CN116373404B - Cylindrical carbon fiber composite material structure with low radar cross section characteristic - Google Patents

Cylindrical carbon fiber composite material structure with low radar cross section characteristic Download PDF

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CN116373404B
CN116373404B CN202310356835.XA CN202310356835A CN116373404B CN 116373404 B CN116373404 B CN 116373404B CN 202310356835 A CN202310356835 A CN 202310356835A CN 116373404 B CN116373404 B CN 116373404B
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carbon fiber
composite material
material layer
fiber composite
horizontal ground
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CN116373404A (en
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刘选
吴琦
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Beihang University
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Beihang University
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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
    • B32B5/22—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
    • 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
    • B32B5/12—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 characterised by the relative arrangement of fibres or filaments of different layers, e.g. the fibres or filaments being parallel or perpendicular to each other
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
    • H05K9/00—Screening of apparatus or components against electric or magnetic fields
    • H05K9/0073—Shielding materials
    • H05K9/0081—Electromagnetic shielding materials, e.g. EMI, RFI shielding
    • H05K9/0088—Electromagnetic shielding materials, e.g. EMI, RFI shielding comprising a plurality of shielding layers; combining different shielding material 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
    • B32B2250/00—Layers arrangement
    • B32B2250/05—5 or more layers
    • 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
    • B32B2250/00—Layers arrangement
    • B32B2250/20—All layers 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
    • 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
    • B32B2260/021—Fibrous or filamentary layer
    • B32B2260/023—Two or more layers
    • 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
    • B32B2262/106—Carbon fibres, e.g. graphite 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
    • 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
    • Y02A—TECHNOLOGIES FOR ADAPTATION TO CLIMATE CHANGE
    • Y02A90/00—Technologies having an indirect contribution to adaptation to climate change
    • Y02A90/10—Information and communication technologies [ICT] supporting adaptation to climate change, e.g. for weather forecasting or climate simulation

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  • Physics & Mathematics (AREA)
  • Electromagnetism (AREA)
  • Engineering & Computer Science (AREA)
  • Microelectronics & Electronic Packaging (AREA)
  • Laminated Bodies (AREA)
  • Shielding Devices Or Components To Electric Or Magnetic Fields (AREA)

Abstract

The invention relates to the technical field of electromagnetic compatibility, in particular to a cylindrical carbon fiber composite material structure with low radar cross section characteristics, which comprises a plurality of carbon fiber composite material layers, wherein the carbon fiber composite material layers are formed by resin material substrates and carbon fiber wires, and the carbon fiber wires are uniformly distributed in the resin material substrates; the arrangement directions of the carbon fiber filaments in two adjacent carbon fiber composite material layers are different, and the angle difference values of the arrangement directions are not uniform. According to the cylindrical carbon fiber composite material, the cylindrical carbon fiber composite material has good shielding effect and low radar scattering cross section while ensuring structural strength through the arrangement of the inner diameter size of the cylindrical carbon fiber composite material layer, the conductivity of carbon fiber wires in the composite material layer and the dielectric constant of the resin material substrate; the arrangement mode of carbon fiber wires with non-uniform angle difference arrangement is selected, and the single-station radar cross section of the cylindrical carbon fiber composite material layer is reduced.

