CN112608205A - Hydroxyl-terminated polyethylene oxide and propylene oxide random co-polyether type propellant and preparation method thereof - Google Patents
Hydroxyl-terminated polyethylene oxide and propylene oxide random co-polyether type propellant and preparation method thereof Download PDFInfo
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- CN112608205A CN112608205A CN202011483420.1A CN202011483420A CN112608205A CN 112608205 A CN112608205 A CN 112608205A CN 202011483420 A CN202011483420 A CN 202011483420A CN 112608205 A CN112608205 A CN 112608205A
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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
- C06B33/08—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 with a nitrated organic compound
- C06B33/10—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 with a nitrated organic compound the compound being an aromatic
-
- 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
- C06B21/0025—Compounding the ingredient the ingredient being a polymer bonded explosive or thermic component
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- 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
Abstract
The invention provides a hydroxyl-terminated polyethylene oxide and propylene oxide random co-polyether propellant and a preparation method thereof, wherein the hydroxyl-terminated polyethylene oxide and propylene oxide random co-polyether propellant comprises the following components in percentage by mass: adhesive: 6 to 15 percent; plasticizer: 5% -20%; oxidizing agent: 30% -65%; curing agent: 0.3% -1.5%; fuel: 5% -22%; other functional auxiliary agents: and the balance, wherein the adhesive adopts hydroxyl-terminated polyethylene oxide propylene oxide random copolyether, the number average molecular weight is 1000-10000, and the glass transition temperature is-70 to-85 ℃. According to the invention, by selecting a specific raw material combination and a proper process method, the prepared propellant has higher oxygen coefficient, low residue, excellent low-temperature performance and safety performance, can meet the 1.3-level danger level, is only combusted and does not detonate through all six low-vulnerability test examinations, and is suitable for the advanced tactical missile with higher requirements on the low-temperature performance and the safety of the propellant.
Description
Technical Field
The invention belongs to the technical field of solid propellants, relates to a hydroxyl-terminated polyethylene oxide and propylene oxide random co-polyether propellant and a preparation method thereof, and particularly relates to a hydroxyl-terminated polyethylene oxide and propylene oxide random co-polyether propellant which is good in low-temperature performance, high in safety and low in residue and can pass all six low-vulnerability tests and a preparation method thereof.
Background
Along with the continuous development of advanced high-performance missile weapons, higher requirements on the performance of a propellant are provided, the propellant has good low-temperature performance and high safety, and low residues become an important development direction of the propellant for the solid missile engine, the propellant adopted by most of the missile engines at home and abroad at present is a butyl hydroxyl propellant, the technology developed for decades is mature, but the foreign experiments show that: the low-temperature performance, particularly the low-temperature ignition performance, of the butylated hydroxytoluene propellant is poor, the propellant is easy to explode under impact when ignited at a lower temperature (particularly minus 55 ℃), and many low-temperature trial run explosion accidents of the butylated hydroxytoluene propellant occur abroad, mainly because the butylated hydroxytoluene propellant adopts hydroxyl-terminated polybutadiene adhesive, more olefin bonds exist in molecular chain segments of the adhesive, the rigidity of molecular chains is strong, so that the butylated hydroxytoluene propellant is easy to crack under the ignition impact when an engine is ignited at a lower temperature, and the combustion surface is out of control and explodes.
Compared with other propellants, the content of oxygen in the butyl hydroxyl propellant adhesive and the plasticizer is relatively low, the oxygen coefficient is relatively low under the condition that the content of aluminum powder in the propellant is high, the propellant aluminum powder in an engine is not favorably combusted fully, residues are high, and the engine energy cannot be effectively exerted. Meanwhile, the current carrier-borne and no-load missile weapon models also put forward higher requirements on the safety of the engine, and the propellant is required to meet the 1.3-level danger level and needs to be examined through a low vulnerability test, so that the research and development work of a novel propellant needs to be carried out aiming at the problems of the butylated hydroxytoluene propellant at present, and the requirement of the advanced tactical missile engine on a high-performance propellant is met.
Disclosure of Invention
In order to overcome the defects in the prior art, the inventor of the invention carries out intensive research and provides a hydroxyl-terminated polyethylene oxide and propylene oxide random copolyether type propellant and a preparation method thereof.
