A thickness-adaptive flexible thermal protection system and a method of manufacturing the same

Abstract

The application provides a thickness-adaptive flexible thermal protection system and a preparation method thereof. The flexible thermal protection system comprises, from top to bottom, a high-temperature-resistant fiber flexible surface layer, a high-temperature-resistant metal foil radiation shielding layer, a fluffy high-temperature-resistant fiber cotton heat-insulating deformation reserve function layer and a low-permeability elastic deformation material layer, 2-3 adjacent layers in the high-temperature-resistant fiber flexible surface layer, the high-temperature-resistant metal foil radiation shielding layer, the fluffy high-temperature-resistant fiber cotton heat-insulating deformation reserve function layer and the low-permeability elastic deformation material layer are stitched into an integral structure by high-temperature-resistant fiber stitching lines for multiple times, the integral structure is compressed to a reserve deformation position and integrally stitched by a characteristic temperature failure stitching line, the characteristic temperature failure stitching line is broken at a preset temperature to release the deformation reserve of the integral structure. The flexible thermal protection system can automatically release the reserve deformation at the preset temperature, and the high-temperature adaptability of the flexible thermal protection system of an aerospace high-speed aircraft is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of aerospace engineering pneumatic thermal protection systems, and in particular to a thickness-adaptive flexible thermal protection system and a preparation method thereof. Background Art

[0002] Flexible thermal insulation materials play an important role in the thermal protection system of aerospace high-speed aircraft. In order to meet the requirements of repeated use of aerospace high-speed aircraft, high requirements are placed on the safety, reliability and high temperature resistance of thermal insulation materials.

[0003] Thermal insulation materials used on the surfaces of high-speed aerospace vehicles are primarily divided into two types: rigid and flexible. Compared to rigid ceramic materials, flexible insulation materials offer better thermal compatibility and are relatively simple to manufacture and install. Currently, the second generation of flexible insulation materials used on a large scale is primarily composed of quartz fiber, with a maximum operating temperature of 750°C. This insulation material consists of silica fiber wool sandwiched between woven silica quartz cloth, which is then sewn together with silica fiber sutures to enhance its strength.

[0004] However, when aerodynamic heating is applied to flexible thermal protection systems for high-speed aerospace vehicles, they can produce certain flexible or elastic deformations, which can deteriorate the local aerodynamic heating environment or even cause ablation failure of the flexible material. Therefore, a flexible thermal protection system that can improve the high-temperature adaptability of high-speed aerospace vehicles is desired.

[0005] In view of this, the present invention is proposed. Summary of the Invention

[0006] The purpose of the present invention is to provide a thickness-adaptive flexible thermal protection system and a preparation method thereof, in which the characteristic temperature failure suture line of the flexible thermal protection system automatically releases the reserve deformation after reaching a preset temperature, thereby suppressing and compensating the deformation of the flexible thermal protection system caused by aerodynamic thermal effects, thereby improving the high-temperature adaptability of the flexible thermal protection system of aerospace high-speed aircraft.

[0007] The present invention provides a thickness-adaptive flexible thermal protection system, comprising a high-temperature resistant fiber flexible surface layer, a high-temperature resistant metal foil radiation shielding layer, a fluffy high-temperature fiber cotton thermal insulation deformation reserve functional layer and a low-permeability elastic deformation material layer stacked in sequence from top to bottom. The adjacent 2-3 layers of the high-temperature resistant fiber flexible surface layer, the high-temperature resistant metal foil radiation shielding layer, the fluffy high-temperature fiber cotton thermal insulation deformation reserve functional layer and the low-permeability elastic deformation material layer are sewn multiple times into an integral structure through high-temperature fiber sutures. The overall structure is compressed to a reserve deformation position and is sewn as a whole through characteristic temperature failure sutures. The characteristic temperature failure sutures break at a preset temperature to release the deformation reserve of the overall structure.

