CN108727146A - A kind of fuel-rich propellant of boracic based composite metal powder - Google Patents
A kind of fuel-rich propellant of boracic based composite metal powder Download PDFInfo
- Publication number
- CN108727146A CN108727146A CN201810606163.2A CN201810606163A CN108727146A CN 108727146 A CN108727146 A CN 108727146A CN 201810606163 A CN201810606163 A CN 201810606163A CN 108727146 A CN108727146 A CN 108727146A
- Authority
- CN
- China
- Prior art keywords
- fuel
- boron
- metal powder
- composite metal
- boryl
- 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.)
- Pending
Links
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
- C06B23/00—Compositions characterised by non-explosive or non-thermic constituents
-
- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- 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
- C06B33/06—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 an inorganic oxygen-halogen salt
-
- 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
- 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
- C06B33/14—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 at least one being an inorganic nitrogen-oxygen salt
Landscapes
- Chemical & Material Sciences (AREA)
- Organic Chemistry (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Inorganic Chemistry (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Combustion & Propulsion (AREA)
- Solid Fuels And Fuel-Associated Substances (AREA)
Abstract
The present invention relates to a kind of fuel-rich propellants of boracic based composite metal powder, include the component of following quality proportioning：Fuel：30%~50%；Oxidant：25%~40%；Adhesive：15%~25%；Properties modifier：3%~10%, the fuel includes the boryl composite metal powder of coreshell type structure.The present invention is introduced by regarding the boryl composite metal powder of nucleocapsid as high-energy fuel in fuel-rich propellant formula, it is high to solve boron powder firing temperature, the low problem of efficiency of combustion, the combustibility and energy characteristics of fuel-rich propellant can not only be improved, processing performance can also be improved, punching engine can be solved to high-performance fuel-rich propellant needs of problems, had a extensive future.
Description
Technical field
The present invention relates to fuel-rich propellant fields, and in particular to a kind of fuel-rich propulsion of boracic based composite metal powder
Agent.
Background technology
Solid rocket ramjet organically combines the advantages of solid propellant rocket and airbreathing motor.With it is solid
Body rocket engine is compared, and due to making oxidant using the oxygen in air, the energy of propellant is greatly improved, specific impulse is
2~4 times of solid propellant rocket；Compared with airbreathing motor, due to being retracted gas principle using inner mold face pressure, rotation is omitted
The labyrinths such as rotation member, engine structure are simplified.Therefore, using Ducted rocket as the guided missile of power have it is small,
The characteristics of light-weight, far firing range, may be implemented whole dynamic flight, enhance the penetration ability and latter end attacking ability of guided missile.
Solid rocket ramjet uses solid fuel-rich propellant as power source, wherein fuel content reach 30~
50%, thus fuel performance be determine the key factor that can give full play to of the potential excellent properties of solid rocket ramjet it
One, boron-based fuel-rich has very high calorific value, is the preferred propellant of Ducted rocket.But due to boron powder itself
Firing temperature it is higher (1900K), and the very strong boron oxide compound (B of viscosity is generated in boron powder combustion process2O3) it is covered in boron powder table
Face so that boron powder ignition difficulties are difficult to fully burn, and influence its practical application in fuel-rich propellant.
Invention content
To solve the above-mentioned problems in the prior art, containing boryl for punching engine the present invention provides a kind of
The fuel-rich propellant of composite metal powder, the propellant compositions substitute part metals fuel with boryl composite metal powder, solve
Boron powder firing temperature is high, and the low problem of efficiency of combustion can meet advanced Ramjet Missile to high-performance fuel-rich propellant
Demand improves the processing performance and combustibility of propellant under the premise of not influencing propellant comprehensive performance.
The present invention relates to following technical solutions：
A kind of fuel-rich propellant of boracic based composite metal powder, includes the component of following quality proportioning：
Fuel：30%~50%；
Oxidant：25%~40%；
Adhesive：15%~25%；
Properties modifier：3%~10%,
The fuel includes boryl composite metal powder, the complex method of the boryl composite metal powder be using boron as core,
For metal using fusing point less than boron as surface layer, low-melting-point metal is covered in the surface of boron, forms the compound gold of boryl of coreshell type structure
Belong to powder.
