Active flexible heat-proof material as well as preparation method and application thereof

Abstract

The invention discloses an active flexible heat-proof material as well as a preparation method and application thereof. The active flexible heat-proof material comprises an active flexible heat-proof material heat-insulating layer, a metal reflecting layer and a fiber fabric layer which are sequentially stacked, the active flexible heat-proof material heat insulation layer is prepared by mixing methyl hydrogen liquid ceramic resin, methyltrimethoxysilane, a catalyst, a diluent, a graphite substrate, ceramic chopped fibers and silicon dioxide hollow microspheres and then calcining. The material is low in overall density and excellent in heat insulation performance, the material structure is stable in an extreme high-temperature environment, the heat insulation performance is not attenuated, and the safety of internal equipment is ensured. The method is suitable for a spacecraft surface sensitive to weight or a high-speed aircraft thermal protection system, the structural load can be reduced, and the energy efficiency can be improved.

Description

Technical Field

[0001] This invention belongs to the field of flexible heat-resistant materials, and relates to an active flexible heat-resistant material, its preparation method and application. Background Technology

[0002] With the rapid development of future aviation weaponry technology, aircraft are facing the need for high Mach numbers (3~10). As the core propulsion technology for future hypersonic vehicles, the combined aerospace engine has an increased thrust-to-weight ratio (15~20) due to the increase in flight Mach number, resulting in a sharp increase in turbine inlet temperature (2100~2200K).

[0003] The high-temperature region of aero-engines has gradually expanded from the nozzle end to the leading-edge guide vanes, and the installation position of some actuators has been moved from the engine casing to the engine duct. The high-temperature environment of the engine duct will directly affect the actuators. Therefore, key actuating components such as fan guide vanes / compressors, low-pressure turbines, throats, and vectoring nozzles all face high-temperature environments. Among them, the actuation system installed after the afterburner has an operating environment temperature that has reached 350°C for extended periods and a medium temperature of 160°C, thus placing higher demands on the safe operation of aero-engine actuation systems in ultra-high temperature environments. However, the lack of effective high-temperature thermal protection technology is a common and bottleneck problem in the upgrading and replacement of aero-engine actuation systems.

[0004] To address the high-temperature thermal protection of hypersonic aircraft / aero-engine actuation systems, there is an urgent need to develop novel active flexible thermal protection materials and structural designs that offer high efficiency, long-term temperature resistance, and high reliability. This will solve the problem of the difficulty in improving the temperature resistance level of hypersonic aircraft / aero-engine actuation systems, enhance the key technologies of lightweight, small size, high temperature resistance, and strong thermal insulation integration, meet the harsh environmental requirements of hypersonic aircraft / aero-engines, and achieve a thermal conductivity of ≤0.04W / (m·K) after thermal insulation at an environment of 350℃ for the actuation system. Summary of the Invention

[0005] The purpose of this invention is to provide an active flexible heat-resistant material, its preparation method, and its application, thereby solving the problem of difficulty in improving the temperature resistance level of hypersonic aircraft / aero-engine actuation systems in the prior art.

[0006] To achieve the above objectives, the present invention employs the following technical solution: An active flexible heat protection material includes an active flexible heat protection material insulation layer, a metal reflective layer and a fiber fabric layer stacked sequentially. The active flexible heat insulation material insulation layer is prepared by calcining a mixture of methylhydrogen liquid ceramic resin, methyltrimethoxysilane, catalyst, diluent, graphite substrate, chopped ceramic fibers and hollow silica microspheres.

[0007] Furthermore, the metal reflective layer includes at least one single-sided aluminized polyimide film, at least one polyimide tape, and at least one aluminum foil tape; The fiber fabric layer includes at least one layer of alkali-free fiberglass cloth, at least one layer of ceramic fiber cloth, and at least one layer of quartz fiber cloth.

[0008] Furthermore, in the active flexible heat insulation material insulation layer, the catalyst is a gel catalyst, preferably dilute nitric acid; The diluent is deionized water.

[0009] Furthermore, the active flexible heat-resistant material has a thermal conductivity of 0.032~0.04 W / (m·K) and a temperature resistance of 800~1300℃ in an aerobic environment.

