CN114394879A - Low-vulnerability propellant with low-temperature adaptability - Google Patents
Low-vulnerability propellant with low-temperature adaptability Download PDFInfo
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- 239000003380 propellant Substances 0.000 title claims abstract description 67
- 239000004014 plasticizer Substances 0.000 claims abstract description 18
- 239000000853 adhesive Substances 0.000 claims abstract description 15
- 230000001070 adhesive effect Effects 0.000 claims abstract description 15
- 239000002360 explosive Substances 0.000 claims abstract description 9
- POCJOGNVFHPZNS-ZJUUUORDSA-N (6S,7R)-2-azaspiro[5.5]undecan-7-ol Chemical compound O[C@@H]1CCCC[C@]11CNCCC1 POCJOGNVFHPZNS-ZJUUUORDSA-N 0.000 claims abstract description 7
- -1 3, 3-bis-azidomethylbutoxy-tetrahydrofuran Chemical group 0.000 claims abstract description 7
- BSPUVYFGURDFHE-UHFFFAOYSA-N Nitramine Natural products CC1C(O)CCC2CCCNC12 BSPUVYFGURDFHE-UHFFFAOYSA-N 0.000 claims abstract description 7
- POCJOGNVFHPZNS-UHFFFAOYSA-N isonitramine Natural products OC1CCCCC11CNCCC1 POCJOGNVFHPZNS-UHFFFAOYSA-N 0.000 claims abstract description 7
- 239000012752 auxiliary agent Substances 0.000 claims abstract description 6
- 239000003795 chemical substances by application Substances 0.000 claims abstract description 6
- 239000000446 fuel Substances 0.000 claims abstract description 6
- 229910052751 metal Inorganic materials 0.000 claims abstract description 6
- 239000002184 metal Substances 0.000 claims abstract description 6
- 239000007800 oxidant agent Substances 0.000 claims abstract description 6
- 230000001590 oxidative effect Effects 0.000 claims abstract description 6
- JLHVSPWCFKIFAI-UHFFFAOYSA-N [N-]=[N+]=NCC(COCCCOCC(CN=[N+]=[N-])N=[N+]=[N-])N=[N+]=[N-] Chemical compound [N-]=[N+]=NCC(COCCCOCC(CN=[N+]=[N-])N=[N+]=[N-])N=[N+]=[N-] JLHVSPWCFKIFAI-UHFFFAOYSA-N 0.000 claims abstract description 4
- 239000007767 bonding agent Substances 0.000 claims description 31
- 239000000203 mixture Substances 0.000 claims description 13
- 239000002262 Schiff base Substances 0.000 claims description 9
- 102100037152 BAG family molecular chaperone regulator 1 Human genes 0.000 claims description 8
- 101710089792 BAG family molecular chaperone regulator 1 Proteins 0.000 claims description 8
- 230000007935 neutral effect Effects 0.000 claims description 8
- NDYLCHGXSQOGMS-UHFFFAOYSA-N CL-20 Chemical compound [O-][N+](=O)N1C2N([N+]([O-])=O)C3N([N+](=O)[O-])C2N([N+]([O-])=O)C2N([N+]([O-])=O)C3N([N+]([O-])=O)C21 NDYLCHGXSQOGMS-UHFFFAOYSA-N 0.000 claims description 5
- 239000003054 catalyst Substances 0.000 claims description 4
- 229920000642 polymer Polymers 0.000 claims description 4
- 239000003381 stabilizer Substances 0.000 claims description 4
- 239000000126 substance Substances 0.000 claims description 4
- GDDNTTHUKVNJRA-UHFFFAOYSA-N 3-bromo-3,3-difluoroprop-1-ene Chemical group FC(F)(Br)C=C GDDNTTHUKVNJRA-UHFFFAOYSA-N 0.000 claims description 3
- 239000012948 isocyanate Substances 0.000 claims description 3
- 150000002513 isocyanates Chemical class 0.000 claims description 3
- XIFJZJPMHNUGRA-UHFFFAOYSA-N n-methyl-4-nitroaniline Chemical compound CNC1=CC=C([N+]([O-])=O)C=C1 XIFJZJPMHNUGRA-UHFFFAOYSA-N 0.000 claims description 3
- DVKJHBMWWAPEIU-UHFFFAOYSA-N toluene 2,4-diisocyanate Chemical compound CC1=CC=C(N=C=O)C=C1N=C=O DVKJHBMWWAPEIU-UHFFFAOYSA-N 0.000 claims description 3
- ZHXAZZQXWJJBHA-UHFFFAOYSA-N triphenylbismuthane Chemical group C1=CC=CC=C1[Bi](C=1C=CC=CC=1)C1=CC=CC=C1 ZHXAZZQXWJJBHA-UHFFFAOYSA-N 0.000 claims description 3
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 2
- 239000004449 solid propellant Substances 0.000 abstract description 15
- 230000009477 glass transition Effects 0.000 description 20
- 238000002156 mixing Methods 0.000 description 15
- 150000001540 azides Chemical class 0.000 description 7
- 238000012360 testing method Methods 0.000 description 6
- 238000000034 method Methods 0.000 description 5
- 238000002360 preparation method Methods 0.000 description 5
