CN109851457B - Electrically-controlled solid propellant containing metal fuel and preparation method thereof - Google Patents
Electrically-controlled solid propellant containing metal fuel and preparation method thereof Download PDFInfo
- Publication number
- CN109851457B CN109851457B CN201910223087.1A CN201910223087A CN109851457B CN 109851457 B CN109851457 B CN 109851457B CN 201910223087 A CN201910223087 A CN 201910223087A CN 109851457 B CN109851457 B CN 109851457B
- Authority
- CN
- China
- Prior art keywords
- metal fuel
- percent
- propellant
- solid propellant
- stirring
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Landscapes
- Adhesives Or Adhesive Processes (AREA)
- Air Bags (AREA)
Abstract
The invention relates to an electric control solid propellant containing metal fuel and a preparation method thereof, belongs to the technical field of solid propellants, and particularly relates to a high-energy electric control solid propellant containing metal fuel. The propellant can obviously improve the energy performance of the electric control solid propellant, meets the requirement of 1.3 level of danger level, and is suitable for the propellant for attitude and orbit control with higher requirement on the energy performance of the propellant.
Description
Technical Field
The invention relates to an electric control solid propellant containing metal fuel and a preparation method thereof, belongs to the technical field of solid propellants, and particularly relates to a high-energy electric control solid propellant containing metal fuel.
Background
Advanced missile weaponry requires long range, strong penetration and high survivability, and the engine is urgently required to have the characteristics of higher energy, accurate controllable thrust, good safety performance and the like, so that the development of a solid propellant technology with multiple starting capability is urgently needed. Meanwhile, the technologies of near space aircrafts, various satellites, deep space exploration and the like also provide requirements on the engine for stable and reliable work, high efficiency, large thrust, wide adjustable range and the like. The solid propulsion technology has the advantages of simple structure, quick response, convenient use and maintenance and the like, and is more widely applied to strategic and tactical missile weapons; however, the burning speed of the solid propellant cannot be regulated and controlled in time, so that the thrust regulating capability of the solid rocket engine is limited, the solid rocket engine does not have flexible energy management capability, and the wide application of the solid propellant technology is restricted.
The electric control solid propellant is a novel solid propellant technology based on the special electrical characteristics of key components, the combustion speed of the propellant can be adjusted by adjusting the magnitude of external voltage, and further the thrust of an engine can be adjusted, so that the electric control solid propellant is an important direction for the development of the field of the solid propellant in the future. The theoretical specific impulse of the existing electric control solid propellant is about 220s, and the capacity performance of the existing electric control solid propellant needs to be further improved.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the electric control solid propellant has high energy, the theoretical specific impulse can reach more than 250s, and the safety performance of the propellant meets the requirement of 1.3 level of danger level. Aluminum powder Al, boron powder B, silicon powder Si, magnesium powder Mg or tungsten powder W and the like are used as metal fuels, the metal fuels are subjected to special coating modification treatment before use, and a bonding agent is added to improve the interface performance so as to obtain the electric control solid propellant with good uniformity and compactness.
