CN111925263A - High-combustion-speed azide micro-smoke propellant and preparation process thereof - Google Patents
High-combustion-speed azide micro-smoke propellant and preparation process thereof Download PDFInfo
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- CN111925263A CN111925263A CN202010524290.5A CN202010524290A CN111925263A CN 111925263 A CN111925263 A CN 111925263A CN 202010524290 A CN202010524290 A CN 202010524290A CN 111925263 A CN111925263 A CN 111925263A
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- propellant
- burning rate
- nano
- rate catalyst
- oxidizer
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- 239000003380 propellant Substances 0.000 title claims abstract description 127
- 239000000779 smoke Substances 0.000 title claims abstract description 33
- 150000001540 azides Chemical class 0.000 title claims abstract description 26
- 238000002360 preparation method Methods 0.000 title claims abstract description 14
- 239000003054 catalyst Substances 0.000 claims abstract description 80
- 239000000853 adhesive Substances 0.000 claims abstract description 48
- 230000001070 adhesive effect Effects 0.000 claims abstract description 48
- 239000007800 oxidant agent Substances 0.000 claims abstract description 34
- 239000006185 dispersion Substances 0.000 claims abstract description 16
- 239000004014 plasticizer Substances 0.000 claims abstract description 14
- 239000002994 raw material Substances 0.000 claims abstract description 14
- 239000003795 chemical substances by application Substances 0.000 claims abstract description 13
- 239000003381 stabilizer Substances 0.000 claims abstract description 12
- 239000002360 explosive Substances 0.000 claims abstract description 10
- 238000004519 manufacturing process Methods 0.000 claims abstract description 10
- 230000001590 oxidative effect Effects 0.000 claims abstract description 9
- 239000012752 auxiliary agent Substances 0.000 claims abstract description 5
- 239000000725 suspension Substances 0.000 claims abstract description 5
- GDDNTTHUKVNJRA-UHFFFAOYSA-N 3-bromo-3,3-difluoroprop-1-ene Chemical group FC(F)(Br)C=C GDDNTTHUKVNJRA-UHFFFAOYSA-N 0.000 claims description 31
- 239000002002 slurry Substances 0.000 claims description 22
- 238000002485 combustion reaction Methods 0.000 claims description 19
- 238000002156 mixing Methods 0.000 claims description 15
- 239000011230 binding agent Substances 0.000 claims description 14
- 239000002245 particle Substances 0.000 claims description 13
- AGCQZYRSTIRJFM-UHFFFAOYSA-N triethylene glycol dinitrate Chemical compound [O-][N+](=O)OCCOCCOCCO[N+]([O-])=O AGCQZYRSTIRJFM-UHFFFAOYSA-N 0.000 claims description 9
- 239000003292 glue Substances 0.000 claims description 8
- 239000000028 HMX Substances 0.000 claims description 6
- -1 butylene oxide tetrahydrofuran azide Chemical compound 0.000 claims description 6
- 239000010419 fine particle Substances 0.000 claims description 6
- 239000002202 Polyethylene glycol Substances 0.000 claims description 5
- 239000004721 Polyphenylene oxide Substances 0.000 claims description 5
- CPLXHLVBOLITMK-UHFFFAOYSA-N magnesium oxide Inorganic materials [Mg]=O CPLXHLVBOLITMK-UHFFFAOYSA-N 0.000 claims description 5
- GAGSAAHZRBTRGD-UHFFFAOYSA-N oxirane;oxolane Chemical compound C1CO1.C1CCOC1 GAGSAAHZRBTRGD-UHFFFAOYSA-N 0.000 claims description 5
- 229920000570 polyether Polymers 0.000 claims description 5
- 229920001223 polyethylene glycol Polymers 0.000 claims description 5
- 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 claims description 5
- 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 claims description 4
- 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 4
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 4
- SNIOPGDIGTZGOP-UHFFFAOYSA-N Nitroglycerin Chemical compound [O-][N+](=O)OCC(O[N+]([O-])=O)CO[N+]([O-])=O SNIOPGDIGTZGOP-UHFFFAOYSA-N 0.000 claims description 4
- GWEVSGVZZGPLCZ-UHFFFAOYSA-N Titan oxide Chemical compound O=[Ti]=O GWEVSGVZZGPLCZ-UHFFFAOYSA-N 0.000 claims description 4
- 229910026551 ZrC Inorganic materials 0.000 claims description 4
- OTCHGXYCWNXDOA-UHFFFAOYSA-N [C].[Zr] Chemical group [C].[Zr] OTCHGXYCWNXDOA-UHFFFAOYSA-N 0.000 claims description 4
- 239000011362 coarse particle Substances 0.000 claims description 4
- 239000000395 magnesium oxide Substances 0.000 claims description 4
- 239000000463 material Substances 0.000 claims description 4
- QUAMCNNWODGSJA-UHFFFAOYSA-N 1,1-dinitrooxybutyl nitrate Chemical compound CCCC(O[N+]([O-])=O)(O[N+]([O-])=O)O[N+]([O-])=O QUAMCNNWODGSJA-UHFFFAOYSA-N 0.000 claims description 3
- 239000000006 Nitroglycerin Substances 0.000 claims description 3
- 229960003711 glyceryl trinitrate Drugs 0.000 claims description 3
- HCHKCACWOHOZIP-UHFFFAOYSA-N Zinc Chemical compound [Zn] HCHKCACWOHOZIP-UHFFFAOYSA-N 0.000 claims description 2
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 claims description 2
- 229910052782 aluminium Inorganic materials 0.000 claims description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 2
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 claims description 2
- 150000001879 copper Chemical class 0.000 claims description 2
