Anisotropic ablation-resistant thermal insulation material, preparation method and application

Abstract

The application discloses anisotropic ablation-resistant thermal insulation material, a preparation method and application, and comprises the following raw material components in parts by weight: 100 parts of base rubber, 20-50 parts of ablation-resistant filler, 5-10 parts of organic fiber, 5-10 parts of inorganic fiber and 1-5 parts of vulcanization aid. The anisotropic ablation-resistant thermal insulation material has better ablation performance, shorter preparation period, lower cost, higher interface bonding reliability, an oxyacetylene wire ablation rate of 0.001-0.005 mm / s and a mass ablation rate of 0.03-0.06 g / s, and when used as a thermal insulation layer of an engine shell, can effectively protect the engine shell during engine operation. The method realizes the preparation of the multilayer thermal insulation material through continuous layered co-extrusion, layering and superposition, calendering and shaping, cutting and mould pressing, wherein the layering and superposition has shearing, stretching and compressing effects on the rubber compound, promotes the orientation of the fibers in the rubber compound, the layers of the finally prepared anisotropic ablation-resistant thermal insulation material are well adhered to each other, and defects are not easily formed in the interlayer interface.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of rubber materials, and particularly relates to an anisotropic ablation-resistant thermal insulation material, a preparation method and application. BACKGROUND

[0002] Missile weapons develop towards high speed, long range and high mobility. When the missile is flying at high speed and high mobility, the solid rocket engine will generate certain amount of radial and axial overload. Under the overload condition, the trajectory of high-temperature gas and solid particles changes, and a high-temperature and high-speed solid particle gathering area is formed in the local combustion chamber, which aggravates the thermal chemical ablation and mechanical erosion of the insulation material in the engine combustion chamber, causes the failure of the thermal protection structure, and further leads to the failure of the engine flight. At present, the method for solving the long-time overload ablation of the engine combustion chamber is to increase the thickness of the insulation layer in the ablation severe area, or to apply continuous fiber reinforced rubber composite materials, fiber reinforced hard resin composite materials and other anti-erosion materials. However, increasing the thickness of the insulation layer will increase the negative mass of the engine, which is not conducive to the range and mobility of the engine. The manufacturing cost of the fiber reinforced rubber or resin-based composite material is high, the cycle is long, the forming process is complex, and there are problems of low interfacial bonding strength and poor interfacial deformation matching, which is difficult to adapt to the development trend of high performance, high reliability and low cost of the solid rocket engine.

[0003] In summary, it is urgent to develop an ablation-resistant and erosion-resistant insulation layer with simple manufacturing process, excellent interfacial performance and low cost. SUMMARY

[0004] In view of the above defects and deficiencies in the prior art, the application provides an anisotropic ablation-resistant thermal insulation material, a preparation method and application, to solve the technical problems of high manufacturing cost, long cycle and complex forming process of the thermal insulation material for the engine combustion chamber in the prior art.

[0005] In order to achieve the above-mentioned purpose, the application adopts the following technical solutions:

[0006] An anisotropic ablation-resistant thermal insulation material, by weight, comprises the following raw material components: 95-110 parts of base rubber, 20-50 parts of ablation-resistant filler, 5-10 parts of organic fiber, 5-10 parts of inorganic fiber and 1-5 parts of vulcanization aid.

[0007] The application also has the following technical features:

[0008] Specifically, the base rubber is selected from one or more of silicone rubber, ethylene propylene diene rubber and nitrile rubber.

[0009] Further, the ablation-resistant filler is selected from one or more of boron phenolic resin, zirconium boride and white carbon black.

[0010] Further, the organic fiber is selected from one or more of aramid fiber, polybenzoxazole fiber and acrylonitrile fiber; the inorganic fiber is selected from one or more of carbon fiber, mullite fiber and high silica fiber; and the vulcanization aid is sulfur or dicumyl peroxide.

[0011] Further, the anisotropic ablative thermal insulation material has a width of 50mm-2800mm, a thickness of 1mm-30mm, an oxyacetylene line ablation rate of 0.001-0.005mm / s and a mass ablation rate of 0.03-0.06g / s.

