CN109305868A - A kind of high-energy solid propellant - Google Patents
A kind of high-energy solid propellant Download PDFInfo
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- CN109305868A CN109305868A CN201811123268.9A CN201811123268A CN109305868A CN 109305868 A CN109305868 A CN 109305868A CN 201811123268 A CN201811123268 A CN 201811123268A CN 109305868 A CN109305868 A CN 109305868A
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- propellant
- solid propellant
- energy solid
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- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B33/00—Compositions containing particulate metal, alloy, boron, silicon, selenium or tellurium with at least one oxygen supplying material which is either a metal oxide or a salt, organic or inorganic, capable of yielding a metal oxide
- C06B33/08—Compositions containing particulate metal, alloy, boron, silicon, selenium or tellurium with at least one oxygen supplying material which is either a metal oxide or a salt, organic or inorganic, capable of yielding a metal oxide with a nitrated organic compound
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- 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
- C06B23/001—Fillers, gelling and thickening agents (e.g. fibres), absorbents for nitroglycerine
-
- 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
- C06B23/009—Wetting agents, hydrophobing agents, dehydrating agents, antistatic additives, viscosity improvers, antiagglomerating agents, grinding agents and other additives for working up
-
- 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
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- Chemical & Material Sciences (AREA)
- Organic Chemistry (AREA)
- Engineering & Computer Science (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Combustion & Propulsion (AREA)
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Abstract
The present invention provides a kind of high-energy solid propellants, belong to propellant technical field.The propellant raw material includes the component of following mass percent: ammonium perchlorate 45%~59%, aluminium powder 0~5%, explosive 18%~35%, curing agent 1.29%~1.64%, function additive 0.91%-1.91%, energetic plasticiser 11.07%~12.60% and adhesive 4.11%~5.93%, wherein, described adhesive is nitrine glycidol ether and tetrahydrofuran copolyether or 3, bis- (azido-methyl) epoxy butanes of 3- and tetrahydrofuran copolyether, the energetic plasticiser is nitroglycerine, butanetriol trinitrate, trimethylolethane trimethacrylate nitrate, the mixture of one of triethylene glycol dinitrate and N- butyl -2- nitre oxygen ethyl ammonium nitrate.The present invention reduces propellant glass transition temperature and improves propellant high and low temperature mechanical property under the premise of keeping original propellant high specific impulse, low signature performance, and then widens its use temperature range, at the same time, further improves propellant security performance.
Description
Technical field
The present invention relates to a kind of high-energy solid propellants, belong to solid propellant technical field.
Background technique
Land, sea, air army all-purpose missile and multipurpose tactical missile are a kind of tactics that current countries in the world are given priority to
The characteristics of weapon, this kind of guided missile has high existence, strong prominent anti-, Long-range precision strike and adapts to wide scope working environment, this is just
So that the propellant as missile dynamic source while meeting high specific impulse, low signature, need to take into account wider temperature and be applicable in
Range and good security performance.It is low by China topography Xi Gaodong, north and south region span is big is influenced, usually require that guided missile is sent out
Motivation reliably working under -60 DEG C~+70 DEG C environment, therefore it is required that propellant has good tensile strength at the corresponding temperature
And elongation.At the same time, most to meet the requirement of different missile operations carriers and operational environment to propellant security performance
Engine calls propellant meets 1.3 grades of insensitiveness characteristics.
Nitrine class propellant is current countries in the world in high specific impulse, the primary study object of low characteristic signal propellant.?
Azide polyethers (GAP (glycidyl azide polymer), BAMO (3,3- bis- (azido-methyl) epoxy butane copolyethers), AMMO (3- first
Base -3- azidomethyl-methyl oxetane copolyether) etc.) matched in high energy low characteristic signal propellant using desensitized explosive FOX-7 substitution
The conventional explosives such as HMX or RDX in side, propellant can be realized 1.3 level security class requirement of propellant, but GAP, BAMO,
Itself glass transition temperature of the azido binders such as AMMO is higher, usually at -40 DEG C or more, causes propellant basic at -50 DEG C or less
In brittle glassy state, elongation is extremely low, limits its application in wide apaptability tactical missile.
