Skin structure for wing, aircraft having skin structure and method for mounting skin structure

Abstract

The present invention relates to a skin structure for a wing, the skin structure comprising: a skin forming a part of an aerodynamic configuration of the wing; and a skin body which is internally attached to the skin skin with respect to the wing and protrudes toward the interior of the wing, in which the skin skin includes an outer surface layer and a thermal insulation layer, the skin body is internally attached to the thermal insulation layer with respect to the wing, and the thermal insulation layer is internally attached to the outer surface layer with respect to the wing, wherein the thermal conductivity of the material of the insulating layer is lower than that of the material of the skin body, and wherein the hardness of the material of the outer skin layer is higher than that of the material of the insulating layer. The invention further relates to an aircraft with the skin structure and a method for mounting the skin structure.

Description

technical field [0001] The present invention relates to a skin structure for an airfoil, in particular to a skin structure for a high-temperature region of a fixed leading edge of an airfoil that meets heat insulation requirements. The invention also relates to an aircraft with a skin structure and a method for installing the skin structure. Background technique [0002] The skin structure of the aircraft wing, especially the skin structure of the fixed leading edge of the wing, should be able to meet the requirements of anti-bird strike, maintain the aerodynamic shape, and bear the coordinated deformation load of the wing. These requirements can be summarized that the skin structure should have the strength of the wing structure according to the standard. [0003] At present, the skin structure of aircraft wings generally uses glass fiber / carbon fiber panels and honeycomb core reinforcement structures as composite skin structures, such as Figure 1A As shown, it has light ...

AI Technical Summary

Problems solved by technology

[0006] The temperature of the discharged hot air is generally above 155°C, which exceeds the allowable temperature of conventional composite materials for composite skin structures, and easily causes over-temperature damage

However, designing or selecting high-temperature-resistant composite materials (such as thermoplastic materials) for this alone requires a small area, a small amount, and no versatility, and the cost of individual customization is high.

Although the metal skin structure has better high temperature resistance, it is heavy and has disadvantages in terms of economy.

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