CN116162009A - Low-sensitivity solid propellant and preparation method thereof - Google Patents
Low-sensitivity solid propellant and preparation method thereof Download PDFInfo
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- 239000004449 solid propellant Substances 0.000 title claims abstract description 40
- 238000002360 preparation method Methods 0.000 title claims abstract description 11
- 230000035945 sensitivity Effects 0.000 claims abstract description 43
- 239000007767 bonding agent Substances 0.000 claims abstract description 29
- 239000007800 oxidant agent Substances 0.000 claims abstract description 22
- 238000002156 mixing Methods 0.000 claims abstract description 21
- GDDNTTHUKVNJRA-UHFFFAOYSA-N 3-bromo-3,3-difluoroprop-1-ene Chemical compound FC(F)(Br)C=C GDDNTTHUKVNJRA-UHFFFAOYSA-N 0.000 claims abstract description 17
- 239000000203 mixture Substances 0.000 claims abstract description 17
- 230000001590 oxidative effect Effects 0.000 claims abstract description 17
- 239000003795 chemical substances by application Substances 0.000 claims abstract description 12
- 239000000853 adhesive Substances 0.000 claims abstract description 8
- 230000001070 adhesive effect Effects 0.000 claims abstract description 8
- 230000007935 neutral effect Effects 0.000 claims abstract description 8
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 6
- -1 butyl hydroxy Chemical group 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
- 229920002121 Hydroxyl-terminated polybutadiene Polymers 0.000 claims abstract description 5
- NIMLQBUJDJZYEJ-UHFFFAOYSA-N isophorone diisocyanate Chemical compound CC1(C)CC(N=C=O)CC(C)(CN=C=O)C1 NIMLQBUJDJZYEJ-UHFFFAOYSA-N 0.000 claims abstract description 5
- 238000000034 method Methods 0.000 claims description 16
- 239000002002 slurry Substances 0.000 claims description 16
- 238000005266 casting Methods 0.000 claims description 15
- 239000004014 plasticizer Substances 0.000 claims description 11
- 239000000654 additive Substances 0.000 claims description 6
- DOIRQSBPFJWKBE-UHFFFAOYSA-N dibutyl phthalate Chemical compound CCCCOC(=O)C1=CC=CC=C1C(=O)OCCCC DOIRQSBPFJWKBE-UHFFFAOYSA-N 0.000 claims description 6
- 238000005303 weighing Methods 0.000 claims description 6
- 239000011230 binding agent Substances 0.000 claims description 4
- 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 4
- 239000005058 Isophorone diisocyanate Substances 0.000 claims description 3
- MIMDHDXOBDPUQW-UHFFFAOYSA-N dioctyl decanedioate Chemical compound CCCCCCCCOC(=O)CCCCCCCCC(=O)OCCCCCCCC MIMDHDXOBDPUQW-UHFFFAOYSA-N 0.000 claims description 3
- 239000012798 spherical particle Substances 0.000 claims description 3
- AMEDKBHURXXSQO-UHFFFAOYSA-N azonous acid Chemical class ONO AMEDKBHURXXSQO-UHFFFAOYSA-N 0.000 claims description 2
- 239000003380 propellant Substances 0.000 abstract description 31
- BAPJBEWLBFYGME-UHFFFAOYSA-N Methyl acrylate Chemical compound COC(=O)C=C BAPJBEWLBFYGME-UHFFFAOYSA-N 0.000 abstract description 4
- OMIGHNLMNHATMP-UHFFFAOYSA-N 2-hydroxyethyl prop-2-enoate Chemical compound OCCOC(=O)C=C OMIGHNLMNHATMP-UHFFFAOYSA-N 0.000 abstract description 2
- NLHHRLWOUZZQLW-UHFFFAOYSA-N Acrylonitrile Chemical compound C=CC#N NLHHRLWOUZZQLW-UHFFFAOYSA-N 0.000 abstract description 2
- 230000000052 comparative effect Effects 0.000 description 15
- 239000002245 particle Substances 0.000 description 11
- 230000008569 process Effects 0.000 description 11
- 239000007787 solid Substances 0.000 description 9
- 238000004880 explosion Methods 0.000 description 7
- 230000007547 defect Effects 0.000 description 6
- 239000000463 material Substances 0.000 description 5
- 239000011148 porous material Substances 0.000 description 5
- 238000002485 combustion reaction Methods 0.000 description 4
- 238000009472 formulation Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 239000011159 matrix material Substances 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000011160 research Methods 0.000 description 3
- 239000003054 catalyst Substances 0.000 description 2
- 239000003814 drug Substances 0.000 description 2
- 239000002360 explosive Substances 0.000 description 2
- 230000001788 irregular Effects 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-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
- 239000004970 Chain extender Substances 0.000 description 1
- BSPUVYFGURDFHE-UHFFFAOYSA-N Nitramine Natural products CC1C(O)CCC2CCCNC12 BSPUVYFGURDFHE-UHFFFAOYSA-N 0.000 description 1
- 239000004721 Polyphenylene oxide Substances 0.000 description 1
- 230000003679 aging effect Effects 0.000 description 1