Summary of the invention
The purpose of the present invention is aiming at the problems existing in the prior art, providing a kind of high-energy solid propellant, keeping
Under the premise of original propellant high specific impulse, low signature performance, reduces propellant glass transition temperature and improve propellant high and low temperature
Mechanical property, and then its use temperature range is widened, at the same time, further improve propellant security performance.
Above-mentioned purpose of the invention is achieved by following technical solution:
A kind of high-energy solid propellant, raw material include the component of following mass percent:
Ammonium perchlorate 45%~59%, aluminium powder 0~5%, explosive 18%~35%, curing agent 1.29%~1.64%, function
Energy auxiliary agent 0.91%-1.91%, energetic plasticiser 11.07%~12.60% and adhesive 4.11%~5.93%, wherein institute
Stating adhesive is nitrine glycidol ether and tetrahydrofuran copolyether or bis- (azido-methyl) epoxy butanes of 3,3- and tetrahydrofuran
Copolyether, the energetic plasticiser are nitroglycerine, butanetriol trinitrate, trimethylolethane trimethacrylate nitrate, two three second of contracting
The mixture of one of glycol dinitrate and N- butyl -2- nitre oxygen ethyl ammonium nitrate.
In an alternative embodiment, the explosive is octogen or 1, one in 1- diamino -2,2- dinitro ethylene
Kind or combination.
In an alternative embodiment, the nitrine glycidol ether and tetrahydrofuran copolyether are random copolymer, and
It is 40%~60% that nitrine glycidol ether unit, which accounts for the percentage composition of copolymerization units sum, in strand.
In an alternative embodiment, the molecular weight of the nitrine glycidol ether and tetrahydrofuran copolyether is 6000~
12000, average hydroxyl quantity >=2 into each strand.
In an alternative embodiment, bis- (azido-methyl) epoxy butanes of 3, the 3- and tetrahydrofuran copolyether are random
Copolymer, and in strand bis- (azido-methyl) epoxybutane units of 3,3- account for copolymerization units sum percentage composition be 40%~
50%.
In an alternative embodiment, bis- (azido-methyl) epoxy butanes of 3, the 3- and tetrahydrofuran copolyether molecular weight
It is 5000~10000, average hydroxyl quantity >=2 into each strand.
In an alternative embodiment, quality hundred of the N- butyl -2- nitre oxygen ethyl ammonium nitrate in the energetic plasticiser
Dividing content is 40%~60%, and plasticising is 2.0~3.0 than range.
In an alternative embodiment, the curing agent is hexamethylene-diisocyanate or dimer (fatty acid) yl diisocyanate
One of ester or combination.
In an alternative embodiment, the function additive includes that mechanical property auxiliary agent, stabilization agent, steady combustion agent and solidification are urged
Agent.
In an alternative embodiment, the mechanical property auxiliary agent is neutral polymer binder, and the stabilization agent is N, N-
Dimethylaniline, the steady combustion agent are titanium dioxide or zirconium carbide, and the curing catalysts are cumyl peroxide.
The advantages of the present invention over the prior art are that:
Propellant provided by the invention is shunk sweet compared with the GAP propellant of existing high energy low signature using nitrine
Oily ether and bis- (azido-methyl) epoxy butanes of tetrahydrofuran copolyether GAP-THF or 3,3- and tetrahydrofuran copolyether BAMO-THF
As adhesive, the good mixing energetic plasticiser of compatibility therewith, and corresponding adjustment curing agent, curing catalysts, power are introduced
The composition such as performance aids is learned, a kind of high performance energetic binder system is formd.Above-mentioned adhesive composition is applied in high energy
In low signature formula, propellant glass transition temperature is significantly reduced, and cryogenic mechanics performance greatly improves, and the performance of propellant meets
The technical need that solid propellant rocket works normally under -60 DEG C~+70 DEG C environment.At the same time, propellant security level
It is 1.3 grades, meets the missile armaments such as carrier-borne, airborne, vehicle-mounted to the requirement in terms of propellant security performance.Therefore, of the invention
Propellant has significantly widened the application range of nitrine class high energy low characteristic signal propellant.
