UAV surface coating, preparation method thereof and UAV

Abstract

A UAV surface coating includes at least a bonding layer, an antioxidant layer, an oxygen-blocking propagation layer and a heat-insulation cooling layer. The coating is fabricated on a surface of a UAV machine body or covers on the surface of the UAV machine body through a composite material matrix. The UAV machine body is made of lightweight material, and the composite material matrix includes a resin-based composite matrix and a ceramic-based composite matrix. Wherein, a thickness of the bonding layer is from 20 ?m to 200 ?m, a thickness of the oxygen-blocking propagation layer is from 20 ?m to 200 ?m, and a thickness of the heat-insulation cooling layer is from 80 ?m to 1000 ?m.

Claims

1. A UAV surface coating, at least comprising: a bonding layer, an antioxidant layer, an oxygen-blocking propagation layer and a heat-insulation cooling layer; wherein the coating is fabricated on a surface of a UAV machine body or covers on the surface of the UAV machine body through a composite material matrix; the UAV machine body is made of lightweight material; the composite material matrix includes a resin-based composite matrix and a ceramic-based composite matrix, wherein, a thickness of the bonding layer is from 20 ?m to 200 ?m, a thickness of the oxygen-blocking propagation layer is from 20 ?m to 200 ?m, and a thickness of the heat-insulation cooling layer is from 80 ?m to 1000 ?m.

2. The UAV surface coating according to claim 1, wherein, the resin-based composite matrix is a fiber-reinforced material with an organic polymer as matrix, and the fiber-reinforced material is one of glass fiber, carbon fiber, basalt fiber and aramid fiber.

3. The UAV surface coating according to claim 1, wherein, the ceramic-based composite matrix is one of silicon carbide fiber-reinforced silicon carbide, carbon fiber-reinforced carbon, carbon fiber-reinforced silicon carbide and silicon carbide fiber-reinforced carbon.

4. The UAV surface coating according to claim 1, wherein, the lightweight material is selected from at least one of carbon fiber braid, titanium alloy and aluminum alloy, and internal parts of the UAV are bonded to the lightweight material through ethylene propylene rubber.

5. The UAV surface coating according to claim 1, wherein, a raw material of the bonding layer is a material with a thermal expansion coefficient similar to that of the lightweight material, and is selected from at least one of aluminum, iron, magnesium, calcium, silicon, tantalum, vanadium, yttrium, zirconium, hafnium, niobium, molybdenum and tungsten.

6. The UAV surface coating according to claim 1, wherein, a thermal expansion coefficient buffer layer is provided between the oxygen-blocking propagation layer and the heat-insulation cooling layer on the ceramic-based composite matrix, and a thickness of the thermal expansion coefficient buffer layer is from 30 ?m to 50 ?m.

7. The UAV surface coating according to claim 6, wherein, a thermal expansion coefficient of the oxygen-blocking propagation layer is between 3?10.sup.?6 K.sup.?1 and 6?10.sup.?6 K, a thermal expansion coefficient of the thermal expansion coefficient buffer layer is between 6?10.sup.?6 K.sup.?1 and 9??10.sup.?6 K.sup.?1, and a thermal expansion coefficient of the heat-insulation cooling layer is between 9?10.sup.?6 K.sup.?1 and 11?10.sup.?6 K.sup.?1.

8. The UAV surface coating according to claim 6, wherein, the thermal expansion coefficient buffer layer is a ceramic of RETa.sub.3O.sub.9, wherein RE is composed of one or more rare earth elements.

9. The UAV surface coating according to claim 1, wherein, the antioxidant layer is one of Al.sub.2O.sub.3, SiO.sub.2, Ta.sub.2O.sub.5, Nb.sub.2O.sub.5, ZrO.sub.2, Mo.sub.2O.sub.5 and WO.sub.3, or a combination thereof.

10. The UAV surface coating according to claim 1, wherein, the oxygen-blocking propagation layer is a rare earth tantalate ceramic material, or a rare earth tantalum/niobate ceramic material.

11. The UAV surface coating according to claim 10, wherein, the rare earth tantalate ceramic material is spherical powder of ATaO.sub.4, and A is Al, Fe or the rare earth element; the rare earth tantalum/niobate ceramic is a ceramic material of RETa.sub.1-xNb.sub.xO.sub.4, wherein RE is one or more of the rare earth elements, and 0<x<1.

12. The UAV surface coating according to claim 1, wherein, the heat-insulation cooling layer is a rare earth niobate ceramic material, or a rare earth tantalate ceramic material, or a rare earth tantalum/niobate ceramic material.

13. The UAV surface coating according to claim 12, wherein, the rare earth niobate ceramic material is spherical powder of RE.sub.3NbO.sub.7; the rare earth tantalate ceramic is ceramic of RE.sub.3TaO.sub.7; the rare earth tantalum/niobate ceramic is RE.sub.3Ta.sub.1-yNb.sub.yO.sub.7, wherein RE is one or more of the rare earth elements, and 0<x<1.

14. A preparation method of a UAV surface coating, comprising: preparing a bonding layer on an upper surface of a ceramic-based composite matrix through cold spraying, or preparing the bonding layer on a surface of a resin-based composite matrix or on a surface of UAV machine body through electron beam physical vapor deposition; placing the bonding layer in air for oxidation to form an antioxidant layer; preparing an oxygen-blocking propagation layer on a surface of the antioxidant layer through atmospheric plasma spraying; preparing a heat-insulation cooling layer on a surface of the oxygen-blocking propagation layer through atmospheric plasma spraying.

15. The preparation method of the UAV surface coating according to claim 14, wherein, preparing the heat-insulation cooling layer on the surface of the oxygen-blocking propagation layer through atmospheric plasma spraying on the ceramic-based composite matrix further comprises: preparing a thermal expansion coefficient buffer layer on the surface of the oxygen-blocking propagation layer through atmospheric plasma spraying; preparing the heat-insulation cooling layer on a surface of the thermal expansion coefficient buffer layer through atmospheric plasma spraying.

16. The preparation method of the UAV surface coating according to claim 14, wherein, process parameters of the cold spraying comprise that compressed nitrogen is used as working gas, a spraying pressure is 0.66 MPa, a spraying distance is 30 mm, a spraying temperature is 800? C., and a powder feeding rate is 40 g/min; process parameters of the atmospheric plasma spraying comprise that a spraying gun power is from 30 kW to 50 kW, a spraying gun distance is from 80 mm to 160 mm, a gas flow rate of argon is from 3 slpm to 10 slpm, a gas flow rate of hydrogen is from 3 slpm to 10 slpm, a feeding rate is from 30 g/min to 50 g/min, a spraying gun rate is from 80 mm/s to 300 mm/s, and a spraying time is from 1 min to 20 min.

17. The preparation method of the UAV surface coating according to claim 14, wherein, process parameters of the electron beam physical vapor deposition comprise that a substrate temperature in a deposition process is from 300? C. to 500? C., a target-base distance is from 200 mm to 400 mm, an incident angle is from 30? to 50?, an accelerating voltage of electrons is from 20 kV to 30 kV, a vacuum degree is less than 5?10.sup.?3 Pa, and a deposition rate is from 50 nm/min to 150 nm/min, wherein the substrate comprises: the ceramic-based composite matrix, the resin-based composite matrix or the UAV machine body.

18. The preparation method of the UAV surface coating according to claim 14, wherein, placing the bonding layer in air for oxidation to form the antioxidant layer comprises: placing the bonding layer in the air for heating oxidation to form the antioxidant layer, a heating temperature being from 30? C. to 300? C., and a thickness of the antioxidant layer not exceeding 20 ?m.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0062] FIG. 1 is a schematic structural view of a UAV surface coating according to an embodiment of the disclosure.

[0063] FIG. 2 is a microstructure view of the UAV surface coating after being insulated at 800? C. according to an embodiment of the disclosure.

[0064] FIG. 3 is a second schematic structural view of the UAV surface coating according to an embodiment of the disclosure.

[0065] FIG. 4 is a third schematic structural view of the UAV surface coating according to an embodiment of the disclosure.

[0066] FIG. 5 is a schematic system view of a UAV according to an embodiment of the disclosure.

[0067] FIG. 6 is a schematic structural view of a UAV module according to an embodiment of the disclosure.

DETAILED DESCRIPTION

[0068] The following describes the implementation of the disclosure through specific embodiments, and those skilled in the art can easily understand other advantages and effects of the disclosure from the content disclosed in this specification. The disclosure may also be implemented or applied through other different specific embodiments. Various details in this specification may also be modified or changed based on different viewpoints and applications without departing from the disclosure. It should be noted that, the following embodiments and the features in the embodiments can be combined with each other without conflict.

[0069] It should be noted that drawings provided in the embodiments are only illustrative of a basic idea of the disclosure. The drawings only show assemblies related to the disclosure instead of drawing according to the number, shape and size of the assemblies in actual implementation. In actual implementation, the type, quantity and ratio of each assembly may be changed at will, and a layout of the assemblies may also be more complicated.

Embodiment 1

[0070] The disclosure provides a UAV surface coating and a preparation method thereof. Please refer to FIG. 1. In an embodiment of the disclosure, the UAV surface coating is coated on a surface of the UAV machine body through a resin-based composite matrix, which is a fiber-reinforced material with organic polymer as the matrix, and a reinforcing fiber is glass fiber. A bonding layer with a thickness of 30 ?m, an oxygen-blocking propagation layer with a thickness of 50 ?m, and a heat-insulation cooling layer with a thickness of 1000 ?m are sequentially prepared on the resin-based composite matrix. Silicon (Si) is used as the bonding layer, LuTa.sub.0.5Nb.sub.0.5O.sub.4 is used as the oxygen-blocking propagation layer, and ceramic coating of Lu.sub.3Ta.sub.0.3Nb.sub.0.7O.sub.7 is used as the heat-insulation cooling layer.

[0071] Specifically: (1) a silicon (Si) bonding layer with a thickness of 30 ?m is prepared on a surface of a glass fiber matrix through electron beam physical vapor deposition, in a process of electron beam physical vapor deposition, the silicon (Si) bonding layer is used as a target source, the bonding layer is deposited on the surface of the glass fiber matrix, a temperature of the glass fiber matrix is 350? C., the target-base distance is 300 mm, an incident angle is 30?, an accelerating voltage of electrons is 20 kV, a vacuum degree is less than 2?10.sup.?3 Pa, and a deposition rate is 100 nm/min.

[0072] (2) The silicon (Si) bonding layer is placed in air for oxidation to obtain a SiO.sub.2 antioxidant layer with a thickness of less than 1 ?m. The oxygen-blocking propagation layer of LuTa.sub.0.5Nb.sub.0.5O.sub.4 ceramic layer with a thickness of 50 ?m is prepared by atmospheric plasma spraying on a surface of the antioxidant layer, and LuTa.sub.0.5Nb.sub.0.5O.sub.4 spherical powder is first prepared through high-temperature solid-phase method by using Lu.sub.2O.sub.3, Nb.sub.2O.sub.5 and Ta.sub.2O.sub.5 as raw materials. Argon is used as protective gas and hydrogen is used as combustion gas in a process of spraying the LuTa.sub.0.5Nb.sub.0.5O.sub.4 spherical powder through atmospheric plasma spraying by a spraying gun. Wherein, a spraying gun power is 45 kW, and a spraying gun distance is 130 mm, gas flow rates of the argon and the hydrogen is 45/12 slpm and 40/10 slpm respectively, a feeding rate is 60 g/min, a spraying gun rate is 200 mm/s, and a spraying time is 2 min.

[0073] (3) A reflective heat insulation layer with Lu.sub.3Ta.sub.0.3Nb.sub.0.7O.sub.7 ceramic coating with a thickness of 1000 ?m is prepared through atmospheric plasma spraying on a surface of the ceramic oxygen-blocking propagation layer of LuTa.sub.0.5Nb.sub.0.5O.sub.4, and Lu.sub.3Ta.sub.0.3Nb.sub.0.7O.sub.7 spherical powder is prepared through the high-temperature solid-phase method by using Lu.sub.2O.sub.3, Nb.sub.2O.sub.5 and Ta.sub.2O.sub.5 as raw materials. The Argon is used as the protective gas and the hydrogen is used as the combustion gas in the process of spraying the Lu.sub.3Ta.sub.0.3Nb.sub.0.7O.sub.7 spherical powder through atmospheric plasma spraying by the spraying gun. Wherein, the spraying gun power is 43 kW, and the spraying gun distance is 140 mm, the gas flow rates of the argon and the hydrogen is 42/12 slpm and 45/15 slpm respectively, the feeding rate is 50 g/min, the spraying gun rate is 100 mm/s, and the spraying time is 20 min.

Embodiment 2

[0074] The disclosure provides the UAV surface coating and the preparation method thereof. Please refer to FIG. 1. In an embodiment of the disclosure, the UAV surface coating is coated on the surface of the UAV machine body through the resin-based composite matrix, which is the fiber-reinforced material with organic polymer as the matrix, and the reinforcing fiber is carbon fiber. The bonding layer with the thickness of 100 ?m, the oxygen-blocking propagation layer with the thickness of 75 ?m, and the heat-insulation cooling layer with the thickness of 100 ?m are sequentially prepared on the resin-based composite matrix. Aluminum (Al) is used as the bonding layer, Tm.sub.1/4Yb.sub.1/4Lu.sub.1/4Sc.sub.1/4Ta.sub.0.8Nb.sub.0.2O.sub.4 is used as the oxygen-blocking propagation layer, and ceramic coating of Y.sub.3Ta.sub.0.5Nb.sub.0.5O.sub.7 is used as the heat-insulation cooling layer.

