Resin-based high-energy laser protection composite coating and preparation method thereof

Abstract

The application discloses a resin-based high-energy laser protection composite coating and a preparation method thereof. The resin-based high-energy laser protection composite coating comprises a three-layer structure, and a porous heat insulation layer, a heat dissipation layer and an ablation layer are sequentially arranged on the surface of a base body from bottom to top. The porous heat insulation layer comprises a high-temperature-resistant resin binder and hollow microspheres. The heat dissipation layer comprises a high-temperature-resistant resin binder and a heat-conducting material. The ablation layer comprises a high-temperature-resistant resin binder, a high-melting-point carbide ceramic powder, a low-melting-point carbide ceramic powder and a short-cut fiber powder. The preparation method is simple and easy to implement and has low cost. The ablation, heat dissipation and heat insulation effects of different functional layers are used to achieve the purpose of protecting the base body material. The prepared composite coating has excellent laser protection performance and can be applied to a high-energy laser irradiation environment.

Description

Technical Field

[0001] The present invention belongs to the technical field of laser protective coatings, and in particular relates to a resin-based high-energy laser protective composite coating and a preparation method thereof. Background Art

[0002] The rapid development of laser technology has significantly increased laser power, leading to the emergence of highly destructive high-energy lasers. High-energy lasers can penetrate and damage traditional metals, ceramics, and resins within seconds, posing a serious threat to devices and equipment exposed to high-energy laser radiation. Therefore, protecting against the damaging effects of high-energy lasers has become a major challenge in the field of defense.

[0003] Applying a laser protective coating to the surface of a substrate is currently the primary means of combating damage from high-energy lasers. These coatings include reflective, ablative, and thermal-insulating types. Reflective coatings utilize high reflectivity to dissipate laser energy through reflection, reducing the material's absorption of laser energy and thereby improving the coating's resistance to laser damage. While these coatings offer excellent protection, their high reflectivity places high demands on the environment in which they are used. Scratches or oxidation can severely impact their performance. Ablative coatings utilize an endothermic ablation reaction to dissipate laser-deposited heat, thereby mitigating the ultra-high temperature fields caused by laser ablation. Thermal-insulating coatings utilize their low thermal conductivity to isolate the heat from the substrate, providing protection against laser ablation damage. Ablative and thermal-insulating coatings are less susceptible to environmental influences and are more suitable for practical applications. However, because these coatings absorb and convert extremely high laser energy, their protective properties are generally weak, making them less resistant to damage from large, high-performance lasers.

[0004] In summary, while current research has designed and produced a variety of laser-protective coatings, existing technologies all have drawbacks. While ablative or thermal-insulating coatings are more suitable for practical applications, their limited energy consumption mechanisms result in relatively weak laser protection. Therefore, further improving the laser-protective performance of coatings remains a challenging technical challenge requiring continued research. Summary of the Invention

[0005] The purpose of the present invention is to overcome the shortcomings of the existing technology and provide a resin-based high-energy laser protective composite coating and a preparation method thereof. Through the three effects of ablation, heat conduction and thermal insulation, it synergistically achieves protection against high-energy laser ablation damage, achieves the purpose of protecting the base material, and solves the problems existing in the laser protective coating in the above-mentioned background technology.

[0006] One of the technical solutions adopted by the present invention to solve its technical problems is: providing a resin-based high-energy laser protective composite coating, including a three-layer structure, with a porous thermal insulation layer, a heat conduction layer and an ablation layer distributed on the surface of the substrate from bottom to top; the porous thermal insulation layer includes a high-temperature resistant resin binder and hollow microspheres; the heat conduction layer includes a high-temperature resistant resin binder and a thermal conductive material; the ablation layer includes a high-temperature resistant resin binder, high-melting point carbide ceramic powder, low-melting point carbide ceramic powder and chopped fiber powder.

[0007] In a preferred embodiment of the present invention, the high temperature resistant resin binder is a thermosetting resin having a carbon residue rate greater than 50% at 900° C., including silicone resin, phenolic resin or boron-modified phenolic resin.

[0008] In a preferred embodiment of the present invention, the hollow microspheres are phenolic hollow microspheres, alumina hollow microspheres or mullite hollow microspheres with a diameter of 20-80 μm.

