CN111499479B - Combustion speed regulator for carbon-based zinc oxide composite propellant and low-temperature preparation method thereof - Google Patents

Combustion speed regulator for carbon-based zinc oxide composite propellant and low-temperature preparation method thereof Download PDF

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CN111499479B
CN111499479B CN202010288091.9A CN202010288091A CN111499479B CN 111499479 B CN111499479 B CN 111499479B CN 202010288091 A CN202010288091 A CN 202010288091A CN 111499479 B CN111499479 B CN 111499479B
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molecules
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based substrate
inert gas
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CN111499479A (en
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冯昊
李建国
龚婷
张王乐
惠龙飞
秦利军
李丹
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Xian Modern Chemistry Research Institute
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    • 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
    • C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
    • C06B29/00—Compositions containing an inorganic oxygen-halogen salt, e.g. chlorate, perchlorate
    • C06B29/22—Compositions containing an inorganic oxygen-halogen salt, e.g. chlorate, perchlorate the salt being ammonium perchlorate
    • 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
    • C06D5/06—Generation of pressure gas, e.g. for blasting cartridges, starting cartridges, rockets by reaction of two or more solids
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C16/00—Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes
    • C23C16/22—Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes characterised by the deposition of inorganic material, other than metallic material
    • C23C16/30—Deposition of compounds, mixtures or solid solutions, e.g. borides, carbides, nitrides
    • C23C16/40—Oxides
    • C23C16/407—Oxides of zinc, germanium, cadmium, indium, tin, thallium or bismuth
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C16/00—Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes
    • C23C16/44—Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes characterised by the method of coating
    • C23C16/4417—Methods specially adapted for coating powder
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C16/00—Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes
    • C23C16/44—Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes characterised by the method of coating
    • C23C16/455—Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes characterised by the method of coating characterised by the method used for introducing gases into reaction chamber or for modifying gas flows in reaction chamber
    • C23C16/45523—Pulsed gas flow or change of composition over time
    • C23C16/45525—Atomic layer deposition [ALD]
    • C23C16/45527—Atomic layer deposition [ALD] characterized by the ALD cycle, e.g. different flows or temperatures during half-reactions, unusual pulsing sequence, use of precursor mixtures or auxiliary reactants or activations

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  • Organic Chemistry (AREA)
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  • General Chemical & Material Sciences (AREA)
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  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Inorganic Chemistry (AREA)
  • Combustion & Propulsion (AREA)
  • Chemical Vapour Deposition (AREA)
  • Carbon And Carbon Compounds (AREA)

Abstract

The invention provides a low-temperature preparation method of a combustion speed regulator for a carbon-based zinc oxide composite propellant, which mainly comprises the steps of exposing a carbon-based substrate in diethyl zinc vapor, and enabling vapor molecules of the carbon-based substrate to be adsorbed on the surface of the carbon-based substrate; blowing the diethyl zinc molecules which are partially physically adsorbed on the surface of the substrate away from the surface of the substrate by using inert gas; exposing the carbon-based substrate to water vapor to chemically react water vapor molecules with the adsorbed diethyl zinc molecules; the by-products and the excess vapor molecules on the surface of the substrate are blown off the surface of the substrate by using inert gas. Compared with the traditional combustion speed regulator and a carbon-based combustion speed regulator prepared by other methods, the combustion speed regulator prepared by the invention has the advantages of excellent combustion speed regulating capability, capability of effectively reducing the AP decomposition temperature, optimized energy release structure, mild preparation temperature, high automation degree, good safety performance, direct use of products without post-treatment, easiness in realization of batch production and environmental friendliness.

Description

Combustion speed regulator for carbon-based zinc oxide composite propellant and low-temperature 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 combustion speed regulator for a carbon-based zinc oxide composite propellant and a low-temperature preparation method thereof.