[0075] Specifically: (1) an aluminum (Al) bonding layer with the thickness of 100 ?m is prepared on the surface of a glass fiber matrix through electron beam physical vapor deposition, in the process of electron beam physical vapor deposition, the aluminum (Al) bonding layer is used as the target source, the bonding layer is deposited on the surface of the matrix, the temperature of the matrix is 350? C., the target-base distance is 300 mm, the incident angle is 30?, the accelerating voltage of electrons is 20 kV, the vacuum degree is less than 2?10.sup.?3 Pa, and the deposition rate is 100 nm/min.

[0076] (2) The aluminum (Al) bonding layer is placed in the air for oxidation to obtain an Al.sub.2O.sub.3 antioxidant layer with a thickness of less than 1 ?m. The oxygen-blocking propagation layer of Tm.sub.1/4Yb.sub.1/4Lu.sub.1/4Sc.sub.1/4Ta.sub.0.8Nb.sub.0.2O.sub.4 ceramic layer with a thickness of 75 ?m is prepared by atmospheric plasma spraying on the surface of the antioxidant layer. Tm.sub.1/4Yb.sub.1/4Lu.sub.1/4Sc.sub.1/4Ta.sub.0.8Nb.sub.0.2O.sub.4 spherical powder is first prepared through high-temperature solid-phase method by using Sc.sub.2O.sub.3, Tm.sub.2O.sub.3, Yb.sub.2O.sub.3, Lu.sub.2O.sub.3, Nb.sub.2O.sub.5 and Ta.sub.2O.sub.5 as raw materials. The argon is used as the protective gas and the hydrogen is used as the combustion gas in a process of spraying the Tm.sub.1/4Yb.sub.1/4Lu.sub.1/4Sc.sub.1/4Ta.sub.0.8Nb.sub.0.2O.sub.4 spherical powder through atmospheric plasma spraying by the spraying gun. Wherein, the spraying gun power is 45 kW, and the spraying gun distance is 130 mm, the gas flow rates of the argon and the hydrogen is 45/12 slpm and 40/10 slpm respectively, the feeding rate is 60 g/min, the spraying gun rate is 200 mm/s, and the spraying time is 20 min.

[0077] (3) A reflective heat insulation layer with Y.sub.3Ta.sub.0.5Nb.sub.0.5O.sub.7 ceramic coating with a thickness of 100 ?m is prepared through atmospheric plasma spraying on a surface of the ceramic oxygen-blocking propagation layer of Tm.sub.1/4Yb.sub.1/4Lu.sub.1/4Sc.sub.1/4Ta.sub.0.8Nb.sub.0.2O.sub.4. Y.sub.3Ta.sub.0.5Nb.sub.0.5O.sub.7 spherical powder is prepared through the high-temperature solid-phase method by using Y.sub.2O.sub.3, Nb.sub.2O.sub.5 and Ta.sub.2O.sub.5 as raw materials. The argon is used as the protective gas and the hydrogen is used as the combustion gas in a process of spraying the Lu.sub.3Ta.sub.0.3Nb.sub.0.7O.sub.7 spherical powder through atmospheric plasma spraying by the spraying gun. Wherein, the spraying gun power is 43 kW, and the spraying gun distance is 140 mm, the gas flow rates of the argon and the hydrogen is 42/12 slpm and 45/15 slpm respectively, the feeding rate is 50 g/min, the spraying gun rate is 100 mm/s, and the spraying time is 2 min.

Embodiment 3

[0078] The disclosure provides the UAV surface coating and the preparation method thereof. Please refer to FIG. 1. In an embodiment of the disclosure, the UAV surface coating is coated on the surface of the UAV machine body through the resin-based composite matrix, which is the fiber-reinforced material with organic polymer as the matrix, and the reinforcing fiber is basalt fiber. The bonding layer with the thickness of 50 ?m, the oxygen-blocking propagation layer with the thickness of 80 ?m, and the heat-insulation cooling layer with the thickness of 600 ?m are sequentially prepared on the resin-based composite matrix. Tantalum niobium molybdenum alloy is used as the bonding layer, YTa.sub.0.5Nb.sub.0.5O.sub.4 is used as the oxygen-blocking propagation layer, and ceramic coating of YGdDyTa.sub.0.5Nb.sub.0.5O.sub.7 is used as the heat-insulation cooling layer.

[0079] Specifically: (1) a tantalum niobium molybdenum alloy bonding layer with the thickness of 50 ?m is prepared on the surface of a glass fiber matrix through electron beam physical vapor deposition, in the process of electron beam physical vapor deposition, the tantalum niobium molybdenum alloy bonding layer is used as the target source, the bonding layer is deposited on the surface of the matrix, the temperature of the matrix is 350? C., the target-base distance is 300 mm, the incident angle is 30?, the accelerating voltage of electrons is 20 kV, the vacuum degree is less than 2?10.sup.?3 Pa, and the deposition rate is 100 nm/min.

[0080] (2) The tantalum niobium molybdenum alloy bonding layer is placed in the air for oxidation to obtain the corresponding oxide antioxidant layer with the thickness of less than 1 ?m. The oxygen-blocking propagation layer of YTa.sub.0.5Nb.sub.0.5O.sub.4 ceramic layer with a thickness of 75 ?m is prepared by atmospheric plasma spraying on the surface of the antioxidant layer, and YTa.sub.0.5Nb.sub.0.5O.sub.4 spherical powder is first prepared through the high-temperature solid-phase method by using Y.sub.2O.sub.3, Nb.sub.2O.sub.5 and Ta.sub.2O.sub.5 as raw materials. The argon is used as the protective gas and the hydrogen is used as the combustion gas in a process of spraying the YTa.sub.0.5Nb.sub.0.5O.sub.4 spherical powder through atmospheric plasma spraying by the spraying gun. Wherein, the spraying gun power is 45 kW, and the spraying gun distance is 130 mm, the gas flow rates of the argon and the hydrogen is 45/12 slpm and 40/10 slpm respectively, the feeding rate is 60 g/min, the spraying gun rate is 200 mm/s, and the spraying time is 2 min.

[0081] (3) A reflective heat insulation layer with YGdDyTa.sub.0.5Nb.sub.0.5O.sub.7 ceramic coating with a thickness of 600 ?m is prepared through atmospheric plasma spraying on a surface of the ceramic oxygen-blocking propagation layer of YTa.sub.0.5Nb.sub.0.5O.sub.4. YGdDyTa.sub.0.5Nb.sub.0.5O.sub.7 spherical powder is prepared through the high-temperature solid-phase method by using Dy.sub.2O.sub.3, Gd.sub.2O.sub.3, Y.sub.2O.sub.3, Nb.sub.2O.sub.5 and Ta.sub.2O.sub.5 as raw materials. The argon is used as the protective gas and the hydrogen is used as the combustion gas in a process of spraying the YGdDyTa.sub.0.5Nb.sub.0.5O.sub.7 spherical powder through atmospheric plasma spraying by the spraying gun. Wherein, the spraying gun power is 43 kW, and the spraying gun distance is 140 mm, the gas flow rates of the argon and the hydrogen is 42/12 slpm and 45/15 slpm respectively, the feeding rate is 50 g/min, the spraying gun rate is 100 mm/s, and the spraying time is 12 min.

Embodiment 4

[0082] The disclosure provides the UAV surface coating and the preparation method thereof. Please refer to FIG. 1. In an embodiment of the disclosure, the UAV surface coating is coated on the surface of the UAV machine body through the resin-based composite matrix, which is the fiber-reinforced material with organic polymer as the matrix, and the reinforcing fiber is aramid fiber. The bonding layer with the thickness of 60 ?m, the oxygen-blocking propagation layer with the thickness of 60 ?m, and the heat-insulation cooling layer with the thickness of 720 ?m are sequentially prepared on the resin-based composite matrix. Zirconium-silicon alloy is used as the bonding layer, SmTa.sub.0.2Nb.sub.0.8O.sub.4 is used as the oxygen-blocking propagation layer, and ceramic coating of SmEuGdTa.sub.0.2Nb.sub.0.8O.sub.7 is used as the heat-insulation cooling layer.

[0083] Specifically: (1) a zirconium-silicon alloy bonding layer with the thickness of 50 ?m is prepared on the surface of the glass fiber matrix through electron beam physical vapor deposition, in the process of electron beam physical vapor deposition, the zirconium-silicon alloy bonding layer is used as the target source, the bonding layer is deposited on the surface of the matrix, the temperature of the matrix is 350? C., the target-base distance is 300 mm, the incident angle is 30?, the accelerating voltage of electrons is 20 kV, the vacuum degree is less than 2?10.sup.?3 Pa, and the deposition rate is 100 nm/min.

[0084] (2) The zirconium-silicon alloy bonding layer is placed in the air for oxidation to obtain the corresponding oxide antioxidant layer with the thickness of less than 1 ?m. The oxygen-blocking propagation layer of SmTa.sub.0.2Nb.sub.0.8O.sub.4 ceramic layer with a thickness of 60 ?m is prepared by atmospheric plasma spraying on the surface of the antioxidant layer, and SmTa.sub.0.2Nb.sub.0.8O.sub.4 spherical powder is first prepared through the high-temperature solid-phase method by using Sm.sub.2O.sub.3, Nb.sub.2O.sub.5 and Ta.sub.2O.sub.5 as raw materials. The argon is used as the protective gas and the hydrogen is used as the combustion gas in a process of spraying the SmTa.sub.0.2Nb.sub.0.8O.sub.4 spherical powder through atmospheric plasma spraying by the spraying gun. Wherein, the spraying gun power is 45 kW, and the spraying gun distance is 130 mm, the gas flow rates of the argon and the hydrogen is 45/12 slpm and 40/10 slpm respectively, the feeding rate is 60 g/min, the spraying gun rate is 200 mm/s, and the spraying time is 2 min.

[0085] (3) A reflective heat insulation layer with SmTa.sub.0.2Nb.sub.0.8O.sub.4 ceramic coating with a thickness of 720 ?m is prepared through atmospheric plasma spraying on a surface of the ceramic oxygen-blocking propagation layer of SmEuGdTa.sub.0.2Nb.sub.0.8O.sub.7. SmEuGdTa.sub.0.2Nb.sub.0.8O.sub.7 spherical powder is prepared through the high-temperature solid-phase method by using Sm.sub.2O.sub.3, Gd.sub.2O.sub.3, Eu.sub.2O.sub.3, Nb.sub.2O.sub.5 and Ta.sub.2O.sub.5 as raw materials. The argon is used as the protective gas and the hydrogen is used as the combustion gas in a process of spraying the SmEuGdTa.sub.0.2Nb.sub.0.8O.sub.7 spherical powder through atmospheric plasma spraying by the spraying gun. Wherein, the spraying gun power is 43 kW, and the spraying gun distance is 140 mm, the gas flow rates of the argon and the hydrogen is 42/12 slpm and 45/15 slpm respectively, the feeding rate is 50 g/min, the spraying gun rate is 100 mm/s, and the spraying time is 15 min.

Embodiment 5

[0086] The disclosure provides the UAV surface coating and the preparation method thereof. Please refer to FIG. 1. In an embodiment of the disclosure, the UAV surface coating is coated on a surface of the UAV machine body through a resin-based composite matrix, which is a fiber-reinforced material with organic polymer as the matrix, and a reinforcing fiber is glass fiber. The bonding layer with a thickness of 30 ?m, the oxygen-blocking propagation layer with a thickness of 50 ?m, and the heat-insulation cooling layer with a thickness of 500 ?m are sequentially prepared on the resin-based composite matrix. The silicon (Si) is used as the bonding layer, the LuTa.sub.0.5Nb.sub.0.5O.sub.4 is used as the oxygen-blocking propagation layer, and the ceramic coating of Lu.sub.3Ta.sub.0.3Nb.sub.0.7O.sub.7 is used as the heat-insulation cooling layer.

[0087] Specifically: (1) the silicon (Si) bonding layer with the thickness of 30 ?m is prepared on the surface of the glass fiber matrix through electron beam physical vapor deposition, in the process of electron beam physical vapor deposition, the silicon (Si) bonding layer is used as the target source, the bonding layer is deposited on the surface of the glass fiber matrix, the temperature of the glass fiber matrix is 350? C., the target-base distance is 300 mm, the incident angle is 30?, the accelerating voltage of electrons is 20 kV, the vacuum degree is less than 2?10.sup.?3 Pa, and the deposition rate is 100 nm/min.

[0088] (2) The silicon (Si) bonding layer is placed in air for oxidation to obtain the SiO2 antioxidant layer with the thickness of less than 1 ?m. The oxygen-blocking propagation layer of LuTa.sub.0.5Nb.sub.0.5O.sub.4 ceramic layer with the thickness of 50 ?m is prepared by atmospheric plasma spraying on the surface of the antioxidant layer, and LuTa.sub.0.5Nb.sub.0.5O.sub.4 spherical powder is first prepared through high-temperature solid-phase method by using Lu.sub.2O.sub.3, Nb.sub.2O.sub.5 and Ta.sub.2O.sub.5 as raw materials. The argon is used as the protective gas and the hydrogen is used as the combustion gas in the process of spraying the LuTa.sub.0.5Nb.sub.0.5O.sub.4 spherical powder through atmospheric plasma spraying by the spraying gun. Wherein, the spraying gun power is 45 kW, and the spraying gun distance is 130 mm, the gas flow rates of the argon and the hydrogen is 45/12 slpm and 40/10 slpm respectively, the feeding rate is 60 g/min, the spraying gun rate is 200 mm/s, and the spraying time is 2 min.

