Patent Application
20240263314
The disclosure relates to a technical field of material application, and in particular to a UAV surface coating, a preparation method thereof and a UAV.
With the deepening of the research and application of the Unmanned Aerial Vehicle (UAV), its maximum take-off weight has reached more than ten tons. A use of the unmanned low-altitude aerial vehicles at the fire rescue site for fire extinguishing, personnel rescue, communication connections and material delivery and other tasks can effectively reduce the danger of traditional pilots when performing the tasks, at the same time, the unmanned low-altitude aerial vehicles are with small sizes, easy to operate, and have small restrictions on take-off sites when carrying out the fire rescue in a city, which is more suitable for modern development trends. It is necessary to effectively reduce the weight of the aircraft itself, and at the same time increase what it can carry. However, in the prior art, different kinds of resin-based composites or ceramic-based composites are usually used to manufacture the machine body of the low-altitude aircraft. The resin-based composites have the problems of low melting point, insufficient high temperature resistance and easy to be corroded by smoke at the fire site, which leads to failure, thus limiting the applications in large fires scenes and high-temperature fire scenes. While, the ceramic-based composites are silicon carbide fiber-reinforced silicon carbide, carbon fiber-reinforced carbon, carbon fiber-reinforced silicon carbide and silicon carbide fiber-reinforced carbon ceramic-based composites with a melting point of more than 2000° C., and have advantages of low density, strong plasticity and high specific strength similar to the resin-based composites. However, the disadvantage of the above-mentioned ceramic matrix composites is that they will be oxidized and fail when exposed to air at high temperatures.
In addition, 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. Moreover, the conventional fire extinguishing UAVs are not very capable of targeted fire-extinguishing at the fire site, and cannot carry out a long-distance, accurate and efficient fire-extinguishing at the fire site.
The disclosure provides a UAV surface coating, a preparation method thereof and the UAV, which mainly solves problems of conventional UAVs with poor high temperature resistance and poor long-distance accurate fire extinguishing capability.
In order to achieve the above purpose and other purposes, a technical scheme of the disclosure is as follows.
The disclosure provides the UAV surface coating, and the coating at least includes 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 the 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 μm to 200 μm, a thickness of the oxygen-blocking propagation layer is from 20 μm to 200 μm, and a thickness of the heat-insulation cooling layer is from 80 μm to 1000 μm.
In some embodiments, 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.
In some embodiments, 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.
In some embodiments, 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.
In some embodiments, 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, aluminum, calcium, silicon, tantalum, vanadium, yttrium, zirconium, hafnium, silicon, niobium, molybdenum and tungsten.
In some embodiments, 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 μm to 50 μm.
In some embodiments, a thermal expansion coefficient of the oxygen-blocking propagation layer is between 3×10−6 K−1 and 6×10−6 K, a thermal expansion coefficient of the thermal expansion coefficient buffer layer is between 6×10−6 K−1 and 9××10−6 K−1, and a thermal expansion coefficient of the heat-insulation cooling layer is between 9×10−6 K−1 and 11×10−6 K−1.
In some embodiments, the thermal expansion coefficient buffer layer is a ceramic of RETa3O9, wherein RE is composed of one or more rare earth elements.
In some embodiments, the antioxidant layer is one or more mixtures of Al2O3, SiO2, Ta2O5, Nb2O5, ZrO2, Mo2O5 and WO3 or a combination thereof.
In some embodiments, the oxygen-blocking propagation layer is a rare earth tantalate ceramic material, or a rare earth tantalum/niobate ceramic material.
In some embodiments, the rare earth tantalate ceramic material is spherical powder of ATaO4, and A is Al, Fe or the rare earth element;
the rare earth tantalum/niobate ceramic is a ceramic material of RETa1-xNbxO4, wherein RE is one or more of the rare earth elements, and 0<x<1.
In some embodiments, 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.
In some embodiments, the rare earth niobate ceramic material is spherical powder of RE3NbO7;
The disclosure further provides a preparation method of the UAV surface coating, including:
In some embodiments, preparing a heat-insulation cooling layer on the surface of the oxygen-blocking propagation layer through atmospheric plasma spraying on the ceramic-based composite matrix further includes:
In some embodiments, process parameters of the cold spraying include 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;
In some embodiments, wherein, process parameters of the electron beam physical vapor deposition include 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 5×10−3 Pa, and a deposition rate is from 50 nm/min to 150 nm/min, wherein the substrate includes: the ceramic-based composite matrix, the resin-based composite matrix or the UAV machine body.