Description

Cylindrical carbon fiber composite material structure with low radar cross section characteristic
Technical Field
The invention relates to the technical field of electromagnetic compatibility, in particular to a carbon fiber composite material multilayer structure with low radar cross section characteristics.
Background
The carbon fiber composite material is a novel material with high tensile strength, high modulus and low density, has excellent mechanical property, chemical stability and electromagnetic shielding property, is widely applied in the aerospace field in recent years, and can be applied to the structural design of an aircraft fuselage to reduce the weight of the aircraft. The carbon fiber/epoxy and carbon fiber/bismaleimide composite material is often applied to the parts of an airplane body, a main wing, a vertical tail wing, a flat tail wing, a skin and the like, so that the performances of fatigue resistance, corrosion resistance and the like of the composite material are greatly improved. The carbon fiber composite material is also applied to structural components of rocket bodies and engine shells and satellite main body structure bearing parts, and is an important heat-resistant material such as bullet tips, engine spray pipe throat liners, ablation-resistant components and the like. Carbon fiber composites are typically multi-layered structures, each layer being composed of a carbon fiber reinforced resin substrate.
Due to the requirements of the supersonic aircraft on electromagnetic compatibility and stealth performance, the carbon fiber composite material serving as the cabin section material of the fuselage needs to meet the characteristics of high shielding effectiveness and low radar scattering cross section while ensuring structural strength. Most of the current applications of carbon fiber composite materials focus on the mechanical properties and thermal properties, and less focuses on the changes of shielding effectiveness and stealth properties of cylindrical carbon fiber composite materials. Furthermore, the shielding effectiveness of a shielding body and its radar cross section tend to be inversely related, and therefore carbon fiber composite structures for aerospace vehicles require a tradeoff between shielding effectiveness and radar cross section.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provide a cylindrical carbon fiber composite material structure with low radar cross section characteristics, which ensures the structural strength and simultaneously has smaller radar cross section (echo width).
The aim of the invention is achieved by the following technical scheme:
the cylindrical carbon fiber composite material structure with the characteristic of low radar scattering cross section comprises a plurality of carbon fiber composite material layers, wherein the carbon fiber composite material layers are formed by a resin material substrate and carbon fiber wires, and the carbon fiber wires are uniformly distributed in the resin material substrate; the arrangement directions of the carbon fiber filaments in two adjacent carbon fiber composite material layers are different, and the angle difference values of the arrangement directions are not uniform.
Further, the carbon fiber composite material layer has six layers, respectively: the carbon fiber composite material comprises a first composite material layer, a second composite material layer, a third composite material layer, a fourth composite material layer, a fifth composite material layer and a sixth composite material layer, wherein the first composite material layer is vertically arranged between carbon fiber filaments and the horizontal ground, the second composite material layer is parallelly arranged between the carbon fiber filaments and the horizontal ground, the included angle between the carbon fiber filaments and the horizontal ground is 45 degrees, the included angle between the carbon fiber filaments and the horizontal ground is 135 degrees, the fifth composite material layer is parallelly arranged between the carbon fiber filaments and the horizontal ground, and the sixth composite material layer is vertically arranged between the carbon fiber filaments and the horizontal ground.
Further, the carbon fiber composite material layer has eight layers, respectively: the carbon fiber composite material comprises a first composite material layer, a second composite material layer, a third composite material layer, a fourth composite material layer, a fifth composite material layer, a sixth composite material layer, a seventh composite material layer and an eighth composite material layer, wherein the first composite material layer is vertically arranged between carbon fiber filaments and the horizontal ground, the second composite material layer is vertically arranged between the carbon fiber filaments and the horizontal ground, the included angle between the carbon fiber filaments and the horizontal ground is 30 degrees, the included angle between the carbon fiber filaments and the horizontal ground is 60 degrees, the included angle between the carbon fiber filaments and the horizontal ground is 120 degrees, the included angle between the carbon fiber filaments and the horizontal ground is 150 degrees, and the carbon fiber filaments and the horizontal ground are parallel.
Further, the carbon fiber filaments in the same resin material substrate are parallel to each other.
Further, the carbon fiber filaments are T800-H carbon fiber filaments.
Further, the carbon fiber composite material multilayer structure is cylindrical, and the inner diameter D of the carbon fiber composite material multilayer structure is 106-112 cm.
Further, the thickness d of the carbon fiber composite material layer is 0.126-0.166 mm.
Further, the resin material substrate has a dielectric constant ε m 2.0 to 3.2.
Further, the height h of the carbon fiber composite material multilayer structure is 0.5 m-8 m.
Further, the pitch p of the carbon fiber filaments in the same resin material substrate is 0.08-0.1 mm, and both ends of the carbon fiber filaments are shielded by metal plates.
The invention has the following advantages:
1. through the arrangement of the inner diameter size of the cylindrical carbon fiber composite material layer, the conductivity of carbon fiber wires in the composite material layer and the dielectric constant of the resin material substrate, the cylindrical carbon fiber composite material has the effect of low radar scattering cross section while ensuring the structural strength, and has good shielding effectiveness.
2. By changing the angles of the arrangement directions of the carbon fiber wires among the carbon fiber composite material layers, the arrangement mode of the carbon fiber wires with non-uniform angle difference arrangement is selected, and the single-station radar cross section of the cylindrical carbon fiber composite material layer is reduced.