[0009] In a preferred embodiment of the present invention, the thermally conductive material is thermally conductive graphite powder with a diameter of 20-80 μm, flake graphite with a sheet diameter of 0.2-0.4 mm, or graphene with a sheet diameter of 5-10 μm.

[0010] In a preferred embodiment of the present invention, the particle size of the high melting point carbide ceramic powder and the low melting point carbide ceramic powder is 5-40 μm, the high melting point carbide ceramic powder is zirconium carbide or titanium carbide, and the low melting point carbide ceramic powder is silicon carbide.

[0011] In a preferred embodiment of the present invention, the chopped fiber powder is zirconia chopped fiber powder, chopped glass fiber powder or carbon fiber powder, and the fiber length is 5-80 μm.

[0012] In a preferred embodiment of the present invention, the thickness of the porous heat-insulating layer is 0.5-1 mm, the thickness of the heat-conducting layer is 0.2-0.6 mm, and the thickness of the ablation layer is 0.5-1 mm.

[0013] The second technical solution adopted by the present invention to solve the technical problem is: providing a method for preparing a resin-based high-energy laser protective composite coating, comprising the following steps:

[0014] Step 1. Substrate surface pretreatment;

[0015] Step 2. Adding a silane coupling agent and hollow microspheres to a high-temperature resistant resin binder, uniformly dispersing the mixture to obtain a porous thermal insulation layer coating slurry, applying the porous thermal insulation layer coating slurry to the substrate surface, and pre-curing the mixture to obtain a pre-cured porous thermal insulation layer; the porous thermal insulation layer coating slurry is composed of 80% to 85% of a high-temperature resistant resin binder, 1% to 2% of a silane coupling agent, and 14% to 18% of hollow microspheres by mass;

[0016] Step 3. Adding a silane coupling agent and a thermally conductive material to a high-temperature resistant resin binder, uniformly dispersing the mixture to obtain a thermally conductive layer coating slurry, applying the thermally conductive layer coating slurry to the surface of the precured porous thermal insulation layer, and precuring the precured thermally conductive layer; the thermally conductive layer coating slurry comprises, by mass, 90% to 93% of a high-temperature resistant resin binder, 1% to 2% of a silane coupling agent, and 6% to 8% of a thermally conductive material;

[0017] Step 4. Adding a silane coupling agent, chopped fiber powder, high melting point carbide ceramic powder, and low melting point carbide ceramic powder to a high temperature resistant resin binder, uniformly dispersing the mixture to obtain an ablation layer coating slurry, applying the ablation layer coating slurry to the surface of the pre-cured heat conduction layer, and pre-curing the mixture to obtain a pre-cured ablation layer; the ablation layer coating slurry comprises, by mass, 30% to 40% of a high temperature resistant resin binder, 1% to 2% of a silane coupling agent, 50% to 60% of a high melting point carbide ceramic powder, 8% to 10% of a low melting point carbide ceramic powder, and 1% to 2% of a chopped fiber powder;

[0018] Step 5. After the pre-cured coating obtained in step 4 is heat-cured, a resin-based laser protection composite coating can be obtained.

[0019] In a preferred embodiment of the present invention, the substrate is a metal substrate or a resin-based composite substrate; the method for pretreating the substrate surface includes cleaning the surface of the substrate, removing dust and oil impurities attached to the surface of the substrate, and performing a roughening treatment; the roughening treatment is to use 400-800 mesh sandpaper to uniformly polish the substrate surface.

[0020] In a preferred embodiment of the present invention, in step 2 and step 3, the uniform dispersion method is to use a high-speed stirring disperser with a rotation speed of 500-1000 r / min to stir for 20-40 minutes, and then use a homogenizer with a rotation speed of 1500-2000 r / min to homogenize for 2-4 minutes.

[0021] In a preferred embodiment of the present invention, in step 4, the uniform dispersion method includes:

[0022] ① Add silane coupling agent and chopped fiber powder to high temperature resistant resin binder, and ultrasonically disperse for 10-15 minutes in an ice bath at an ultrasonic frequency of 20-30kHz to obtain chopped fiber powder dispersion slurry;

[0023] ② Add high melting point carbide ceramic powder and low melting point carbide ceramic powder to the chopped fiber powder dispersion slurry, and use a high-speed stirring disperser with a speed of 200-500r / min to stir for 5-10min, then ultrasonically disperse in an ice bath at an ultrasonic frequency of 20-30kHz for 10-15min, and finally homogenize with a homogenizer at a speed of 1500-2000r / min for 2-4min.