In some embodiments, placing the bonding layer in air for oxidation to form an antioxidant layer includes:
The disclosure further provides a UAV. The UAV includes a UAV machine body, a central control module, and an information acquisition module, a temperature detection module, a pressure control module, a UAV module and an efficient fire protection module respectively connected with the central control module;
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 μm to 200 μm, a thickness of the oxygen-blocking propagation layer is from 20 μm to 200 μm, and a thickness of the heat-insulation cooling layer is from 80 μm to 1000 μm.
In some embodiments, the preset fire extinguishing strategy includes:
In some embodiments, the analysis results obtained by the analyzing and processing of the second data set about the fire source and the point before the fire spreading are that 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, and specific positions of the fire source and the point before the fire spreading are found.
In some embodiments, the UAV machine body 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.
In some embodiments, the aircraft propeller is made of carbon fiber.
In some embodiments, the relevant information includes a time of fire occurrence, a fire location, a fire type, and a fire estimation level.
In some embodiments, the fire-extinguishing raw material is an efficient compressible foam fire extinguishing agent.
In some embodiments, 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.
In some embodiments, the safety helmet 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.
In some embodiments, the UAV 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.
As mentioned above, the application provides the UAV surface coating, preparation method thereof and UAV, which has the following beneficial effects.
The disclosure uses the lightweight material for the UAV machine body, and the machine body is covered with the coating. The coating at least includes the bonding layer, the antioxidant layer, an oxygen-blocking layer and the heat-insulation cooling layer, which can provide the UAV with effects of thermal insulation and cooling, oxygen propagation resistance and anti-oxidation, and effectively improve an ultimate working temperature and oxidation resistance of the lightweight material, so that the UAV can be used in high-temperature and high-corrosive environments such as fire rescue, realize a low-altitude flight, and extend its duration life. When using the above-mentioned coating as a material of the machine body of the UAV for fire rescue, advantages such as low thermal conductivity and multi-layer structure to improve the thermal insulation and cooling effect can ensure that internal parts of the machine body are under its ultimate service temperature in a service environment of the fire scene, so as to serve effectively for a long time.
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.
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.
The disclosure provides a UAV surface coating and a preparation method thereof. Please refer to
Specifically: (1) a silicon (Si) bonding layer with a thickness of 30 μm 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 2×10−3 Pa, and a deposition rate is 100 nm/min.
(2) The silicon (Si) bonding layer is placed in air for oxidation to obtain a SiO2 antioxidant layer with a thickness of less than 1 μm. The oxygen-blocking propagation layer of LuTa0.5Nb0.5O4 ceramic layer with a thickness of 50 μm is prepared by atmospheric plasma spraying on a surface of the antioxidant layer, and LuTa0.5Nb0.5O4 spherical powder is first prepared through high-temperature solid-phase method by using Lu2O3, Nb2O5 and Ta2O5 as raw materials. Argon is used as protective gas and hydrogen is used as combustion gas in a process of spraying the LuTa0.5Nb0.5O4 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.
(3) A reflective heat insulation layer with Lu3Ta0.3Nb0.7O7 ceramic coating with a thickness of 1000 μm is prepared through atmospheric plasma spraying on a surface of the ceramic oxygen-blocking propagation layer of LuTa0.5Nb0.5O4, and Lu3Ta0.3Nb0.7O7 spherical powder is prepared through the high-temperature solid-phase method by using Lu2O3, Nb2O5 and Ta2O5 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 Lu3Ta0.3Nb0.7O7 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.
The disclosure provides the UAV surface coating and the preparation method thereof. Please refer to
Specifically: (1) an aluminum (Al) bonding layer with the thickness of 100 μm 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 2×10−3 Pa, and the deposition rate is 100 nm/min.
(2) The aluminum (Al) bonding layer is placed in the air for oxidation to obtain an Al2O3 antioxidant layer with a thickness of less than 1 μm. The oxygen-blocking propagation layer of Tm1/4Yb1/4Lu1/4Sc1/4Ta0.8Nb0.2O4 ceramic layer with a thickness of 75 μm is prepared by atmospheric plasma spraying on the surface of the antioxidant layer. Tm1/4Yb1/4Lu1/4Sc1/4Ta0.8Nb0.2O4 spherical powder is first prepared through high-temperature solid-phase method by using Sc2O3, Tm2O3, Yb2O3, Lu2O3, Nb2O5 and Ta2O5 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 Tm1/4Yb1/4Lu1/4Sc1/4Ta0.8Nb0.2O4 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.