Drawings
FIG. 1 is a schematic view of a planar carbon fiber composite according to embodiment 1 of the present invention;
FIG. 2 is a schematic view of a cylindrical carbon fiber composite material according to embodiment 1 of the present invention;
FIG. 3 is a graph showing the shielding effectiveness parameters of embodiment 1 of the present invention;
FIG. 4 is a single station echo width parameter chart of embodiment 1 of the present invention;
FIG. 5 is a schematic view of the structure of a planar carbon fiber composite according to embodiment 2 of the present invention;
FIG. 6 is a graph showing the shielding effectiveness parameters of embodiment 2 of the present invention;
FIG. 7 is a single station echo width parameter chart of embodiment 2 of the present invention;
Detailed Description
The present invention will be further described with reference to the accompanying drawings, but the scope of the present invention is not limited to the following.
It should be noted that: because the length of the cylindrical carbon fiber composite multilayer structure for the space vehicle cabin is often much longer than the incident wavelength, the echo width can reflect the scattering characteristics of the cylindrical carbon fiber composite multilayer structure.
The cylindrical carbon fiber composite material structure with the characteristic of low radar scattering cross section comprises a plurality of carbon fiber composite material layers, wherein the carbon fiber composite material layers are formed by a resin material substrate and carbon fiber wires, and the carbon fiber wires are uniformly distributed in the resin material substrate; the arrangement directions of the carbon fiber filaments in two adjacent carbon fiber composite material layers are different, and the angle difference values of the arrangement directions are not uniform. The carbon fiber filaments in the same resin material substrate are parallel to each other. The carbon fiber filaments are T800-H carbon fiber filaments. The carbon fiber composite material multilayer structure is cylindrical, and the inner diameter D of the carbon fiber composite material multilayer structure is 106-112 cm. The thickness d of the carbon fiber composite material layer is 0.126-0.166 mm. The dielectric constant epsilon of the resin material substrate m 2.0 to 3.2. The height h of the carbon fiber composite material multilayer structure is 0.5 m-8 m. The distance p between the carbon fiber wires in the same resin material substrate is 0.08-0.1 mm, and the two ends of the carbon fiber wires are shielded by metal plates.
Example 1:
as shown in fig. 1 and 2, in this embodiment, the carbon fiber composite material layer has six layers, respectively: first composite material layer with carbon fiber wires vertically arranged on horizontal ground, second composite material layer with carbon fiber wires horizontally arranged on horizontal ground, and carbon fiberThe carbon fiber composite comprises a third composite layer, a fourth composite layer and a fifth composite layer, wherein the included angle between the carbon fiber and the horizontal ground is 45 degrees, the included angle between the carbon fiber and the horizontal ground is 135 degrees, the fifth composite layer is parallel to the carbon fiber and the horizontal ground, and the sixth composite layer is perpendicular to the horizontal ground. The angle difference of the arrangement direction of the carbon fiber wires of the six composite carbon fiber composite material layers is 90 degrees, 45 degrees, 90 degrees, 45 degrees and 90 degrees in sequence. The dimensions of the above parameters are as follows: d=112 cm, epsilon m = 2,h =3m; p=0.1 mm, d=0.162 mm. As shown in fig. 3 and 4, in this embodiment, the echo width measurement frequency range is 2-18 GHz, the incident wave is a plane wave polarized vertically, the shielding effectiveness is increased by about 50dB on average compared with a multi-layer carbon fiber composite material with an angle of 90 ° for six layers, the single-station echo width is reduced by about 0.3m, the shielding effectiveness is increased by about 20dB on average compared with a multi-layer carbon fiber composite material with an angle of 45 ° for six layers, the single-station echo width is reduced by about 0.5m, and the scattering cut-off is smaller.
Example 2:
as shown in fig. 5, the carbon fiber composite material layers have eight layers, which are respectively: the carbon fiber composite material comprises a first composite material layer, a second composite material layer, a third composite material layer, a fourth composite material layer, a fifth composite material layer, a sixth composite material layer, a seventh composite material layer and an eighth composite material layer, wherein the first composite material layer is vertically arranged between carbon fiber filaments and the horizontal ground, the second composite material layer is vertically arranged between the carbon fiber filaments and the horizontal ground, the included angle between the carbon fiber filaments and the horizontal ground is 30 degrees, the included angle between the carbon fiber filaments and the horizontal ground is 60 degrees, the included angle between the carbon fiber filaments and the horizontal ground is 120 degrees, the included angle between the carbon fiber filaments and the horizontal ground is 150 degrees, and the carbon fiber filaments and the horizontal ground are parallel. The angle difference values of the eight composite carbon fiber composite material layers in the arrangement direction of the carbon fiber wires are 90 degrees, 30 degrees and 30 degrees in sequence, and the dimensions of the parameters are as follows: d=106 cm, epsilon m =2.2, h=3m; p=0.09 mm, d=0.126 mm. As shown in FIGS. 6 and 7, the echo width measurement frequency range in this embodiment is 2-18 GHz, and the incident wave is vertically polarizedPlane waves. The shielding effectiveness is increased by about 60dB on average compared to a multi-layer carbon fiber composite having an angle of 90 ° with eight layers, the single-station echo width is reduced by about 0.1m, and the shielding effectiveness is increased by about 15dB on average compared to a multi-layer carbon fiber composite having an angle of 45 ° with eight layers, the single-station echo width is reduced by about 0.34m, and there is a smaller scattering stub.
The cylindrical surface carbon fiber composite material multilayer structure which is arranged at non-equiangular intervals can be suitable for application of space rocket cabins and the like.
Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made therein without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.