- 230000003712 anti-aging effect Effects 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 239000012752 auxiliary agent Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 239000003431 cross linking reagent Substances 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 239000000945 filler Substances 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 230000009477 glass transition Effects 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- POCJOGNVFHPZNS-UHFFFAOYSA-N isonitramine Natural products OC1CCCCC11CNCCC1 POCJOGNVFHPZNS-UHFFFAOYSA-N 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 229920000570 polyether Polymers 0.000 description 1
- 239000000843 powder Substances 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000005086 pumping Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 238000003860 storage Methods 0.000 description 1
- 230000007847 structural defect Effects 0.000 description 1
- 239000000126 substance Substances 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
- C06B33/12—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 the material being two or more oxygen-yielding compounds
-
- 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
Landscapes
- Chemical & Material Sciences (AREA)
- Organic Chemistry (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Adhesives Or Adhesive Processes (AREA)
Abstract
The invention relates to a low-sensitivity solid propellant and a preparation method thereof. The formula basically comprises the following components: hydroxyl-terminated polybutadiene is used as an adhesive, aluminum powder is used as metal fuel, a mixture of Ammonium Perchlorate (AP) and superfine spherical 1, 1-dihydroxy-5, 5' -bitetrazole dihydroxyamine salt (TKX-50) is used as an oxidant, and isophorone diisocyanate (IPDI) is used as a curing agent. The bonding agent is prepared by mixing neutral bonding agent (acrylonitrile, hydroxyethyl acrylate, methyl acrylate, NPBA) and alcohol amine bonding agent. Compared with the existing butyl hydroxy propellant, the formula and the preparation method provided by the invention can effectively reduce the mechanical sensitivity and the electrostatic sensitivity of the propellant.
Description
Technical Field
The invention relates to a low-sensitivity solid propellant and a preparation method thereof, belonging to the field of solid propellants.
Background
The solid propellant is an energetic material with specific functions and is a power source of a solid rocket engine. With the development of tactical missile technology in recent years, solid rocket engines have put higher requirements on propellant performance. In addition to meeting the energy requirements of the propellant, it is also desirable that the propellant possess a lower sensitivity. How to reduce the sensitivity of solid propellants is becoming a major concern for industry and scientific researchers.
The sensitivity of a solid propellant is primarily dependent on the characteristics of the solid components, such as oxidizer and explosive, contained therein. Firstly the safety characteristics of the solid component itself play a critical role in the sensitivity of the propellant. In general, where the solid component itself has a relatively high sensitivity, the solid propellant will have a relatively high sensitivity; while the sensitivity of the solid component is relatively low, the sensitivity of the propellant will be relatively low.
Secondly, the particle size morphology of the solid component can also obviously influence the sensitivity of the solid propellant, the untreated oxidant and the explosive particles are irregular in shape, and the surface is rough to form a plurality of edges and corners and protruding points. After the external force is applied, solid component particles in the propellant can be extruded and collide, the edges and the raised points are rubbed with each other, and the propellant is easy to burn and explode. The phenomenon of combustion explosion caused by local high temperature due to interaction of microscopic structural defects of the heterogeneous energetic material is called as a hot spot effect.
Meanwhile, a small amount of gas is mixed into the solid propellant in the charging process to form micro-pores, and after the solid propellant is subjected to the curing process, the micro-pores undergo high temperature and extrusion to cause defects such as debonding of the interface between the oxidant particles and the adhesive to generate micro-cracks, and the defects can also cause the increase of hot spots when the solid propellant is stimulated, so that the sensitivity of the solid propellant is improved.
The high sensitivity can increase the safety risk of the solid propellant in the transportation, storage and use processes, and the accidents such as combustion, explosion and the like can be easily caused when the solid propellant is subjected to external stimulus (such as impact, friction, static electricity and the like), so that serious consequences such as casualties, property loss and the like are caused.
