CN116082102B - Ammonium nitrate-based ternary composite electric control solid propellant and preparation method thereof - Google Patents
Ammonium nitrate-based ternary composite electric control solid propellant and preparation method thereof Download PDFInfo
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- CN116082102B CN116082102B CN202310125660.1A CN202310125660A CN116082102B CN 116082102 B CN116082102 B CN 116082102B CN 202310125660 A CN202310125660 A CN 202310125660A CN 116082102 B CN116082102 B CN 116082102B
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- 239000004449 solid propellant Substances 0.000 title claims abstract description 67
- PAWQVTBBRAZDMG-UHFFFAOYSA-N 2-(3-bromo-2-fluorophenyl)acetic acid Chemical compound OC(=O)CC1=CC=CC(Br)=C1F PAWQVTBBRAZDMG-UHFFFAOYSA-N 0.000 title claims abstract description 63
- 239000011206 ternary composite Substances 0.000 title claims abstract description 40
- 238000002360 preparation method Methods 0.000 title claims abstract description 29
- 239000003380 propellant Substances 0.000 claims description 48
- 239000003822 epoxy resin Substances 0.000 claims description 46
- 229920000647 polyepoxide Polymers 0.000 claims description 46
- MUBZPKHOEPUJKR-UHFFFAOYSA-N Oxalic acid Chemical compound OC(=O)C(O)=O MUBZPKHOEPUJKR-UHFFFAOYSA-N 0.000 claims description 33
- 238000003756 stirring Methods 0.000 claims description 31
- GDDNTTHUKVNJRA-UHFFFAOYSA-N 3-bromo-3,3-difluoroprop-1-ene Chemical compound FC(F)(Br)C=C GDDNTTHUKVNJRA-UHFFFAOYSA-N 0.000 claims description 29
- 239000002994 raw material Substances 0.000 claims description 19
- 239000002002 slurry Substances 0.000 claims description 19
- 239000000654 additive Substances 0.000 claims description 13
- 230000000996 additive effect Effects 0.000 claims description 13
- WNROFYMDJYEPJX-UHFFFAOYSA-K aluminium hydroxide Chemical compound [OH-].[OH-].[OH-].[Al+3] WNROFYMDJYEPJX-UHFFFAOYSA-K 0.000 claims description 11
- 235000006408 oxalic acid Nutrition 0.000 claims description 11
- YNKVVRHAQCDJQM-UHFFFAOYSA-P diazanium dinitrate Chemical compound [NH4+].[NH4+].[O-][N+]([O-])=O.[O-][N+]([O-])=O YNKVVRHAQCDJQM-UHFFFAOYSA-P 0.000 claims description 10
- -1 polytetrafluoroethylene Polymers 0.000 claims description 9
- 229920001343 polytetrafluoroethylene Polymers 0.000 claims description 9
- 239000004810 polytetrafluoroethylene Substances 0.000 claims description 9
- 229920005989 resin Polymers 0.000 claims description 9
- 239000011347 resin Substances 0.000 claims description 9
- 238000007711 solidification Methods 0.000 claims description 9
- 230000008023 solidification Effects 0.000 claims description 9
- PXKLMJQFEQBVLD-UHFFFAOYSA-N bisphenol F Chemical compound C1=CC(O)=CC=C1CC1=CC=C(O)C=C1 PXKLMJQFEQBVLD-UHFFFAOYSA-N 0.000 claims description 6
- GYZLOYUZLJXAJU-UHFFFAOYSA-N diglycidyl ether Chemical compound C1OC1COCC1CO1 GYZLOYUZLJXAJU-UHFFFAOYSA-N 0.000 claims description 6
- 238000000034 method Methods 0.000 claims description 6
- 239000002245 particle Substances 0.000 claims description 6
- VPWNQTHUCYMVMZ-UHFFFAOYSA-N 4,4'-sulfonyldiphenol Chemical compound C1=CC(O)=CC=C1S(=O)(=O)C1=CC=C(O)C=C1 VPWNQTHUCYMVMZ-UHFFFAOYSA-N 0.000 claims description 3
- DGUJJOYLOCXENZ-UHFFFAOYSA-N 4-[2-[4-(oxiran-2-ylmethoxy)phenyl]propan-2-yl]phenol Chemical compound C=1C=C(OCC2OC2)C=CC=1C(C)(C)C1=CC=C(O)C=C1 DGUJJOYLOCXENZ-UHFFFAOYSA-N 0.000 claims description 3
