CN111468092B - Carbon-based titanium dioxide composite combustion catalyst for propellant and preparation method thereof - Google Patents

Carbon-based titanium dioxide composite combustion catalyst for propellant and preparation method thereof Download PDF

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CN111468092B
CN111468092B CN202010288096.1A CN202010288096A CN111468092B CN 111468092 B CN111468092 B CN 111468092B CN 202010288096 A CN202010288096 A CN 202010288096A CN 111468092 B CN111468092 B CN 111468092B
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carbon
based substrate
molecules
reaction chamber
titanium dioxide
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CN111468092A (en
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冯昊
***
李丹
龚婷
秦利军
张王乐
惠龙飞
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Xian Modern Chemistry Research Institute
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
    • B01J—CHEMICAL OR PHYSICAL PROCESSES, e.g. CATALYSIS OR COLLOID CHEMISTRY; THEIR RELEVANT APPARATUS
    • B01J21/00—Catalysts comprising the elements, oxides, or hydroxides of magnesium, boron, aluminium, carbon, silicon, titanium, zirconium, or hafnium
    • B01J21/18—Carbon
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
    • B01J—CHEMICAL OR PHYSICAL PROCESSES, e.g. CATALYSIS OR COLLOID CHEMISTRY; THEIR RELEVANT APPARATUS
    • B01J37/00—Processes, in general, for preparing catalysts; Processes, in general, for activation of catalysts
    • B01J37/08—Heat treatment
    • C—CHEMISTRY; METALLURGY
    • C06—EXPLOSIVES; MATCHES
    • C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
    • C06B23/00—Compositions characterised by non-explosive or non-thermic constituents
    • C06B23/007—Ballistic modifiers, burning rate catalysts, burning rate depressing agents, e.g. for gas generating
    • C—CHEMISTRY; METALLURGY
    • C06—EXPLOSIVES; MATCHES
    • C06D—MEANS FOR GENERATING SMOKE OR MIST; GAS-ATTACK COMPOSITIONS; GENERATION OF GAS FOR BLASTING OR PROPULSION (CHEMICAL PART)
    • C06D5/00—Generation of pressure gas, e.g. for blasting cartridges, starting cartridges, rockets

Abstract

The invention provides a carbon-based titanium dioxide composite combustion catalyst for a propellant and a preparation method thereof, wherein the preparation method mainly comprises the steps of exposing a carbon-based substrate in titanium tetraisopropoxide steam, and enabling steam molecules to carry out chemical and physical adsorption on the surface of the carbon-based substrate; blowing off titanium tetraisopropoxide molecules physically adsorbed on the surface by using inert gas; exposing the carbon-based substrate in hydrogen peroxide or steam of water to enable steam molecules of the carbon-based substrate to perform radical replacement reaction with adsorbed titanium tetraisopropoxide molecules; the displaced radicals and excess vapor molecules from the surface of the carbon-based substrate are blown off the surface using an inert gas. According to the composite combustion catalyst prepared by the invention, titanium dioxide is uniformly dispersed on the carbon-based surface, the loading capacity of the titanium dioxide is accurate and adjustable, the structure is accurate and controllable, the active site is fully exposed, the crystal boundary catalysis and the concerted catalysis are fully utilized, the combustion catalyst is good in performance, and the environment is friendly.

Description

Carbon-based titanium dioxide composite combustion catalyst for propellant and preparation method thereof
Technical Field
The invention belongs to the technical field of powder material surface modification and preparation thereof, and particularly relates to a carbon-based titanium dioxide composite combustion catalyst for a propellant and a preparation method thereof.
Background
The combustion performance of the propellant has a significant impact on the ballistic performance of rocket engines. The operating time and the flying speed of the rocket engine are determined by the combustion speed, and the stability of the operating performance of the rocket engine is directly influenced by the influence of external conditions (temperature and pressure). Therefore, controlling and regulating the combustion performance of rocket propellants is important to meet the performance requirements of various types of artillery, rocket engines, and rocket weapons. The use of combustion catalysts is the most common method for regulating and improving the combustion performance of propellants. The traditional combustion catalyst can realize controllable regulation of the combustion speed and the combustion speed pressure index of the propellant in a lower combustion speed range.
However, the conventional combustion catalyst cannot effectively adjust the combustion performance of the propellant in a wider combustion speed range due to the defects of composition and structure, large particle size, small specific surface area, insufficient contact with other components of the propellant and the like. In addition, most of the traditional combustion catalysts contain lead salt, and the requirements of environmental friendliness and low characteristic signals are difficult to meet.