- 239000007787 solid Substances 0.000 description 5
- 238000010998 test method Methods 0.000 description 5
- 230000000052 comparative effect Effects 0.000 description 4
- 238000001514 detection method Methods 0.000 description 4
- XTFIVUDBNACUBN-UHFFFAOYSA-N 1,3,5-trinitro-1,3,5-triazinane Chemical compound [O-][N+](=O)N1CN([N+]([O-])=O)CN([N+]([O-])=O)C1 XTFIVUDBNACUBN-UHFFFAOYSA-N 0.000 description 3
- 230000003044 adaptive effect Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- ZQXWPHXDXHONFS-UHFFFAOYSA-N 1-(2,2-dinitropropoxymethoxy)-2,2-dinitropropane Chemical compound [O-][N+](=O)C([N+]([O-])=O)(C)COCOCC(C)([N+]([O-])=O)[N+]([O-])=O ZQXWPHXDXHONFS-UHFFFAOYSA-N 0.000 description 2
- 238000005266 casting Methods 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 239000012634 fragment Substances 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000002002 slurry Substances 0.000 description 2
- IPPYBNCEPZCLNI-UHFFFAOYSA-N trimethylolethane trinitrate Chemical compound [O-][N+](=O)OCC(C)(CO[N+]([O-])=O)CO[N+]([O-])=O IPPYBNCEPZCLNI-UHFFFAOYSA-N 0.000 description 2
- RDLIBIDNLZPAQD-UHFFFAOYSA-N 1,2,4-butanetriol trinitrate Chemical compound [O-][N+](=O)OCCC(O[N+]([O-])=O)CO[N+]([O-])=O RDLIBIDNLZPAQD-UHFFFAOYSA-N 0.000 description 1
- 239000004721 Polyphenylene oxide Substances 0.000 description 1
- 230000003321 amplification Effects 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000011230 binding agent Substances 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 238000013329 compounding Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 239000000945 filler Substances 0.000 description 1
- 238000009472 formulation Methods 0.000 description 1
- 239000003721 gunpowder Substances 0.000 description 1
- 238000009863 impact test Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 238000003199 nucleic acid amplification method Methods 0.000 description 1
- UZGLIIJVICEWHF-UHFFFAOYSA-N octogen Chemical compound [O-][N+](=O)N1CN([N+]([O-])=O)CN([N+]([O-])=O)CN([N+]([O-])=O)C1 UZGLIIJVICEWHF-UHFFFAOYSA-N 0.000 description 1
- 229920000570 polyether Polymers 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 230000002889 sympathetic effect Effects 0.000 description 1
- WYURNTSHIVDZCO-UHFFFAOYSA-N tetrahydrofuran Substances C1CCOC1 WYURNTSHIVDZCO-UHFFFAOYSA-N 0.000 description 1
- AGCQZYRSTIRJFM-UHFFFAOYSA-N triethylene glycol dinitrate Chemical compound [O-][N+](=O)OCCOCCOCCO[N+]([O-])=O AGCQZYRSTIRJFM-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- 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
-
- 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
-
- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B45/00—Compositions or products which are defined by structure or arrangement of component of product
- C06B45/04—Compositions or products which are defined by structure or arrangement of component of product comprising solid particles dispersed in solid solution or matrix not used for explosives where the matrix consists essentially of nitrated carbohydrates or a low molecular organic explosive
- C06B45/06—Compositions or products which are defined by structure or arrangement of component of product comprising solid particles dispersed in solid solution or matrix not used for explosives where the matrix consists essentially of nitrated carbohydrates or a low molecular organic explosive the solid solution or matrix containing an organic component
- C06B45/10—Compositions or products which are defined by structure or arrangement of component of product comprising solid particles dispersed in solid solution or matrix not used for explosives where the matrix consists essentially of nitrated carbohydrates or a low molecular organic explosive the solid solution or matrix containing an organic component the organic component containing a resin
-
- 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
Abstract