The technical scheme provided by the invention is as follows:
in a first aspect, a hydroxyl-terminated polyethylene oxide and propylene oxide random copolyether propellant comprises the following components in percentage by mass:
adhesive: 6 to 15 percent;
plasticizer: 5% -20%;
oxidizing agent: 30% -65%;
curing agent: 0.3% -1.5%;
fuel: 5% -22%;
other functional auxiliary agents: and (4) the balance.
In a second aspect, a process for preparing a hydroxyl terminated polyethylene oxide propylene oxide random copolyether propellant comprises the steps of:
step 1, premixing an adhesive and a plasticizer before use according to a designed plasticizing ratio to obtain a uniform glue solution;
step 2, weighing the functional additives into the glue solution in sequence, and placing the glue solution in a mixing pot for premixing for 5-10 min; adding fuel for premixing for 5-10 min; then sequentially adding the weighed oxidant, secondary oxidant and curing agent, mixing for 60-80 min at 45-55 ℃, and vacuumizing during mixing to obtain propellant slurry finally;
step 3, pouring the propellant slurry in the step 2 into a mold or an engine shell through a vacuum pouring system;
and 4, step 4: curing the mold or engine with the slurry at 50-60 deg.c for 3-7 days.
According to the hydroxyl-terminated polyethylene oxide and propylene oxide random co-polyether type propellant and the preparation method thereof provided by the invention, the following beneficial effects are achieved:
(1) the hydroxyl-terminated polyethylene oxide and propylene oxide random copolyether is used as an adhesive, the molecular weight of the adhesive is 1000-10000, the adhesive is liquid at normal temperature, the glass transition temperature is about-70-85 ℃, the adhesive has good compatibility with a polar energetic plasticizer, more ether bonds are contained in the adhesive, more flexible chain segments are contained, and a propellant can absorb partial mechanical energy when being subjected to ignition impact of an engine and external mechanical stimulation, so that the engine can pass low-temperature test run examination and low-vulnerability test; the melting temperature of the cured hydroxyl-terminated polyethylene oxide and propylene oxide random copolyether adhesive is relatively low, and the cured hydroxyl-terminated polyethylene oxide and propylene oxide random copolyether adhesive is easy to become viscous-state liquid when being heated slowly, so that the combustion surface of the propellant is not greatly increased under the heating condition, the propellant is easy to extinguish, and severe slow-speed roasting response generated by the propellant is avoided; meanwhile, because a large number of ether bonds exist in the adhesive, the oxygen content of the adhesive is higher than that of the existing HTPB and HTPE type adhesives (hydroxyl-terminated polyethylene oxide tetrahydrofuran copolymer), so that a higher oxygen atmosphere can be provided for the combustion of aluminum powder in the propellant, the combustion residues of the propellant aluminum powder can be effectively reduced, and the engine energy can be favorably exerted;
(2) the propellant adopts the insensitive energetic plasticizer, such as BunNA, TEGDN, BTTN, TMETN and the like, the energy of the propellant can be distributed between solid and liquid components by adding the insensitive energetic plasticizer, the liquid component in the propellant is decomposed before the solid component in the propellant, and all energy in the propellant is not concentrated and rapidly released, so that the slow burning response degree of the propellant is reduced; the propellant meets the requirement of 1.3-grade hazard level, and can pass all six low-vulnerability tests of slow burning, fast burning, bullet impact, sympathetic explosion test, energy-gathered jet impact and fragment impact;
(3) ammonium Perchlorate (AP) is used as a main oxidant, Ammonium Nitrate (AN), phase-stable ammonium nitrate (PSAN) and the like are used as secondary oxidants, and the addition of a small amount of insensitive ammonium nitrate can obviously improve the safety performance of the propellant, reduce the dangerous level of the propellant and reduce the response probability of the propellant to dangerous stimulation; the addition of ammonium nitrate is also beneficial to reducing the slow-speed roasting response degree of the propellant, the main reason is that the decomposition temperature of the ammonium nitrate is lower, so that the propellant can be subjected to decomposition reaction at a lower temperature, the energy of the propellant is released gradually, and meanwhile, the oxygen content of the ammonium nitrate is higher, so that the energy of the propellant can be exerted to a certain extent;
(4) the propellant adopts a passive energetic plasticizer and a polyethylene oxide and propylene oxide random copolyether type adhesive, the plasticizing ratio of the propellant is 0.3-1.5, the propellant can be suitable for different processes by adjusting the plasticizing ratio, and can be correspondingly applied to various advanced tactical missile weapons such as carrier-borne, airborne, air-ground and ground.
