CN111087273A - Four-component composite propellant containing iodate coated aluminum powder and preparation method thereof - Google Patents

Four-component composite propellant containing iodate coated aluminum powder and preparation method thereof Download PDF

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CN111087273A
CN111087273A CN201911312356.8A CN201911312356A CN111087273A CN 111087273 A CN111087273 A CN 111087273A CN 201911312356 A CN201911312356 A CN 201911312356A CN 111087273 A CN111087273 A CN 111087273A
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aluminum powder
iodate
coated
propellant
component composite
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严启龙
唐得云
陈书文
刘佩进
何国强
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Northwestern Polytechnical University
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    • C—CHEMISTRY; METALLURGY
    • C06—EXPLOSIVES; MATCHES
    • C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
    • C06B33/00—Compositions containing particulate metal, alloy, boron, silicon, selenium or tellurium with at least one oxygen supplying material which is either a metal oxide or a salt, organic or inorganic, capable of yielding a metal oxide
    • C06B33/12—Compositions containing particulate metal, alloy, boron, silicon, selenium or tellurium with at least one oxygen supplying material which is either a metal oxide or a salt, organic or inorganic, capable of yielding a metal oxide the material being two or more oxygen-yielding compounds
    • C—CHEMISTRY; METALLURGY
    • C06—EXPLOSIVES; MATCHES
    • C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
    • C06B21/00—Apparatus or methods for working-up explosives, e.g. forming, cutting, drying
    • C06B21/0008—Compounding the ingredient
    • C06B21/0016—Compounding the ingredient the ingredient being nitrocellulose or oranitro cellulose based propellant; Working up; gelatinising; stabilising
    • C—CHEMISTRY; METALLURGY
    • C06—EXPLOSIVES; MATCHES
    • C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
    • C06B21/00—Apparatus or methods for working-up explosives, e.g. forming, cutting, drying
    • C06B21/0033—Shaping the mixture
    • C06B21/0058—Shaping the mixture by casting a curable composition, e.g. of the plastisol type
    • 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

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Abstract

The invention discloses a four-component composite propellant containing iodate coated aluminum powder and a preparation method thereof, which are used for solving the technical problem that the aluminum powder composite propellant prepared by the existing method is low in combustion efficiency. The four-component composite propellant containing iodate coated aluminum powder is prepared by uniformly mixing iodate coated modified aluminum powder, an oxidant, a binder, a plasticizer and a curing agent, curing and crosslinking. The preparation method comprises the steps that the connecting agent BL is coated with micron aluminum powder in an oxygen-containing environment through polymerization reaction, and the coated aluminum powder is dispersed in distilled water again after being filtered, cleaned and dried. Dropwise adding nitrate solution and iodate solution into the dispersion liquid coated with the aluminum powder under the stirring condition, growing iodate on the surface of the dispersion liquid in situ to obtain iodate-coated micron aluminum powder, mixing and curing the iodate-coated micron aluminum powder and a binder and the like to obtain the iodate-coated aluminum powder-containing four-component composite propellant. Due to the catalytic action of iodate, the combustion efficiency is improved.

