A high-temperature-resistant flexible heat-resistant and insulating skin and a preparation method thereof

Abstract

The present application relates to the technical field of flexible thermal protection material, in particular to a high-temperature-resistant flexible heat-proof and heat-insulating skin and a preparation method thereof. The present application provides a high-temperature-resistant flexible heat-proof and heat-insulating skin, which comprises the following functional layers in turn along the thickness direction: a heat-proof layer, a heat-insulating layer and a load-bearing layer; wherein the heat-proof layer is used for bearing aerodynamic heat load, resisting airflow scouring and reducing heat flow entering; the heat-insulating layer is used for hindering heat transfer, reducing overall density and providing flexible support; and the load-bearing layer is used for bearing external force load and preventing airflow penetration. The present application provides a high-temperature-resistant flexible heat-proof and heat-insulating skin and a preparation method thereof, which can provide a novel thermal protection material with high-temperature resistance, scouring resistance, high-efficiency heat insulation and good flexibility.

Description

Technical Field

[0001] This invention relates to the field of flexible thermal protection materials technology, and in particular to a high-temperature resistant flexible heat-insulating skin and its preparation method. Background Technology

[0002] Spacecraft employing traditional deceleration technology rely primarily on their rigid aerodynamic shape for slowing during entry, descent, and landing to achieve safe parachute deployment within a limited descent altitude. However, the spacecraft's dimensions are strictly limited by the size of the launch vehicle's fairing, resulting in serious problems with traditional deceleration technologies that rely on the spacecraft's rigid aerodynamic shape, such as small effective drag area, poor deceleration effect, and low payload ratio, which cannot meet the needs of future spacecraft development.

[0003] To overcome the bottlenecks of traditional deceleration technologies, deployable aerodynamic decelerators have gained increasing attention and research as a novel deceleration technology. This technology utilizes a retraction-deployment mechanism to alter the spacecraft's configuration, achieving a larger drag surface and thus better aerodynamic deceleration. Compared to traditional deceleration technologies that rely on the rigid aerodynamic shape of the spacecraft, deployable aerodynamic decelerators offer advantages such as simple structure, high versatility, small retracted volume, and large deployed area. They are no longer limited by the fairing size of the launch vehicle, and the aerodynamic layout and dimensions of the drag surface can be flexibly designed according to specific missions and payloads, showing broad application prospects in future deep space exploration, space transportation, and other fields.

[0004] However, during aerodynamic deceleration, the intense compression and friction between the deployable aerodynamic reducer and the planetary atmosphere subject the drag surface to severe aerodynamic / thermal loads. This necessitates that the reducer's drag surface possess excellent heat insulation performance, while also exhibiting good flexibility to ensure its shape transformation capability. However, current typical high-temperature thermal protection materials fall short of these requirements: rigid thermal insulation tiles lack flexibility and are difficult to deform; flexible thermal insulation felts are thick and have low insulation efficiency; and rubber-based thermal protection materials have high density and are not resistant to ablation. Therefore, there is an urgent need for a lightweight thermal protection material that combines excellent heat insulation performance with good flexibility to meet the stringent thermal protection requirements of deployable aerodynamic reducers.

[0005] Furthermore, with the rise of research on trans-domain variable-configuration aircraft, aircraft skins not only need to possess excellent erosion resistance and thermal insulation properties to withstand the intense airflow erosion and aerodynamic heating during hypersonic flight, but also need to have good flexibility to adapt to continuous changes in aircraft configuration. Traditional rigid thermal insulation structures such as ceramic heat insulation tiles and sandwich layers lack flexibility and cannot meet the needs of variable-configuration aircraft. While novel flexible thermal protection structures such as actively cooled flexible skins can balance thermal insulation performance and flexibility, their thermal protection function depends on the cooling medium to remove heat. Therefore, additional storage, delivery, and control systems for the cooling medium are required, increasing the size and weight of the aircraft. At the same time, the complex microchannel structure also poses a risk of cooling medium blockage and leakage. Therefore, there is an urgent need to develop new thermal protection materials that combine high temperature resistance, erosion resistance, high-efficiency thermal insulation, and good flexibility. Summary of the Invention

[0006] This invention provides a high-temperature resistant flexible heat-insulating skin and its preparation method, which can provide a new type of thermal protection material that combines high temperature resistance, erosion resistance, high-efficiency heat insulation and good flexibility.

[0007] In a first aspect, embodiments of the present invention provide a high-temperature resistant flexible heat-insulating skin, comprising, along its thickness direction, the following flexible functional layers: The structure comprises a heat-resistant layer, a heat-insulating layer, and a load-bearing layer; wherein the heat-resistant layer is used to withstand aerodynamic heat loads, resist incoming flow erosion, and reduce heat flow ingress; the heat-insulating layer is used to impede heat transfer, reduce overall density, and provide flexible support; and the load-bearing layer is used to bear external loads and prevent airflow penetration.

[0008] Optionally, the heat-resistant layer comprises any one or more stacks of fiber cloth and silicone rubber / fiber composite cloth; The fiber cloth is any one or more of carbon fiber cloth, glass fiber cloth, basalt fiber cloth, high silica fiber cloth, quartz fiber cloth, mullite fiber cloth, alumina fiber cloth, and silicon carbide fiber cloth; wherein, the thickness of a single layer of fiber cloth is 0.1~0.6mm. The silicone rubber used in the silicone rubber / fiber composite fabric is any one or more of dimethyl silicone rubber, methyl vinyl silicone rubber, methyl phenyl vinyl silicone rubber, fluorosilicone rubber, nitrile silicone rubber, phenylene silicone rubber, and phenyl ether silicone rubber. The fiber material used in the silicone rubber / fiber composite fabric is any one or more of carbon fiber cloth, glass fiber cloth, basalt fiber cloth, high silica fiber cloth, quartz fiber cloth, mullite fiber cloth, alumina fiber cloth, and silicon carbide fiber cloth. The thickness of a single layer of silicone rubber / fiber composite fabric is 0.15~0.8mm.