- JRPRCOLKIYRSNH-UHFFFAOYSA-N bis(oxiran-2-ylmethyl) benzene-1,2-dicarboxylate Chemical compound C=1C=CC=C(C(=O)OCC2OC2)C=1C(=O)OCC1CO1 JRPRCOLKIYRSNH-UHFFFAOYSA-N 0.000 claims description 3
- 238000002156 mixing Methods 0.000 claims description 3
- 239000007787 solid Substances 0.000 abstract description 6
- 238000009472 formulation Methods 0.000 description 13
- 239000000203 mixture Substances 0.000 description 13
- 238000005303 weighing Methods 0.000 description 12
- 238000002485 combustion reaction Methods 0.000 description 10
- NILJXUMQIIUAFY-UHFFFAOYSA-N hydroxylamine;nitric acid Chemical compound ON.O[N+]([O-])=O NILJXUMQIIUAFY-UHFFFAOYSA-N 0.000 description 7
- 239000007788 liquid Substances 0.000 description 6
- 230000008033 biological extinction Effects 0.000 description 4
- 238000003860 storage Methods 0.000 description 4
- 239000007800 oxidant agent Substances 0.000 description 3
- 230000001590 oxidative effect Effects 0.000 description 3
- 238000000354 decomposition reaction Methods 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 108091092878 Microsatellite Proteins 0.000 description 1
- GRYLNZFGIOXLOG-UHFFFAOYSA-N Nitric acid Chemical compound O[N+]([O-])=O GRYLNZFGIOXLOG-UHFFFAOYSA-N 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 239000012752 auxiliary agent Substances 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 239000003431 cross linking reagent Substances 0.000 description 1
- 239000003814 drug Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005684 electric field Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000011010 flushing procedure Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 229910017604 nitric acid Inorganic materials 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 239000008247 solid mixture Substances 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 231100000331 toxic Toxicity 0.000 description 1
- 230000002588 toxic effect Effects 0.000 description 1
Classifications
-
- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B31/00—Compositions containing an inorganic nitrogen-oxygen salt
- C06B31/28—Compositions containing an inorganic nitrogen-oxygen salt the salt being ammonium nitrate
-
- 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
Landscapes
- Chemical & Material Sciences (AREA)
- Organic Chemistry (AREA)
- Inorganic Chemistry (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Epoxy Resins (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
Abstract
The invention discloses an ammonium nitrate-based ternary composite electric control solid propellant and a preparation method thereof. The ammonium nitrate-based electric control solid propellant has good flame insensitive property, can be ignited and burnt only when the direct-current voltage is 140V, is extinguished immediately after the power supply is disconnected, and has positive correlation between the burning speed and the voltage amplitude. The preparation method is simple, green and environment-friendly, has potential to amplify the preparation process, and has application prospect of controlling the attitude and orbit of a solid engine or a satellite.
Description
Technical Field
The invention belongs to the field of solid propellant research, and particularly relates to an ammonium nitrate-based ternary composite electric control solid propellant and a preparation method thereof.