Description

Four-component composite propellant containing iodate coated aluminum powder and preparation method thereof
Technical Field
The invention relates to a four-component composite propellant containing iodate coated aluminum powder and a preparation method of the four-component composite propellant containing iodate coated aluminum powder.
Background
Aluminum powder is often used as a metal fuel in composite propellants due to its higher enthalpy of oxidation. Aluminum powder, however, faces some difficulties in primary applications. The characteristics of small particle size and large specific surface area of the nano aluminum powder have great advantages in improving the burning speed and the burning efficiency of the propellant, but the technical problems caused by the extremely easy oxidation and large viscosity of the nano aluminum powder are two reasons for limiting the application of the nano aluminum powder in the propellant (preparation and modification of the nano metal powder and the application of the nano metal powder in the propellant [ J ]. chemical propellant and high polymer material, 2017,15(04): 7-14.). The micron aluminum powder has low cost, and has higher active aluminum content than the nanometer aluminum powder, so that the micron aluminum powder is still applied to the existing propellant formula.
The micron aluminum powder also has a great disadvantage of low combustion efficiency, which is a major problem to be solved by related researchers at home and abroad at present. (progress of aluminum agglomeration research in solid propellant Combustion Process [ J)]Aerospace report 2016,37(4):371-]The explosive and fire journal, 2016,39(06): 74-79). Iodate can react with aluminum powder violently to release a large amount of heat and gas, and the iodate-coated micron aluminum powder is used for replacing the conventional micron aluminum powder in the composite propellant, so that the size of a combustion product of the iodate-coated micron aluminum powder is hopeful to be lower than that of the original aluminum powder, and the combustion efficiency (IO) of aluminum powder in the composite propellant is greatly increased3)3by employment of tea polyphenols as an interfacial layer[J].Chemical Engineering Journal,2020,381:122747.)。
Disclosure of Invention
In order to overcome the defect that the combustion efficiency of the aluminum powder composite propellant prepared by the existing method is low, the invention provides a four-component composite propellant containing iodate coated aluminum powder and a preparation method thereof. The four-component composite propellant containing iodate coated modified aluminum powder, oxidant, binder, plasticizer and curing agent is prepared by uniformly mixing, curing and crosslinking. The preparation method comprises the steps of coating micron aluminum powder by a connecting agent BL in an oxygen-containing environment through polymerization reaction in a weakly alkaline environment, filtering, cleaning and drying, and then dispersing the coated aluminum powder into distilled water again. Dropwise adding nitrate solution and iodic acid solution into the dispersion liquid coated with the aluminum powder under the stirring condition, and growing iodate on the surface in situ to obtain iodate-coated micrometer aluminum powder Al @ BL @ M (IO)3)xThe obtained Al @ BLM (IO)3)xThe propellant slurry is vacuum poured into a mold or an engine shell, and then is subjected to a crosslinking reaction at a certain temperature to be cured. Because the iodate contains metal cations and has a combustion catalysis effect on the propellant, the four-component composite propellant containing the iodate coated aluminum powder has a high combustion speed characteristic.
The technical scheme adopted by the invention for solving the technical problems is as follows: the four-component composite propellant containing iodate coated aluminum powder is characterized in that after a connecting agent is used for coating the aluminum powder, iodate is generated on the surface of the aluminum powder in situ, and the four-component composite propellant is prepared by mixing the following components in parts by weight to prepare propellant slurry and crosslinking and curing the propellant slurry:
Figure BDA0002324884160000021
the preparation method of the four-component composite propellant containing the iodate coated aluminum powder is characterized by comprising the following steps:
step one, controlling the pH of a solution to be 8.5 in a NaCl-Tris buffer solution at the temperature of 25-30 ℃, adding aluminum powder and a connecting agent,and stirring for 4 hours to obtain the aluminum powder Al @ BL coated by the connecting agent, wherein the concentration ratio of the aluminum powder to the connecting agent is 2: 1. Then according to the chemical reaction equation xHIO3+M(NO3)x→M(IO3)x+xHNO3Adding the corresponding HIO3And nitrate M (NO)3)xStirring for 0.5h to obtain Al @ BL @ M (IO) containing the following parts by weight3)xThen, the mixture is filtered, washed and dried.
10-20 parts of aluminum powder
0.5-5 of connecting agent
Iodate 1.0-10
Step two, mixing Al @ BL @ M (MIO)3)xAnd putting the oxidant and the ammonium nitrate explosive into a drying oven, setting the temperature to be 50-70 ℃, and drying for 12-48 h.
And step three, mixing the following components in parts by weight, and uniformly stirring for 0.5-1.5 h at 50-80 ℃.
Figure BDA0002324884160000031
And step four, vacuum casting the propellant slurry into a mold or an engine shell, wherein the vacuum casting time is 0.5-1 h.
And fifthly, transferring the mold filled with the propellant slurry into an oven for heating and curing, wherein the curing temperature is 80-90 ℃, and the curing time is 72-96 hours.
The aluminum powder is micron aluminum powder with the average particle size of more than 1.2 mu m.
The storage time of the micron aluminum powder is not more than one year from the preparation.
The connecting agent is one or more of tea polyphenol, epigallocatechin gallate and tannic acid.
The iodate is any one of ferric iodate, cupric iodate, silver iodate, nickel iodate or cobalt iodate.
The oxidant is a mixture of ammonium perchlorate AP and hexogen RDX.
The binder is hydroxyl-terminated polybutadiene HTPB.
The plasticizer is dioctyl sebacate DOS.
The curing agent is isophorone diisocyanate (IPDI).