Preferably, the grain size of the boryl composite metal powder is one kind or group in 0.2~1 μm, 1~4 μm, 4~10 μm
It closes.
Preferably, the content of boron is not less than 70% (wt%) in the boryl composite metal powder.
Preferably, the fusing point is aluminium powder, magnesium powder, one kind in titanium valve or combination less than the metal of boron.
Preferably, the fusing point is 600~1800 DEG C less than the melting point metal of boron, and will not be formed in combustion viscous
The low-melting-point metal of thick shape oxide so that the igniting of boron powder is easy, fully burns.
Preferably, the fuel further includes boron, magnesium, aluminium, titanium, boron carbide (B4C one kind in) or combination.
Preferably, the oxidant is ammonium perchlorate, potassium hyperchlorate, ammonium nitrate, potassium nitrate, octogen, hexogen, three
One kind in aminoguanidine nitrate or combination.
Preferably, the properties modifier is triphenyl bismuth, methyl stearate, lecithin, isodecyl pelargonate, adipic acid two
Pungent fat, citrate, Plexol 201, three [1- (2- methyl) '-aziridino] phosphine oxides, boron trifluoride-triethanolamine, oxygen
Change that iron, octyl ferrocene, Kato be pungent, N, N- diphenyl-para-phenylene diamines, N- phenyl-2-naphthylamines, N- phenyl-N- cyclohexyls are to benzene
One kind in diamines, lithium fluoride or combination.
Compared with prior art, the beneficial effects of the invention are as follows：
1, using boron as core, for the metal using fusing point less than boron powder as surface layer, low-melting-point metal is covered in boron powder surface, is formed
Hud typed boryl metal composite powder solves boron powder ignition difficulties while keeping boron powder high heating value, and efficiency of combustion is low to ask
Topic.
2, the related component in fuel-rich propellant is replaced with boryl composite metal powder, can not only improves combustibility and energy
Measure performance, moreover it is possible to improve processing performance, punching engine can be solved to high-performance fuel-rich propellant needs of problems.
Specific implementation mode
In order to which technical characteristic, purpose and the advantageous effect to the present invention are more clearly understood, in conjunction with specific example
Technical scheme of the present invention is carried out it is described further below, techniques not described means of the present invention by usual manner in the art into
Row, it should be understood that these examples are only for illustrating the present invention and are not intended to limit the scope of the present invention.
A kind of fuel-rich propellant of boracic based composite metal powder, includes the component of following quality proportioning：
Fuel：30%~50%；
Oxidant：25%~40%；
Adhesive：15%~25%；
Properties modifier：3%~10%.
End value in above-mentioned each component content is the limit content of the component, in propellant design process, certain component
Content cannot be below its minimum, can not be higher than its peak, otherwise can seriously affect the performance of propellant.When each component contains
Amount less than its minimum when, under normal circumstances all can not normal ignition, propellant also can not self-sustaining burning；When each component content is high
When its peak, combustibility is fine, but fuel content must reduce, and energy characteristics cannot be satisfied punching engine use
It is required that；Even if when each component content is equal to its minimum or peak, propellant normal ignition and self-sustaining burning is realized
When minimum amount or highest dosage, other performances of propellant are equally very poor under this condition, cannot be satisfied requirement.
The fuel includes boryl composite metal powder, the complex method of the boryl composite metal powder be using boron as core,
For metal using fusing point less than boron as surface layer, low-melting-point metal is covered in the surface of boron, forms the compound gold of boryl of coreshell type structure
Belong to powder.Many characteristics such as boryl composite metal powder combines the high heating value of B, and the metal on surface layer is readily burned, compare current high energy
Common amorphous boron powder in fuel-rich propellant, the powder body material have lower firing temperature, higher oxidation activity, more
High efficiency of combustion and with the good compatibility of fourth hydroxyl adhesive.