Background
The energy source and working medium for obtaining thrust of the solid rocket engine are derived from a solid mixture and are called solid propellant. Compared with liquid rocket propellant, the solid propellant has the advantages of excellent storage property, excellent carrying property, high energy density, low cost and the like. It also has some inherent disadvantages such as lower specific flushing, limited working time and poor repeated start-stop. Although liquid propellants have good combustion controllability, which can extinguish and re-burn at any time, they are often extremely toxic and require complex low temperature high pressure storage devices to maintain their liquid state, otherwise the liquid propellants are very unstable over a higher temperature range. The continued development of missile weapons and spacecraft technology has placed higher demands on the propellants that power them. For example, small space vehicles such as microsatellites are required to frequently implement orbital, formation flight and attitude adjustment, a propulsion system is required to have multiple ignition and thrust adjustment functions, and random control of thrust is also a trend of tactical missile solid engine development.
The method aims at the problems that the current solid rocket engine cannot be started and stopped repeatedly, and the requirement of controllable thrust cannot be met. The electric control solid propellant can combine the advantages of solid rocket and liquid rocket, and is a propellant with the characteristics of repeated ignition and flameout, controllable combustion speed, controllable output energy, environmental friendliness and low risk.
At present, hydroxylamine nitrate is often used as an oxidant for the electric control solid propellant, but because the conductivity of the hydroxylamine nitrate is high, siphon current is easily generated on the surface far away from the propellant, so that the surface of the propellant is burnt in a large area. In addition, the ignition voltage of the hydroxylamine nitrate electronically controlled solid propellant is above 140V; hydroxylamine nitrate is gradually decomposed during storage, and nitric acid generated after decomposition accelerates the decomposition of the hydroxylamine nitrate, so that the performance of the hydroxylamine nitrate electronically controlled solid propellant in long-term storage is deteriorated; the preparation method of the type of electric control solid propellant is complex, and the batch preparation of the propellant is difficult to realize by using the liquid oxidant.
Therefore, the research and development of the solid propellant which has low cost, environment protection, simple preparation, safety and stability, low ignition voltage and controllable combustion ignition/extinction by on/off has important significance.
Disclosure of Invention
Aiming at the defects and shortcomings in the existing solid propellant technology and overcoming the defects of the existing electric control solid propellant, the invention aims to provide the ammonium nitrate-based electric control solid propellant and the preparation method thereof.
In order to achieve the above purpose, the invention adopts the following technical scheme:
the ammonium nitrate-based ternary composite electronic control solid propellant consists of the following raw materials in percentage by mass:
ammonium nitrate: 33% -37%;
ammonium perchlorate: 33% -35%;
epoxy resin: 28% -34%;
the sum of the above components is 100%.
Optionally, an inorganic additive is also added, wherein the inorganic additive accounts for 4-8% of the total amount of the ammonium nitrate-based ternary composite electronically controlled solid propellant.
Optionally, the inorganic additive is at least one selected from aluminum hydroxide and oxalic acid.
Alternatively, ammonium nitrate: 33.4 to 34.4 percent;
ammonium perchlorate: 33.3%;
epoxy resin: 32.3 to 33.3 percent.
Optionally, aluminum hydroxide or oxalic acid is also added according to the percentage of the total amount of the ammonium nitrate-based ternary composite electronically controlled solid propellant.
Optionally, 4% of aluminum hydroxide and 4% of oxalic acid are added according to the percentage of the total amount of the ammonium nitrate-based ternary composite electronically controlled solid propellant.
Optionally, the ammonium perchlorate has a particle size of 200 μm and the ammonium nitrate has a particle size of 350. Mu.m.
Optionally, the epoxy resin is selected from at least one of bisphenol a glycidyl ether resin, diglycidyl phthalate, bisphenol S glycidyl ether resin and bisphenol F glycidyl ether resin.
The invention relates to a preparation method of an ammonium nitrate-based ternary composite electric control solid propellant, which is the ammonium nitrate-based ternary composite electric control solid propellant provided by the invention;
the preparation method of the propellant comprises the following steps: dispersing ammonium nitrate and ammonium perchlorate in epoxy resin, adding a small amount of inorganic additive, stirring in vacuum at room temperature for 5-15 min, and curing at normal pressure and room temperature for 2-4 h to obtain the ternary composite electronically controlled solid propellant of ammonium nitrate-ammonium perchlorate-epoxy resin.