[0008] In the present invention, the material of the high-temperature resistant fiber flexible surface layer is selected from a flexible fiber cloth material that is resistant to high temperatures and has the ability to deform; preferably, the flexible fiber cloth material can be selected from silicon carbide fiber woven cloth, carbon fiber woven cloth, alumina fiber woven cloth, silica fiber cloth, mullite fiber cloth, high silica fiber cloth, basalt fiber cloth or at least one of silicon carbide fiber woven cloth, carbon fiber woven cloth, alumina fiber woven cloth, silica fiber mesh, mullite fiber mesh, high silica fiber mesh and basalt fiber mesh; in addition, the weaving method of the flexible fiber cloth material is plain, twill or satin, the weaving volume density is 30-60%, and the single layer thickness is 0.1-0.3mm.

[0009] In the present invention, the material of the high-temperature resistant metal foil radiation shielding layer is selected from a metal foil material that is resistant to high temperatures and has deformation ability and radiation blocking properties; preferably, the metal foil material can be selected from at least one of nickel foil, stainless steel foil and aluminum foil; in addition, the single layer thickness of the metal foil material is 0.01-0.03 mm.

[0010] In the present invention, the material of the fluffy high-temperature fiber cotton thermal insulation deformation storage functional layer is selected from a flexible fiber reinforced aerogel composite material with low thermal conductivity and deformation ability; preferably, the flexible fiber reinforced aerogel composite material can be selected from at least one of silicon carbide fiber reinforced silica aerogel material, carbon fiber reinforced silica aerogel material, alumina fiber reinforced silica aerogel material, silica fiber reinforced silica aerogel material, mullite fiber reinforced silica aerogel material, high silica fiber reinforced silica aerogel material, basalt fiber reinforced silica aerogel material or silicon carbide fiber reinforced polyimide aerogel material, carbon fiber reinforced polyimide aerogel material, alumina fiber reinforced polyimide aerogel material, silica fiber reinforced polyimide aerogel material, mullite fiber reinforced polyimide aerogel material, high silica fiber reinforced polyimide aerogel material and basalt fiber reinforced polyimide aerogel material; in addition, the single layer thickness of the flexible fiber reinforced aerogel composite material is 0.2-0.5 mm.

[0011] In the present invention, the material of the low-permeability elastic deformation material layer is selected from a flexible fiber-reinforced elastomer composite material with low permeability and deformation ability; preferably, the flexible fiber-reinforced elastomer composite material can be selected from at least one of silicon carbide fiber-reinforced silicone rubber material, carbon fiber-reinforced silicone rubber material, alumina fiber-reinforced silicone rubber material, silica fiber-reinforced silicone rubber material, mullite fiber-reinforced silicone rubber material, high-silica fiber-reinforced silicone rubber material, basalt fiber-reinforced silicone rubber material, and aramid fiber-reinforced silicone rubber material; in addition, the single-layer thickness of the flexible fiber-reinforced elastomer composite material is 0.1-0.5 mm.

[0012] In the present invention, the four functional layers, namely the high-temperature resistant fiber flexible surface layer, the high-temperature resistant metal foil radiation shielding layer, the fluffy high-temperature fiber cotton insulation deformation reserve functional layer and the low-permeability elastic deformation material layer, can each select one or several single functional layers. The single functional layer can be composed of one or several layers of the same single layer material. The number of single layer material layers of the single functional layer can be selected by the designer according to the specific use environment.

[0013] After determining the specific number of functional layers, the high-temperature fiber flexible surface layer, the high-temperature metal foil radiation shielding layer, the fluffy high-temperature fiber cotton insulation deformation reserve functional layer, and the low-permeability elastic deformation material layer are stacked in order from top to bottom. After stacking, the high-temperature fiber sutures are first used to sew the entire flexible structure. There are no strict restrictions on the method of sewing the high-temperature fiber sutures, as long as they can sew the four functional layers into the overall structure without restricting the overall structure's deformation reserve.