In recent years, micro-nano combustion catalysts have the characteristics of small particle size, high specific surface area, low apparent activation energy and the like, can be fully contacted with other components in a propellant, can regulate the combustion performance of the propellant in a wider range, and are widely concerned by scholars at home and abroad. Furthermore, the carbon material in the combustion catalyst may form a carbon skeleton at the propellant combustion face for the loading of the catalyst particles and the heat conduction between the flame zone and the preheating zone. Therefore, carbon-based micro-nano combustion catalysts are widely researched and prepared.
However, the current carbon-based micro-nano combustion catalyst is difficult to exert the high-efficiency catalysis of a multiphase grain boundary and the synergistic catalysis among different species due to the fact that the structure is single or the micro-nano composite structure cannot be precisely and controllably synthesized, so that the micro-nano combustion catalyst cannot effectively exert the high-efficiency performance regulation capability in the practical application of the propellant.
Disclosure of Invention
Technical problem to be solved
The invention provides a carbon-based titanium dioxide composite combustion catalyst for a propellant and a preparation method thereof, and aims to solve the technical problem of how to prepare the carbon-based titanium dioxide composite combustion catalyst.
(II) technical scheme
In order to solve the technical problem, the invention provides a preparation method of a carbon-based titanium dioxide composite combustion catalyst for a propellant, which comprises the following steps:
step 1, placing a carbon-based substrate in a reaction chamber of chemical vapor deposition equipment, and sealing a sample inlet and a sample outlet of the chemical vapor deposition equipment;
step 2, respectively heating the reaction chamber and the titanium tetraisopropoxide containing container to ensure that the temperature of the reaction chamber is 80-200 ℃ and the temperature of the containing container is 30-100 ℃;
step 3, injecting inert gas into the reaction chamber, and vacuumizing the reaction chamber to ensure that the reaction chamber has a certain vacuum degree;
step 4, injecting titanium tetraisopropoxide molecules into the reaction chamber in a gas bubbling mode, wherein the injection time is t1, so that the carbon-based substrate is fully exposed in the titanium tetraisopropoxide steam molecules, and the titanium tetraisopropoxide molecules are subjected to chemical adsorption and physical adsorption on the surface of the carbon-based substrate;
step 5, injecting inert gas into the reaction chamber for a time t2, and blowing titanium tetraisopropoxide molecules physically adsorbed on the surface of the carbon-based substrate away from the surface of the carbon-based substrate by using the inert gas;
step 6, injecting hydrogen peroxide or steam molecules of water into the reaction chamber for a time period t3, so that the carbon-based substrate is fully exposed in the hydrogen peroxide or steam molecules of water, and the hydrogen peroxide or steam molecules of water and titanium tetraisopropoxide molecules adsorbed on the surface of the carbon-based substrate are subjected to a group replacement reaction;
and 7, injecting inert gas into the reaction chamber for a time t4, and blowing the replaced groups on the surface of the carbon-based substrate and the redundant hydrogen peroxide or water vapor molecules off the surface of the carbon-based substrate by using the inert gas to obtain the carbon-based titanium dioxide composite combustion catalyst.
Further, the carbon-based substrate material is at least one of activated carbon, carbon black, graphite, graphene, carbon nanotubes, fullerene and mesoporous carbon, or a mixture of any of the above materials in any proportion.
Further, the inert gas is one of helium, nitrogen or argon.
Further, in step 1, the carbon-based substrate is laid in a reaction chamber of the chemical vapor deposition apparatus, or the carbon-based substrate is placed in the reaction chamber of the chemical vapor deposition apparatus after being placed in the porous container.
Further, in step 3, the flow rate of the inert gas is 10sccm to 500sccm, and the vacuum degree is not more than 300Pa.
Further, in step 5 and step 7, the flow rate of the inert gas is 10sccm to 500sccm.
Furthermore, the injection time t1 is 50s to 1000s, the injection time t2 is 100s to 1000s, the injection time t3 is 50s to 1000s, and the injection time t4 is 100s to 1000s.
Further, the preparation method further comprises a step 8 of repeatedly executing the step 4 to the step 7, so that the weight of the carbon-based substrate is increased after the surface of the carbon-based substrate is loaded with the titanium dioxide.
Further, in step 8, the surface of the carbon-based substrate is weighted by 3% to 100% after loading titanium dioxide.