Optionally, the method specifically comprises the following steps:
sequentially mixing epoxy resin, ammonium nitrate and ammonium perchlorate at room temperature, adding an inorganic additive, and stirring under vacuum to obtain uniform and bubble-free medicinal slurry;
the stirring speed range is controlled between 200 and 300 revolutions per minute; the stirring time ranges from 5 minutes to 15 minutes;
and step two, directly pouring the uniformly stirred slurry obtained in the step one into a polytetrafluoroethylene mould at room temperature, and standing for 2 hours at normal pressure and room temperature to obtain the solid propellant formed by solidification.
Compared with the prior art, the invention has the following advantages:
(1) Compared with the hydroxylamine nitrate electric control solid propellant, the ammonium nitrate-ammonium perchlorate-epoxy resin ternary composite electric control solid propellant can be solidified at normal temperature so as to facilitate subsequent batch preparation due to the adoption of the epoxy resin as an adhesive.
(2) As the adopted oxidant is ammonium nitrate and ammonium perchlorate, mainly ammonium nitrate is influenced by electric energy and is decomposed and melted under the action of an electric field, and the generated ionic molten epoxy resin migrates and conducts electricity.
(3) The ammonium nitrate-based ternary composite electric control solid propellant does not need to add raw materials such as a curing agent, a cross-linking agent, a functional auxiliary agent and the like, and the preparation method is simpler and more convenient than other types of electric control solid propellants, and has the characteristics of low cost of raw materials and controllable combustion surface.
(4) When the electric ignition test is carried out on the ammonium nitrate-based ternary composite electric control solid propellant, the propellant can realize ignition under the direct-current voltage of 140V, and after the applied voltage is removed, the propellant can realize flameout. The ammonium nitrate-based ternary composite electronically controlled solid propellant is an ideal electronically controlled solid propellant formulation system.
(5) The method for preparing the electric control solid propellant has the advantages of low raw material cost, simple process, green pollution-free property, high safety, capability of carrying out casting molding of moulds of different shapes in a state of uniformly stirring medicine slurry in vacuum, good adaptability and potential application to solid engines or attitude and orbit control.
Drawings
The accompanying drawings are included to provide a further understanding of the disclosure, and are incorporated in and constitute a part of this specification, illustrate the disclosure and together with the description serve to explain, but do not limit the disclosure. In the drawings:
FIG. 1 is an electronically controlled solid propellant cured to shape according to example 1;
FIG. 2 shows the occurrence of sparks in the propellant immediately after power-on in example 1;
FIG. 3 is a graph of the propellant of example 1 burning at 140V;
FIG. 4 is the propellant extinction after the power failure of example 1;
fig. 5 is the appearance of the ammonium nitrate-based ternary composite electronically controlled solid propellant of example 1 after combustion.
Detailed Description
The invention utilizes the special electrochemical characteristic of ammonium nitrate, which is crosslinked with epoxy resin to form solid propellant, and the addition of ammonium perchlorate component can reduce the melting point of ammonium nitrate, so that a conductive area is generated when the ammonium nitrate burns, the resistance of the propellant is reduced, a conductive path is formed between electrodes, the electric control solid propellant realizes ignition combustion under ohmic heating effect, and when the power supply is disconnected, the propellant is extinguished immediately. The ternary composite electric control solid propellant can be influenced by electric energy to realize ignition and extinction.
The embodiment of the invention provides an ammonium nitrate-based ternary composite electric control solid propellant, which can meet the requirements of electric control solid propellant and can be solidified at room temperature, and the solid propellant comprises the following raw materials in percentage by mass: ammonium nitrate: 33% -37%; ammonium perchlorate: 33% -35%; epoxy resin: 28% -34%; the sum of the above components is 100%.
In the embodiment of the disclosure, an inorganic additive is also added, wherein the inorganic additive accounts for 4-8% of the total amount of the ammonium nitrate-based ternary composite electronically controlled solid propellant.