- 229910052593 corundum Inorganic materials 0.000 claims description 2
- GYZLOYUZLJXAJU-UHFFFAOYSA-N diglycidyl ether Chemical compound C1OC1COCC1CO1 GYZLOYUZLJXAJU-UHFFFAOYSA-N 0.000 claims description 2
- 229910052742 iron Inorganic materials 0.000 claims description 2
- AXZKOIWUVFPNLO-UHFFFAOYSA-N magnesium;oxygen(2-) Chemical compound [O-2].[Mg+2] AXZKOIWUVFPNLO-UHFFFAOYSA-N 0.000 claims description 2
- 229910044991 metal oxide Inorganic materials 0.000 claims description 2
- 150000004706 metal oxides Chemical class 0.000 claims description 2
- 229910000480 nickel oxide Inorganic materials 0.000 claims description 2
- 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 claims description 2
- TWNQGVIAIRXVLR-UHFFFAOYSA-N oxo(oxoalumanyloxy)alumane Chemical compound O=[Al]O[Al]=O TWNQGVIAIRXVLR-UHFFFAOYSA-N 0.000 claims description 2
- GNRSAWUEBMWBQH-UHFFFAOYSA-N oxonickel Chemical compound [Ni]=O GNRSAWUEBMWBQH-UHFFFAOYSA-N 0.000 claims description 2
- 150000003839 salts Chemical class 0.000 claims description 2
- OGIDPMRJRNCKJF-UHFFFAOYSA-N titanium oxide Inorganic materials [Ti]=O OGIDPMRJRNCKJF-UHFFFAOYSA-N 0.000 claims description 2
- 229910001845 yogo sapphire Inorganic materials 0.000 claims description 2
- 229910052725 zinc Inorganic materials 0.000 claims description 2
- 239000011701 zinc Substances 0.000 claims description 2
- 229910052726 zirconium Inorganic materials 0.000 claims description 2
- 125000002887 hydroxy group Chemical group [H]O* 0.000 claims 1
- 238000000034 method Methods 0.000 abstract description 19
- 230000008569 process Effects 0.000 abstract description 18
- 239000000203 mixture Substances 0.000 description 15
- 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 description 10
- XIFJZJPMHNUGRA-UHFFFAOYSA-N n-methyl-4-nitroaniline Chemical compound CNC1=CC=C([N+]([O-])=O)C=C1 XIFJZJPMHNUGRA-UHFFFAOYSA-N 0.000 description 9
- 239000007767 bonding agent Substances 0.000 description 7
- 238000012545 processing Methods 0.000 description 7
- 230000007935 neutral effect Effects 0.000 description 5
- 229920000642 polymer Polymers 0.000 description 5
- 238000012360 testing method Methods 0.000 description 5
- DVKJHBMWWAPEIU-UHFFFAOYSA-N toluene 2,4-diisocyanate Chemical compound CC1=CC=C(N=C=O)C=C1N=C=O DVKJHBMWWAPEIU-UHFFFAOYSA-N 0.000 description 5
- 239000012757 flame retardant agent Substances 0.000 description 4
- 239000007787 solid Substances 0.000 description 4
- 238000010521 absorption reaction Methods 0.000 description 3
- 238000005054 agglomeration Methods 0.000 description 3
- 230000002776 aggregation Effects 0.000 description 3
- 238000006243 chemical reaction Methods 0.000 description 3
- 238000004132 cross linking Methods 0.000 description 3
- 238000011160 research Methods 0.000 description 3
- RTZKZFJDLAIYFH-UHFFFAOYSA-N Diethyl ether Chemical compound CCOCC RTZKZFJDLAIYFH-UHFFFAOYSA-N 0.000 description 2
- 238000005266 casting Methods 0.000 description 2
- 230000003197 catalytic effect Effects 0.000 description 2
- 238000006555 catalytic reaction Methods 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- WYURNTSHIVDZCO-UHFFFAOYSA-N tetrahydrofuran Substances C1CCOC1 WYURNTSHIVDZCO-UHFFFAOYSA-N 0.000 description 2
- 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 description 1
- RBACIKXCRWGCBB-UHFFFAOYSA-N 1,2-Epoxybutane Chemical compound CCC1CO1 RBACIKXCRWGCBB-UHFFFAOYSA-N 0.000 description 1
- BSPUVYFGURDFHE-UHFFFAOYSA-N Nitramine Natural products CC1C(O)CCC2CCCNC12 BSPUVYFGURDFHE-UHFFFAOYSA-N 0.000 description 1
- 239000000654 additive Substances 0.000 description 1
- 230000000996 additive effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 125000000484 butyl group Chemical group [H]C([*])([H])C([H])([H])C([H])([H])C([H])([H])[H] 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000007123 defense Effects 0.000 description 1
- 239000000945 filler Substances 0.000 description 1
- 239000013022 formulation composition Substances 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 239000003721 gunpowder Substances 0.000 description 1
- 239000012948 isocyanate Substances 0.000 description 1
- 150000002513 isocyanates Chemical class 0.000 description 1
- POCJOGNVFHPZNS-UHFFFAOYSA-N isonitramine Natural products OC1CCCCC11CNCCC1 POCJOGNVFHPZNS-UHFFFAOYSA-N 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000011056 performance test Methods 0.000 description 1
- 229920001748 polybutylene Polymers 0.000 description 1
- 239000000376 reactant Substances 0.000 description 1
- 239000004449 solid propellant Substances 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
- YLQBMQCUIZJEEH-UHFFFAOYSA-N tetrahydrofuran Natural products C=1C=COC=1 YLQBMQCUIZJEEH-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- 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
-
- 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
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B23/00—Compositions characterised by non-explosive or non-thermic constituents
- C06B23/007—Ballistic modifiers, burning rate catalysts, burning rate depressing agents, e.g. for gas generating
-
- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B29/00—Compositions containing an inorganic oxygen-halogen salt, e.g. chlorate, perchlorate
- C06B29/22—Compositions containing an inorganic oxygen-halogen salt, e.g. chlorate, perchlorate the salt being ammonium perchlorate
-
- 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
- C06B45/105—The resin being a polymer bearing energetic groups or containing a soluble organic explosive
Landscapes
- Chemical & Material Sciences (AREA)
- Organic Chemistry (AREA)
- Molecular Biology (AREA)
- Health & Medical Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- Dispersion Chemistry (AREA)
- Inorganic Chemistry (AREA)
- Crystallography & Structural Chemistry (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Adhesives Or Adhesive Processes (AREA)
- Catalysts (AREA)
Abstract
The invention provides a high-combustion-speed azide micro-smoke propellant and a preparation process thereof, wherein the propellant is prepared from the following raw material components in percentage by mass: adhesive: 5.2% -13%; an energy-containing plasticizer: 10% -20%; oxidizing agent: 35% -55%; energetic explosive: 15% -30%; nano burning rate catalyst: 2% -5.6%; a flame stabilizer: 0.5 to 1 percent; curing agent: 1% -2%; functional auxiliary agents: and (4) the balance. The invention carries out pre-dispersion treatment on a part of inert adhesive and the nano burning rate catalyst to form suspension, adds the pre-dispersed nano burning rate catalyst into the propellant, obviously improves the burning rate of the propellant, has the burning rate of 6.86MPa of more than or equal to 50mm/s, and greatly reduces the content of superfine or fine-grained oxidant in the formula under the condition of reaching the same burning rate, thereby greatly improving the process performance of the propellant and simultaneously reducing the safety risk in the production process of the propellant.
Description
Technical Field
The invention belongs to the technical field of solid propellants, and particularly relates to a high-combustion-speed azide micro-smoke propellant and a preparation process thereof.
Background
The new generation of antitank missiles, air defense missiles, interception missiles, high-speed kinetic energy missiles and the like have requirements on high energy, high burning speed, low characteristic signals and the like for a propellant system. The high-combustion-speed propellant can enable the solid rocket engine to generate larger thrust in a short time, meanwhile, the end face combustion charging of the rocket engine can be realized, the loading coefficient is increased, the loading amount is increased, the negative mass of the engine is reduced, and the range is increased. The azide propellant has the advantages of high energy, high burning speed of the body, clean fuel gas, low characteristic signals and the like, so that the azide propellant becomes the first choice of the current high-burning-speed high-energy low-smoke or micro-smoke propellant.
Generally, the method for improving the burning rate of the high-energy micro-smoke propellant mostly adopts the technical means of improving the content of fine-grained or ultrafine Ammonium Perchlorate (AP), adding a nanometer burning rate catalyst, improving the content of the nanometer burning rate catalyst, improving the solid content and the like. However, the contents of fine-grained solid filler and solid (mainly oxidant) in the components are high, so that the viscosity of the propellant in the mixing process and the discharged slurry is high, the phenomena of rapid increase of the temperature and the torque of the propellant are easy to occur when the propellant is mixed in a vertical mixer, and the safety risks of production and tests are greatly increased. Meanwhile, as the viscosity of propellant slurry is high, the nano burning rate catalyst is not uniformly dispersed in the propellant and is easy to agglomerate into small particles with the particle size of phi 1 mm-phi 3mm, and the flower plates are easy to block in the vacuum spraying and casting process, so that the casting requirement of a new generation of high-performance missile engine cannot be met. In addition, due to the agglomeration characteristic of the nano burning rate catalyst, after the addition amount of the nano burning rate catalyst in the propellant reaches a saturation amount, the burning rate of the propellant is basically unchanged along with the increase of the content of the nano burning rate catalyst, so that the addition amount of the nano burning rate catalyst is small or the burning rate catalysis efficiency of the nano burning rate catalyst is low, and the improvement range of the burning rate of the propellant is greatly limited.
In view of this, research is needed to solve the problems of low combustion rate catalytic efficiency, high production and test safety risks and poor process performance of the nano combustion rate catalyst in the high combustion rate and high energy micro-smoke propellant, so as to provide a high combustion rate azide micro-smoke propellant with controllable safety risks and excellent process performance and a preparation process thereof.