In addition, the invention also provides a carbon-based titanium dioxide composite combustion catalyst for the propellant, and the catalyst is prepared by adopting the method.
(III) advantageous effects
The invention provides a carbon-based titanium dioxide composite combustion catalyst for a propellant and a preparation method thereof, wherein the preparation method mainly comprises the steps of exposing a carbon-based substrate in titanium tetraisopropoxide steam to enable steam molecules to carry out chemical and physical adsorption on the surface of the carbon-based substrate; blowing off titanium tetraisopropoxide molecules physically adsorbed on the surface by using inert gas; exposing the carbon-based substrate in hydrogen peroxide or water vapor to enable vapor molecules of the carbon-based substrate to perform radical replacement reaction with adsorbed titanium tetraisopropoxide molecules; the displaced radicals and excess vapor molecules from the surface of the carbon-based substrate are blown off the surface using an inert gas. According to the composite combustion catalyst prepared by the invention, titanium dioxide is uniformly dispersed on the carbon-based surface, the loading capacity of the titanium dioxide is accurate and adjustable, the structure is accurate and controllable, the active site is fully exposed, the grain boundary catalysis and the concerted catalysis are fully utilized, the combustion catalyst is good in performance, and the environment is friendly.
The beneficial technical effects of the invention specifically comprise:
1. the carbon-based titanium dioxide composite combustion catalyst has the advantages of mild chemical gas phase synthesis conditions, no pollution in the whole process, simplicity in operation, high safety, high controllability and reproducibility of the product, and easiness in industrial realization and popularization.
2. The carbon-based titanium dioxide composite combustion catalyst is used for the combustion speed catalysis of the propellant, and has the advantages of no pollution to the environment and good dispersibility.
3. The carbon-based titanium dioxide composite combustion catalyst can realize high-efficiency combustion catalysis of the propellant on the premise of reducing the energy density reduction of the propellant as much as possible.
Drawings
FIG. 1 is a graph showing the percentage of the total titania loading on the surface of an activated carbon substrate that increases with the number of chemical vapor deposition cycles in example 1 of the present invention.
FIG. 2 is a graph showing the weight gain of titania loading per cycle on the surface of an activated carbon substrate as the number of chemical vapor deposition cycles increases in example 1 of the present invention.
FIG. 3 shows the crystallization of the activated carbon-based titanium dioxide composite combustion catalyst after 20 CVD processes in example 1 of the present invention, after annealing at different temperatures.
FIG. 4 shows AC @ TiO in example 1 of the present invention 2 A TEM image (a) and a titanium element distribution diagram (b) of the composite combustion catalyst.
FIG. 5 is the AC @ TiO after different chemical vapor phase reaction cycles in example 1 of the present invention 2 DSC curve of composite combustion catalyst versus thermal decomposition of AP.
FIG. 6 is the AC @ TiO form cycle after different chemical vapor phase reaction cycles in example 1 of the present invention 2 TG curve of composite combustion catalyst versus AP thermal decomposition.
FIG. 7 is the AC @ TiO after different chemical vapor phase reaction cycles in example 1 of the present invention 2 DTG curve of composite combustion catalyst versus thermal decomposition of AP.
FIG. 8 shows examples 1 of the present invention in which AC, P25, AC/P25 (12.17%) and AC @1c-TiO are used 2 Comparative graph (DSC curve) of the decomposition catalytic performance of combustion catalyst to AP.
FIG. 9 is a TEM image of the ordered mesoporous carbon material in example 2 of the present invention.
FIG. 10 shows the ordered mesoporous carbon-titanium dioxide composite combustion catalyst MC @1c-TiO in example 2 of the present invention 2 DSC curve for catalytic decomposition of AP combustion.
Detailed Description
In order to make the objects, contents and advantages of the present invention clearer, the following detailed description of the embodiments of the present invention will be made in conjunction with the accompanying drawings and examples.