In an embodiment of the present disclosure, the inorganic additive is selected from at least one of aluminum hydroxide and oxalic acid.
In embodiments of the present disclosure, ammonium nitrate: 33.4 to 34.4 percent; ammonium perchlorate: 33.3%; epoxy resin: 32.3 to 33.3 percent.
In embodiments of the present disclosure, aluminum hydroxide or oxalic acid is also added in an amount of 4% by weight of the total amount of ammonium nitrate based ternary composite electronically controlled solid propellant.
In the embodiment of the disclosure, 4% of aluminum hydroxide and 4% of oxalic acid are also added in percentage of the total amount of the ammonium nitrate-based ternary composite electronically controlled solid propellant.
In the examples of the present disclosure, the particle size of ammonium perchlorate is 200 μm and the particle size of ammonium nitrate is 350 μm.
In an embodiment of the present disclosure, the epoxy resin is selected from at least one of bisphenol a glycidyl ether resin, diglycidyl phthalate, bisphenol S glycidyl ether resin, and bisphenol F glycidyl ether resin.
The preparation method of the ammonium nitrate-based ternary composite electric control solid propellant comprises the following steps: dispersing ammonium nitrate and ammonium perchlorate in epoxy resin, adding a small amount of inorganic additive, stirring in vacuum at room temperature for 5-15 min, and curing at normal pressure and room temperature for 2-4 h to obtain the ternary composite electronically controlled solid propellant of ammonium nitrate-ammonium perchlorate-epoxy resin.
Optionally, the method specifically comprises the following steps:
sequentially mixing epoxy resin, ammonium nitrate and ammonium perchlorate at room temperature, adding an inorganic additive, and stirring under vacuum to obtain uniform and bubble-free medicinal slurry; the stirring speed range is controlled between 200 and 300 revolutions per minute; the stirring time ranges from 5 minutes to 15 minutes;
and step two, directly pouring the uniformly stirred slurry obtained in the step one into a polytetrafluoroethylene mould at room temperature, and standing for 2 hours at normal pressure and room temperature to obtain the solid propellant formed by solidification.
The raw materials used in the examples of the present invention are all commercially available products.
The following specific embodiments of the present invention are given according to the above technical solutions, and it should be noted that the present invention is not limited to the following specific embodiments, and all equivalent changes made on the basis of the technical solutions of the present application fall within the protection scope of the present invention.
Example 1:
weighing raw materials according to the formula of the table 1;
the embodiment provides an ammonium nitrate-ammonium perchlorate-epoxy resin ternary composite propellant and a preparation method thereof, wherein the preparation method comprises the following steps:
weighing epoxy resin under the condition of room temperature, and adding the epoxy resin into a beaker;
sequentially adding ammonium nitrate and ammonium perchlorate into a beaker at room temperature, and stirring under vacuum to obtain uniformly-stirred and bubble-free medicinal slurry;
the stirring speed range is controlled to be 200 revolutions per minute; the stirring time range is 10 minutes;
and thirdly, directly pouring the uniformly stirred slurry obtained in the first step into a polytetrafluoroethylene mould at room temperature, and standing for 2 hours at normal pressure and room temperature to obtain the solid propellant formed by solidification.
Table 1 example 1 raw material formulation table
| Formulation components | Mass fraction/% |
| Ammonium nitrate | 33.4 |
| Ammonium perchlorate | 33.3 |
| Epoxy resin | 33.3 |
The measured ignition voltage of the propellant is 140V, and the density of the propellant is 1.23g/cm 3 Propellant processingThe theoretical specific impulse is 190.8s, and the ignition is repeated for 1 time.
FIG. 1 is a photograph of the appearance of the electronically controlled solid propellant cured and formed in accordance with example 1;
FIG. 2 is a photograph of the appearance of a spark in the propellant immediately upon power-up in example 1;
FIG. 3 is a photograph of the propellant of example 1 burning at 140V;
FIG. 4 is a photograph of the propellant extinguished after the power has been removed in example 1;
fig. 5 is a photograph showing the appearance of the ammonium nitrate-based ternary composite electronically controlled solid propellant of example 1 after combustion.