The invention has the beneficial effects that: the four-component composite propellant containing iodate coated aluminum powder is prepared by uniformly mixing iodate coated modified aluminum powder, an oxidant, a binder, a plasticizer and a curing agent, curing and crosslinking. The preparation method comprises the steps of coating micron aluminum powder by a connecting agent BL in an oxygen-containing environment through polymerization reaction in a weakly alkaline environment, filtering, cleaning and drying, and then dispersing the coated aluminum powder into distilled water again. Dropwise adding nitrate solution and iodic acid solution into the dispersion liquid coated with the aluminum powder under the stirring condition, and growing iodate on the surface in situ to obtain iodate-coated micrometer aluminum powder Al @ BL @ M (IO)3)xThe obtained Al @ BLM (IO)3)xThe propellant slurry is vacuum poured into a mold or an engine shell, and then is subjected to a crosslinking reaction at a certain temperature to be cured. Because the iodate contains metal cations and has a combustion catalysis effect on the propellant, the four-component composite propellant containing the iodate coated aluminum powder has a high combustion speed characteristic.
The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments.
Drawings
FIG. 1 is a flow chart of the preparation method of the four-component composite propellant containing iodate coated aluminum powder.
FIG. 2 is a particle size distribution plot of propellant combustion products according to an embodiment of the present invention.
Detailed Description
The following examples refer to fig. 1-2.
The @ used in the invention is defined as cladding, and M refers to Fe, Cu, Bi, Co and Ni.
Example 1: a four-component composite propellant of conventional aluminum powder is used as a comparative example, and a mixture of ammonium perchlorate AP and hexogen RDX is selected as an oxidant; the binder is hydroxyl-terminated polybutadiene HTPB, and the curing agent is isophorone diisocyanate IPDI; the plasticizer is selected from dioctyl sebacate DOS; the fuel is Al, and the specific component ratio is referred to table one.
The specific manufacturing steps of the composite propellant are as follows:
step one, raw material treatment: and putting the Al, the ammonium perchlorate and the hexogen into a drying oven, setting the temperature to be 60 ℃, and drying for 24 hours.
Step two, weighing and mixing: mixing the components, stirring uniformly for 120min at 60 deg.C.
Step three, vacuum pouring: and (3) vacuum-casting the propellant slurry into a mold or an engine shell, wherein the vacuum-casting time is 1 h.
Step four, curing: and transferring the mold filled with the propellant slurry into an oven for heating and curing, wherein the curing temperature is 90 ℃, and the curing time is 72 hours.
Step five, preparing the medicine: demoulding after the curing is completed and processing the propellant into medicinal strips with the size of-5 multiplied by 25 mm.
It can be seen from Table two that the propellant of comparative example 1 has a burning rate of 5.12m s-1From FIG. 2, it can be seen that the agglomerated average particle size of the combustion product of example 1 was 4.06 μm, which is 238% larger than the particle size of the initial aluminum powder, which is 1.2 μm.
Example 2: al @ TA @ Fe (IO)3)3The oxidant is a mixture of ammonium perchlorate AP and hexogen RDX; the binder is hydroxyl-terminated polybutadiene HTPB; the curing agent is isophorone diisocyanate (IPDI); the plasticizer is selected from dioctyl sebacate DOS; the fuel is Al @ TA @ Fe (IO)3)3Specific component ratios thereof are shown in table 1, for example.
The specific manufacturing steps of the composite propellant are as follows:
step one, at the temperature of 25 ℃, in a NaCl-Tris buffer solution, controlling the pH of the solution to be 8.5, adding aluminum powder and tannic acid TA, wherein the concentration ratio of the aluminum powder to the tannic acid TA is 2:1, and stirring for 4 hours to obtain the tannic acid TA coated aluminum powder Al @ TA. Then according to the chemical reaction equation xHIO3+M(NO3)x→M(IO3)x+xHNO3Adding the corresponding HIO3And Fe (NO)3)3So that Fe (IO) is generated3)3The weight ratio of the Al to the Fe is 2.5, and the mixture is stirred for 0.5h to obtain Al @ TA @ Fe (IO)3)3Then, the mixture is filtered, washed and dried.
Step two, raw material treatment: mixing Al @ TA @ Fe (IO)3)3And putting the ammonium perchlorate and the hexogen into an oven, setting the temperature to be 60 ℃, and drying for 24 hours.
Step three, weighing and mixing: mixing the components, stirring uniformly for 120min at 60 deg.C.
Step four, vacuum pouring: and (3) vacuum-casting the propellant slurry into a mold or an engine shell, wherein the vacuum-casting time is 1 h.
Step five, curing: and transferring the mold filled with the propellant slurry into an oven for heating and curing, wherein the curing temperature is 90 ℃, and the curing time is 72 hours.
Step six, preparing the pharmaceutical strip: demoulding after the curing is completed and processing the propellant into medicinal strips with the size of-5 multiplied by 25 mm.
From Table II, it can be seen that the propellant of example 2 has a burning rate of 6.13m s-1Increased by 1.01m s compared with example 1-1(ii) a It can be seen from FIG. 2 that the agglomerated average particle size of the combustion product of example 2 was 0.51 μm, which is a 690% reduction from comparative example 1, and was 42% of the particle size of the initial aluminum powder, which is 1.2 μm.
Example 3: al @ TA @ Cu (IO)3)2The oxidant is a mixture of ammonium perchlorate AP and hexogen RDX; the binder is hydroxyl-terminated polybutadiene HTPB; the curing agent is isophorone diisocyanate (IPDI); the plasticizer is selected from dioctyl sebacate DOS; the fuel is Al @ TA @ Cu (IO)3)2Specific component ratios thereof are shown in table 1, for example.
The specific manufacturing steps of the composite propellant are as follows:
step one, at the temperature of 28 ℃, in a NaCl-Tris buffer solution, controlling the pH of the solution to be 8.5, adding aluminum powder and TA, wherein the concentration ratio of the aluminum powder to the TA is 2:1, and stirring for 4 hours to obtain TA-coated aluminum powder Al @ TA. Then followChemical reaction equation xHIO3+M(NO3)x→M(IO3)x+xHNO3Adding the corresponding HIO3And Cu (NO)3)2So that Fe (IO) is generated3)3The weight ratio of the Al to the TA is 2.5, and the Al to the TA to the Cu (IO) is obtained after stirring for 0.5h3)2Then, the mixture is filtered, washed and dried.
