF

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Publication number
CN115157819A
CN115157819A CN202210818589.0A CN202210818589A CN115157819A CN 115157819 A CN115157819 A CN 115157819A CN 202210818589 A CN202210818589 A CN 202210818589A CN 115157819 A CN115157819 A CN 115157819A
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China
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wave
honeycomb
absorbing
composite material
core material
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Chinese (zh)
Inventor
孙新
王岩
张久霖
贺军哲
王伟强
董勤一
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Beijing Institute of Environmental Features
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Beijing Institute of Environmental Features
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Priority to CN202210818589.0A priority Critical patent/CN115157819A/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
    • B32B29/00—Layered products comprising a layer of paper or cardboard
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B31—MAKING ARTICLES OF PAPER, CARDBOARD OR MATERIAL WORKED IN A MANNER ANALOGOUS TO PAPER; WORKING PAPER, CARDBOARD OR MATERIAL WORKED IN A MANNER ANALOGOUS TO PAPER
    • B31D—MAKING ARTICLES OF PAPER, CARDBOARD OR MATERIAL WORKED IN A MANNER ANALOGOUS TO PAPER, NOT PROVIDED FOR IN SUBCLASSES B31B OR B31C
    • B31D3/00—Making articles of cellular structure, e.g. insulating board
    • B31D3/02—Making articles of cellular structure, e.g. insulating board honeycombed structures, i.e. the cells having an essentially hexagonal section
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B31—MAKING ARTICLES OF PAPER, CARDBOARD OR MATERIAL WORKED IN A MANNER ANALOGOUS TO PAPER; WORKING PAPER, CARDBOARD OR MATERIAL WORKED IN A MANNER ANALOGOUS TO PAPER
    • B31D—MAKING ARTICLES OF PAPER, CARDBOARD OR MATERIAL WORKED IN A MANNER ANALOGOUS TO PAPER, NOT PROVIDED FOR IN SUBCLASSES B31B OR B31C
    • B31D3/00—Making articles of cellular structure, e.g. insulating board
    • B31D3/02—Making articles of cellular structure, e.g. insulating board honeycombed structures, i.e. the cells having an essentially hexagonal section
    • B31D3/0284—Laminating honeycomb cores; applying cover sheets to core edges; working core edges
    • 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
    • B32B29/02—Layered products comprising a layer of paper or cardboard 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
    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form
    • B32B3/02—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by features of form at particular places, e.g. in edge regions
    • B32B3/08—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by features of form at particular places, e.g. in edge regions characterised by added members at particular parts
    • 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 form; Layered products 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 form; Layered products 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 form; Layered products 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
    • B32B37/12—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by using adhesives
    • B32B37/1284—Application of 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
    • B32B38/00—Ancillary operations in connection with laminating processes
    • 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
    • B32B38/00—Ancillary operations in connection with laminating processes
    • B32B38/08—Impregnating
    • 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
    • B32B38/00—Ancillary operations in connection with laminating processes
    • B32B38/16—Drying; Softening; Cleaning
    • B32B38/164—Drying
    • 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
    • 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
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/068—Fuselage sections
    • D—TEXTILES; PAPER
    • D21—PAPER-MAKING; PRODUCTION OF CELLULOSE
    • D21H—PULP COMPOSITIONS; PREPARATION THEREOF NOT COVERED BY SUBCLASSES D21C OR D21D; IMPREGNATING OR COATING OF PAPER; TREATMENT OF FINISHED PAPER NOT COVERED BY CLASS B31 OR SUBCLASS D21G; PAPER NOT OTHERWISE PROVIDED FOR
    • D21H27/00—Special paper not otherwise provided for, e.g. made by multi-step processes
    • D21H27/30—Multi-ply
    • D21H27/40—Multi-ply at least one of the sheets being non-planar, e.g. crêped
    • 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
    • B32B38/00—Ancillary operations in connection with laminating processes
    • B32B2038/0052—Other operations not otherwise provided for
    • B32B2038/0076—Curing, vulcanising, cross-linking
    • 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
    • B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
    • B32B2260/02—Composition of the impregnated, bonded or embedded layer
    • B32B2260/028—Paper 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
    • B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
    • B32B2260/04—Impregnation, embedding, or binder material
    • B32B2260/046—Synthetic resin
    • 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
    • B32B2307/20—Properties of the layers or laminate having particular electrical or magnetic properties, e.g. piezoelectric
    • B32B2307/212—Electromagnetic interference shielding

Abstract

The invention provides a honeycomb wave-absorbing composite material and a preparation method thereof, wherein the honeycomb wave-absorbing composite material comprises a skin and a honeycomb wave-absorbing core material; the honeycomb wave-absorbing core material is impregnated with wave-absorbing agent slurry, and pouring sealant is filled in honeycomb holes of the honeycomb wave-absorbing core material; the honeycomb wave-absorbing composite material prepared by the method can absorb electromagnetic wave energy on the premise of bearing structural mechanics, is a good wave-absorbing integrated composite material, and has wide application value in the field of aerocrafts.

Description

Honeycomb wave-absorbing composite material and preparation method and application thereof
Technical Field
The invention relates to the technical field of wave-absorbing materials, in particular to a honeycomb wave-absorbing composite material and a preparation method thereof.