Fig. 1 and 5 illustrate the non-uniformity of the combustion surface back-shift before and after ignition of the propellant. Fig. 2-4 illustrate that the propellant first ignites from the region near the electrode, resulting in non-uniformity of the combustion surface.
Example 2:
weighing raw materials according to the formula of the table 2;
the embodiment provides an ammonium nitrate-ammonium perchlorate-epoxy resin ternary composite propellant and a preparation method thereof, wherein the preparation method comprises the following steps:
weighing epoxy resin under the condition of room temperature, and adding the epoxy resin into a beaker;
sequentially adding ammonium nitrate and ammonium perchlorate into a beaker at room temperature, and stirring under vacuum to obtain uniformly-stirred and bubble-free medicinal slurry;
the stirring speed range is controlled to be 200 revolutions per minute; the stirring time range is 10 minutes;
and thirdly, directly pouring the uniformly stirred slurry obtained in the first step into a polytetrafluoroethylene mould at room temperature, and standing for 2.5 hours at normal pressure and room temperature to obtain the solid propellant formed by solidification.
Table 2 example 2 raw material formulation table
| Formulation components | Mass fraction/% |
| Ammonium nitrate | 34.4 |
| Ammonium perchlorate | 33.3 |
| Epoxy resin | 32.3 |
The measured ignition voltage of the propellant is 140V, and the density of the propellant is 1.19g/cm 3 The theoretical specific impulse of the propellant is 191.6s, and the ignition can be repeated for 1 time.
Example 3:
weighing raw materials according to the formula of the table 3;
the embodiment provides an ammonium nitrate-ammonium perchlorate-epoxy resin ternary composite propellant and a preparation method thereof, wherein the preparation method comprises the following steps:
weighing epoxy resin under the condition of room temperature, and adding the epoxy resin into a beaker;
sequentially adding ammonium nitrate and ammonium perchlorate into a beaker at room temperature, and stirring under vacuum to obtain uniformly-stirred and bubble-free medicinal slurry;
the stirring speed range is controlled to be 200 revolutions per minute; the stirring time range is 10 minutes;
and thirdly, directly pouring the uniformly stirred slurry obtained in the first step into a polytetrafluoroethylene mould at room temperature, and standing for 2.5 hours at normal pressure and room temperature to obtain the solid propellant formed by solidification.
Table 3 example 3 raw material formulation table
| Formulation components | Mass fraction/% |
| Ammonium nitrate | 37 |
| Ammonium perchlorate | 35 |
| Epoxy resin | 28 |
The actual measured ignition voltage of the propellant is 140V, the density of the propellant is 1.13g/cm < 3 >, the theoretical specific impulse of the propellant is 197.2s, and the ignition can be repeated for 2 times.
Example 4:
weighing raw materials according to the formula of the table 4;
the embodiment provides an ammonium nitrate-ammonium perchlorate-epoxy resin ternary composite propellant and a preparation method thereof, wherein the preparation method comprises the following steps:
weighing epoxy resin under the condition of room temperature, and adding the epoxy resin into a beaker;
sequentially adding ammonium nitrate and ammonium perchlorate into a beaker at room temperature, adding aluminum hydroxide additionally, and stirring under vacuum to obtain uniformly-stirred and bubble-free medicinal slurry;
the stirring speed range is controlled to be 200 revolutions per minute; the stirring time range is 10 minutes;
and thirdly, directly pouring the uniformly stirred slurry obtained in the first step into a polytetrafluoroethylene mould at room temperature, and standing for 2.5 hours at normal pressure and room temperature to obtain the solid propellant formed by solidification.