[0024] In a preferred embodiment of the present invention, in steps 2-4, the coating method is knife coating using a coating machine, and the coating rate is 20-40 mm / s.

[0025] In a preferred embodiment of the present invention, in steps 2-4, the pre-curing method is to place the applied coating in a forced air oven, set the temperature to 50-70° C., and keep the temperature for 5-10 hours.

[0026] In a preferred embodiment of the present invention, in step 5, the heat preservation and curing process is firstly to keep the temperature at 80-90°C for 5-7 hours, then to keep the temperature at 100-120°C for 5-7 hours, and finally to keep the temperature at 130-150°C for 5-7 hours.

[0027] Compared with the background technology, this technical solution has the following advantages:

[0028] 1. The present invention significantly improves the laser ablation resistance of the resin-based coating through the synergistic cooperation of the ablation heat consumption, point heat source guidance and heat insulation effects of different functional layers;

[0029] ① The outermost layer of the coating is the ablation layer, which can consume the heat of laser deposition through ablation reaction. The filling of high-melting-point carbides can effectively improve the anti-penetration ability of the ablation layer under high-energy laser ablation conditions. The filling of low-melting-point carbides, whose oxidation product silicon oxide, can melt into a high-viscosity glassy state at high temperature, seal cracks and holes, and improve the density of the coating during the ablation process.

[0030] ② The middle layer of the coating is a heat conduction layer. It can effectively conduct the laser-deposited heat to the periphery of the ablation area through its high thermal conductivity, targeting the characteristics of the laser localized point heat source, thereby alleviating the ultra-high temperature in the ablation area.

[0031] ③The bottom layer of the coating is a heat-insulating layer, which can effectively isolate the conduction of heat to the base material through the low thermal conductivity of the porous microspheres, thereby reducing the base temperature.

[0032] 2. The preparation method of the composite coating of the present invention is simple and has high production efficiency. The prepared composite coating can be used in an environment exposed to high-energy laser irradiation and has good industrial applicability. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1This is a cross-sectional morphology of the resin-based high-energy laser protective composite coating prepared in Example 1.

[0034] Figure 2 The resin-based high-energy laser protection composite coating prepared in Example 1 was subjected to a power density of 1000 W / cm 2 Macroscopic morphology after 30s of laser (beam spot size 10×10mm) irradiation.

[0035] Figure 3 The resin-based high-energy laser protection composite coating prepared in Example 1 was subjected to a power density of 1000 W / cm 2 Macroscopic morphology of the back surface of the aluminum alloy substrate after irradiation with laser (beam spot size 10×10mm) for 30s.

[0036] Figure 4 The resin-based high-energy laser protection composite coating prepared in Example 1 was subjected to a power density of 1000 W / cm 2 Temperature curve of the back surface of the coating during 30s of laser irradiation (beam spot size 10×10mm). DETAILED DESCRIPTION

[0037] The present invention will be further described below with reference to specific embodiments. It should be noted that the terms "upper" and "lower" are merely for the purpose of facilitating and simplifying the description of the present invention, and are not intended to indicate or imply that the coatings referred to must have a specific orientation, be constructed, or operate in a specific orientation. Therefore, they should not be construed as limiting the present invention.

[0038] In the following embodiments:

[0039]

[0040]

[0041] Example 1

[0042] The preparation method of the resin-based high-energy laser protection composite coating described in this embodiment is as follows: on the surface of an aluminum alloy substrate, a porous thermal insulation layer, a heat-conducting layer and an ablation layer are prepared in sequence, and the components and their mass fractions of the porous thermal insulation layer are as follows: 85% silicone resin, 1% silane coupling agent, and 14% phenolic hollow microspheres (diameter 50μm); the components and their mass fractions of the heat-conducting layer are as follows: 93% silicone resin, 1% silane coupling agent, and 6% thermal conductive graphite powder (diameter 40μm); the components and their mass fractions of the ablation layer are as follows: 30% silicone resin, 1% silane coupling agent, 60% zirconium carbide (particle size 18μm), 8% silicon carbide (particle size 5μm), and 1% zirconium oxide chopped fiber powder (length 10μm).