The application relates to the field of solid propellants, and particularly discloses a low-vulnerability propellant with low-temperature adaptability, which is calculated by taking the total mass of the propellant as 100%, and comprises the following components in percentage by mass: 10-12% of adhesive, 11-15% of plasticizer, 45-60% of oxidant, 5-12% of nitramine explosive, 5-19% of metal fuel, 0.6-0.8% of curing agent and 0.9-1.5% of auxiliary agent, wherein the adhesive is 3, 3-bis-azidomethylbutoxy-tetrahydrofuran copolyether; the plasticizer is any one or more of 1, 3-bis (2, 3-diazidopropoxy) propane and 2, 2-bis (azidomethyl) propane-1, 3-dibutyrate. The propellant has the characteristics of good low-temperature adaptability, safety and the like, and can be used as a power source of a high-performance tactical weapon system or an aerospace attitude and orbit control system with higher requirements on low temperature.
Description
Technical Field
The application belongs to the technical field of solid propellants and relates to a low-vulnerability propellant with low-temperature adaptability.
Background
With the continuous deepening of the development of various tactical missile weapon systems and the diversification of tasks, the risk of facing low-temperature extreme environments is increased day by day, the working temperature range of the solid rocket engine is wider and wider, and researchers pay more and more attention to the low-temperature performance of the solid propellant. The low-temperature service temperature of the propellant is reduced from the prior-40 ℃ to-55 ℃ and even-60 ℃. In the application process of the solid propellant in China in recent years, the problem that the low-temperature mechanical property is difficult to meet the use requirement is often encountered, and the low-temperature ignition test run fault of the engine occurs. Therefore, the development of a solid propellant with good low temperature adaptability is the key to maintaining the structural integrity of the grain of the solid rocket engine.
The low-temperature performance of the solid propellant is closely related to the types and the performances of the components. The adhesive types commonly used in the low-vulnerability propellant at present mainly comprise hydroxyl-terminated polyether adhesive HTPE, azide adhesive GAP and PBT, the plasticizer types mainly comprise insensitive energetic plasticizers such as BDNPF/A, Bu-NENA, TEGDN, BTTN and TMETN, and the glass transition temperature of the propellant is generally higher than-65 ℃. HTPE propellants plasticized by BDNPF/A have glass transition temperatures Tg of around-45 ℃ (Comfort T F. Process in HTPE propellants [ C ]// NDIA 39th Annual Gun amplification/microsiles socket Conference, 2004). The glass transition temperature Tg of the Bu-NENA plasticized PBT propellant is-65 ℃ (Wufang Bu-NENA/PBT propellant safety performance, solid rocket technology, 2019, 42 (4): 483-.
The research on improving the low-temperature adaptability of the solid propellant at home and abroad is mainly based on reducing the glass transition temperature of the propellant and improving the interface bonding property of the propellant matrix and the solid filler; however, the existing solid propellant is difficult to meet the comprehensive requirements of the advanced solid rocket engine in the aspects of glass transition temperature, low-temperature mechanical property, low vulnerability and the like.
Disclosure of Invention
In order to enable the propellant to have the characteristics of low glass transition temperature, excellent low-temperature mechanical property and good safety, the application discloses a low-vulnerability propellant with low-temperature adaptability. Insensitive azide energetic materials BDAP1 and ButBOMP with the glass transition temperature below-95 ℃ are adopted as plasticizers to reduce the glass transition temperature of the propellant, and the low-temperature mechanical property of the propellant is improved through the mixture of a neutral polymer bonding agent NPBA and a Schiff base bonding agent BAG-1.