[0009] Optionally, the thermal insulation layer comprises any one or more stacks of aerogel, fiber felt, fiber paper, aerogel / fiber composite felt, and aerogel / fiber composite paper; The aerogel is any one or more of flexible polyimide aerogel, flexible phenolic aerogel, flexible organosilicon aerogel, and flexible ceramic fiber aerogel stacked together; wherein the thickness of a single layer of aerogel is 0.2~3.0 mm. The fiber felt is any one or more of the following: pre-oxidized fiber felt, carbon fiber felt, glass fiber felt, basalt fiber felt, high silica fiber felt, quartz fiber felt, mullite fiber felt, alumina fiber felt, zirconium oxide fiber felt, and silicon carbide fiber felt stacked together; wherein, the thickness of a single layer of fiber felt is 0.5~3.0mm. The fiber paper is any one or more of the following: carbon fiber paper, glass fiber paper, basalt fiber paper, high silica fiber paper, quartz fiber paper, mullite fiber paper, alumina fiber paper, zirconium oxide fiber paper, and silicon carbide fiber paper; wherein, the thickness of a single layer of fiber paper is 0.2~1.0 mm. The aerogel / fiber composite felt uses aerogel materials that are any one or more of the following: phenolic aerogel, silica aerogel, mullite aerogel, alumina aerogel, and zirconia aerogel stacked together. The fiber felt materials used in the aerogel / fiber composite felt are any one or more of the following: pre-oxidized fiber felt, carbon fiber felt, glass fiber felt, basalt fiber felt, high silica fiber felt, quartz fiber felt, mullite fiber felt, alumina fiber felt, zirconia fiber felt, and silicon carbide fiber felt stacked together. The thickness of a single layer of aerogel / fiber composite felt is 0.5~3.0 mm. The aerogel / fiber composite paper uses aerogel material that is any one or more of phenolic aerogel, silica aerogel, mullite aerogel, alumina aerogel, and zirconia aerogel stacked together. The fiber paper material used in the aerogel / fiber composite paper uses any one or more of carbon fiber paper, glass fiber paper, basalt fiber paper, high silica fiber paper, quartz fiber paper, mullite fiber paper, alumina fiber paper, zirconia fiber paper, and silicon carbide fiber paper stacked together. The thickness of a single layer of aerogel / fiber composite paper is 0.2~1.0 mm.

[0010] Optionally, the load-bearing layer comprises any one or more stacks of fiber cloth and polymer / fiber composite cloth; The fiber cloth is any one or more of the following: aramid fiber cloth, polyimide fiber cloth, poly(p-phenylenebenzodioxazole) fiber cloth, poly[2,5-dihydroxy-1,4-phenylenepyridinium diimidazole] fiber cloth, carbon fiber cloth, glass fiber cloth, high silica fiber cloth, and quartz fiber cloth; wherein, the thickness of a single layer of fiber cloth is 0.1~0.3mm. The polymer used in the polymer / fiber composite fabric is any one or more of dimethyl silicone rubber, methyl vinyl silicone rubber, methyl phenyl vinyl silicone rubber, fluorosilicone rubber, nitrile silicone rubber, phenylene silicone rubber, phenyl ether silicone rubber, fluororubber, perfluoroether rubber, and polytetrafluoroethylene. The fiber material used in the polymer / fiber composite fabric is any one or more of aramid fiber cloth, polyimide fiber cloth, poly(p-phenylenebenzodioxazole) fiber cloth, poly[2,5-dihydroxy-1,4-phenylenepyridinium diimidazole] fiber cloth, carbon fiber cloth, glass fiber cloth, high silica fiber cloth, and quartz fiber cloth stacked together. The thickness of a single layer of polymer / fiber composite fabric is 0.15~0.5mm.

[0011] Optionally, the weaving method of the single-layer material in the heat-insulating layer and the load-bearing layer can be any one of plain weave, twill weave, or satin weave.

[0012] Optionally, different functional layers are connected to each other and to each layer within each functional layer by fiber optic cables or organic adhesives. The fiber thread is any one or more of carbon fiber thread, glass fiber thread, basalt fiber thread, high silica fiber thread, quartz fiber thread, mullite fiber thread, alumina fiber thread, and silicon carbide fiber thread; wherein, the linear density of a single fiber thread is 100~1200 tex, and the twist is 40~300 T / m. The organic adhesive is any one or more of silicone, epoxy resin, and acrylic adhesive.

[0013] Secondly, embodiments of the present invention provide a method for preparing a high-temperature resistant flexible heat-insulating skin, used to prepare any of the high-temperature resistant flexible heat-insulating skins described above, the preparation method comprising: (1) Determine the type, thickness, number of layers and arrangement order of materials used in each functional layer based on the service environment and the comprehensive performance of the materials themselves; (2) Cut the materials used in each functional layer into specific shapes as needed; (3) Lay the materials for each functional layer from bottom to top in a pre-designed order; (4) Determine the suturing method, stitches, and stitch length based on the size of the skin and the requirements for flexibility and strength; (5) Use fiber thread to sew together the internal layers of the heat-insulating layer and the heat insulation layer with higher temperature according to the pre-designed stitch pattern, stitch and stitch distance; (6) Use organic adhesive to bond the unstitched insulation layer and the insulation layer to the load-bearing layer.