Wherein, in the boryl composite metal powder based on boron, the content of boron is not less than 70%, in combustion,
The inflammable metal of outer layer lights offer heat source first, lights part of boron, and provide heat source for second-time burning, so its content is not required to
It is too high.The mass fraction of the inflammable metal of outer layer is the conclusion obtained by a large number of experiments not above 30%, first, inflammable
The calorific value of metal powder is not high, and content is too high to reduce propellant heat value, secondly, solidifying after the too high burning of combustible metal powder content
Rephasing will be more, can equally influence the combustibility of propellant.Engine test is the results show that when combustible metal powder content exists
When 28% or so, unburned complete free state combustible metal will be contained in combustion residue, and the effect of combustible metal is only
It is to improve ignition performance and provide heat source, after the completion of primary combustion, combustible metal just completes its mission, if inflammable gold
Belong to no completely burned, propellant energy can be substantially reduced by further participating in second-time burning.Therefore, when the quality of the metal on surface layer
When score is not above 30%, it can learn that the content of boron in boryl composite metal powder is not less than 70%.
The fusing point is 600~1800 DEG C less than the melting point metal of boron, and will not form thick oxygen in combustion
The low-melting-point metal of compound can be aluminium powder, magnesium powder, one kind in titanium valve or combination.Have by the coating metal of representative of magnesium
Excellent igniting and combustibility, but its calorific value is relatively low, and magnesium is introduced in propellant formulation can improve combustibility, but can be notable
Reduce the quality calorific value of propellant.In order to improve the ignition performance of propellant and improve primary combustion temperature, by the boron with high heating value
It is carried out with magnesium, aluminium and/or titanium with excellent ignition performance compound, prepares hud typed hybrid fuel, it is this hud typed
For hybrid fuel using the boron of high heating value as core, magnesium, aluminium and/or titanium with excellent ignition performance cover its surface, are formed hud typed
Hybrid fuel.
The grain size of the boryl composite metal powder is one kind or combination in 0.2~1 μm, 1~4 μm, 4~10 μm.
The fuel further includes one kind or combination in boron, magnesium, aluminium, titanium, boron carbide.
The oxidant is ammonium perchlorate (AP), potassium hyperchlorate (KP), ammonium nitrate (AN), potassium nitrate (KN), octogen
(HMX), hexogen (RDX), one kind in triaminoguanidinium nitrate (TAGN) or combination.
The properties modifier is that triphenyl bismuth (TPB), methyl stearate, lecithin, isodecyl pelargonate, adipic acid two are pungent
Fat (DOA), citrate, Plexol 201 (DOS), three [1- (2- methyl) '-aziridino] phosphine oxides (MAPO), trifluoro
Change that boron triethanolamine, iron oxide, octyl ferrocene, Kato be pungent, N, N- diphenyl-para-phenylene diamines, N- phenyl-2-naphthylamines, N- benzene
Base-N- cyclohexyls p-phenylenediamine, one kind in lithium fluoride or combination.
Described adhesive is HTPB+ isocyanate systems, isocyanates IPDI, TDI, N-100, HMDI etc..
Embodiment 1
Boryl composite metal powder forms：Boron content 95%, content of magnesium 5%.
(1) propellant formulation forms
(2) performance of propellant
From embodiment 1 it is known that actual measurement calorific value=32.3MJkg-1, efficiency of combustion=90.8%, the performance of propellant is excellent
It is good.
Embodiment 2
Boryl composite metal powder forms：Boron content 90%, content of magnesium 10%.
(1) propellant formulation forms
(2) performance of propellant
From embodiment 2 it is known that actual measurement calorific value=31.7MJkg-1, efficiency of combustion=90.9%, the performance of propellant is excellent
It is good.
Embodiment 3
Boryl composite metal powder forms：Boron content 85%, content of magnesium 15%.
(1) propellant formulation forms
(2) performance of propellant
From embodiment 3 it is known that actual measurement calorific value=33.6MJkg-1, efficiency of combustion=90.8%, the performance of propellant is excellent
It is good.
Embodiment 4
Boryl composite metal powder forms：Boron content 80%, aluminium content 20%.