The technical scheme is as follows:
the low-temperature adaptive low-vulnerability propellant comprises the following components in percentage by mass, calculated by taking the total mass of the propellant as 100 percent:
10 to 12 percent of adhesive
11 to 15 percent of plasticizer
45 to 60 percent of oxidant
5 to 12 percent of nitramine explosive
5 to 19 percent of metal fuel
0.6 to 0.8 percent of curing agent
0.9 to 1.5 percent of auxiliary agent,
wherein the adhesive is 3, 3-bis-azidomethylbutoxy-tetrahydrofuran copolyether;
the plasticizer is any one or more of 1, 3-bis (2, 3-diazidopropoxy) propane and 2, 2-bis (azidomethyl) propane-1, 3-dibutyrate.
By adopting the technical scheme, the glass transition temperature of the propellant is effectively reduced by taking PBT as an adhesive and introducing the insensitive energy-containing azide plasticizer BDAP1 and/or ButBOMP which have better compatibility and low-temperature performance with the PBT.
Preferably, the auxiliary agent is a mixture of a bonding agent, a chemical stabilizer and a curing catalyst, and the content of the bonding agent is 0.3-0.6% of the total mass of the propellant.
Preferably, the bonding agent is a mixture of a neutral polymer bonding agent NPBA and a Schiff base bonding agent BAG-1.
Preferably, the BAG-1 molecular structural formula is as follows:
(x+y+z＝5.3)。
through the technical scheme, through experiments, the inventor finds that when x + y + z is less than 5.3, the bonding agent is easily dissolved in the plasticizer and cannot play a bonding role; when x + y + z is more than 5.3, the bonding agent lacks activity and the bonding effect is poor.
Preferably, the bonding agent comprises, by mass, 20% to 80% of NPBA and 20% to 80% of BAG-1, wherein the NPBA accounts for 100% of the total mass of the bonding agent.
Under the condition of the proportion of the neutral bonding agent and the Schiff base bonding agent, the propellant has good low-temperature mechanical property and lower glass transition temperature.
Preferably, the oxidant is ammonium perchlorate.
Preferably, the nitramine explosive is any one or more of hexanitrohexaazaisopentane CL-20, HMX and RDX.
Preferably, the metal fuel is aluminum powder.
Preferably, the curing agent is any one or more of toluene diisocyanate TDI and polyfunctional isocyanate N-100.
Preferably, the chemical stabilizer is at least one of N-methyl-p-nitroaniline MNA and 2-dinitrodiphenylamine 2-NDPA.
The curing catalyst is triphenyl bismuth TPB.
The preparation method of the propellant comprises the following steps:
a preparation method of low-temperature adaptive low-vulnerability propellant comprises the following steps of mixing by using a vertical mixer, and realizing production of engine explosive columns by using a vacuum casting system:
(1) mixing the adhesive and the plasticizer to form uniform liquid, wherein the mixing temperature is 40-50 ℃, and the mixing time is 20-50 min;
(2) adding an oxidant, nitramine explosive and metal fuel into the mixture of the adhesive and the plasticizer, and mixing at the temperature of 40-60 ℃ for 50-100 min;
(3) adding a curing agent and an auxiliary agent into the mixture obtained in the step (2) for mixing, wherein the mixing temperature is 40-50 ℃, and the mixing time is 20-40 min;
(4) and (4) filling the propellant slurry obtained in the step (3) into a mould, and curing for 120-168 h at the temperature of 50-60 ℃ to obtain the propellant grain.
