Aircraft anti-icing composite material and preparation method thereof

A composite material and deicing technology, applied in the field of aviation chemistry, can solve the problems of poor performance of deicing materials

Pending Publication Date: 2020-02-11
上海鸿鹄骥航科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In view of the above-mentioned defects of the prior art, what the present invention aims to solve is the problem that the anti-icing materials currently used on aircraft have poor performance after long-term repeated use.

Method used

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  • Aircraft anti-icing composite material and preparation method thereof
  • Aircraft anti-icing composite material and preparation method thereof
  • Aircraft anti-icing composite material and preparation method thereof

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0034] The anodized aluminum single-pass porous material with a pore diameter of 40nm, a pore depth of 30um, and a pore spacing of 300nm is adhered to an aluminum plate with the same area and a thickness of 2mm, with the side with holes facing up. Adhere N55 NdFeB magnets of the same area under the aluminum plate, and then suspend the magnetic particles into 5-10nm spherical iron tetroxide, and dissolve them in the base liquid after surface treatment with sodium oleate to obtain the magnetic fluid. The base liquid is mainly composed of weight The percentage is 80% of paraffin oil and 20% by weight of Grade III clean environment-friendly aviation kerosene, which can be purchased on the market. The magnetic fluid is added to the surface of the anodized aluminum single-pass porous material until it does not overflow from the surface of the anodized aluminum single-pass porous material, and the anti-icing composite material is obtained.

[0035] Such as figure 1 Shown is the SEM ...

Embodiment 2

[0038] The anodized aluminum single-pass porous material with a pore diameter of 200nm, a pore depth of 80um, and a pore spacing of 500nm was adhered to a polymethyl methacrylate plate with the same area and a thickness of 4mm, with the side with holes facing up. Adhere EP-B type NdFeB magnets of the same area under the aluminum plate, and then make the suspended magnetic particles into 10-20nm spherical iron tetroxide, and after surface treatment with PEG2000, dissolve them in the base liquid to obtain the magnetic fluid. It is added to the surface of the anodized aluminum single-pass porous material until it does not overflow from the surface of the anodized aluminum single-pass porous material, and the anti-icing composite material is obtained.

[0039] Such as image 3 Shown is the SEM image of the anodized aluminum single-pass porous material.

[0040] The anti-icing performance of the composite material is evaluated by the ice adhesion test. The dynamometer is Sandu SH-...

Embodiment 3

[0042]The anodized aluminum single-pass porous material with a pore diameter of 100nm, a pore depth of 60um, and a pore spacing of 400nm was adhered to a polymethyl methacrylate plate with the same area and a thickness of 3mm, with the side with holes facing up. Adhere a samarium-cobalt permanent magnet of the same area under the aluminum plate, and then make the suspended magnetic particles 15-20nm spherical ferric oxide, which is surface-treated with polyethylene glycol (PEG2000) with an average molecular weight of 2000, and then dissolved in the base liquid The magnetic fluid is obtained, and the magnetic fluid is added to the surface of the anodized aluminum single-pass porous material until it does not overflow from the surface of the anodized aluminum single-pass porous material, and the anti-icing composite material is obtained.

[0043] Such as Figure 5 As shown, the anti-icing performance of the composite material is evaluated by the ice adhesion test, the dynamomete...

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Abstract

The invention discloses an aircraft anti-icing composite material and a preparation method thereof. The composite material is of a multi-layer structure, wherein the multi-layer structure consists ofa substrate, a flaky material and a permanent magnet from top to bottom in sequence; the substrate consists of anodic aluminum oxide one-way porous material absorption magnetic fluids; the flaky material is one of a polymethyl methacrylate plate or an aluminum plate; the bottom surface of the substrate is bonded with the flaky material through an adhesive; and the permanent magnet is bonded with the bottom surface of the flaky material through an adhesive. The composite material disclosed by the invention is excellent in anti-icing performance, ice can barely adhere to the substrate, formed ice can be very easily removed from a surface, in addition, the anti-icing service life is long, nearly 70 times of icing and deicing circulation can be endured, and the composite material has the advantages of being simple and convenient in combination method, low in cost, good in practicability, and the like, can be effectively applied to aircrafts with long lasting effects, and is capable of preventing icing accidents.

Description

technical field [0001] The invention relates to the field of aviation chemistry, in particular to an aircraft anti-icing composite material and a preparation method thereof. Background technique [0002] Icing is a common phenomenon in nature. Except for a few cases, people suffer from various hazards caused by icing. In the field of wind power generation, wind farms built in cold and humid areas also have many adverse effects on the icing problem on the surface of wind turbine blades and unit surfaces. Icing on the surface of the blades will increase the load on the blades or even deform them, reduce the service life of the blades, affect the balance of the wind turbine, reduce the power generation efficiency, and cause damage to the wind turbine. It has been reported that icing on the surface of wind turbine blades will cause the annual power generation rate of the unit to drop by as much as 50%. In terms of outdoor power transmission facilities and communication lines, ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B32B27/30B32B3/12B32B7/12B32B9/00B32B9/04B32B15/04B32B15/16B32B27/06B32B27/14B32B33/00
CPCB32B3/12B32B5/16B32B7/12B32B9/00B32B9/041B32B9/045B32B15/04B32B15/16B32B27/06B32B27/14B32B27/308B32B33/00B32B2605/18
Inventor 刘洪黄小彬孔维梁
Owner 上海鸿鹄骥航科技有限公司
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