[0014] In one embodiment, the fluffy high-temperature fiber cotton thermal insulation deformation storage functional layer is encapsulated by a fluffy high-temperature fiber cotton packaging material, the high-temperature resistant fiber flexible surface layer, the high-temperature resistant metal foil radiation shielding layer and the fluffy high-temperature fiber cotton packaging material are sewn by a high-temperature fiber suture line, and the fluffy high-temperature fiber cotton packaging material and the low-permeability elastic deformation material layer are sewn by a high-temperature fiber suture line, so that the above four functional layers are sewn into an integral structure.

[0015] The fluffy high-temperature fiber cotton packaging material is selected from a fiber cotton material that is resistant to high temperatures and has deformation and rebound properties. The fluffy high-temperature fiber cotton packaging material can be selected from at least one of silicon carbide fiber cotton, carbon fiber cotton, alumina fiber cotton, silica fiber cotton, mullite fiber cotton, high silica fiber cotton and basalt fiber cotton; in addition, the single-layer thickness of the fluffy high-temperature fiber cotton packaging material can be calculated and designed according to the designer's target control temperature, and the thickness range is usually 0.2-50.0mm.

[0016] The sutures used are, from high to low temperature, silicon carbide fiber, carbon fiber, alumina fiber, silica fiber, mullite fiber, high silica fiber, basalt fiber, steel wire, and aluminum wire. The appropriate suture can be selected based on actual needs. The suture density can be 1-5 stitches / cm², for example, 2-3 stitches / cm².

[0017] Specifically, the high-temperature fiber suture can be selected from at least one of silicon carbide fiber, carbon fiber, alumina fiber, silica fiber, mullite fiber, high-silica fiber, basalt fiber, steel wire, and aluminum wire. The high-temperature fiber suture is primarily used to maintain the integrity of the main structure. It is understood that the high-temperature fiber suture does not have the temperature characteristic failure function of a characteristic temperature failure suture and is not destroyed at a preset temperature.

[0018] After sewing the four functional layers into a single structure using high-temperature fiber sutures, the structure is compressed to its reserve deformation and then sewn together using characteristic temperature failure sutures. There are no strict restrictions on how the characteristic temperature failure sutures are sewn, and they can be sewn where the reserve deformation needs to be released. Specifically, the characteristic temperature failure sutures can be used to sew the four functional layers together: the high-temperature resistant fiber flexible surface layer, the high-temperature resistant metal foil radiation shielding layer, the fluffy high-temperature fiber cotton insulation deformation reserve functional layer, and the low-permeability elastic deformation material layer.

[0019] Furthermore, the characteristic temperature failure suture can be selected from at least one of tungsten wire, tantalum wire, molybdenum wire, niobium wire, zirconium wire, hafnium wire, nickel wire, iron wire, stainless steel wire, silver wire, copper wire, aluminum wire, carbon fiber wire, silicon carbide fiber wire, quartz fiber wire, high silica fiber wire, glass fiber wire, aramid fiber wire, and nylon fiber wire. The characteristic temperature failure suture is primarily designed to break at a preset temperature to release the deformation reserve of the overall structure.

[0020] The present invention also provides a method for preparing the thickness-adaptive flexible thermal protection system, comprising the following steps:

[0021] S1: stacking the high-temperature resistant fiber flexible surface layer, the high-temperature resistant metal foil radiation shielding layer, the fluffy high-temperature fiber cotton heat insulation deformation reserve functional layer, and the low-permeability elastic deformation material layer in sequence from top to bottom;

[0022] S2: Use high-temperature fiber suture thread to sew 2-3 layers of the high-temperature resistant fiber flexible surface layer, the high-temperature resistant metal foil radiation shielding layer, the fluffy high-temperature fiber cotton thermal insulation deformation reserve functional layer and the low-permeability elastic deformation material layer multiple times into an overall structure;

[0023] S3: The entire structure is compressed to the reserve deformation position, and then the entire structure is sutured using the characteristic temperature failure suture line.