(3) A reflective heat insulation layer with Y3Ta0.5Nb0.5O7 ceramic coating with a thickness of 100 μm is prepared through atmospheric plasma spraying on a surface of the ceramic oxygen-blocking propagation layer of Tm1/4Yb1/4Lu1/4Sc1/4Ta0.8Nb0.2O4. Y3Ta0.5Nb0.5O7 spherical powder is prepared through the high-temperature solid-phase method by using Y2O3, Nb2O5 and Ta2O5 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 Lu3Ta0.3Nb0.7O7 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.
The disclosure provides the UAV surface coating and the preparation method thereof. Please refer to
Specifically: (1) a tantalum niobium molybdenum alloy bonding layer with the thickness of 50 μm 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 2×10−3 Pa, and the deposition rate is 100 nm/min.
(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 μm. The oxygen-blocking propagation layer of YTa0.5Nb0.5O4 ceramic layer with a thickness of 75 μm is prepared by atmospheric plasma spraying on the surface of the antioxidant layer, and YTa0.5Nb0.5O4 spherical powder is first prepared through the high-temperature solid-phase method by using Y2O3, Nb2O5 and Ta2O5 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 YTa0.5Nb0.5O4 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.
(3) A reflective heat insulation layer with YGdDyTa0.5Nb0.5O7 ceramic coating with a thickness of 600 μm is prepared through atmospheric plasma spraying on a surface of the ceramic oxygen-blocking propagation layer of YTa0.5Nb0.5O4. YGdDyTa0.5Nb0.5O7 spherical powder is prepared through the high-temperature solid-phase method by using Dy2O3, Gd2O3, Y2O3, Nb2O5 and Ta2O5 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 YGdDyTa0.5Nb0.5O7 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.
The disclosure provides the UAV surface coating and the preparation method thereof. Please refer to
Specifically: (1) a zirconium-silicon alloy bonding layer with the thickness of 50 μm 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 2×10−3 Pa, and the deposition rate is 100 nm/min.
(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 μm. The oxygen-blocking propagation layer of SmTa0.2Nb0.8O4 ceramic layer with a thickness of 60 μm is prepared by atmospheric plasma spraying on the surface of the antioxidant layer, and SmTa0.2Nb0.8O4 spherical powder is first prepared through the high-temperature solid-phase method by using Sm2O3, Nb2O5 and Ta2O5 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 SmTa0.2Nb0.8O4 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.
(3) A reflective heat insulation layer with SmTa0.2Nb0.8O4 ceramic coating with a thickness of 720 μm is prepared through atmospheric plasma spraying on a surface of the ceramic oxygen-blocking propagation layer of SmEuGdTa0.2Nb0.8O7. SmEuGdTa0.2Nb0.8O7 spherical powder is prepared through the high-temperature solid-phase method by using Sm2O3, Gd2O3, Eu2O3, Nb2O5 and Ta2O5 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 SmEuGdTa0.2Nb0.8O7 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.
The disclosure provides the UAV surface coating and the preparation method thereof. Please refer to
Specifically: (1) the silicon (Si) bonding layer with the thickness of 30 μm 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 2×10−3 Pa, and the deposition rate is 100 nm/min.
(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 μm. The oxygen-blocking propagation layer of LuTa0.5Nb0.5O4 ceramic layer with the thickness of 50 μm is prepared by atmospheric plasma spraying on the surface of the antioxidant layer, and LuTa0.5Nb0.5O4 spherical powder is first prepared through high-temperature solid-phase method by using Lu2O3, Nb2O5 and Ta2O5 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 LuTa0.5Nb0.5O4 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.
(3) A reflective heat insulation layer with Lu3Ta0.3Nb0.7O7 ceramic coating with the thickness of 500 μm is prepared through atmospheric plasma spraying on the surface of the ceramic oxygen-blocking propagation layer of LuTa0.5Nb0.5O4. Lu3Ta0.3Nb0.7O7 spherical powder is prepared through the high-temperature solid-phase method by using Lu2O3, Nb2O5 and Ta2O5 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 Lu3Ta0.3Nb0.7O7 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.