[0010] A method for preparing the active flexible heat-resistant material includes: Methylhydrogen liquid ceramic resin, methyltrimethoxysilane, catalyst, diluent and graphite substrate are mixed evenly and dried to obtain component A; Component A, chopped ceramic fibers and hollow silica microspheres were mixed, spread evenly and calcined to obtain an active flexible heat insulation material layer. A single-sided aluminized polyimide film, polyimide tape, and aluminum foil tape are sequentially laminated to obtain a metal reflective layer; Each layer of alkali-free fiberglass cloth, ceramic fiber cloth, and quartz fiber cloth is coated with silicone rubber, and then layered and laminated in sequence. The fiber fabric layer is obtained by vacuum hot pressing and sealing. The active flexible heat protection material is obtained by sequentially layering and bonding the heat insulation layer, the metal reflective layer, and the fiber fabric layer.

[0011] Furthermore, by mass, component A includes 60 parts of methylhydrogen liquid ceramic resin, 10-20 parts of methyltrimethoxysilane, 20-35 parts of catalyst, 10-25 parts of diluent, and 5-10 parts of graphite substrate.

[0012] Furthermore, the mass ratio of component A, chopped ceramic fibers, and hollow silica microspheres is 35~50:10~25:6~8.

[0013] Furthermore, the drying temperature of component A is 60~80℃, and the drying time is 20~24h.

[0014] Furthermore, the calcination atmosphere is nitrogen, the calcination temperature is 1000~1200℃, and the calcination time is 24~26 h.

[0015] The application of the active flexible heat-resistant material on the surface of actuating components of supersonic aircraft / aero-engines involves preparing the active flexible heat-resistant material into heat-insulating modules, attaching the heat-insulating modules to the protruding and / or recessed parts of the actuating component surface in sections, and connecting the heat-insulating modules by stitching.

[0016] Compared with the prior art, the present invention has the following beneficial effects: This invention provides an active flexible heat-resistant material, comprising an active flexible heat-resistant material insulation layer, a metal reflective layer, and a fiber fabric layer. The metal reflective layer reflects heat radiation through high reflectivity, reducing heat absorption. Working synergistically with the insulation layer, it forms a dual-effect protection mechanism of "reflection + barrier," significantly reducing the material's surface temperature. The fiber fabric layer, acting as a flexible skeleton, endows the material with bendable and foldable properties, allowing it to conform to complex curved surfaces and resist cracking under vibration or mechanical impact, thus extending its service life. The active flexible heat-resistant material insulation layer is prepared by calcining a mixture of methylhydrogen liquid ceramic resin, methyltrimethoxysilane, a catalyst, a diluent, a graphite substrate, chopped ceramic fibers, and hollow silica microspheres. Hollow silica microspheres serve as the core thermal insulation filler; their internal vacuum or gas structure significantly reduces thermal conductivity, forming a highly efficient thermal barrier. Methylhydrogen liquid ceramic resin and methyltrimethoxysilane act as the matrix material, forming a lightweight ceramic network through calcination, further reducing heat transfer. Short-cut ceramic fibers dispersed within the matrix form a three-dimensional reinforcing network, enhancing the material's tensile and tear resistance. A graphite substrate improves the material's high-temperature oxidation resistance and prevents thermochemical degradation. The mixed calcination process ensures uniform dispersion of all components, forming a dense microstructure, resulting in high material performance consistency and scalable production to meet industrial application requirements. This invention's material exhibits low overall density and excellent thermal insulation performance. Even under extreme high-temperature environments, the material structure remains stable, and its thermal insulation performance does not diminish, ensuring the safety of internal equipment. It is suitable for thermal protection systems on weight-sensitive spacecraft surfaces or high-speed aircraft, reducing structural load and improving energy efficiency. Tests show that the active flexible heat-resistant material prepared by this invention has a thermal conductivity of 0.032~0.04 W / (m·K) and a temperature resistance of 800~1300℃ in an aerobic environment, exhibiting excellent heat insulation and temperature resistance performance.