[0024] Furthermore, fluffy high-temperature fiber cotton packaging material is used to encapsulate the fluffy high-temperature fiber cotton thermal insulation deformation storage functional layer, high-temperature fiber suture thread is used to sew the high-temperature resistant fiber flexible surface layer, the high-temperature resistant metal foil radiation shielding layer and the fluffy high-temperature fiber cotton packaging material, and high-temperature fiber suture thread is used to sew the fluffy high-temperature fiber cotton packaging material and the low-permeability elastic deformation material layer.

[0025] After the whole is sewn together, it is marked and cut according to the required size and shape to obtain a thickness-adaptive flexible thermal protection system.

[0026] The present invention provides a thickness-adaptive flexible thermal protection system and its fabrication method. This system pre-compresses fluffy, high-temperature fiber cotton with high-temperature resilience to create a deformation reserve, which is then constrained using a characteristic temperature-failure suture with a characteristic temperature-failure function. In actual use, under the influence of the aircraft's aerodynamic heating environment, the characteristic temperature-failure suture automatically releases the reserved deformation upon reaching a preset temperature, thereby suppressing and compensating for deformation of the flexible thermal protection system caused by aerodynamic heating, thereby improving the high-temperature adaptability of the flexible thermal protection system for high-speed aerospace aircraft.

[0027] Furthermore, the modulus of the fluffy, high-temperature fiber cotton, after deformation release, increases further after exposure to high temperatures. The flexible thermal protection system's ability to resist deformation and mitigate aerodynamic thermal loads synergizes, significantly reducing the ablation retreat rate and improving the structure's ability to withstand high temperatures and high dynamic pressures. This thickness-adaptive flexible thermal protection system can be applied to high-speed aerospace vehicle hot-end components requiring thermal protection, deformation, or storage, such as large windward surfaces and wing surfaces. It is suitable for thermal protection of flexible components in high-speed aerospace vehicles. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] In order to more clearly illustrate the technical solutions in the specific embodiments or prior art of the present application, the drawings needed to be used in the specific embodiments or prior art description will be briefly introduced as follows. Obviously, the drawings described below are some embodiments of the present application, and for those skilled in the art, other drawings can also be obtained without creative labor on the basis of these drawings.

[0029] Figure 1 Structural schematic diagram of a thickness-adaptive flexible thermal protection system in a deformed storage state according to an embodiment.

[0030] Figure 2 Structural schematic diagram of a thickness-adaptive flexible thermal protection system in a deformed release state according to an embodiment.

[0031] Legend of reference signs:

[0032] 1: high-temperature-resistant fiber flexible surface layer; 2: high-temperature-resistant metal foil radiation shielding layer; 3: fluffy high-temperature-resistant fiber cotton heat insulation and deformed storage function layer; 4: fluffy high-temperature-resistant fiber cotton packaging sleeve; 5: low-permeability elastic deformed material layer; 6: first high-temperature-resistant fiber stitching line; 7: second high-temperature-resistant fiber stitching line; 8: characteristic temperature failure stitching line. DETAILED DESCRIPTION

[0033] It should be noted that the following detailed description is exemplary and is intended to provide further explanation of the present application. Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs.

[0034] It should be noted that the terms used herein are only intended to describe specific embodiments, and are not intended to limit the exemplary embodiments according to the present application. As used herein, the singular form also includes the plural form unless the context clearly indicates otherwise, and furthermore, it should be understood that when the terms "comprise" and / or "include" are used in the specification, there is a feature, step, operation, device, component and / or combination thereof.

[0035] The technical solutions of the present application will be described below in conjunction with the embodiments. Obviously, the described embodiments are some embodiments of the present application, and not all embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor are within the scope of protection of the present application.