Background
The combustion performance of the propellant has a significant impact on the ballistic performance of rocket engines. The combustion speed determines the working time and flight speed of the rocket engine, and the stability of the working 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. Flame rate modifiers are the most common means of modifying and improving the combustion performance of propellants. The traditional burning rate regulator can realize controllable regulation of the burning rate and the burning rate pressure index of the propellant in a lower burning rate range.
However, the conventional combustion rate regulator cannot effectively regulate the combustion performance of the propellant in a wider combustion rate 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 speed regulators contain lead salt, so that the requirements of environmental friendliness and low characteristic signals are difficult to meet.
In recent years, micro-nano combustion speed regulators can be fully contacted with other components in the propellant due to the characteristics of small particle size, high specific surface area, low apparent activation energy and the like, and can regulate the combustion performance of the propellant in a wider range, so that the micro-nano combustion speed regulators are widely concerned by domestic and foreign scholars. Furthermore, the carbon material in the flame speed regulator may form a carbon skeleton at the propellant combustion face for loading of the catalyst particles and heat transfer between the flame zone and the preheating zone. Therefore, carbon-based micro-nano fuel rate regulators are widely researched and prepared.
However, the current carbon-based micro-nano burning rate regulator has the defects that the structure is single or the micro-nano composite structure cannot be precisely and controllably synthesized, and the high-efficiency catalysis of a multiphase grain boundary and the synergistic catalysis among different species are difficult to play, so that the micro-nano burning rate regulator cannot effectively play the high-efficiency performance regulating capability in the practical application of the propellant.
Disclosure of Invention
Technical problem to be solved
The invention provides a combustion speed regulator for a carbon-based zinc oxide composite propellant and a low-temperature preparation method thereof, and aims to solve the technical problem of how to prepare the combustion speed regulator for the carbon-based zinc oxide composite propellant.
(II) technical scheme
In order to solve the technical problems, the invention provides a low-temperature preparation method of a combustion speed regulator for a carbon-based zinc oxide composite 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, heating the reaction chamber to enable the temperature of the reaction chamber to be 50-180 ℃;
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 diethyl zinc molecules into the reaction chamber in a self-volatilization mode, wherein the injection time is t1, so that the carbon-based substrate is fully exposed in the diethyl zinc vapor molecules, and the diethyl zinc molecules are adsorbed on the surface of the carbon-based substrate;
step 5, injecting inert gas into the reaction chamber for a time period t2, and blowing diethyl zinc 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 steam molecules of water into the reaction chamber in a self-volatilization mode, wherein the injection time is t3, so that the carbon-based substrate is fully exposed in the steam molecules of the water, and the steam molecules of the water and diethyl zinc molecules adsorbed on the surface of the carbon-based substrate are subjected to surface chemical reaction;
and 7, injecting inert gas into the reaction chamber for a time period t4, and blowing the replaced groups and the physically adsorbed water vapor molecules on the surface of the carbon-based substrate away from the surface of the carbon-based substrate by using the inert gas.
Further, the carbon-based substrate material is at least one of activated carbon, carbon black, graphite, graphene, 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 the sample groove and then placed in the reaction chamber of the chemical vapor deposition equipment, or the carbon-based substrate is placed in the reaction chamber of the chemical vapor deposition equipment after being arranged in the porous container,
further, in the step 3, the flow rate of the inert gas is 30sccm to 200sccm, and the vacuum degree is not more than 200 Pa.
Further, in step 5 and step 7, the flow rate of the inert gas is 30sccm to 200 sccm.
Further, the injection time period t1 is 50s to 500s, the injection time period t2 is 50s to 1000s, the injection time period t3 is 50s to 500s, and the injection time period t4 is 50s to 1000 s.
In addition, the invention also provides a combustion speed regulator for the carbon-based zinc oxide composite propellant, and the combustion speed regulator is prepared by adopting the method.