The application research report on TKX-50 mainly focuses on energy research, xiong Weijiang research on the influence of TKX-50 on the energy performance of HTPB propellant, wherein the use amount of TKX-50 is 10%, and special treatment on TKX-50 is not explicitly mentioned. Liu Yunfei the application feasibility of TKX-50 in hydroxyl-terminated polyether propellant is studied, the particle size distribution of TKX-50 used is uneven, the particle morphology is irregular, and the propellant slurry process performance is poor when the use amount is more than 25%.
Disclosure of Invention
The invention solves the technical problems that: overcomes the defects of the prior art, provides a low-sensitivity solid propellant and a preparation method thereof, and reduces the sensitivity of the solid propellant.
The technical scheme of the invention is as follows:
the low-sensitivity solid propellant comprises, by mass, 5-11% of a binder, 60-80% of an oxidant, 0.5-1.5% of a curing agent, 3-18% of a metal fuel, 1-4% of a plasticizer, 0.1-0.5% of a bonding agent and 0.1-2% of other additives;
the oxidant is a mixture of Ammonium Perchlorate (AP) and 1, 1-dihydroxy-5, 5' -bitetrazole dihydroxyamine salt (TKX-50).
In the present invention, the binder is hydroxyl-terminated polybutadiene (HTPB). The adhesive is used for providing a matrix material in the formulation process.
The TKX-50 accounts for 5-30% of the total mass percent of the solid propellant.
The 1, 1-dihydroxy-5, 5' -bi tetrazole dihydroxyamine salt (TKX-50) is a spherical particle, and d 50 ＜10μm。
In the invention, the oxidant is a mixture of ammonium perchlorate and TKX-50, wherein TKX-50 accounts for 5-30% of the total weight of the solid propellant, and the rest oxidants are ammonium perchlorate. The oxidizer is used to provide a portion of the oxygen element in the combustion of the propellant as a filler for the binder matrix. In the present invention, the curing agent is isophorone diisocyanate (IPDI). In the process of curing the propellant, the IPDI and the adhesive and other components undergo curing reaction to form the material of the cross-linked network matrix structure.
The curing agent may also be Toluene Diisocyanate (TDI).
The metal fuel in the invention is aluminum powder. The metal fuel is used for improving the heat value of the propellant and keeping the combustion stability.
The plasticizer in the invention is dibutyl phthalate. The plasticizer is used for improving the technological property and low-temperature mechanical property of the propellant and reducing the glass transition temperature of the propellant. The plasticizer may also be dioctyl sebacate.
The bonding agent is a mixture of neutral bonding agent NPBA (copolymerized by acrylonitrile, hydroxyethyl acrylate and methyl acrylate) and alcohol amine bonding agent, and has the function of being adsorbed on the surface of TKX-50 to improve the technological performance of the propellant slurry.
The mass ratio of the neutral bonding agent NPBA to the alcohol amine bonding agent is 9:1-1:1.
The other additives in the invention are a burning rate catalyst, a process auxiliary agent, a curing catalyst and an anti-aging agent, and are used for improving the mechanical property, the process property, the burning property and the aging property of the propellant.
A method for preparing low sensitivity solid propellant comprises
Weighing an adhesive, a plasticizer, a bonding agent and other additives according to a proportion, adding aluminum powder, and uniformly premixing to prepare slurry;
weighing ammonium perchlorate and TKX-50 according to a proportion and uniformly mixing to obtain an oxidant mixture;
uniformly mixing all the thin slurry with a half of the oxidant mixture, then adding the rest of the oxidant mixture, uniformly mixing, adding a curing agent when mixing for 60min, continuously mixing for 60min, and vacuumizing after mixing is completed to obtain casting slurry;
pouring the pouring slurry into a vacuum pouring cylinder for forming.
The vacuumizing time is more than 15min; the vacuum degree is less than or equal to 800Pa.
The diameter of the holes in the pattern plate is less than or equal to 4mm, and the casting time is more than or equal to 30min.
The casting circulation water temperature is 50 ℃.