(1) using GAP-THF, BAMO-THF as adhesive in propellant provided by the invention, and it is soft using strand
The preferable HDI and/or DDI of property is as curing agent, propellant glass transition temperature Tg≤ -65 DEG C (see 1~embodiment of embodiment 8)；
(2) -60 DEG C of the maximum tensile strength σ of propellant provided by the inventionm>=4.11MPa, maximum elongation rate εm≥
48.1% ,+70 DEG C of the maximum tensile strength σm>=0.78MPa, maximum elongation rate εm>=45.7% (see 1~embodiment of embodiment 8),
Mechanical properties of propellant shows as maximum elongation rate and varies with temperature little feature within the scope of -60 DEG C~+70 DEG C simultaneously；
(3) in propellant provided by the invention plasticizer using one in energetic plasticiser NG, BTTN, TEGDN, TMETN
Kind forms naked nitric acid ester system with insensitiveness energetic plasticiser Bu-NENA.The plasticiser system and BAMO-THF, GAP-THF phase
Capacitive is good, while security performance is preferable, when HMX content is no more than 20% in propellant or addition FOX-7 replaces HMX condition
Under, propellant security level reaches 1.3 grades.
(4) adhesive GAP-THF or BAMO-THF flexibility, wellability and the plasticity that propellant of the present invention uses compared with
By force, the mixing energetic plasticiser that large dosage can be used is plasticized, and maximum plasticising ratio can be improved to 3.0, is meeting propellant system
Solid content can be improved under the premise of technique to 80%~82% by making, and generally improve propellant energy level, standard hair
Specific impulse I is surveyed under motivation 6.86MPasp≥242s。
(5) the naked nitric acid ester plasticising azide polyethers and tetrahydrofuran copolymer adhesive used in propellant of the present invention
(GAP-THF or BAMO-THF) system, Propellant Processing Characteristics are good, easily operated, with wider application prospect and relatively strong
Practical value.
Specific embodiment
Below in conjunction with specific embodiment, the present invention is described in detail, but protection scope is not limited thereto, and should wrap
The full content of claim narration is included, and by several embodiments below, field technical staff is fully able to implement complete
The full content of invention claim.
The embodiment of the invention provides a kind of high-energy solid propellant, raw material includes the component of following mass percent:
Ammonium perchlorate AP45%~59%, aluminium powder Al0~5%, explosive 18%~35%, curing agent 1.29%~
1.64%, function additive 0.91%~1.91%, energetic plasticiser 11.07%~12.60% and adhesive 4.11%~
5.93%, wherein described adhesive is nitrine glycidol ether and tetrahydrofuran copolyether GAP-THF or 3, bis- (the nitrine first of 3-
Base) epoxy butane and tetrahydrofuran copolyether BAMO-THF, the energetic plasticiser nitroglycerine NG, butanetriol trinitrate
One of BTTN, trimethylolethane trimethacrylate nitrate TMETN, triethylene glycol dinitrate TEGDN and N- butyl -2- nitre
The mixture of oxygen ethyl ammonium nitrate Bu-NENA.
One of described preferred octogen HMX or 1,1- diamino -2,2- dinitro ethylene FOX-7 of explosive or group
It closes；The nitrine glycidol ether and tetrahydrofuran copolyether GAP-THF is random copolymer, and nitrine shrinks in strand
The percentage composition that glycerol ether unit GAP accounts for copolymerization units sum is preferably 40%~60%, the nitrine glycidol ether with
The molecular weight of tetrahydrofuran copolyether GAP-THF is preferably 6000~12000, and the average hydroxyl quantity into each strand is excellent
Choosing >=2；Bis- (azido-methyl) epoxy butanes of 3, the 3- and tetrahydrofuran copolyether BAMO-THF are random copolymer, and point
The percentage composition that bis- (azido-methyl) the epoxy butane BAMO units of 3,3- account for copolymerization units sum in subchain is preferably 40%~
Bis- (azido-methyl) epoxy butanes of 50%, 3, the 3- and tetrahydrofuran copolyether BAMO-THF molecular weight be 5000~
10000, average hydroxyl quantity >=2 into each strand；The curing agent hexamethylene-diisocyanate HDI, dimerization
The mixture of fatty acid diisocyanate DDI and the two；The preferred mechanical property auxiliary agent of the function additive, stabilization agent, steady combustion
Agent and the combination of curing catalysts；The preferred neutral polymer binder NPBA of mechanical property auxiliary agent, the stabilization agent are preferred
N,N-Dimethylaniline NN, the preferred titanium dioxide of the steady combustion agent or zirconium carbide, the preferred peroxidating two of curing catalysts are different
Propyl benzene DCP.