(1) propellant formulation forms
(2) performance of propellant
From embodiment 4 it is known that actual measurement calorific value=33.2MJkg-1, efficiency of combustion=91.5%, the performance of propellant is excellent
It is good.
Embodiment 5
Boryl composite metal powder forms：Boron content 75%, aluminium content 25%.
(1) propellant formulation forms
(2) performance of propellant
From embodiment 5 it is known that actual measurement calorific value=33.9MJkg-1, efficiency of combustion=91.2%, the performance of propellant is excellent
It is good.
Embodiment 6
Boryl composite metal powder forms：Boron content 70%, Ti content 30%.
(1) propellant formulation forms
(2) performance of propellant
From embodiment 6 it is known that actual measurement calorific value=34.7MJkg-1, efficiency of combustion=91.8%, the performance of propellant is excellent
It is good.
Embodiment 7
Boryl composite metal powder forms：Boron content 90%, content of magnesium 10%.
(1) propellant formulation forms
(2) performance of propellant
From embodiment 7 it is known that actual measurement calorific value=35.9MJkg1, efficiency of combustion=90.5%, the performance of propellant is excellent
It is good.
Above-described embodiment 1-7, the propellant actual measurement calorific value for being added to boryl composite metal powder is all higher, and efficiency of combustion all exists
90% or more, combustibility and energy characteristics are improved, improves processing performance, punching engine can be solved, high-performance fuel-rich is pushed away
Into agent needs of problems.
Comparative Examples
(1) propellant formulation forms
(2) performance of propellant
Formula actual measurement calorific value without boryl composite metal powder is relatively low, and efficiency of combustion is all 70% or so, the performance of propellant
Difference.
The study found that boryl composition metal fuel can significantly reduce boron firing temperature, combustion efficiency of boron powder and propulsion are improved
Agent burn rate further increases the energy level of boron-propellant, improves the comprehensive performance of boron-based fuel-rich.
Replace the metal fuel in fuel-rich propellant with boryl composite metal powder, can not only improve combustibility, improves
Energy characteristics, moreover it is possible to improve processing performance, advanced tactical missile power plant punching engine can be solved to high-performance fuel-rich
The needs of problems of propellant, has a extensive future.
Finally it should be noted that：The above embodiments are only used to illustrate the technical solution of the present invention., rather than its limitations；To the greatest extent
Present invention has been described in detail with reference to the aforementioned embodiments for pipe, it will be understood by those of ordinary skill in the art that：Its according to
So can with technical scheme described in the above embodiments is modified, either to which part or all technical features into
Row equivalent replacement；And these modifications or replacements, various embodiments of the present invention technology that it does not separate the essence of the corresponding technical solution
The range of scheme should all cover in the claim of the present invention and the range of specification.
Claims (8)
1. a kind of fuel-rich propellant of boracic based composite metal powder, it is characterised in that include the component of following quality proportioning：
Fuel：30%~50%；
Oxidant：25%~40%；
Adhesive：15%~25%；
Properties modifier：3%~10%,
The fuel includes boryl composite metal powder, and the complex method of the boryl composite metal powder is using boron as core, with molten
Point is surface layer less than the metal of boron, and low-melting-point metal is covered in the surface of boron, forms the boryl composite metal powder of coreshell type structure.
2. fuel-rich propellant according to claim 1, it is characterised in that：The grain size of the boryl composite metal powder is
One kind in 0.2~1 μm, 1~4 μm, 4~10 μm or combination.
3. fuel-rich propellant according to claim 1, it is characterised in that：The content of boron in the boryl composite metal powder
Not less than 70% (wt%).
4. fuel-rich propellant according to claim 1, it is characterised in that：The fusing point less than boron metal be aluminium powder,
One kind in magnesium powder, titanium valve or combination.
5. fuel-rich propellant according to claim 1, it is characterised in that：The fusing point is less than the melting point metal of boron
600~1800 DEG C.
6. fuel-rich propellant according to claim 1, it is characterised in that：The fuel further includes boron, magnesium, aluminium, titanium, carbon
Change boron (B4C one kind in) or combination.