The technical solution of the invention is as follows:
the electrically-controlled solid propellant containing the metal fuel comprises the following components in percentage by mass, calculated by taking the total mass of the electrically-controlled solid propellant as 100 percent:
main adhesive: 9 to 15 percent of water-soluble hydroxyl-containing polymer;
a main oxidant: 63 to 75 percent of hydroxylamine nitrate HAN
Secondary oxidant: 0 to 6 percent
Metal fuel: 1 to 20 percent
A crosslinking agent: 0.5 to 2 percent
Plasticizer: 0.5 to 2 percent
Bonding agent: 0 to 1 percent
Auxiliary adhesive agent: 0 to 2 percent of
A stabilizer: 0 to 1 percent
The main adhesive is one or a mixture of polyvinyl alcohol PVA and polyethylene oxide PEO, and the molecular weight is 70000-100000;
the main oxidant is hydroxylamine nitrate HAN;
the secondary oxidant is ammonium nitrate AN and sodium nitrate NaNO3Potassium nitrate KNO3One or a mixture of two or more of them;
the metal fuel is aluminum powder Al, boron powder B, silicon powder Si, magnesium powder Mg or tungsten powder W, and the metal fuel is coated and modified, and the particle size is 1-30 mu m;
the cross-linking agent is a borate compound (glycerol borate GYB, diethylene glycol borate EYB and the like) capable of being slowly hydrolyzed;
the plasticizer is one or a mixture of more than two of silicone oil SiY, glycerol GY and polyethylene glycol PEG;
the bonding agent is one or a mixture of more than two of silane coupling agents (KH560, KH570 and the like) or alcohol amine bonding agents (diethanolamine DEA, triethanolamine TEA and the like);
the auxiliary adhesive is one or a mixture of more than two of methyl hydroxyethyl cellulose MHEC, cyclodextrin beta-CD and polyvinylpyrrolidone PVP, and the mass ratio of the auxiliary adhesive to the main adhesive is 0.1-0.2: 1;
the stabilizer is bipyridine Bpy or ethylene diamine tetraacetic acid EDTA;
the preferred scheme of the electric control solid propellant is as follows:
main binder PVA: 9 percent;
main oxidant HAN: 66 percent;
secondary oxidant AN: 3 percent;
metal fuel Al: 18 percent;
crosslinking agent GYB: 1 percent;
plasticizer PEG: 1 percent;
bonding agent TEA: 0.5%%;
auxiliary binder MHEC: 1 percent;
stabilizer Bpy: 0.5 percent.
A method of making an electrically controlled solid propellant, the method comprising the steps of:
(1) adding a secondary oxidant and a stabilizer into a main oxidant solution, stirring, and uniformly mixing to obtain a mixed oxidant solution;
(2) adding a main adhesive into the mixed oxidant solution obtained in the step (1), and heating and stirring the mixed oxidant solution under a vacuum condition for dissolving and removing bubbles and completely dissolving the main adhesive to obtain a mixed solution; the heating temperature is 45-55 ℃;
(3) adding metal fuel into the mixed solution obtained in the step (2), and stirring to fully disperse the metal fuel in the adhesive matrix;
(4) adding a bonding agent, a cross-linking agent, a plasticizer and an auxiliary adhesive into the solution obtained in the step (3), and stirring at room temperature under a vacuum condition to obtain uniform slurry;
(5) and (4) pouring the medicinal slurry obtained in the step (4) into a mould, freezing and solidifying at low temperature, repeatedly freezing and unfreezing for more than 3 times, and solidifying and forming to obtain the electric control solid propellant.
In the step (4), the low-temperature freezing temperature is-20 ℃ to-45 ℃, and the curing time is 72-120 h.
In the step (3), before adding the metal fuel, pre-coating treatment is carried out on the metal fuel, wherein the pre-coating comprises inorganic matter coating and organic matter coating;
inorganic matter coating: mixing metal fuel, ethanol, water and ammonia water, adding TEOS solution after uniform mixing for reaction at the reaction temperature of 30-40 ℃ for 3-4h, and repeatedly washing the product with ethanol for not less than three times after the reaction is finished to obtain the coated metal fuel;
the mass ratio of the metal fuel, ethanol, water, ammonia water and TEOS solution is 1: 20-25: 1-2: 1-3: 4-6, directly adopting a commercial analytical reagent for TEOS solution;
organic matter coating: adding acrylonitrile and acrylic ester into an organic solvent according to a certain proportion, adding AIBN serving as an initiator, uniformly stirring, adding metal fuel, stirring at 60 ℃ to obtain a suspension, washing the suspension, and drying to obtain the completely-coated metal fuel. Mixing acrylonitrile, acrylic ester, an organic solvent, an initiator and a metal fuel in a mass ratio of 1-2: 1-2: 100-200: 0.1-0.5: 10, the organic solvent is toluene.