Background
The composite material technology and the product thereof have unique advantages in light weight and high strength, and greatly promote the rapid progress of the aviation technology. Modern aircraft have a large number of edge structures at the periphery of the fuselage, which are subjected to large aerodynamic loads, which requires high mechanical load-bearing capacity of the material components; in addition, with the rapid development of modern radar technology, particularly the continuous enhancement of imaging capability, the method can perform imaging detection on various targets and provide clear outline information so as to further realize the detection and identification of the targets, the exposure of the outline information is mainly caused by the strong scattering characteristics of edge structures, and if effective measures are not taken in time, sensitive information such as self structural shapes and the like can be easily exposed.
At present, in traditional design and application work, the edge structure of the fuselage of the aerospace craft is usually made of metal materials or carbon fiber composite materials, and the two materials belong to reflectors of electromagnetic waves and are not beneficial to realizing absorption and loss of radar waves; the existing honeycomb wave-absorbing material has certain wave-absorbing performance, but the mechanical property is poor, and the existing honeycomb wave-absorbing material cannot bear severe aviation environment generally when being used as an edge structure, so that the invention provides a honeycomb wave-absorbing composite material and a preparation method thereof, which are used for solving the technical bottleneck faced by the development of the current advanced aviation aircraft.
Disclosure of Invention
The invention provides a honeycomb wave-absorbing composite material and a preparation method thereof, the preparation method is simple, the implementation period is short, the mass production and the application are convenient, and the prepared honeycomb wave-absorbing composite material has excellent mechanical bearing and electromagnetic wave absorption performance and can meet the application environment of an edge structure of an aviation aircraft.
In a first aspect, the invention provides a honeycomb wave-absorbing composite material, which comprises a skin and a honeycomb wave-absorbing core material; the wave absorbing core material is impregnated with wave absorbing agent slurry, and pouring sealant is filled in honeycomb holes of the wave absorbing core material.
Preferably, the skin is a glass fiber composite material or an aramid fiber composite material.
Preferably, the thickness of the skin is 0.5-2.0 mm.
Preferably, the honeycomb core material is aramid paper honeycomb material.
Preferably, the thickness of the honeycomb core material is 5-25 mm.
Preferably, the wave absorber slurry comprises a wave absorber, epoxy resin, a curing agent and an auxiliary agent; more preferably, in the wave absorber slurry, the mass ratio of the wave absorber, the epoxy resin, the curing agent and the auxiliary agent is (1-10): (60 to 85): (3-12): (0.5-5).
Preferably, the content of the wave absorbent slurry in the honeycomb wave absorbing core material is 300-500 g/m 2 。
Preferably, the wave absorbing agent is at least one of carbon black, carbon nanotubes, graphene or mesoporous carbon.
Preferably, the epoxy resin is bisphenol a type epoxy resin or bisphenol F type epoxy resin;
the curing agent is preferably an amine curing agent.
Preferably, the auxiliary agent is at least one of methyl cellulose, sodium carboxymethyl cellulose, SY-F7090H, disputer-S19 and BYK-181.
Preferably, the pouring sealant is a two-component epoxy resin adhesive or a two-component polyurethane adhesive.
Preferably, the skin is bonded with the honeycomb wave-absorbing core material through a glue film; more preferably, the adhesive film is a two-component epoxy resin adhesive.
In a second aspect, the present invention provides a method for preparing the honeycomb wave-absorbing composite material according to any one of the first aspect, including the following steps:
(1) Uniformly stirring and mixing the wave absorber, the epoxy resin, the curing agent and the auxiliary agent to obtain wave absorber slurry;
(2) Dipping the honeycomb core material into the wave absorbing agent slurry, and airing and drying to obtain a hollow honeycomb core material;
(3) Filling pouring sealant into the honeycomb pores of the hollow honeycomb core material, and curing to obtain a honeycomb wave-absorbing core material;
(4) And carrying out numerical control processing on the honeycomb wave-absorbing core material, adhering a skin on the upper surface of the honeycomb wave-absorbing core material, and curing to obtain the honeycomb wave-absorbing composite material.
Preferably, in the step (2), the temperature of the impregnation is 25-40 ℃, and the time of the impregnation is 2-10 h;
in the step (2), the airing temperature is 25-30 ℃, and the airing time is 24-48 h;
in the step (2), the drying temperature is 40-55 ℃, and the drying time is 5-16 h.
Preferably, in the step (1), the rotation speed of the stirring is 350-450 r/min, and the stirring time is 2-4 h.
Preferably, in the step (3) and the step (4), the curing temperature is 30-70 ℃, and the curing time is 5-12 h.
Preferably, in the step (4), the honeycomb wave-absorbing core material is subjected to numerical control machining according to the three-dimensional model of the edge structure.
In a third aspect, the invention provides an application of the honeycomb wave-absorbing composite material in the first aspect in an edge structure; preferably in the context of an edge structure of a fuselage of an aerospace vehicle.
Compared with the prior art, the invention at least has the following beneficial effects:
(1) The aramid fiber paper honeycomb material is used as a honeycomb core material, is soaked in wave absorbent slurry, is filled with a pouring sealant component, and is covered with a skin to obtain the honeycomb wave-absorbing composite material, the honeycomb wave-absorbing composite material not only has an excellent broadband wave-absorbing function, but also has high strength, excellent process, strong operability and low cost, can absorb electromagnetic wave energy on the premise of bearing structural mechanics, is a good wave-absorbing integrated composite material, and can bear severe aviation environment serving as an edge structure of a body of a space vehicle;
(2) The raw materials required by the preparation of the honeycomb wave-absorbing composite material are simple and easy to obtain, the process method is simple and convenient, the process flow is short, the industrial batch production is easy to realize, and the honeycomb wave-absorbing composite material has wide application value in the field of aerocrafts.