7. fuel-rich propellant according to claim 1, it is characterised in that：The oxidant is ammonium perchlorate, perchloric acid
One kind in potassium, ammonium nitrate, potassium nitrate, octogen, hexogen, triaminoguanidinium nitrate or combination.
8. fuel-rich propellant according to claim 1, it is characterised in that：The properties modifier is triphenyl bismuth, firmly
Resin acid methyl esters, lecithin, isodecyl pelargonate, adipic acid dibutyl ester, citrate, Plexol 201, three [1- (2- methyl)
'-aziridino] phosphine oxide, boron trifluoride-triethanolamine, iron oxide, octyl ferrocene, Kato be pungent, N, N- diphenyl-para-phenylene diamines,
N- phenyl-2-naphthylamines, N- phenyl-N- cyclohexyls p-phenylenediamine, one kind in lithium fluoride or combination.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810606163.2A CN108727146A (en) | 2018-06-13 | 2018-06-13 | A kind of fuel-rich propellant of boracic based composite metal powder |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810606163.2A CN108727146A (en) | 2018-06-13 | 2018-06-13 | A kind of fuel-rich propellant of boracic based composite metal powder |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108727146A true CN108727146A (en) | 2018-11-02 |
Family
ID=63929321
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810606163.2A Pending CN108727146A (en) | 2018-06-13 | 2018-06-13 | A kind of fuel-rich propellant of boracic based composite metal powder |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108727146A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110981665A (en) * | 2019-12-24 | 2020-04-10 | 湖北航天化学技术研究所 | Boron-containing fuel-rich propellant for platform combustion |
| CN111170816A (en) * | 2020-01-19 | 2020-05-19 | 湖北航天化学技术研究所 | Boron-containing fuel-rich propellant |
| CN111689821A (en) * | 2020-06-23 | 2020-09-22 | 江苏智仁景行新材料研究院有限公司 | Activated boron powder and preparation method thereof |
| CN115124396A (en) * | 2022-06-15 | 2022-09-30 | 西北工业大学 | Magnesium-based metal fuel with high primary combustion efficiency and preparation method and application thereof |
| CN115415536A (en) * | 2022-08-15 | 2022-12-02 | 西安近代化学研究所 | Aluminum-boron micro-nano composite material, preparation method and application thereof |
| CN115925499A (en) * | 2022-12-14 | 2023-04-07 | 南京理工大学 | Green-ray pyrotechnic composition based on high-activity boron powder and preparation method thereof |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8465607B1 (en) * | 2008-09-18 | 2013-06-18 | The United States Of America As Represented By The Secretary Of The Navy | Higher-performance solid-rocket propellants and methods of utilizing them |
| CN104030868A (en) * | 2014-06-03 | 2014-09-10 | 浙江大学 | Solid rocket ramjet boron-loaded solid propellant and application of Bi2O3 |
-
2018
- 2018-06-13 CN CN201810606163.2A patent/CN108727146A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8465607B1 (en) * | 2008-09-18 | 2013-06-18 | The United States Of America As Represented By The Secretary Of The Navy | Higher-performance solid-rocket propellants and methods of utilizing them |
| CN104030868A (en) * | 2014-06-03 | 2014-09-10 | 浙江大学 | Solid rocket ramjet boron-loaded solid propellant and application of Bi2O3 |
Non-Patent Citations (12)
| Title |
|---|
| （美）舒马赫: "《海水腐蚀手册》", 30 April 1985, 国防工业出版社 * |
| K. K. PACE 等: "Effect of magnesium-coated boron particles on burning characteristics of fuels in high-speed crossflows", 《INTERNATIONAL JOURNAL OF ENERGETIC MATERIALS AND CHEMICAL PROPULSION》 * |
| 余永刚 等: "《发射燃烧学》", 31 March 2016, 北京航空航天大学出版社 * |
| 庞爱民: "《高能固体推进剂性能及配方设计专家系统》", 30 June 2014, 国防工业出版社 * |
| 庞维强 等: "《富燃料固体火箭推进剂技术》", 31 August 2016, 西北工业大学出版社 * |