[0017] This invention also provides a method for preparing an active flexible heat-insulating material. The method involves uniformly mixing methylhydrogen liquid ceramic resin, methyltrimethoxysilane, a catalyst, a diluent, and a graphite substrate, followed by drying to obtain component A. Component A, chopped ceramic fibers, and hollow silica microspheres are then mixed, uniformly spread, and calcined to obtain the active flexible heat-insulating material insulation layer. Through a two-stage mixing process, component A is prepared first, followed by the introduction of chopped ceramic fibers and hollow microspheres, preventing fiber agglomeration or microsphere breakage and ensuring uniform dispersion of the components. The uniform spreading of the raw materials followed by calcination ensures uniform heat transfer, avoids structural defects caused by localized overheating, and improves the density and porosity controllability of the insulation layer. A single-sided aluminized polyimide film, polyimide tape, and aluminum foil tape are sequentially laminated to obtain a metal reflective layer, forming a "metal-polymer-metal" composite structure. This ensures high reflectivity while the polymer layer buffers thermal stress, preventing cracking of the metal layer. Each layer of alkali-free fiberglass cloth, ceramic fiber cloth, and quartz fiber cloth is coated with silicone rubber, and then sequentially laminated and sealed by vacuum hot pressing to obtain a fiber fabric layer, forming a gradient reinforcement structure that balances flexibility and high-temperature resistance. The active flexible heat-insulating material insulation layer, the metal reflective layer, and the fiber fabric layer are then sequentially laminated to obtain the active flexible heat-insulating material. This invention features strong process compatibility, clear process steps, independent control of the performance of each layer, and high production efficiency. It avoids the problems of component migration or structural inhomogeneity in traditional one-piece molding processes, improving material consistency. Simultaneously, it possesses a triple protection mechanism of "reflection + barrier + flexibility," significantly improving heat insulation efficiency compared to traditional materials, while also being flexible and bendable to meet the requirements of curved surface lamination.

[0018] This invention also provides an application of an active flexible heat-insulating material. This invention combines the active flexible heat-insulating material with the actuating components to obtain a composite integrated structure with a high degree of fit. After a real-world environmental test at 350°C, the heat insulation performance is tested, and the temperature after insulation is less than 230°C, which meets the technical requirements. Attached Figure Description

[0019] To more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of the present invention and should not be regarded as a limitation on the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0020] Figure 1 This is a schematic diagram of the modular design and stacked structure of the curved surface position according to the present invention.

[0021] Figure 2 The active flexible heat-resistant material prepared in Example 1 of the present invention is shown in the diagrams of its application to the actuating components and its testing in a real environment.

[0022] Figure 3 The figure shows the test results of the active flexible heat-resistant material prepared in Example 1 of the present invention under a real environment of 350°C with heat insulation coating on the actuating parts. Detailed Implementation

[0023] To enable those skilled in the art to understand the features and effects of the present invention, the terms and expressions used in the specification and claims are explained and defined in general below. Unless otherwise specified, all technical and scientific terms used herein have the ordinary meaning understood by those skilled in the art regarding the present invention, and in case of conflict, the definitions in this specification shall prevail.

[0024] The theories or mechanisms described and disclosed herein, whether right or wrong, should not in any way limit the scope of the invention, that is, the contents of the invention can be implemented without being limited by any particular theory or mechanism.

[0025] In this document, all features defined by numerical ranges or percentage ranges, such as numerical values, quantities, contents, and concentrations, are for the sake of brevity and convenience only. Accordingly, descriptions of numerical ranges or percentage ranges should be considered as covering and specifically disclosing all possible sub-ranges and individual numerical values ​​(including integers and fractions) within those ranges.

[0026] In this article, unless otherwise specified, “contains,” “includes,” “containing,” “has,” or similar terms cover the meanings of “composed of” and “mainly composed of,” for example, “A contains a” covers the meanings of “A contains a and others” and “A contains only a.”

[0027] For the sake of brevity, not all possible combinations of the technical features in each implementation scheme or embodiment are described herein. Therefore, as long as there is no contradiction in the combination of these technical features, the technical features in each implementation scheme or embodiment can be combined arbitrarily, and all possible combinations should be considered within the scope of this specification.