Step two, raw material treatment: mixing Al @ TA @ Cu (IO)3)2And putting the ammonium perchlorate and the hexogen into an oven, setting the temperature to be 50 ℃, and drying for 12 h.
Step three, weighing and mixing: mixing the components, stirring uniformly for 30min at 50 deg.C.
Step four, vacuum pouring: and (3) vacuum-casting the propellant slurry into a mold or an engine shell, wherein the vacuum-casting time is 0.5 h.
Step five, curing: and transferring the mold filled with the propellant slurry into an oven for heating and curing, wherein the curing temperature is 80 ℃, and the curing time is 96 hours.
Step six, preparing the pharmaceutical strip: demoulding after the curing is completed and processing the propellant into medicinal strips with the size of-5 multiplied by 25 mm.
From Table II, it can be seen that the propellant burning rate of example 3 is 5.44m s-1Increased by 0.32m s compared with example 1-1(ii) a It can be seen from FIG. 2 that the agglomerated average particle size of the combustion product of example 3 was 1.41 μm, which is a 250% reduction from comparative example 1, and is 120% of the particle size of the initial aluminum powder, which is 1.2 μm.
Example 4: al @ TP @ Fe (IO)3)3The oxidant is a mixture of ammonium perchlorate AP and hexogen RDX; the binder is hydroxyl-terminated polybutadiene HTPB; the curing agent is isophorone diisocyanate (IPDI); the plasticizer is selected from dioctyl sebacate DOS; the fuel is Al @ TA @ Fe (IO)3)3Specific component ratios thereof are shown in table 1, for example.
The specific manufacturing steps of the composite propellant are as follows:
step one, at the temperature of 28 ℃, in NaCl-Tris buffer solution, controlling the pH of the solution to be 8.5, adding aluminum powder and tea polyphenol TP, aluminumAnd stirring for 4 hours to obtain TP-coated aluminum powder Al @ TP, wherein the concentration ratio of the powder to the TA is 2: 1. Then according to the chemical reaction equation xHIO3+M(NO3)x→M(IO3)x+xHNO3Adding the corresponding HIO3And Fe (NO)3)3So that Fe (IO) is generated3)3The weight ratio of the Al to the TP is 2.5, and the mixture is stirred for 0.5h to obtain Al @ TP @ Fe (IO)3)3Then, the mixture is filtered, washed and dried.
Step two, raw material treatment: mixing Al @ TP @ Fe (IO)3)3And putting the ammonium perchlorate and the hexogen into an oven, setting the temperature to be 50 ℃, and drying for 36 hours.
Step three, weighing and mixing: mixing the components, stirring uniformly for 90min at 70 deg.C.
Step four, vacuum pouring: and (3) vacuum-casting the propellant slurry into a mold or an engine shell, wherein the vacuum-casting time is 0.5 h.
Step five, curing: and transferring the mold filled with the propellant slurry into an oven for heating and curing, wherein the curing temperature is 85 ℃, and the curing time is 84 h.
Step six, preparing the pharmaceutical strip: demoulding after the curing is completed and processing the propellant into medicinal strips with the size of-5 multiplied by 25 mm.
From Table II, it can be seen that the burning rate of the propellant of example 4 is 7.09m s-1Increased by 1.97m s compared with example 1-1(ii) a It can be seen from FIG. 2 that the agglomerated average particle size of the combustion product of example 4 was 0.97 μm, which is a 320% reduction from comparative example 1, and is 80% of the particle size of the initial aluminum powder, which is 1.2 μm.
Example 5: al @ TP @ Cu (IO)3)2The oxidant is a mixture of ammonium perchlorate AP and hexogen RDX; the binder is hydroxyl-terminated polybutadiene HTPB; the curing agent is isophorone diisocyanate (IPDI); the plasticizer is selected from dioctyl sebacate DOS; the fuel is Al @ TP @ Cu (IO)3)2Specific component ratios thereof are shown in table 1, for example.
The specific manufacturing steps of the composite propellant are as follows:
step one, under the temperature of 30 ℃,and (2) in NaCl-Tris buffer solution, controlling the pH of the solution to be 8.5, adding aluminum powder and TP, wherein the concentration ratio of the aluminum powder to the TA is 2:1, and stirring for 4h to obtain TP-coated aluminum powder Al @ TP. Then according to the chemical reaction equation xHIO3+M(NO3)x→M(IO3)x+xHNO3Adding the corresponding HIO3And Cu (NO)3)2So that Fe (IO) is generated3)3The weight ratio of the Al to the TP is 2.5, and the mixture is stirred for 0.5h to obtain Al @ TP @ Cu (IO)3)2Then, the mixture is filtered, washed and dried.
Step two, raw material treatment: mixing Al @ TP @ Cu (IO)3)2And putting the ammonium perchlorate and the hexogen into an oven, and drying for 48 hours at the set temperature of 70 ℃.
Step three, weighing and mixing: mixing the components, stirring uniformly for 120min at 80 deg.C.
Step four, vacuum pouring: and (3) vacuum-casting the propellant slurry into a mold or an engine shell, wherein the vacuum-casting time is 1 h.
Step five, curing: and transferring the mold filled with the propellant slurry into an oven for heating and curing, wherein the curing temperature is 85 ℃, and the curing time is 84 h.
Step six, preparing the pharmaceutical strip: demoulding after the curing is completed and processing the propellant into medicinal strips with the size of-5 multiplied by 25 mm.
From Table II, it can be seen that the burning rate of the propellant of example 5 is 5.66m s-1Increased by 0.55m s compared with example 1-1(ii) a It can be seen from FIG. 2 that the agglomerated average particle size of the combustion product of example 5 was 0.50 μm, which is a 690% reduction from comparative example 1, and is 42% of the particle size of the initial aluminum powder, which is 1.2 μm.
The formulations for all examples and the theoretical specific impulse calculated using the CEA software are shown in Table 1, and the burning rates at 1MPa under argon are shown in Table two.
TABLE 1 formulation and theoretical impact for examples 1-7
Figure BDA0002324884160000081
Note: the theoretical specific impulse is obtained by thermodynamic calculation software CEA and calculation according to the formation enthalpy data of aerospace industry standard QJ 1953-90. In the table √ indicates that the substance is present in the propellant formulation as encapsulated μ -Al.
TABLE 2 burn rates of examples 1-7 at 1MPa
Figure BDA0002324884160000082
。