Table 4 example 4 raw material formulation table
| Formulation components | Mass fraction/% |
| Ammonium nitrate | 33.4 |
| Ammonium perchlorate | 33.3 |
| Epoxy resin | 33.3 |
| Aluminum hydroxide | 4 |
The actual measured ignition voltage of the propellant is 140V, the density of the propellant is 1.28g/cm < 3 >, the theoretical specific impulse of the propellant is 186.8s, and the ignition can be repeated for 3 times.
Example 5:
weighing raw materials according to the formula of the table 5;
the embodiment provides an ammonium nitrate-ammonium perchlorate-epoxy resin ternary composite propellant and a preparation method thereof, wherein the preparation method comprises the following steps:
weighing epoxy resin under the condition of room temperature, and adding the epoxy resin into a beaker;
sequentially adding ammonium nitrate and ammonium perchlorate into a beaker at room temperature, adding oxalic acid additionally, and stirring under vacuum to obtain uniformly-stirred and bubble-free medicinal slurry;
the stirring speed range is controlled to be 200 revolutions per minute; the stirring time range is 10 minutes;
and thirdly, directly pouring the uniformly stirred slurry obtained in the first step into a polytetrafluoroethylene mould at room temperature, and standing for 2.5 hours at normal pressure and room temperature to obtain the solid propellant formed by solidification.
Table 5 example 5 raw material formulation table
| Formulation components | Mass fraction/% |
| Ammonium nitrate | 33.4 |
| Ammonium perchlorate | 33.3 |
| Epoxy resin | 33.3 |
| Oxalic acid | 4 |
The actual measured ignition voltage of the propellant is 140V, the density of the propellant is 1.24g/cm < 3 >, the theoretical specific impulse of the propellant is 183.6s, and the ignition can be repeated for 3 times.
Example 6:
weighing raw materials according to the formula of the table 6;
the embodiment provides an ammonium nitrate-ammonium perchlorate-epoxy resin ternary composite propellant and a preparation method thereof, wherein the preparation method comprises the following steps:
weighing epoxy resin under the condition of room temperature, and adding the epoxy resin into a beaker;
sequentially adding ammonium nitrate and ammonium perchlorate into a beaker at room temperature, adding oxalic acid and aluminum hydroxide, and stirring in vacuum to obtain uniformly-stirred and bubble-free medicinal slurry;
the stirring speed range is controlled to be 200 revolutions per minute; the stirring time range is 10 minutes;
and thirdly, directly pouring the uniformly stirred slurry obtained in the first step into a polytetrafluoroethylene mould at room temperature, and standing for 2.5 hours at normal pressure and room temperature to obtain the solid propellant formed by solidification.
Table 5 example 5 raw material formulation table
| Formulation components | Mass fraction/% |
| Ammonium nitrate | 33.4 |
| Ammonium perchlorate | 33.3 |
| Epoxy resin | 33.3 |
| Aluminum hydroxide | 4 |
| Oxalic acid | 4 |
The actual measured ignition voltage of the propellant is 150V, the density of the propellant is 1.31g/cm < 3 >, the theoretical specific impulse of the propellant is 184.1s, and the ignition can be repeated for 7 times.
From the results of the above examples, it can be seen that the electronically controlled solid propellant prepared by the present invention can be prepared at normal temperature, and can undergo ignition combustion reaction at an applied voltage of 140V, and the propellant stops burning after power failure; when the inorganic additive is added, the propellant can realize repeated ignition and extinction for a larger number of times.
The preferred embodiments of the present disclosure have been described in detail above with reference to the accompanying drawings, but the present disclosure is not limited to the specific details of the above embodiments, and various simple modifications may be made to the technical solutions of the present disclosure within the scope of the technical concept of the present disclosure, and all the simple modifications belong to the protection scope of the present disclosure.
In addition, the specific features described in the foregoing embodiments may be combined in any suitable manner, and in order to avoid unnecessary repetition, the present disclosure does not further describe various possible combinations.
Moreover, any combination between the various embodiments of the present disclosure is possible as long as it does not depart from the spirit of the present disclosure, which should also be construed as the disclosure of the present disclosure.