[0036] Embodiment 1

[0037] In conjunction with Figure 1As shown, the thickness adaptive flexible thermal protection system of this embodiment includes a high-temperature resistant fiber flexible surface layer 1, a high-temperature resistant metal foil radiation shielding layer 2, a fluffy high-temperature fiber cotton thermal insulation deformation reserve functional layer 3 and a low-permeability elastic deformation material layer 5 which are stacked in sequence from top to bottom. The adjacent 2-3 layers of the high-temperature resistant fiber flexible surface layer 1, the high-temperature resistant metal foil radiation shielding layer 2, the fluffy high-temperature fiber cotton thermal insulation deformation reserve functional layer 3 and the low-permeability elastic deformation material layer 5 are stitched into an integral structure multiple times through high-temperature fiber stitching lines. The overall structure is compressed to the reserve deformation position and stitched as a whole through characteristic temperature failure stitching lines 8. The characteristic temperature failure stitching lines 8 break at a preset temperature to release the deformation reserve of the overall structure.

[0038] Specifically, the high-temperature resistant fiber flexible surface layer 1 is composed of 0.14mm thick plain woven silicon carbide fiber woven cloth, 0.12mm thick plain carbon fiber woven cloth, and 0.16mm thick plain woven alumina fiber woven cloth, which are stacked in sequence from top to bottom. The number of layers of 0.14mm thick plain woven silicon carbide fiber woven cloth is 3 layers, the number of layers of 0.12mm thick plain carbon fiber woven cloth is 2 layers, and the number of layers of 0.16mm thick plain woven alumina fiber woven cloth is 2 layers.

[0039] The high temperature resistant metal foil radiation shielding layer 2 is a 0.01 mm stainless steel foil, and the number of layers used is one.

[0040] The fluffy high-temperature fiber cotton heat-insulating deformation reserve functional layer 3 is a single-layer 0.5mm-thick quartz mesh reinforced silica aerogel composite material, and the number of layers used is 2.

[0041] The fluffy high-temperature fiber cotton heat insulation deformation storage functional layer 3 is encapsulated by the fluffy high-temperature fiber cotton encapsulation sleeve 4. The material of the fluffy high-temperature fiber cotton encapsulation sleeve 4 is a single-layer silicon carbide fiber cotton with a thickness of 0.20 mm, which has high temperature resistance and deformation rebound performance, and the number of layers used is 1.

[0042] The low-permeability elastic deformation material layer 5 is a quartz fiber reinforced silicone rubber composite material with a single layer thickness of 0.5 mm, and the number of layers used is one.

[0043] From top to bottom, three layers of 0.14 mm thick plain woven silicon carbide fiber woven cloth, two layers of 0.12 mm thick plain woven carbon fiber woven cloth, two layers of 0.16 mm thick plain woven alumina fiber woven cloth, one layer of 0.01 mm stainless steel foil, two layers of 0.5 mm quartz mesh reinforced silica aerogel composite material encapsulated by a fluffy high-temperature fiber cotton encapsulation sleeve 4, and one layer of 0.5 mm quartz fiber reinforced silicone rubber composite material are stacked in sequence.

[0044] The high-temperature fiber suture line uses 1K carbon fiber line, 3 layers of 0.14mm thick plain woven silicon carbide fiber woven cloth, 2 layers of 0.12mm thick plain woven carbon fiber woven cloth, 2 layers of 0.16mm thick plain woven alumina fiber woven cloth, 1 layer of 0.01mm stainless steel foil, fluffy high-temperature fiber cotton packaging sleeve 4, and 2 layers of 0.5mm quartz mesh reinforced silica aerogel composite material. The upper part is sutured by the first high-temperature fiber suture line 6 (i.e., 1K carbon fiber line), and the suture density is 2-3 stitches / square centimeter.

[0045] The lower part of two layers of 0.5 mm quartz mesh reinforced silica aerogel composite material, the fluffy high-temperature fiber cotton packaging sleeve 4, and one layer of 0.5 mm quartz fiber reinforced silicone rubber composite material are sewn together through a second high-temperature fiber suture line 7 (1K carbon fiber line) with a suture density of 2-3 stitches / square centimeter to form an overall structure.