[0028] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the present invention will be clearly and completely described below in conjunction with the embodiments of the present invention. The present invention will be further illustrated with specific embodiments. It should be understood that these embodiments are only for illustrating the present invention and not for limiting the scope of the present invention. The described embodiments are some embodiments of the present invention, not all embodiments. The detailed description of the embodiments of the present invention is not intended to limit the scope of the claimed invention, but merely represents selected embodiments of the invention. Furthermore, it should be understood that after reading the teachings of this invention, those skilled in the art can make various modifications or alterations to the present invention, and these equivalent forms also fall within the scope defined by the appended claims. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without inventive effort are within the scope of protection of the present invention.

[0029] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., refer to specific features, structures, materials, or characteristics described in connection with that embodiment or example, which are included in at least one embodiment or example of the embodiments of this application. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0030] To enable those skilled in the art to more clearly understand the technical solutions described in this invention, the following embodiments are provided for illustration. It should be noted that the following embodiments do not constitute a limitation on the scope of protection claimed by this invention. Unless otherwise specified, the raw materials, reagents, or apparatus used in the following embodiments can be obtained from conventional commercial sources or by existing known methods. Conventional instruments and equipment in the art are used in the following embodiments. Experimental methods in the following embodiments that do not specify specific conditions are generally performed under conventional conditions or according to the manufacturer's recommendations. Various raw materials used in the following embodiments are all conventional commercially available products with specifications that are conventional in the art, unless otherwise stated. In the specification of this invention and the following embodiments, unless otherwise specified, "%" represents weight percentage, "parts" represents parts by weight, and "ratio" represents weight ratio.

[0031] The present invention will now be described in further detail with reference to the accompanying drawings: Based on the high-temperature thermal protection requirements of hypersonic aircraft / aircraft engine actuation systems, this invention provides an active flexible heat protection material, which and its composite structure possess high-temperature resistance and strong thermal insulation properties.

[0032] The active flexible heat protection material of the present invention comprises an active flexible heat protection material insulation layer, a metal reflective layer and a fiber fabric layer stacked sequentially.

[0033] Preferably, the metal reflective layer includes at least one single-sided aluminized polyimide film, at least one polyimide tape, and at least one aluminum foil tape.

[0034] Preferably, the fiber fabric layer includes at least one layer of alkali-free glass fiber cloth, at least one layer of ceramic fiber cloth, and at least one layer of quartz fiber cloth.

[0035] Preferably, the catalyst in the active flexible heat insulation material insulation layer is a gel catalyst; more preferably, it is dilute nitric acid.

[0036] Preferably, the diluent is deionized water.

[0037] This invention also provides a method for preparing an active flexible heat-resistant material, specifically including the following steps: Methylhydrogen liquid ceramic resin, methyltrimethoxysilane, catalyst, diluent and graphite substrate were mixed and stirred evenly in a certain proportion, and dried at 60~80℃ for 20~24 h to obtain component A; Component A, chopped ceramic fibers and hollow silica microspheres are mixed, evenly spread on a ceramic firing rack, and placed in a high-temperature box furnace for calcination in a nitrogen atmosphere. After calcination, the ceramic firing rack is removed and the product is taken out, thus obtaining the active flexible heat insulation material insulation layer. A single-sided aluminized polyimide film, polyimide tape, and aluminum foil tape are sequentially laminated to obtain a metal reflective layer; Each layer of alkali-free fiberglass cloth, ceramic fiber cloth, and quartz fiber cloth is coated with silicone rubber, and then layered and laminated in sequence. The fiber fabric layer is obtained by vacuum hot pressing and sealing. The active flexible heat protection material is obtained by sequentially layering and bonding the heat insulation layer, the metal reflective layer, and the fiber fabric layer.

[0038] Preferably, by mass, component A comprises 60 parts of methylhydrogen liquid ceramic resin, 10-20 parts of methyltrimethoxysilane, 20-35 parts of catalyst, 10-25 parts of diluent and 5-10 parts of graphite substrate.

[0039] Preferably, the mass ratio of component A, chopped ceramic fibers, and hollow silica microspheres is 35~50:10~25:6~8.

[0040] Preferably, the calcination temperature is 1000~1200℃ and the calcination time is 24~26 h.

[0041] Tests on the thermal conductivity and temperature resistance under aerobic conditions of the active flexible heat-resistant material prepared by this invention revealed that the thermal conductivity of the insulation layer of the active flexible heat-resistant material prepared by this invention is 0.032~0.04 W / (m·K), and the temperature resistance under aerobic conditions is 800~1300℃, demonstrating excellent heat insulation and temperature resistance performance.