Aiming at the factors influencing the sensitivity of the solid propellant, the invention uses the superfine spherical TKX-50 (1, 1-dihydroxy-5, 5' -bitetrazole dihydroxyamine salt) of the low-sensitivity energetic material as an oxidant to partially replace ammonium perchlorate. On the one hand, TKX-50 is relatively insensitive in chemical property and has lower mechanical sensitivity. The striking explosion probability of the 10kg drop hammer of TKX-50 is 16%, and the characteristic drop height of the 5kg drop hammer is 50.1cm; the friction explosion probability of the 90-degree swing angle is 24% under the pressure of 3.92 MPa. On the other hand, the spherical treatment of TKX-50 can effectively reduce the edges and the raised points on the particle surface of the propellant TKX-50, so that the particle surface is flat and smooth, and the explosion probability of the solid propellant when the solid propellant is impacted by the outside is reduced. The superfine treatment can reduce the gaps among the solid particles, reduce defects and play a role in reducing the mechanical sensitivity of the propellant. Meanwhile, in the aspect of the preparation process, the invention improves the mixing and pouring process, reduces the formation of micro-pores in the propellant by increasing the vacuumizing time, reducing the pouring speed and the like, and further plays a role in reducing the internal defects of the propellant and reducing the sensitivity of the propellant. Currently, low sensitivity propellants for reducing the feel using this method have not been reported.
The relevant literature is silent about the effect of the use of the spherical TKX-50 on the sensitivity of the propellant, and neither about the vacuum operation after the end of mixing nor about the pattern plate aperture size and the casting time during the casting process. The invention reduces the sensitivity of the solid propellant by selecting the spherical TKX-50, vacuumizing operation after the mixing is finished, and limiting the aperture size and the casting time of the pattern plate in the casting process.
In summary, the present application at least includes the following beneficial technical effects:
the processed superfine spherical TKX-50 is used, the spherical treatment and the superfine treatment reduce the particle surface defects while the material has low sensitivity, so that the TKX-50 particle surface is flat and smooth, and the sensitivity of the solid propellant is further reduced.
The invention adopts the combination of neutral bonding agent and alcohol amine bonding agent to improve the technological performance of the medicine slurry, and ensures that TKX-50 is used as a secondary oxidant to partially replace ammonium perchlorate and nitramine, thus the medicine slurry has good technological performance when the consumption of TKX-50 reaches 30 percent.
Detailed Description
The present application is described in further detail below in connection with specific embodiments:
the preparation processes of examples 1-2 are as follows: weighing the adhesive, the cross-linking agent, the chain extender, the plasticizer, the bonding agent and other additives according to a proportion, adding aluminum powder, and uniformly premixing to prepare slurry. Weighing and mixing ammonium perchlorate and TKX-50 according to a proportion; the tank was opened, the temperature was set at 60 ℃, the mixer was heated and idled, after checking for no problems, the full portion of slurry was added and half of the mixture of AP and TKX-50 was added. Mixing for 5min in the normal vehicle, stopping adding the rest AP and TKX-50. And adding the curing agent when mixing is continued for 60min, and vacuumizing and maintaining for 15min after mixing is completed. And casting in a vacuum casting cylinder by adopting a pattern plate with the diameter of 4mm for 30min for molding, wherein the casting circulation water temperature is 50 ℃.
The 1, 1-dihydroxy-5, 5' -bistetrazole dihydroxyamine salt (TKX-50) in examples 1 and 2 was d 50 Spherical particles < 10 mu.
The contents of the respective components in examples 1 and 2 were different.
Example 1
In this example, the oxidant is AP+TKX-50, the curing agent is IPDI, and the plasticizer is dibutyl phthalate. The bonding agent is neutral bonding agent NPBA and alcohol amine bonding agent with the mass ratio of 1:1.
Example 2
In this example, AP+TKX-50 was used as the oxidizing agent, TDI was used as the curing agent, and dioctyl sebacate was used as the plasticizer. The bonding agent is neutral bonding agent NPBA and alcohol amine bonding agent with the mass ratio of 9:1.
Comparative example 1
In this comparative example, the difference from example 3 is only that: 72.8% AP was used as the oxidizing agent.
The preparation process of comparative example 1 was the same as in example 1.
Comparative example 2
In this comparative example, the difference from example 1 is only that: in the preparation process, no vacuum pumping is performed after the mixing is completed.
Comparative example 3
Compared to example 3, the only difference is that: the bonding agent is alcohol amine bonding agent phosphoric acid boric acid diethanolamine ester.
The contents and properties of the components of the formulations of the examples and comparative examples are shown in tables 1 and 2, respectively.