[0046] The characteristic temperature failure suture line 8 uses a metal nickel wire with a nominal diameter of 0.2 mm. After the overall structure is compressed to the reserve deformation position, the metal nickel wire with a nominal diameter of 0.2 mm is used for overall suture. After the overall suture, it can be marked and cut according to the required size and shape to obtain a thickness-adaptive flexible thermal protection system.

[0047] The thickness adaptive flexible thermal protection system of this embodiment forms deformation reserve by pre-compressing fluffy high-temperature fiber cotton with high-temperature rebound performance, and uses characteristic temperature failure suture line 8 with characteristic temperature failure function to constrain deformation reserve. Figure 2 As shown, during actual use, under the influence of the aircraft's aerodynamic heating environment, the metal nickel wire of the characteristic temperature failure suture line 8 automatically releases its reserve deformation after reaching the melting point of about 1450°C, thereby suppressing and compensating for the deformation of the flexible thermal protection system caused by the aerodynamic thermal effect, and improving the high-temperature adaptability of the flexible thermal protection system of aerospace high-speed aircraft; in addition, the modulus of the fluffy high-temperature fiber cotton after deformation release is further increased after experiencing high temperature, and the flexible thermal protection system's ability to resist deformation and the aerodynamic thermal load reduction are coordinated, so that the flexible thermal protection system can significantly reduce the ablation retreat rate and improve the structure's high-temperature resistance and high dynamic pressure adaptability. The above-mentioned thickness-adaptive flexible thermal protection system can be applied to aerospace high-speed aircraft hot-end components with thermal protection, deformation or storage requirements, such as large-area windward surfaces and wing surfaces of aircraft, and is suitable for thermal protection of flexible components of aerospace high-speed aircraft.

[0048] Example 2

[0049] Combine Figure 1 、 Figure 2 As shown, this embodiment provides a method for preparing a thickness-adaptive flexible thermal protection system, and the steps are as follows:

[0050] S1: stacking the high-temperature resistant fiber flexible surface layer 1, the high-temperature resistant metal foil radiation shielding layer 2, the fluffy high-temperature fiber cotton heat insulation deformation reserve functional layer 3, and the low-permeability elastic deformation material layer 5 in order from top to bottom;

[0051] S2: Using high-temperature fiber suture thread, sew two or three adjacent layers of the high-temperature resistant fiber flexible surface layer 1, the high-temperature resistant metal foil radiation shielding layer 2, the fluffy high-temperature fiber cotton heat insulation deformation storage functional layer 3, and the low-permeability elastic deformation material layer 5 multiple times into an integral structure;

[0052] S3: After compressing the entire structure to the reserve deformation position, the entire structure is sutured using the characteristic temperature failure suture line 8.

[0053] Specifically, the fluffy high-temperature fiber cotton heat insulation deformation storage functional layer 3 is first encapsulated by the fluffy high-temperature fiber cotton encapsulation sleeve 4. The material of the fluffy high-temperature fiber cotton encapsulation sleeve 4 is a single layer of silicon carbide fiber cotton with a thickness of 0.20 mm, and the number of layers used is 1.

[0054] Next, three layers of 0.14 mm thick plain woven silicon carbide fiber woven cloth, two layers of 0.12 mm thick plain woven carbon fiber woven cloth, two layers of 0.16 mm thick plain woven alumina fiber woven cloth, one layer of 0.01 mm stainless steel foil, two layers of 0.5 mm quartz mesh reinforced silica aerogel composite material encapsulated by a fluffy high-temperature fiber cotton encapsulation sleeve 4, and one layer of 0.5 mm quartz fiber reinforced silicone rubber composite material were stacked in sequence from top to bottom.