| 张端庆: "《火药用原材料性能与制备》", 31 January 1995, 北京理工大学出版社 * |
| 李疏芬 等: "提高含硼固体燃料燃烧性能的研究", 《推进技术》 * |
| 欧育湘: "《炸药学》", 28 February 2014, 北京理工大学出版社 * |
| 汪勇: "《粮油副产物加工学》", 31 July 2016, 暨南大学出版社 * |
| 游首先 等: "《兵器工业科学技术辞典 火药与炸药》", 31 December 1991, 国防工业出版社 * |
| 王伯羲 等: "《火药燃烧理论》", 31 December 1997, 北京理工大学出版社 * |
| 王泽山: "《含能材料概论》", 31 January 2006, 哈尔滨工业大学出版社 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110981665A (en) * | 2019-12-24 | 2020-04-10 | 湖北航天化学技术研究所 | Boron-containing fuel-rich propellant for platform combustion |
| CN111170816A (en) * | 2020-01-19 | 2020-05-19 | 湖北航天化学技术研究所 | Boron-containing fuel-rich propellant |
| CN111689821A (en) * | 2020-06-23 | 2020-09-22 | 江苏智仁景行新材料研究院有限公司 | Activated boron powder and preparation method thereof |
| CN115124396A (en) * | 2022-06-15 | 2022-09-30 | 西北工业大学 | Magnesium-based metal fuel with high primary combustion efficiency and preparation method and application thereof |
| CN115415536A (en) * | 2022-08-15 | 2022-12-02 | 西安近代化学研究所 | Aluminum-boron micro-nano composite material, preparation method and application thereof |
| CN115925499A (en) * | 2022-12-14 | 2023-04-07 | 南京理工大学 | Green-ray pyrotechnic composition based on high-activity boron powder and preparation method thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108727146A (en) | A kind of fuel-rich propellant of boracic based composite metal powder | |
| CN109305869B (en) | Carborane propellant and preparation method thereof | |
| US8444785B2 (en) | Solid composite propellants and methods of making propellants | |
| CN108191589B (en) | Fuel-rich propellant with boron content in high burning speed pressure index | |
| CN111170816A (en) | Boron-containing fuel-rich propellant | |
| CN105130720A (en) | Propellant with high energy and low temperature sensitive coefficient of burning | |
| CN109384636A (en) | A kind of hydrocarbon fuel-rich propellant and preparation method thereof | |
| CN109574773B (en) | Boron-containing fuel-rich propellant | |
| CN105777459A (en) | Low pressure exponent and low residue fuel gas generating agent and preparing method thereof | |
| CN109503301B (en) | Hydrocarbon fuel-rich propellant | |
| CN110981665B (en) | Boron-containing fuel-rich propellant for platform combustion | |
| KR101664236B1 (en) | Propellant for ducted rocket | |
| CN108892599A (en) | A kind of fuel-rich propellant formula | |
| JP2002527344A (en) | Injection of double-based solid rocket propellant containing ballistic modifier pasted into inert polymer | |
| CN106938965A (en) | A kind of nitric acid ammonium low burn temperature clean fuel gas propellant | |
| CN106748601A (en) | A kind of good NEPE propellants of cryogenic mechanics performance | |
| CN111704516B (en) | Hydroxyl-terminated aluminum-free propellant and preparation method thereof | |
| CN114349584B (en) | Propellant with low ablation property, high energy and low characteristic signal | |
| CN107512997A (en) | A kind of low burning rate high-energy solid propellant | |
| CN114196454A (en) | Solid fuel containing high nitrogen compound | |
| CN109467492B (en) | Negative pressure intensity index propellant | |
| KR102633762B1 (en) | Insensitive smokeless solid propellant composition comprising N-Guanylurea dinitramide | |
| CN111892966B (en) | High-energy metal fuel for boron-containing propellant | |
| KR102062878B1 (en) | Glycidyl azide polymer based solid composite propellant | |
| KR20140022500A (en) | Nonplasticizer solid propellant composition for kick motor of space launch vehicle |
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 | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20181102 |