(III) advantageous effects
The invention provides a low-temperature preparation method of a combustion speed regulator for a carbon-based zinc oxide composite propellant, which mainly comprises the steps of exposing a carbon-based substrate in diethyl zinc vapor, and enabling vapor molecules of the carbon-based substrate to be adsorbed on the surface of the carbon-based substrate; blowing the diethyl zinc molecules which are partially physically adsorbed on the surface of the substrate away from the surface of the substrate by using inert gas; exposing the carbon-based substrate to water vapor to chemically react water vapor molecules with the adsorbed diethyl zinc molecules; the by-products and the excess vapor molecules on the surface of the substrate are blown off the surface of the substrate by using inert gas. Compared with the traditional combustion speed regulator and a carbon-based combustion speed regulator prepared by other methods, the combustion speed regulator prepared by the invention has the advantages of excellent combustion speed regulating capability, capability of effectively reducing the AP decomposition temperature, optimized energy release structure, mild preparation temperature, high automation degree, good safety performance, direct use of products without post-treatment, easiness in realization of batch production and environmental friendliness.
The beneficial technical effects of the invention specifically comprise:
1. the carbon-based zinc oxide composite combustion speed regulator has the advantages of low preparation temperature, no pollution in the preparation process, high safety and stability, high controllability and reproducibility of the product, and easy industrial realization and popularization.
2. The carbon-based zinc oxide composite burning rate regulator is used for regulating the burning rate of the propellant, and has the advantages of no pollution to the environment and good dispersibility.
3. The carbon-based zinc oxide composite combustion speed regulator is less rigid and has excellent combustion speed regulation performance.
Drawings
FIG. 1 is a schematic view of the rotation of activated carbon in a CVD reaction chamber after the activated carbon is placed in a rotating cage according to example 1 of the present invention.
FIG. 2 is a graph showing data on a quartz crystal microbalance for preparing zinc oxide by chemical vapor deposition in example 1 of the present invention.
Fig. 3 is a schematic view of a combustion rate regulator for an activated carbon-based zinc oxide composite propellant formed after zinc oxide is loaded on the surface of an activated carbon substrate in example 1 of the present invention.
FIG. 4 is a DSC decomposition curve of a mixture of pure AP and AP mixed with an AC @ ZnO burning rate adjustment of example 1 of the present invention.
FIG. 5 is a DSC decomposition curve of a mixture of pure AP and AP mixed with CNT @ ZnO burn rate adjustment of example 1 of the present invention.
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 combustion speed regulator for a carbon-based zinc oxide composite propellant and a low-temperature preparation method thereof, wherein the used carbon-based substrate material is an Activated Carbon (AC) material, the specific surface area is 1250 square meters per gram, and the preparation method specifically comprises the following steps:
step 1, as shown in figure 1, placing activated carbon in a porous container and then in a reaction chamber of chemical vapor deposition equipment, installing a quartz crystal microbalance at a sample inlet and a sample outlet of the chemical reaction deposition equipment, and then sealing the sample inlet and the sample outlet of the chemical reaction deposition equipment;
step 2, respectively heating the chemical vapor deposition reaction chambers by electric heating wires to enable the temperature of the chemical vapor deposition reaction chambers to be 100 ℃;
3, introducing nitrogen with the flow rate of 100sccm 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 50 Pa;
and 4, opening the body regulating valve, injecting diethyl zinc molecules into a reaction chamber of the chemical vapor deposition equipment in a self-volatilization mode, wherein the injection time is 300s, so that the activated carbon is fully exposed in the diethyl zinc vapor molecules, and the diethyl zinc molecules are subjected to chemical adsorption on the surface of the activated carbon substrate, wherein the specific chemical reaction is as follows:
||-OH+Zn(C2H5)2→||-O-Zn-C2H5+C2H6
step 5, injecting nitrogen with the flow rate of 100sccm into the reaction chamber from the inlet of the vapor deposition equipment, wherein the injection time is 800s, and blowing part or all of the physically adsorbed diethyl zinc molecules on the surface of the activated carbon substrate away from the surface of the substrate material;
step 6, opening the body regulating valve, injecting water vapor molecules into a reaction chamber of the chemical vapor deposition equipment in a self-volatilization mode, wherein the injection time is 400s, fully exposing the material obtained in the step 5 in the water vapor molecules, and enabling the water molecules to perform a radical exchange reaction with diethyl zinc molecules adsorbed on the surface of the substrate material, wherein the specific chemical reaction formula is as follows:
||-O-Zn-C2H5+H2O→||-OZnOx+C2H6
and 7, injecting nitrogen with the flow rate of 100sccm into the reaction chamber from the inlet of the vapor deposition equipment, wherein the injection time is usually 800s, and blowing the replaced groups and the redundant water vapor molecules on the surface of the material obtained in the step 6 away from the surface of the material to finish the preparation of the AC @ ZnO combustion speed regulator.