Compared with the prior art, the invention has the following beneficial effects:
(1) the metal fuel is introduced into the formula of the electric control solid propellant, so that the combustion temperature of the propellant can be obviously improved, and the energy performance of the propellant is improved;
(2) the invention adopts inorganic substance or organic polymer to carry out pre-coating pretreatment on the metal fuel, thereby not only isolating the direct contact between the metal fuel and the liquid oxidant, improving the intrinsic safety, but also avoiding possible reaction pores in the preparation and storage processes and improving the compactness of the propellant;
(3) according to the invention, the borate compound capable of being slowly hydrolyzed is used as the cross-linking agent, so that the problems of over-fast local cross-linking reaction and uneven reaction caused by using boric acid or borax as the cross-linking agent are avoided, and the uniformity of the medicine slurry is improved;
(4) the invention increases the crosslinking density of the propellant and the mutual bonding force among all the components by the synergistic action of the crosslinking agent and the bonding agent, so that a more compact crosslinking network is formed in the propellant system;
(5) the invention adopts a small amount of bipyridyl Bpy and ethylene diamine tetraacetic acid EDTA as stabilizers for complexing metal ions in a high-concentration liquid oxidizer and improving the stabilizers of the liquid oxidizer, thereby improving the stability of the solid propellant;
(6) the invention adopts the liquid organic matter with good compatibility with the liquid oxidant and the polyvinyl alcohol as the plasticizer, thus obviously improving the fluidity of the slurry;
(7) the propellant can obviously improve the energy performance of the electric control solid propellant, the theoretical specific impulse can reach 250s, and the safety performance of the propellant meets the requirement of 1.3 levels of danger level.
(8) The invention relates to a high-energy electric control solid propellant containing metal fuel, which comprises the following components in percentage by mass: main adhesive: 9% -15%; a main oxidant: 63% -75%; secondary oxidant: 0% -6%; metal fuel: 1% -20%, cross-linking agent: 0.5% -2%, plasticizer: 0.5 to 2 percent; bonding agent: 0% -1%; auxiliary adhesive agent: 0% -2%; a stabilizer: 0 to 1 percent. Wherein the binder is one or a combination of polyvinyl alcohol PVA or polyethylene oxide PEO; the main oxidant is hydroxylamine nitrate HAN; the secondary oxidant is ammonium nitrate AN and sodium nitrate NaNO3Potassium nitrate KNO3One or a combination of; the metal fuel is aluminum powder Al, boron powder B, silicon powder Si, magnesium powder Mg or tungsten powder W and the like; the cross-linking agent is a borate compound which can be slowly hydrolyzed;the plasticizer is one or a combination of silicone oil, glycerol or polyethylene glycol (PEG); the bonding agent is one or a combination of a silane coupling agent or an alcohol amine bonding agent; the auxiliary binder is one or a combination of methyl hydroxyethyl cellulose MHEC, cyclodextrin beta-CD and polyvinylpyrrolidone PVP; the stabilizer is bipyridine Bpy, ethylene diamine tetraacetic acid EDTA, etc. The propellant can obviously improve the energy performance of the electric control solid propellant, meets the requirement of 1.3 level of danger level, and is suitable for the propellant for attitude and orbit control with higher requirement on the energy performance of the propellant.
Detailed Description
The present invention will be described in further detail with reference to specific examples, but is not limited thereto.
Example 1
The propellant comprises the following components:
propellant theoretical specific impulse 252s, propellant density: 1.71g/cm3Normal temperature tensile strength: 0.81MPa, maximum elongation: 156.1 percent (the mechanical property test refers to GJB 770B-2005 gunpowder test method), and the safety performance meets the requirement of the danger level of 1.3 (the safety property test refers to GJB 6195-.