Claims (2)

1. A cylindrical carbon fiber composite material structure with low radar cross section characteristic is characterized in that: the carbon fiber composite material comprises six or eight carbon fiber composite material layers, wherein the carbon fiber composite material layers are formed by resin material substrates and carbon fiber filaments, and the carbon fiber filaments are uniformly distributed in the resin material substrates; the arrangement directions of the carbon fiber filaments in two adjacent carbon fiber composite material layers are different, and the angle difference values of the arrangement directions are not uniform;
carbon fiber wires in the same resin material substrate are parallel to each other;
the carbon fiber composite material structure is cylindrical, and the inner diameter D of the carbon fiber composite material structure is 106-112 cm;
thickness of the carbon fiber composite material layerd0.126-0.166 mm;
dielectric constant of the resin material substrate2.0 to 3.2;
height of the carbon fiber composite structureh0.5 m-8 m;
spacing of carbon fiber filaments within the same resin material substratepIs 0 to08-0.1 mm, and both ends of the carbon fiber wires are shielded by metal plates;
the carbon fiber composite material layer has six layers, respectively: the carbon fiber composite material comprises a first composite material layer, a second composite material layer, a third composite material layer, a fourth composite material layer, a fifth composite material layer and a sixth composite material layer, wherein the first composite material layer is vertically arranged between carbon fiber filaments and the horizontal ground, the second composite material layer is parallel to the horizontal ground, the included angle between the carbon fiber filaments and the horizontal ground is 45 degrees, the fourth composite material layer is 135 degrees, the fifth composite material layer is parallel to the horizontal ground, and the sixth composite material layer is vertically arranged between the carbon fiber filaments and the horizontal ground;
or:
the carbon fiber composite material layer has eight layers, respectively: the carbon fiber composite material comprises a first composite material layer, a second composite material layer, a third composite material layer, a fourth composite material layer, a fifth composite material layer, a sixth composite material layer, a seventh composite material layer and an eighth composite material layer, wherein the first composite material layer is vertically arranged between carbon fiber filaments and the horizontal ground, the second composite material layer is vertically arranged between the carbon fiber filaments and the horizontal ground, the included angle between the carbon fiber filaments and the horizontal ground is 30 degrees, the included angle between the carbon fiber filaments and the horizontal ground is 60 degrees, the included angle between the carbon fiber filaments and the horizontal ground is 120 degrees, the included angle between the carbon fiber filaments and the horizontal ground is 150 degrees, and the carbon fiber filaments and the horizontal ground are parallel.
2. A cylindrical carbon fiber composite structure having low radar cross-section characteristics as set forth in claim 1, wherein: the carbon fiber filaments are T800-H carbon fiber filaments.
CN202310356835.XA 2023-04-06 2023-04-06 Cylindrical carbon fiber composite material structure with low radar cross section characteristic Active CN116373404B (en)

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Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111125861A (en) * 2019-09-10 2020-05-08 西北工业大学 Efficient wave-absorbing ultrathin carbon fiber reinforced composite material and design optimization method thereof
CN213073498U (en) * 2020-09-22 2021-04-27 西北工业大学 Electromagnetic shielding carbon fiber reinforced composite material based on 3D printing
CN112781443A (en) * 2021-01-04 2021-05-11 宁波曙翔新材料股份有限公司 Stealth, ablation and bearing integrated light launching box and preparation method thereof

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111125861A (en) * 2019-09-10 2020-05-08 西北工业大学 Efficient wave-absorbing ultrathin carbon fiber reinforced composite material and design optimization method thereof
CN213073498U (en) * 2020-09-22 2021-04-27 西北工业大学 Electromagnetic shielding carbon fiber reinforced composite material based on 3D printing
CN112781443A (en) * 2021-01-04 2021-05-11 宁波曙翔新材料股份有限公司 Stealth, ablation and bearing integrated light launching box and preparation method thereof

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