Claims (10)

1. The four-component composite propellant containing the iodate coated aluminum powder is characterized in that after the aluminum powder is coated by a connecting agent, iodate is generated on the surface of the aluminum powder in situ, and the four-component composite propellant is prepared by mixing the following components in parts by weight to prepare propellant slurry and crosslinking and curing the propellant slurry:
Figure FDA0002324884150000011
2. the method for preparing the four-component composite propellant containing the iodate coated aluminum powder as claimed in claim 1 is characterized by comprising the following steps:
step one, controlling the pH of a solution to be 8.5 in a NaCl-Tris buffer solution at the temperature of 25-30 ℃, adding aluminum powder and a connecting agent, wherein the concentration ratio of the aluminum powder to the connecting agent is 2:1, and stirring for 4 hours to obtain connecting agent coated aluminum powder Al @ BL; then according to the chemical reaction equation xHIO3+M(NO3)x→M(IO3)x+xHNO3Adding the corresponding HIO3And nitrate M (NO)3)xStirring for 0.5h to obtain Al @ BL @ M (IO) containing the following parts by weight3)xThen filtering, cleaning and drying;
10-20 parts of aluminum powder
0.5-5 of connecting agent
Iodate 1.0-10
Step two, mixing Al @ BL @ M (MIO)3)xOxidizer and ammonium nitrate explosivePutting the mixture into a drying oven, setting the temperature to be 50-70 ℃, and drying for 12-48 h;
step three, mixing the following components in parts by weight, and uniformly stirring for 0.5-1.5 h at the stirring temperature of 50-80 ℃;
Figure FDA0002324884150000012
Figure FDA0002324884150000021
step four, vacuum casting the propellant slurry into a mold or an engine shell, wherein the vacuum casting time is 0.5-1 h;
and fifthly, transferring the mold filled with the propellant slurry into an oven for heating and curing, wherein the curing temperature is 80-90 ℃, and the curing time is 72-96 hours.
3. The iodate-coated aluminum powder-containing four-component composite propellant as claimed in claim 1, wherein: the aluminum powder is micron aluminum powder with the average particle size of more than 1.2 mu m.
4. The iodate-coated aluminum powder-containing four-component composite propellant as claimed in claim 3, wherein: the storage time of the micron aluminum powder is not more than one year from the preparation.
5. The iodate-coated aluminum powder-containing four-component composite propellant as claimed in claim 1, wherein: the connecting agent is one or more of tea polyphenol, epigallocatechin gallate and tannic acid.
6. The iodate-coated aluminum powder-containing four-component composite propellant as claimed in claim 1, wherein: the iodate is any one of ferric iodate, cupric iodate, silver iodate, nickel iodate or cobalt iodate.
7. The iodate-coated aluminum powder-containing four-component composite propellant as claimed in claim 1, wherein: the oxidant is a mixture of ammonium perchlorate AP and hexogen RDX.
8. The iodate-coated aluminum powder-containing four-component composite propellant as claimed in claim 1, wherein: the binder is hydroxyl-terminated polybutadiene HTPB.
9. The iodate-coated aluminum powder-containing four-component composite propellant as claimed in claim 1, wherein: the plasticizer is dioctyl sebacate DOS.
10. The iodate-coated aluminum powder-containing four-component composite propellant as claimed in claim 1, wherein: the curing agent is isophorone diisocyanate (IPDI).
CN201911312356.8A 2019-12-18 2019-12-18 Four-component composite propellant containing iodate coated aluminum powder and preparation method thereof Pending CN111087273A (en)