The disclosure provides the UAV surface coating and the preparation method thereof. Please refer to
Specifically: (1) the aluminum (Al) bonding layer with the thickness of 100 μm 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 2×10−3 Pa, and the deposition rate is 100 nm/min.
(2) The aluminum (Al) bonding layer is placed in the air for oxidation to obtain the Al2O3 antioxidant layer with the thickness of less than 1 μm. The oxygen-blocking propagation layer of Tm1/4Yb1/4Lu1/4Sc1/4Ta0.8Nb0.2O4 ceramic layer with the thickness of 75 μm is prepared by atmospheric plasma spraying on the surface of the antioxidant layer. The Tm1/4Yb1/4Lu1/4Sc1/4Ta0.2Nb0.2O4 spherical powder is first prepared through high-temperature solid-phase method by using Sc2O3, Tm2O3, Yb2O3, Lu2O3, Nb2O5 and Ta2O5 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 Tm1/4Yb1/4Lu1/4Sc1/4Ta0.8Nb0.2O4 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.
(3) The reflective heat insulation layer with Y3Ta0.5Nb0.5O7 ceramic coating with the thickness of 500 μm is prepared through atmospheric plasma spraying on a surface of the ceramic oxygen-blocking propagation layer of Tm1/4Yb1/4Lu1/4Sc1/4Ta0.2Nb0.2O4. Y3Ta0.5Nb0.5O7 spherical powder is prepared through the high-temperature solid-phase method by using Y2O3, Nb2O5 and Ta2O5 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 Lu3Ta0.3Nb0.7O7 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.
The disclosure provides the UAV surface coating and the preparation method thereof. Please refer to
Specifically: (1) the silicon (Si) bonding layer with the thickness of 30 μm 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 2×10−3 Pa, and the deposition rate is 100 nm/min.
(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 μm. The oxygen-blocking propagation layer of LuTa0.5Nb0.5O4 ceramic layer with the thickness of 50 μm is prepared by atmospheric plasma spraying on the surface of the antioxidant layer, and the LuTa0.5Nb0.5O4 spherical powder is first prepared through high-temperature solid-phase method by using Lu2O3, Nb2O5 and Ta2O5 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 LuTa0.5Nb0.5O4 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.
The disclosure provides the UAV surface coating and the preparation method thereof. Please refer to
Specifically: (1) The oxygen-blocking propagation layer of Tm1/4Yb1/4Lu1/4Sc1/4Ta0.2Nb0.2O4 ceramic layer with the thickness of 75 μm is prepared by atmospheric plasma spraying on a surface of the matrix. The Tm1/4Yb1/4Lu1/4Sc1/4Ta0.2Nb0.2O4 spherical powder is first prepared through high-temperature solid-phase method by using Sc2O3, Tm2O3, Yb2O3, Lu2O3, Nb2O5 and Ta2O5 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 Tm1/4Yb1/4Lu1/4Sc1/4Ta0.8Nb0.2O4 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.
(2) The reflective heat insulation layer with Y3Ta0.5Nb0.5O7 ceramic coating with the thickness of 500 μm is prepared through atmospheric plasma spraying on a surface of the ceramic oxygen-blocking propagation layer of Tm1/4Yb1/4Lu1/4Sc1/4Ta0.8Nb0.2O4. Y3Ta0.5Nb0.5O7 spherical powder is prepared through the high-temperature solid-phase method by using Y2O3, Nb2O5 and Ta2O5 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 Y3Ta0.5Nb0.5O7 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.
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 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
The disclosure provides the UAV surface coating and the preparation method thereof. Please refer to
Specifically: (1) a tantalum (Ta) bonding layer with the thickness of 100 μm 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 Ta2O5 with a thickness less than 1 μm on its surface.
(2) The oxygen-blocking propagation layer of YbTaO4 ceramic material with a thickness of 35 μm is prepared by atmospheric plasma spraying on a surface of the antioxidant layer of dense tantalum oxide Ta2O5. YbTaO4 spherical powder is first prepared through high-temperature solid-phase method by using Yb2O3 and Ta2O5 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.