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 introduced below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
FIG. 1 is a flow chart of a preparation method of a honeycomb wave-absorbing composite material provided by the invention;
FIG. 2 is a schematic diagram of the position distribution of a skin and a honeycomb wave-absorbing core material when the honeycomb wave-absorbing composite material provided by the invention is bonded to the edge bonding surface of the fuselage structure.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer and more complete, the technical solutions in the embodiments of the present invention will be described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention, and based on the embodiments of the present invention, all other embodiments obtained by a person of ordinary skill in the art without creative efforts belong to the scope of the present invention.
As shown in fig. 2, the invention provides a honeycomb wave-absorbing composite material, which comprises a skin and a honeycomb wave-absorbing core material; the honeycomb wave-absorbing core material is impregnated with wave-absorbing agent slurry, and pouring sealant is filled in honeycomb holes of the honeycomb wave-absorbing core material; in the invention, the skin is positioned on the honeycomb wave-absorbing core material.
At present, the fuselage edge component of the traditional aerospace craft is generally made of metal materials or carbon fiber materials, both the two materials can reflect electromagnetic waves, so that the stealth performance of the fuselage edge component is poor, sensitive information such as the appearance of the fuselage is very easy to expose, in order to improve the situation, composite materials with wave absorption performance can be adopted as the fuselage edge structure, however, the edge structure of the fuselage often needs to bear severe aviation environment, and the wave absorption materials are required to have excellent electromagnetic wave absorption performance under the premise of bearing structural mechanics; the honeycomb material is a common wave-absorbing material, but the traditional honeycomb wave-absorbing material is of a hollow structure, when the material is used for a machine body edge structure, water vapor is easily accumulated in a honeycomb pore structure under a high-temperature environment, so that the wave-absorbing performance of the edge structure is poor, the stealth effect cannot be achieved, the edge structure is aged, and the use requirement of the edge structure of an aviation aircraft cannot be met. According to the invention, the honeycomb core material is firstly soaked in the slurry containing the wave absorbing agent, so that the wave absorbing agent slurry uniformly covers the surface of the honeycomb core material, thereby endowing the honeycomb core material with certain wave absorbing performance, and then the honeycomb holes of the honeycomb core material are filled with the pouring sealant, so that the mechanical strength of the honeycomb core material is enhanced, and the wave absorbing agent slurry on the surface of the honeycomb core material can be effectively prevented from falling, thereby generating adverse influence on the wave absorbing performance of the honeycomb core material; in addition, the water vapor accumulated in the honeycomb pores can be prevented from being accumulated to cause the aging of the edge structure; and finally, the skin is pasted on the surface of the honeycomb core material, so that the wave absorbing performance of the composite material can be further improved, and the effects of corrosion resistance and pneumatic load transmission can be achieved.
According to some preferred embodiments, the skin is a glass fiber composite material or an aramid fiber composite material, and plays a role in packaging and protecting the composite material; the glass fiber composite material and the aramid fiber composite material are the existing common materials, and both can be obtained by purchasing on the market.
According to some preferred embodiments, the skin has a thickness of 0.5 to 2.0mm (e.g. may be 0.5mm, 0.8mm, 1mm, 1.2mm, 1.5mm, 1.8mm or 2.0 mm); in the invention, the thickness of the skin material is controlled within the range, so that the skin material has excellent wave-absorbing performance, corrosion resistance and pneumatic load transmission performance within a proper thickness range; if the thickness of the skin is lower than the above range, the overall performance of the composite material may be degraded, and if the thickness of the skin is higher than the above range, not only the weight of the fuselage may be increased, but also the production cost may be increased.
According to some preferred embodiments, the honeycomb core is an aramid paper honeycomb material. The aramid fiber paper honeycomb material not only has certain electromagnetic wave absorption capacity, but also has strong structural stability, heat insulation and water resistance, is used as a raw material of a honeycomb core material, is impregnated with wave-absorbing agent slurry on the surface, and is filled with pouring sealant in honeycomb pores, so that the prepared composite material has excellent broadband wave-absorbing performance on the premise of bearing structural mechanics; it should be noted that, the source of the aramid paper honeycomb material in the present invention is not particularly limited as long as the shape specification specified in the present invention is satisfied: 7-9 kg/m 3 The size of the cells is 6-8 mm, and the cells can be obtained by purchasing on the market at will.
According to some preferred embodiments, the honeycomb core has a thickness of 5 to 25mm (e.g., may be 5mm, 8mm, 10mm, 12mm, 15mm, 18mm, 20mm, 23mm, or 25 mm). The thickness of the honeycomb core material refers to the height direction of honeycomb holes in the honeycomb core material, and the wave-absorbing performance and the mechanical performance of the wave-absorbing composite material can be controlled through the thickness of the honeycomb core material, so that the wave-absorbing composite material prepared by the method has excellent mechanical bearing capacity and electromagnetic wave absorption performance under the condition that the overall mass is not remarkably increased; if the thickness of the honeycomb core is less than the above range, the mechanical properties and electromagnetic wave absorption properties of the composite material are poor, and if the thickness of the honeycomb core is greater than the above range, the overall weight of the composite material is increased, which is not favorable for achieving the requirement of weight reduction, and the corresponding cost is increased.