Example 1
The embodiment provides a carbon-based titanium dioxide composite combustion catalyst for a propellant and a preparation method thereof, wherein the used carbon-based material is an activated carbon material, and the specific surface area is 1250 square meters per gram, and the preparation method specifically comprises the following steps:
step 1, flatly paving activated carbon in a reaction chamber of chemical vapor deposition equipment, and then sealing a sample inlet and a sample outlet of the chemical vapor deposition equipment;
step 2, respectively heating the chemical vapor deposition reaction chamber and the titanium tetraisopropoxide containing container by electric heating wires to ensure that the temperatures of the chemical vapor deposition reaction chamber and the titanium tetraisopropoxide containing container are respectively 140 ℃ and 40 ℃;
3, introducing argon with the flow rate of 50sccm into the reaction chamber from the inlet of the vapor deposition equipment, and exhausting gas at the outlet of the vapor deposition equipment by using a vacuum pump to ensure that the vacuum degree in the reaction chamber is about 100 Pa;
step 4, injecting titanium tetraisopropoxide molecules into a reaction chamber of the chemical vapor deposition equipment in a gas bubbling mode, wherein the injection time is 600s, so that the activated carbon is fully exposed in the titanium tetraisopropoxide vapor molecules, and the titanium tetraisopropoxide molecules are subjected to chemical adsorption and physical adsorption on the surface of the activated carbon substrate, and the specific chemical reaction is as follows:
||-OH+Ti(OPr) 4 →||-OTi(OPr) 3 +HOPr
step 5, injecting argon gas with the flow rate of 50sccm into the reaction chamber from the inlet of the vapor deposition equipment for 1200s, and blowing part or all of the physically adsorbed titanium tetraisopropoxide molecules on the surface of the activated carbon substrate away from the surface of the substrate material;
step 6, opening the regulating valve to inject hydrogen peroxide vapor molecules into a reaction chamber of the chemical vapor deposition equipment, wherein the injection time is 500s, so that the material obtained in the step 5 is in the H state 2 O 2 Fully exposing the steam molecules to ensure that dioxygen water molecules and titanium tetraisopropoxide molecules adsorbed on the surface of the substrate material have a group displacement reaction, wherein the specific chemical reaction formula is as follows:
||-OTi(OPr) 3 +H 2 O 2 →||-OTiO x +HOPr
step 7, injecting argon gas with the flow rate of 50sccm into the reaction chamber from the inlet of the vapor deposition equipment, wherein the injection time is 1200s, and blowing the replaced groups on the surface of the material obtained in the step 6 and redundant hydrogen peroxide vapor molecules off the surface of the material;
and 8, repeatedly executing the steps 4 to 7, and determining the mass ratio of the titanium dioxide in the prepared activated carbon-based titanium dioxide composite combustion catalyst by using an electronic balance. Repeating for 1 time to obtain AC @1c-TiO as shown in FIG. 1 2 The proportion of titanium dioxide is 12.17%; repeating for 2 times to obtain AC @2c-TiO 2 The proportion of the titanium dioxide is 19.06 percent; repeating the reaction for 3 times to obtain AC @3c-TiO 2 The proportion of titanium dioxide is 23.43 percent; repeating for 5 times to obtain AC @5c-TiO 2 The proportion of titanium dioxide is 28.82 percent; repeating for 10 times to obtain AC @10c-TiO 2 The proportion of the titanium dioxide is 30.90 percent; repeating for 15 times to obtain AC @15c-TiO 2 The proportion of the titanium dioxide is 35.49 percent; repeating for 20 times to obtain AC @20c-TiO 2 The content of titanium dioxide was 37.18%. As shown in fig. 2, the titanium dioxide weight gain per cycle gradually decreases with the increase of the number of cycles, indicating that a large number of micropores and a part of mesopores are gradually blocked and the specific surface area is decreased.
The prepared high-load activated carbon-based titanium dioxide composite combustion catalyst AC @20c-TiO 2 Annealing is carried out at different temperatures, the crystal form of the annealing is researched, and the research finds that (shown in figure 3): the titanium dioxide has no crystal form after annealing at 300 ℃, and then the titanium dioxide is gradually changed into an anatase phase and a rutile phase from the anatase phase along with the increase of the annealing temperature.
Prepared by using TEM pairThe activated carbon-based titanium dioxide composite combustion catalyst is characterized, and the result shows (as shown in figure 4) that the prepared AC @ TiO 2 The titanium dioxide in the composite combustion catalyst is highly dispersed.
Mixing the prepared AC @ TiO 2 The DSC, TG and DTG of the composite combustion catalyst and the propellant were fully mixed with an oxidant AP, and the results are shown in fig. 5, 6 and 7, and the corresponding results are obtained, which indicates that the higher the loading amount of titanium dioxide is, the higher the catalytic activity is. Considering that titanium dioxide will reduce the energy density of the propellant, the lower the titanium dioxide loading the better its overall performance. FIG. 8 shows AC, P25, AC/P25 (12.17%) and AC @1c-TiO 2 Comparative data on the decomposition catalytic performance of a combustion catalyst on AP, wherein P25 is commercial titanium dioxide, AC/P25 (12.17%) means that AC and P25 are physically mixed, and the proportion of P25 is equal to AC @1c-TiO 2 Medium TiO2 2 The ratio is the same, i.e. 12.17%. Different samples T were obtained according to FIG. 8 onset 、T offset 、T max And first and second mass loss, the results are shown in table 1.