Disclosure of Invention
The invention aims to overcome the defects and safety risks in the prior art and provide a high-combustion-rate azide micro-smoke propellant with controllable safety risks and excellent process performance. The invention is completed by adding the predispersed nano burning rate catalyst into the propellant, reasonably selecting and optimally designing each component, content and parameter in the propellant, obviously improving the burning rate of the propellant, reducing the addition of superfine or fine-grained AP, further greatly improving the flow leveling property of the discharged propellant slurry and the safety performance in the production process, obtaining the raw material composition of the high-burning-rate high-energy micro-smoke propellant with good process performance, and meeting the technical requirements of a new generation of high-performance missile weapon system on high-energy micro-smoke propellant with high burning rate, safety, controllability and excellent process performance.
The technical scheme provided by the invention is as follows:
in a first aspect, the high-combustion-speed azide micro-smoke propellant is prepared from the following raw material components in percentage by mass:
adhesive: 5.2% -13%;
an energy-containing plasticizer: 10% -20%;
oxidizing agent: 35% -55%;
energetic explosive: 15% -30%;
nano burning rate catalyst: 2% -5.6%;
a flame stabilizer: 0.5 to 1 percent;
curing agent: 1% -2%;
functional auxiliary agents: and (4) the balance.
In a second aspect, a process for preparing a high-combustion-rate azide micro-smoke propellant, is used for preparing the high-combustion-rate azide micro-smoke propellant of the first aspect, and includes:
step 1, performing pre-dispersion treatment on part of inert adhesive and a nano burning rate catalyst according to a set proportion to obtain a pre-dispersed nano burning rate catalyst;
step 2, premixing the energy-containing adhesive and the energy-containing plasticizer before use to form uniform glue solution;
step 3, pre-dispersing the pre-dispersed nano burning rate catalyst, the functional assistant, the flame stabilizer, the inert adhesive and the glue solution before mixing, adding the pre-mixed material into a mixing pot, sequentially adding the energetic explosive, the oxidant and the curing agent, uniformly mixing at 50-60 ℃, and then pouring the slurry into an engine shell or a mold by using a vacuum pouring system;
and 4, curing the engine shell or the die after the slurry is poured at 45-55 ℃ for at least 5 days.
According to the high-combustion-speed azide micro-smoke propellant and the preparation process thereof provided by the invention, the high-combustion-speed azide micro-smoke propellant has the following beneficial effects:
(1) the invention pre-disperses a part of inert adhesive in the propellant and the nano burning rate catalyst according to a certain proportion to form a fine suspension with good flow leveling property and uniform dispersion, solves the problems of easy agglomeration and non-uniform dispersion of the nano burning rate catalyst in the propellant, and greatly improves the addition amount and the burning rate catalysis efficiency. Under the condition that the formula composition is unchanged and the nano burning rate catalyst with the same content is added into the propellant in a pre-dispersion mode, the burning rate of the propellant is obviously improved;
(2) in the invention, no new inert additive is introduced into the pre-dispersed nano burning rate catalyst, so that the energy performance and the mechanical property of the propellant are basically not influenced, and the rest components, contents and parameters in the propellant are optimally designed, so that the propellant not only has high burning rate, but also has excellent performances such as high energy, excellent mechanical property and the like;
(3) according to the technical scheme, the oxidizer AP with different grain size grading is adopted, so that the addition amount of the superfine or fine grain size AP can be obviously reduced, the technological performance of the propellant and the safety performance in the production process are greatly improved, and the high-energy micro-smoke propellant composition with high burning speed, controllable production safety risk and excellent technological performance is obtained.
Detailed Description
The features and advantages of the present invention will become more apparent and appreciated from the following detailed description of the invention.
The word "exemplary" is used exclusively herein to mean "serving as an example, embodiment, or illustration. Any embodiment described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other embodiments.
According to the first aspect of the invention, the high-burning-rate azide micro-smoke propellant is prepared from the following raw material components in percentage by mass:
adhesive: 5.2% -13%;
an energy-containing plasticizer: 10% -20%;
oxidizing agent: 35% -55%;
energetic explosive: 15% -30%;
nano burning rate catalyst: 2% -5.6%;
a flame stabilizer: 0.5 to 1 percent;
curing agent: 1% -2%;
functional auxiliary agents: and (4) the balance.
In the invention, the adhesive comprises an energy-containing adhesive and an inert adhesive, wherein the energy-containing adhesive is selected from any one or combination of polyazide glycidyl ether (GAP) or epoxy butane tetrahydrofuran azide Polyether (PBT); the inert adhesive is selected from any one or the combination of hydroxyl-terminated ethylene oxide-tetrahydrofuran copolyether (PET) or polyethylene glycol (PEG).
Furthermore, the mass ratio of the energy-containing adhesive to the inert adhesive is between 1.0 and 3.0. If the amount of energetic binder is low and below the minimum of the above range, low energy of the propellant results; if the amount of the energy-containing binder is higher than the maximum value of the above range, the amount of the inert binder is small, and a propellant having excellent mechanical properties cannot be obtained.