According to some preferred embodiments, the wave absorber slurry comprises a wave absorber, an epoxy resin, a curing agent and an auxiliary agent; the wave absorbing agent is mainly used for realizing the wave absorbing function of the composite material in a specific wave band, and the auxiliary agent is mainly used for uniformly dispersing the wave absorbing agent in the epoxy resin so as to ensure the uniformity of the wave absorbing agent on the surface of the honeycomb core material in the subsequent impregnation process.
According to some preferred embodiments, in the wave absorbent slurry, the mass ratio of the wave absorbent, the epoxy resin, the curing agent and the auxiliary agent is (1-10): (60 to 85): (3-12): (0.5-5) (for example, a ratio of 1; the invention controls the proportion of each component in the wave absorbing agent slurry in the above range through a large number of creative experiments, and can ensure that the composite material finally prepared has the best comprehensive performance, particularly the wave absorbing performance and the mechanical performance; if the proportion of the components is lower than or higher than the above proportion, the preparation of the composite material with the best comprehensive performance is not facilitated, for example, the dispersion of the wave absorbing agent is not uniform, the slurry of the wave absorbing agent falls into powder, the weight of the composite material is heavy, and the like.
According to some preferred embodiments, the content of the wave absorber slurry in the honeycomb core material is 300 to 500g/m 2 (for example, it may be 300g/m 2 、350g/m 2 、400g/m 2 、450g/m 2 Or 500g/m 2 ) (ii) a The invention relates to a honeycomb core materialThe wave absorbing agent slurry is controlled within the range, so that the wave absorbing agent slurry can be ensured to be good in adhesion on the honeycomb core material, and the honeycomb core material can be ensured to have excellent broadband wave absorbing performance.
According to some preferred embodiments, the wave absorbing agent is at least one of carbon black, carbon nanotubes, graphene or mesoporous carbon. In the present invention, the carbon black is preferably acetylene-type conductive carbon black, and the carbon nanotube is preferably a multi-wall type; at least one of the components is any one or a mixture of any several components mixed in any proportion.
According to some preferred embodiments, the epoxy resin is a bisphenol a type epoxy resin or a bisphenol F type epoxy resin, and specific designations thereof may be E44, E41, E55, E51, or the like, for example; the curing agent is preferably an amine curing agent, and can be an aromatic amine curing agent such as m-phenylenediamine, an aliphatic amine curing agent such as ethylenediamine, and an imidazole curing agent such as 2-methylimidazole.
According to some preferred embodiments, the auxiliary agent is at least one of methylcellulose, sodium carboxymethylcellulose, SY-F7090H, dispuper-S19, BYK-181; it should be noted that, in the present invention, the auxiliary agents are preferably three of the above-mentioned auxiliary agents for compounding, and when the auxiliary agents are compounded, the compounding ratio between the auxiliary agents is preferably 1.
According to some preferred embodiments, the potting adhesive is a two-component epoxy adhesive or a two-component polyurethane adhesive; in the invention, the two-component epoxy resin adhesive refers to an adhesive prepared by taking epoxy resin as a main body, and also comprises a corresponding epoxy resin curing agent; the two-component polyurethane adhesive is an adhesive prepared by taking polyurethane as a main body, and also comprises a corresponding polyurethane curing agent, and when the two-component polyurethane adhesive is used, the two components are uniformly mixed according to a proportion, and then can be completely cured; meanwhile, in the present invention, the potting adhesive fills each honeycomb hole in the honeycomb core material, so the addition amount of the potting adhesive is mainly determined according to the area of the honeycomb hole, and when mixing, the mass ratio of the epoxy resin and/or the curing agent may be 5. According to the invention, the two-component epoxy resin adhesive and the two-component polyurethane adhesive are used as pouring sealants and filled into honeycomb pores of the honeycomb core material, so that the weight of the honeycomb core material is not increased remarkably, the honeycomb core material is endowed with excellent mechanical property and ageing resistance, more importantly, the pouring sealants do not cause the reduction of the wave-absorbing property of the honeycomb core material, the wave-absorbing agent slurry on the surface of the honeycomb core material can be effectively prevented from falling off, and the adverse effect on the wave-absorbing property of the honeycomb core material is further avoided.
According to some preferred embodiments, the skin is bonded with the honeycomb wave-absorbing core material through a glue film; the adhesive film is a two-component epoxy resin adhesive. It should be noted that, in the present invention, the type of the glue film is the same as that of the two-component epoxy resin potting adhesive.