(3) The thermal expansion coefficient buffer layer with Tm Ta3O9 ceramic coating with the thickness of 30 μm is prepared through atmospheric plasma spraying on a surface of the ceramic oxygen-blocking propagation layer of YbTaO4. Tm Ta3O9 spherical powder is first prepared through the high-temperature solid-phase method by using Tm2O3 and Ta2O5 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.
(4) A heat-insulation cooling layer with Tm3TaO7 ceramic coating with the thickness of 200 μm is prepared through atmospheric plasma spraying on a surface of the ceramic thermal expansion coefficient buffer layer of Tm Ta3O9. Tm3TaO7 spherical powder is first prepared through high-temperature solid-phase method by using Tm2O3 and Ta2O5 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.
The disclosure provides the UAV surface coating and the preparation method thereof. Please refer to
Specifically: (1) a tantalum bonding layer with the thickness of 200 μm 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 Ta2O5 with a thickness less than 1 μm on its surface.
(2) The oxygen-blocking propagation layer of Yb1/2Lu1/2TaO4 ceramic coating with the thickness of 50 μm is prepared by atmospheric plasma spraying on the surface of the antioxidant layer of dense tantalum oxide Ta2O5. Yb1/2Lu1/2TaO4 spherical powder is first prepared through high-temperature solid-phase method by using Lu2O3, Yb2O3 and Ta2O5 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.
(3) The thermal expansion coefficient buffer layer with La1/3Ho1/3Tm1/3Ta3O9 ceramic coating with the thickness of 50 μm is prepared through atmospheric plasma spraying on a surface of the ceramic oxygen-blocking propagation layer of Yb1/2Lu1/2TaO4. La1/3Ho1/3Tm1/3Ta3O9 spherical powder is first prepared through the high-temperature solid-phase method by using La2O3, Ho2O3, Tm2O3 and Ta2O5 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.
(4) A heat-insulation cooling layer with Y3TaO7 ceramic coating with the thickness of 100 μm is prepared through atmospheric plasma spraying on a surface of the ceramic thermal expansion coefficient buffer layer of La1/3Ho1/3Tm1/3Ta3O9. Y3TaO7 spherical powder is first prepared through high-temperature solid-phase method by using Y2O3 and Ta2O5 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.
The disclosure provides the UAV surface coating and the preparation method thereof. Please refer to
Specifically: (1) a tantalum bonding layer with the thickness of 150 μm 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 Ta2O5 with a thickness less than 1 μm on its surface.
(2) The oxygen-blocking propagation layer of ScTaO4 ceramic coating with a thickness of 35 μm is prepared by atmospheric plasma spraying on the surface of the antioxidant layer of dense tantalum oxide Ta2O5. ScTaO4 spherical powder is first prepared through high-temperature solid-phase method by using Sc2O3 and Ta2O5 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.
(3) The thermal expansion coefficient buffer layer with LaTa3O9 ceramic coating with the thickness of 30 μm is prepared through atmospheric plasma spraying on a surface of the ceramic oxygen-blocking propagation layer of ScTaO4. LaTa3O9 spherical powder is first prepared through the high-temperature solid-phase method by using La2O3 and Ta2O5 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.
(4) A heat-insulation cooling layer with YLaDyTaO7 ceramic coating with the thickness of 1000 μm is prepared through atmospheric plasma spraying on a surface of the ceramic thermal expansion coefficient buffer layer of LaTa3O9. YLaDyTaO7 spherical powder is first prepared through high-temperature solid-phase method by using Y2O3, La2O3, Dy2O3 and Ta2O5 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.
The disclosure provides the UAV surface coating and the preparation method thereof. Please refer to
Specifically: (1) the tantalum bonding layer with the thickness of 170 μm 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 Ta2O5 with the thickness less than 1 μm on its surface.
(2) The oxygen-blocking propagation layer of Sc1/3Yb1/3Lu1/3TaO4 ceramic coating with the thickness of 35 μm is prepared by atmospheric plasma spraying on the surface of the antioxidant layer of dense tantalum oxide Ta2O5. Sc1/3Yb1/3Lu1/3TaO4 spherical powder is first prepared through high-temperature solid-phase method by using Sc2O3, Lu2O3, Yb2O3 and Ta2O5 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.