[0042] This invention also provides an application of an active flexible thermal protection material on the surface of actuating components of supersonic aircraft / aero-engines. Since the actuation systems of supersonic aircraft / aero-engines are primarily irregularly shaped components with numerous protrusions and depressions on their surfaces, a composite structure design is required, taking into account the component's external dimensions and structural characteristics. A modular design is adopted for curved areas such as protrusions and depressions on the surface of the actuating components. The main implementation steps are as follows: Active flexible heat-resistant materials are used to prepare heat-insulating modules; The heat insulation module is applied in sections to the raised and / or recessed parts of the moving part surface; The joints of the insulation modules are connected using a stitching design, and the components are combined using mechanical methods or high-temperature adhesive bonding. A structural diagram is shown below. Figure 1 As shown.

[0043] The technical solution of the present invention will be further described in detail below through specific embodiments: Example 1: 60 parts of methylhydrogen liquid ceramic resin, 10 parts of methyltrimethoxysilane, 25 parts of dilute nitric acid, 18 parts of deionized water and 7 parts of graphite substrate were mixed and stirred evenly in a certain proportion, and dried at 60°C for 24 h to obtain component A. Mix 35g of component A, 18g of chopped ceramic fibers and 7g of hollow silica microspheres, spread them evenly on a ceramic firing rack, and place them in a high-temperature box furnace for calcination in a nitrogen atmosphere. The calcination temperature is 1000℃ and the calcination time is 26 h. After calcination, remove the ceramic firing rack and take out the product to obtain the active flexible heat insulation material insulation layer. Two layers of single-sided aluminized polyimide film, one layer of polyimide tape, and five layers of aluminum foil tape are sequentially laminated to obtain a metal reflective layer. Two layers of alkali-free fiberglass cloth, three layers of ceramic fiber cloth, and four layers of quartz fiber cloth are coated with silicone rubber, then laminated in sequence and sealed by vacuum hot pressing to obtain the fiber fabric layer. The active flexible heat protection material is obtained by sequentially layering and bonding the heat insulation layer, the metal reflective layer, and the fiber fabric layer.

[0044] Example 2: 60 parts of methylhydrogen liquid ceramic resin, 16 parts of methyltrimethoxysilane, 30 parts of dilute nitric acid, 22 parts of deionized water and 5 parts of graphite substrate were mixed and stirred evenly in a certain proportion, and dried at 65°C for 21 h to obtain component A. Mix 48g of component A, 21g of chopped ceramic fibers and 6g of hollow silica microspheres, spread them evenly on a ceramic firing rack, and place them in a high-temperature box furnace for calcination in a nitrogen atmosphere. The calcination temperature is 1100℃ and the calcination time is 24 h. After calcination, remove the ceramic firing rack and take out the product to obtain the active flexible heat insulation material insulation layer. A metal reflective layer is prepared by sequentially laminating three layers of single-sided aluminized polyimide film, four layers of polyimide tape, and one layer of aluminum foil tape. Two layers of alkali-free fiberglass cloth, two layers of ceramic fiber cloth, and three layers of quartz fiber cloth are coated with silicone rubber, then laminated in sequence and sealed by vacuum hot pressing to obtain a fiber fabric layer. The active flexible heat protection material is obtained by sequentially layering and bonding the heat insulation layer, the metal reflective layer, and the fiber fabric layer.

[0045] Example 3: 60 parts of methylhydrogen liquid ceramic resin, 20 parts of methyltrimethoxysilane, 35 parts of dilute nitric acid, 22 parts of deionized water and 10 parts of graphite substrate were mixed and stirred evenly in a certain proportion, and dried at 80°C for 22 h to obtain component A. Mix 50g of component A, 16g of chopped ceramic fibers and 8g of hollow silica microspheres, spread them evenly on a ceramic firing rack, and place them in a high-temperature box furnace for calcination in a nitrogen atmosphere. The calcination temperature is 1200℃ and the calcination time is 25 h. After calcination, remove the ceramic firing rack and take out the product to obtain the active flexible heat insulation material insulation layer. Four layers of single-sided aluminized polyimide film, three layers of polyimide tape, and one layer of aluminum foil tape are sequentially laminated to obtain a metal reflective layer. After coating one layer of alkali-free fiberglass cloth, one layer of ceramic fiber cloth and three layers of quartz fiber cloth with silicone rubber, they are stacked and bonded together in sequence, and then sealed by vacuum hot pressing to obtain the fiber fabric layer. The active flexible heat protection material is obtained by sequentially layering and bonding the heat insulation layer, the metal reflective layer, and the fiber fabric layer.