[0055] Subsequently, 1K carbon fiber wire (i.e., high-temperature fiber suture wire) was used to sew three layers of 0.14 mm thick plain woven silicon carbide fiber woven cloth, two layers of 0.12 mm thick plain woven carbon fiber woven cloth, two layers of 0.16 mm thick plain woven alumina fiber woven cloth, one layer of 0.01 mm stainless steel foil, a fluffy high-temperature fiber cotton packaging sleeve 4, and two layers of 0.5 mm quartz mesh reinforced silica aerogel composite material at an upper portion thereof, with a suture density of 2-3 stitches / cm2.

[0056] Then, 1K carbon fiber thread (i.e., high-temperature fiber suture thread) is used to sew the lower part of the two layers of 0.5mm quartz mesh reinforced silica aerogel composite material, the fluffy high-temperature fiber cotton packaging sleeve 4, and the one layer of 0.5mm quartz fiber reinforced silicone rubber composite material with a suture density of 2-3 stitches / square centimeter to form an overall structure.

[0057] Finally, the overall structure is compressed to the reserve deformation position, and then the overall structure is sutured using a quartz fiber filament with a twist of 180 and a nominal diameter of 0.2 mm (i.e., characteristic temperature failure suture line 8). After the overall suture, it is marked and cut according to the required size and shape to obtain a flexible thermal protection system.

[0058] The flexible thermal protection system prepared in this embodiment, when subjected to an aerodynamic heating environment, will break and fail and release the deformation reserve when the characteristic temperature failure suture line 8 reaches a surface temperature of about 1650°C, thereby compensating for the deformation of the flexible thermal protection system caused by the aerodynamic environment of the aircraft. It can serve as a deformation reserve self-deployed flexible thermal protection system for high-speed aerospace aircraft to resist the aerodynamic heating environment.

[0059] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the above embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the above embodiments, or replace some or all of the technical features therein with equivalents. However, these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A thickness-adaptive flexible thermal protection system, characterized in that: It includes a high-temperature resistant fiber flexible surface layer, a high-temperature resistant metal foil radiation shielding layer, a fluffy high-temperature fiber cotton thermal insulation deformation reserve functional layer and a low-permeability elastic deformation material layer stacked in sequence from top to bottom. The high-temperature resistant fiber flexible surface layer, the high-temperature resistant metal foil radiation shielding layer, the fluffy high-temperature fiber cotton thermal insulation deformation reserve functional layer and the low-permeability elastic deformation material layer are sutured multiple times by high-temperature fiber sutures to form an overall structure. The overall structure is compressed to the reserve deformation position and sutured as a whole by characteristic temperature failure sutures. The characteristic temperature failure sutures break at a preset temperature to release the deformation reserve of the overall structure. The fluffy high-temperature fiber cotton thermal insulation deformation reserve functional layer is encapsulated by a fluffy high-temperature fiber cotton packaging sleeve. The high-temperature resistant fiber flexible surface layer, the high-temperature resistant metal foil radiation shielding layer and the fluffy high-temperature fiber cotton packaging sleeve are sutured by high-temperature fiber sutures The fluffy high-temperature fiber cotton packaging sleeve and the low-permeability elastic deformation material layer are sewn together by high-temperature fiber suture lines. The material of the fluffy high-temperature fiber cotton thermal insulation deformation storage functional layer is selected from flexible fiber reinforced aerogel composite materials. The material of the fluffy high-temperature fiber cotton packaging sleeve is selected from at least one of silicon carbide fiber cotton, carbon fiber cotton, alumina fiber cotton, and silica fiber cotton. The material of the low-permeability elastic deformation material layer is selected from at least one of silicon carbide fiber reinforced silicone rubber material, carbon fiber reinforced silicone rubber material, alumina fiber reinforced silicone rubber material, silica fiber reinforced silicone rubber material, aramid fiber reinforced silicone rubber material, silicon carbide fiber reinforced polyimide material, carbon fiber reinforced polyimide material, alumina fiber reinforced polyimide material, silica fiber reinforced polyimide material, and aramid fiber reinforced polyimide material.