TABLE 1
Figure BDA0002449293020000071
As shown in table 1, the addition of AC greatly reduced the low-temperature onset decomposition temperature of AP, but the maximum weight loss rate temperature point of the low-temperature decomposition stage did not change much; the temperature points of the pyrolysis starting temperature and the maximum weight loss rate in the pyrolysis stage are reduced by about 30 ℃, and the difference between the final decomposition finishing temperature point and the temperature point is 30 ℃; in addition, the weight loss rate in the low-temperature decomposition stage is greatly increased from the previous 6.76 percent to 48.78 percent, so that the temperature range of the real heat release process is wide, the heat release is not concentrated, and the heat release amount is small.
The addition of P25 enables the low-temperature decomposition starting temperature of AP and the temperature point of the maximum weight loss rate in the low-temperature decomposition stage to be reduced by about 80 ℃; the decomposition temperature at the beginning of high temperature is reduced by about 80 ℃ in the same way, but the temperature point of the maximum weight loss rate in the high-temperature decomposition stage is reduced by about 20 ℃, and the weight loss rate in the low-temperature decomposition stage in the whole decomposition process is almost the same as that of pure AP, so that the whole heat release structure is similar to that of the pure AP, and the maximum heat release peak is about 20 ℃ ahead of the temperature.
Addition of AC/P25 (12.17%) AC synergized with titanium dioxide compared to pure AC and P25. But the dispersibility is poor, so the catalytic effect is far different from that of AC @1c-TiO2, and the prepared activated carbon-based titanium dioxide composite combustion catalyst combines the high-temperature decomposition peak and the low-temperature decomposition peak of AP and reduces the temperature from 438 ℃ of the high-temperature decomposition of the AP to 328 ℃.
Example 2
This example proposes a carbon-based titanium dioxide composite combustion catalyst for propellant and a preparation method thereof, where the carbon-based material is ordered mesoporous carbon (as shown in fig. 9), and the specific surface area is 600 square meters per gram, and the preparation method specifically includes the following steps:
step 1, placing the ordered mesoporous carbon in a porous container and then in a reaction chamber of chemical vapor deposition equipment, and then sealing an inlet and an outlet of a sample of the chemical vapor deposition equipment;
step 2, respectively heating the chemical vapor deposition reaction chamber and the titanium tetraisopropoxide containing container by electric heating wires to ensure that the temperatures of the chemical vapor deposition reaction chamber and the titanium tetraisopropoxide containing container are respectively 160 ℃ and 60 ℃;
3, introducing argon with the flow rate of 60sccm into the reaction chamber from an inlet of the vapor deposition equipment, and extracting air from an outlet of the vapor deposition equipment by using a vacuum pump to enable the vacuum degree in the reaction chamber to be about 110 Pa;
step 4, injecting titanium tetraisopropoxide molecules into a reaction chamber of the chemical vapor deposition equipment in a gas bubbling mode, wherein the injection time is 400s, so that the ordered mesoporous carbon is fully exposed in titanium tetraisopropoxide vapor molecules, and the titanium tetraisopropoxide molecules are subjected to chemical adsorption and physical adsorption on the surface of an ordered mesoporous carbon substrate, and the specific chemical reaction is as follows:
||-OH+Ti(OPr) 4 →||-OTi(OPr) 3 +HOPr
step 5, injecting argon gas with the flow rate of 60sccm into the reaction chamber from the inlet of the vapor deposition equipment for 800s, and blowing part or all of the physically adsorbed titanium tetraisopropoxide molecules on the surface of the ordered mesoporous carbon substrate away from the surface of the substrate material;
step 6, opening the regulating valve to inject hydrogen peroxide vapor molecules into a reaction chamber of the chemical vapor deposition equipment, wherein the injection time is 300s, so that the material obtained in the step five is in the H state 2 O 2 Fully exposing the steam molecules to ensure that dioxygen water molecules and titanium tetraisopropoxide molecules adsorbed on the surface of the substrate material have a group displacement reaction, wherein the specific chemical reaction formula is as follows:
||-OTi(OPr) 3 +H 2 O 2 →||-OTiO x +HOPr
step 7, injecting argon gas with the flow rate of 60sccm into the reaction chamber from the inlet of the vapor deposition equipment, wherein the injection time is 600s, and blowing the replaced groups on the surface of the material obtained in the step 6 and redundant hydrogen peroxide vapor molecules off the surface of the material;
the serial number of the ordered mesoporous carbon titanium dioxide composite combustion catalyst after one cycle is MC @1c-TiO 2 FIG. 10 shows a composite combustion catalyst MC @1c-TiO with ordered mesoporous carbon and titanium dioxide 2 DSC curve for catalytic decomposition of AP combustion. As can be seen from the figure, MC @1c-TiO compared to pure AP 2 The addition of the combustion catalyst enables the AP decomposition temperature to be reduced from 423 ℃ to 312 ℃ previously, and a good combustion catalysis effect is achieved.