[0012] The application also protects a preparation method of the anisotropic ablative thermal insulation material, comprising the following steps:

[0013] Step 1: adding a formula amount of base rubber, ablative filler, organic fiber, inorganic fiber and vulcanizing agent into a double-roll open mill to perform normal temperature mixing to obtain a mixed rubber;

[0014] Step 2: sending the mixed rubber into a co-extrusion system to be uniformly plasticized and then extruded into a flow combiner provided with at least two flow channels to be converged to obtain a multi-layer composite rubber;

[0015] Step 3: the multi-layer composite material is cut and divided and laminated by a layer multiplier connected with the flow combiner, and then is widened and compacted by an extruder head die connected with the layer multiplier to obtain a multi-layer structure rubber;

[0016] Step 4: cutting the multi-layer structure rubber obtained in Step 3 along the thickness direction at a set cutting angle and cutting interval distance to obtain a multi-layer structure cutting rubber; placing a plurality of multi-layer structure cutting rubbers with cutting surfaces upward in parallel in a mold, and performing pre-vulcanization treatment by using a flat vulcanization machine to obtain a preformed rubber; and sequentially performing cutting, shaping and vulcanization mold pressing of the preformed rubber to obtain the anisotropic ablative thermal insulation material.

[0017] In Step 1, the base rubber, the ablative filler, the organic fiber, the inorganic fiber and the vulcanization aid are 95-110 parts, 20-50 parts, 5-10 parts, 5-10 parts and 1-5 parts by weight, respectively.

[0018] Further, in Step 4, the set cutting angle is 0-45°, and the cutting interval distance is 1-30mm.

[0019] Further, in Step 4, the temperature of the pressurized vulcanization treatment is 120-150℃, and the pressure is 1-10MPa.

[0020] The application also protects the use of the anisotropic ablation-resistant thermal insulation material as an engine shell thermal insulation layer, or the use of the anisotropic ablation-resistant thermal insulation material prepared by the preparation method of the anisotropic ablation-resistant thermal insulation material as an engine shell thermal insulation layer.

[0021] The application also protects an engine shell, which is provided with an anisotropic ablation-resistant thermal insulation layer formed by the anisotropic ablation-resistant thermal insulation material described above on the inner wall of the engine shell, or an anisotropic ablation-resistant thermal insulation layer formed by the anisotropic ablation-resistant thermal insulation material prepared by the preparation method of the anisotropic ablation-resistant thermal insulation material; the anisotropic ablation-resistant thermal insulation material is formed on the inner wall of the engine shell through a preforming-bag vulcanization process, the thickness of the thermal insulation layer is 1mm-30mm; the pre-vulcanization process parameters include a temperature of 80-100℃ and a pressure of 10-12MPa; the bag mold vulcanization process parameters include a temperature of 140-150℃ and a pressure of 0.6-0.8MPa.

[0022] Compared with the prior art, the application has the following beneficial effects:

[0023] (1) The anisotropic ablation-resistant thermal insulation material provided by the application has better ablation performance, shorter preparation period, lower cost, higher interface bonding reliability, an oxyacetylene wire ablation rate of 0.001-0.005mm / s, a difference between the radial thermal conductivity coefficient and the axial thermal conductivity coefficient of 0.04-0.08W / m·k, and a mass ablation rate of 0.03-0.06g / s, and can be used as an engine shell thermal insulation layer to effectively protect the engine shell when the engine is working.

[0024] (2) The method realizes the preparation of the multilayer thermal insulation material through continuous layered co-extrusion, layered lamination, calendering, cutting and molding, wherein the layered lamination has shearing, stretching and compressing effects on the rubber compound, promotes the orientation of the fibers in the rubber compound, the layers of the anisotropic ablation-resistant thermal insulation material finally prepared are well adhered to each other, defects are not easily formed at the interlayer interface, and the anisotropic ablation-resistant thermal insulation material can be continuously prepared, and has the characteristics of high production efficiency, uniform material quality and short period.