Detailed Description
The features and advantages of the present invention will become more apparent and appreciated from the following detailed description of the invention.
According to the first aspect of the invention, the hydroxyl-terminated polyethylene oxide and propylene oxide random copolyether propellant comprises the following components in percentage by mass:
adhesive: 6 to 15 percent;
plasticizer: 5% -20%;
oxidizing agent: 30% -65%;
secondary oxidant: 0% -20%;
curing agent: 0.3% -1.5%;
fuel: 5% -22%;
other functional auxiliary agents: the balance is preferably 0.3 to 6%.
In the invention, the adhesive adopts hydroxyl-terminated polyethylene oxide and propylene oxide random copolyether, the number average molecular weight is 1000-10000, and the glass transition temperature is-70 to-85 ℃.
The hydroxyl-terminated polyethylene oxide and propylene oxide random copolyether is used as an adhesive, the molecular weight of the adhesive is 1000-10000, the adhesive is liquid at normal temperature, the glass transition temperature is about-70-85 ℃, the adhesive has good compatibility with a polar energetic plasticizer, more ether bonds are contained in the adhesive, more flexible chain segments are contained, and a propellant can absorb partial mechanical energy when being subjected to ignition impact of an engine and external mechanical stimulation, so that the engine can pass low-temperature test run examination and low-vulnerability test; the melting temperature of the cured hydroxyl-terminated polyethylene oxide and propylene oxide random copolyether adhesive is relatively low, and the cured hydroxyl-terminated polyethylene oxide and propylene oxide random copolyether adhesive is easy to become viscous-state liquid when being heated slowly, so that the combustion surface of the propellant is not greatly increased under the heating condition, the propellant is easy to extinguish, and severe slow-speed roasting response generated by the propellant is avoided; meanwhile, because a large number of ether bonds exist in the adhesive, the oxygen content of the adhesive is higher than that of the existing HTPB and HTPE type adhesives (hydroxyl-terminated polyethylene oxide tetrahydrofuran copolymer), so that a higher oxygen atmosphere can be provided for the combustion of aluminum powder in the propellant, the combustion residues of the propellant aluminum powder can be effectively reduced, and the engine energy can be favorably exerted.
In the present invention, the plasticizer is selected from one of triethylene glycol dinitrate (TEGDN), 1,2, 4-butanetriol trinitrate (BTTN), bis (2, 22-dinitropropyl) formal (BDPF), bis (2, 2-dinitropropyl) acetal (BDPA), buntanoethyl nitrate (BuNENA), trimethylolethane trinitrate (TMETN), or a combination thereof.
Preferably, the mass ratio (plasticizing ratio) of the plasticizer to the adhesive in the propellant is 0.3-1.5.
The propellant adopts the insensitive energetic plasticizer, such as BunNA, TEGDN, BTTN, TMETN and the like, compared with the non-insensitive energetic plasticizer which has higher energy but poorer safety than nitroglycerin, the insensitive energetic plasticizer has higher safety and is insensitive to mechanical stimulation, the energy of the propellant can be distributed between solid and liquid components due to the addition of the insensitive energetic plasticizer, the liquid component in the propellant is decomposed before the solid component in the propellant, and all the energy in the propellant is not intensively and quickly released, so that the slow burning response degree of the propellant is reduced; the propellant meets the requirement of 1.3-grade hazard level, and can pass all six low-vulnerability tests of slow burning, fast burning, bullet impact, sympathetic explosion test, energy-gathered jet impact and fragment impact.
In the invention, the oxidant is Ammonium Perchlorate (AP), and the granularity is 3-360 μm.
In the invention, the secondary oxidant is selected from one or a combination of Ammonium Nitrate (AN) or phase-stabilized ammonium nitrate (PSAN).
Ammonium Perchlorate (AP) is used as a main oxidant, Ammonium Nitrate (AN), phase-stable ammonium nitrate (PSAN) and the like are used as secondary oxidants, and the addition of a small amount of insensitive ammonium nitrate can obviously improve the safety performance of the propellant, reduce the dangerous level of the propellant and reduce the response probability of the propellant to dangerous stimulation; the addition of ammonium nitrate is also beneficial to reducing the slow-speed roasting response degree of the propellant, the main reason is that the decomposition temperature of the ammonium nitrate is low, so that the propellant can be subjected to decomposition reaction at a low temperature, the energy of the propellant is released gradually, and meanwhile, the oxygen content of the ammonium nitrate is high, so that the energy of the propellant can be exerted to a certain extent.