The above description is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, several modifications and variations can be made without departing from the technical principle of the present invention, and these modifications and variations should also be regarded as the protection scope of the present invention.

Claims (9)

1. The application of the carbon-based titanium dioxide composite combustion catalyst in catalyzing the combustion of a propellant is characterized in that the carbon-based titanium dioxide composite combustion catalyst is prepared by the following method:
step 1, placing a carbon-based substrate in a reaction chamber of chemical vapor deposition equipment, and sealing a sample inlet and a sample outlet of the chemical vapor deposition equipment;
step 2, respectively heating the reaction chamber and the titanium tetraisopropoxide containing container to ensure that the temperature of the reaction chamber is 80-200 ℃ and the temperature of the containing container is 30-100 ℃;
step 3, injecting inert gas into the reaction chamber, and performing vacuum pumping treatment to ensure that the reaction chamber has a certain vacuum degree;
step 4, injecting titanium tetraisopropoxide molecules into the reaction chamber in a gas bubbling mode, wherein the injection time is t1, so that the carbon-based substrate is fully exposed in the titanium tetraisopropoxide steam molecules, and the titanium tetraisopropoxide molecules are subjected to chemical adsorption and physical adsorption on the surface of the carbon-based substrate;
step 5, injecting inert gas into the reaction chamber for a time t2, and blowing titanium tetraisopropoxide molecules physically adsorbed on the surface of the carbon-based substrate away from the surface of the carbon-based substrate by using the inert gas;
step 6, injecting hydrogen peroxide or steam molecules of water into the reaction chamber for a time period t3, so that the carbon-based substrate is fully exposed in the hydrogen peroxide or steam molecules of water, and the hydrogen peroxide or steam molecules of water and titanium tetraisopropoxide molecules adsorbed on the surface of the carbon-based substrate are subjected to a group replacement reaction;
and 7, injecting inert gas into the reaction chamber for a time t4, and blowing the replaced groups on the surface of the carbon-based substrate and the redundant hydrogen peroxide or water vapor molecules off the surface of the carbon-based substrate by using the inert gas to obtain the carbon-based titanium dioxide composite combustion catalyst.
2. The use of claim 1, wherein the carbon-based substrate material is at least one of activated carbon, carbon black, graphite, graphene, carbon nanotubes, fullerenes, mesoporous carbon.
3. The use of claim 1, wherein the inert gas is one of helium, nitrogen, or argon.
4. The use of claim 1, wherein in step 1, the carbon-based substrate is laid flat in a reaction chamber of a chemical vapor deposition apparatus, or the carbon-based substrate is placed in a reaction chamber of a chemical vapor deposition apparatus after being placed in a porous container.
5. The use according to claim 1, wherein in step 3, the inert gas has a flow rate of 10sccm to 500sccm and a vacuum degree of not more than 300Pa.
6. The use according to claim 1, wherein the inert gas has a flow rate of 10sccm to 500sccm in steps 5 and 7.
7. Use according to claim 1, wherein the injection duration t1 is between 50s and 1000s, the injection duration t2 is between 100s and 1000s, the injection duration t3 is between 50s and 1000s, and the injection duration t4 is between 100s and 1000s.
8. The use according to claim 1, wherein the preparation method further comprises the step 8: and (5) repeating the steps 4 to 7, so that the surface of the carbon-based substrate is weighted after being loaded with titanium dioxide.
9. The use of claim 8, wherein in step 8, the surface of the carbon-based substrate is loaded with titanium dioxide and then the weight is increased by 3% to 100%.
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