[0089] (3) A reflective heat insulation layer with Lu.sub.3Ta.sub.0.3Nb.sub.0.7O.sub.7 ceramic coating with the thickness of 500 ?m is prepared through atmospheric plasma spraying on the surface of the ceramic oxygen-blocking propagation layer of LuTa.sub.0.5Nb.sub.0.5O.sub.4. Lu.sub.3Ta.sub.0.3Nb.sub.0.7O.sub.7 spherical powder is prepared through the high-temperature solid-phase method by using Lu.sub.2O.sub.3, Nb.sub.2O.sub.5 and Ta.sub.2O.sub.5 as raw materials. The Argon is used as the protective gas and the hydrogen is used as the combustion gas in the process of spraying the Lu.sub.3Ta.sub.0.3Nb.sub.0.7O.sub.7 spherical powder through atmospheric plasma spraying by the spraying gun. Wherein, the spraying gun power is 43 kW, and the spraying gun distance is 140 mm, the gas flow rates of the argon and the hydrogen is 42/12 slpm and 45/15 slpm respectively, the feeding rate is 50 g/min, the spraying gun rate is 100 mm/s, and the spraying time is 10 min.

Embodiment 6

[0090] The disclosure provides the UAV surface coating and the preparation method thereof. Please refer to FIG. 1. In an embodiment of the disclosure, the UAV surface coating is coated on the surface of the UAV machine body through the resin-based composite matrix, which is the fiber-reinforced material with organic polymer as the matrix, and the reinforcing fiber is carbon fiber. The bonding layer with the thickness of 100 ?m, the oxygen-blocking propagation layer with the thickness of 75 ?m, and the heat-insulation cooling layer with the thickness of 500 ?m are sequentially prepared on the resin-based composite matrix. The aluminum (Al) is used as the bonding layer, the Tm.sub.1/4Yb.sub.1/4Lu.sub.1/4Sc.sub.1/4Ta.sub.0.8Nb.sub.0.2O.sub.4 is used as the oxygen-blocking propagation layer, and the ceramic coating of Y.sub.3Ta.sub.0.5Nb.sub.0.5O.sub.7 is used as the heat-insulation cooling layer.

[0091] Specifically: (1) the aluminum (Al) bonding layer with the thickness of 100 ?m is prepared on the surface of the glass fiber matrix through electron beam physical vapor deposition, in the process of electron beam physical vapor deposition, the aluminum (Al) bonding layer is used as the target source, the bonding layer is deposited on the surface of the matrix, the temperature of the matrix is 350? C., the target-base distance is 300 mm, the incident angle is 30?, the accelerating voltage of electrons is 20 kV, the vacuum degree is less than 2?10.sup.?3 Pa, and the deposition rate is 100 nm/min.

[0092] (2) The aluminum (Al) bonding layer is placed in the air for oxidation to obtain the Al.sub.2O.sub.3 antioxidant layer with the thickness of less than 1 ?m. The oxygen-blocking propagation layer of Tm.sub.1/4Yb.sub.1/4Lu.sub.1/4Sc.sub.1/4Ta.sub.0.8Nb.sub.0.2O.sub.4 ceramic layer with the thickness of 75 ?m is prepared by atmospheric plasma spraying on the surface of the antioxidant layer. The Tm.sub.1/4Yb.sub.1/4Lu.sub.1/4Sc.sub.1/4Ta.sub.0.2Nb.sub.0.2O.sub.4 spherical powder is first prepared through high-temperature solid-phase method by using Sc.sub.2O.sub.3, Tm.sub.2O.sub.3, Yb.sub.2O.sub.3, Lu.sub.2O.sub.3, Nb.sub.2O.sub.5 and Ta.sub.2O.sub.5 as raw materials. The argon is used as the protective gas and the hydrogen is used as the combustion gas in a process of spraying the Tm.sub.1/4Yb.sub.1/4Lu.sub.1/4Sc.sub.1/4Ta.sub.0.8Nb.sub.0.2O.sub.4 spherical powder through atmospheric plasma spraying by the spraying gun. Wherein, the spraying gun power is 45 kW, and the spraying gun distance is 130 mm, the gas flow rates of the argon and the hydrogen is 45/12 slpm and 40/10 slpm respectively, the feeding rate is 60 g/min, the spraying gun rate is 200 mm/s, and the spraying time is 20 min.

[0093] (3) The reflective heat insulation layer with Y.sub.3Ta.sub.0.5Nb.sub.0.5O.sub.7 ceramic coating with the thickness of 500 ?m is prepared through atmospheric plasma spraying on a surface of the ceramic oxygen-blocking propagation layer of Tm.sub.1/4Yb.sub.1/4Lu.sub.1/4Sc.sub.1/4Ta.sub.0.2Nb.sub.0.2O.sub.4. Y.sub.3Ta.sub.0.5Nb.sub.0.5O.sub.7 spherical powder is prepared through the high-temperature solid-phase method by using Y.sub.2O.sub.3, Nb.sub.2O.sub.5 and Ta.sub.2O.sub.5 as raw materials. The argon is used as the protective gas and the hydrogen is used as the combustion gas in the process of spraying the Lu.sub.3Ta.sub.0.3Nb.sub.0.7O.sub.7 spherical powder through atmospheric plasma spraying by the spraying gun. Wherein, the spraying gun power is 43 kW, and the spraying gun distance is 140 mm, the gas flow rates of the argon and the hydrogen is 42/12 slpm and 45/15 slpm respectively, the feeding rate is 50 g/min, the spraying gun rate is 100 mm/s, and the spraying time is 10 min.

Comparative Embodiment 1

[0094] The disclosure provides the UAV surface coating and the preparation method thereof. Please refer to FIG. 1. In an embodiment of the disclosure, the UAV surface coating is coated on the surface of the UAV machine body through the resin-based composite matrix, which is the fiber-reinforced material with organic polymer as the matrix, and the reinforcing fiber is glass fiber. The bonding layer with the thickness of 30 ?m and the oxygen-blocking propagation layer with the thickness of 50 ?m are sequentially prepared on the resin-based composite matrix. The silicon (Si) is used as the bonding layer, and the LuTa.sub.0.5Nb.sub.0.5O.sub.4 is used as the oxygen-blocking propagation layer.

[0095] Specifically: (1) the silicon (Si) bonding layer with the thickness of 30 ?m is prepared on the surface of the glass fiber matrix through electron beam physical vapor deposition, in the process of electron beam physical vapor deposition, the silicon (Si) bonding layer is used as the target source, the bonding layer is deposited on the surface of the glass fiber matrix, the temperature of the glass fiber matrix is 350? C., the target-base distance is 300 mm, the incident angle is 30?, the accelerating voltage of electrons is 20 kV, the vacuum degree is less than 2?10.sup.?3 Pa, and the deposition rate is 100 nm/min.

[0096] (2) The silicon (Si) bonding layer is placed in air for oxidation to obtain the SiO2 antioxidant layer with the thickness of less than 1 ?m. The oxygen-blocking propagation layer of LuTa.sub.0.5Nb.sub.0.5O.sub.4 ceramic layer with the thickness of 50 ?m is prepared by atmospheric plasma spraying on the surface of the antioxidant layer, and the LuTa.sub.0.5Nb.sub.0.5O.sub.4 spherical powder is first prepared through high-temperature solid-phase method by using Lu.sub.2O.sub.3, Nb.sub.2O.sub.5 and Ta.sub.2O.sub.5 as raw materials. The argon is used as the protective gas and the hydrogen is used as the combustion gas in the process of spraying the LuTa.sub.0.5Nb.sub.0.5O.sub.4 spherical powder through atmospheric plasma spraying by the spraying gun. Wherein, the spraying gun power is 45 kW, and the spraying gun distance is 130 mm, the gas flow rates of the argon and the hydrogen is 45/12 slpm and 40/10 slpm respectively, the feeding rate is 60 g/min, the spraying gun rate is 200 mm/s, and the spraying time is 2 min.

Comparative Embodiment 2

[0097] The disclosure provides the UAV surface coating and the preparation method thereof. Please refer to FIG. 1. In an embodiment of the disclosure, the UAV surface coating is coated on the surface of the UAV machine body through the resin-based composite matrix, which is the fiber-reinforced material with organic polymer as the matrix, and the reinforcing fiber is carbon fiber. The oxygen-blocking propagation layer with the thickness of 75 ?m, and the heat-insulation cooling layer with the thickness of 500 ?m are sequentially prepared on the resin-based composite matrix. The aluminum (Al) is used as the bonding layer, the Tm.sub.1/4Yb.sub.1/4Lu.sub.1/4Sc.sub.1/4Ta.sub.0.8Nb.sub.0.2O.sub.4 is used as the oxygen-blocking propagation layer, and the ceramic coating of Y.sub.3Ta.sub.0.5Nb.sub.0.5O.sub.7 is used as the heat-insulation cooling layer.

[0098] Specifically: (1) The oxygen-blocking propagation layer of Tm.sub.1/4Yb.sub.1/4Lu.sub.1/4Sc.sub.1/4Ta.sub.0.2Nb.sub.0.2O.sub.4 ceramic layer with the thickness of 75 ?m is prepared by atmospheric plasma spraying on a surface of the matrix. The Tm.sub.1/4Yb.sub.1/4Lu.sub.1/4Sc.sub.1/4Ta.sub.0.2Nb.sub.0.2O.sub.4 spherical powder is first prepared through high-temperature solid-phase method by using Sc.sub.2O.sub.3, Tm.sub.2O.sub.3, Yb.sub.2O.sub.3, Lu.sub.2O.sub.3, Nb.sub.2O.sub.5 and Ta.sub.2O.sub.5 as raw materials. The argon is used as the protective gas and the hydrogen is used as the combustion gas in a process of spraying the Tm.sub.1/4Yb.sub.1/4Lu.sub.1/4Sc.sub.1/4Ta.sub.0.8Nb.sub.0.2O.sub.4 spherical powder through atmospheric plasma spraying by the spraying gun. Wherein, the spraying gun power is 45 kW, and the spraying gun distance is 130 mm, the gas flow rates of the argon and the hydrogen is 45/12 slpm and 40/10 slpm respectively, the feeding rate is 60 g/min, the spraying gun rate is 200 mm/s, and the spraying time is 20 min.

[0099] (2) The reflective heat insulation layer with Y.sub.3Ta.sub.0.5Nb.sub.0.5O.sub.7 ceramic coating with the thickness of 500 ?m is prepared through atmospheric plasma spraying on a surface of the ceramic oxygen-blocking propagation layer of Tm.sub.1/4Yb.sub.1/4Lu.sub.1/4Sc.sub.1/4Ta.sub.0.8Nb.sub.0.2O.sub.4. Y.sub.3Ta.sub.0.5Nb.sub.0.5O.sub.7 spherical powder is prepared through the high-temperature solid-phase method by using Y.sub.2O.sub.3, Nb.sub.2O.sub.5 and Ta.sub.2O.sub.5 as raw materials. The argon is used as the protective gas and the hydrogen is used as the combustion gas in the process of spraying the Y.sub.3Ta.sub.0.5Nb.sub.0.5O.sub.7 spherical powder through atmospheric plasma spraying by the spraying gun. Wherein, the spraying gun power is 43 kW, and the spraying gun distance is 140 mm, the gas flow rates of the argon and the hydrogen is 42/12 slpm and 45/15 slpm respectively, the feeding rate is 50 g/min, the spraying gun rate is 100 mm/s, and the spraying time is 10 min.

[0100] A composition of a material system prepared in the above embodiments 1-6 and the comparative embodiments 1-2 is shown in Table 1, and a softening temperature and a heat insulation cooling gradient of the material are tested. A test process is to heat a material coating surface, and a temperature of a coating surface and a temperature of an interface between the matrix and the coating are tested. A temperature when a resin-based composite material softens and separates from the coating is determined as the softening temperature, and a temperature difference between the coating surface and the interface during softening is the thermal insulation cooling gradient. The original softening temperatures of the resin-based materials reinforced by the glass fiber, the carbon fiber, the basalt fiber and the aramid fiber used in the disclosure are 140? C., 145? C., 120? C. and 94? C., respectively.

TABLE-US-00001 TABLE 1 reinforcing fiber bonding layer oxygen-blocking propagation layer heat-insulation cooling layer Embodiment 1: glass fiber 30 ?m-Si 50 ?m LuTa.sub.0.5Nb.sub.0.5O.sub.4 1000 ?m Lu.sub.3Ta.sub.0.3Nb.sub.0.7O.sub.7 Embodiment 2: carbon fiber 100 ?m-Al 75 ?m Tm.sub.1/4Yb.sub.1/4Lu.sub.1/4Sc.sub.1/4Ta.sub.0.8Nb.sub.0.2O.sub.4 100 ?m Y.sub.3Ta.sub.0.5Nb.sub.0.5O.sub.7 Embodiment 3: basalt fiber 50 ?m-TaNbMo 80 ?m YTa.sub.0.5Nb.sub.0.5O.sub.4 600 ?m YGdDyTa.sub.0.5Nb.sub.0.5O.sub.7 Embodiment 4: aramid fiber 60 ?m-ZrSi 60 ?m SmTa.sub.0.2Nb.sub.0.8O.sub.4 720 ?m SmEuGdTa.sub.0.2Nb.sub.0.8O.sub.7 Embodiment 5: glass fiber 30 ?m-Si 100 ?m LuTa.sub.0.5Nb.sub.0.5O.sub.4 500 ?m Lu.sub.3Ta.sub.0.3Nb.sub.0.7O.sub.7 Embodiment 6: carbon fiber 100 ?m-Al 75 ?m Tm.sub.1/4Yb.sub.1/4Lu.sub.1/4Sc.sub.1/4Ta.sub.0.8Nb.sub.0.2O.sub.4 500 ?m Y.sub.3Ta.sub.0.5Nb.sub.0.5O.sub.7 Comparative glass fiber 30 ?m-Si 100 ?m LuTa.sub.0.5Nb.sub.0.5O.sub.4 embodiment 1: Comparative carbon fiber 75 ?m Tm.sub.1/4Yb.sub.1/4Lu.sub.1/4Sc.sub.1/4Ta.sub.0.8Nb.sub.0.2O.sub.4 500 ?m embodiment 2: Y.sub.3Ta.sub.0.5Nb.sub.0.5O.sub.7

TABLE-US-00002 TABLE 2 heat insulation softening cooling temperature gradient (? C.) (? C.) Embodiment 1: 592 732 Embodiment 2: 210 355 Embodiment 3: 341 461 Embodiment 4: 406 500 Embodiment 5: 308 448 Embodiment 6: 487 632 Comparative 52 192 embodiment 1: Comparative 200 345 embodiment 2:

[0101] Table 2 shows that a gradient coating prepared for different types of resin-based composite material can provide excellent thermal insulation protection properties and increase its working temperature by 100? C. to 600? C., while a coating without a gradient composite coating as the preparation of the disclosure can also improve a certain thermal insulation cooling gradient, but the performance is obviously insufficient. In addition, when the binder layer was not prepared in the comparative embodiment 2, it is found that the coating material is peeled off after two thermal cycles, while thermal cycle life of other materials exceeded 20 times. Please refer to FIG. 2. FIG. 2 is a microstructure view of a prepared composite gradient coating after a heat preservation at 800? C., and a tight bonding between layers proved that a binding force of the coating is strong and there were no obvious cracks and pores.