[0046] Example 4: 60 parts of methylhydrogen liquid ceramic resin, 12 parts of methyltrimethoxysilane, 28 parts of dilute nitric acid, 10 parts of deionized water and 6 parts of graphite substrate were mixed and stirred evenly in a certain proportion, and dried at 70°C for 20 h to obtain component A. Mix 43g of component A, 25g of chopped ceramic fibers and 6g of hollow silica microspheres, spread them evenly on a ceramic firing rack, and place them in a high-temperature box furnace for calcination in a nitrogen atmosphere. The calcination temperature is 1150℃ and the calcination time is 24 h. After calcination, remove the ceramic firing rack and take out the product to obtain the active flexible heat insulation material insulation layer. Four layers of single-sided aluminized polyimide film, two layers of polyimide tape, and three layers of aluminum foil tape are sequentially laminated to obtain a metal reflective layer. Five layers of alkali-free fiberglass cloth, three layers of ceramic fiber cloth, and one layer of quartz fiber cloth are coated with silicone rubber, then laminated in sequence and sealed by vacuum hot pressing to obtain a fiber fabric layer. The active flexible heat protection material is obtained by sequentially layering and bonding the heat insulation layer, the metal reflective layer, and the fiber fabric layer.

[0047] Example 5: 60 parts of methylhydrogen liquid ceramic resin, 10 parts of methyltrimethoxysilane, 20 parts of dilute nitric acid, 15 parts of deionized water and 6 parts of graphite substrate were mixed and stirred evenly in a certain proportion, and dried at 75°C for 23 h to obtain component A. Mix 39g of component A, 10g of chopped ceramic fibers and 7g of hollow silica microspheres, spread them evenly on a ceramic firing rack, and place them in a high-temperature box furnace for calcination in a nitrogen atmosphere at a temperature of 1200℃ for 26 hours. After calcination, remove the ceramic firing rack and take out the product to obtain the active flexible heat insulation material insulation layer. A metal reflective layer is prepared by sequentially bonding one layer of single-sided aluminized polyimide film, two layers of polyimide tape, and five layers of aluminum foil tape. After coating one layer of alkali-free fiberglass cloth, three layers of ceramic fiber cloth and four layers of quartz fiber cloth with silicone rubber, they are stacked and bonded together in sequence, and then sealed by vacuum hot pressing to obtain the fiber fabric layer. The active flexible heat protection material is obtained by sequentially layering and bonding the heat insulation layer, the metal reflective layer, and the fiber fabric layer.

[0048] Example 6: 60 parts of methylhydrogen liquid ceramic resin, 16 parts of methyltrimethoxysilane, 24 parts of dilute nitric acid, 20 parts of deionized water and 8 parts of graphite substrate were mixed and stirred evenly in a certain proportion, and dried at 680℃ for 22 h to obtain component A. Mix 41g of component A, 13g of chopped ceramic fibers and 6g of hollow silica microspheres, spread them evenly on a ceramic firing rack, and place them in a high-temperature box furnace for calcination in a nitrogen atmosphere at a temperature of 1050℃ for 25 hours. After calcination, remove the ceramic firing rack and take out the product to obtain the active flexible heat insulation material insulation layer. Two layers of single-sided aluminized polyimide film, five layers of polyimide tape, and three layers of aluminum foil tape are sequentially laminated to obtain a metal reflective layer. After coating three layers of alkali-free fiberglass cloth, three layers of ceramic fiber cloth and four layers of quartz fiber cloth with silicone rubber, they are stacked and bonded together in sequence, and then sealed by vacuum hot pressing to obtain the fiber fabric layer. The active flexible heat protection material is obtained by sequentially layering and bonding the heat insulation layer, the metal reflective layer, and the fiber fabric layer.