Example 2
The propellant comprises the following components:
| formulation composition | Content/% wt |
| PVA | 10 |
| HAN | 64 |
| AN | 4 |
| B | 18 |
| EYB | 1 |
| PEG | 1.5 |
| DEA | 0.5 |
| β-CD | 0.5 |
| EDTA | 0.5 |
Propellant theoretical specific impulse 249s, propellant density: 1.66g/cm3Normal temperature tensile strength: 0.85MPa, maximum elongation: 155.2 percent (the mechanical property test refers to GJB 770B-2005 gunpowder test method), and the safety performance meets the requirement of the danger level of 1.3 (the safety property test refers to GJB 6195-.
Example 3
The propellant comprises the following components:
propellant theoretical specific impulse 247s, propellant density: 1.58g/cm3Normal temperature tensile strength: 0.78MPa, maximum elongation: 158.5% (the mechanical property test refers to GJB 770B-2005 gunpowder test method), and the safety performance meets the requirement of the danger level of 1.3 (the safety property test refers to GJB 6195-.
Example 4
The propellant comprises the following components:
| formulation composition | Content/% wt |
| PVA | 9.5 |
| HAN | 65 |
| AN | 4 |
| Si | 18 |
| EYB | 1 |
| PEG | 1 |
| TEA | 0.5 |
| PVP | 0.5 |
| Bpy | 0.5 |
Propellant theoretical specific impulse 248s, propellant density: 1.66g/cm3Normal temperature tensile strength: 0.73MPa, maximum elongation: 157.2% (the mechanical property test refers to GJB 770B-2005 gunpowder test method), and the safety performance meets the requirement of the danger level of 1.3 (the safety property test refers to GJB 6195-.
Example 5
The propellant comprises the following components:
propellant theoretical specific impulse 245s, propellant density: 1.62g/cm3Normal temperature tensile strength: 0.86MPa, maximum elongation: 145.3% (the mechanical property test refers to GJB 770B-2005 gunpowder test method), and the safety performance meets the requirement of the danger level of 1.3 (the safety property test refers to GJB 6195-.
Example 6
The propellant comprises the following components:
| formulation composition | Content/% wt |
| PEO | 11 |
| HAN | 73 |
| AN | 2 |
| B | 10 |
| GYB | 0.5 |
| PEG | 1 |
| DEA | 1 |
| β-CD | 1 |
| Bpy | 0.5 |
Propellant theoretical specific impulse 242s, propellant density: 1.60g/cm3Normal temperature tensile strength: 0.88MPa, maximum elongation: 143.6% (the mechanical property test refers to GJB 770B-2005 gunpowder test method), the safety performance meets the requirement of the danger level of 1.3 (the safety property test refers to GJB 6195-.
Example 7
The propellant comprises the following components:
propellant theoretical specific impulse 242s, propellant density: 1.56g/cm3Normal temperature tensile strength: 0.83MPa, maximum elongation: 147.3% (the mechanical property test refers to GJB 770B-2005 gunpowder test method), the safety performance meets the requirement of the danger level of 1.3 (the safety property test refers to GJB 6195-.
Example 8
The propellant comprises the following components:
| formulation composition | Content/% wt |
| PVA | 15 |
| HAN | 69 |
| AN | 4 |
| Al | 5 |
| EYB | 1.5 |
| PEG | 2 |
| TEA | 1 |
| PVP | 1.5 |
| EDTA | 1 |
Propellant theoretical specific impulse 235s, propellant density: 1.57g/cm3Normal temperature tensile strength: 0.93MPa, maximum elongation: 132.5% (the mechanical property test refers to GJB 770B-2005 gunpowder test method), and the safety performance meets the requirement of the danger level of 1.3 (the safety property test refers to GJB 6195-.
Example 9
The propellant comprises the following components:
| formulation composition | Content/% wt |
| PEO | 15 |
| HAN | 71 |
| NaNO3 | 5 |
| B | 5 |
| GYB | 1 |
| SiY | 1 |
| TEA | 0.5 |
| PVP | 1 |
| Bpy | 0.5 |
Propellant theoretical specific impulse 234s, propellant density: 1.55g/cm3Normal temperature tensile strength: 0.98MPa, maximum elongation: 135.5 percent (the mechanical property test refers to GJB 770B-2005 gunpowder test method), and the safety performance meets the requirement of the danger level of 1.3 (the safety property test refers to GJB 6195-.