In the invention, the curing agent is an isocyanate compound, and is selected from one or a combination of Toluene Diisocyanate (TDI), isophorone diisocyanate (IPDI), 4' -dicyclohexyl methane diisocyanate (HMDI) or polyfunctional isocyanate (N-100).
In the present invention, the fuel is aluminum powder (Al), preferably having a particle size of 1 μm to 100 μm.
In the invention, the other functional auxiliary agents comprise a curing catalyst, a stabilizer and a bonding agent, and can also comprise an optional burning rate catalyst; wherein the curing catalyst is one or the combination of triphenyl bismuth (TPB) or dibutyltin dilaurate (DBTDL); the stabilizer is selected from one or the combination of N-methyl-p-nitroaniline (MNA) or 2-dinitrodiphenylamine (2-NDPA); the bonding agent is selected from alcamines, enamines and other bonding agents; the burning rate catalyst is selected from metal oxides such as aluminum, lead, bismuth and the like.
According to a second aspect of the present invention, there is provided a process for preparing a hydroxyl-terminated polyethylene oxide propylene oxide random copolyether type propellant, for preparing the hydroxyl-terminated polyethylene oxide propylene oxide random copolyether type propellant of the first aspect, comprising the steps of:
step 1, premixing an adhesive and a plasticizer before use according to a designed plasticizing ratio to obtain a uniform glue solution;
step 2, weighing the functional additives into the glue solution in sequence, and placing the glue solution in a mixing pot for premixing for 5-10 min; adding fuel for premixing for 5-10 min; then sequentially adding the weighed oxidant, secondary oxidant and curing agent, mixing for 60-80 min at 45-55 ℃, and vacuumizing during mixing to obtain propellant slurry finally;
step 3, pouring the propellant slurry obtained in the step 2 into a mold or an engine shell through a vacuum pouring system;
and 4, step 4: curing the mold or engine with the slurry at 50-60 deg.c for 3-7 days.
Examples
Example 1
(1) The composition of the propellant;
(2) preparation of propellant:
step 1, premixing an adhesive and a plasticizer before use according to a designed plasticizing ratio to obtain a uniform glue solution;
step 2, weighing the functional additives into the glue solution in sequence, and placing the glue solution in a mixing pot for premixing for 5-10 min; adding fuel for premixing for 5-10 min; then sequentially adding the weighed oxidant, secondary oxidant and curing agent, mixing for 60-80 min at 45-55 ℃, and vacuumizing during mixing to obtain propellant slurry finally;
step 3, pouring the propellant slurry in the step 2 into a mold or an engine shell through a vacuum pouring system;
and 4, step 4: curing the mold or engine with the slurry at 50-60 deg.c for 3-7 days.
(3) Performance of the propellant:
propellant theoretical specific impulse: 264.0s (6.86MPa,25 ℃); density of propellant: 1.763g/cm3；
Propellant normal temperature strength: 0.78 MPa; normal temperature elongation: 80 percent; low-temperature elongation: 70 percent;
oxygen coefficient of propellant: 1.456; six low vulnerability tests: passing;
-55 ℃ low temperature test run: and (4) passing.
Example 2
(1) Composition of the propellant:
(2) preparation of propellant: the same as in example 1.
(3) Performance of the propellant:
propellant theoretical specific impulse: 263.4s (6.86MPa,25 ℃); density of propellant: 1.821g/cm3；
Propellant normal temperature strength: 0.82 MPa; normal temperature elongation: 82%; low-temperature elongation: 73 percent;
oxygen coefficient of propellant: 1.401, respectively; six low vulnerability tests: passing;
-55 ℃ low temperature test run: and (4) passing.
Example 3
(1) Composition of the propellant:
| formulation composition | Content (mass%) of |
| Hydroxy terminated polyethylene oxide propylene oxide random copolyethers | 8.0 |
| Enamine bonding agent | 0.15 |
| TEGDN | 10.7 |
| TDI | 0.5 |
| Al | 18 |
| AP | 62.0 |
| TPB | 0.05 |
| MNA | 0.5 |
| 2-NDPA | 0.1 |
(2) Preparation of propellant: the same as in example 1.