In the present invention, the energetic plasticizer is selected from any one of Nitroglycerin (NG), trimethylolethane trinitrate (TMETN), triethylene glycol dinitrate (TEGDN), butanetriol trinitrate (BTTN), or nitroxyethylnitramines (NENAs), or a combination thereof.
Furthermore, the plasticizing ratio (i.e. the mass ratio of the energetic plasticizer/the total amount of the binder) is between 1.0 and 3.0. If the energetic plasticizer is relatively low and is lower than the minimum value of the range, on one hand, the adhesiveness formed by premixing the adhesive and the energetic plasticizer is high, and on the other hand, the process performance of the prepared propellant is poor; if the energy-containing plasticization ratio is relatively high and is higher than the maximum value of the above range, the content of the adhesive is relatively low, that is, the concentration of the reactant of the crosslinking reaction in the propellant system is reduced, thereby affecting the network crosslinking reaction of the propellant system and causing poor mechanical properties of the propellant.
In the present invention, the oxidant is Ammonium Perchlorate (AP).
Further, the median diameter d of the oxidizing agent50Is 1-300 μm. If the particle size is lower than the minimum value of the above range, on one hand, the process performance of the propellant is deteriorated, and on the other hand, as AP has moisture absorption property, the smaller the particle size is, the more moisture absorption is, and the network crosslinking reaction of the propellant is easily influenced due to the moisture absorption in the production and test processes; if the particle size is higher than the maximum value of the above range, the extent of increase in the burning rate of the propellant is limited.
Further, the oxidizer is divided into a fine-particle oxidizer and a coarse-particle oxidizer, the fine-particle oxidizer and the coarse-particle oxidizer are used as raw materials of the propellant, and the median particle diameter d of the fine-particle oxidizer501 to 10 mu m, the median diameter d of the coarse-grained oxidant50Is 100-300 μm.
Furthermore, the mass ratio of the fine-grained oxidant to the coarse-grained oxidant is (1-2.3): 1.
In the present invention, the energetic explosive is selected from any one of or a combination of HMX, RDX, or CL-20.
In the invention, the nanometer burning rate catalyst is any one or the combination of lead salt, copper salt and oxides of lead, zinc, zirconium, iron and aluminum, wherein the median particle diameter d50All are between 50nm and 100 nm. The particle size is important for the catalytic effect of the nano burning rate catalyst, and the inventor researches and discovers that the small particle size of the nano burning rate catalyst in the raw material components, which is lower than the minimum value of the range, can influence the dispersion uniformity of the nano burning rate catalyst; if the particle size of the nano burning rate catalyst in the raw material components is large and higher than the maximum value of the above range, the catalyst efficiency is lowered.
Further, the nano burning rate catalyst is used for preparing the propellant in a raw material state in a pre-dispersion treatment mode, and the pre-dispersion treatment comprises the following steps: mixing a part of inert adhesive in the adhesive with the nano burning rate catalyst according to a set proportion to form a fine suspension with good fluidity and uniform dispersion. Particularly, through research, the mass ratio of the inert adhesive to the nano burning rate catalyst in the pre-dispersed burning rate catalyst is 3/7-5/5. If the amount of the inert binder is small, a fine suspension cannot be formed; if the consumption of the inert adhesive is larger, the total content of the inert adhesive is unchanged after the formulation composition is fixed, and if the mass ratio of the inert adhesive to the nano burning rate catalyst is increased, the addition amount of the burning rate catalyst is reduced, so that the amplitude of increasing the burning rate of the propellant is reduced.
It is worth noting that the nano burning rate catalyst in the propellant can be added in higher content without aggravating agglomeration phenomenon and slurry viscosity/fluidity due to the pre-dispersion treatment of the nano burning rate catalyst. In the prior art, the addition amount of the nano burning rate catalyst accounts for about 1-2.5% of the propellant, but in the invention, the addition amount of the nano burning rate catalyst can reach 2.5-5% of the propellant, and the added nano burning rate catalyst can obviously improve the burning rate of the propellant.
In the invention, the combustion stabilizer is selected from high-melting-point zirconium carbide ZrC or one or more of the following high-melting-point metal oxides: titanium oxide TiO2Magnesium oxide MgO, nickel oxide NiO, aluminum oxide Al2O3。
In the present invention, the curing agent is preferably any one or a combination of Tolylene Diisocyanate (TDI), polyfunctional isocyanate (N-100), and the like;
in the invention, the functional auxiliary agent comprises a curing catalyst, a stabilizer and a bonding agent, wherein the curing catalyst is preferably triphenyl bismuth TPB, the stabilizer is preferably N-methyl paranitroaniline (MNA), and the bonding agent is preferably a Neutral Polymer Bonding Agent (NPBA).
The high-combustion-speed nitrogen-laminated micro-smoke propellant has the combustion speed of more than or equal to 50mm/s at 6.86MPa under the condition of keeping higher energy and better mechanical property level, the yield value of the propellant discharged slurry and the yield value of the slurry after 5 hours are not more than 50Pa, the viscosity is not more than 400 Pa.s, and the technical requirements of a new generation of tactical missile engine on high-combustion speed and excellent technological property of the high-energy micro-smoke propellant are met.