[0014] Optionally, when using fiber optic threads for stitching, at least one layer of insulation should be left unpierced by the fiber optic threads to prevent the formation of a rapid heat conduction channel that reaches the load-bearing layer directly.

[0015] Optionally, the surfaces to be bonded may be treated with a silane coupling agent or plasma before bonding with organic adhesive to improve bond strength.

[0016] Optionally, the silane coupling agent is any one or more of KH550, KH560, KH570, and VTPS; The plasma gas composition is any one or more of helium, argon, air, nitrogen, oxygen, hydrogen, ammonia, and carbon dioxide.

[0017] Compared with the prior art, the present invention has at least the following beneficial effects: The high-temperature resistant flexible heat-insulating skin provided by this invention overcomes the inherent defects of traditional rigid heat-insulating tiles, such as lack of flexibility and difficulty in deformation, large thickness and low heat insulation efficiency of flexible heat-insulating felt, and high density and poor ablation resistance of rubber-based heat protection materials. It achieves effective compatibility between low density, high flexibility and high efficiency heat insulation, and can meet the flexible heat protection requirements above 1300℃.

[0018] The high-temperature resistant flexible heat insulation skin provided by this invention has good compressive strength, which is an order of magnitude higher than that of traditional flexible heat insulation felt based on ceramic fiber cotton. It has better out-of-plane deformation resistance under high dynamic pressure environment, which not only helps to maintain the aerodynamic shape, but also ensures that the heat insulation performance will not be significantly reduced due to thickness compression caused by high dynamic pressure.

[0019] The high-temperature resistant flexible heat-insulating skin preparation method provided by this invention has high design flexibility. The type, number of layers, and interlayer bonding method of the single-layer materials used in each functional layer can be flexibly selected and combined according to the actual service environment and different performance requirements such as load-bearing capacity, heat insulation, deformation, thickness, and density. At the same time, multiple high-temperature resistant flexible heat-insulating skins can also be cut and spliced ​​as needed, thereby realizing on-demand customization of any size and different materials.

[0020] The method for preparing high-temperature resistant flexible heat-insulating skin provided by this invention is simple, with flexible and diverse raw material selection, and has the potential for large-scale and mass production. It not only has broad application prospects in aerospace fields such as deployable aerodynamic reducers and cross-domain variable structure aircraft, but can also be extended to new energy vehicles, fire rescue, energy conservation and emission reduction fields such as thermal runaway protection of power batteries, high-temperature operation protection, and thermal insulation of industrial kilns, which can generate good economic and social benefits. Attached Figure Description

[0021] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0022] Figure 1 This is a schematic diagram of the high-temperature resistant flexible heat-insulating skin structure of the present invention; Figure 2 This is a schematic diagram of the high-temperature resistant flexible heat-insulating skin layer layup and interlayer stitching and bonding method in Embodiment 1 of the present invention; Figure 3 This is a curve showing the surface temperature change over time during the thermal protection performance evaluation of the high-temperature resistant flexible heat-insulating skin obtained in Embodiment 3 of the present invention. Figure 4 This is a schematic diagram of the surface stitching method of the high-temperature resistant flexible heat-insulating skin in Embodiment 4 of the present invention; Figure 5 This is a stress-strain curve diagram of the high-temperature resistant flexible heat-insulating skin obtained in Embodiment 4 of the present invention during the test of its compressive strength. Figure 6 This is a graph showing the change in back surface temperature over time during the thermal protection performance evaluation of the high-temperature resistant flexible heat-insulating skin obtained in Embodiment 4 of the present invention.

[0023] In the picture: 1-Heatproof layer, 11-Twill quartz fiber cloth, 12-Plain basalt fiber cloth, 2-Heat insulation layer, 21-Quartz fiber paper, 22-Silica aerogel / high silica fiber composite felt, 23-Silica aerogel / pre-oxygenated fiber composite felt, 24-Flexible organosilicon aerogel, 3-Bearing layer, 31-Methyl vinyl silicone rubber / plain aramid fiber composite cloth, 4-Fiber thread, 41-Quartz fiber thread, 5-Organic adhesive, 51-Organic silicone water. Detailed Implementation

[0024] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are some embodiments of the present invention, but not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0025] In the description of the embodiments of the present invention, unless otherwise expressly specified and limited, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance; unless otherwise specified or stated, the term "multiple" refers to two or more; the terms "connected," "fixed," etc., should be interpreted broadly. For example, "connected" can be a fixed connection, a detachable connection, an integral connection, or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in the present invention according to the specific circumstances.

[0026] In this specification, it should be understood that the directional terms such as "upper" and "lower" used in the description of the embodiments of the present invention are used to describe the angles shown in the accompanying drawings and should not be construed as limiting the embodiments of the present invention. Furthermore, in the context, it should also be understood that when it is mentioned that one element is connected "upper" or "lower" to another element, it can be directly connected to the other element "upper" or "lower," or indirectly connected to the other element "upper" or "lower" through an intermediate element.

[0027] like Figure 1 As shown, this embodiment of the invention provides a high-temperature resistant flexible heat-insulating skin, which includes the following flexible functional layers sequentially along the thickness direction: The structure comprises a heat-resistant layer, a heat-insulating layer, and a load-bearing layer; wherein the heat-resistant layer is used to withstand aerodynamic heat loads, resist incoming flow erosion, and reduce heat flow ingress; the heat-insulating layer is used to impede heat transfer, reduce overall density, and provide flexible support; and the load-bearing layer is used to bear external loads and prevent airflow penetration.