Embodiment 7

[0102] The disclosure provides the UAV surface coating and the preparation method thereof. Please refer to FIG. 3. In an embodiment of the disclosure, the UAV surface coating is coated on the surface of the UAV machine body through the ceramic-based composite matrix, which is made of silicon carbide fiber-reinforced silicon carbide. The bonding layer with the thickness of 100 ?m, the antioxidant layer with a thickness less than 1 ?m, the oxygen-blocking propagation layer with the thickness of 30 ?m, the thermal expansion coefficient buffer layer with the thickness of 30 ?m and the heat-insulation cooling layer with the thickness of 100 ?m are sequentially deposited on the silicon carbide fiber-reinforced silicon carbide matrix. Tantalum (Ta) is used as the bonding layer. The oxygen-blocking propagation layer is made of rare earth tantalate ceramic material of RETaO.sub.4, wherein, RE is Yb, and the thermal expansion coefficient buffer layer is made of ceramic of RETa.sub.3O.sub.9, wherein, RE is Tm.

[0103] Specifically: (1) a tantalum (Ta) bonding layer with the thickness of 100 ?m is prepared on a surface of the silicon carbide fiber-reinforced silicon carbide matrix through cold spraying. In a process of cold spraying, compressed nitrogen is used as working gas. A spraying pressure is 0.66 MPa, a spraying distance is 30 mm, a spraying temperature is 800? C., and a powder feeding rate is 40 g/min. After the material coated with the tantalum bonding layer is placed in the air, an oxidation of the tantalum may form an antioxidant layer of dense tantalum oxide Ta.sub.2O.sub.5 with a thickness less than 1 ?m on its surface.

[0104] (2) The oxygen-blocking propagation layer of YbTaO.sub.4 ceramic material with a thickness of 35 ?m is prepared by atmospheric plasma spraying on a surface of the antioxidant layer of dense tantalum oxide Ta.sub.2O.sub.5. YbTaO.sub.4 spherical powder is first prepared through high-temperature solid-phase method by using Yb.sub.2O.sub.3 and Ta.sub.2O.sub.5 as raw materials. The argon is used as the protective gas and the hydrogen is used as the combustion gas in a process of spraying the oxygen-blocking propagation layer through atmospheric plasma spraying. Wherein, during the spraying, the spraying gun power is 42 kW, and the spraying gun distance is 100 mm, the gas flow rates of the argon and the hydrogen is 40/12 slpm and 45/10 slpm respectively, the feeding rate is 50 g/min, the spraying gun rate is 300 mm/s, and the spraying time is 1 min.

[0105] (3) The thermal expansion coefficient buffer layer with Tm Ta.sub.3O.sub.9 ceramic coating with the thickness of 30 ?m is prepared through atmospheric plasma spraying on a surface of the ceramic oxygen-blocking propagation layer of YbTaO.sub.4. Tm Ta.sub.3O.sub.9 spherical powder is first prepared through the high-temperature solid-phase method by using Tm.sub.2O.sub.3 and Ta.sub.2O.sub.5 as raw materials. The argon is used as the protective gas and the hydrogen is used as the combustion gas in the process of spraying thermal expansion coefficient buffer layer through atmospheric plasma spraying. Wherein, the spraying gun power is 46 kW, and the spraying gun distance is 150 mm, the gas flow rates of the argon and the hydrogen is 42/12 slpm and 40/10 slpm respectively, the feeding rate is 30 g/min, the spraying gun rate is 300 mm/s, and the spraying time is 2 min.

[0106] (4) A heat-insulation cooling layer with Tm.sub.3TaO.sub.7 ceramic coating with the thickness of 200 ?m is prepared through atmospheric plasma spraying on a surface of the ceramic thermal expansion coefficient buffer layer of Tm Ta.sub.3O.sub.9. Tm.sub.3TaO.sub.7 spherical powder is first prepared through high-temperature solid-phase method by using Tm.sub.2O.sub.3 and Ta.sub.2O.sub.5 as raw materials. The argon is used as the protective gas and the hydrogen is used as the combustion gas in a process of spraying the heat-insulation cooling layer through atmospheric plasma spraying. Wherein, the spraying gun power is 46 kW, and the spraying gun distance is 150 mm, the gas flow rates of the argon and the hydrogen is 42/12 slpm and 40/10 slpm respectively, the feeding rate is 30 g/min, the spraying gun rate is 300 mm/s, and the spraying time is 2 min.

Embodiment 8

[0107] The disclosure provides the UAV surface coating and the preparation method thereof. Please refer to FIG. 3. In an embodiment of the disclosure, the UAV surface coating is coated on the surface of the UAV machine body through the ceramic-based composite matrix, which is made of silicon carbide fiber-reinforced silicon carbide. The bonding layer with the thickness of 200 ?m, the antioxidant layer with the thickness less than 1 ?m, the oxygen-blocking propagation layer with the thickness of 50 ?m, the thermal expansion coefficient buffer layer with the thickness of 50 ?m and the heat-insulation cooling layer with the thickness of 100 ?m are sequentially deposited on the carbon fiber-reinforced silicon carbide. The tantalum (Ta) is used as the bonding layer. The oxygen-blocking propagation layer is made of rare earth tantalate ceramic coating of RETaO.sub.4, wherein, RE is Yb and Lu, and the thermal expansion coefficient buffer layer is made of ceramic of RETa.sub.3O.sub.9, wherein, RE is La, Ho and Tm.

[0108] Specifically: (1) a tantalum bonding layer with the thickness of 200 ?m is prepared on a surface of the silicon carbide fiber-reinforced silicon carbide matrix through cold spraying. In a process of cold spraying, compressed nitrogen is used as working gas. A spraying pressure is 0.66 MPa, a spraying distance is 30 mm, a spraying temperature is 800? C., and a powder feeding rate is 40 g/min. After the material coated with the tantalum bonding layer is placed in the air, an oxidation of the tantalum may form an antioxidant layer of dense tantalum oxide Ta.sub.2O.sub.5 with a thickness less than 1 ?m on its surface.

[0109] (2) The oxygen-blocking propagation layer of Yb.sub.1/2Lu.sub.1/2TaO.sub.4 ceramic coating with the thickness of 50 ?m is prepared by atmospheric plasma spraying on the surface of the antioxidant layer of dense tantalum oxide Ta.sub.2O.sub.5. Yb.sub.1/2Lu.sub.1/2TaO.sub.4 spherical powder is first prepared through high-temperature solid-phase method by using Lu.sub.2O.sub.3, Yb.sub.2O.sub.3 and Ta.sub.2O.sub.5 as raw materials. The argon is used as the protective gas and the hydrogen is used as the combustion gas in the process of spraying the oxygen-blocking propagation layer through atmospheric plasma spraying. Wherein, during the spraying, the spraying gun power is 42 kW, and the spraying gun distance is 100 mm, the gas flow rates of the argon and the hydrogen is 40/12 slpm and 45/10 slpm respectively, the feeding rate is 50 g/min, the spraying gun rate is 300 mm/s, and the spraying time is 2 min.

[0110] (3) The thermal expansion coefficient buffer layer with La.sub.1/3Ho.sub.1/3Tm.sub.1/3Ta.sub.3O.sub.9 ceramic coating with the thickness of 50 ?m is prepared through atmospheric plasma spraying on a surface of the ceramic oxygen-blocking propagation layer of Yb.sub.1/2Lu.sub.1/2TaO.sub.4. La.sub.1/3Ho.sub.1/3Tm.sub.1/3Ta.sub.3O.sub.9 spherical powder is first prepared through the high-temperature solid-phase method by using La.sub.2O.sub.3, Ho.sub.2O.sub.3, Tm.sub.2O.sub.3 and Ta.sub.2O.sub.5 as raw materials. The argon is used as the protective gas and the hydrogen is used as the combustion gas in the process of spraying the thermal expansion coefficient buffer layer through atmospheric plasma spraying. Wherein, the spraying gun power is 46 kW, and the spraying gun distance is 150 mm, the gas flow rates of the argon and the hydrogen is 42/12 slpm and 40/10 slpm respectively, the feeding rate is 30 g/min, the spraying gun rate is 300 mm/s, and the spraying time is 3 min.

[0111] (4) A heat-insulation cooling layer with Y.sub.3TaO.sub.7 ceramic coating with the thickness of 100 ?m is prepared through atmospheric plasma spraying on a surface of the ceramic thermal expansion coefficient buffer layer of La.sub.1/3Ho.sub.1/3Tm.sub.1/3Ta.sub.3O.sub.9. Y.sub.3TaO.sub.7 spherical powder is first prepared through high-temperature solid-phase method by using Y.sub.2O.sub.3 and Ta.sub.2O.sub.5 as raw materials. The argon is used as the protective gas and the hydrogen is used as the combustion gas in a process of spraying the heat-insulation cooling ceramic layer through atmospheric plasma spraying. Wherein, the spraying gun power is 46 kW, and the spraying gun distance is 150 mm, the gas flow rates of the argon and the hydrogen is 42/12 slpm and 40/10 slpm respectively, the feeding rate is 30 g/min, the spraying gun rate is 300 mm/s, and the spraying time is 2 min.

Embodiment 9

[0112] The disclosure provides the UAV surface coating and the preparation method thereof. Please refer to FIG. 3. In an embodiment of the disclosure, the UAV surface coating is coated on the surface of the UAV machine body through the ceramic-based composite matrix, which is made of carbon fiber-reinforced silicon carbide. The bonding layer with the thickness of 150 ?m, the antioxidant layer with the thickness less than 1 ?m, the oxygen-blocking propagation layer with the thickness of 35 ?m, the thermal expansion coefficient buffer layer with the thickness of 35 ?m and the heat-insulation cooling layer with the thickness of 1000 ?m are sequentially deposited on the carbon fiber-reinforced silicon carbide matrix. The tantalum (Ta) is used as the bonding layer. The oxygen-blocking propagation layer is made of rare earth tantalate ceramic coating of RETaO.sub.4, wherein, RE is Sc, and the thermal expansion coefficient buffer layer is made of ceramic of RETa.sub.3O.sub.9, wherein, RE is La.

[0113] Specifically: (1) a tantalum bonding layer with the thickness of 150 ?m is prepared on a surface of the carbon fiber-reinforced silicon carbide matrix through cold spraying. In a process of cold spraying, compressed nitrogen is used as working gas. A spraying pressure is 0.66 MPa, a spraying distance is 30 mm, a spraying temperature is 800? C., and a powder feeding rate is 40 g/min. After the material coated with the tantalum bonding layer is placed in the air, an oxidation of the tantalum may form an antioxidant layer of dense tantalum oxide Ta.sub.2O.sub.5 with a thickness less than 1 ?m on its surface.

[0114] (2) The oxygen-blocking propagation layer of ScTaO.sub.4 ceramic coating with a thickness of 35 ?m is prepared by atmospheric plasma spraying on the surface of the antioxidant layer of dense tantalum oxide Ta.sub.2O.sub.5. ScTaO.sub.4 spherical powder is first prepared through high-temperature solid-phase method by using Sc.sub.2O.sub.3 and Ta.sub.2O.sub.5 as raw materials. The argon is used as the protective gas and the hydrogen is used as the combustion gas in the process of spraying the oxygen-blocking propagation layer through atmospheric plasma spraying. Wherein, during the spraying, the spraying gun power is 42 kW, and the spraying gun distance is 100 mm, the gas flow rates of the argon and the hydrogen is 40/12 slpm and 45/10 slpm respectively, the feeding rate is 50 g/min, the spraying gun rate is 300 mm/s, and the spraying time is 2 min.

[0115] (3) The thermal expansion coefficient buffer layer with LaTa.sub.3O.sub.9 ceramic coating with the thickness of 30 ?m is prepared through atmospheric plasma spraying on a surface of the ceramic oxygen-blocking propagation layer of ScTaO.sub.4. LaTa.sub.3O.sub.9 spherical powder is first prepared through the high-temperature solid-phase method by using La.sub.2O.sub.3 and Ta.sub.2O.sub.5 as raw materials. The argon is used as the protective gas and the hydrogen is used as the combustion gas in the process of spraying the thermal expansion coefficient buffer layer through atmospheric plasma spraying. Wherein, the spraying gun power is 46 kW, and the spraying gun distance is 150 mm, the gas flow rates of the argon and the hydrogen is 42/12 slpm and 40/10 slpm respectively, the feeding rate is 30 g/min, the spraying gun rate is 300 mm/s, and the spraying time is 3 min.