[0025] (3) After the anisotropic ablation-resistant thermal insulation material provided by the application is used on the engine shell, the ablation-resistant impact capacity of the engine is enhanced, the service life is longer, and the working reliability is higher. BRIEF DESCRIPTION OF DRAWINGS

[0026] The accompanying drawings are included to provide a further understanding of the present disclosure and constitute a part of the specification, and together with the specific embodiments described below, serve to explain the present disclosure, but do not constitute a limitation on the present disclosure.

[0027] Figure 1A schematic structural diagram of the anisotropic ablation-resistant thermal insulation material provided by the present application, wherein a is an anisotropic thermal insulation material with an orientation angle of 15 °C, and b is an anisotropic thermal insulation material with an orientation angle of 0 °.

[0028] Figure 2 A carbonized layer structure after ablation of the anisotropic ablation-resistant thermal insulation material prepared for Example 2;

[0029] Figure 3 A carbonized layer structure after ablation of the thermal insulation material prepared for Comparative Example 1.

[0030] The technical solutions of the present application will be further described below in combination with examples. DETAILED DESCRIPTION

[0031] The technical solutions in the embodiments of the present application will be clearly and completely described below. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, any other embodiments obtained by any person of ordinary skill in the art belong to the scope of protection of the present application.

[0032] The technical concept of the present application is that, considering that the ablation environments faced by different positions of the engine thermal insulation layer are different, an obviously anisotropic thermal insulation layer is prepared through component selection and preparation method design, so as to maximize the utilization of the performance of the thermal insulation layer, thereby reducing the negative mass of the engine, specifically including: adjusting the number of layers of the cutting gum under the same thickness through changing the number of layer multipliers, so as to adjust the orientation degree of the fiber material in the single-layer structure; and adjusting the cutting angle and the laying mode, so as to control the thermal conductivity performance of the thermal insulation layer in different directions.

[0033] The present application provides an anisotropic ablation-resistant thermal insulation material, wherein the base rubber is 95-110 parts by weight, the ablation-resistant filler is 20-50 parts by weight, the organic fiber is 5-10 parts by weight, the inorganic fiber is 5-10 parts by weight, and the vulcanization aid is 1-5 parts by weight.

[0034] As a preference, the base rubber is selected from one or more of silicone rubber, ethylene-propylene-diene rubber, and nitrile rubber.

[0035] As a preference, the ablation-resistant filler is selected from one or more of boron phenolic resin, zirconium boride, and white carbon black.

[0036] As a preference, the organic fiber is selected from one or more of aramid fiber, polybenzoxazole fiber, and acrylonitrile fiber; the inorganic fiber is selected from one or more of carbon fiber, mullite fiber, and high-silica fiber; and the vulcanization aid is sulfur or dicumyl peroxide.

[0037] Preferably, the anisotropic ablation-resistant thermal insulation material has a width of 50-2800 mm, a thickness of 1-30 mm, an oxyacetylene line ablation rate of 0.001-0.005 mm / s, and a mass ablation rate of 0.03-0.06 g / s.

[0038] The application also protects a preparation method of the anisotropic ablation-resistant thermal insulation material, comprising the following steps:

[0039] Step 1: adding a formula amount of base rubber, ablation-resistant filler, organic fiber, inorganic fiber and vulcanizing agent into a double-roller open mill to perform normal-temperature mixing, to obtain a mixed rubber;

[0040] Preferably, the base rubber, the ablation-resistant filler, the organic fiber, the inorganic fiber and the vulcanizing aid are in a weight ratio of 95-110:20-50:5-10:5-10:1-5.