[0028] In this embodiment, the surface heat insulation layer mainly serves to withstand aerodynamic heat loads, resist incoming flow erosion, and reduce heat flow ingress; the middle heat insulation layer mainly serves to hinder heat transfer, reduce overall density, and provide flexible support; and the bottom load-bearing layer mainly serves to bear external loads and prevent airflow penetration.

[0029] In some embodiments of the present invention, the heat-resistant layer comprises any one or more stacks of fiber cloth and silicone rubber / fiber composite cloth; The fiber cloth is any one or more of carbon fiber cloth, glass fiber cloth, basalt fiber cloth, high silica fiber cloth, quartz fiber cloth, mullite fiber cloth, alumina fiber cloth, and silicon carbide fiber cloth; wherein, the thickness of a single layer of fiber cloth is 0.1~0.6mm. The silicone rubber used in the silicone rubber / fiber composite fabric is any one or more of dimethyl silicone rubber, methyl vinyl silicone rubber, methyl phenyl vinyl silicone rubber, fluorosilicone rubber, nitrile silicone rubber, phenylene silicone rubber, and phenyl ether silicone rubber. The fiber material used in the silicone rubber / fiber composite fabric is any one or more of carbon fiber cloth, glass fiber cloth, basalt fiber cloth, high silica fiber cloth, quartz fiber cloth, mullite fiber cloth, alumina fiber cloth, and silicon carbide fiber cloth. The thickness of a single layer of silicone rubber / fiber composite fabric is 0.15~0.8mm.

[0030] In some embodiments of the present invention, the heat insulation layer comprises any one or more stacks of aerogel, fiber felt, fiber paper, aerogel / fiber composite felt, and aerogel / fiber composite paper; The aerogel is any one or more of flexible polyimide aerogel, flexible phenolic aerogel, flexible organosilicon aerogel, and flexible ceramic fiber aerogel stacked together; wherein the thickness of a single layer of aerogel is 0.2~3.0 mm. The fiber felt is any one or more of the following: pre-oxidized fiber felt, carbon fiber felt, glass fiber felt, basalt fiber felt, high silica fiber felt, quartz fiber felt, mullite fiber felt, alumina fiber felt, zirconium oxide fiber felt, and silicon carbide fiber felt stacked together; wherein, the thickness of a single layer of fiber felt is 0.5~3.0mm. The fiber paper is any one or more of the following: carbon fiber paper, glass fiber paper, basalt fiber paper, high silica fiber paper, quartz fiber paper, mullite fiber paper, alumina fiber paper, zirconium oxide fiber paper, and silicon carbide fiber paper; wherein, the thickness of a single layer of fiber paper is 0.2~1.0 mm. The aerogel / fiber composite felt uses aerogel materials that are any one or more of the following: phenolic aerogel, silica aerogel, mullite aerogel, alumina aerogel, and zirconia aerogel stacked together. The fiber felt materials used in the aerogel / fiber composite felt are any one or more of the following: pre-oxidized fiber felt, carbon fiber felt, glass fiber felt, basalt fiber felt, high silica fiber felt, quartz fiber felt, mullite fiber felt, alumina fiber felt, zirconia fiber felt, and silicon carbide fiber felt stacked together. The thickness of a single layer of aerogel / fiber composite felt is 0.5~3.0 mm. The aerogel / fiber composite paper uses aerogel material that is any one or more of phenolic aerogel, silica aerogel, mullite aerogel, alumina aerogel, and zirconia aerogel stacked together. The fiber paper material used in the aerogel / fiber composite paper uses any one or more of carbon fiber paper, glass fiber paper, basalt fiber paper, high silica fiber paper, quartz fiber paper, mullite fiber paper, alumina fiber paper, zirconia fiber paper, and silicon carbide fiber paper stacked together. The thickness of a single layer of aerogel / fiber composite paper is 0.2~1.0 mm.

[0031] In some embodiments of the present invention, the load-bearing layer comprises any one or more stacks of fiber cloth and polymer / fiber composite cloth; The fiber cloth is any one or more of the following: aramid fiber cloth, polyimide fiber cloth, poly(p-phenylenebenzodioxazole) fiber cloth, poly[2,5-dihydroxy-1,4-phenylenepyridinium diimidazole] fiber cloth, carbon fiber cloth, glass fiber cloth, high silica fiber cloth, and quartz fiber cloth; wherein, the thickness of a single layer of fiber cloth is 0.1~0.3mm. The polymer used in the polymer / fiber composite fabric is any one or more of dimethyl silicone rubber, methyl vinyl silicone rubber, methyl phenyl vinyl silicone rubber, fluorosilicone rubber, nitrile silicone rubber, phenylene silicone rubber, phenyl ether silicone rubber, fluororubber, perfluoroether rubber, and polytetrafluoroethylene. The fiber material used in the polymer / fiber composite fabric is any one or more of aramid fiber cloth, polyimide fiber cloth, poly(p-phenylenebenzodioxazole) fiber cloth, poly[2,5-dihydroxy-1,4-phenylenepyridinium diimidazole] fiber cloth, carbon fiber cloth, glass fiber cloth, high silica fiber cloth, and quartz fiber cloth stacked together. The thickness of a single layer of polymer / fiber composite fabric is 0.15~0.5mm.