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112341299A (en) * 2020-11-05 2021-02-09 南京理工大学 Preparation of nano core-shell Al @ KIO by spray coprecipitation method4Thermite method
CN114309593A (en) * 2021-09-24 2022-04-12 中北大学 Preparation method of multi-transition metal coated micron aluminum composite fuel

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20050097817A (en) * 2004-04-02 2005-10-10 국방과학연구소 Solid propellent containing metal deactivator and preparation method thereof
CN106831279A (en) * 2016-11-28 2017-06-13 湖北航天化学技术研究所 A kind of cold curing propellant

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20050097817A (en) * 2004-04-02 2005-10-10 국방과학연구소 Solid propellent containing metal deactivator and preparation method thereof
CN106831279A (en) * 2016-11-28 2017-06-13 湖北航天化学技术研究所 A kind of cold curing propellant

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
DEYUN TANG ET. AL.: "Controlled reactivity of metastable n-Al@Bi(IO3)3 by employment of tea polyphenols as an interfacial layer", 《CHEMICAL ENGINEERING JOURNAL》 *

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112341299A (en) * 2020-11-05 2021-02-09 南京理工大学 Preparation of nano core-shell Al @ KIO by spray coprecipitation method4Thermite method
CN114309593A (en) * 2021-09-24 2022-04-12 中北大学 Preparation method of multi-transition metal coated micron aluminum composite fuel
CN114309593B (en) * 2021-09-24 2024-04-05 中北大学 Preparation method of multielement transition metal coated micron aluminum composite fuel

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Application publication date: 20200501