[0041] Step 2: sending the mixed rubber into a co-extrusion system to be uniformly plasticized, and then extruding the mixed rubber into a flow combiner provided with at least two flow channels to be laminated, to obtain a multi-layer composite rubber;

[0042] Step 3: cutting and laminating the multi-layer composite material through a layer multiplier connected to the flow combiner, and then widening and compacting the multi-layer composite material through an extruder head die connected to the layer multiplier, to obtain a multi-layer structure rubber;

[0043] Step 4: cutting the multi-layer structure rubber obtained in Step 3 along the thickness direction at a set cutting angle and cutting interval distance, to obtain a multi-layer structure cutting rubber; placing a plurality of the multi-layer structure cutting rubbers with the cutting surfaces upward in a mold, and performing pre-vulcanization treatment on the multi-layer structure cutting rubbers by using a flat vulcanization machine, to obtain a preformed rubber; and sequentially performing cutting, shaping and vulcanization molding on the preformed rubber, to obtain the anisotropic ablation-resistant thermal insulation material.

[0044] Preferably, the set cutting angle is 0-45°, and the cutting interval distance is 1-30 mm.

[0045] Preferably, the temperature of the pressurized vulcanization treatment is 120-150℃, and the pressure is 1-10 MPa.

[0046] Unless otherwise specified, the raw materials used in the application are commercially available.

[0047] The extruder used in the application is commercially available, and the flow combiner, the layer multiplier and the forming die are all existing devices. The co-extrusion system formed by the above devices can realize the one-time completion of rubber sheet pressing, layering and widening and compacting. The cutting is automatically and continuously performed on the rubber sheet along the thickness direction by using a cutting machine.

[0048] The oxygen-ethyne line ablation rate test is performed according to the standard GJB 323B-2018, the oxygen-ethyne line ablation rate and the mass ablation rate are calculated according to the standard, and the thermal conductivity test is performed according to ISO22007-2: Determination of the thermal conductivity and thermal diffusivity of plastics - Part 2: Transient plane heat source (hot disc) method. The scanning electron microscope image is tested by using an S4800 type scanning electron microscope of Japan Hitachi Company.

[0049] Embodiment 1

[0050] According to the above technical solution, as shown in Figure 1 , the embodiment provides an anisotropic ablation-resistant thermal insulation material, which is prepared by the following method:

[0051] Step 1, according to the weight fraction, 100 parts of EPDM rubber as the base rubber, 10 parts of white carbon black, 15 parts of boron phenolic resin, 7 parts of aramid fiber, 10 parts of carbon fiber and 5 parts of sulfur are added to a two-roll open mill for normal temperature mixing for 15 minutes to obtain a mixed rubber;

[0052] Step 2, the mixed rubber is divided into two parts, and then added into a co-extrusion system to be extruded into a flow collector provided with two flow channels to obtain a double-layer composite rubber;

[0053] Step 3, the double-layer composite rubber is cut and divided by a layer multiplier connected to the flow collector, and then widened and compacted in an extruder head die connected to the multi-layer multiplier to obtain a 4-layer structure rubber;

[0054] Step 4, the 4-layer structure rubber is cut along the thickness direction at a set cutting angle and cutting interval distance to obtain a plurality of 4-layer structure cutting rubbers; wherein the cutting angle is 0°, and the cutting interval distance is 10 mm; the plurality of 4-layer structure cutting rubbers are placed in a flat plate mold in turn with the cutting surface upward, and are molded by a flat plate vulcanizing machine at 150°C and 10MPa for 30 minutes to obtain a product.

[0055] The anisotropic ablation-resistant thermal insulation material prepared in this embodiment has a thickness of 10 mm, and the structure is as shown in Figure 1 b, and the width can be adjusted by cutting.

[0056] The ablation-resistant thermal insulation material prepared in this embodiment is subjected to performance detection, and the results are as follows: the oxygen-ethyne line ablation rate is 0.005 mm / s, the mass ablation rate is 0.06 g / s, the radial thermal conductivity is 0.26 W / m·k, the axial thermal conductivity is 0.22 W / m·k, and there is a significant difference between the radial thermal conductivity and the axial thermal conductivity, which proves the anisotropy of the internal structure of the ablation-resistant thermal insulation material prepared in this embodiment.