[0032] In some embodiments of the present invention, the weaving method of the single-layer material in the heat-insulating layer and the load-bearing layer is any one of plain weave, twill weave, or satin weave.

[0033] In some embodiments of the present invention, different functional layers are connected to each other and to each layer within each functional layer by fiber optics or organic adhesives. The fiber thread is any one or more of carbon fiber thread, glass fiber thread, basalt fiber thread, high silica fiber thread, quartz fiber thread, mullite fiber thread, alumina fiber thread, and silicon carbide fiber thread; wherein, the linear density of a single fiber thread is 100~1200 tex, and the twist is 40~300 T / m. The organic adhesive is any one or more of silicone, epoxy resin, and acrylic adhesive.

[0034] It is understandable that the type, thickness, number of layers, and arrangement order of materials used in each of the above functional layers are determined based on the service environment and the comprehensive performance of the materials themselves. These materials are cut into specific shapes as needed, then laid out layer by layer in a pre-designed sequence, and finally bonded together using fiber filaments or organic adhesives. The types of fiber filaments and organic adhesives used are also determined based on the service environment and the comprehensive performance of the materials themselves.

[0035] The fiber threads are used to connect the various layers within the heat-insulating layer and the higher-temperature insulation layer. At least one insulation layer must remain unpierced by the fiber threads to prevent the formation of a rapid heat conduction channel directly to the load-bearing layer. The stitching method, stitch type, and stitch spacing are determined based on the skin size and the required flexibility and strength.

[0036] This invention provides a method for preparing a high-temperature resistant flexible heat-insulating skin, used to prepare any of the high-temperature resistant flexible heat-insulating skins described above, the preparation method comprising: (1) Determine the type, thickness, number of layers and arrangement order of materials used in each functional layer based on the service environment and the comprehensive performance of the materials themselves; (2) Cut the materials used in each functional layer into specific shapes as needed; (3) Lay the materials for each functional layer from bottom to top in a pre-designed order; (4) Determine the suturing method, stitches, and stitch length based on the size of the skin and the requirements for flexibility and strength; (5) Use fiber thread to sew together the internal layers of the heat-insulating layer and the heat insulation layer with higher temperature according to the pre-designed stitch pattern, stitch and stitch distance; (6) Use organic adhesive to bond the unstitched insulation layer and the insulation layer to the load-bearing layer.

[0037] In some embodiments of the present invention, when using fiber thread for sewing, at least one heat insulation layer is retained that is not penetrated by the fiber thread in order to avoid forming a rapid heat conduction channel that directly reaches the load-bearing layer.

[0038] In some embodiments of the present invention, the surfaces to be bonded are treated with a silane coupling agent or plasma before bonding with organic adhesive to improve the bonding strength.

[0039] In some embodiments of the present invention, the silane coupling agent is any one or more of KH550, KH560, KH570, and VTPS; The plasma gas composition is any one or more of helium, argon, air, nitrogen, oxygen, hydrogen, ammonia, and carbon dioxide.

[0040] To more clearly illustrate the technical solution and advantages of the present invention, the following detailed description of a method for preparing a cranial repair material is provided through several embodiments. Example 1

[0041] (1) Selection of heat-insulating layer materials One layer of 0.3mm thick twill quartz fiber cloth and two layers of 0.2mm thick plain basalt fiber cloth were selected as the heat insulation layer material.

[0042] (2) Selection of insulation material Two layers of 1.0mm thick quartz fiber paper, two layers of 1.0mm thick silica aerogel / high silica fiber composite felt, two layers of 1.0mm thick silica aerogel / pre-oxygenated fiber composite felt, and one layer of 1.0mm thick flexible organosilicon aerogel were selected as the thermal insulation layer materials.

[0043] (3) Selection of load-bearing layer materials A 0.3mm thick methyl vinyl silicone rubber / plain weave aramid fiber composite fabric was selected as the load-bearing layer material.

[0044] (4) Layup sequence The layup sequence from the outside to the inside is as follows: 1 layer of twill quartz fiber cloth, 2 layers of plain basalt fiber cloth, 2 layers of quartz fiber paper, 2 layers of silica aerogel / high silica fiber composite felt, 2 layers of silica aerogel / pre-oxygenated fiber composite felt, 1 layer of flexible organosilicon aerogel, and 1 layer of methyl vinyl silicone rubber / plain aramid fiber composite cloth.

[0045] (5) Interlayer stitching and bonding Quartz fiber thread with a linear density of 190 tex was selected as the suture thread. One layer of twill quartz fiber cloth, two layers of plain basalt fiber cloth, two layers of quartz fiber paper, two layers of silica aerogel / high silica fiber composite felt, and two layers of silica aerogel / pre-oxygenated fiber composite felt were sewn together as a whole. The sewing method was single-strand bidirectional sewing, and the suture spacing was 5 mm × 5 mm.

[0046] Using silicone water as an adhesive, a layer of flexible silicone aerogel is bonded to the back of the second layer of silica aerogel / pre-oxidized fiber composite felt after sewing. Then, a layer of methyl vinyl silicone rubber / plain weave aramid fiber composite fabric is bonded to the back of the flexible silicone aerogel.

[0047] Layup sequence and interlayer stitching and bonding methods, such as Figure 2 As shown. Example 2

[0048] (1) Selection of heat-insulating layer materials One layer of 0.5mm thick methyl phenyl vinyl silicone rubber / satin mullite fiber composite cloth and two layers of 0.3mm thick twill quartz fiber cloth were selected as the heat insulation layer material.