Example 10
The propellant comprises the following components:
| formulation composition | Content/% wt |
| PVA | 14 |
| HAN | 70 |
| AN | 6 |
| Si | 5 |
| EYB | 1.5 |
| SiY | 1 |
| DEA | 1.5 |
| Bpy | 1 |
Propellant theoretical specific impulse 232s, propellant density: 1.55g/cm3Normal temperature tensile strength: 0.95MPa, maximum elongation: 130.2% (the mechanical property test refers to GJB 770B-2005 gunpowder test method), and the safety performance meets the requirement of the danger level of 1.3 (the safety property test refers to GJB 6195-.
The formula is only the specific embodiment listed in the invention, and the electrically-controlled solid propellant can be obtained by the preparation method provided by the invention. The scope of the present invention is not limited thereto, and any changes or substitutions that can be easily made by those skilled in the art within the technical scope of the present invention will be covered by the present invention.
Claims (1)
1. An electrically controlled solid propellant containing a metal fuel, characterized by:
the total mass of the electric control solid propellant is 100%, and the components of the electric control solid propellant and the mass percentage of each component are as follows:
main binder PVA: 9 percent;
main oxidant HAN: 66 percent;
secondary oxidant AN: 3 percent;
metal fuel Al: 18 percent;
crosslinking agent GYB: 1 percent;
plasticizer PEG: 1 percent;
bonding agent TEA: 0.5 percent;
auxiliary binder MHEC: 1 percent;
stabilizer Bpy: 0.5 percent;
the molecular weight of the main adhesive is 70000-100000, the metal fuel is subjected to coating modification treatment before use, the particle size is 1-30 mu m, and the coating modification treatment is inorganic matter coating or organic matter coating;
the method for coating the inorganic substance comprises the following steps: mixing metal fuel, ethanol, water and ammonia water, adding TEOS solution after uniform mixing for reaction at the reaction temperature of 30-40 ℃ for 3-4h, and repeatedly washing the product with ethanol for not less than three times after the reaction is finished to obtain the coated metal fuel;
the mass ratio of the metal fuel, ethanol, water, ammonia water and TEOS solution is 1: 20-25: 1-2: 1-3: 4-6;
the organic matter coating method comprises the following steps: adding acrylonitrile and acrylic ester into an organic solvent, adding AIBN serving as an initiator, uniformly stirring, adding metal fuel, stirring to obtain a suspension, washing the suspension, and drying to obtain the completely-coated metal fuel, wherein the mass ratio of the acrylonitrile to the acrylic ester to the organic solvent to the initiator to the metal fuel is 1-2: 1-2: 100-200: 0.1-0.5: 10, the organic solvent is toluene;
the preparation method of the electric control solid propellant comprises the following steps:
(1) adding a secondary oxidant and a stabilizer into a main oxidant solution, stirring, and uniformly mixing to obtain a mixed oxidant solution;
(2) adding a main adhesive into the mixed oxidant solution obtained in the step (1), and heating and stirring the mixed oxidant solution under a vacuum condition for dissolving and removing bubbles and completely dissolving the main adhesive to obtain a mixed solution; the heating temperature is 45-55 ℃;
(3) adding metal fuel into the mixed solution obtained in the step (2), and stirring to fully disperse the metal fuel in the adhesive matrix;
(4) adding a bonding agent, a cross-linking agent, a plasticizer and an auxiliary adhesive into the solution obtained in the step (3), and stirring at room temperature under a vacuum condition to obtain uniform slurry;
(5) pouring the medicinal slurry obtained in the step (4) into a mould, freezing and solidifying at low temperature, repeatedly freezing and unfreezing for more than 3 times, and solidifying and forming to obtain the electric control solid propellant;
in the step (4), the low-temperature freezing temperature is-20 ℃ to-45 ℃, and the curing time is 72-120 h;