In an alternative embodiment, quality hundred of the N- butyl -2- nitre oxygen ethyl ammonium nitrate in the energetic plasticiser
Dividing content is 40%~60%, and plasticising is 2.0~3.0 than range.The plasticiser system solves common energetic plasticiser nitrification
Glycerol, butanetriol trinitrate, trimethylolethane trimethacrylate nitrate, triethylene glycol dinitrate and bis- (the nitrine first of 3,3-
Base) epoxy butane and tetrahydrofuran copolyether BAMO-THF or nitrine glycidol ether and tetrahydrofuran copolyether GAP-THF it is viscous
The problem of mixture poor compatibility, propellant druggability are good.In 2.0~3.0 plasticising than in range, solid content can be mentioned in propellant
Up to 82%, while improving propellant specific impulse, mechanical properties of propellant meets tactical missile engine in wide temperature model
The requirement enclosed.In addition, the introducing of N- butyl -2- nitre oxygen ethyl ammonium nitrate is conducive to improve propellant safety in plasticizer
Can, when octogen HMX mass percentage≤20% in formula or addition FOX-7 substitution HMX, propellant meets 1.3 grades
Insensitiveness characteristic.
Propellant finished product can be made up in propellant formulation provided in an embodiment of the present invention of conventional propellant preparation method.
The following are several specific embodiments of the invention, raw materials used in each embodiment is commercial product, wherein bonding
Agent, plasticizer are provided by dawn chemical research designing institute；
Embodiment 1
(1) propellant formulation composition (mass percent) is as shown in table 1-1:
Table 1-1 propellant formulation
Raw material is weighed according to above-mentioned formula to be mixed through vertical mixer.The mixture of adhesive and plasticizer mixes in advance
Conjunction forms uniform liquid, referred to as glue.Al powder, neutral polymer binder, stabilization agent, solidification are firstly added in mixing machine
Catalyst with 70% glue mixture mixing 10min, then be added HMX or FOX-7 mixing 15min, add AP mix
30min, be eventually adding curing agent and 30% glue mixture, mix 20min, 55 DEG C ± 2 DEG C of mixing temperature, Composite Propellant Slurry
It is cast into mold after discharging through vacuum pouring tank, is finally placed in 50 DEG C of oil bath baking ovens after solidifying 7 days and obtains propellant finished product,
Subsequent each embodiment preparation method is identical as the present embodiment.
(2) comprehensive performance of propellant is as shown in table 2-1:
Table 2-1 performance of propellant parameter list
Signal characteristic: propellant plumage cigarette visible light transmittance 65.3%, laser transmittance 73.5%, near-infrared transmitance
81.9%, middle infrared transmittivity 85.6%, far infrared transmitance 90.2%, microwave attenuation 0.34dB, in plumage flame, far infrared radiation
Intensity reduces by 70% and 89% compared with 18.5%Al HTPB propellant.
Embodiment 2
(1) propellant formulation composition (mass percent) is as shown in table 1-2:
Table 1-2 propellant formulation
(2) comprehensive performance of propellant is as shown in table 2-2:
Table 2-2 performance of propellant parameter list
Signal characteristic: propellant plumage cigarette visible light transmittance 65.6%, laser transmittance 73.9%, near-infrared transmitance
82.4%, middle infrared transmittivity 84.9%, far infrared transmitance 90.4%, microwave attenuation 0.34dB, in plumage flame, far infrared radiation
Intensity reduces by 70% and 90% compared with 18.5%Al HTPB propellant.
Embodiment 3
(1) propellant formulation forms (mass percent) as shown in table 1-3:
Table 1-3 propellant formulation
(2) combustibility of propellant is as shown in table 2-3:
Table 2-3 performance of propellant parameter list
Signal characteristic: propellant plumage cigarette visible light transmittance 75.5%, laser transmittance 87.1%, near-infrared transmitance
87.6%, middle infrared transmittivity 94.2%, far infrared transmitance 98.6%, microwave attenuation 0.27dB, in plumage flame, far infrared radiation
Intensity reduces by 73% and 95% compared with 18.5%Al HTPB propellant.