[0049] (2) Selection of insulation material Two layers of 1.0mm thick mullite aerogel / alumina fiber composite paper, nine layers of 0.4mm thick flexible silica ceramic fiber aerogel, two layers of 1.0mm thick silica aerogel / pre-oxidized fiber composite felt, and two layers of 0.5mm thick flexible polyimide aerogel were selected as the thermal insulation layer materials.

[0050] (3) Selection of load-bearing layer materials A 0.3mm thick methyl vinyl silicone rubber / plain weave polyimide fiber composite fabric was selected as the load-bearing layer material.

[0051] (4) Layup sequence The layup sequence from the outside to the inside is as follows: 1 layer of methyl phenyl vinyl silicone rubber / satin mullite fiber composite cloth, 2 layers of twill quartz fiber cloth, 2 layers of mullite aerogel / alumina fiber composite paper, 9 layers of flexible silica ceramic fiber aerogel, 2 layers of silica aerogel / pre-oxidized filament fiber composite felt, 2 layers of flexible polyimide aerogel, and 1 layer of methyl vinyl silicone rubber / plain polyimide fiber composite cloth.

[0052] (5) Interlayer stitching and bonding Mullite fiber thread with a linear density of 400 tex was selected as the suture thread. One layer of methyl phenyl vinyl silicone rubber / satin mullite fiber composite cloth, two layers of twill quartz fiber cloth, two layers of mullite aerogel / alumina fiber composite paper, nine layers of flexible silica ceramic fiber aerogel, and two layers of silica aerogel / pre-oxygenated fiber composite felt were sewn together as a whole. The sewing method was double-strand bidirectional sewing, and the suture spacing was 8mm×8mm.

[0053] Using silicone rubber as the first adhesive, the first layer of flexible polyimide aerogel was first bonded to the back of the sewn second layer of silica aerogel / pre-oxidized fiber composite felt. Then, the second layer of flexible polyimide aerogel was bonded to the back of the first layer. Using epoxy resin as the second adhesive, a layer of methyl vinyl silicone rubber / plain weave polyimide fiber composite fabric was bonded to the back of the second layer of flexible polyimide aerogel. Before bonding the methyl vinyl silicone rubber / plain weave polyimide fiber composite fabric, its surface was pre-treated with a plasma cleaner (air was used as the working gas) to improve its adhesive properties. Example 3

[0054] (1) Selection of heat-insulating layer materials One layer of 0.5mm thick fluorosilicone rubber / twill alumina fiber composite cloth and two layers of 0.3mm thick twill mullite fiber cloth were selected as the heat insulation layer material.

[0055] (2) Selection of insulation material The insulation layer material consists of two 1.5mm thick layers of alumina aerogel / alumina fiber composite felt, three 1.0mm thick layers of mullite aerogel / quartz fiber composite felt, two 1.0mm thick layers of silica aerogel / glass fiber composite paper, and one 0.6mm thick layer of flexible phenolic aerogel.

[0056] (3) Selection of load-bearing layer materials A 0.3mm thick layer of perfluoroether rubber / twill PBO fiber composite fabric was selected as the load-bearing layer material.

[0057] (4) Layup sequence The layering sequence from the outside to the inside is as follows: 1 layer of fluorosilicone rubber / twill alumina fiber composite cloth, 2 layers of twill mullite fiber cloth, 2 layers of alumina aerogel / alumina fiber composite felt, 3 layers of mullite aerogel / quartz fiber composite felt, 2 layers of silica aerogel / glass fiber composite paper, 1 layer of flexible phenolic aerogel, and 1 layer of perfluoroether rubber / twill PBO fiber composite cloth.

[0058] (5) Interlayer stitching and bonding Alumina fiber thread with a linear density of 420 tex was selected as the suture thread. One layer of fluorosilicone rubber / twill alumina fiber composite fabric, two layers of twill mullite fiber fabric, two layers of alumina aerogel / alumina fiber composite felt, three layers of mullite aerogel / quartz fiber composite felt, and two layers of silica aerogel / glass fiber composite paper were sewn together as a whole. The sewing method was single-strand bidirectional sewing, and the sewing interval was 10 mm × 10 mm.

[0059] Silicone ether liquid was selected as the first adhesive to bond a layer of flexible phenolic aerogel to the back of the sewn second layer of silica aerogel / glass fiber composite paper. Acrylic ester adhesive was selected as the second adhesive to bond a layer of perfluoroether rubber / twill PBO fiber composite fabric to the back of the flexible phenolic aerogel. Before bonding the perfluoroether rubber / twill PBO fiber composite fabric, its surface was pretreated with silane coupling agent VTPS to improve its adhesive properties.

[0060] (6) Thermal protection performance assessment The thermal protection performance of the prepared high-temperature resistant flexible heat-insulating skin was tested using a Manpu gas cylinder (a mixture of propyne, propylene, and propane) and an oxygen-free welding torch for 120 seconds. Temperature changes on the skin surface were recorded during the test using a dual-color infrared thermometer. Figure 3 As shown, thermocouples were used to record the temperature changes on the back of the skin during the test. The highest temperature on the skin surface exceeded 1300℃ during the test, while the temperature on the back remained below 200℃. Example 4

[0061] (1) Selection of heat-insulating layer materials One layer of 0.35mm thick phenylene ether silicone rubber / plain weave silicon carbide fiber composite cloth and two layers of 0.25mm thick satin alumina fiber cloth were selected as the heat insulation layer material.