[0057] The anisotropic ablation-resistant thermal insulation material provided by the embodiment can be used to prepare an engine shell thermal insulation layer, and specifically comprises the following steps: according to the ablation distribution inside the engine combustion chamber, converging section thermal insulation layer components and head section components are obtained by using the anisotropic thermal insulation material through a pre-sulfurization process and a mold forming process, the processing temperature is 90 ℃, and the pressure is 10 MPa; then the converging section thermal insulation layer components, the head section components and a cylindrical section thermal insulation layer are formed on the inner wall of the engine shell by means of a gas bag vulcanization process, the forming process parameters comprise a forming temperature of 150 ℃ and a forming pressure of 0.8 MPa; and finally a thermal insulation layer with a thickness of 2 mm to 20 mm is formed on the engine shell, and the thickness can be adjusted as needed.

[0058] Engine test:

[0059] The anisotropic thermal insulation layer of the engine shell provided by the embodiment is subjected to an engine ground test, and the residual shell is complete.

[0060] Embodiment 2

[0061] According to the above technical solution, an anisotropic ablation-resistant thermal insulation material is provided, the preparation raw materials and the preparation method are basically the same as those of embodiment 1, and the only difference is that after being converged into 2 layers of composite rubber in the current collector, the 2 layers of composite rubber are cut and divided by 2 layer multipliers and laminated to obtain an 8-layer structure extrudate, and then an 8-layer structure rubber is obtained; the obtained 8-layer structure rubber is cut along the thickness direction at a cutting angle of 15° and a cutting interval distance of 10 mm, and then the cutting surface of the 8-layer structure rubber is placed in a mold in parallel for pre-sulfurization treatment, and a flat vulcanizing machine is used for pressing at 150 ℃ and 10 MPa for 30 minutes.

[0062] The thickness of the anisotropic ablation-resistant thermal insulation material prepared in the embodiment is 10 mm, and the structure is as shown in Figure 1 a, and the width of the cutting can be adjusted.

[0063] The SEM image of the anisotropic ablation-resistant thermal insulation material prepared in the embodiment is as shown in Figure 1 From the figure, it can be seen that after the ablation experiment, there is an obvious parallel strip skeleton structure in the carbonized layer of the anisotropic thermal insulation material, which indicates that the fiber is carbonized to form a skeleton structure under high temperature conditions.

[0064] The ablation-resistant thermal insulation material prepared in the embodiment is subjected to performance detection, and the results are as follows: the oxyacetylene line ablation rate is 0.001 mm / s, the mass ablation rate is 0.03 g / s, the radial thermal conductivity coefficient of the material is 0.31 W / m·k, the axial thermal conductivity coefficient is 0.24 W / m·k, and there is a significant difference between the radial thermal conductivity coefficient and the axial thermal conductivity coefficient, which proves the anisotropy of the internal structure of the ablation-resistant thermal insulation material prepared in the embodiment.

[0065] The anisotropic ablation-resistant thermal insulation material provided by the embodiment can be used to prepare an engine shell thermal insulation layer, and the use mode is the same as that of the embodiment 1. After the engine ground test, the residual shell is intact.

[0066] Comparative Example 1

[0067] The comparative example provides a thermal insulation material, the preparation raw materials and steps 1 to 4 of the preparation method are the same as those of the embodiment 1, and the only difference is that the 4-layer structural adhesive is not cut in step 4, but is directly placed in the mold, and then is subjected to the pressurized vulcanization treatment under the same conditions as those of the embodiment 1 to obtain the thermal insulation material.

[0068] The thickness of the anisotropic ablation-resistant thermal insulation material prepared in the comparative example is 10 mm.

[0069] The thermal insulation material prepared in the comparative example is subjected to performance detection by using the detection method used in the embodiment 1, and the detection result is that the oxyacetylene linear ablation rate is 0.14 mm / s, the mass ablation rate is 0.1 g / s, the radial thermal conductivity of the material is 0.21 W / m·k, and the axial thermal conductivity is 0.26 W / m·k.

[0070] It can be seen from the embodiment 1, the embodiment 2 and the comparative example 1 that the radial thermal conductivity and the axial thermal conductivity of the anisotropic ablation-resistant thermal insulation material prepared in the embodiment 1, the embodiment 2 and the comparative example 1 are obviously different, which is caused by the different orientation directions of the ablation-resistant functional filler fibers in the material.