In summary, the present application at least includes the following beneficial technical effects:
(1) the glass transition temperature of the propellant is low: by using PBT as an adhesive and introducing the insensitive energy-containing azide plasticizers BDAP1 and ButBOMP which have better compatibility and low-temperature performance with the PBT, the Tg of the propellant is effectively reduced, and the glass transition temperature of the propellant is reduced to be lower than-70 ℃;
(2) the propellant has excellent low-temperature mechanical properties: by adopting a neutral bonding agent NPBA suitable for nitramine explosives and a Schiff base bonding agent suitable for AP of an azide energetic propellant formula system, the low-temperature mechanical property of the propellant is effectively improved, and the maximum elongation of the propellant at-60 ℃ is more than 35%;
(3) the low-temperature mechanical property of the low-vulnerability propellant is effectively improved by adopting the approaches of compounding the plasticizer with the glass transition temperature of below 95 ℃ below zero, the neutral bonding agent and the Schiff base bonding agent and the like, and the low-vulnerability propellant formula with good low-temperature adaptability is obtained.
Detailed Description
The present application is described in further detail in conjunction with the following. The scope of protection is not limited thereto but includes the full contents of the claims set forth below, and those skilled in the art can fully implement the claims of the present invention by the following several examples.
3, 3-bis-azidomethyloxybutylene-tetrahydrofuran copolyether, PBT, is commercially available;
ammonium perchlorate, i.e., AP, commercially available;
hexanitrohexaazaisowurtzitane, CL-20, commercially available;
HMX, commercially available;
hexogen, RDX, commercially available;
1, 3-bis (2, 3-diazidopropoxy) propane, BDAP1, commercially available;
2, 2-bis (azidomethyl) propane-1, 3-dibutyrate, ButBAMP, commercially available;
n-methyl-p-nitroaniline, MNA, commercially available;
2-dinitrodiphenylamine, 2-NDPA, commercially available;
toluene diisocyanate, TDI, commercially available;
polyfunctional isocyanates, N-100, commercially available;
neutral polymer bonding agent, NPBA, commercially available;
a Schiff base bonding agent, BAG-1, self-made, prepared according to the method of the embodiment 2 in a novel Schiff base bonding agent with the application number of 202110484629.8, a preparation method and a solid propellant;
triphenylbismuth, TPB, commercially available.
The preparation method of the propellant comprises the following steps:
a preparation method of low-temperature adaptive low-vulnerability propellant comprises the following steps of mixing by using a vertical mixer, and realizing production of engine explosive columns by using a vacuum casting system:
(1) mixing the adhesive and the plasticizer to form uniform liquid, wherein the mixing temperature is 50 ℃, and mixing is carried out for 30 min;
(2) adding an oxidant, a nitramine explosive and a metal fuel into the mixture of the adhesive and the plasticizer, mixing at 53 ℃ for 85 min;
(3) adding a curing agent and an auxiliary agent into the mixture obtained in the step 2, mixing at the mixing temperature of 50 ℃ for 30 min;
(4) and (4) filling the propellant slurry obtained in the step (3) into a mould, and curing for 168 hours at 50 ℃ to obtain the propellant grain.
The following examples and comparative examples were prepared according to this method, and the contents of the components were different.
Examples 1 to 5
(1) Propellant composition (mass percent) see table 1:
TABLE 1 propellant compositions of examples 1-5
(2) Performance of propellant
The detection method comprises the following steps:
glass transition temperature (Tg): a method for measuring the glass transition temperature of the Q/G325-2016 composite solid propellant;
low temperature mechanical properties at-60 ℃ (100 mm/min): GJB770B-2005 gunpowder test method;
six low vulnerability tests:
QJ20152-2012 solid propellant slow-speed roasting combustion test method
QJ20153-2012 solid propellant fast burning test method
Sympathetic explosion test method for QJ20447-2016 solid propellant
QJ20448-2016 solid propellant fragment, jet flow and thermal fragment test method
QJ20450-2016 solid propellant bullet impact test method.
The test data for examples 1-5 are shown in Table 2:
TABLE 2 examination data for examples 1 to 5
Examples 6 to 11, the differences in the partial component contents from example 1 are shown in Table 3;
TABLE 3 propellant compositions of examples 6-11
(2) Performance of propellant
The detection methods of the six low-vulnerability tests are the same as the detection methods of the glass transition temperature (Tg) and the low-temperature mechanical property (100mm/min) at-60 ℃.
The data for the tests of examples 6-13 are shown in Table 4:
TABLE 4 examination data for examples 6 to 11
Comparative example 1
The difference from example 1 is that: BDAP1 was replaced with TMETN of equal weight.