As shown in fig. 2, the invention also provides a preparation method of any one of the above honeycomb wave-absorbing composite materials, which comprises the following steps:
(1) Uniformly stirring and mixing the wave absorber, the epoxy resin, the curing agent and the auxiliary agent to obtain wave absorber slurry;
(2) Dipping the honeycomb core material into the wave absorbing agent slurry, and airing and drying to obtain a hollow honeycomb core material; firstly, cutting a honeycomb core material to a proper thickness, soaking the honeycomb core material into wave absorbing agent slurry at a certain temperature, and airing and drying the honeycomb core material after the wave absorbing agent slurry on the surface of the honeycomb core material reaches a certain amount to firmly bond the wave absorbing agent slurry on the surface of the honeycomb core material;
(3) Placing a hollow honeycomb core material on a glass plate, filling prepared pouring sealant into each honeycomb pore of the hollow honeycomb core material, and curing to obtain a honeycomb wave-absorbing core material;
(4) Carrying out numerical control machining on the honeycomb wave-absorbing core material according to the edge structure of the aircraft body, then coating a glue film on the upper surface or the lower surface of the honeycomb wave-absorbing core material, wherein the coating thickness of the glue film can be 0.2mm, then covering a skin on the glue film, and curing to obtain the honeycomb wave-absorbing composite material; when the composite material is used, one side of the skin faces outwards, and one side of the honeycomb wave-absorbing core material is bonded with the edge bonding surface of the fuselage structure, for example, as shown in fig. 2.
According to some preferred embodiments, in the step (1), the rotation speed of the stirring is 350 to 450r/min (for example, 350r/min, 380r/min, 400r/min, 420r/min or 450 r/min), and the stirring time is 2 to 4h (for example, 2h, 2.5h, 3h, 3.5h or 4 h); in the invention, the stirring speed and time are controlled within the above range during stirring, so that the components can be uniformly mixed, and the problem of performance reduction caused by air bubbles in the slurry can be effectively avoided.
According to some preferred embodiments, in the step (2), the temperature of the impregnation is 25 to 40 ℃ (for example, may be 25 ℃, 28 ℃, 30 ℃, 35 ℃, 38 ℃ or 40 ℃), and the time of the impregnation is 2 to 10 hours (for example, may be 2 hours, 3 hours, 4 hours, 5 hours, 6 hours, 7 hours, 8 hours, 9 hours or 10 hours); in the invention, when the impregnation is carried out, the impregnation is preferably carried out for multiple times, the impregnation can be carried out for 8 to 15 times, the time of single impregnation is 15 to 75min, and the final impregnation time is controlled to be 2 to 10 hours;
the temperature of the airing is 25-30 ℃ (for example, 25 ℃, 26 ℃, 27 ℃, 28 ℃, 29 ℃ or 30 ℃), and the time of the airing is 24-48 h (for example, 24h, 30h, 32h, 36h, 40h, 44h or 48 h);
the temperature of the drying is 40 to 55 ℃ (for example, 40 ℃, 42 ℃, 45 ℃, 46 ℃, 48 ℃, 50 ℃ or 55 ℃), and the time of the drying is 5 to 16h (for example, 5h, 8h, 10h, 12h, 14h or 16 h).
According to some preferred embodiments, in the step (3) and the step (4), the curing temperature is 30 to 70 ℃ (for example, may be 30 ℃, 40 ℃, 50 ℃, 60 ℃ or 70 ℃), and the curing time is 5 to 12 hours (for example, may be 5 hours, 6 hours, 7 hours, 8 hours, 9 hours, 10 hours, 11 hours or 12 hours).
The invention also provides an application of the honeycomb wave-absorbing composite material in an edge structure; according to some preferred embodiments, the honeycomb wave-absorbing composite material is applied to an edge structure of a fuselage of an aerospace vehicle.
In order to more clearly illustrate the technical scheme and advantages of the present invention, a honeycomb composite wave-absorbing material for an edge structure and a preparation method thereof are described in detail through several embodiments.
In the following examples, the density of the aramid paper honeycomb material was 8.5kg/m 3 The size of the cells is 6mm.
Example 1:
(1) Mixing a carbon black wave absorber with bisphenol A epoxy resin E44, a m-phenylenediamine curing agent and an auxiliary agent according to a ratio, and stirring for 3 hours at 400r/min to obtain wave absorber slurry; wherein the mass ratio of the wave absorbing agent to the epoxy resin to the curing agent to the auxiliary agent is 3.5;
(2) Cutting the aramid fiber paper honeycomb material to 6mm, using the cut aramid fiber paper honeycomb material as a honeycomb core material, soaking the honeycomb core material in the wave absorbing agent slurry for 5 hours at the temperature of 30 ℃, and then drying the honeycomb core material in the air (at the temperature of 26 ℃ for 30 hours) and drying the honeycomb core material (at the temperature of 45 ℃ for 15 hours) to obtain a hollow honeycomb core material; wherein the content of the wave absorbent slurry in the hollow honeycomb core material is 400g/m 2 ；
(3) Preparing a two-component epoxy resin pouring sealant, placing a hollow honeycomb core material on a glass plate, filling the pouring sealant into honeycomb holes of the hollow honeycomb core material until the honeycomb holes are filled with the pouring sealant, and curing at 35 ℃ for 8 hours to obtain a honeycomb wave-absorbing core material; wherein the mass ratio of the epoxy resin to the curing agent in the pouring sealant is 5;
(4) And carrying out numerical control processing on the honeycomb wave-absorbing core material according to the edge structure three-dimensional model, then coating a glue film on the upper surface of the honeycomb wave-absorbing core material, covering a glass fiber composite material skin (1 mm) on the glue film, and curing for 5 hours at 40 ℃ to obtain the honeycomb wave-absorbing composite material.
The wave-absorbing test is carried out on the honeycomb wave-absorbing composite material obtained in the embodiment, and the reflectivity of the composite material in C, X and Ku wave bands is less than or equal to-12.5 dB, and the composite material has excellent wave-absorbing performance.