[0049] The active flexible heat-resistant material prepared in Example 1 of this invention is used to fabricate a heat-insulating module, which is then applied in sections to the protruding and recessed areas on the surface of the actuating component. The seams of the heat-insulating module are connected using a stitching design, covering the entire actuating component. Figure 2 As shown, the actuating parts after being covered were subjected to a real-world environmental test at 350°C, and the results are as follows. Figure 3 As shown.

[0050] from Figure 3 It can be seen that when the measured ambient temperature continues to increase and reaches 350℃ within 250 minutes, the temperature of the actuating parts covered by the active flexible heat-resistant material prepared in Example 1 of this invention is always below 190℃, proving that the active flexible heat-resistant material prepared in this invention has excellent heat insulation and temperature resistance performance.

[0051] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. An active flexible heat-resistant material, characterized in that, It includes an active flexible heat insulation material layer, a metal reflective layer, and a fiber fabric layer stacked in sequence; The active flexible heat insulation material insulation layer is prepared by calcining a mixture of methylhydrogen liquid ceramic resin, methyltrimethoxysilane, catalyst, diluent, graphite substrate, chopped ceramic fibers and hollow silica microspheres.

2. The active flexible heat-resistant material according to claim 1, characterized in that, The metal reflective layer includes at least one single-sided aluminized polyimide film, at least one polyimide tape, and at least one aluminum foil tape; The fiber fabric layer includes at least one layer of alkali-free fiberglass cloth, at least one layer of ceramic fiber cloth, and at least one layer of quartz fiber cloth.

3. The active flexible heat-resistant material according to claim 1, characterized in that, In the heat insulation layer of the active flexible heat-resistant material, the catalyst is a gel catalyst, preferably dilute nitric acid; The diluent is deionized water.

4. The active flexible heat-resistant material according to claim 1, characterized in that, The active flexible heat-resistant material has a thermal conductivity of 0.032~0.04 W / (m·K) and a temperature resistance of 800~1300℃ in an aerobic environment.

5. A method for preparing the active flexible heat-resistant material according to any one of claims 1 to 4, characterized in that, include: Methylhydrogen liquid ceramic resin, methyltrimethoxysilane, catalyst, diluent and graphite substrate are mixed evenly and dried to obtain component A; Component A, chopped ceramic fibers and hollow silica microspheres were mixed, spread evenly and calcined to obtain an active flexible heat insulation material layer. A single-sided aluminized polyimide film, polyimide tape, and aluminum foil tape are sequentially laminated to obtain a metal reflective layer; Each layer of alkali-free fiberglass cloth, ceramic fiber cloth, and quartz fiber cloth is coated with silicone rubber, and then layered and laminated in sequence. The fiber fabric layer is obtained by vacuum hot pressing and sealing. The active flexible heat protection material is obtained by sequentially layering and bonding the heat insulation layer, the metal reflective layer, and the fiber fabric layer.

6. The method for preparing the active flexible heat-resistant material according to claim 5, characterized in that, By mass, component A includes 60 parts of methylhydrogen liquid ceramic resin, 10-20 parts of methyltrimethoxysilane, 20-35 parts of catalyst, 10-25 parts of diluent and 5-10 parts of graphite substrate.

7. The method for preparing the active flexible heat-resistant material according to claim 5, characterized in that, The mass ratio of component A, chopped ceramic fibers and hollow silica microspheres is (35~50):(10~25):(6~8).

8. The method for preparing the active flexible heat-resistant material according to claim 5, characterized in that, The drying temperature of component A is 60~80℃, and the drying time is 20~24h.

9. The method for preparing the active flexible heat-resistant material according to claim 5, characterized in that, The calcination atmosphere is nitrogen, the calcination temperature is 1000~1200℃, and the calcination time is 24~26 h.

10. The application of the active flexible heat-resistant material according to any one of claims 1 to 4 on the surface of actuating components of a supersonic aircraft / aero-engine, characterized in that, Active flexible heat-resistant material is prepared into heat-insulating modules, which are then applied in sections to the protrusions and / or recesses on the surface of the actuating parts. The heat-insulating modules are then connected by stitching.

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