[0116] (4) A heat-insulation cooling layer with YLaDyTaO.sub.7 ceramic coating with the thickness of 1000 ?m is prepared through atmospheric plasma spraying on a surface of the ceramic thermal expansion coefficient buffer layer of LaTa.sub.3O.sub.9. YLaDyTaO.sub.7 spherical powder is first prepared through high-temperature solid-phase method by using Y.sub.2O.sub.3, La.sub.2O.sub.3, Dy.sub.2O.sub.3 and Ta.sub.2O.sub.5 as raw materials. The argon is used as the protective gas and the hydrogen is used as the combustion gas in the process of spraying the heat-insulation cooling ceramic layer through atmospheric plasma spraying. Wherein, the spraying gun power is 46 kW, and the spraying gun distance is 150 mm, the gas flow rates of the argon and the hydrogen is 42/12 slpm and 40/10 slpm respectively, the feeding rate is 30 g/min, the spraying gun rate is 300 mm/s, and the spraying time is 10 min.

Embodiment 10

[0117] The disclosure provides the UAV surface coating and the preparation method thereof. Please refer to FIG. 3. In an embodiment of the disclosure, the UAV surface coating is coated on the surface of the UAV machine body through the ceramic-based composite matrix, which is made of carbon fiber-reinforced carbon. The bonding layer with the thickness of 170 ?m, the antioxidant layer with the thickness less than 1 ?m, the oxygen-blocking propagation layer with the thickness of 35 ?m, the thermal expansion coefficient buffer layer with the thickness of 40 ?m and the heat-insulation cooling layer with the thickness of 500 ?m are sequentially deposited on the carbon fiber-reinforced carbon matrix. The tantalum (Ta) is used as the bonding layer. The oxygen-blocking propagation layer is made of rare earth tantalate ceramic coating of RETaO.sub.4, wherein, RE is Sc, Yb and Lu, and the thermal expansion coefficient buffer layer is made of ceramic of RETa.sub.3O.sub.9, wherein, RE is La, Ho, Er and Tm.

[0118] Specifically: (1) the tantalum bonding layer with the thickness of 170 ?m is prepared on the surface of the carbon fiber-reinforced carbon matrix through cold spraying. In the process of cold spraying, the compressed nitrogen is used as the working gas. The spraying pressure is 0.66 MPa, the spraying distance is 30 mm, the spraying temperature is 800? C., and the powder feeding rate is 40 g/min. After the material coated with the tantalum bonding layer is placed in the air, the oxidation of the tantalum may form the antioxidant layer of dense tantalum oxide Ta.sub.2O.sub.5 with the thickness less than 1 ?m on its surface.

[0119] (2) The oxygen-blocking propagation layer of Sc.sub.1/3Yb.sub.1/3Lu.sub.1/3TaO.sub.4 ceramic coating with the thickness of 35 ?m is prepared by atmospheric plasma spraying on the surface of the antioxidant layer of dense tantalum oxide Ta.sub.2O.sub.5. Sc.sub.1/3Yb.sub.1/3Lu.sub.1/3TaO.sub.4 spherical powder is first prepared through high-temperature solid-phase method by using Sc.sub.2O.sub.3, Lu.sub.2O.sub.3, Yb.sub.2O.sub.3 and Ta.sub.2O.sub.5 as raw materials. The argon is used as the protective gas and the hydrogen is used as the combustion gas in the process of spraying the oxygen-blocking propagation layer through atmospheric plasma spraying. Wherein, during the spraying, the spraying gun power is 42 kW, and the spraying gun distance is 100 mm, the gas flow rates of the argon and the hydrogen is 40/12 slpm and 45/10 slpm respectively, the feeding rate is 50 g/min, the spraying gun rate is 300 mm/s, and the spraying time is 2 min.

[0120] (3) The thermal expansion coefficient buffer layer with La.sub.1/4Ho.sub.1/4Tm.sub.1/4Er.sub.1/4Ta.sub.3O.sub.9 ceramic coating with the thickness of 40 ?m is prepared through atmospheric plasma spraying on a surface of the ceramic oxygen-blocking propagation layer of Sc.sub.1/3Yb.sub.1/3Lu.sub.1/3TaO.sub.4. La.sub.1/4Ho.sub.1/4Tm.sub.1/4Er.sub.1/4Ta.sub.3O.sub.9 spherical powder is first prepared through the high-temperature solid-phase method by using Er.sub.2O.sub.3, La.sub.2O.sub.3, Ho.sub.2O.sub.3, Tm.sub.2O.sub.3 and Ta.sub.2O.sub.5 as raw materials. The argon is used as the protective gas and the hydrogen is used as the combustion gas in the process of spraying the thermal expansion coefficient buffer layer through atmospheric plasma spraying. Wherein, the spraying gun power is 46 kW, and the spraying gun distance is 150 mm, the gas flow rates of the argon and the hydrogen is 42/12 slpm and 40/10 slpm respectively, the feeding rate is 30 g/min, the spraying gun rate is 300 mm/s, and the spraying time is 3 min.

[0121] (4) A heat-insulation cooling layer with Y.sub.3TaO.sub.7 ceramic coating with the thickness of 500 ?m is prepared through atmospheric plasma spraying on a surface of the ceramic thermal expansion coefficient buffer layer of La.sub.1/4Ho.sub.1/4Tm.sub.1/4Er.sub.1/4Ta.sub.3O.sub.9. The Y.sub.3TaO.sub.7 spherical powder is first prepared through high-temperature solid-phase method by using Y.sub.2O.sub.3 and Ta.sub.2O.sub.5 as raw materials. The argon is used as the protective gas and the hydrogen is used as the combustion gas in the process of spraying the heat-insulation cooling ceramic layer through atmospheric plasma spraying. Wherein, the spraying gun power is 46 kW, and the spraying gun distance is 150 mm, the gas flow rates of the argon and the hydrogen is 42/12 slpm and 40/10 slpm respectively, the feeding rate is 30 g/min, the spraying gun rate is 300 mm/s, and the spraying time is 10 min.

Comparative Embodiment 3

[0122] The disclosure provides the UAV surface coating and the preparation method thereof. Please refer to FIG. 1. In an embodiment of the disclosure, the UAV surface coating is coated on the surface of the UAV machine body through the ceramic-based composite matrix, which is made of silicon carbide fiber-reinforced carbon. The bonding layer with the thickness of 200 ?m, the antioxidant layer with the thickness less than 1 ?m, the oxygen-blocking propagation layer with the thickness of 50 ?m and the heat-insulation cooling layer with the thickness of 100 ?m are sequentially deposited on the silicon carbide fiber-reinforced carbon matrix. The tantalum (Ta) is used as the bonding layer. The oxygen-blocking propagation layer is made of rare earth tantalate ceramic coating of RETaO.sub.4, wherein, RE is Yb and Lu, and the thermal expansion coefficient buffer layer is made of ceramic of RETa.sub.3O.sub.9, wherein, RE is La, Ho and Tm.

[0123] Specifically: (1) the tantalum bonding layer with the thickness of 200 ?m is prepared on the surface of the silicon carbide fiber-reinforced carbon matrix through cold spraying. In the process of cold spraying, the compressed nitrogen is used as the working gas. The spraying pressure is 0.66 MPa, the spraying distance is 30 mm, the spraying temperature is 800? C., and the powder feeding rate is 40 g/min. After the material coated with the tantalum bonding layer is placed in the air, the oxidation of the tantalum may form the antioxidant layer of dense tantalum oxide Ta.sub.2O.sub.5 with the thickness less than 1 ?m on its surface.

[0124] (2) The oxygen-blocking propagation layer of Yb.sub.1/2Lu.sub.1/2TaO.sub.4 ceramic coating with the thickness of 50 ?m is prepared by atmospheric plasma spraying on the surface of the antioxidant layer of dense tantalum oxide Ta.sub.2O.sub.5. Yb.sub.1/2Lu.sub.1/2TaO.sub.4 spherical powder is first prepared through high-temperature solid-phase method by using Lu.sub.2O.sub.3, Yb.sub.2O.sub.3 and Ta.sub.2O.sub.5 as raw materials. The argon is used as the protective gas and the hydrogen is used as the combustion gas in the process of spraying the oxygen-blocking propagation layer through atmospheric plasma spraying. Wherein, during the spraying, the spraying gun power is 42 kW, and the spraying gun distance is 100 mm, the gas flow rates of the argon and the hydrogen is 40/12 slpm and 45/10 slpm respectively, the feeding rate is 50 g/min, the spraying gun rate is 300 mm/s, and the spraying time is 2 min.

[0125] (3) The heat-insulation cooling layer with Y.sub.3TaO.sub.7 ceramic coating with the thickness of 100 ?m is prepared through atmospheric plasma spraying on a surface of the oxygen-blocking propagation layer of Yb.sub.1/2Lu.sub.1/2TaO.sub.4 ceramic coating. The Y.sub.3TaO.sub.7 spherical powder is first prepared through high-temperature solid-phase method by using Y.sub.2O.sub.3 and Ta.sub.2O.sub.5 as raw materials. The argon is used as the protective gas and the hydrogen is used as the combustion gas in the process of spraying the heat-insulation cooling ceramic layer through atmospheric plasma spraying. Wherein, the spraying gun power is 46 kW, and the spraying gun distance is 150 mm, the gas flow rates of the argon and the hydrogen is 42/12 slpm and 40/10 slpm respectively, the feeding rate is 30 g/min, the spraying gun rate is 300 mm/s, and the spraying time is 2 min.

Comparative Embodiment 4

[0126] The disclosure provides the UAV surface coating and the preparation method thereof. Please refer to FIG. 3. In an embodiment of the disclosure, the UAV surface coating is coated on the surface of the UAV machine body through the ceramic-based composite matrix, which is made of carbon fiber-reinforced silicon carbide. The oxygen-blocking propagation layer with the thickness of 35 ?m, the thermal expansion coefficient buffer layer with the thickness of 35 ?m and the heat-insulation cooling layer with the thickness of 1000 ?m are sequentially deposited on the carbon fiber-reinforced silicon carbide matrix. The tantalum (Ta) is used as the bonding layer. The oxygen-blocking propagation layer is made of rare earth tantalate ceramic coating of RETaO.sub.4, wherein, RE is Sc, and the thermal expansion coefficient buffer layer is made of ceramic of RETa.sub.3O.sub.9, wherein, RE is La.

[0127] Specifically: (1) The oxygen-blocking propagation layer of ScTaO.sub.4 ceramic coating with the thickness of 35 ?m is prepared by atmospheric plasma spraying on the surface of the matrix. The ScTaO.sub.4 spherical powder is first prepared through high-temperature solid-phase method by using Sc.sub.2O.sub.3 and Ta.sub.2O.sub.5 as raw materials. The argon is used as the protective gas and the hydrogen is used as the combustion gas in the process of spraying the oxygen-blocking propagation layer through atmospheric plasma spraying. Wherein, during the spraying, the spraying gun power is 42 kW, and the spraying gun distance is 100 mm, the gas flow rates of the argon and the hydrogen is 40/12 slpm and 45/10 slpm respectively, the feeding rate is 50 g/min, the spraying gun rate is 300 mm/s, and the spraying time is 2 min.

[0128] (2) The thermal expansion coefficient buffer layer with LaTa.sub.3O.sub.9 ceramic coating with the thickness of 35 ?m is prepared through atmospheric plasma spraying on the surface of the ceramic oxygen-blocking propagation layer of ScTaO.sub.4. The LaTa.sub.3O.sub.9 spherical powder is first prepared through the high-temperature solid-phase method by using La.sub.2O.sub.3 and Ta.sub.2O.sub.5 as raw materials. The argon is used as the protective gas and the hydrogen is used as the combustion gas in the process of spraying the thermal expansion coefficient buffer layer through atmospheric plasma spraying. Wherein, the spraying gun power is 46 kW, and the spraying gun distance is 150 mm, the gas flow rates of the argon and the hydrogen is 42/12 slpm and 40/10 slpm respectively, the feeding rate is 30 g/min, the spraying gun rate is 300 mm/s, and the spraying time is 3 min.

[0129] (3) A heat-insulation cooling layer with YLaDyTaO.sub.7 ceramic coating with the thickness of 1000 ?m is prepared through atmospheric plasma spraying on a surface of the ceramic thermal expansion coefficient buffer layer of LaTa.sub.3O.sub.9. YLaDyTaO.sub.7 spherical powder is first prepared through high-temperature solid-phase method by using Y.sub.2O.sub.3, La.sub.2O.sub.3, Dy.sub.2O.sub.3 and Ta.sub.2O.sub.5 as raw materials. The argon is used as the protective gas and the hydrogen is used as the combustion gas in the process of spraying the heat-insulation cooling ceramic layer through atmospheric plasma spraying. Wherein, the spraying gun power is 46 kW, and the spraying gun distance is 150 mm, the gas flow rates of the argon and the hydrogen is 42/12 slpm and 40/10 slpm respectively, the feeding rate is 30 g/min, the spraying gun rate is 300 mm/s, and the spraying time is 10 min.

[0130] A specific composition of a material system prepared in the above embodiments 7-10 is shown in Table 3. In order to characterize a performance of the embodiments and comparative embodiments, a number of thermal cycles required for failure, an oxidation weight loss rate and the heat insulation cooling gradient are tested. Wherein, a thermal cycling test process is to use a flame to heat the coating surface to 1000? C. and keep the temperature for 3 minutes, and then cool it for 2 minutes. This cycle continues until the coating peels off or a material oxidizes and loses more than 10% weight. After weighing a mass of the material system before (W1) and after (W2) the total number of thermal cycles, the oxidation weight loss rate is (W1?W2)/W1?100%. While a temperature difference between the coating surface and a contact interface between the matrix and the coating during a first test is a heat insulation cooling gradient of the coating material, and results are shown in Table 4.