Embodiment 4
(1) propellant formulation composition (mass percent) is as shown in table 1-4:
Table 1-4 propellant formulation
(2) combustibility of propellant is as shown in Table 2-4:
Table 2-4 performance of propellant parameter list:
Signal characteristic: propellant plumage cigarette visible light transmittance 75.7%, laser transmittance 87.5%, near-infrared transmitance
86.9%, middle infrared transmittivity 93.3%, far infrared transmitance 98.4%, microwave attenuation 0.27dB, in plumage flame, far infrared radiation
Intensity reduces by 73% and 95% compared with 18.5%Al HTPB propellant.
Embodiment 5
(1) propellant formulation forms (mass percent) as shown in tables 1 to 5:
Table 1-5 propellant formulation
(2) comprehensive performance of propellant is as shown in table 2-5:
Table 2-5 performance of propellant parameter list
Signal characteristic: propellant plumage cigarette visible light transmittance 65.9%, laser transmittance 73.1%, near-infrared transmitance
82.3%, middle infrared transmittivity 85%, far infrared transmitance 90.7%, microwave attenuation 0.34dB, in plumage flame, far infrared radiation it is strong
Degree reduces by 70% and 90% compared with 18.5%Al HTPB propellant.
Embodiment 6
(1) propellant formulation composition (mass percent) is as shown in table 1-6:
Table 1-6 propellant formulation
(2) comprehensive performance of propellant is as shown in table 2-6:
Table 2-6 performance of propellant parameter list
Signal characteristic: propellant plumage cigarette visible light transmittance 71.2%, laser transmittance 77.1%, near-infrared transmitance
84.0%, middle infrared transmittivity 86.2%, far infrared transmitance 92.3%, microwave attenuation 0.31dB, in plumage flame, far infrared radiation
Intensity reduces by 72% and 92% compared with 18.5%Al HTPB propellant.
Embodiment 7
(1) propellant formulation composition (mass percent) is as shown in table 1-7:
Table 1-7 propellant formulation
(2) comprehensive performance of propellant is as shown in table 2-7:
Table 2-7 performance of propellant parameter list:
Signal characteristic: propellant plumage cigarette visible light transmittance 65.4%, laser transmittance 73.3%, near-infrared transmitance
81.6%, middle infrared transmittivity 83.3%, far infrared transmitance 90.7%, microwave attenuation 0.33dB, in plumage flame, far infrared radiation
Intensity reduces by 71% and 90% compared with 18.5%Al HTPB propellant.
Embodiment 8
(1) propellant formulation composition (mass percent) is as shown in table 1-8:
Table 1-8 propellant formulation
(2) comprehensive performance of propellant is as shown in Table 2-8:
Table 2-8 performance of propellant parameter list
Signal characteristic: propellant plumage cigarette visible light transmittance 71.7%, laser transmittance 77.4%, near-infrared transmitance
84.3%, middle infrared transmittivity 86.5%, far infrared transmitance 92.4%, microwave attenuation 0.31dB, in plumage flame, far infrared radiation
Intensity reduces by 72% and 91% compared with 18.5%Al HTPB propellant.
The foregoing is merely the optimal specific embodiments of the present invention, but scope of protection of the present invention is not limited thereto,
In the technical scope disclosed by the present invention, any changes or substitutions that can be easily thought of by anyone skilled in the art,
It should be covered by the protection scope of the present invention.The content that description in the present invention is not described in detail belongs to this field profession
The well-known technique of technical staff.
Claims (10)
1. a kind of high-energy solid propellant, which is characterized in that its raw material includes the component of following mass percent:
Ammonium perchlorate 45%~59%, aluminium powder 0~5%, explosive 18%~35%, curing agent 1.29%~1.64%, function help
Agent 0.91%-1.91%, energetic plasticiser 11.07%~12.60% and adhesive 4.11%~5.93%, wherein described viscous
Mixture is that nitrine glycidol ether and tetrahydrofuran copolyether or bis- (azido-methyl) epoxy butanes of 3,3- and tetrahydrofuran are copolymerized
Ether, the energetic plasticiser are nitroglycerine, butanetriol trinitrate, trimethylolethane trimethacrylate nitrate, triethylene-glycol
The mixture of one of dinitrate and N- butyl -2- nitre oxygen ethyl ammonium nitrate.