The propellant performance is detected as follows:
glass transition temperature: tg-58 ℃;
low temperature mechanical properties at-60 ℃ (100 mm/min): sigmam＝7.17MPa，εm＝10％.
Comparative example 2
The difference from example 1 is that: PBT was replaced with equal weight GAP.
The propellant performance is detected as follows:
glass transition temperature: tg ═ 61 ℃;
low temperature mechanical properties at-60 ℃ (100 mm/min): sigmam＝7.85MPa，εm＝8％.
According to the detection results in the table 2, the PBT adhesive is adopted, and the insensitive energy-containing azide plasticizer BDAP1 and/or ButBOMP with better compatibility and low-temperature performance are/is introduced, so that the Tg of the propellant is effectively reduced, and the glass transition temperature of the propellant is reduced to be lower than-70 ℃. By adopting a neutral bonding agent NPBA and azide energetic propellant formula system suitable for the Schiff base bonding agent of AP, the low-temperature mechanical property of the propellant is effectively improved, and the maximum elongation of the propellant at-60 ℃ is more than 35%.
As can be seen from the test results of Table 4 and comparative examples 1-2, in example 1 and examples 6-7, but when the content of the binder exceeds the design content, the glass transition temperature of the propellant increases, and when the content of the plasticizer exceeds the design content, the low vulnerability thereof is not easy to pass; in example 1 and examples 8-11, the low temperature elongation of the propellant is low when the propellant is used with a single bonding agent or when both bonding agents are not in the formulation ranges defined herein.
The above embodiments are preferred embodiments of the present application, and the protection scope of the present application is not limited by the above embodiments, so: all equivalent changes made according to the structure, shape and principle of the present application shall be covered by the protection scope of the present application.
Claims (10)
1. A low vulnerability propellant with low temperature adaptability, characterized in that: calculated by taking the total mass of the propellant as 100 percent, the mass percentage of each component is as follows:
wherein the adhesive is 3, 3-bis-azidomethylbutoxy-tetrahydrofuran copolyether;
the plasticizer is any one or more of 1, 3-bis (2, 3-diazidopropoxy) propane and 2, 2-bis (azidomethyl) propane-1, 3-dibutyrate.
2. The propellant of claim 1, wherein: the auxiliary agent is a mixture of a bonding agent, a chemical stabilizer and a curing catalyst.
3. The propellant of claim 2, wherein: the bonding agent is a mixture of a neutral polymer bonding agent NPBA and a Schiff base bonding agent BAG-1.
4. The propellant of claim 3, wherein: the BAG-1 molecular structural formula is as follows:
(x+y+z＝5.3)。
5. the propellant of claim 3, wherein: the bonding agent is characterized in that the bonding agent comprises 20-80% of NPBA and 20-80% of BAG-1, wherein the NPBA accounts for 100% of the total mass of the bonding agent.
6. The propellant according to any one of claims 1 to 5, wherein: the oxidant is ammonium perchlorate.
7. The propellant according to any one of claims 1 to 5, wherein: the nitramine explosive is any one or more of hexanitrohexaazaisowurtzitane CL-20, HMX and RDX.
8. The propellant according to any one of claims 1 to 5, wherein: the metal fuel is aluminum powder.
9. The propellant according to any one of claims 1 to 5, wherein: the curing agent is any one or more of toluene diisocyanate TDI and polyfunctional isocyanate N-100.
10. The propellant of claim 2, wherein: the chemical stabilizer is at least one of N-methyl-p-nitroaniline MNA and 2-dinitrodiphenylamine 2-NDPA;
the curing catalyst is triphenyl bismuth.
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| CN202111564552.1A CN114394879A (en) | 2021-12-20 | 2021-12-20 | Low-vulnerability propellant with low-temperature adaptability |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5316600A (en) * | 1992-09-18 | 1994-05-31 | The United States Of America As Represented By The Secretary Of The Navy | Energetic binder explosive |
| US6997996B1 (en) * | 1995-11-13 | 2006-02-14 | The United States Of America As Represented By The Secretary Of The Army | High energy thermoplastic elastomer propellant |
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