(3) The thermal expansion coefficient buffer layer with La1/4Ho1/4Tm1/4Er1/4Ta3O9 ceramic coating with the thickness of 40 μm is prepared through atmospheric plasma spraying on a surface of the ceramic oxygen-blocking propagation layer of Sc1/3Yb1/3Lu1/3TaO4. La1/4Ho1/4Tm1/4Er1/4Ta3O9 spherical powder is first prepared through the high-temperature solid-phase method by using Er2O3, La2O3, Ho2O3, Tm2O3 and Ta2O5 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.
(4) A heat-insulation cooling layer with Y3TaO7 ceramic coating with the thickness of 500 μm is prepared through atmospheric plasma spraying on a surface of the ceramic thermal expansion coefficient buffer layer of La1/4Ho1/4Tm1/4Er1/4Ta3O9. The Y3TaO7 spherical powder is first prepared through high-temperature solid-phase method by using Y2O3 and Ta2O5 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.
The disclosure provides the UAV surface coating and the preparation method thereof. Please refer to
Specifically: (1) the tantalum bonding layer with the thickness of 200 μm 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 Ta2O5 with the thickness less than 1 μm on its surface.
(2) The oxygen-blocking propagation layer of Yb1/2Lu1/2TaO4 ceramic coating with the thickness of 50 μm is prepared by atmospheric plasma spraying on the surface of the antioxidant layer of dense tantalum oxide Ta2O5. Yb1/2Lu1/2TaO4 spherical powder is first prepared through high-temperature solid-phase method by using Lu2O3, Yb2O3 and Ta2O5 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.
(3) The heat-insulation cooling layer with Y3TaO7 ceramic coating with the thickness of 100 μm is prepared through atmospheric plasma spraying on a surface of the oxygen-blocking propagation layer of Yb1/2Lu1/2TaO4 ceramic coating. The Y3TaO7 spherical powder is first prepared through high-temperature solid-phase method by using Y2O3 and Ta2O5 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.
The disclosure provides the UAV surface coating and the preparation method thereof. Please refer to
Specifically: (1) The oxygen-blocking propagation layer of ScTaO4 ceramic coating with the thickness of 35 μm is prepared by atmospheric plasma spraying on the surface of the matrix. The ScTaO4 spherical powder is first prepared through high-temperature solid-phase method by using Sc2O3 and Ta2O5 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.
(2) The thermal expansion coefficient buffer layer with LaTa3O9 ceramic coating with the thickness of 35 μm is prepared through atmospheric plasma spraying on the surface of the ceramic oxygen-blocking propagation layer of ScTaO4. The LaTa3O9 spherical powder is first prepared through the high-temperature solid-phase method by using La2O3 and Ta2O5 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.
(3) A heat-insulation cooling layer with YLaDyTaO7 ceramic coating with the thickness of 1000 μm is prepared through atmospheric plasma spraying on a surface of the ceramic thermal expansion coefficient buffer layer of LaTa3O9. YLaDyTaO7 spherical powder is first prepared through high-temperature solid-phase method by using Y2O3, La2O3, Dy2O3 and Ta2O5 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.
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.
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.
Please refer to
(1) the silicon (Si) bonding layer with the thickness of 50 μm 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 2×10−3 Pa, and the deposition rate is 100 nm/min.
(2) After a Si coating is prepared, it is placed in the air and heated at 300° C. for oxidation to obtain a SiO2 coating with a thickness of 10 μm, which means the antioxidant layer.
(3) An oxygen-blocking propagation layer of YbTaO4 ceramic coating with a thickness of 50 μm is prepared on a surface of the antioxidant layer through atmospheric plasma spraying. The YbTaO4 spherical powder is first prepared through high-temperature solid-phase method by using Yb2O3 and Ta2O5 as raw materials. Then, the YbTaO4 ceramic coating is prepared through atmospheric plasma spraying with the YbTaO4 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.
(4) A heat-insulation cooling layer with La3NbO7 ceramic coating with a thickness of 300 μm is prepared through atmospheric plasma spraying on the surface of the oxygen-blocking propagation layer. La3NbO7 spherical powder is first prepared through the high-temperature solid-phase method by using La2O3 and Nb2O5 as raw materials. Then, the La3NbO7 ceramic coating is prepared through atmospheric plasma spraying with the La3NbO7 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.
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.
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
Please refer to
(1) the aluminum (Al) bonding layer with the thickness of 50 μm 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 3×10−3 Pa, and the deposition rate is 100 nm/min.