[0043] The specific steps include:

[0044] Step 1. Use 400 grit sandpaper to polish the surface of the aluminum alloy substrate;

[0045] Step 2. Add 1g of silane coupling agent and 14g of phenolic hollow microspheres to 85g of silicone resin, stir for 20min using a high-speed stirring disperser (speed 1000r / min), and then homogenize with a homogenizer for 4min (speed 1500r / min) to obtain a porous insulation layer coating slurry, apply the coating slurry to the surface of the sandpaper-polished aluminum alloy substrate through a coater (coating rate 20mm / s, thickness set to 1mm), place in a blast oven at 50°C for 10h to obtain a pre-cured porous insulation layer.

[0046] Step 3. Add 1g of silane coupling agent and 6g of thermal conductive graphite powder to 93g of silicone resin, stir for 20min using a high-speed stirring disperser (speed 1000r / min), and then homogenize with a homogenizer for 4min (speed 1500r / min) to obtain a thermal conductive layer coating slurry, and apply the coating slurry to the surface of the pre-cured porous insulation layer through a coater (coating rate 20mm / s, thickness set to 0.6mm), put it into a blast oven and keep it warm at 50°C for 10h to obtain a pre-cured thermal conductive layer.

[0047] Step 4. Add 1g of silane coupling agent and 1g of zirconium oxide chopped fiber powder to 30g of silicone resin, ultrasonically disperse for 10min under ice bath conditions (ultrasonic frequency is 30kHz) to obtain a chopped fiber powder dispersion slurry, add 60g of zirconium carbide and 8g of silicon carbide to the chopped fiber powder dispersion slurry, and use a high-speed stirring disperser to stir for 5min (speed 500r / min), and then ultrasonically disperse for 10min under ice bath conditions (ultrasonic frequency is 30kHz), and finally homogenize with a homogenizer for 4min (speed 1500r / min) to obtain an ablation layer coating slurry, and apply the coating slurry to the surface of the pre-cured thermal conductive layer through a coater (coating rate 20mm / s, thickness set to 1mm), and place it in a blast oven at 50°C for 10h to obtain a pre-cured ablation layer.

[0048] Step 5. Place the coating obtained in step 4 into a blast oven, keep it warm at 90°C for 5 hours, keep it warm at 120°C for 5 hours, and keep it warm at 150°C for 5 hours to obtain a resin-based high-energy laser protection composite coating with a total thickness of 2.6 mm.

[0049] Figure 1This is a cross-sectional morphology of a resin-based high-energy laser protective composite coating. It can be seen that the coating has three functional layers: a porous thermal insulation layer, a heat conduction layer, and an ablation layer, distributed from bottom to top on the surface of the aluminum alloy substrate. The prepared resin-based high-energy laser protective composite coating was subjected to a high-energy laser irradiation experiment. When the laser power density was 1000W / cm 2 When the irradiation time is 30s, significant ablation occurs on the coating surface, and the area of ​​the ablation region is significantly larger than the laser beam spot size (10×10mm), which indicates that the coating effectively conducts the heat deposited by laser irradiation to the surrounding area. Figure 3 This is the macroscopic morphology of the back surface of the aluminum alloy substrate after the resin-based high-energy laser protective composite coating is irradiated by laser. It can be seen that there are no failure signs such as melting and breakdown on the surface of the substrate. Figure 4 It is the temperature rise curve of the back surface of the substrate during laser irradiation. It can be seen that during the laser irradiation process, the highest temperature of the substrate is only 198°C, which is far lower than the melting point of aluminum alloy, indicating that the resin-based high-energy laser protective composite coating has excellent laser protection performance.