[0062] (2) Selection of insulation material The insulation layer material consists of one 2.0 mm thick zirconia fiber felt, six 1.0 mm thick silica aerogel / quartz fiber composite paper, three 1.0 mm thick silica aerogel / pre-oxidized fiber composite felt, and two 0.5 mm thick flexible polyimide aerogel.

[0063] (3) Selection of load-bearing layer materials A 0.15mm thick polytetrafluoroethylene / plain weave glass fiber composite fabric was selected as the load-bearing layer material.

[0064] (4) Layup sequence The layup sequence from the outside to the inside is as follows: 1 layer of phenylene ether-supported silicone rubber / plain weave silicon carbide fiber composite cloth, 2 layers of satin weave alumina fiber cloth, 1 layer of zirconium oxide fiber felt, 6 layers of silica aerogel / quartz fiber composite paper, 3 layers of silica aerogel / pre-oxidized fiber composite felt, 2 layers of flexible polyimide aerogel, and 1 layer of polytetrafluoroethylene / plain weave glass fiber composite cloth.

[0065] (5) Interlayer stitching and bonding Using 220tex silicon carbide fiber thread as suture, one layer of phenylene ether-supported silicone rubber / plain weave silicon carbide fiber composite fabric, two layers of satin weave alumina fiber fabric, one layer of zirconium oxide fiber felt, six layers of silica aerogel / quartz fiber composite paper, and three layers of silica aerogel / pre-oxidized fiber composite felt are sewn together. The sewing method is double-strand bidirectional sewing, with a stitch spacing of 20mm × 20mm. Adjacent stitches are staggered. The sewing method is as follows. Figure 4 As shown.

[0066] Using silicone adhesive as the first bonding agent, the first layer of flexible polyimide aerogel was first bonded to the back of the sewn third layer of silica aerogel / pre-oxidized fiber composite felt. Then, the second layer of flexible polyimide aerogel was bonded to the back of the first layer. Using acrylic adhesive as the second bonding agent, one layer of PTFE / plain weave fiberglass composite fabric was bonded to the back of the second layer of flexible polyimide aerogel. Before bonding the PTFE / plain weave fiberglass composite fabric, its surface was pre-treated with a plasma cleaner (a mixture of argon and oxygen) to improve its bonding performance.

[0067] (6) Compressive strength test The compressive strength of the prepared high-temperature resistant flexible heat-insulating skin was tested using a universal testing machine. The sample size was 50×50mm. 2 The loading rate was 5 mm / min, and loading was stopped when the compressive strain of the skin exceeded 10%. The stress-strain curve during compression is shown below. Figure 5 As shown, when the compressive strain is 10%, the compressive strength of the skin can reach 20.2 kPa.

[0068] (7) Thermal protection performance assessment The thermal protection performance of the prepared high-temperature resistant flexible heat-insulating skin was tested using a muffle furnace. Before testing, the temperature inside the muffle furnace was heated to 1300℃ and maintained constant. Then, the skin was placed in a pre-reserved heating window at the top of the muffle furnace for single-sided heating testing, with a testing time of 120 seconds. Thermocouples were used to record the temperature change of the center of the back side of the skin over time during the testing process. Figure 6 As shown. At the end of the test, the center temperature of the back of the skin was 70℃, and the temperature continued to rise, reaching a maximum of 146℃ in 242 seconds.

[0069] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A high-temperature resistant flexible heat-insulating skin, characterized in that, Along the thickness direction, it includes the following flexible functional layers in sequence: The structure comprises a heat-resistant layer, a heat-insulating layer, and a load-bearing layer; wherein the heat-resistant layer is used to withstand aerodynamic heat loads, resist incoming flow erosion, and reduce heat flow ingress; the heat-insulating layer is used to impede heat transfer, reduce overall density, and provide flexible support; and the load-bearing layer is used to bear external loads and prevent airflow penetration.

2. The high-temperature resistant flexible heat-insulating skin according to claim 1, characterized in that, The heat-resistant layer comprises any one or more stacks of fiber cloth and silicone rubber / fiber composite cloth; The fiber cloth is any one or more of carbon fiber cloth, glass fiber cloth, basalt fiber cloth, high silica fiber cloth, quartz fiber cloth, mullite fiber cloth, alumina fiber cloth, and silicon carbide fiber cloth; wherein, the thickness of a single layer of fiber cloth is 0.1~0.6mm. The silicone rubber used in the silicone rubber / fiber composite fabric is any one or more of dimethyl silicone rubber, methyl vinyl silicone rubber, methyl phenyl vinyl silicone rubber, fluorosilicone rubber, nitrile silicone rubber, phenylene silicone rubber, and phenyl ether silicone rubber. The fiber material used in the silicone rubber / fiber composite fabric is any one or more of carbon fiber cloth, glass fiber cloth, basalt fiber cloth, high silica fiber cloth, quartz fiber cloth, mullite fiber cloth, alumina fiber cloth, and silicon carbide fiber cloth. The thickness of a single layer of silicone rubber / fiber composite fabric is 0.15~0.8mm.