TABLE-US-00003 TABLE 3 oxygen-blocking heat-insulation matrix bonding layer propagation layer buffer layer cooling layer Embodiment 7 SiC.sub.f/SiC 100 ?m 30 ?m YbTaO.sub.4 30 ?m 200 ?m TmTa.sub.3O.sub.9 Tm.sub.3TaO.sub.7 Embodiment 8 SiC.sub.f/SiC 200 ?m 50 ?m Yb.sub.1/2Lu.sub.1/2TaO.sub.4 50 ?m 100 ?m La.sub.1/3Ho.sub.1/3Tm.sub.1/3Ta.sub.3O.sub.9 Y.sub.3TaO.sub.7 Embodiment 9 C.sub.f/SiC 150 ?m 35 ?m ScTaO.sub.4 35 ?m 1000 ?m LaTa.sub.3O.sub.9 YLaDyTaO.sub.7 Embodiment 10 C.sub.f/C 170 ?m 35 ?m Sc.sub.1/3Yb.sub.1/3Lu.sub.1/3TaO.sub.4 40 ?m 500 ?m La.sub.1/4Ho.sub.1/4Tm.sub.1/4Er.sub.1/4Ta.sub.3O.sub.9 Y.sub.3TaO.sub.7 Comparative SiC.sub.f/C 200 ?m 50 ?m Yb.sub.1/2Lu.sub.1/2TaO.sub.4 100 ?m embodiment 3: Y.sub.3TaO.sub.7 Comparative C.sub.f/SiC 35 ?m ScTaO.sub.4 35 ?m 1000 ?m embodiment 4: LaTa.sub.3O.sub.9 YLaDyTaO.sub.7

TABLE-US-00004 TABLE 4 number of oxidation heat insulation thermal weight cooling gradient cycles loss rate (? C.) Embodiment 7 303 12 482 Embodiment 8 317 15 409 Embodiment 9 1352 10 627 Embodiment 10 1068 13 516 Comparative 23 26 388 embodiment 3: Comparative 16 22 611 embodiment 4:

[0131] The test results show that the materials with a complete coating system have excellent thermal insulation and cooling effect, and can be used for a long time in a temperature environment of 1000? C., which prevents an oxidation failure of the above-mentioned matrix materials. While the materials without a complete coating system fail early due to a large difference in thermal expansion coefficient and weak adhesion, so they cannot meet the service requirements.

Embodiment 11

[0132] Please refer to FIG. 4. In this embodiment, lightweight material for manufacturing the UAV machine body is selected from carbon fiber braid. Internal parts of the UAV and a carbon fiber braided machine body are combined by ethylene propylene rubber. A specific production process is that the ethylene propylene rubber is covered on a surface of the UAV, and then a lightweight material casing of the UAV machine body may be buckled on its surface. The carbon fiber braid material is used as the matrix, a coating including bonding layer, antioxidant layer, oxygen-blocking propagation layer and heat-insulation cooling layer is prepared on a matrix surface, and the specific operations are as follows:

[0133] (1) the silicon (Si) bonding layer with the thickness of 50 ?m is prepared on a surface of the carbon fiber braid through electron beam physical vapor deposition. In a process of the deposition, the substrate temperature is 350? C., the target-base distance is 300 mm, the incident angle is 30?, the accelerating voltage of electrons is 20 kV, the vacuum degree is less than 2?10.sup.?3 Pa, and the deposition rate is 100 nm/min.

[0134] (2) After a Si coating is prepared, it is placed in the air and heated at 300? C. for oxidation to obtain a SiO.sub.2 coating with a thickness of 10 ?m, which means the antioxidant layer.

[0135] (3) An oxygen-blocking propagation layer of YbTaO4 ceramic coating with a thickness of 50 ?m is prepared on a surface of the antioxidant layer through atmospheric plasma spraying. The YbTaO.sub.4 spherical powder is first prepared through high-temperature solid-phase method by using Yb.sub.2O.sub.3 and Ta.sub.2O.sub.5 as raw materials. Then, the YbTaO.sub.4 ceramic coating is prepared through atmospheric plasma spraying with the YbTaO.sub.4 spherical powder, and process parameters of the atmospheric plasma spraying are as follows: the spraying gun power is 42 kW, and the spraying gun distance is 120 mm, the gas flow rates of the argon and the hydrogen is 40/12 slpm and 45/10 slpm respectively, the feeding rate is 45 g/min, the spraying gun rate is 200 mm/s, and the spraying time is 2 min.

[0136] (4) A heat-insulation cooling layer with La.sub.3NbO.sub.7 ceramic coating with a thickness of 300 ?m is prepared through atmospheric plasma spraying on the surface of the oxygen-blocking propagation layer. La.sub.3NbO.sub.7 spherical powder is first prepared through the high-temperature solid-phase method by using La.sub.2O.sub.3 and Nb.sub.2O.sub.5 as raw materials. Then, the La.sub.3NbO.sub.7 ceramic coating is prepared through atmospheric plasma spraying with the La.sub.3NbO.sub.7 spherical powder, and process parameters of the atmospheric plasma spraying are as follows: the spraying gun power is 43 kW, and the spraying gun distance is 120 mm, the gas flow rates of the argon and the hydrogen is 42/12 slpm and 45/15 slpm respectively, the feeding rate is 50 g/min, the spraying gun rate is 100 mm/s, and the spraying time is 10 min.

[0137] The inventor tested a thermal conductivity of the coating system (excluding ethylene propylene rubber) prepared on the surface of the lightweight material carbon fiber braid provided in this embodiment with the temperature, and found that the thermal conductivity increases slightly with an increase of the temperature, but an overall thermal conductivity of the material system is extremely low. The overall thermal conductivity between 0.32 W/m/K and 0.48 W/m/K is proved that it has excellent thermal insulation protection in a high temperature environment.

[0138] A microstructure view of the coating system prepared in the embodiment is obtained. Wherein the antioxidant layer is very thin and only a black part area on a surface of the bonding layer. It may also be seen from FIG. 3 that a combination of materials between the coatings is tight, and there is no obvious crack existing, which proves that the coating material with extremely strong binding force can be obtained by adopting a preparation process of the disclosure.

Embodiment 12

[0139] Please refer to FIG. 4. In this embodiment, the lightweight material for manufacturing the UAV machine body is selected from TC4 titanium alloy material. The TC4 titanium alloy material is used as the matrix, the coating including bonding layer, antioxidant layer, oxygen-blocking propagation layer and heat-insulation cooling layer is prepared on the matrix surface, and the specific operations are as follows:

[0140] (1) the aluminum (Al) bonding layer with the thickness of 50 ?m is prepared on a surface of the TC4 titanium alloy through electron beam physical vapor deposition. In the process of the deposition, the substrate temperature is 400? C., the target-base distance is 300 mm, the incident angle is 45?, the accelerating voltage of electrons is 22 kV, the vacuum degree is less than 3?10.sup.?3 Pa, and the deposition rate is 100 nm/min.

[0141] (2) After an Al coating is prepared, it is placed in the air and heated at 100? C. for oxidation to obtain an Al.sub.2O.sub.3 coating with a thickness less than 10 ?m, which means the antioxidant layer.

[0142] (3) An oxygen-blocking propagation layer of Yb.sub.0.5Lu.sub.0.5TaO.sub.4 ceramic coating with a thickness of 50 ?m is prepared on a surface of the antioxidant layer through atmospheric plasma spraying. The Yb.sub.0.5Lu.sub.0.5TaO.sub.4 spherical powder is first prepared through high-temperature solid-phase method by using Lu.sub.2O.sub.3, Yb.sub.2O.sub.3 and Ta.sub.2O.sub.3 as raw materials. Then, Yb.sub.0.5Lu.sub.0.5TaO.sub.4 ceramic coating is prepared through atmospheric plasma spraying with the Yb.sub.0.5Lu.sub.0.5TaO.sub.4 spherical powder, and process parameters of the atmospheric plasma spraying are as follows: the spraying gun power is 42 kW, and the spraying gun distance is 120 mm, the gas flow rates of the argon and the hydrogen is 40/12 slpm and 45/10 slpm respectively, the feeding rate is 45 g/min, the spraying gun rate is 200 mm/s, and the spraying time is 2 min.

[0143] (4) A heat-insulation cooling layer with Y.sub.3NbO.sub.7 ceramic coating with a thickness of 350 ?m is prepared through atmospheric plasma spraying on the surface of the oxygen-blocking propagation layer. Y.sub.3NbO.sub.7 spherical powder is first prepared through the high-temperature solid-phase method by using Y.sub.2O.sub.3 and Nb.sub.2O.sub.5 as raw materials. Then, the Y.sub.3NbO.sub.7 ceramic coating is prepared through atmospheric plasma spraying with the Y.sub.3NbO.sub.7 spherical powder, and process parameters of the atmospheric plasma spraying are as follows: the spraying gun power is 43 kW, and the spraying gun distance is 100 mm, the gas flow rates of the argon and the hydrogen is 42/12 slpm and 45/15 slpm respectively, the feeding rate is 40 g/min, the spraying gun rate is 100 mm/s, and the spraying time is 11 min.

Embodiment 13

[0144] Please refer to FIG. 4. In this embodiment, the lightweight material for manufacturing the UAV machine body is selected from aluminum alloy. The aluminum alloy is used as the matrix, the coating including bonding layer, antioxidant layer, oxygen-blocking propagation layer and heat-insulation cooling layer is prepared on the matrix surface, and the specific operations are as follows:

[0145] (1) the aluminum (Al) bonding layer with the thickness of 20 ?m is prepared on a surface of the aluminum alloy through electron beam physical vapor deposition. In the process of the deposition, the substrate temperature is 400? C., the target-base distance is 300 mm, the incident angle is 45?, the accelerating voltage of electrons is 22 kV, the vacuum degree is less than 3?10.sup.?3 Pa, and the deposition rate is 100 nm/min.

[0146] (2) After the Al coating is prepared, it is placed in the air and heated at 100? C. for oxidation to obtain an Al.sub.2O.sub.3 coating with the thickness less than 10 ?m, which means the antioxidant layer.

[0147] (3) An oxygen-blocking propagation layer of AlTaO.sub.4 ceramic coating with a thickness of 100 ?m is prepared on the surface of the antioxidant layer through atmospheric plasma spraying. AlTaO.sub.4 spherical powder is first prepared through high-temperature solid-phase method by using Al.sub.2O.sub.3 and Ta.sub.2O.sub.5 as raw materials. Then, the AlTaO.sub.4 ceramic coating is prepared through atmospheric plasma spraying with the AlTaO.sub.4 spherical powder, and process parameters of the atmospheric plasma spraying are as follows: the spraying gun power is 42 kW, and the spraying gun distance is 120 mm, the gas flow rates of the argon and the hydrogen is 40/12 slpm and 45/10 slpm respectively, the feeding rate is 45 g/min, the spraying gun rate is 200 mm/s, and the spraying time is 5 min.

[0148] (4) A heat-insulation cooling layer with Sm.sub.3NbO.sub.7 ceramic coating with a thickness of 600 ?m is prepared through atmospheric plasma spraying on the surface of the oxygen-blocking propagation layer. Sm.sub.3NbO.sub.7 spherical powder is first prepared through the high-temperature solid-phase method by using Sm.sub.2O.sub.3 and Nb.sub.2O.sub.5 as raw materials. Then, the Sm.sub.3NbO.sub.7 ceramic coating is prepared through atmospheric plasma spraying with the Sm.sub.3NbO.sub.7 spherical powder, and process parameters of the atmospheric plasma spraying are as follows: the spraying gun power is 43 kW, and the spraying gun distance is 100 mm, the gas flow rates of the argon and the hydrogen is 42/12 slpm and 45/15 slpm respectively, the feeding rate is 40 g/min, the spraying gun rate is 100 mm/s, and the spraying time is 20 min.

Embodiment 14

[0149] Please refer to FIG. 4. In this embodiment, the lightweight material for manufacturing the UAV machine body is selected from the aluminum alloy. The aluminum alloy is used as the matrix, the coating including bonding layer, antioxidant layer, oxygen-blocking propagation layer and heat-insulation cooling layer is prepared on the matrix surface, and the specific operations are as follows:

[0150] (1) a tantalum (Ta) bonding layer with the thickness of 100 ?m is prepared on the surface of the aluminum alloy through electron beam physical vapor deposition. In the process of the deposition, the substrate temperature is 400? C., the target-base distance is 300 mm, the incident angle is 45?, the accelerating voltage of electrons is 22 kV, the vacuum degree is less than 3?10.sup.?3 Pa, and the deposition rate is 100 nm/min.

[0151] (2) After the tantalum coating is prepared, it is placed in the air and heated at 30? C. for oxidation to obtain a Ta.sub.2O.sub.5 coating with the thickness less than 10 ?m, which means the antioxidant layer.

[0152] (3) An oxygen-blocking propagation layer of YTaO.sub.4 ceramic coating with a thickness of 50 ?m is prepared on the surface of the antioxidant layer through atmospheric plasma spraying. YTaO.sub.4 spherical powder is first prepared through high-temperature solid-phase method by using Y.sub.2O.sub.3 and Ta.sub.2O.sub.5 as raw materials. Then, the YTaO.sub.4 ceramic coating is prepared through atmospheric plasma spraying with the YTaO.sub.4 spherical powder, and process parameters of the atmospheric plasma spraying are as follows: the spraying gun power is 42 kW, and the spraying gun distance is 120 mm, the gas flow rates of the argon and the hydrogen is 40/12 slpm and 45/10 slpm respectively, the feeding rate is 45 g/min, the spraying gun rate is 200 mm/s, and the spraying time is 2 min.