in the step (3), before adding the metal fuel, pre-coating the metal fuel, wherein the pre-coating method is inorganic matter coating or organic matter coating;
the inorganic substance coating method comprises the following steps: mixing metal fuel, ethanol, water and ammonia water, adding TEOS solution after uniform mixing for reaction at the reaction temperature of 30-40 ℃ for 3-4h, and repeatedly washing the product with ethanol for not less than three times after the reaction is finished to obtain the coated metal fuel;
the mass ratio of the metal fuel, ethanol, water, ammonia water and TEOS solution is 1: 20-25: 1-2: 1-3: 4-6;
the organic matter coating method comprises the following steps: adding acrylonitrile and acrylic ester into an organic solvent according to a certain proportion, adding AIBN serving as an initiator, uniformly stirring, adding metal fuel, stirring at 60 ℃ to obtain a suspension, washing the suspension, and drying to obtain the completely-coated metal fuel; acrylonitrile, acrylic ester, an organic solvent, an initiator and a metal fuel ratio of 1-2: 1-2: 100-200: 0.1-0.5: 10, the organic solvent is toluene.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910223087.1A CN109851457B (en) | 2019-03-22 | 2019-03-22 | Electrically-controlled solid propellant containing metal fuel and preparation method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910223087.1A CN109851457B (en) | 2019-03-22 | 2019-03-22 | Electrically-controlled solid propellant containing metal fuel and preparation method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109851457A CN109851457A (en) | 2019-06-07 |
| CN109851457B true CN109851457B (en) | 2021-10-01 |
Family
ID=66901516
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910223087.1A Active CN109851457B (en) | 2019-03-22 | 2019-03-22 | Electrically-controlled solid propellant containing metal fuel and preparation method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109851457B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111892466A (en) * | 2020-07-24 | 2020-11-06 | 北京理工大学 | High-density high-energy metal fuel |
| CN112299933A (en) * | 2020-10-31 | 2021-02-02 | 西北工业大学 | Polyoxyethylene group ion conductive propellant and preparation method thereof |
| CN114195605B (en) * | 2021-12-23 | 2022-10-11 | 中国人民解放军国防科技大学 | Hydrogen peroxide gel propellant containing metal fuel and preparation method thereof |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108070044A (en) * | 2018-02-05 | 2018-05-25 | 中国科学院长春应用化学研究所 | A kind of gel rubber material and preparation method thereof |
| CN108341948A (en) * | 2017-01-25 | 2018-07-31 | 翁秋梅 | A kind of hybrid cross-linked dynamic aggregation object and its application |
| CN108610486A (en) * | 2017-01-25 | 2018-10-02 | 翁秋梅 | A kind of energy-absorbing method based on the hybrid cross-linked dynamic aggregation object of combination |
Family Cites Families (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101580653B (en) * | 2009-06-10 | 2012-05-09 | 华南理工大学 | Organic-inorganic hybrid nanometer film coating aluminum powder pigment and preparation method and application thereof |
| CN102516831A (en) * | 2011-11-25 | 2012-06-27 | 中山大学 | Preparation method for organic/inorganic hybridization cladding aluminum composite particle |
| CN102827496A (en) * | 2012-09-17 | 2012-12-19 | 张家港楚人新材料科技有限公司 | Method for packaging and modifying surface of substance |
| US9182207B2 (en) * | 2012-10-24 | 2015-11-10 | Digital Solid State Propulsion, Inc. | Liquid electrically initiated and controlled gas generator composition |
| CN105175332A (en) * | 2014-05-30 | 2015-12-23 | 湖北航天化学技术研究所 | Stabilizer for hydroxylamine nitrate |
| CN105355879B (en) * | 2015-11-11 | 2019-07-02 | 兰州理工大学 | Composite carbon coated metal oxide and preparation method thereof |
| CN106365935A (en) * | 2016-08-26 | 2017-02-01 | 湖北航天化学技术研究所 | High-strength electric-control solid propellant |