[0050] Example 2

[0051] This embodiment provides a resin-based high-energy laser protection composite coating. A porous thermal insulation layer, a heat conduction layer, and an ablation layer are sequentially prepared on the surface of an aluminum alloy substrate. The components and their mass fractions for preparing the porous thermal insulation layer are as follows: 80% silicone resin, 2% silane coupling agent, and 18% phenolic hollow microspheres (20 μm diameter); the components and their mass fractions for preparing the heat conduction layer are as follows: 90% silicone resin, 2% silane coupling agent, and 8% flake graphite (0.27 mm diameter); and the components and their mass fractions for preparing the ablation layer are as follows: 40% silicone resin, 1% silane coupling agent, 50% titanium carbide (40 μm particle size), 8% silicon carbide (40 μm particle size), and 1% zirconia chopped fiber powder (20 μm length).

[0052] The preparation method of the resin-based high-energy laser protective composite coating described in this embodiment is as follows:

[0053] Step 1. Use 800-grit sandpaper to polish the surface of the resin-based composite material matrix;

[0054] Step 2. Add 2 g of silane coupling agent and 18 g of phenolic hollow microspheres to 80 g of silicone resin, stir for 40 min using a high-speed stirring disperser (speed 500 r / min), and then homogenize for 2 min (speed 2000 r / min) through a homogenizer to obtain a porous insulation layer coating slurry, and apply the coating slurry to the surface of the resin-based composite material substrate after sandpaper polishing using a coater (coating rate 40 mm / s, thickness set to 0.5 mm), place it in a blast oven and keep it warm at 70 ° C for 5 h to obtain a pre-cured porous insulation layer.

[0055] Step 3. Add 2g of silane coupling agent and 8g of thermal conductive graphite powder to 90g of silicone resin, stir for 40min using a high-speed stirring disperser (speed 500r / min), and then homogenize with a homogenizer for 2min (speed 2000r / min) to obtain a thermal conductive layer coating slurry, and apply the coating slurry to the surface of the pre-cured porous insulation layer through a coater (coating rate 40mm / s, thickness set to 0.2mm), place it in a blast oven and keep it warm at 70°C for 5h to obtain a pre-cured thermal conductive layer.

[0056] Step 4. Add 1g of silane coupling agent and 1g of zirconium oxide chopped fiber powder to 40g of silicone resin, ultrasonically disperse for 15min under ice bath conditions (ultrasonic frequency is 20kHz) to obtain a chopped fiber powder dispersion slurry, add 50g of titanium carbide and 8g of silicon carbide to the chopped fiber powder dispersion slurry, and use a high-speed stirring disperser to stir for 10min (speed 200r / min), and then ultrasonically disperse for 15min under ice bath conditions (ultrasonic frequency is 20kHz), and finally homogenize with a homogenizer for 2min (speed 2000r / min) to obtain an ablation layer coating slurry, and apply the coating slurry to the surface of the pre-cured thermal conductive layer through a coater (coating rate 40mm / s, thickness set to 0.5mm), put it into a blast oven and keep it warm at 70°C for 5h to obtain a pre-cured ablation layer.

[0057] Step 5. Place the coating obtained in step 4 into a blast oven, keep it warm at 80°C for 7 hours, keep it warm at 100°C for 7 hours, and keep it warm at 130°C for 7 hours to obtain a resin-based high-energy laser protection composite coating with a total thickness of 1.2 mm.

[0058] Example 3

[0059] This embodiment provides a resin-based high-energy laser protection composite coating. A porous thermal insulation layer, a heat conduction layer, and an ablation layer are sequentially formed on the surface of an aluminum alloy substrate. The components and their mass fractions for the porous thermal insulation layer are as follows: 80% boron-modified phenolic resin, 2% silane coupling agent, and 18% alumina hollow microspheres (50 μm diameter). The components and their mass fractions for the heat conduction layer are as follows: 92% boron-modified phenolic resin, 2% silane coupling agent, and 6% graphene (5 μm flake diameter). The components and their mass fractions for the ablation layer are as follows: 35% boron-modified phenolic resin, 1% silane coupling agent, 55% zirconium carbide (20 μm particle size), 8% silicon carbide (20 μm particle size), and 1% chopped glass fiber powder (20 μm length).