(2) After an Al coating is prepared, it is placed in the air and heated at 100° C. for oxidation to obtain an Al2O3 coating with a thickness less than 10 μm, which means the antioxidant layer.
(3) An oxygen-blocking propagation layer of Yb0.5Lu0.5TaO4 ceramic coating with a thickness of 50 μm is prepared on a surface of the antioxidant layer through atmospheric plasma spraying. The Yb0.5Lu0.5TaO4 spherical powder is first prepared through high-temperature solid-phase method by using Lu2O3, Yb2O3 and Ta2O3 as raw materials. Then, Yb0.5Lu0.5TaO4 ceramic coating is prepared through atmospheric plasma spraying with the Yb0.5Lu0.5TaO4 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.
(4) A heat-insulation cooling layer with Y3NbO7 ceramic coating with a thickness of 350 μm is prepared through atmospheric plasma spraying on the surface of the oxygen-blocking propagation layer. Y3NbO7 spherical powder is first prepared through the high-temperature solid-phase method by using Y2O3 and Nb2O5 as raw materials. Then, the Y3NbO7 ceramic coating is prepared through atmospheric plasma spraying with the Y3NbO7 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.
Please refer to
(1) the aluminum (Al) bonding layer with the thickness of 20 μm 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 3×10−3 Pa, and the deposition rate is 100 nm/min.
(2) After the Al coating is prepared, it is placed in the air and heated at 100° C. for oxidation to obtain an Al2O3 coating with the thickness less than 10 μm, which means the antioxidant layer.
(3) An oxygen-blocking propagation layer of AlTaO4 ceramic coating with a thickness of 100 μm is prepared on the surface of the antioxidant layer through atmospheric plasma spraying. AlTaO4 spherical powder is first prepared through high-temperature solid-phase method by using Al2O3 and Ta2O5 as raw materials. Then, the AlTaO4 ceramic coating is prepared through atmospheric plasma spraying with the AlTaO4 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.
(4) A heat-insulation cooling layer with Sm3NbO7 ceramic coating with a thickness of 600 μm is prepared through atmospheric plasma spraying on the surface of the oxygen-blocking propagation layer. Sm3NbO7 spherical powder is first prepared through the high-temperature solid-phase method by using Sm2O3 and Nb2O5 as raw materials. Then, the Sm3NbO7 ceramic coating is prepared through atmospheric plasma spraying with the Sm3NbO7 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.
Please refer to
(1) a tantalum (Ta) bonding layer with the thickness of 100 μm 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 3×10−3 Pa, and the deposition rate is 100 nm/min.
(2) After the tantalum coating is prepared, it is placed in the air and heated at 30° C. for oxidation to obtain a Ta2O5 coating with the thickness less than 10 μm, which means the antioxidant layer.
(3) An oxygen-blocking propagation layer of YTaO4 ceramic coating with a thickness of 50 μm is prepared on the surface of the antioxidant layer through atmospheric plasma spraying. YTaO4 spherical powder is first prepared through high-temperature solid-phase method by using Y2O3 and Ta2O5 as raw materials. Then, the YTaO4 ceramic coating is prepared through atmospheric plasma spraying with the YTaO4 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.
(4) A heat-insulation cooling layer with the Y3NbO7 ceramic coating with the thickness of 80 μm is prepared through atmospheric plasma spraying on the surface of the oxygen-blocking propagation layer. Y3NbO7 spherical powder is first prepared through the high-temperature solid-phase method by using Y2O3 and Nb2O5 as raw materials. Then, the Y3NbO7 ceramic coating is prepared through atmospheric plasma spraying with the Y3NbO7 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.
Please refer to
(1) the Zirconium-hafnium alloy (ZrHf) bonding layer with the thickness of 60 μm 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 3×10−3 Pa, and the deposition rate is 100 nm/min.
(2) After a ZrHf coating is prepared, it is placed in the air and heated at 280° C. for oxidation to obtain a ZrO2/HfO2 coating with a thickness less than 10 μm, which means the antioxidant layer.