FIG. 2 shows a quartz crystal microbalance test curve for monitoring the gas phase synthesis of zinc oxide by changes in the surface mass of the wafer of the quartz crystal microbalance, which is shown to stabilize after a rapid increase in the surface mass of the wafer during the injection of diethylzinc, indicating that the surface chemistry has been completed; the subsequent nitrogen injection slightly reduces the surface quality of the wafer, and diethyl zinc physically adsorbed on the surface part of the wafer is blown off the surface; the subsequent water injection slightly increases the quality of the wafer surface, which shows that the process not only has radical exchange reaction, but also has partial physical adsorption; a final nitrogen purge blows some of the physisorption off the wafer surface.
FIG. 3 is a schematic view of a combustion rate regulator for forming an activated carbon-based zinc oxide composite propellant after zinc oxide is loaded on the surface of an activated carbon substrate by a chemical vapor deposition method
The prepared burning rate regulator for the activated carbon-based zinc oxide composite propellant is mixed with Ammonium Perchlorate (AP) which is an oxidant for the composite solid propellant, and the burning rate regulation performance of the compound solid propellant is researched by DSC. FIG. 4 shows DSC decomposition curves of pure AP and a mixture of AP mixed with an AC @ ZnO flame rate adjustment. The AP crystal transition peaks of pure AP and AP mixture mixed with the flame speed modifier were substantially the same near 245 ℃, indicating that the flame speed modifier did not affect the crystal transition of AP. Pure AP has the obvious low-temperature decomposition exothermic peak and high-component decomposition exothermic peak which are respectively at 358.6 ℃ and 437.2 ℃; the low-temperature decomposition peak and the high-temperature decomposition peak of the AP mixture mixed with the AC @ ZnO combustion speed regulation are combined into one peak and reduced to 323.7 ℃, so that the decomposition temperature of the AP is greatly reduced, and the release is more concentrated and more effective.
Example 2
The embodiment provides a combustion speed regulator for a carbon-based zinc oxide composite propellant and a low-temperature preparation method thereof, wherein a carbon-based substrate material is a Carbon Nano Tube (CNT) material, the specific surface area is 820 square meters per gram, and the preparation method specifically comprises the following steps:
step 1, paving a carbon nano tube in a sample groove, placing the sample groove 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 chambers by electric heating wires to enable the temperature of the chemical vapor deposition reaction chambers to be 80 ℃;
3, introducing nitrogen with the flow rate of 50sccm into the reaction chamber from an inlet of the vapor deposition equipment, and exhausting gas at an outlet of the vapor deposition equipment by using a vacuum pump to enable the vacuum degree in the reaction chamber to be about 30 Pa;
step 4, opening the body regulating valve, injecting diethyl zinc molecules into a reaction chamber of the chemical vapor deposition equipment in a self-volatilization mode, wherein the injection time is 200s, so that the activated carbon is fully exposed in the diethyl zinc vapor molecules, and the diethyl zinc molecules are chemically adsorbed on the surface of the carbon nanotube substrate, and the specific chemical reaction is as follows:
||-OH+Zn(C2H5)2→||-O-Zn-C2H5+C2H6
step 5, injecting nitrogen with the flow rate of 50sccm into the reaction chamber from the inlet of the vapor deposition equipment, wherein the injection time is 500s, and blowing part or all of the physically adsorbed diethyl zinc molecules on the surface of the carbon nanotube substrate away from the surface of the substrate material;
step 6, opening the body regulating valve, injecting water vapor molecules into a reaction chamber of the chemical vapor deposition equipment in a self-volatilization mode, wherein the injection time is 400s, fully exposing the material obtained in the step 5 in the water vapor molecules, and enabling the water molecules to perform a radical exchange reaction with diethyl zinc molecules adsorbed on the surface of the substrate material, wherein the specific chemical reaction formula is as follows:
||-O-Zn-C2H5+H2O→||-OZnOx+C2H6
and 7, injecting nitrogen with the flow rate of 100sccm into the reaction chamber from the inlet of the vapor deposition equipment for 500s, and blowing the replaced groups and the redundant water vapor molecules on the surface of the material obtained in the step 6 away from the surface of the material to finish the preparation of the CNT @ ZnO combustion speed regulator.