[0060] The preparation method of the resin-based high-energy laser protective composite coating described in this embodiment is as follows:

[0061] Step 1. Use 400 grit sandpaper to polish the surface of the aluminum alloy substrate;

[0062] Step 2. Add 2g of silane coupling agent and 18g of alumina hollow microspheres to 80g of boron-modified phenolic resin, stir for 30min using a high-speed stirring disperser (speed 800r / min), and then homogenize with a homogenizer for 3min (speed 1800r / min) to obtain a porous insulation layer coating slurry, and apply the coating slurry to the surface of the sandpaper-polished aluminum alloy substrate using a coater (coating rate 30mm / s, thickness set to 0.8mm), place it in a blast oven and keep it warm at 50°C for 10h to obtain a pre-cured porous insulation layer.

[0063] Step 3. Add 2 g of silane coupling agent and 6 g of graphene to 92 g of boron-modified phenolic resin, stir for 30 min using a high-speed stirring disperser (speed 800 r / min), and then homogenize with a homogenizer for 3 min (speed 1800 r / min) to obtain a thermal conductive layer coating slurry, and apply the coating slurry to the surface of the pre-cured porous insulation layer through a coater (coating rate 30 mm / s, thickness set to 0.4 mm), place it in a blast oven and keep it warm at 50 ° C for 10 h to obtain a pre-cured thermal conductive layer.

[0064] Step 4. Add 1 g of silane coupling agent and 1 g of chopped glass fiber powder to 35 g of boron-modified phenolic resin, ultrasonically disperse for 13 minutes under ice bath conditions (ultrasonic frequency is 25 kHz) to obtain a chopped fiber powder dispersion slurry, add 55 g of zirconium carbide and 8 g of silicon carbide to the chopped fiber powder dispersion slurry, and use a high-speed stirring disperser to stir for 8 minutes (speed 400 r / min), and then ultrasonically disperse for 13 minutes under ice bath conditions (ultrasonic frequency is 25 kHz), and finally homogenize with a homogenizer for 3 minutes (speed 1800 r / min) to obtain an ablation layer coating slurry, and apply the coating slurry to the surface of the pre-cured thermal conductive layer through a coater (coating rate 30 mm / s, thickness set to 0.8 mm), place it in a blast oven and keep it warm at 70°C for 5 hours to obtain a pre-cured ablation layer.

[0065] Step 5. Place the coating obtained in step 4 into a blast oven, keep it warm at 80°C for 7 hours, keep it warm at 100°C for 7 hours, and keep it warm at 130°C for 7 hours to obtain a resin-based high-energy laser protective composite coating with a total thickness of 2 mm.

[0066] The above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit the same. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or replace some or all of the technical features therein with equivalents. However, these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A resin-based high-energy laser protective composite coating, characterized by: A porous thermal insulation layer, a heat conduction layer, and an ablation layer are sequentially distributed on the surface of the substrate from bottom to top; the porous thermal insulation layer comprises a high-temperature resistant resin binder and hollow microspheres; the heat conduction layer comprises a high-temperature resistant resin binder and a thermal conductive material; and the ablation layer comprises a high-temperature resistant resin binder, high-melting-point carbide ceramic powder, low-melting-point carbide ceramic powder, and chopped fiber powder. The high temperature resistant resin binder is a thermosetting resin with a carbon residue rate greater than 50% at 900°C, including silicone resin, phenolic resin or boron modified phenolic resin; The particle size of the high-melting-point carbide ceramic powder and the low-melting-point carbide ceramic powder is 5-40 μm, the high-melting-point carbide ceramic powder is zirconium carbide or titanium carbide, and the low-melting-point carbide ceramic powder is silicon carbide; The thermal conductive material is thermal conductive graphite powder with a diameter of 20-80 μm, flake graphite with a sheet diameter of 0.2-0.4 mm, or graphene with a sheet diameter of 5-10 μm; The chopped fiber powder is zirconia chopped fiber powder, chopped glass fiber powder or carbon fiber powder, and the fiber length is 5-80 μm.

2. The resin-based high-energy laser protective composite coating according to claim 1, characterized in that: The hollow microspheres are phenolic hollow microspheres, alumina hollow microspheres or mullite hollow microspheres with a diameter of 20-80 μm.

3. The resin-based high-energy laser protective composite coating according to claim 1, characterized in that: The thickness of the porous heat-insulating layer is 0.5-1 mm, the thickness of the heat-conducting layer is 0.2-0.6 mm, and the thickness of the ablation layer is 0.5-1 mm.