3. The high-temperature resistant flexible heat-insulating skin according to claim 1, characterized in that, The thermal insulation layer comprises any one or more stacks of aerogel, fiber felt, fiber paper, aerogel / fiber composite felt, and aerogel / fiber composite paper; The aerogel is any one or more of flexible polyimide aerogel, flexible phenolic aerogel, flexible organosilicon aerogel, and flexible ceramic fiber aerogel stacked together; wherein the thickness of a single layer of aerogel is 0.2~3.0 mm. The fiber felt is any one or more of the following: pre-oxidized fiber felt, carbon fiber felt, glass fiber felt, basalt fiber felt, high silica fiber felt, quartz fiber felt, mullite fiber felt, alumina fiber felt, zirconium oxide fiber felt, and silicon carbide fiber felt stacked together; wherein, the thickness of a single layer of fiber felt is 0.5~3.0mm. The fiber paper is any one or more of the following: carbon fiber paper, glass fiber paper, basalt fiber paper, high silica fiber paper, quartz fiber paper, mullite fiber paper, alumina fiber paper, zirconium oxide fiber paper, and silicon carbide fiber paper; wherein, the thickness of a single layer of fiber paper is 0.2~1.0 mm. The aerogel / fiber composite felt uses aerogel materials that are any one or more of the following: phenolic aerogel, silica aerogel, mullite aerogel, alumina aerogel, and zirconia aerogel stacked together. The fiber felt materials used in the aerogel / fiber composite felt are any one or more of the following: pre-oxidized fiber felt, carbon fiber felt, glass fiber felt, basalt fiber felt, high silica fiber felt, quartz fiber felt, mullite fiber felt, alumina fiber felt, zirconia fiber felt, and silicon carbide fiber felt stacked together. The thickness of a single layer of aerogel / fiber composite felt is 0.5~3.0 mm. The aerogel / fiber composite paper uses aerogel material that is any one or more of phenolic aerogel, silica aerogel, mullite aerogel, alumina aerogel, and zirconia aerogel stacked together. The fiber paper material used in the aerogel / fiber composite paper uses any one or more of carbon fiber paper, glass fiber paper, basalt fiber paper, high silica fiber paper, quartz fiber paper, mullite fiber paper, alumina fiber paper, zirconia fiber paper, and silicon carbide fiber paper stacked together. The thickness of a single layer of aerogel / fiber composite paper is 0.2~1.0 mm.

4. The high-temperature resistant flexible heat-insulating skin according to claim 1, characterized in that, The load-bearing layer comprises any one or more stacks of fiber cloth and polymer / fiber composite cloth; The fiber cloth is any one or more of the following: aramid fiber cloth, polyimide fiber cloth, poly(p-phenylenebenzodioxazole) fiber cloth, poly[2,5-dihydroxy-1,4-phenylenepyridinium diimidazole] fiber cloth, carbon fiber cloth, glass fiber cloth, high silica fiber cloth, and quartz fiber cloth; wherein, the thickness of a single layer of fiber cloth is 0.1~0.3mm. The polymer used in the polymer / fiber composite fabric is any one or more of dimethyl silicone rubber, methyl vinyl silicone rubber, methyl phenyl vinyl silicone rubber, fluorosilicone rubber, nitrile silicone rubber, phenylene silicone rubber, phenyl ether silicone rubber, fluororubber, perfluoroether rubber, and polytetrafluoroethylene. The fiber material used in the polymer / fiber composite fabric is any one or more of aramid fiber cloth, polyimide fiber cloth, poly(p-phenylenebenzodioxazole) fiber cloth, poly[2,5-dihydroxy-1,4-phenylenepyridinium diimidazole] fiber cloth, carbon fiber cloth, glass fiber cloth, high silica fiber cloth, and quartz fiber cloth stacked together. The thickness of a single layer of polymer / fiber composite fabric is 0.15~0.5mm.

5. A high-temperature resistant flexible heat-insulating skin according to claim 2 or 4, characterized in that, The weaving method of the single-layer material in the heat-insulating layer and the load-bearing layer is any one of plain weave, twill weave, or satin weave.

6. The high-temperature resistant flexible heat-insulating skin according to claim 1, characterized in that, Different functional layers are connected to each other and to the layers within each functional layer by fiber optics or organic adhesives; The fiber thread is any one or more of carbon fiber thread, glass fiber thread, basalt fiber thread, high silica fiber thread, quartz fiber thread, mullite fiber thread, alumina fiber thread, and silicon carbide fiber thread; wherein, the linear density of a single fiber thread is 100~1200 tex, and the twist is 40~300 T / m. The organic adhesive is any one or more of silicone, epoxy resin, and acrylic adhesive.

7. A method for preparing a high-temperature resistant flexible heat-insulating skin, characterized in that, The method for preparing the high-temperature resistant flexible heat-insulating skin according to any one of claims 1-6 includes: (1) Determine the type, thickness, number of layers and arrangement order of materials used in each functional layer based on the service environment and the comprehensive performance of the materials themselves; (2) Cut the materials used in each functional layer into specific shapes as needed; (3) Lay the materials for each functional layer from bottom to top in a pre-designed order; (4) Determine the suturing method, stitches, and stitch length based on the size of the skin and the requirements for flexibility and strength; (5) Use fiber thread to sew together the internal layers of the heat-insulating layer and the heat insulation layer with higher temperature according to the pre-designed stitch pattern, stitch and stitch distance; (6) Use organic adhesive to bond the unstitched insulation layer and the insulation layer to the load-bearing layer.

8. The preparation method according to claim 7, characterized in that, When using fiber sutures for stitching, at least one layer of insulation should be left unbroken by the fiber sutures to prevent the formation of a rapid heat conduction channel that reaches the load-bearing layer.

9. The preparation method according to claim 7, characterized in that, Before bonding with organic adhesives, treat the surfaces to be bonded with silane coupling agents or plasma to improve the bonding strength.

10. The preparation method according to claim 9, characterized in that, The silane coupling agent is any one or more of KH550, KH560, KH570, and VTPS; The plasma gas composition is any one or more of helium, argon, air, nitrogen, oxygen, hydrogen, ammonia, and carbon dioxide.

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