Nano superhydrophobic surface used for airplane antifreezing and deicing and preparation method thereof

A super-hydrophobic surface and nano-technology, applied in aircraft parts, deicing devices, optomechanical equipment, etc., can solve problems such as huge power consumption, difficult implementation, and complex design, so as to reduce the amount of condensation and reduce icing degree, the effect of reducing the viscosity

Inactive Publication Date: 2010-05-12
SHANGHAI JIAO TONG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] After searching the literature of the prior art, it was found that in the patent of Chinese application publication number: CN1347630, entitled "Method and System for Surface Deicing", it is proposed to use ferroelectrics, lossy dielectrics, ferromagnets or semiconductor materials for coatings Arranged under the aircraft skin, and apply alternating current through the electrical conductor to generate an electromagnetic field. After the coating absorbs the energy from the electroma...

Method used

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  • Nano superhydrophobic surface used for airplane antifreezing and deicing and preparation method thereof
  • Nano superhydrophobic surface used for airplane antifreezing and deicing and preparation method thereof
  • Nano superhydrophobic surface used for airplane antifreezing and deicing and preparation method thereof

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Embodiment 1

[0031] Such as figure 1 As shown, this embodiment includes: a substrate 1, a hydrophobic microstructure 2 and a hydrophobic nano-modified film 3, wherein: the hydrophobic microstructure 1 is connected to the upper surface of the substrate 1, and the secondary hydrophobic nano-film 3 is located on the upper surface of the hydrophobic microstructure 2, forming Functional surfaces with superhydrophobic properties.

[0032] The base 1 is an aircraft skin made of aluminum alloy;

[0033] The hydrophobic microstructure 2 is a vertical columnar array structure, including a number of metal columns 4 with a parallel spacing of 10 microns. The metal columns are cylinders, the lower end of which is fixedly connected to the substrate, and the cross section of the upper end is a square structure.

[0034] The contact area between the metal pillar 4 and the substrate 1 is 100 square micrometers, and the height is 3 micrometers.

[0035] The components and contents of the hydrophobic nano-...

Embodiment 2

[0044] Anti- / de-icing surface of aircraft based on micro-nano superhydrophobic structure using cones as hydrophobic microstructures

[0045] Figure 5 uses a cone with a needle-point shape on the upper end surface as the hydrophobic microstructure 2. As shown in the figure, the hydrophobic microstructure 2 of the super-hydrophobic aircraft anti- / de-icing surface based on the micro-nano scale structure is formed by the cone on the aircraft. Arrayed on the leather base 1, the height of the conical microstructure 2 is 3-15 microns, and the radius of the lower end section is 5-50 microns. The array distribution pitch and the coating form of the nano-modified film 3 are consistent with those in Example 1. The preparation method of this embodiment is basically the same as that of Example 1.

Embodiment 3

[0046] Embodiment 3 adopts cuboid as the aircraft anti-icing / de-icing surface based on the micro-nano superhydrophobic structure of the hydrophobic microstructure

[0047] Fig. 6 is the schematic diagram of the aircraft anti- / de-icing surface structure based on the micro-nano super-hydrophobic structure of the present embodiment where the hydrophobic micro-structure 2 is a cuboid. , arrayed on the aircraft skin substrate 1, the height of the cuboid microstructure 2 is 3-15 microns, the cross-section can be square or rectangular, the length of the cross-section is 5-50 microns, and the width is also 5-50 microns. The nanoparticle radius of the hydrophobic nano-modified film 3 on the superhydrophobic surface, the array distribution spacing of the cuboids on the aircraft skin substrate 1, and the coating form of the nano-modified film 3 are consistent with those in Example 1. The preparation method of this embodiment is basically the same as that of Example 1.

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Abstract

The invention belongs to the technical field of surface treatment, and relates to a nano superhydrophobic surface used for airplane antifreezing and deicing and a preparation method thereof. The preparation method comprises the following steps: making a hydrophobic microstructure on a substrate by non-silicon surface micromachining technology or microreplication method; coating a nano decorative film on the surface of the hydrophobic microstructure; and baking the prepared hydrophobic microstructure and the substrate coated with the nano decorative film to obtain the dry and clean superhydrophobic surface. The nano superhydrophobic surface improves the contact properties between the surface of an airplane and waterdrops and greatly reduces the degree that a fuselage is infiltrated by the waterdrops; and the nano decorative film can also further reduce the viscous force of the waterdrops when the waterdrops slip the surface of the fuselage, the number of the waterdrops condensed on the surface of the fuselage is reduced, the icing degree on the surface of the airplane is effectively reduced, and the aim of high-efficiency, clean and low-cost airplane ice prevention/removal is achieved.

Description

technical field [0001] The invention relates to a material in the technical field of surface treatment and its preparation, in particular to a nanometer super-hydrophobic surface for aircraft anti-icing and deicing and a preparation method thereof. Background technique [0002] During the flight, the windward surface of the aircraft often freezes due to the impact and accumulation of supercooled water droplets, which will bring great harm to flight safety. For example, the icing of the speed measuring and pressure measuring sensor probes will cause the instrument indication to be distorted; the icing of the aircraft (tail) wing will affect the aerodynamic shape, increase the flight resistance, reduce the lift, and affect the maneuverability and stability of the whole aircraft; Ice intake components can stall the engine, etc. According to a report in the United States in 1998, in the ten years from 1988 to 1998, there were no less than 10 accidents caused by the sudden icing...

Claims

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Application Information

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IPC IPC(8): B64C1/12B64D15/00G03F7/00
Inventor 丁桂甫杨卓青王艳汪红姚锦元
Owner SHANGHAI JIAO TONG UNIV
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