The prepared burning rate regulator for the carbon nanotube-based zinc oxide composite propellant is mixed with Ammonium Perchlorate (AP) which is an oxidant for the composite solid propellant, and the burning rate regulation performance of the composite solid propellant is researched by DSC. FIG. 5 shows DSC decomposition curves of pure AP and AP blends with adjusted burning rate of CNT @ ZnO. The AP crystal transition peaks of pure AP and AP mixture mixed with the flame speed modifier were substantially the same near 245 ℃, indicating that the flame speed modifier did not affect the crystal transition of AP. Pure AP has the obvious low-temperature decomposition exothermic peak and high-component decomposition exothermic peak which are respectively at 358.6 ℃ and 437.2 ℃; the low-temperature decomposition peak and the high-temperature decomposition peak of the AP mixture mixed with the CNT @ ZnO burning rate regulation are combined into one peak and reduced to 332.4 ℃, so that the decomposition temperature of the AP is greatly reduced, and the quantity release is more concentrated and more effective.
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 (6)

1. The application of the carbon-based zinc oxide composite material as a combustion speed regulator of a composite propellant is characterized in that the carbon-based zinc oxide composite material 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, heating the reaction chamber to enable the temperature of the reaction chamber to be 50-180 ℃;
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 diethyl zinc molecules into the reaction chamber in a self-volatilization mode, wherein the injection time is t1, and t1 is 50-500 s, so that the carbon-based substrate is fully exposed in the diethyl zinc vapor molecules, and the diethyl zinc molecules are adsorbed on the surface of the carbon-based substrate;
step 5, injecting inert gas into the reaction chamber, wherein the injection time is t2, and t2 is 50-1000 s, and blowing diethyl zinc 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 steam molecules of water into the reaction chamber in a self-volatilization mode, wherein the injection time is t3, and t3 is 50-500 s, so that the carbon-based substrate is fully exposed in the steam molecules of the water, and the steam molecules of the water and diethyl zinc molecules adsorbed on the surface of the carbon-based substrate are subjected to surface chemical reaction;
and 7, injecting inert gas into the reaction chamber for a time period t4 and a time period t4 of 50 s-1000 s, and blowing the replaced groups on the surface of the carbon-based substrate and the physically adsorbed water vapor molecules away from the surface of the carbon-based substrate by using the inert gas.
2. The use according to claim 1, wherein the carbon-based substrate material is at least one of activated carbon, carbon black, graphite, graphene, nanotubes, fullerenes, mesoporous carbon, or a mixture of any of the above in any proportion.
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 placed in a reaction chamber of a chemical vapor deposition apparatus after being laid down in a sample cell, or the carbon-based substrate is placed in a reaction chamber of a chemical vapor deposition apparatus after being loaded in a porous container.
5. The use according to claim 1, wherein in step 3, the inert gas has a flow rate of 30sccm to 200sccm and a vacuum degree of not more than 200 Pa.
6. The use according to claim 1, wherein the inert gas has a flow rate of 30 to 200sccm in steps 5 and 7.
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