(3) Performance of the propellant:
propellant theoretical specific impulse: 262.7s (6.86MPa,25 ℃); density of propellant: 1.813g/cm3；
Propellant normal temperature strength: 0.8 MPa; normal temperature elongation: 75 percent; low-temperature elongation: 72 percent;
oxygen coefficient of propellant: 1.537; six low vulnerability tests: passing;
-55 ℃ low temperature test run: and (4) passing.
Example 4
(1) Composition of the propellant:
| formulation composition | Content (mass%) of |
| Hydroxy terminated polyethylene oxide propylene oxide random copolyethers | 8.0 |
| Enamine bonding agent | 0.15 |
| BuNENA | 7.6 |
| TEGDN | 3 |
| TDI | 0.5 |
| Al | 18 |
| AP | 62 |
| TPB | 0.05 |
| MNA | 0.6 |
| 2-NDPA | 0.1 |
(2) Preparation of propellant: the same as in example 1.
(3) Performance of the propellant:
propellant theoretical specific impulse: 263.3s (6.86MPa,25 ℃); density of propellant: 1.804g/cm3；
Propellant normal temperature strength: 0.9 MPa; normal temperature elongation: 68 percent; low-temperature elongation: 60 percent;
oxygen coefficient of propellant: 1.502; six low vulnerability tests: passing;
-55 ℃ low temperature test run: and (4) passing.
Example 5
(1) Composition of the propellant:
(2) preparation of propellant: the same as in example 1.
(3) Performance of the propellant:
propellant theoretical specific impulse: 262.7s (6.86MPa,25 ℃); density of propellant:1.789g/cm3；
propellant normal temperature strength: 0.77 MPa; normal temperature elongation: 75 percent; low-temperature elongation: 65 percent;
oxygen coefficient of propellant: 1.551, respectively; six low vulnerability tests: passing;
-55 ℃ low temperature test run: and (4) passing.
Example 6
(1) Composition of the propellant:
| formulation composition | Content (mass%) of |
| Hydroxy terminated polyethylene oxide propylene oxide random copolyethers | 10.0 |
| Enamine bonding agent | 0.15 |
| TMETN | 8.6 |
| TDI | 0.5 |
| Al | 18 |
| AP | 61 |
| TPB | 0.05 |
| MNA | 0.7 |
| Alumina oxide | 1.0 |
(2) Preparation of propellant: the same as in example 1.
(3) Performance of the propellant:
propellant theoretical specific impulse: 260.8s (6.86MPa,25 ℃); density of propellant: 1.808g/cm3(25℃)；
Propellant normal temperature strength: 0.83 MPa; normal temperature elongation: 80 percent; low-temperature elongation: 74 percent;
oxygen coefficient of propellant: 1.448; six low vulnerability tests: passing;
-55 ℃ low temperature test run: and (4) passing.
Example 7
(1) Composition of the propellant:
| formulation composition | Content (mass%) of |
| Hydroxy terminated polyethylene oxide propylene oxide random copolyethers | 7.0 |
| Enamine bonding agent | 0.15 |
| TEGDN | 10.6 |
| TDI | 0.6 |
| Al | 5 |
| AP | 66 |
| PSAN | 10 |
| TPB | 0.05 |
| MNA | 0.6 |
(2) Preparation of propellant: the same as in example 1.
(3) Performance of the propellant:
propellant theoretical specific impulse: 255.1s (6.86MPa,25 ℃); density of propellant: 1.746g/cm3；
Propellant normal temperature strength: 0.79 Mpa; normal temperature elongation: 73 percent; low-temperature elongation: 67%;
oxygen coefficient of propellant: 3.276; six low vulnerability tests: passing;
-55 ℃ low temperature test run: and (4) passing.
Example 8
(1) Composition of the propellant:
(2) preparation of propellant: the same as in example 1.
(3) Performance of the propellant:
propellant theoretical specific impulse: 263.1s (6.86MPa,25 ℃); density of propellant: 1.810g/cm3；
Propellant normal temperature strength: 0.86 MPa; normal temperature elongation: 73 percent; low-temperature elongation: 68 percent;
oxygen coefficient of propellant: 1.408, respectively; six low vulnerability tests: passing;
-55 ℃ low temperature test run: and (4) passing.
Example 9
(1) Composition of the propellant:
(2) preparation of propellant: the same as in example 1.
(3) Performance of the propellant:
propellant theoretical specific impulse: 263.2s (6.86MPa,25 ℃); density of propellant: 1.771g/cm3(25℃)；
Propellant normal temperature strength: 0.86 MPa; normal temperature elongation: 70 percent; low-temperature elongation: 63%;
oxygen coefficient of propellant: 1.299; six low vulnerability tests: passing;
-55 ℃ low temperature test run: and (4) passing.
The invention has been described in detail with reference to specific embodiments and illustrative examples, but the description is not intended to be construed in a limiting sense. Those skilled in the art will appreciate that various equivalent substitutions, modifications or improvements may be made to the technical solution of the present invention and its embodiments without departing from the spirit and scope of the present invention, which fall within the scope of the present invention. The scope of the invention is defined by the appended claims.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
Claims (10)
1. A hydroxyl-terminated polyethylene oxide and propylene oxide random copolyether propellant is characterized by comprising the following components in percentage by mass:
adhesive: 6 to 15 percent;
plasticizer: 5% -20%;
oxidizing agent: 30% -65%;
curing agent: 0.3% -1.5%;
fuel: 5% -22%;
other functional auxiliary agents: and (4) the balance.
2. The propellant according to claim 1, wherein the adhesive is hydroxyl-terminated polyethylene oxide propylene oxide random copolyether, the number average molecular weight is 1000-10000, and the glass transition temperature is-70 ℃ to-85 ℃.
3. The propellant of claim 1, wherein the plasticizer is selected from one of triethylene glycol dinitrate (TEGDN), 1,2, 4-butanetriol trinitrate (BTTN), bis (2, 22-dinitropropyl) formal (BDPF), bis (2, 2-dinitropropyl) acetal (BDPA), bunitroammoniumethyl ethyl nitrate (BuNENA), trimethylolethane trinitrate (TMETN), or combinations thereof.
4. The propellant according to claim 1, wherein the mass ratio of the plasticizer to the binder in the propellant is 0.3 to 1.5.
5. The propellant according to claim 1, wherein the oxidizer is ammonium perchlorate, preferably with a particle size of 3 to 360 μm.
6. The propellant of claim 1, wherein the curing agent is an isocyanate compound selected from one or a combination of Toluene Diisocyanate (TDI), isophorone diisocyanate (IPDI), 4' -dicyclohexylmethane diisocyanate (HMDI), or multifunctional isocyanates (N-100).
7. The propellant according to claim 1, wherein the fuel is aluminum powder, preferably with a particle size of 1 to 100 μm.
8. The propellant of claim 1 wherein the other functional adjuvants comprise a cure catalyst, a stabilizer, a bonding agent, and optionally a burn rate catalyst; wherein the curing catalyst is one or the combination of triphenyl bismuth (TPB) or dibutyltin dilaurate (DBTDL); the stabilizer is selected from one or the combination of N-methyl-p-nitroaniline (MNA) or 2-dinitrodiphenylamine (2-NDPA); the bonding agent is selected from alcamines or enamine bonding agents; the burning rate catalyst is selected from metal oxides.
9. The propellant according to claim 1, further comprising a secondary oxidant, wherein the content of the secondary oxidant is 0-20% by mass, and the secondary oxidant is selected from one or a combination of ammonium nitrate or phase-stabilized ammonium nitrate.
10. A process for the preparation of a hydroxyl terminated polyethylene oxide propylene oxide random copolyether propellant as claimed in any one of claims 1 to 9, comprising the steps of:
step 1, premixing an adhesive and a plasticizer before use according to a designed plasticizing ratio to obtain a uniform glue solution;
step 2, weighing the functional additives into the glue solution in sequence, and placing the glue solution in a mixing pot for premixing for 5-10 min; adding fuel for premixing for 5-10 min; then sequentially adding the weighed oxidant, secondary oxidant and curing agent, mixing for 60-80 min at 45-55 ℃, and vacuumizing during mixing to obtain propellant slurry finally;
step 3, pouring the propellant slurry obtained in the step 2 into a mold or an engine shell through a vacuum pouring system;
and 4, step 4: curing the mold or engine with the slurry at 50-60 deg.c for 3-7 days.
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| CN114394879A (en) * | 2021-12-20 | 2022-04-26 | 湖北航天化学技术研究所 | Low-vulnerability propellant with low-temperature adaptability |
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