According to a second aspect of the present invention, there is provided a process for preparing a high-combustion-rate azide-based micro-smoke propellant, for preparing the high-combustion-rate azide-based micro-smoke propellant according to the first aspect, comprising the following steps:
step 1, performing pre-dispersion treatment on part of inert adhesive and a nano burning rate catalyst according to a set proportion to obtain a pre-dispersed nano burning rate catalyst;
step 2, premixing the energy-containing adhesive and the energy-containing plasticizer before use to form uniform glue solution;
step 3, pre-dispersing the pre-dispersed nano burning rate catalyst, the functional assistant, the flame stabilizer, the inert adhesive and the glue solution before mixing, adding the pre-mixed material into a mixing pot, sequentially adding the energetic explosive, the oxidant and the curing agent, uniformly mixing at 50-60 ℃, and then pouring the slurry into an engine shell or a mold by using a vacuum pouring system;
and 4, curing the engine shell or the die after the slurry is poured at 45-55 ℃ for at least 5 days, such as 5-7 days.
Examples
Example 1
The propellant composition is shown in table 1:
TABLE 1
| Composition of raw materials | Quality (g) |
| Polyazidoglycidyl ether GAP/hydroxy-terminated ethylene oxide-tetrahydrofuran copolyether PET | 70/35 |
| Nitro glycerin NG/triethylene glycol dinitrate TEGDN | 79/79 |
| HMX (HMX) | 200 |
| Ammonium perchlorate AP (2 mu m) | 100 |
| Ammonium perchlorate AP (7 mu m) | 220 |
| Ammonium perchlorate AP (130 μm) | 155 |
| Nanometer burning rate catalyst (100nm) | 30 |
| Flame-retardant agent (Al)2O3) | 10 |
| Curing agent (TDI) | 13.1 |
| Triphenylbismuth (TPB) | 0.1 |
| N-methyl-p-nitroaniline (MNA) | 6 |
| Neutral Polymer Bonding Agent (NPBA) | 2.8 |
The preparation process of 1kg of propellant is as follows:
step 1, performing pre-dispersion treatment on 30g of inert adhesive and 30g of nano burning rate catalyst to obtain a pre-dispersed nano burning rate catalyst; the mass ratio of the inert adhesive to the nano burning rate catalyst is 5/5;
step 2, premixing the energy-containing adhesive and the plasticizer to form uniform glue solution before use;
step 3, pre-dispersing the pre-dispersed nano burning rate catalyst, the functional assistant, the flame stabilizer, the inert adhesive and the glue solution before mixing, adding the pre-mixed material into a mixing pot, sequentially adding the energetic explosive, the oxidant, the curing agent and the like, uniformly mixing at 55 ℃, and pouring the slurry into a mold by using a vacuum pouring system;
and 4, placing the mixture in an oil bath oven at 50 ℃ for curing for 5 days.
The performance tests of the propellant obtained in the embodiment specifically comprise the tests of combustion performance and process performance, wherein the test standard of the combustion performance is GJB770B-2005 (gunpowder test method); propellant charges were discharged using a rotational viscometer (HAAKE, Germany)The rheological properties of the slurries are characterized mainly by a shear rate of 1s-1Viscosity (i.e., apparent viscosity) and shear rate of 1s-1The fluidity and the leveling property of the propellant discharged slurry are respectively judged according to the maximum shear stress (namely the yield value).
The combustion and processing properties of the propellant are shown in table 2 below:
TABLE 2
As can be seen from Table 2, the combustion rate of the propellant 6.86MPa is 58.86mm/s, the yield value and the viscosity of the discharged slurry are 17.3Pa and 266.8Pa · s respectively, the propellant has better flow leveling property, and the yield value and the viscosity increase amplitude are not large along with the increase of time. Therefore, the azide micro-smoke propellant has the characteristics of high burning speed and excellent process performance.
Example 2
The propellant composition is shown in table 3:
TABLE 3
The preparation process of 1kg of propellant is as follows:
step 1, carrying out pre-dispersion treatment on 18g of inert adhesive and 40g of nano burning rate catalyst to obtain a pre-dispersed nano burning rate catalyst; the mass ratio of the inert adhesive to the nano burning rate catalyst is 3/6.7 (between 3/7-5/5);
steps 2 to 4 were the same as those in example 1.
The combustion and processing properties of the propellant are shown in table 4 below:
TABLE 4
As can be seen from Table 4, the burning rate of the propellant 6.86MPa is 63.15mm/s, the yield value and the viscosity of the discharged slurry are 22.1Pa and 259.2 Pa.s respectively, the flow leveling property is better, and the yield value and the viscosity increase amplitude are not large along with the increase of time. The azide micro-smoke propellant has the characteristics of high burning speed and excellent process performance.
Example 3
The propellant composition is shown in table 5:
TABLE 5
The preparation process of 1kg of propellant is as follows:
step 1, pre-dispersing 30g of inert adhesive and 50g of nano burning rate catalyst to obtain a pre-dispersed nano burning rate catalyst; the mass ratio of the inert adhesive to the nano burning rate catalyst is 3/5;
steps 2 to 4 were the same as those in example 1.
The combustion and processing properties of the propellant are shown in table 6 below:
TABLE 6
As can be seen from Table 6, the burning rate of the propellant 6.86MPa is 53.22mm/s, the yield value and the viscosity of the discharged slurry are respectively 20.5Pa and 246.9Pa · s, the flow leveling property is better, and the yield value and the viscosity increase amplitude are not large along with the increase of time. The azide micro-smoke propellant has the characteristics of high burning speed and excellent process performance.
