Shell-tile integrated thermal protection structure

Abstract

The utility model provides a shell-tile integrated thermal protection structure which comprises a surface layer made of a first material, a middle layer made of a second material and an inner layer made of a third material, the first material adopts a ceramic-based thermal protection material, the second material adopts a polyimide foam thermal protection material, and the third material adopts a resin-based composite material. According to the shell-tile integrated thermal protection structure, thermal protection materials with different properties can be combined in a multi-layer mode in a relatively simple mode, so that the defects that a single thermal insulation tile is high in brittleness, poor in mechanical property and the like can be overcome, and the problems of thermal insulation and pneumatic impact of the outer surface of an aircraft can be solved.

Description

Technical Field

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

[0002] When a high-speed aircraft is flying, its outer surface will generate a lot of aerodynamic heat and be subjected to the test of atmospheric dynamic loads. It is necessary to solve the problems of thermal insulation and aerodynamic impact on the outer surface of the aircraft. At present, the structure of installing thick thermal insulation tiles on the outer surface of the aircraft is generally adopted. In order to improve the thermal insulation performance, a single method of increasing the thickness of the thermal insulation layer is usually adopted, but this method will increase the weight of the structure and the performance is not significant. In addition, the thermal insulation tiles themselves have the disadvantages of high brittleness and poor mechanical properties.

[0003] In order to improve the performance of aircraft, a new type of thermal protection structure is needed. Utility Model Content

[0004] The purpose of the present application is to provide a shell-and-tile integrated thermal protection structure to solve or alleviate at least one problem in the background technology.

[0005] The technical solution of the present application is: a shell-tile integrated thermal protection structure, comprising: a surface layer composed of a first material, a middle layer composed of a second material, and an inner layer composed of a third material, wherein the first material is a ceramic fiber reinforced thermal protection composite material, the second material is a ceramic tile thermal protection insulation material, and the third material is a resin-based composite material.

[0006] Furthermore, the first material constituting the surface layer and the second material constituting the middle layer are formed into an integral shell structure through a high-temperature sintering heat treatment process, and the integral shell structure is bonded with the third material constituting the inner layer to form an integrated structure.

[0007] The shell-tile integrated thermal protection structure provided in the present application can combine thermal protection materials of different properties in a multi-layer manner in a relatively simple manner, thereby overcoming the shortcomings of high brittleness and poor mechanical properties of a single thermal insulation tile, and solving the problems of thermal insulation and aerodynamic impact on the outer surface of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0008] 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.

[0009] Figure 1 This is a schematic diagram of the shell-shell integrated thermal protection structure of this application. DETAILED DESCRIPTION

[0010] 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.

[0011] In order to enable the thermal insulation tiles in the prior art to overcome the shortcomings of high brittleness and poor mechanical properties of thermal protection materials, and to solve the problems of thermal insulation and aerodynamic impact on the outer surface of the aircraft, the present application provides a new combined thermal protection structure.

[0012] like Figure 1 As shown, the present application provides a new type of combined thermal protection structure which is a shell-shell integrated thermal protection structure, which includes a surface layer 11 composed of a first material, a middle layer 12 composed of a second material, and an inner layer 13 composed of a third material, wherein the first material is a material with friction resistance, high temperature resistance, and corrosion resistance, the second material is a material with low thermal conductivity, high temperature resistance, and corrosion resistance, and the third material is a material with a higher ability to withstand overall loads and maintain stability.

[0013] In the preferred embodiment of the present application, the first material of the surface layer 11 is made of ceramic fiber reinforced thermal protection composite material, the second material of the middle layer 12 is made of ceramic tile thermal protection insulation material, and the third material of the inner layer 13 is made of resin-based composite material.

[0014] Furthermore, the surface layer 11 and the middle layer 12 are formed into a shell tile integral structure through a high-temperature sintering heat treatment process, and then bonded with the inner layer 13 to form an integrated structure.

[0015] In the present application, the thermal protection layer of the surface layer 11 is designed to be thinner in thickness and lighter in weight, and has the characteristics of good wear resistance, high temperature resistance and corrosion resistance; the thermal protection layer of the middle layer 12 is designed to be thicker in thickness, lighter in weight, loose in texture, has lower thermal conductivity, and is resistant to high temperatures and has good corrosion resistance; the thermal protection layer of the inner layer 13 is designed to be of the thickness of the aircraft skin, and has the characteristics of light weight, high strength, good fatigue resistance and corrosion resistance.

[0016] The shell-tile integrated thermal protection structure provided in the present application can combine thermal protection materials of different properties in a multi-layer manner in a relatively simple manner, thereby overcoming the shortcomings of high brittleness and poor mechanical properties of a single thermal insulation tile, and solving the problems of thermal insulation and aerodynamic impact on the outer surface of the aircraft.

[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 shell-tile integrated thermal protection structure, characterized in that: include: The surface layer is made of a first material, the middle layer is made of a second material, and the inner layer is made of a third material, wherein the first material is a ceramic-based thermal protection material, the second material is a polyimide foam thermal protection material, and the third material is a resin-based composite material.

2. The shell-shoe integrated thermal protection structure according to claim 1, characterized in that: The first material constituting the surface layer and the second material constituting the middle layer are formed into a shell tile integral structure through a high-temperature sintering heat treatment process, and the shell tile integral structure and the third material constituting the inner layer are bonded to form an integrated structure.

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