4. The method for preparing a resin-based high-energy laser protective composite coating according to any one of claims 1 to 3, characterized in that: The steps include: Step 1. Substrate surface pretreatment; Step 2. Adding a silane coupling agent and hollow microspheres to a high-temperature resistant resin binder, uniformly dispersing the mixture to obtain a porous thermal insulation layer coating slurry, applying the porous thermal insulation layer coating slurry to the substrate surface, and pre-curing the mixture to obtain a pre-cured porous thermal insulation layer; the porous thermal insulation layer coating slurry is composed of 80% to 85% of a high-temperature resistant resin binder, 1% to 2% of a silane coupling agent, and 14% to 18% of hollow microspheres by mass; Step 3. Adding a silane coupling agent and a thermally conductive material to a high-temperature resistant resin binder, uniformly dispersing the mixture to obtain a thermally conductive layer coating slurry, applying the thermally conductive layer coating slurry to the surface of the precured porous thermal insulation layer, and precuring the precured thermally conductive layer; the thermally conductive layer coating slurry comprises, by mass, 90% to 93% of a high-temperature resistant resin binder, 1% to 2% of a silane coupling agent, and 6% to 8% of a thermally conductive material; Step 4. Adding a silane coupling agent, chopped fiber powder, high melting point carbide ceramic powder, and low melting point carbide ceramic powder to a high temperature resistant resin binder, uniformly dispersing the mixture to obtain an ablation layer coating slurry, applying the ablation layer coating slurry to the surface of the pre-cured heat conduction layer, and pre-curing the mixture to obtain a pre-cured ablation layer; the ablation layer coating slurry comprises, by mass, 30% to 40% of a high temperature resistant resin binder, 1% to 2% of a silane coupling agent, 50% to 60% of a high melting point carbide ceramic powder, 8% to 10% of a low melting point carbide ceramic powder, and 1% to 2% of a chopped fiber powder; Step 5. After the pre-cured coating obtained in step 4 is heat-cured, a resin-based laser protection composite coating can be obtained.

5. The method for preparing a resin-based high-energy laser protective composite coating according to claim 4, characterized in that: The substrate is a metal substrate or a resin-based composite material substrate; the substrate surface pretreatment method includes cleaning the substrate surface and performing a roughening treatment; the roughening treatment is to use 400-800 mesh sandpaper to evenly polish the substrate surface.

6. The method for preparing a resin-based high-energy laser protective composite coating according to claim 4, characterized in that: In step 2 and step 3, the uniform dispersion method is to use a high-speed stirring disperser with a rotation speed of 500-1000 r / min to stir for 20-40 minutes, and then use a homogenizer with a rotation speed of 1500-2000 r / min to homogenize for 2-4 minutes.

7. The method for preparing a resin-based high-energy laser protective composite coating according to claim 4, characterized in that: In step 4, the uniform dispersion method includes: ① Add silane coupling agent and chopped fiber powder to high temperature resistant resin binder, and ultrasonically disperse for 10-15 minutes in an ice bath at an ultrasonic frequency of 20-30kHz to obtain chopped fiber powder dispersion slurry; ② Add high melting point carbide ceramic powder and low melting point carbide ceramic powder to the chopped fiber powder dispersion slurry, and use a high-speed stirring disperser with a speed of 200-500r / min to stir for 5-10min, then ultrasonically disperse in an ice bath at an ultrasonic frequency of 20-30kHz for 10-15min, and finally homogenize with a homogenizer at a speed of 1500-2000r / min for 2-4min.

8. The method for preparing a resin-based high-energy laser protective composite coating according to claim 4, characterized in that: In step 2-4, the coating method is knife coating using a coating machine, and the coating rate is 20-40 mm / s.

9. The method for preparing a resin-based high-energy laser protective composite coating according to claim 4, characterized in that: In step 2-4, the pre-curing method is to place the applied coating in a forced air oven, set the temperature to 50-70° C., and keep the temperature for 5-10 hours.

10. The method for preparing a resin-based high-energy laser protective composite coating according to claim 4, characterized in that: In step 5, the heat preservation and curing process is to first keep the temperature at 80-90°C for 5-7 hours, then keep the temperature at 100-120°C for 5-7 hours, and finally keep the temperature at 130-150°C for 5-7 hours.

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