Example 2:
(1) Mixing a wave absorber containing graphene and carbon black (the mass ratio of the graphene to the carbon black is 1; wherein the wave absorbing agent, the epoxy resin, the curing agent and the auxiliary agent are mixed according to the ratio of 1;
(2) Cutting the aramid fiber paper honeycomb material to 10mm, soaking the honeycomb material in the wave absorbing agent slurry for 3 hours at the temperature of 35 ℃, and then drying (the temperature is 28 ℃, the time is 24 hours) and drying (the temperature is 40 ℃, the time is 16 hours) to obtain a hollow honeycomb core material; wherein the content of the wave absorbent slurry in the honeycomb core material is 300g/m 2 ；
(3) Preparing two-component epoxy resin pouring sealant, placing a hollow honeycomb core material on a glass plate, filling the pouring sealant into honeycomb holes of the hollow honeycomb core material until the honeycomb holes are filled with the pouring sealant, and then curing at 50 ℃ for 8 hours to obtain a honeycomb wave-absorbing core material; wherein the mass ratio of the epoxy resin to the curing agent in the pouring sealant is 5;
(4) And carrying out numerical control processing on the honeycomb wave-absorbing core material according to the edge structure three-dimensional model, then coating a glue film on the upper surface of the honeycomb wave-absorbing core material, covering a glass fiber composite material skin (2 mm) on the glue film, and curing for 8 hours at 50 ℃ to obtain the honeycomb wave-absorbing composite material.
Wave absorption tests are carried out on the honeycomb wave-absorbing composite material obtained in the embodiment, and the reflectivity of the honeycomb wave-absorbing composite material in C, X and Ku wave bands is less than or equal to-10.1 dB, so that the honeycomb wave-absorbing composite material has excellent broadband wave-absorbing performance.
Example 3:
(1) Mixing a wave absorber containing carbon black, carbon nanotubes and mesoporous carbon (the mass ratio of the carbon black to the carbon nanotubes to the mesoporous carbon is 1; wherein, the wave absorbing agent, the epoxy resin, the curing agent and the auxiliary agent are mixed according to the proportion of 10;
(2) Cutting an aramid fiber paper honeycomb material to 25mm, soaking the honeycomb material in the wave absorbing agent slurry for 10 hours at 40 ℃, and then drying (the temperature is 30 ℃, the time is 48 hours) and drying (the temperature is 55 ℃, the time is 10 hours) to obtain a hollow honeycomb core material; wherein the content of the wave absorbent slurry in the honeycomb core material is 450g/m 2 ；
(3) Preparing a two-component epoxy resin pouring sealant, placing a hollow honeycomb core material on a glass plate, filling the pouring sealant into honeycomb holes of the hollow honeycomb core material until the honeycomb holes are filled with the pouring sealant, and curing at 70 ℃ for 10 hours to obtain a honeycomb wave-absorbing core material; wherein the mass ratio of the epoxy resin to the curing agent in the pouring sealant is 5;
(4) And carrying out numerical control processing on the honeycomb wave-absorbing core material according to the edge structure three-dimensional model, then coating a glue film on the upper surface of the honeycomb wave-absorbing core material, covering a glass fiber composite material skin (0.5 mm) on the glue film, and curing for 5 hours at 70 ℃ to obtain the honeycomb wave-absorbing composite material.
Wave absorption tests are carried out on the honeycomb wave-absorbing composite material obtained in the embodiment, and the reflectivity of the honeycomb wave-absorbing composite material in C, X and Ku wave bands is less than or equal to-13.0 dB, so that the honeycomb wave-absorbing composite material has excellent wave-absorbing performance.
Example 4:
example 4 is essentially the same as example 1, except that: in the step (1), the absorbent is a carbon nanotube.
The wave-absorbing test is carried out on the honeycomb wave-absorbing composite material obtained in the embodiment, and the reflectivity of the composite material in C, X and Ku wave bands is less than or equal to-11.0 dB, so that the composite material has excellent broadband wave-absorbing performance.
Example 5:
example 5 is essentially the same as example 1, except that: in the step (1), the mass ratio of the absorbent, the resin, the curing agent and the auxiliary agent is 5.
The wave-absorbing test is carried out on the honeycomb wave-absorbing composite material obtained in the embodiment, and the reflectivity of the composite material in C, X and Ku wave bands is less than or equal to-11.5 dB, so that the composite material has excellent broadband wave-absorbing performance.
Example 6:
example 6 is essentially the same as example 1, except that: in the step (2), the thickness of the aramid paper honeycomb is 8mm.
Wave absorption tests are carried out on the honeycomb wave-absorbing composite material obtained in the embodiment, and the reflectivity of the honeycomb wave-absorbing composite material in C, X and Ku wave bands is less than or equal to-9.5 dB, so that the honeycomb wave-absorbing composite material has excellent broadband wave-absorbing performance.
Example 7:
example 7 is essentially the same as example 1, except that: in the step (3), the pouring sealant is a two-component polyurethane adhesive.
The wave-absorbing test is carried out on the honeycomb wave-absorbing composite material obtained in the embodiment, and the reflectivity of the composite material in C, X and Ku wave bands is less than or equal to-12.5 dB, so that the composite material has excellent broadband wave-absorbing performance.