[0071] However, the radial thermal conductivity of the material prepared in the embodiment 1 and the embodiment 2 is obviously higher than that of the material prepared in the comparative example 1, which indicates that the radial orientation of the fibers and other ablation-resistant fillers in the embodiments is more obvious, which is beneficial to the formation of a continuous and dense structure of the carbonized layer in the radial direction in the ablation process, so as to more effectively resist the erosion in the direction of the heat flow, and indicates that the cutting and paving operation in the embodiment 1 significantly changes the anisotropic performance of the material.

[0072] Comparative Example 2

[0073] The comparative example provides a thermal insulation material, the preparation raw materials and step 1 of the preparation method are the same as those of the embodiment 2, and then the obtained rubber compound is directly placed in the mold, and is subjected to the pressurized vulcanization treatment under the same conditions as those of the embodiment 2 to obtain an isotropic thermal insulation material.

[0074] The thickness of the anisotropic ablation-resistant thermal insulation material prepared in the comparative example is 10 mm.

[0075] The adiabatic material prepared in the present comparative example was subjected to performance detection by using the detection method used in Example 1, and the detection results were as follows: the oxyacetylene line ablation rate was 0.09 mm / s, the mass ablation rate was 0.08 g / s, and the thermal conductivities in the radial and axial directions were 0.25 W / m·k and 0.26 W / m·k, respectively, and the thermal conductivities in different directions were similar.

[0076] It can be seen from Example 1, Example 2 and Comparative Example 2 that:

[0077] The materials prepared in Example 1 and Example 2 have more significant differences in the radial thermal conductivity and the axial thermal conductivity, while the material prepared in Comparative Example 2 has similar radial thermal conductivity and axial thermal conductivity, indicating that, compared with the traditional mixing process, the ablation-resistant adiabatic material prepared by the orientation treatment and anisotropy design of the adiabatic material in the present application has more obvious anisotropy, and finally the ablation performance is obviously improved.

[0078] It can be seen from Example 1, Example 2 and Comparative Example 2 that: Figure 2 and Figure 3 It can also be seen that the carbonized layer structure formed by the material prepared in Example 2 after the ablation test has good structural integrity and a dense overall structure, while the carbonized layer structure formed by the material prepared in Comparative Example 2 after ablation has obvious continuous holes and other defects, resulting in a significant decrease in the strength of the carbonized layer, which is not conducive to resisting the impact of heat flow.

[0079] Comparative Example 3

[0080] The present comparative example provides an adiabatic material, which has the same raw materials as Example 2. After the rubber compound is prepared, the adiabatic material is not subjected to lamination by using a co-extrusion system, but is subjected to lamination by using a manual layering method, and then the compound is pressed into a composite rubber material with the same thickness as Example 2 by using a two-roll open mill. Then, the composite rubber material is subjected to cutting, laying and press vulcanization under the same conditions as Example 2, and the adiabatic material is obtained.

[0081] The anisotropic ablation-resistant adiabatic material prepared in the present comparative example has a thickness of 10 mm.

[0082] The adiabatic material prepared in the present comparative example was subjected to performance detection by using the detection method used in Example 1, and the detection results were as follows: the oxyacetylene line ablation rate was 0.07 mm / s, the mass ablation rate was 0.08 g / s, the axial thermal conductivity was 0.26 W / m·k, and the radial thermal conductivity was 0.28 W / m·k.

[0083] It can be seen from Example 1, Example 2 and Comparative Example 3 that: the materials prepared in Example 1 and Example 2 have more significant differences in the radial thermal conductivity and the axial thermal conductivity, while the material prepared in Comparative Example 3 has similar radial thermal conductivity and axial thermal conductivity, indicating that the anisotropy of the material prepared by using the manual layering lamination method is not obvious.

[0084] The preferred embodiments of the present application are described in detail above with reference to the accompanying drawings, but the present application is not limited to the specific details of the above-described embodiments, and various simple modifications can be made to the technical solutions of the present application within the technical concept of the present application, and these simple modifications all belong to the protection scope of the present application.