| CN106478323A (en) * | 2016-10-21 | 2017-03-08 | 重庆大学 | Automatically controlled solid propellant of a kind of high-performance and preparation method thereof |
| CN106495972A (en) * | 2016-10-21 | 2017-03-15 | 重庆大学 | A kind of electric ignition solid propellant of fuel-rich containing aluminum and preparation method thereof |
| CN106905091B (en) * | 2017-03-15 | 2019-05-07 | 重庆大学 | It is a kind of based on perchlorate can automatically controlled burning solid propellant and preparation method thereof |
| CN108358733B (en) * | 2018-03-14 | 2020-07-03 | 安徽理工大学 | Method for coating energetic additive by thermal expansion hollow microspheres |
-
2019
- 2019-03-22 CN CN201910223087.1A patent/CN109851457B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108341948A (en) * | 2017-01-25 | 2018-07-31 | 翁秋梅 | A kind of hybrid cross-linked dynamic aggregation object and its application |
| CN108610486A (en) * | 2017-01-25 | 2018-10-02 | 翁秋梅 | A kind of energy-absorbing method based on the hybrid cross-linked dynamic aggregation object of combination |
| CN108070044A (en) * | 2018-02-05 | 2018-05-25 | 中国科学院长春应用化学研究所 | A kind of gel rubber material and preparation method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109851457A (en) | 2019-06-07 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109851457B (en) | Electrically-controlled solid propellant containing metal fuel and preparation method thereof | |
| US4019933A (en) | Pot life extension of isocyanate cured propellants by aziridine compounds | |
| CN108456558B (en) | Nano energy storage fuel and preparation method thereof | |
| CN110776384A (en) | Polymer and nano aluminum powder compounded microsphere | |
| CN105130720A (en) | Propellant with high energy and low temperature sensitive coefficient of burning | |
| CN109305869B (en) | Carborane propellant and preparation method thereof | |
| CN109574773B (en) | Boron-containing fuel-rich propellant | |
| CN108129248B (en) | Method for solving post-curing problem of room-temperature cured butyl hydroxyl propellant and prepared product | |
| CN113248340B (en) | High-pressure-strength-index low-combustion-temperature gas generating agent and preparation method thereof | |
| CN111036302B (en) | Graphene-ferric gallate combustion catalyst and synthesis method thereof | |
| CN107641066A (en) | A kind of solid rocket propellant and preparation method | |
| CN110054537B (en) | Electric control solid propellant and preparation method thereof | |
| CN111054440B (en) | Graphene-ferrocene compound for solid propellant and synthetic method thereof | |
| JP6431181B2 (en) | Binder for nitrogen-containing oxidants | |
| CN110759800A (en) | High-energy high-mechanical-property electronic control solid propellant | |
| CN114539009A (en) | Preparation method of high-stability high-compatibility modified aluminum-lithium alloy powder | |
| CN111138236B (en) | 1,2, 4-triazole nitrate coated boron-magnesium composite metal powder fuel and preparation method thereof | |
| CN113563142A (en) | High-molecular fluorine-rich oxidant-based aluminothermic high-explosive-heat industrial explosive and preparation method thereof | |
| CN116041124B (en) | Poly (hydroxyethyl acrylate) nitrate modified CL-20-based composite material, preparation method and application | |
| CN116082102B (en) | Ammonium nitrate-based ternary composite electric control solid propellant and preparation method thereof | |
| US9505666B2 (en) | Methods to desensitize hydrazinium nitroformate (HNF) | |
| CN118026788A (en) | Boron-containing fuel-rich propellant and preparation method thereof | |
| CN113582791A (en) | Sensitized fluorine-rich oxidant-based industrial explosive and preparation method thereof | |
| CN118459293A (en) | Power-variable ammunition capable of realizing controllable kinetic energy based on voltage and preparation method thereof | |
| CN115466155A (en) | LLM-105/AP energetic composite material and preparation method thereof |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |