Light aircraft thermal protection structure

Abstract

The utility model provides a light aircraft thermal protection structure which comprises a thermal protection main body with a porous network structure, the surface of the thermal protection main body is subjected to compactness treatment to form a waterproof layer, the thermal protection main body is bonded to the surface of aircraft skin in a gluing mode, and the waterproof layer is arranged on the surface of the thermal protection main body. And a gap between the thermal protection main bodies is filled with sealing putty. According to the light aircraft thermal protection structure, high temperature can be prevented from being transmitted into the aircraft body, and the waterproof requirement is met.

Description

Technical Field

[0001] The present application belongs to the field of aircraft structure design, and in particular relates to a lightweight aircraft thermal protection structure. Background Art

[0002] At present, high-speed aircraft generally use thicker insulation tiles installed on the outer surface for thermal protection, but thicker insulation tiles will affect the performance of lightweight aircraft. In order to optimize the thermal protection structure and improve the performance of the aircraft, the existing technology can arrange the thermal protection structure inside the skin. Conventional low-density thermal protection materials are loose inside, mostly with loose porous structures, which are difficult to meet the waterproof requirements. Utility Model Content

[0003] The purpose of the present application is to provide a lightweight aircraft thermal protection structure to solve or alleviate at least one problem in the background technology.

[0004] The technical solution of the present application is: a lightweight aircraft thermal protection structure, which includes: a thermal protection body with a porous network structure, the surface of the thermal protection body is treated by densification to form a waterproof layer, the thermal protection body is bonded to the surface of the aircraft skin by gluing, and the gaps between adjacent thermal protection bodies are filled with sealing putty.

[0005] Furthermore, the heat protection body is a foam material, and a porous network structure is formed by mutual aggregation of colloidal particles.

[0006] Furthermore, the heat protection body is a block structure.

[0007] Furthermore, the aircraft skin is made of heat-resistant materials such as titanium alloy.

[0008] The lightweight aircraft thermal protection structure provided in the present application can not only block the high temperature from being transmitted into the fuselage, but also meet the waterproof requirements. BRIEF DESCRIPTION OF THE DRAWINGS

[0009] In order to more clearly illustrate the technical solution provided by the present application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of the present application.

[0010] Figure 1 This is a schematic diagram of the thermal protection structure of the lightweight aircraft of this application. DETAILED DESCRIPTION

[0011] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below in conjunction with the drawings in the embodiments of this application.

[0012] In order to enable the thermal protection structure of a lightweight aircraft to both block the transfer of high temperature into the fuselage and meet the waterproof requirement, the present application provides a thermal protection structure of a lightweight aircraft.

[0013] like Figure 1 As shown, the lightweight aircraft internal thermal protection structure provided by the present application mainly includes a thermal protection body 3 with a porous network structure, and the thermal protection body 3 is a block structure. In some embodiments of the present application, the thermal protection body 3 is a foam material, which is a nanoporous network structure formed by the mutual aggregation of colloidal particles, and has the characteristics of low thermal conductivity and low density.

[0014] However, due to the porous characteristics of the heat protection body 3, it has strong water and moisture absorption properties. After the block-shaped heat protection body 3 is manufactured by a mold, its surface is densified to form a waterproof layer 2.

[0015] The heat protection body 3 is bonded to the surface of the aircraft skin 1 by means of adhesive bonding 4, and the gaps between the block-shaped heat protection bodies 3 are filled with high-temperature sealing putty 5. In some embodiments of the present application, the aircraft skin 1 can be made of heat-resistant materials such as titanium alloy.

[0016] The lightweight aircraft thermal protection structure provided in the present application can not only block the high temperature from being transmitted into the fuselage, but also meet the waterproof requirements.

[0017] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A lightweight aircraft thermal protection structure, characterized in that: The lightweight aircraft thermal protection structure includes: a thermal protection body with a porous network structure, the surface of the thermal protection body is treated by densification to form a waterproof layer, the thermal protection body is bonded to the surface of the aircraft skin by gluing, and the gaps between adjacent thermal protection bodies are filled with sealing putty.

2. The lightweight aircraft thermal protection structure according to claim 1, characterized in that: The heat protection body is a foam material, and a porous network structure is formed by mutual aggregation of colloidal particles.

3. The lightweight aircraft thermal protection structure according to claim 2, characterized in that: The heat protection body is a block structure.

4. The lightweight aircraft thermal protection structure according to claim 1, characterized in that: The aircraft skin is made of titanium alloy heat-resistant material.

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