(3) An oxygen-blocking propagation layer of (Sm1/3Yb1/3Ho1/3) TaO4 ceramic coating with a thickness of 50 μm is prepared on the surface of the antioxidant layer through atmospheric plasma spraying. (Sm1/3Yb1/3Ho1/3) TaO4 spherical powder is first prepared through high-temperature solid-phase method by using Ho2O3, Sm2O3, Yb2O3 and Ta2O5 as raw materials. Then, the (Sm1/3Yb1/3Ho1/3) TaO4 ceramic coating is prepared through atmospheric plasma spraying with the (Sm1/3Yb1/3Ho1/3) TaO4 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.
(4) A heat-insulation cooling layer with the (Sm1/3Yb1/3Ho1/3)3NbO7 ceramic coating with a thickness of 250 μm is prepared through atmospheric plasma spraying on the surface of the oxygen-blocking propagation layer. (Sm1/3Yb1/3Ho1/3)3NbO7 spherical powder is first prepared through the high-temperature solid-phase method by using Ho2O3, Sm2O3, Yb2O3 and Nb2O5 as raw materials. Then, the (Sm1/3Yb1/3Ho1/3)3NbO7 ceramic coating is prepared through atmospheric plasma spraying with the (Sm1/3Yb1/3Ho1/3)3NbO7 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.
Please refer to
(1) the calcium-magnesium (CaMg) bonding layer with the thickness of 75 μm 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 2×10−3 Pa, and the deposition rate is 100 nm/min.
(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 μm, which means the antioxidant layer.
(3) An oxygen-blocking propagation layer of Yb1/4Lu1/4Y1/4Sc1/4TaO4 ceramic coating with a thickness of 75 μm is prepared on the surface of the antioxidant layer through atmospheric plasma spraying. Yb1/4Lu1/4Y1/4Sc1/4TaO4 spherical powder is first prepared through high-temperature solid-phase method by using Yb2O3, Lu2O3, Y2O3, Sc2O3 and Ta2O5 as raw materials. Then, the Yb1/4Lu1/4Y1/4Sc1/4TaO4 ceramic coating is prepared through atmospheric plasma spraying with the Yb1/4Lu1/4Y1/4Sc1/4TaO4 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.
(4) A heat-insulation cooling layer with (Yb1/4Lu1/4Y1/4Sc1/4)3NbO7 ceramic coating with a thickness of 420 μm is prepared through atmospheric plasma spraying on the surface of the oxygen-blocking propagation layer. (Yb1/4Lu1/4Y1/4Sc1/4)3NbO7 spherical powder is first prepared through the high-temperature solid-phase method by using Yb2O3, Lu2O3, Y2O3, Sc2O3 and Nb2O5 as raw materials. Then, the (Yb1/4Lu1/4Y1/4Sc1/4)3NbO7 ceramic coating is prepared through atmospheric plasma spraying with the (Yb1/4Lu1/4Y1/4Sc1/4)3NbO7 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.
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.
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.
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.
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.)
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:
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.
Please refer to
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.
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.
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.
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 μm to 200 μm, the thickness of the oxygen-blocking propagation layer is from 20 μm to 100 μm, the thickness of the heat-insulation cooling layer is from 80 μm to 1000 μm, and the thickness of the antioxidant layer is less than 20 μm.
Please refer to
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.
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.
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.
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.
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.
A specific process of the embodiment is as follows:
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.
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.
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.
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.
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.
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.
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.
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.
A specific process of this embodiment is the same as that of embodiment 17, with the following differences:
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.
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.
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.
A specific process of this embodiment is the same as that of embodiment 17, with the following differences:
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.
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.
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.
A specific process of this embodiment is the same as that of embodiment 17, with the following differences:
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.
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.
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.
| Number | Date | Country | Kind |
|---|---|---|---|
| 202111218198.7 | Oct 2021 | CN | national |
| 202111218199.1 | Oct 2021 | CN | national |
| 202111277394.1 | Oct 2021 | CN | national |
| 202111401595.8 | Nov 2021 | CN | national |
The present application is a continuation Application of PCT application No. PCT/CN2022/123842 filed on Oct. 8, 2022, which claims the benefit of CN202111218199.1 filed on Oct. 20, 2021, CN202111218198.7 filed on Oct. 20, 2021, CN202111277394.1 filed on Oct. 29, 2021, and CN202111401595.8 filed on Nov. 19, 2021. All the above are hereby incorporated by reference for all purposes.
| Number | Date | Country | |
|---|---|---|---|
| Parent | PCT/CN2022/123842 | Oct 2022 | WO |
| Child | 18638651 | US |