[0153] (4) A heat-insulation cooling layer with the Y.sub.3NbO.sub.7 ceramic coating with the thickness of 80 ?m is prepared through atmospheric plasma spraying on the surface of the oxygen-blocking propagation layer. Y.sub.3NbO.sub.7 spherical powder is first prepared through the high-temperature solid-phase method by using Y.sub.2O.sub.3 and Nb.sub.2O.sub.5 as raw materials. Then, the Y.sub.3NbO.sub.7 ceramic coating is prepared through atmospheric plasma spraying with the Y.sub.3NbO.sub.7 spherical powder, and process parameters of the atmospheric plasma spraying are as follows: the spraying gun power is 43 kW, and the spraying gun distance is 100 mm, the gas flow rates of the argon and the hydrogen is 42/12 slpm and 45/15 slpm respectively, the feeding rate is 40 g/min, the spraying gun rate is 100 mm/s, and the spraying time is 3 min.

Embodiment 15

[0154] Please refer to FIG. 4. In this embodiment, the lightweight material for manufacturing the UAV machine body is selected from TC4 titanium alloy material. The TC4 titanium alloy material is used as the matrix, the coating including bonding layer, antioxidant layer, oxygen-blocking propagation layer and heat-insulation cooling layer is prepared on a matrix surface, and the specific operations are as follows:

[0155] (1) the Zirconium-hafnium alloy (ZrHf) bonding layer with the thickness of 60 ?m is prepared on the surface of the TC4 titanium alloy through electron beam physical vapor deposition. In the process of the deposition, the substrate temperature is 400? C., the target-base distance is 300 mm, the incident angle is 45?, the accelerating voltage of electrons is 22 kV, the vacuum degree is less than 3?10.sup.?3 Pa, and the deposition rate is 100 nm/min.

[0156] (2) After a ZrHf coating is prepared, it is placed in the air and heated at 280? C. for oxidation to obtain a ZrO.sub.2/HfO.sub.2 coating with a thickness less than 10 ?m, which means the antioxidant layer.

[0157] (3) An oxygen-blocking propagation layer of (Sm.sub.1/3Yb.sub.1/3Ho.sub.1/3) TaO.sub.4 ceramic coating with a thickness of 50 ?m is prepared on the surface of the antioxidant layer through atmospheric plasma spraying. (Sm.sub.1/3Yb.sub.1/3Ho.sub.1/3) TaO.sub.4 spherical powder is first prepared through high-temperature solid-phase method by using Ho.sub.2O.sub.3, Sm.sub.2O.sub.3, Yb.sub.2O.sub.3 and Ta.sub.2O.sub.5 as raw materials. Then, the (Sm.sub.1/3Yb.sub.1/3Ho.sub.1/3) TaO.sub.4 ceramic coating is prepared through atmospheric plasma spraying with the (Sm.sub.1/3Yb.sub.1/3Ho.sub.1/3) TaO.sub.4 spherical powder, and process parameters of the atmospheric plasma spraying are as follows: the spraying gun power is 42 kW, and the spraying gun distance is 120 mm, the gas flow rates of the argon and the hydrogen is 40/12 slpm and 45/10 slpm respectively, the feeding rate is 45 g/min, the spraying gun rate is 200 mm/s, and the spraying time is 2 min.

[0158] (4) A heat-insulation cooling layer with the (Sm.sub.1/3Yb.sub.1/3Ho.sub.1/3).sub.3NbO.sub.7 ceramic coating with a thickness of 250 ?m is prepared through atmospheric plasma spraying on the surface of the oxygen-blocking propagation layer. (Sm.sub.1/3Yb.sub.1/3Ho.sub.1/3).sub.3NbO.sub.7 spherical powder is first prepared through the high-temperature solid-phase method by using Ho.sub.2O.sub.3, Sm.sub.2O.sub.3, Yb.sub.2O.sub.3 and Nb.sub.2O.sub.5 as raw materials. Then, the (Sm.sub.1/3Yb.sub.1/3Ho.sub.1/3).sub.3NbO.sub.7 ceramic coating is prepared through atmospheric plasma spraying with the (Sm.sub.1/3Yb.sub.1/3Ho.sub.1/3).sub.3NbO.sub.7 spherical powder, and process parameters of the atmospheric plasma spraying are as follows: the spraying gun power is 43 kW, and the spraying gun distance is 100 mm, the gas flow rates of the argon and the hydrogen is 42/12 slpm and 45/15 slpm respectively, the feeding rate is 40 g/min, the spraying gun rate is 100 mm/s, and the spraying time is 9 min.

Embodiment 16

[0159] Please refer to FIG. 4. In this embodiment, the lightweight material for manufacturing the UAV machine body is selected from the carbon fiber braid. The carbon fiber braid is used as the matrix, the coating including bonding layer, antioxidant layer, oxygen-blocking propagation layer and heat-insulation cooling layer is prepared on the matrix surface, and the specific operations are as follows:

[0160] (1) the calcium-magnesium (CaMg) bonding layer with the thickness of 75 ?m is prepared on the surface of the carbon fiber braid through electron beam physical vapor deposition. In a process of the deposition, the substrate temperature is 350? C., the target-base distance is 300 mm, the incident angle is 30?, the accelerating voltage of electrons is 20 kV, the vacuum degree is less than 2?10.sup.?3 Pa, and the deposition rate is 100 nm/min.

[0161] (2) After a CaMg coating is prepared, it is placed in the air and heated at 120? C. for oxidation to obtain a CaO/MgO coating with a thickness of 10 ?m, which means the antioxidant layer.

[0162] (3) An oxygen-blocking propagation layer of Yb.sub.1/4Lu.sub.1/4Y.sub.1/4Sc.sub.1/4TaO.sub.4 ceramic coating with a thickness of 75 ?m is prepared on the surface of the antioxidant layer through atmospheric plasma spraying. Yb.sub.1/4Lu.sub.1/4Y.sub.1/4Sc.sub.1/4TaO.sub.4 spherical powder is first prepared through high-temperature solid-phase method by using Yb.sub.2O.sub.3, Lu.sub.2O.sub.3, Y.sub.2O.sub.3, Sc.sub.2O.sub.3 and Ta.sub.2O.sub.5 as raw materials. Then, the Yb.sub.1/4Lu.sub.1/4Y.sub.1/4Sc.sub.1/4TaO.sub.4 ceramic coating is prepared through atmospheric plasma spraying with the Yb.sub.1/4Lu.sub.1/4Y.sub.1/4Sc.sub.1/4TaO.sub.4 spherical powder, and process parameters of the atmospheric plasma spraying are as follows: the spraying gun power is 42 kW, and the spraying gun distance is 120 mm, the gas flow rates of the argon and the hydrogen is 40/12 slpm and 45/10 slpm respectively, the feeding rate is 45 g/min, the spraying gun rate is 200 mm/s, and the spraying time is 3 min.

[0163] (4) A heat-insulation cooling layer with (Yb.sub.1/4Lu.sub.1/4Y.sub.1/4Sc.sub.1/4).sub.3NbO.sub.7 ceramic coating with a thickness of 420 ?m is prepared through atmospheric plasma spraying on the surface of the oxygen-blocking propagation layer. (Yb.sub.1/4Lu.sub.1/4Y.sub.1/4Sc.sub.1/4).sub.3NbO.sub.7 spherical powder is first prepared through the high-temperature solid-phase method by using Yb.sub.2O.sub.3, Lu.sub.2O.sub.3, Y.sub.2O.sub.3, Sc.sub.2O.sub.3 and Nb.sub.2O.sub.5 as raw materials. Then, the (Yb.sub.1/4Lu.sub.1/4Y.sub.1/4Sc.sub.1/4).sub.3NbO.sub.7 ceramic coating is prepared through atmospheric plasma spraying with the (Yb.sub.1/4Lu.sub.1/4Y.sub.1/4Sc.sub.1/4).sub.3NbO.sub.7 spherical powder, and process parameters of the atmospheric plasma spraying are as follows: the spraying gun power is 43 kW, and the spraying gun distance is 120 mm, the gas flow rates of the argon and the hydrogen is 42/12 slpm and 45/15 slpm respectively, the feeding rate is 50 g/min, the spraying gun rate is 100 mm/s, and the spraying time is 15 min.

Comparative Embodiment 5

[0164] The carbon fiber braid material is used as the matrix in this comparative embodiment, a coating including bonding layer is prepared on the matrix surface according to a method of the embodiment 11.

Comparative Embodiment 6

[0165] The titanium alloy is used as the matrix in this comparative embodiment, a coating including bonding layer and antioxidant layer is prepared on the matrix surface according to the method of the embodiment 11.

Comparative Embodiment 7

[0166] The carbon fiber braid material is used as the matrix in this comparative embodiment, a coating including bonding layer, antioxidant layer and oxygen-blocking propagation layer is prepared on the matrix surface according to the method of the embodiment 11.

[0167] Coating system structures of above-mentioned embodiments 11-16 and the comparative embodiments 5-7 and specific material compositions and thicknesses of each layer of coating are shown in Table 5. In order to detect protective and heat insulation effect of the surface coating including different material systems on lightweight materials, an ultimate working temperature (high temperature resistance performance), a corresponding heat insulation cooling gradient and an oxidation resistance are tested. A specific test process is to heat the surface of the material prepared with different coatings and observe a melting temperature of the material, thereby obtaining the high temperature resistance performance (ultimate working temperature) of the material. The temperature is kept at the ultimate working temperature for 60 seconds, and a temperature of a contact interface between the lightweight material and the coating is measured through a thermocouple. A temperature difference between the surface temperature and an interface temperature is the heat insulation cooling gradient. A mass of the material before and after the test is measured and the mass before and after the test are Z1 and Z2. Then an oxidation weight gain rate of the material is (Z2?Z1)/Z1?100%. The greater the weight gain rate, the worse its anti-oxidation performance. (A carbon fiber oxidation temperature used in the embodiment of the disclosure is 350? C., an ultimate working temperature of the aluminum alloy is 660? C., and an ultimate working temperature of the titanium alloy is 520? C.)

TABLE-US-00005 TABLE 5 oxygen-blocking reflective bonding antioxidant propagation heat insulation matrix layer layer layer layer Embodiment carbon Si 50 ?m SiO.sub.2 YbTaO.sub.4 50 ?m La.sub.3NbO.sub.7 300 ?m 11 fiber Embodiment titanium Al 50 ?m Al.sub.2O.sub.3 Yb.sub.0.5Lu.sub.0.5TaO.sub.4 50 ?m Y.sub.3NbO.sub.7 350 ?m 12 alloy Embodiment aluminum Al 20 ?m Al.sub.2O.sub.3 AlTaO.sub.4 100 ?m Sm.sub.3NbO.sub.7 600 ?m 13 alloy Embodiment aluminum Ta 100 ?m Ta.sub.2O.sub.5 YTaO.sub.4 50 ?m Y.sub.3NbO.sub.7 80 ?m 14 alloy Embodiment titanium ZrHf 60 ?m ZrO.sub.2/HfO.sub.2 (Sm.sub.1/3Yb.sub.1/3Ho.sub.1/3)TaO.sub.4 50 ?m (Sm.sub.1/3Yb.sub.1/3Ho.sub.1/3).sub.3NbO.sub.7 250 ?m 15 alloy Embodiment carbon CaMg 75 ?m CaO/MgO Yb.sub.1/4Lu.sub.1/4Y.sub.1/4Sc.sub.1/4TaO.sub.4 75 ?m (Yb.sub.1/4Lu.sub.1/4Y.sub.1/4Sc.sub.1/4).sub.3NO.sub.7 420 ?m 16 fiber Comparative carbon Si 50 ?m embodiment 5: fiber Comparative carbon Si 50 ?m SiO.sub.2 embodiment 6: fiber Comparative carbon Si 50 ?m SiO.sub.2 YbTaO.sub.4 20 ?m embodiment 7: fiber

[0168] According to the above methods, the ultimate working temperatures, cooling gradients, oxidation weight gain rates and other properties of embodiments 11-16 and comparative embodiments 5-7 are respectively tested. The results are shown in Table 6 below:

TABLE-US-00006 TABLE 6 ultimate working cooling oxidation weight temperature gradient gain rate Embodiment 11 520? C. 170? C. 3.3% Embodiment 12 1106? C. 586? C. 1.5% Embodiment 13 1270? C. 610? C. 1.0% Embodiment 14 982? C. 322? C. 1.6% Embodiment 15 967? C. 447? C. 5.6% Embodiment 16 698? C. 348? C. 6.9% Comparative 410? C. 60? C. ?10.9% embodiment 5: Comparative 435? C. 85? C. ?6.5% embodiment 6: Comparative 517? C. 167? C. ?3.2% embodiment 7:

Experimental Results and Analysis:

[0169] It may be seen from Table 6, in embodiments 11-16, after a complete coating system is prepared on the surface of the lightweight material matrix, the ultimate working temperature of the lightweight material has been greatly improved, and its thermal insulation and cooling effect is significant. Moreover, through adjusting the thickness of each coating, the heat insulation cooling gradient can be effectively controlled, so that the above-mentioned lightweight materials can be used for a long time at higher temperatures, and a resistance to high-temperature oxidative and ablation of the materials can be effectively improved. Comparing embodiment 11 with comparative embodiments 5-7, it may be seen that compared with comparative embodiments 5-7, the material of embodiment 11 has a higher ultimate working temperature, better thermal insulation and cooling effect, and stronger anti-oxidation ability. A material mass reduction in comparative embodiment 5 is very obvious, which is due to a mass reduction caused by an oxidation and sublimation of the carbon fiber. Material properties of comparative embodiment 6 are better than those of comparative embodiment 5, and material properties of comparative embodiment 7 are better than those of comparative embodiment 6, which indicates that settings of the oxygen-blocking propagation layer and the heat-insulation cooling layer can further improve the high temperature resistance, heat insulation and cooling capabilities, and oxidation resistance.

