CN109305868B - High-energy solid propellant - Google Patents
High-energy solid propellant Download PDFInfo
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- CN109305868B CN109305868B CN201811123268.9A CN201811123268A CN109305868B CN 109305868 B CN109305868 B CN 109305868B CN 201811123268 A CN201811123268 A CN 201811123268A CN 109305868 B CN109305868 B CN 109305868B
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- propellant
- solid propellant
- tetrahydrofuran copolyether
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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
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- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B23/00—Compositions characterised by non-explosive or non-thermic constituents
- C06B23/001—Fillers, gelling and thickening agents (e.g. fibres), absorbents for nitroglycerine
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- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B23/00—Compositions characterised by non-explosive or non-thermic constituents
- C06B23/009—Wetting agents, hydrophobing agents, dehydrating agents, antistatic additives, viscosity improvers, antiagglomerating agents, grinding agents and other additives for working up
-
- 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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- Chemical & Material Sciences (AREA)
- Organic Chemistry (AREA)
- Engineering & Computer Science (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Combustion & Propulsion (AREA)
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Abstract
The invention provides a high-energy solid propellant, and belongs to the technical field of propellants. The propellant raw material comprises the following components in percentage by mass: 45-59% of ammonium perchlorate, 0-5% of aluminum powder, 18-35% of explosive, 1.29-1.64% of curing agent, 0.91-1.91% of functional assistant, 11.07-12.60% of energetic plasticizer and 4.11-5.93% of adhesive, wherein the adhesive is azoglycidyl ether and tetrahydrofuran copolyether or 3, 3-bis (azomethine) butylene oxide and tetrahydrofuran copolyether, and the energetic plasticizer is a mixture of N-butyl-2-nitrooxyethyl ammonium nitrate and one of nitroglycerin, butanetriol trinitrate, trimethylolethane trinitrate and triethylene glycol dinitrate. The invention reduces the vitrification temperature of the propellant and improves the high-temperature and low-temperature mechanical properties of the propellant on the premise of keeping the high specific impulse and low characteristic signal performance of the original propellant, thereby widening the use temperature range of the propellant and further improving the safety performance of the propellant.
Description
Technical Field
The invention relates to a high-energy solid propellant, and belongs to the technical field of solid propellants.
Background
The general missile and the multipurpose tactical missile are a kind of tactical weapons which are mainly developed in all countries in the world at present, the missile has the characteristics of high survival, strong penetration, remote accurate striking and wide-range working environment adaptation, so that the propellant serving as a missile power source meets high specific impulse and low characteristic signals, and simultaneously, the wide temperature application range and good safety performance need to be considered. Under the influence of high west and low east and large north-south region span in China, the missile engine is generally required to reliably work at the temperature of-60 ℃ to +70 ℃, so that the propellant is required to have good tensile strength and elongation at corresponding temperature. Meanwhile, in order to meet the requirements of different missile combat carriers and combat environments on the safety performance of the propellant, most engines require that the propellant meets the 1.3-level insensitive characteristic.
The azide propellant is a key research object of high specific impulse and low characteristic signal propellants in countries in the world at present. In azide polyether (GAP (poly glycidyl azide), BAMO (3, 3-bis (azidomethyl) butylene oxide copolyether), AMMO (3-methyl-3-azidomethyl butylene oxide copolyether) and the like) high-energy low-characteristic signal propellants, insensitive explosive FOX-7 is adopted to replace conventional explosives such as HMX or RDX and the like in a formula, and the propellants can meet the requirement of 1.3-level safety grade of the propellants, but azide adhesives such as GAP, BAMO, AMMO and the like have high glass transition temperature per se, are usually above-40 ℃, so that the propellants are basically brittle glass state below-50 ℃, have extremely low elongation, and limit the application of the propellants in wide-adaptability tactical missiles.
Disclosure of Invention
The invention aims to solve the problems in the prior art, and provides a high-energy solid propellant, which reduces the vitrification temperature of the propellant and improves the high-temperature and low-temperature mechanical properties of the propellant on the premise of keeping the high specific impulse and low characteristic signal properties of the original propellant, thereby widening the use temperature range of the propellant and further improving the safety performance of the propellant.
The above purpose of the invention is realized by the following technical scheme:
the high-energy solid propellant comprises the following raw materials in percentage by mass:
45-59% of ammonium perchlorate, 0-5% of aluminum powder, 18-35% of explosive, 1.29-1.64% of curing agent, 0.91-1.91% of functional assistant, 11.07-12.60% of energetic plasticizer and 4.11-5.93% of adhesive, wherein the adhesive is azoglycidyl ether and tetrahydrofuran copolyether or 3, 3-bis (azomethine) butylene oxide and tetrahydrofuran copolyether, and the energetic plasticizer is a mixture of N-butyl-2-nitrooxyethyl ammonium nitrate and one of nitroglycerin, butanetriol trinitrate, trimethylolethane trinitrate and triethylene glycol dinitrate.
In an alternative embodiment, the explosive is one or a combination of octogen or 1, 1-diamino-2, 2-dinitroethylene.
In an optional embodiment, the azido glycidyl ether and tetrahydrofuran copolyether are random copolymers, and the percentage of azido glycidyl ether units in the molecular chain to the total number of copolymerized units is 40-60%.
In an optional embodiment, the molecular weight of the azido glycidyl ether and tetrahydrofuran copolyether is 6000 to 12000, and the average number of hydroxyl groups in each molecular chain is more than or equal to 2.
In an alternative embodiment, the 3, 3-bis (azidomethyl) butylene oxide and tetrahydrofuran copolyether is a random copolymer, and the percentage of 3, 3-bis (azidomethyl) butylene oxide units in the molecular chain accounts for 40% -50% of the total number of copolymerized units.
In an optional embodiment, the molecular weight of the 3, 3-bis (azidomethyl) butylene oxide-tetrahydrofuran copolyether is 5000-10000, and the average molecular weight is more than or equal to 2 hydroxyl groups in each molecular chain.
In an optional embodiment, the mass percentage content of the N-butyl-2-nitrooxyethyl ammonium nitrate in the energetic plasticizer is 40-60%, and the plasticizing ratio ranges from 2.0 to 3.0.
In an alternative embodiment, the curing agent is one or a combination of hexamethylene diisocyanate or dimer fatty acid diisocyanate.
In an optional embodiment, the functional additives comprise a mechanical property additive, a stabilizer, a flame stabilizer and a curing catalyst.
In an optional embodiment, the mechanical property auxiliary agent is a neutral polymer bonding agent, the stabilizer is N, N-dimethylaniline, the flame stabilizer is titanium dioxide or zirconium carbide, and the curing catalyst is dicumyl peroxide.
Compared with the prior art, the invention has the advantages that:
compared with the existing GAP propellant with high energy and low characteristic signal, the propellant provided by the invention adopts azido glycidyl ether and tetrahydrofuran copolyether GAP-THF or 3, 3-bis (azidomethyl) butylene oxide and tetrahydrofuran copolyether BAMO-THF as the adhesive, introduces the mixed energetic plasticizer with good compatibility with the adhesive, and correspondingly adjusts the components of curing agent, curing catalyst, mechanical property auxiliary agent and the like to form a high-performance energetic adhesive system. When the adhesive system is applied to a high-energy low-characteristic signal formula, the vitrification temperature of the propellant is obviously reduced, the low-temperature mechanical property is greatly improved, and the propellant property meets the technical requirement of normal work of a solid rocket engine in the environment of-60 ℃ to +70 ℃. Meanwhile, the safety level of the propellant is 1.3, and the requirements of missile weapons such as ship-borne weapons, airborne weapons and vehicle-borne weapons on the safety performance of the propellant are met. Therefore, the propellant of the invention greatly widens the application range of azide high-energy low-characteristic signal propellants.
(1) In the propellant provided by the invention, GAP-THF and BAMO-THF are used as adhesives, HDI and/or DDI with good molecular chain flexibility are used as curing agents, and the glass transition temperature T of the propellantgLess than or equal to-65 ℃ (see example 1 to example 8);
(2) the propellant provided by the invention has the maximum tensile strength sigma at 60 ℃ below zeromNot less than 4.11MPa, maximum elongation epsilonmNot less than 48.1%, and maximum tensile strength sigma at +70 deg.CmNot less than 0.78MPa, maximum elongation epsilonmNot less than 45.7% (see examples 1-8), and the mechanical property of the propellant is characterized in that the maximum elongation is not changed much with the temperature within the range of-60 ℃ to +70 ℃;
(3) the plasticizer in the propellant provided by the invention adopts one of energetic plasticizers NG, BTTN, TEGDN and TMETN and a insensitive energetic plasticizer Bu-NENA to form a mixed nitrate system. The plasticizer system has good compatibility with BAMO-THF and GAP-THF, and good safety performance, and when the HMX content in the propellant is not more than 20% or FOX-7 is added to replace HMX, the safety level of the propellant reaches 1.3 level.
(4) The adhesive GAP-THF or BAMO-THF adopted by the propellant has stronger flexibility, wettability and plasticity, can be plasticized by adopting a large amount of mixed energetic plasticizer, the maximum plasticizing ratio can be improved to 3.0, the solid content can be improved to 80-82 percent on the premise of meeting the manufacturing process of the propellant, and the total content is improvedThe energy level of the propellant is improved, and the actual specific impulse I of a standard engine is measured under 6.86MPasp≥242s。
(5) The mixed nitrate plasticizing azido polyether and tetrahydrofuran copolymer adhesive (GAP-THF or BAMO-THF) system adopted in the propellant has good technical performance, is easy to operate, and has wide application prospect and strong practical value.
Detailed Description
The present invention is described in detail below with reference to the specific embodiments, but the scope of protection is not limited thereto, and the present invention shall include the entire contents of the claims, and those skilled in the art can fully implement the entire contents of the claims by the following embodiments.
The embodiment of the invention provides a high-energy solid propellant which comprises the following raw materials in percentage by mass:
the adhesive is composed of, by weight, 45-59% of ammonium perchlorate AP, 0-5% of aluminum powder Al, 18-35% of explosive, 1.29-1.64% of curing agent, 0.91-1.91% of functional assistant, 11.07-12.60% of plasticizer containing energy and 4.11-5.93% of adhesive, wherein the adhesive is azido glycidyl ether and tetrahydrofuran copolyether GAP-THF or 3, 3-bis (azidomethyl) butylene oxide and tetrahydrofuran copolyether BAMO-THF, and the plasticizer containing energy is a mixture of N-butyl-2-nitrooxyethyl ammonium nitrate Bu-NENA and one of nitroglycerin NG, butanetriol trinitrate BTTN, trimethylolethane trinitrate TMETN and triethylene glycol dinitrate TEGDN.
The explosive is preferably one or a combination of octogen HMX or 1, 1-diamino-2, 2-dinitroethylene FOX-7; the azido glycidyl ether and tetrahydrofuran copolyether GAP-THF is a random copolymer, the percentage content of azido glycidyl ether units GAP in molecular chains in the total number of copolymerization units is preferably 40-60%, the molecular weight of the azido glycidyl ether and tetrahydrofuran copolyether GAP-THF is preferably 6000-12000, and the average number of hydroxyl groups in each molecular chain is preferably more than or equal to 2; the 3, 3-bis (azidomethyl) butylene oxide and tetrahydrofuran copolyether BAMO-THF is a random copolymer, the percentage content of 3, 3-bis (azidomethyl) butylene oxide BAMO units in a molecular chain in the total number of copolymerization units is preferably 40-50%, the molecular weight of the 3, 3-bis (azidomethyl) butylene oxide and tetrahydrofuran copolyether BAMO-THF is 5000-10000, and the average molecular weight is more than or equal to 2; the curing agent is Hexamethylene Diisocyanate (HDI), dimer fatty acid diisocyanate (DDI) or a mixture of the HDI and the DDI; the functional auxiliary agent is preferably a combination of a mechanical property auxiliary agent, a stabilizer, a flame stabilizer and a curing catalyst; the mechanical property auxiliary agent is preferably a neutral polymer bonding agent NPBA, the stabilizer is preferably N, N-dimethylaniline NN, the flame retardant is preferably titanium dioxide or zirconium carbide, and the curing catalyst is preferably dicumyl peroxide DCP.
In an optional embodiment, the mass percentage content of the N-butyl-2-nitrooxyethyl ammonium nitrate in the energetic plasticizer is 40-60%, and the plasticizing ratio ranges from 2.0 to 3.0. The plasticizer system solves the problem of poor compatibility of common energetic plasticizers such as nitroglycerin, butanetriol trinitrate, trimethylolethane trinitrate, triethylene glycol dinitrate and 3, 3-bis (azidomethyl) butylene oxide and tetrahydrofuran copolyether BAMO-THF or azidoglycidyl ether and tetrahydrofuran copolyether GAP-THF, and the propellant has good drug properties. Within the plasticizing ratio range of 2.0-3.0, the solid content in the propellant can be increased to 82%, the specific impulse of the propellant is increased, and the mechanical property of the propellant meets the use requirement of a tactical missile engine in a wider temperature range. In addition, the introduction of N-butyl-2-nitrooxyethyl ammonium nitrate in the plasticizer is beneficial to improving the safety performance of the propellant, and when the HMX mass percentage of octogen in the formula is less than or equal to 20% or FOX-7 is added to replace HMX, the propellant meets the insensitive characteristic of level 1.3.
The propellant formulation provided by the embodiment of the invention can be prepared into a finished propellant product by a conventional propellant preparation method.
The following are several specific examples of the present invention, and the raw materials used in each example are all commercially available products, wherein the adhesive and the plasticizer are provided by the dawn chemical research and design institute;
example 1
(1) The propellant formula composition (mass percent) is shown in table 1-1:
TABLE 1-1 propellant formulations
The raw materials are weighed according to the formula and mixed by a vertical mixer. The mixture of binder and plasticizer is pre-mixed to form a homogeneous liquid, referred to as glue. Firstly adding a mixture of Al powder, a neutral polymer bonding agent, a stabilizer, a curing catalyst and 70% of glue into a mixer, mixing for 10min, then adding HMX or FOX-7, mixing for 15min, then adding AP, mixing for 30min, finally adding a mixture of a curing agent and 30% of glue, mixing for 20min, mixing at the temperature of 55 +/-2 ℃, discharging propellant slurry, pouring the propellant slurry into a mold through a vacuum pouring tank, and finally placing the mold into an oil bath oven at the temperature of 50 ℃ for curing for 7 days to obtain a propellant finished product, wherein the preparation method of each subsequent embodiment is the same as that of the embodiment.
(2) The overall performance of the propellant is shown in Table 2-1:
TABLE 2-1 propellant Performance parameters Table
Signal characteristics: the propellant plume visible light transmittance is 65.3%, the laser transmittance is 73.5%, the near infrared transmittance is 81.9%, the mid-infrared transmittance is 85.6%, the far infrared transmittance is 90.2%, the microwave attenuation is 0.34dB, and the mid-far infrared radiation intensity and the far infrared radiation intensity of the plume are reduced by 70% and 89% compared with 18.5% of Al hydroxyl propellant.
Example 2
(1) The propellant formula composition (mass percent) is shown in the following table 1-2:
TABLE 1-2 propellant formulations
(2) The overall performance of the propellant is shown in tables 2-2:
TABLE 2-2 propellant Performance parameters Table
Signal characteristics: the propellant plume visible light transmittance is 65.6%, the laser transmittance is 73.9%, the near infrared transmittance is 82.4%, the mid infrared transmittance is 84.9%, the far infrared transmittance is 90.4%, the microwave attenuation is 0.34dB, and the mid and far infrared radiation intensity of the plume is reduced by 70% and 90% compared with that of 18.5% Al hydroxyl propellant.
Example 3
(1) The propellant formula composition (mass percent) is shown in tables 1-3:
TABLE 1-3 propellant formulations
(2) The combustion properties of the propellants are shown in tables 2 to 3:
TABLE 2-3 propellant Performance parameters Table
Signal characteristics: the propellant plume visible light transmittance is 75.5%, the laser transmittance is 87.1%, the near infrared transmittance is 87.6%, the mid-infrared transmittance is 94.2%, the far infrared transmittance is 98.6%, the microwave attenuation is 0.27dB, and the mid-far infrared radiation intensity and the far infrared radiation intensity of the plume are reduced by 73% and 95% compared with 18.5% of Al hydroxyl propellant.
Example 4
(1) The propellant formula composition (mass percent) is shown in tables 1-4:
TABLE 1-4 propellant formulations
(2) The combustion properties of the propellants are shown in tables 2 to 4:
tables 2-4 propellant performance parameters table:
signal characteristics: the propellant plume visible light transmittance is 75.7%, the laser transmittance is 87.5%, the near infrared transmittance is 86.9%, the mid-infrared transmittance is 93.3%, the far infrared transmittance is 98.4%, the microwave attenuation is 0.27dB, and the mid-far infrared radiation intensity and the far infrared radiation intensity of the plume are reduced by 73% and 95% compared with 18.5% of Al hydroxyl propellant.
Example 5
(1) The propellant formula composition (mass percent) is shown in tables 1-5:
TABLE 1-5 propellant formulations
(2) The overall performance of the propellant is shown in tables 2-5:
TABLE 2-5 propellant Performance parameters Table
Signal characteristics: the propellant plume visible light transmittance is 65.9%, the laser transmittance is 73.1%, the near infrared transmittance is 82.3%, the mid infrared transmittance is 85%, the far infrared transmittance is 90.7%, the microwave attenuation is 0.34dB, and the mid and far infrared radiation intensity of the plume is reduced by 70% and 90% compared with that of 18.5% Al hydroxyl propellant.
Example 6
(1) The propellant formula composition (mass percent) is shown in tables 1-6:
TABLE 1-6 propellant formulations
(2) The overall performance of the propellant is shown in tables 2-6:
TABLE 2-6 propellant Performance parameters Table
Signal characteristics: the propellant plume visible light transmittance is 71.2%, the laser transmittance is 77.1%, the near infrared transmittance is 84.0%, the mid infrared transmittance is 86.2%, the far infrared transmittance is 92.3%, the microwave attenuation is 0.31dB, and the mid and far infrared radiation intensity of the plume is reduced by 72% and 92% compared with that of 18.5% Al hydroxyl propellant.
Example 7
(1) The propellant formula composition (mass percent) is shown in tables 1-7:
TABLE 1-7 propellant formulations
(2) The overall performance of the propellant is shown in tables 2-7:
tables 2-7 propellant performance parameters table:
signal characteristics: the propellant plume visible light transmittance is 65.4%, the laser transmittance is 73.3%, the near infrared transmittance is 81.6%, the mid infrared transmittance is 83.3%, the far infrared transmittance is 90.7%, the microwave attenuation is 0.33dB, and the mid and far infrared radiation intensity of the plume is reduced by 71% and 90% compared with that of 18.5% Al hydroxyl propellant.
Example 8
(1) The propellant formula composition (mass percent) is shown in tables 1-8:
TABLE 1-8 propellant formulations
(2) The overall performance of the propellant is shown in tables 2-8:
TABLE 2-8 propellant Performance parameters Table
Signal characteristics: the propellant plume visible light transmittance is 71.7%, the laser transmittance is 77.4%, the near infrared transmittance is 84.3%, the mid infrared transmittance is 86.5%, the far infrared transmittance is 92.4%, the microwave attenuation is 0.31dB, and the mid and far infrared radiation intensity of the plume is reduced by 72% and 91% compared with that of 18.5% Al hydroxyl propellant.