Example 4
The propellant composition is shown in table 7:
TABLE 7
The preparation process of the propellant comprises the following steps:
step 1, pre-dispersing 20g of inert adhesive and 30g of nano burning rate catalyst to obtain a pre-dispersed nano burning rate catalyst; the mass ratio of the inert adhesive to the nano burning rate catalyst is 4/6;
steps 2 to 4 were the same as those in example 1.
The combustion and processing properties of the propellant are shown in table 8 below:
TABLE 8
As can be seen from Table 8, the burning rate of the propellant 6.86MPa is 55.42mm/s, the yield value and the viscosity of the discharged slurry are 23.3Pa and 263.1Pa · s respectively, the flow leveling property is good, and the yield value and the viscosity increase amplitude are not large along with the increase of time. The azide micro-smoke propellant has the characteristics of high burning speed and excellent process performance.
Example 5
The propellant composition is shown in table 9:
TABLE 9
| Composition of raw materials | Quality (g) |
| Butylene oxide tetrahydrofuran azide polyether PBT/hydroxyl-terminated ethylene oxide-tetrahydrofuran copolyether PET | 73.4/36.6 |
| Triethylene glycol dinitrate TEGDN/butyl nitroxyethyl nitramine Bu-NENA | 72/72 |
| HMX (HMX) | 200 |
| Ammonium perchlorate AP (2 mu m) | 50 |
| Ammonium perchlorate AP (7 mu m) | 280 |
| Ammonium perchlorate AP (130 μm) | 145 |
| Nanometer burning rate catalyst (100nm) | 40 |
| Flame-retardant agent (Al)2O3) | 5 |
| Curing agent (N-100) | 12.8 |
| Triphenylbismuth (TPB) | 0.2 |
| N-methyl-p-nitroaniline (MNA) | 8 |
| Neutral Polymer Bonding Agent (NPBA) | 5 |
The preparation process of the propellant comprises the following steps:
step 1, pre-dispersing 30g of inert adhesive and 40g of nano burning rate catalyst to obtain a pre-dispersed nano burning rate catalyst; the mass ratio of the inert adhesive to the nano burning rate catalyst is 3/4;
steps 2 to 4 were the same as those in example 1.
The combustion and processing properties of the propellant are shown in table 10 below:
watch 10
As can be seen from Table 10, the burning rate of the propellant 6.86MPa is 52.36mm/s, the yield value and the viscosity of the discharged slurry are respectively 21.3Pa and 244.3Pa · s, the flow leveling property is better, and the yield value and the viscosity increase amplitude are not large along with the increase of time. The azide micro-smoke propellant has the characteristics of high burning speed and excellent process performance.
Example 6
The propellant composition is shown in table 11:
TABLE 11
| Composition of raw materials | Quality (g) |
| Polybutylene oxide-tetrahydrofuran azide polyether PBT/polyethylene glycol PEG | 83.4/41.6 |
| Trimethylolethane trinitrate TMETN/butylnitroxyethylnitramine Bu-NENA | 62.5/62.5 |
| RDX of hexogen | 180 |
| Ammonium perchlorate AP (2 mu m) | 60 |
| Ammonium perchlorate AP (5 mu m) | 200 |
| Ammonium perchlorate AP (130 μm) | 240 |
| Nanometer burning rate catalyst (80nm) | 35 |
| Flame-retardant agent (Al)2O3) | 8 |
| Curing agent (TDI) | 13.7 |
| Triphenylbismuth (TPB) | 0.3 |
| N-methyl-p-nitroAniline (MNA) | 8 |
| Neutral Polymer Bonding Agent (NPBA) | 5 |
The preparation process of the propellant comprises the following steps:
step 1, pre-dispersing 35g of inert adhesive and 35g of nano burning rate catalyst to obtain a pre-dispersed nano burning rate catalyst; the mass ratio of the inert adhesive to the nano burning rate catalyst is 5/5;
steps 2 to 4 were the same as those in example 1.
The combustion and processing properties of the propellant are shown in table 12 below:
TABLE 12
As can be seen from Table 12, the burning rate of the propellant 6.86MPa is 51.11mm/s, the yield value and the viscosity of the discharged slurry are 19.8Pa and 251.1Pa · s respectively, the flow leveling property is better, and the yield value and the viscosity increase amplitude are not large along with the increase of time. The azide micro-smoke propellant has the characteristics of high burning speed and excellent process performance.
Example 7
The propellant composition is shown in table 13:
watch 13
| Composition of raw materials | Quality (g) |
| Butylene oxide tetrahydrofuran azide polyether PBT/hydroxyl-terminated ethylene oxide-tetrahydrofuran | 67.5/22.5 |
| Triethylene glycol dinitrate TEGDN | 70.5/70.5 |
| Hexanitrohexaazaisowurtzitane CL-20 | 200 |
| Ammonium perchlorate AP (5 mu m) | 250 |
| Ammonium perchlorate AP (130 μm) | 245 |
| Nanometer burning rate catalyst (50nm) | 40 |
| Flame-retardant agent (Al)2O3) | 5 |
| Curing agent (TDI/N-100) | 14.4 |
| Triphenylbismuth (TPB) | 0.6 |
| N-methyl-p-nitroaniline (MNA) | 8 |
| Neutral Polymer Bonding Agent (NPBA) | 6 |
The preparation process of the propellant comprises the following steps:
step 1, pre-dispersing 20g of inert adhesive and 40g of nano burning rate catalyst to obtain a pre-dispersed nano burning rate catalyst; the mass ratio of the inert adhesive to the nano burning rate catalyst is 1/2;
steps 2 to 4 were the same as those in example 1.