Example 8:
example 8 is essentially the same as example 1, except that: in the step (1), in the wave absorbing agent slurry, the mass ratio of the wave absorbing agent to the epoxy resin to the curing agent to the auxiliary agent is 0.5;
the wave-absorbing test is carried out on the honeycomb wave-absorbing composite material obtained in the embodiment, and the reflectivity of the composite material in C, X and Ku wave bands is less than or equal to-7.3 dB.
Example 9:
example 9 is essentially the same as example 1, except that: in the step (1), the mass ratio of the wave absorbing agent to the epoxy resin to the curing agent to the auxiliary agent in the wave absorbing agent slurry is (11).
The wave-absorbing test is carried out on the honeycomb wave-absorbing composite material obtained in the embodiment, and the reflectivity of the composite material in C, X and Ku wave bands is less than or equal to-14.2 dB.
Example 10:
example 10 is essentially the same as example 1, except that: in the step (1), in the wave absorbing agent slurry, the mass ratio of the wave absorbing agent to the epoxy resin to the curing agent to the auxiliary agent is 3.
The wave-absorbing test is carried out on the honeycomb wave-absorbing composite material obtained in the embodiment, and the reflectivity of the composite material in C, X and Ku wave bands is measured to be less than or equal to-12.2 dB.
Example 11:
example 11 is essentially the same as example 1, except that: in the step (1), in the wave absorbing agent slurry, the mass ratio of the wave absorbing agent to the epoxy resin to the curing agent to the auxiliary agent is 3.
The wave absorption test is carried out on the honeycomb wave absorption composite material obtained in the embodiment, and the reflectivity of the composite material in C, X and Ku wave bands is measured to be less than or equal to-11.6 dB.
Example 12:
example 12 is essentially the same as example 1, except that: in the step (1), in the wave absorbing agent slurry, the mass ratio of the wave absorbing agent to the epoxy resin to the curing agent to the auxiliary agent is 3.
The wave-absorbing test is carried out on the honeycomb wave-absorbing composite material obtained in the embodiment, and the reflectivity of the composite material in C, X and Ku wave bands is measured to be less than or equal to-12.4 dB.
Example 13:
example 13 is essentially the same as example 1, except that: in the step (1), the mass ratio of the wave absorbing agent to the epoxy resin to the curing agent to the auxiliary agent in the wave absorbing agent slurry is 3.
The wave-absorbing test is carried out on the honeycomb wave-absorbing composite material obtained in the embodiment, and the reflectivity of the composite material in C, X and Ku wave bands is measured to be less than or equal to-12.2 dB.
Example 14:
example 14 is essentially the same as example 1, except that: in step (2), the aramid paper honeycomb material is cut to 4mm.
The wave-absorbing test is carried out on the honeycomb wave-absorbing composite material obtained in the embodiment, and the reflectivity of the composite material in C, X and Ku wave bands is measured to be less than or equal to-6.4 dB.
Example 15:
example 15 is essentially the same as example 1, except that: in step (2), the aramid paper honeycomb material was cut to 26mm.
The wave-absorbing test is carried out on the honeycomb wave-absorbing composite material obtained in the embodiment, and the reflectivity of the composite material in C, X and Ku wave bands is measured to be less than or equal to-14.5 dB.
Comparative example 1:
comparative example 1 is substantially the same as example 1 except that: and (4) removing the step (3), namely, filling no pouring sealant in honeycomb holes of the hollow honeycomb core material to form a hollow structure.
And (3) performing wave absorption test on the honeycomb wave-absorbing composite material obtained by the comparative example, and measuring that the reflectivity of the composite material in C, X and Ku wave bands is less than or equal to-11.5 dB.
Comparative example 2:
comparative example 2 is substantially the same as example 1 except that: in the step (3), replacing the pouring sealant with the foaming slurry; weighing 11.9g of isocyanate (PAPI), 7.7g of 303 polyether, 0.19g of silicone oil, 0.16g of triethanolamine, 0.12g of water and 0.2g of conductive carbon black, and uniformly mixing to obtain foaming slurry; and (3) pouring the foaming slurry into a mold cavity, uniformly distributing the foaming slurry on the bottom layer of the mold cavity, and then placing the hollow honeycomb core material into the foaming slurry of the mold cavity. Covering the upper die, and tightening the upper die by using bolts to keep the die cavity closed; and (3) putting the whole die into an oven, heating to 130 ℃, preserving heat for 3 hours, closing the oven, cooling to room temperature (25 ℃), and demoulding to obtain the honeycomb wave-absorbing core material.
Wave absorption tests are carried out on the honeycomb wave-absorbing composite material obtained in the comparative example, and the reflectivity of the honeycomb wave-absorbing composite material in C, X and Ku wave bands is less than or equal to-10.5 dB.
Comparative example 3:
comparative example 3 is substantially the same as example 1 except that: in the step (2), the honeycomb material is an aluminum product honeycomb material.
And (3) performing wave absorption test on the honeycomb wave-absorbing composite material obtained by the comparative example, and measuring that the reflectivity of the composite material in C, X and Ku wave bands is less than or equal to-3.7 dB.
The honeycomb wave-absorbing composite materials in the embodiments 1 to 15 and the comparative examples 1 to 3 are subjected to mechanical property tests, the test results are shown in table 1, wherein the wave-absorbing reflectivity in table 1 refers to the wave-absorbing reflectivity of the honeycomb wave-absorbing composite material in the wave bands of C, X and Ku;
the compression strength test method comprises the following steps: refer to GJB 130.5-1986 test method for compression performance of cemented aluminum honeycomb sandwich structure and core plane;
the surface density test method comprises the following steps: weighing method, wherein the surface density = sample weight/sample area, and the surface density in the invention refers to the surface density of the skin surface;
the method for testing the wave-absorbing reflectivity comprises the following steps: refer to GJB 2038A-2011 radar absorbing material reflectivity test method.
