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Aircraft fairing leading edge assembly

A fairing and leading edge technology, which is applied in the field of aircraft fairing leading edge components, can solve the problems that cannot fully meet the safety requirements of aircraft surface anti-icing and deicing

Active Publication Date: 2016-01-06
LIYANG TECH DEV CENT
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the performance of most of the current low surface energy hydrophobic coatings cannot fully meet the safety requirements for anti-icing of aircraft surfaces.

Method used

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Examples

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Embodiment Construction

[0020] The cowling leading edge assembly according to the present invention comprises a cowling leading edge shell and an anti-icing coating positioned at the outside of the shell, the anti-icing coating comprises a primer and a finish paint, and the primer is an epoxy modified alkyd The resin primer and top coat are silicone modified acrylate paints. Preferably, the dry film thickness of the primer and topcoat is 24 microns and 42 microns, respectively. Preferably, the front edge of the fairing referred to in the present invention refers to the front part of the fairing projected on the front 1 / 5 range of the chord length. More preferably, the thickness of the anti-icing coating on the leading edge shell is not uniform, for example, gradually becomes thinner from the front end of the fairing to the rear, or gradually becomes thicker and then gradually thinner, which can not only improve the anti-icing characteristics but also reduce the Little effect on fairing aerodynamics....

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Abstract

An aircraft radome leading edge assembly comprises a radome leading edge shell and an anti-icing coat positioned outside the shell, the anti-icing coat comprises a primer and a finish, the primer is an epoxy modified alkyd resin primer, and the finish is an organosilicon modified acrylate coating; the thicknesses of the dry films of the primer and the finish are 24mum and 42mum respectively; and the organosilicon modified acrylate coating comprises 55-65wt% of an organosilicon modified acrylic resin, 20-25wt% of a color filler, 3wt% of nanometer calcium carbonate, 3wt% of nanometer aluminum oxide, 1wt% of a leveling agent, 0.8wt% of an antifoaming agent, 1.2wt% of a dispersant, 0.5wt% of a catalyst and 3-5wt% of a solvent. The radome leading edge assembly made in the invention can effectively reduce the formation of ice layers on the leading edge of a radome, and is in favor of the shedding of formed ice layers.

Description

technical field [0001] The invention relates to an aircraft fairing leading edge assembly. Background technique [0002] In today's world, airplanes have gradually become a means of transportation that people pay more and more attention to because of their fast and safe features. However, when the aircraft flies at subsonic speeds below a certain critical Mach number in icing weather conditions, the windward surfaces of some components, such as the leading edge of the fairing, will freeze due to the impact and accumulation of water droplets in the atmosphere. A large number of accidents and studies have shown that even a small amount of ice accumulation on key parts of the aircraft will lead to a decrease in the lift of the aircraft and an increase in flight resistance, which will lead to deterioration of the aerodynamic qualities of the aircraft such as maneuverability and stability. Especially when the aero-engine is under a certain temperature and humidity on the ground ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B32B27/08B32B27/36B32B27/28B64C1/00C09D151/08C09D7/12C08F283/12B05D7/26B05D3/12
Inventor 张俊
Owner LIYANG TECH DEV CENT
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