Claims (6)
1. The ammonium nitrate-based ternary composite electric control solid propellant is characterized by comprising the following raw materials in percentage by mass:
ammonium nitrate: 33% -37%;
ammonium perchlorate: 33% -35%;
epoxy resin: 28% -34%;
the sum of the above components is 100%;
and adding 4% of aluminum hydroxide and 4% of oxalic acid according to the percentage of the total amount of the ammonium nitrate-based ternary composite electronically controlled solid propellant.
2. The ammonium nitrate-based ternary composite electronically controlled solid propellant of claim 1, wherein,
ammonium nitrate: 33.4 to 34.4 percent;
ammonium perchlorate: 33.3%;
epoxy resin: 32.3 to 33.3 percent.
3. The ammonium nitrate-based ternary composite electronically controlled solid propellant of claim 1, wherein the ammonium perchlorate has a particle size of 200 μm and the ammonium nitrate has a particle size of 350 μm.
4. The ammonium nitrate-based ternary composite electronically controlled solid propellant of claim 1, wherein the epoxy resin is selected from at least one of bisphenol a glycidyl ether resin, diglycidyl phthalate, bisphenol S glycidyl ether resin and bisphenol F glycidyl ether resin.
5. The preparation method of the ammonium nitrate-based ternary composite electric control solid propellant is characterized in that the ammonium nitrate-based ternary composite electric control solid propellant is the ammonium nitrate-based ternary composite electric control solid propellant according to any one of claims 2-4;
the preparation method of the propellant comprises the following steps: dispersing ammonium nitrate and ammonium perchlorate in epoxy resin, adding a small amount of inorganic additive, stirring in vacuum at room temperature for 5-15 min, and curing at normal pressure and room temperature for 2-4 h to obtain the ternary composite electronically controlled solid propellant of ammonium nitrate-ammonium perchlorate-epoxy resin.
6. The method for preparing the ammonium nitrate-based ternary composite electronically controlled solid propellant, which is characterized by comprising the following steps of:
sequentially mixing epoxy resin, ammonium nitrate and ammonium perchlorate at room temperature, adding an inorganic additive, and stirring under vacuum to obtain uniform and bubble-free medicinal slurry; the stirring speed range is controlled between 200 and 300 revolutions per minute; the stirring time ranges from 5 minutes to 15 minutes;
and step two, directly pouring the uniformly stirred slurry obtained in the step one into a polytetrafluoroethylene mould at room temperature, and standing for 2 hours at normal pressure and room temperature to obtain the solid propellant formed by solidification.
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|---|---|---|---|---|
| US4158583A (en) * | 1977-12-16 | 1979-06-19 | Nasa | High performance ammonium nitrate propellant |
| US5474625A (en) * | 1993-12-16 | 1995-12-12 | The United States Of America As Represented By The Secretary Of The Navy | Desensitized solid rocket propellant formulation |
| CN112694372A (en) * | 2020-12-25 | 2021-04-23 | 石仲仑 | Epoxy composite propellant, preparation method and application thereof |
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| US11124464B2 (en) * | 2016-09-09 | 2021-09-21 | Terves, Llc | High density hybrid rocket motor |
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|---|---|---|---|---|
| US4158583A (en) * | 1977-12-16 | 1979-06-19 | Nasa | High performance ammonium nitrate propellant |
| US5474625A (en) * | 1993-12-16 | 1995-12-12 | The United States Of America As Represented By The Secretary Of The Navy | Desensitized solid rocket propellant formulation |
| CN112694372A (en) * | 2020-12-25 | 2021-04-23 | 石仲仑 | Epoxy composite propellant, preparation method and application thereof |
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| A Study of the Electrothermal Method for Control over Combustion Velocity under Atmospheric Pressure of Energetic Condensed Systems Based on Ammonium Nitrate;I. V. Khoruzhii;《PHYSICOCHEMICAL STUDIES OF SYSTEMS AND PROCESSES》;1295-1299 * |
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