Embodiment 17

[0170] Please refer to FIG. 5. The disclosure further provides the UAV. The UAV includes the UAV machine body, the central control module 3, and an information acquisition module 1, a temperature detection module 2, a pressure control module 4, a UAV module 5 and an efficient fire protection module 6 respectively connected with the central control module 3.

[0171] The information acquisition module 1 is configured to obtain relevant information of a target fire extinguishing point including time of fire occurrence, fire location, fire type and fire estimation level, then form a first data set, and send the first data set to the central control module.

[0172] The temperature detection module 2 is configured to collect a temperature distribution of a fire scene to form a second data set, and send the second data set to the central control module.

[0173] The pressure control module 4 is configured to monitor a pressure state of an efficient fire extinguishing device and carry out a real-time control of the efficient fire extinguishing device.

[0174] The UAV machine body is made of lightweight material, and the lightweight material is selected from at least one of the carbon fiber braid, the titanium alloy and the aluminum alloy. The lightweight material is used as the matrix, and the method of the above-mentioned embodiment 11-16 is used to form the bonding layer, the antioxidant layer, the oxygen-blocking propagation layer and the heat insulation layer on the matrix in turn. Internal parts of the UAV and a lightweight material machine body are combined by ethylene propylene rubber. A specific production process is that the ethylene propylene rubber is covered on the surface of the UAV, and then the lightweight material casing of the UAV machine body may be buckled on its surface. Methods of embodiments 1-10 may also be used to form a coating on the resin-based composite matrix or the ceramic-based composite matrix, and then the matrix is arranged on the surface of the UAV machine body. The thickness of the bonding layer is from 20 ?m to 200 ?m, the thickness of the oxygen-blocking propagation layer is from 20 ?m to 100 ?m, the thickness of the heat-insulation cooling layer is from 80 ?m to 1000 ?m, and the thickness of the antioxidant layer is less than 20 ?m.

[0175] Please refer to FIG. 6. The UAV module 5 includes a remote controller, an aircraft power control device and a fire-extinguishing UAV. The remote controller is configured to control the fire-extinguishing UAV to perform a fire-extinguishing task issued by the central control module. The aircraft power control device is configured to provide flight power for the fire-extinguishing UAV, and the fire-extinguishing UAV is configured to perform the fire-extinguishing task to put out fires at target fire locations.

[0176] The efficient fire protection module 6 includes an efficient fire-extinguishing device and a safety helmet. The efficient fire-extinguishing device is configured to load efficient compressible foam fire extinguishing agent as fire-extinguishing raw materials to extinguish the fire scene, the efficient compressible foam fire extinguishing agent is non-toxic, harmless, and a reactant obtained by reacting with a combustion matter is also a non-toxic, harmless substance. The safety helmet is used to protect the efficient fire extinguishing device and includes an inner layer and an outer layer. The inner layer is made of a fire-resistant and explosion-proof polymer material, and the outer layer is made of corrosion-resistant material.

[0177] The central control module 3 includes a data storage unit 7, a task issuing unit 8 and an analysis processing unit 9. The data storage unit 7 is configured to store the first data set and the second data set. The task issuing unit 8 is configured to issue the fire-extinguishing task to the UAV module according to the first data set. The analysis processing unit 9 is configured to analyze and process second data to obtain an analysis result of location information of a fire source and location information of a point before a fire spreading. A temperature changing spectrum is obtained according to a temperature detection situation, a detailed on-site temperature distribution is obtained in combination with a Beidou positioning system, specific positions of the fire source and the point before the fire spreading are found, and then a fire extinguishing is carried out according to a preset fire extinguishing strategy.

[0178] The temperature detection module is utilized to collect the temperature distribution of the target fire extinguishing point, and analyze the fire source and the specific point location information before the fire spreading.

[0179] The pressure control module is utilized to control the efficient fire protection module for a targeted fire extinguishing, first extinguish the fire at a point before the fire spreading, and then extinguish the fire source.

[0180] The UAV machine body further includes a load-bearing board, a stabilizing bracket, a balancing stabilizer and an aircraft propeller. The load-bearing board is configured to carry a UAV aircraft. The stabilizing bracket is configured to protect a safety of a fire extinguisher. The balancing stabilizer is configured to maintain the UAV aircraft in a balanced and stable state, and the aircraft propeller is configured to provide a flight lift for the UAV aircraft. Moreover, the aircraft propeller is woven from high-strength, low-quality carbon fiber, and a surface of the propeller is coated with a lightweight coating that is resistant to high temperatures.

[0181] A specific process of the embodiment is as follows:

[0182] First, the information acquisition module 1 obtains information of the target fire extinguishing point such as the time of fire occurrence, the fire location, the fire type and the fire estimation level, forms the first data set, and sends the first data set to the central control module.

[0183] Second, the data storage unit of the central control module 3 receives and stores the first data set and then the task issuing unit issues the fire-extinguishing task to the UAV module according to all of information of the first data set.

[0184] Third, after the remote controller of UAV module 5 receives the fire-extinguishing task, the fire-extinguishing UAV is controlled to begin to execute the fire-extinguishing task. Firstly, the aircraft power control device provides flight power for the fire-extinguishing UAV, and then the remote controller controls a flight distance and a flight attitude of the fire-extinguishing UAV, and controls the fire-extinguishing UAV to fly to the target fire extinguishing point from a fire-extinguishing center.

[0185] Fourth, the temperature detection module 2 begins to work, and collects the on-site temperature distribution of a fire scene and forms the second data set. Then the second data set is sent to the central control module, and the analysis processing unit of the central control module analyzes and processes the second data set, obtains the temperature changing spectrum according to the temperature detection situation, obtains the detailed on-site temperature distribution in combination with the Beidou positioning system, and finds a specific position of the fire source and the point before the fire spreads.

[0186] Fifth, the pressure control module 4 controls the efficient fire extinguishing device of the efficient fire protection module to spray the efficient compressible foam fire extinguishing agent to carry out a targeted fire extinguishing. First the fire is extinguished at the point before it spreads, and then the source of the fire is extinguished. After the fire extinguishing task is completed, the central control module 3 issues a returning control command, the fire-extinguishing UAV is controlled by the remote controller to fly back to the fire-extinguishing center, and the fire extinguishing task is over.

[0187] In recent years, research and application of rescue UAVs have not been in-depth and promoted, but they have been widely used in all aspects of society, especially in a field of firefighting, where UAVs are increasingly used. In recent years, fires have occurred frequently in southwest China, forest and grassland areas, the fires have come and developed rapidly, and the losses in areas with large areas of fire are more serious. The traditional fire extinguisher has a significant fire extinguishing effect for the fire of close range or small fire source, and is generally powerless for the fire of long distance and large fire. The fire-extinguishing UAV in the prior art, generally carries the fire extinguisher and flies to the fire location, sprays fire extinguishing agent to extinguish the fire in advance, which plays a role in containing fire in time. Compared with a fire brigade, an advantage is only that a fire extinguishing response speed is fast, and the UAVs can quickly arrive at the fire scene to extinguish the fire. However, its targeted fire extinguishing ability to the fire is not strong, a fire extinguishing effect is not good, and a whole fire extinguishing process is not intelligent and efficient enough.

[0188] While in the embodiment of the disclosure, it is not only intelligently issue fire-extinguishing task according to the information such as the time of fire occurrence, the fire location, the fire type, and the fire estimation level of the target fire extinguishing point, at the same time, after the fire-extinguishing UAV arrives at the fire scene, it is not directly unplanned to carry out fire extinguishing work, but also the fire-extinguishing UAV first detects the temperature distribution of the fire scene by the temperature detection module, obtains the temperature changing spectrum, obtains the detailed on-site temperature distribution in combination with the Beidou positioning system, and finds the specific locations of the fire source and the point before the fire spreads, and then carries out an efficient targeted and efficient fire extinguishing, which has better fire extinguishing effect, higher efficiency and more intelligence. The efficient compressible foam fire extinguishing agent used during fire extinguishing is non-toxic, harmless, and a reactant obtained by reacting with a combustion matter is also a non-toxic, harmless substance, which can effectively ensure a life safety of animals, evacuees and firefighters at the fire scene. A composition and structure of the UAV are made of high-temperature resistant materials, which can enable the fire-extinguishing UAV to continue to work in a high-temperature environment, and the fire-extinguishing UAV will not be deformed or burned, which further guarantees the fire-extinguishing effect.

Embodiment 18

[0189] This embodiment is basically the same as embodiment 17, and a difference is that: when the fire is larger, and a long-distance fire extinguishing effect is not significant, the temperature detection module detects a precise position of the fire source, and the UAV module is controlled by the remote controller to fly to the fire source. The pressure control module controls the efficient fire extinguishing device to blast, and the fire source is blasted and extinguished at a fixed point at a fixed time, so that the fire is quickly controlled.

[0190] A specific process of this embodiment is the same as that of embodiment 17, with the following differences:

[0191] Fifth, the pressure control module 4 controls the efficient fire extinguishing device of the efficient fire protection module to spray the efficient compressible foam fire extinguishing agent to carry out a targeted fire extinguishing. First the fire is extinguished at the point before it spreads, and then the source of the fire is extinguished. If the long-distance fire extinguishing effect is not significant, the fire is still gradually increasing, the temperature detection module detects the precise position of the fire source, and then the remote controller controls the UAV module to fly to the fire source. The pressure control module controls the efficient fire extinguishing device for blasting, and the fire source is blasted and extinguished at the fixed point at the fixed time, so as to quickly control the fire. Then a backup fire-extinguishing UAV will be dispatched to continue extinguishing the remaining fires until all open flames are extinguished and the fire-extinguishing task is over.

[0192] When the fire extinguishing UAV is carrying out the long-distance fire extinguishing, if there is an emergency, such as a sudden increase in wind volume causes the fire to gradually increase, and the fire cannot be controlled by the long-distance fire extinguishing, a blasting fire extinguishing is directly used to quickly and efficiently extinguish the fire source, so as to avoid more serious losses caused by a continued expansion of the fire. Although blasting and extinguishing will lose the fire-extinguishing UAV, it can control an out-of-control fire in time, reduce an impact of the fire, and ensure the safety of the evacuees and firefighters. Its value is still greater than its economic value of a fire-extinguishing UAV itself.

Embodiment 19

[0193] This embodiment is basically the same as embodiment 17, and a difference is that: after the fire-extinguishing UAV completes the fire-extinguishing task and extinguishes all the open flames at the fire scene, the temperature detection module collects the temperature distribution of the scene again, and determines a point with a temperature greater than 60? C. as a re-ignition point where the fire may re-ignite, and then the fire-extinguishing UAV carries out the targeted fire extinguishing on these re-ignition points one by one until its temperature is reduced to below 40? C.

[0194] A specific process of this embodiment is the same as that of embodiment 17, with the following differences:

[0195] Fifth, the pressure control module 4 controls the efficient fire extinguishing device of the efficient fire protection module to spray the efficient compressible foam fire extinguishing agent to carry out a targeted fire extinguishing. First the fire is extinguished at the point before it spreads, and then the source of the fire is extinguished. After the fire extinguishing task is completed, the temperature detection module collects the temperature distribution of the scene again, and determines the point with the temperature greater than 60? C. as the re-ignition point where the fire may re-ignite. The remote controller of the UAV module 5 controls the fire-extinguishing UAV to fly one by one to 2 meters directly above these re-ignition points, and then the fire-extinguishing UAV carries out the targeted fire extinguishing on these re-ignition points one by one until its temperature is reduced to below 40? C. Finally, the central control module 3 issues a returning control command, the fire-extinguishing UAV is controlled by the remote controller to fly back to the fire-extinguishing center, and the fire extinguishing task is over.

[0196] Combined with an actual situation, in many cases such as a mountain fire or a forest fire, soon after the open flames are extinguished, there will be a re-ignition phenomenon. Therefore, after the fire-extinguishing UAV extinguishes all the open flames, the temperature detection module detects all the points where the temperature is higher than 60? C., and a secondary fire extinguishing is carried out to avoid the re-ignition phenomenon which may cause more serious losses. At the same time, it can also effectively improve the fire extinguishing effect of the fire-extinguishing UAV.

Embodiment 20

[0197] This embodiment is basically the same as embodiment 17, and a difference is that: an intelligent fire-extinguishing UAV system further includes a display module, configured to display the fire extinguishing on-site scene and remaining power of the fire extinguishing UAV in real time.

[0198] A specific process of this embodiment is the same as that of embodiment 17, with the following differences:

[0199] Fifth, the pressure control module 4 controls the efficient fire extinguishing device of the efficient fire protection module to spray the efficient compressible foam fire extinguishing agent to carry out a targeted fire extinguishing. First the fire is extinguished at the point before it spreads, and then the source of the fire is extinguished. During a fire extinguishing process, the display module can display a fire extinguishing on-site scene and remaining power of the fire extinguishing UAV in real time. After the fire extinguishing task is completed, the central control module issues a returning control command, the fire-extinguishing UAV is controlled by the remote controller to fly back to the fire-extinguishing center, and the fire extinguishing task is over.

[0200] Through the display module, the fire extinguishing on-site scene can be viewed in real time, so that a staff can clearly understand a fire extinguishing progress and the fire extinguishing effect. If there is an emergency, they can also take timely countermeasures, and at the same time can check the remaining power of the fire-extinguishing UAV, so as to recall the fire-extinguishing UAV in time when the power is about to run out, which avoids the UAV from crashing due to loss of power.

[0201] The above embodiments only illustrate principles and effects of the disclosure, but are not intended to limit the disclosure. Anyone familiar with this technology may modify or change the above embodiments without departing from a scope of the disclosure. Therefore, all equivalent modifications or changes made by those with ordinary knowledge in the technical field without departing from the technical ideas disclosed in the disclosure shall still be covered by the claims of the disclosure.