The above description is only for the best mode of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention. Those skilled in the art will appreciate that the invention may be practiced without these specific details.
Claims (6)
1. The high-energy solid propellant is characterized by comprising the following raw materials in percentage by mass: 45-59% of ammonium perchlorate, 0-5% of aluminum powder, 18-35% of explosive, 1.29-1.64% of curing agent, 0.91-1.91% of functional assistant, 11.07-12.60% of plasticizer containing energy and 4.11-5.93% of adhesive, wherein the adhesive is azide glycidyl ether and tetrahydrofuran copolyether or 3, 3-bis (azidomethyl) epoxybutane and tetrahydrofuran copolyether, the azide glycidyl ether and tetrahydrofuran copolyether are random copolymer, and the percentage content of azide glycidyl ether units in a molecular chain in the total number of copolymerization units is 40-60%; the 3, 3-bis (azidomethyl) butylene oxide and tetrahydrofuran copolyether is a random copolymer, and the percentage content of 3, 3-bis (azidomethyl) butylene oxide units in a molecular chain in the total number of copolymerization units is 40-50%; the curing agent is one or a combination of hexamethylene diisocyanate or dimer fatty acid diisocyanate; the energy-containing plasticizer is a mixture of N-butyl-2-nitrooxyethyl ammonium nitrate and one of nitroglycerin, butanetriol trinitrate, trimethylolethane trinitrate and triethylene glycol dinitrate, the mass percentage content of the N-butyl-2-nitrooxyethyl ammonium nitrate in the energy-containing plasticizer is 40% -60%, the plasticizing ratio range is 2.0-3.0, and the solid content in the propellant is 80% -82%.
2. The high energy solid propellant of claim 1, wherein: the explosive is one or a combination of octogen or 1, 1-diamino-2, 2-dinitroethylene.
3. The high energy solid propellant of claim 1, wherein: the molecular weight of the azido glycidyl ether and tetrahydrofuran copolyether is 6000-12000, and the average molecular weight is more than or equal to 2.
4. The high energy solid propellant of claim 1, wherein: the molecular weight of the 3, 3-bis (azidomethyl) butylene oxide-tetrahydrofuran copolyether is 5000-10000, and the average molecular weight is that the number of hydroxyl groups in each molecular chain is more than or equal to 2.
5. The high energy solid propellant of claim 1, wherein: the functional auxiliary agent comprises a mechanical property auxiliary agent, a stabilizer, a flame stabilizer and a curing catalyst.
6. The high energy solid propellant according to claim 5, wherein: the mechanical property auxiliary agent is a neutral polymer bonding agent, the stabilizing agent is N, N-dimethylaniline, the flame-retardant agent is titanium dioxide or zirconium carbide, and the curing catalyst is dicumyl peroxide.
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| CN112500253B (en) * | 2020-12-02 | 2022-04-12 | 湖北航天化学技术研究所 | Temperature-sensitive time-varying high-energy solid propellant |
| CN114349584B (en) * | 2022-01-27 | 2023-04-07 | 湖北航天化学技术研究所 | Propellant with low ablation property, high energy and low characteristic signal |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3666576A (en) * | 1970-04-30 | 1972-05-30 | Us Army | Explosive composition containing an energetic acrylate as binder |
| CN106316729A (en) * | 2016-08-24 | 2017-01-11 | 湖北航天化学技术研究所 | Wide adaptive azide polyether propellant |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3666576A (en) * | 1970-04-30 | 1972-05-30 | Us Army | Explosive composition containing an energetic acrylate as binder |
| CN106316729A (en) * | 2016-08-24 | 2017-01-11 | 湖北航天化学技术研究所 | Wide adaptive azide polyether propellant |
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