Fiber-metal hybrid composite material filled with MRE interlayer and preparation method thereof

A technology of composite materials and fiber metal, which is applied in the field of design and preparation of fiber metal hybrid composite materials, can solve problems such as complex preparation process, collapse, and easy damage of foam honeycomb core structure, and achieve simple process, improved damping and energy absorption efficiency, and process mature effect

Active Publication Date: 2021-06-01
NORTHEASTERN UNIV LIAONING
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the foam honeycomb core structure is easily damaged and collapsed during preparation, the preparation process is relatively complicated, and the filling consistency is difficult to guarantee
The above technology mainly involves the preparation method of viscoelastic interlayer materials, and cannot actively control its material properties (stiffness, damping and other parameters)

Method used

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  • Fiber-metal hybrid composite material filled with MRE interlayer and preparation method thereof

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preparation example Construction

[0060] The preparation method of the fiber metal hybrid composite material of filling MRE interlayer, comprises the following steps:

[0061] Step 1, preparation of premixed materials:

[0062] According to the mass percentage, respectively weigh 60-80% of iron powder, 10-20% of lubricant, and 10-20% of matrix, mix the three, and stir evenly to obtain a fluid premixed material;

[0063] Step 2, laminate preparation:

[0064] (1) Take two alloy plates, place one of them in a rectangular mold, spread the above-mentioned premixed materials evenly on the surface of the alloy plate, the laying thickness is 1-2 mm, place another alloy plate on the upper layer, and roll Press until the thickness of the premixed material is 0.8-1.5mm;

[0065] (2) Stand the premixed material after rolling for 48-72 hours to complete curing and forming to form a laminate;

[0066] Step 3, copper wire winding:

[0067] Take out the laminated board, wind the copper wire along the width direction of t...

Embodiment 1

[0091] Fiber-metal hybrid composites filled with MRE interlayers include laminates, and their structural schematic diagrams are shown in figure 1 As shown, the laminated board 4 is used as the middle layer, and the fiber cloth layer 2 and the alloy plate layer 1 are arranged symmetrically up and down in sequence; wherein, the surface of the laminated board 4 is tightly wound with copper wires 3;

[0092] The laminated board 4 is formed by wrapping raw materials with alloy plates, and the raw materials and mass percentages are: 60% of carbonyl iron powder, 20% of silicone oil, and 20% of silicone rubber;

[0093] The thickness of the raw material wrapped by the laminate 4 is 0.8 mm, the total number of layers of fiber cloth is 16 layers, the alloy plate layer is an aluminum alloy plate, and the thickness of a single layer is 0.3 mm. The alloy plate in the laminate 4 is an aluminum alloy plate, and the single layer The thickness is 0.3mm.

[0094] The preparation method of the ...

Embodiment 2

[0108] The preparation method of the fiber metal hybrid composite material of filling MRE interlayer, comprises the following steps:

[0109] Step 1, preparation of premixed materials:

[0110] According to the mass percentage, weigh 64% of carbonyl iron powder, 18% of silicone oil, and 18% of silicone rubber, mix the three in a beaker, stir evenly with a glass rod, and obtain a fluid premixed material with a viscosity of 110,000 cps;

[0111] Step 2, laminate preparation:

[0112] (1) Take two aluminum alloy plates, after removing oil and rust surface pretreatment, place one of them in a rectangular mold, and spread the above premixed material on the surface of the alloy plate evenly, with a laying thickness of 1.2mm. The upper layer is aligned with another alloy plate, and the pressure roller is used to repeatedly roll until the thickness of the premixed material is 1mm;

[0113] (2) Two permanent magnets with different magnetic properties are symmetrically arranged on bo...

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Abstract

The fiber metal hybrid composite material filled with MRE interlayer and the preparation method thereof of the present invention. The composite material includes a laminated board wrapped with iron powder, a lubricant and a matrix to form a raw material. The laminated board is used as the middle layer, and the upper and lower layers are symmetrically arranged with a fiber cloth layer and an alloy board layer in sequence. The surface of the laminated board is tightly wound with copper. Wire. When preparing, mix according to the ratio of raw materials, lay alloy plates up and down, roll to form a laminate, and then wind copper wires, center on the laminate, lay fiber cloth and alloy plates up and down in turn, each layer is glued and rolled to obtain a filling Fiber-metal hybrid composites with MRE sandwiches. The process of the method is simple and the process is mature. The magnetorheological elastomer material in the laminate improves the damping and energy absorption efficiency, and can control the stiffness and damping characteristics within a certain range by changing the magnetic field by controlling the current in the coil.

Description

Technical field: [0001] The invention belongs to the technical field of design and preparation of fiber-metal hybrid composite materials, and in particular relates to a fiber-metal hybrid composite material filled with MRE interlayers and a preparation method thereof. Background technique: [0002] Fiber metal hybrid composite material is a new type of heterogeneous composite material, which combines the advantages of good ductility and corrosion resistance of metal materials with the characteristics of light weight and high strength of fiber reinforced composite materials. In recent years, it has been gradually used in military aircraft, The fuselage skin, vertical and horizontal tail leading edge, rectifying plate, fairing, upper fuselage panel and upper panel stringer of civil aircraft are widely used. As the structural configuration of the above-mentioned composite materials becomes more and more complex, and the working environment becomes more and more harsh, how to re...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B32B5/02B32B5/26B32B15/02B32B15/14B32B15/18B32B15/20B32B37/10B32B38/18C08L83/04C08K3/18
CPCB32B5/02B32B5/26B32B15/14B32B15/18B32B15/20B32B37/10B32B38/18B32B2038/0076B32B2250/40B32B2262/103C08L83/04C08K3/18
Inventor 李晖王文煜任旭辉王子恒刘洋赵思齐胡晓岳闻邦椿
Owner NORTHEASTERN UNIV LIAONING
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