[0085] In addition, various different embodiments of the present application can also be combined arbitrarily, as long as they do not deviate from the idea of the present application, and they should also be considered as disclosed by the present application.

Claims

1. A method for preparing anisotropic ablation-resistant thermal insulation material, characterized in that: The following steps are involved: Step 1: adding the base rubber, ablation-resistant filler, organic fiber, inorganic fiber and vulcanizing agent in the formulated amount to a two-roll mill and mixing them at room temperature to obtain a mixed rubber material; Step 2: feeding the mixed rubber material into a co-extrusion system and plasticizing the mixed rubber material uniformly, and then extruding the mixed rubber material into a manifold having at least two flow channels to obtain a multi-layer composite rubber material; Step 3: The multi-layer composite material is cut, split, and laminated through a layer multiplier connected to the flow combiner, and then widened and compacted through an extruder head mold connected to the layer multiplier to obtain a multi-layer structural rubber compound; Step 4: cutting the multilayer structured rubber material obtained in step 3 along the thickness direction at a set cutting angle and cutting interval to obtain a multilayer structured cut rubber material; placing the plurality of multilayer structured cut rubber materials side by side in a mold with the cut surfaces facing upward, and performing a pressure vulcanization treatment using a flat plate vulcanizer to obtain the obtained multilayer structured cut rubber material; In the step 1, the following are prepared, by weight: 95-110 parts of base rubber, 20-50 parts of ablation-resistant filler, 5-10 parts of organic fiber, 5-10 parts of inorganic fiber and 1-5 parts of vulcanization aid.

2. The method for preparing the anisotropic ablation-resistant thermal insulation material according to claim 1, wherein: The base rubber is selected from one or more of silicone rubber, EPDM rubber and nitrile rubber.

3. The method for preparing anisotropic ablation-resistant thermal insulation material according to claim 1, characterized in that: The ablation-resistant filler is selected from one or more of boron phenolic resin, zirconium boride, and white carbon black.

4. The method for preparing anisotropic ablation-resistant thermal insulation material according to claim 1, wherein: The organic fiber is selected from one or more of aramid fiber, polybenzoxazole fiber and acrylonitrile fiber; the inorganic fiber is selected from one or more of carbon fiber, mullite fiber and high silica fiber; the vulcanization auxiliary agent is sulfur or dicumyl peroxide.

5. The method for preparing anisotropic ablation-resistant thermal insulation material according to claim 1, wherein: The anisotropic ablation-resistant thermal insulation material has a width of 50 mm to 2800 mm, a thickness of 1 mm to 30 mm, an oxyacetylene wire ablation rate of 0.001 to 0.005 mm / s, and a mass ablation rate of 0.03 to 0.06 g / s.

6. The method for preparing anisotropic ablation-resistant thermal insulation material according to claim 1, wherein: In step 4, the cutting angle is set to 0-45°, and the cutting interval is set to 1-30 mm.

7. The method for preparing anisotropic ablation-resistant thermal insulation material according to claim 1, wherein: In step 4, the temperature of the pressurized vulcanization treatment is 120-150° C., and the pressure is 1-10 MPa.

8. Use of the anisotropic ablation-resistant thermal insulation material prepared by the preparation method of the anisotropic ablation-resistant thermal insulation material according to any one of claims 1 to 7 as a thermal insulation layer of an engine casing.

9. An engine housing, characterized in that: An insulating layer formed by an anisotropic ablation-resistant insulating material prepared by the preparation method of an anisotropic ablation-resistant insulating material according to any one of claims 1 to 7; the anisotropic ablation-resistant insulating material is molded onto the inner wall of an engine casing using a pre-vulcanization-airbag molding vulcanization process, and the thickness of the insulating layer is 1 mm to 30 mm; the pre-vulcanization process parameters include a temperature of 80 to 100°C and a pressure of 10 to 12 MPa; the airbag molding vulcanization process parameters include a temperature of 140 to 150°C and a pressure of 0.6 to 0.8 MPa.

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