Table 1 formulation ratios of examples and comparative examples
Table 2 comparison of the properties of examples and comparative examples
Example 1 is comparable to comparative example 1 in impact sensitivity. The 50% burst rate critical firing energy of 1.63J, electrostatic spark sensitivity was significantly lower than that of comparative example 1. The friction sensitivity, the impact sensitivity, and the electrostatic sensitivity were lower than those of comparative example 2. Indicating that process improvements can reduce propellant sensitivity.
Only when the pattern plate casting of 4mm diameter for 30min in example 1 was replaced with a pattern plate casting of 6mm for 20min, the sensitivity of the obtained solid propellant was increased because the increase in the pattern plate pore size resulted in an increase in the amount of slurry passing through the pattern plate pores, and the generated air holes were increased. The reduced casting time also results in increased air pockets in the slurry, which increases the sensitivity of the propellant.
Example 2 has an explosion probability of 0% and an impact sensitivity explosion probability of 16% as compared with comparative example 1. Friction sensitivity and impact sensitivity are reduced. The propellant formulation of example 2 did not ignite the propellant powder at a capacitance of 0.22 muF and a maximum voltage of 6kv, and the electrostatic spark sensitivity was significantly reduced. In contrast to comparative example 3, the process performance of comparative example 3 is not satisfactory, whereas example 2 can be normally cast. Indicating that the bonding agent combination can effectively improve the propellant processing properties after the addition of TKX-50.
Although the present invention has been described in terms of the preferred embodiments, it is not intended to be limited to the embodiments, and any person skilled in the art can make any possible variations and modifications to the technical solution of the present invention by using the methods and technical matters disclosed above without departing from the spirit and scope of the present invention, so any simple modifications, equivalent variations and modifications to the embodiments described above according to the technical matters of the present invention are within the scope of the technical matters of the present invention.
Claims (10)
1. A low sensitivity solid propellant, characterized by: the solid propellant comprises 5 to 11 percent of adhesive, 60 to 80 percent of oxidant, 0.5 to 1.5 percent of curing agent, 3 to 18 percent of metal fuel, 1 to 4 percent of plasticizer, 0.1 to 0.5 percent of bonding agent and 0.1 to 2 percent of other additives by mass percent;
the oxidant is a mixture of ammonium perchlorate and 1, 1-dihydroxy-5, 5' -bistetrazole dihydroxyamine salt.
2. A low sensitivity solid propellant according to claim 1, wherein: the binder is hydroxyl-terminated polybutadiene.
3. A low sensitivity solid propellant according to claim 1, wherein: the 1, 1-dihydroxyl-5, 5' -bitetrazole dihydroxyl amine salt accounts for 5-30% of the total mass percent of the solid propellant.
4. A low sensitivity solid propellant according to claim 1, wherein: the 1, 1-dihydroxy-5, 5' -bi tetrazole dihydroxyamine salt is spherical particles, and d 50 ＜10μm。
5. A low sensitivity solid propellant according to claim 1, wherein: the curing agent is any one of isophorone diisocyanate and toluene diisocyanate, and the metal fuel is aluminum powder.
6. A low sensitivity solid propellant according to claim 1, wherein: the plasticizer is any one of dioctyl sebacate and dibutyl phthalate.
7. A low sensitivity solid propellant according to claim 1, wherein: the bonding agent is a mixture of neutral bonding agent NPBA and alcohol amine bonding agent; the mass ratio of neutral bonding agent NPBA to alcohol amine bonding agent is 9:1-1:1.
8. A preparation method of a low-sensitivity solid propellant is characterized by comprising the following steps: comprising
Weighing an adhesive, a plasticizer, a bonding agent and other additives according to a proportion, adding aluminum powder, and uniformly premixing to prepare slurry;
weighing ammonium perchlorate and TKX-50 according to a proportion and uniformly mixing to obtain an oxidant mixture;
uniformly mixing all the thin slurry with a half of the oxidant mixture, then adding the rest of the oxidant mixture, uniformly mixing, adding a curing agent when mixing for 60min, continuously mixing for 60min, and vacuumizing after mixing is completed to obtain casting slurry;
pouring the pouring slurry into a vacuum pouring cylinder for forming.
9. The method for preparing the low-sensitivity solid propellant according to claim 8, wherein: the vacuumizing time is more than 15min; the vacuum degree is less than or equal to 800Pa.
10. The method for preparing the low-sensitivity solid propellant according to claim 8, wherein: the diameter of the holes in the pattern plate is less than or equal to 4mm, and the casting time is more than or equal to 30min.
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| 乔治·萨顿: "火箭发动机基础", vol. 1, 北京理工大学出版社, pages: 411 - 412 * |
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