The combustion and processing properties of the propellant are shown in table 14 below:
TABLE 14
As can be seen from Table 14, the burning rate of the propellant 6.86MPa is 54.68mm/s, the yield value and the viscosity of the discharged slurry are 25.1Pa and 287.1Pa · s respectively, the propellant has better flow leveling property, and the yield value and the viscosity increase amplitude are not large along with the increase of time. The azide micro-smoke propellant has the characteristics of high burning speed and excellent process performance.
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.
Claims (16)
1. The high-combustion-speed azide micro-smoke propellant is characterized by being prepared from the following raw materials in percentage by mass:
adhesive: 5.2% -13%;
an energy-containing plasticizer: 10% -20%;
oxidizing agent: 35% -55%;
energetic explosive: 15% -30%;
nano burning rate catalyst: 2% -5.6%;
a flame stabilizer: 0.5 to 1 percent;
curing agent: 1% -2%;
functional auxiliary agents: and (4) the balance.
2. The propellant of claim 1, wherein the binder comprises an energetic binder and an inert binder.
3. The propellant of claim 2, wherein the energetic binder is any one or a combination of polyazidyl glycidyl ether or butylene oxide tetrahydrofuran azide polyether.
4. The propellant of claim 2, wherein the inert binder is any one or a combination of a hydroxyl terminated ethylene oxide-tetrahydrofuran copolyether or polyethylene glycol.
5. The propellant of claim 2, wherein the mass ratio of energetic binder to inert binder is between 1.0 and 3.0.
6. The propellant of claim 1, wherein the energetic plasticizer is any one or a combination of nitroglycerin, trimethylolethane trinitrate, triethylene glycol dinitrate, or butanetriol trinitrate or nitrooxyethyl nitramine compounds.
7. The propellant of claim 1, wherein the mass ratio of the energetic plasticizer to the binder is between 1.0 and 3.0.
8. The propellant of claim 1 wherein the oxidizer is ammonium perchlorate and the median particle size of the oxidizer, d, is50Is 1-300 μm.
9. According to the rightThe propellant of claim 8 wherein the oxidizer is divided into a fine-particle oxidizer and a coarse-particle oxidizer, the fine-particle oxidizer and the coarse-particle oxidizer together serving as the oxidizer of the propellant, the fine-particle oxidizer having a median particle diameter d501 to 10 mu m, the median diameter d of the coarse-grained oxidant50Is 100-300 μm.
10. The propellant according to claim 9, wherein the mass ratio of the fine-particle-size oxidizer to the coarse-particle-size oxidizer is (1-2.3): 1.
11. The propellant of claim 1 wherein the energetic explosive is selected from any one or a combination of octogen, hexogen, or hexanitrohexaazaisowurtzitane.
12. The propellant of claim 1, wherein the nano burning rate catalyst is any one or combination of lead salt, copper salt and oxides of lead, zinc, zirconium, iron and aluminum;
median particle diameter d of nano burning rate catalyst50Is 50nm to 100 nm.
13. The propellant according to claim 12, wherein the nano burn rate catalyst is used as a raw material for the preparation of the propellant in a pre-dispersion treatment comprising the steps of: mixing a part of inert adhesive in the adhesive with the nano burning rate catalyst according to a set proportion to form a suspension.
14. The propellant according to claim 13, wherein the mass ratio of the inert binder to the nano burning rate catalyst in the pre-dispersion treated burning rate catalyst is between 3/7 and 5/5.
15. The propellant of claim 1, wherein the combustion stabilizer is zirconium carbide (ZrC), or one or more of the following metal oxides: titanium oxide TiO2Magnesium oxide MgO, nickel oxide NiO, aluminum oxide Al2O3。
16. A process for preparing a high-burning-rate azide-based micro-smoke propellant, which is used for preparing the high-burning-rate azide-based micro-smoke propellant as claimed in one of the claims 1 to 15, and comprises the following steps:
step 1, performing pre-dispersion treatment on part of inert adhesive and a nano burning rate catalyst according to a set proportion to obtain a pre-dispersed nano burning rate catalyst;
step 2, premixing the energy-containing adhesive and the energy-containing plasticizer before use to form uniform glue solution;
step 3, pre-dispersing the pre-dispersed nano burning rate catalyst, the functional assistant, the flame stabilizer, the inert adhesive and the glue solution before mixing, adding the pre-mixed material into a mixing pot, sequentially adding the energetic explosive, the oxidant and the curing agent, uniformly mixing at 50-60 ℃, and then pouring the slurry into an engine shell or a mold by using a vacuum pouring system;
and 4, curing the engine shell or the die after the slurry is poured at 45-55 ℃ for at least 5 days.
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