TABLE 1
Figure BDA0003743277360000131
Figure BDA0003743277360000141
As can be seen from the table 1, the honeycomb wave-absorbing composite material prepared by the embodiment of the invention has excellent broadband wave-absorbing performance on the premise of excellent structural mechanical load, the highest reflectivity of the composite material in C, X and Ku wave bands can be less than or equal to-14.5 dB, and the wave-absorbing integrated composite material has wide application value in the field of aviation aircrafts; in the comparative example 1, when no potting adhesive is filled in the honeycomb wave-absorbing core material, the prepared honeycomb wave-absorbing composite material has low density but poor mechanical strength, and when the honeycomb wave-absorbing composite material is applied to an edge structure, water vapor is easily accumulated in the edge structure to age; in comparative example 2, when the honeycomb wave-absorbing core material is filled with polyurethane foam, the edge structure is easy to accumulate water vapor so as to generate an aging phenomenon; in comparative example 3, when the honeycomb core material is made of an aluminum honeycomb core material, although the mechanical property of the composite material can be significantly enhanced, the composite material has poor wave-absorbing property, and the overall weight of the composite material is large, so that the requirement of weight reduction of the aerospace vehicle cannot be met.
Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention, and not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.

Claims (10)

1. A honeycomb wave-absorbing composite material is characterized in that: the honeycomb wave-absorbing composite material comprises a skin and a honeycomb wave-absorbing core material; the wave absorbing core material is impregnated with wave absorbing agent slurry, and pouring sealant is filled in honeycomb holes of the wave absorbing core material.
2. The cellular wave-absorbing composite material of claim 1, wherein:
the skin is a glass fiber composite material or an aramid fiber composite material; and/or
The thickness of the skin is 0.5-2.0 mm.
3. The cellular wave-absorbing composite material of claim 1, wherein:
the honeycomb wave-absorbing core material is an aramid fiber paper honeycomb material; and/or
The thickness of the honeycomb wave-absorbing core material is 5-25 mm.
4. The cellular wave-absorbing composite material of claim 1, wherein:
the wave absorber slurry comprises a wave absorber, epoxy resin, a curing agent and an auxiliary agent; preferably, in the wave absorber slurry, the mass ratio of the wave absorber, the epoxy resin, the curing agent and the auxiliary agent is (1-10): (60 to 85): (3-12): (0.5 to 5); and/or
The content of the wave absorbent slurry in the honeycomb wave absorbing core material is 300-500 g/m 2 。
5. The cellular wave-absorbing composite material of claim 4, wherein:
the wave absorbing agent is at least one of carbon black, carbon nano tubes, graphene or mesoporous carbon;
the epoxy resin is bisphenol A type epoxy resin or bisphenol F type epoxy resin;
the curing agent is an amine curing agent; and/or
The auxiliary agent is at least one of methyl cellulose, sodium carboxymethyl cellulose, SY-F7090H, dispuper-S19 and BYK-181.
6. The cellular wave-absorbing composite material of claim 1, wherein:
the pouring sealant is a two-component epoxy resin adhesive or a two-component polyurethane adhesive; and/or
The skin is bonded with the honeycomb wave-absorbing core material through a glue film; preferably, the adhesive film is a two-component epoxy resin adhesive.
7. The preparation method of the honeycomb wave-absorbing composite material according to any one of claims 1 to 6, wherein the preparation method comprises the following steps:
(1) Uniformly stirring and mixing the wave absorber, the epoxy resin, the curing agent and the auxiliary agent to obtain wave absorber slurry;
(2) Dipping the honeycomb core material into the wave absorbing agent slurry, and airing and drying to obtain a hollow honeycomb core material;
(3) Filling a pouring sealant into the honeycomb pores of the hollow honeycomb core material, and curing to obtain a honeycomb wave-absorbing core material;
(4) And carrying out numerical control processing on the honeycomb wave-absorbing core material, adhering a skin on the upper surface of the honeycomb wave-absorbing core material, and curing to obtain the honeycomb wave-absorbing composite material.
8. The method for producing according to claim 7, characterized in that:
in the step (2), the dipping temperature is 25-40 ℃, and the dipping time is 2-10 h;
the airing temperature is 25-30 ℃, and the airing time is 24-48 h;
the drying temperature is 40-55 ℃, and the drying time is 5-16 h; and/or
In the step (1), the rotating speed of stirring is 350-450 r/min, and the stirring time is 2-4 h.
9. The method for producing according to claim 7, characterized in that:
in the step (3) and/or the step (4), the curing temperature is 30-70 ℃, and the curing time is 5-12 h; and/or
And (4) carrying out numerical control machining on the honeycomb wave-absorbing core material according to the three-dimensional model of the edge structure.
10. Use of a honeycomb microwave absorbing composite according to any of claims 1 to 6 in edge construction; preferably in the context of an edge structure of a fuselage of an aerospace vehicle.
CN202210818589.0A 2022-07-13 2022-07-13 Honeycomb wave-absorbing composite material and preparation method and application thereof Pending CN115157819A (en)

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