2. a kind of high-energy solid propellant according to claim 1, it is characterised in that: the explosive be octogen or 1,
One of 1- diamino -2,2- dinitro ethylene or combination.
3. a kind of high-energy solid propellant according to claim 1, it is characterised in that: the nitrine glycidol ether with
Tetrahydrofuran copolyether is random copolymer, and the percentage that nitrine glycidol ether unit accounts for copolymerization units sum in strand contains
Amount is 40%~60%.
4. a kind of high-energy solid propellant according to claim 3, it is characterised in that: the nitrine glycidol ether with
The molecular weight of tetrahydrofuran copolyether is 6000~12000, average hydroxyl quantity >=2 into each strand.
5. a kind of high-energy solid propellant according to claim 1, it is characterised in that: 3, the 3- bis- (azido-methyls)
Epoxy butane and tetrahydrofuran copolyether are random copolymer, and bis- (azido-methyl) epoxybutane units of 3,3- account in strand
The percentage composition of copolymerization units sum is 40%~50%.
6. a kind of high-energy solid propellant according to claim 5, it is characterised in that: 3, the 3- bis- (azido-methyls)
Epoxy butane and tetrahydrofuran copolyether molecular weight are 5000~10000, average hydroxyl quantity >=2 into each strand.
7. a kind of high-energy solid propellant according to claim 1, it is characterised in that: the N- butyl -2- nitre oxygen ethyl
Mass percentage of the ammonium nitrate in the energetic plasticiser is 40%~60%, and plasticising is 2.0~3.0 than range.
8. a kind of high-energy solid propellant according to claim 1, it is characterised in that: the curing agent is six methines
One of diisocyanate or dimer (fatty acid) yl diisocyanate or combination.
9. a kind of high-energy solid propellant according to claim 1, it is characterised in that: the function additive includes mechanics
Performance aids, stabilization agent, steady combustion agent and curing catalysts.
10. a kind of high-energy solid propellant according to claim 9, it is characterised in that: during the mechanical property auxiliary agent is
Property polymer bonds mixture, the stabilization agent be n,N-Dimethylaniline, the steady combustion agent be titanium dioxide or zirconium carbide, it is described solid
Change catalyst is cumyl peroxide.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110240532A (en) * | 2019-07-08 | 2019-09-17 | 中国工程物理研究院化工材料研究所 | A kind of preparation method of low ignition threshold value aluminium base particle |
| CN112500253A (en) * | 2020-12-02 | 2021-03-16 | 湖北航天化学技术研究所 | Temperature-sensitive time-varying high-energy solid propellant |
| CN114349584A (en) * | 2022-01-27 | 2022-04-15 | 湖北航天化学技术研究所 | Propellant with low ablation property, high energy and low characteristic signal |
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|---|---|---|---|---|
| US3666576A (en) * | 1970-04-30 | 1972-05-30 | Us Army | Explosive composition containing an energetic acrylate as binder |
| CN106316729A (en) * | 2016-08-24 | 2017-01-11 | 湖北航天化学技术研究所 | Wide adaptive azide polyether propellant |
-
2018
- 2018-09-26 CN CN201811123268.9A patent/CN109305868B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3666576A (en) * | 1970-04-30 | 1972-05-30 | Us Army | Explosive composition containing an energetic acrylate as binder |
| CN106316729A (en) * | 2016-08-24 | 2017-01-11 | 湖北航天化学技术研究所 | Wide adaptive azide polyether propellant |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110240532A (en) * | 2019-07-08 | 2019-09-17 | 中国工程物理研究院化工材料研究所 | A kind of preparation method of low ignition threshold value aluminium base particle |
| CN112500253A (en) * | 2020-12-02 | 2021-03-16 | 湖北航天化学技术研究所 | Temperature-sensitive time-varying high-energy solid propellant |
| CN114349584A (en) * | 2022-01-27 | 2022-04-15 | 湖北航天化学技术研究所 | Propellant with low ablation property, high energy and low characteristic signal |
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| CN109305868B (en) | 2021-07-13 |
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