2. The thickness adaptive flexible thermal protection system according to claim 1, characterized in that: The material of the high-temperature resistant fiber flexible surface layer is selected from at least one of silicon carbide fiber woven cloth, carbon fiber woven cloth, alumina fiber woven cloth, and silica fiber cloth; the weaving method of the high-temperature resistant fiber flexible surface layer is plain, twill or satin, and the single layer thickness is 0.1-0.3mm.

3. The thickness adaptive flexible thermal protection system according to claim 1, characterized in that: The material of the high-temperature resistant metal foil radiation shielding layer is selected from at least one of nickel foil, stainless steel foil and aluminum foil; the single layer thickness of the material of the high-temperature resistant metal foil radiation shielding layer is 0.01-0.03 mm.

4. The thickness adaptive flexible thermal protection system according to claim 1, characterized in that: The material of the fluffy high-temperature fiber cotton thermal insulation deformation storage functional layer is selected from at least one of silicon carbide fiber reinforced silica aerogel material, carbon fiber reinforced silica aerogel material, alumina fiber reinforced silica aerogel material, silica fiber reinforced silica aerogel material, silicon carbide fiber reinforced polyimide aerogel material, carbon fiber reinforced polyimide aerogel material, alumina fiber reinforced polyimide aerogel material, and silica fiber reinforced polyimide aerogel material; the single layer thickness of the material of the fluffy high-temperature fiber cotton thermal insulation deformation storage functional layer is 0.2-0.5mm.

5. The thickness adaptive flexible thermal protection system according to claim 1, characterized in that: The single layer thickness of the low-permeability elastic deformation material layer is 0.1-0.5 mm.

6. The thickness adaptive flexible thermal protection system according to claim 1, characterized in that: The high-temperature fiber suture thread is selected from at least one of silicon carbide fiber thread, carbon fiber thread, alumina fiber thread, silica fiber thread, steel wire thread and aluminum wire thread.

7. The thickness adaptive flexible thermal protection system according to claim 1, characterized in that: The characteristic temperature failure suture is selected from at least one of tungsten wire, tantalum wire, molybdenum wire, niobium wire, zirconium wire, hafnium wire, nickel wire, iron wire, stainless steel wire, silver wire, copper wire, aluminum wire, carbon fiber wire, silicon carbide fiber wire, quartz fiber wire, glass fiber wire, aramid fiber wire and nylon fiber wire.

8. The method for preparing the thickness-adaptive flexible thermal protection system according to any one of claims 1 to 7, characterized in that: The steps include: S1: stacking the high-temperature resistant fiber flexible surface layer, the high-temperature resistant metal foil radiation shielding layer, the fluffy high-temperature fiber cotton heat insulation deformation reserve functional layer, and the low-permeability elastic deformation material layer in sequence from top to bottom; S2: Use high-temperature fiber suture thread to sew 2-3 adjacent layers of the high-temperature resistant fiber flexible surface layer, the high-temperature resistant metal foil radiation shielding layer, the fluffy high-temperature fiber cotton thermal insulation deformation reserve functional layer and the low-permeability elastic deformation material layer multiple times into an integral structure; S3: After compressing the entire structure to the reserve deformation position, the entire structure is sutured using the characteristic temperature failure suture line; Among them, a fluffy high-temperature fiber cotton packaging sleeve is used to encapsulate the fluffy high-temperature fiber cotton thermal insulation deformation storage functional layer, a high-temperature fiber suture thread is used to sew the high-temperature resistant fiber flexible surface layer, the high-temperature resistant metal foil radiation shielding layer and the fluffy high-temperature fiber cotton packaging sleeve, and a high-temperature fiber suture thread is used to sew the fluffy high-temperature fiber cotton packaging sleeve and the low-permeability elastic deformation material layer.

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