CN107867963B - A kind of low burning rate high energy strong mechanical performance composite solidpropellant - Google Patents
A kind of low burning rate high energy strong mechanical performance composite solidpropellant Download PDFInfo
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- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B45/00—Compositions or products which are defined by structure or arrangement of component of product
- C06B45/04—Compositions or products which are defined by structure or arrangement of component of product comprising solid particles dispersed in solid solution or matrix not used for explosives where the matrix consists essentially of nitrated carbohydrates or a low molecular organic explosive
- C06B45/06—Compositions or products which are defined by structure or arrangement of component of product comprising solid particles dispersed in solid solution or matrix not used for explosives where the matrix consists essentially of nitrated carbohydrates or a low molecular organic explosive the solid solution or matrix containing an organic component
- C06B45/10—Compositions or products which are defined by structure or arrangement of component of product comprising solid particles dispersed in solid solution or matrix not used for explosives where the matrix consists essentially of nitrated carbohydrates or a low molecular organic explosive the solid solution or matrix containing an organic component the organic component containing a resin
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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
- C06B33/06—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
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- 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
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Abstract
The present invention relates to a kind of low burning rate high energy strong mechanical performance composite solidpropellants, contain the following parts by weight: adhesive: 6 ~ 7；Plasticizer: 17 ~ 19；Oxidant: 10 ~ 15；The explosive containing energy: 42 ~ 47；Metal fuel: 15 ~ 18；Curing agent: 0.15 ~ 0.25；Curing catalysts: 0.05；Stabilization agent: 0.3；Bonding agent: 0.2.Minimum burn rate can reach 7mm/s under 6.86MPa of the present invention, standard specific impulse is surveyed to stablize greater than 255s, the technical problem that high-energy propellant burn rate further decreases, propellant energy is greatly reduced is solved, realizes the technical requirements of current weapon model propellant high-energy, more low burning rate and strong mechanical performance.
Description
Technical field
The present invention relates to a kind of polyether polyester composite solidpropellants (being abbreviated as NEPE) of nitrate plasticising.
Background technique
The Far Range of missile weapon system, big load, strong prominent anti-, small-sized high maneuverability development trend, constantly require to start
The solid propellant that machine combustion chamber uses has high-energy, alap burn rate, higher mechanical property.Wherein high-energy with
Low burning rate is a pair of sharp contradiction, because the performance of stablizing of energy characteristics is the burn rate item for requiring propellant to reach certain
It is just able to achieve under part.When propellant burning rate is lower than a certain lower limit value, which is usually for high energy NEPE propellant
8mm/s~9mm/s further decreases burn rate using current reduction of speed agent means, and Propellant warp sharply declines.And it bonds
Important component and elastic matrix of the agent as propellant, it is to Propellant warp, mechanical property and combustibility three
Key performance all has great influence.
Currently, for the high energy NEPE propellant of weaponry, there are two main classes, and one kind is equal with terminal hydroxy group ethylene oxide
Polyethers (being abbreviated as PEG) is that the nitrate of adhesive is plasticized propellant (I), and one kind is with terminal hydroxy group ethylene oxide tetrahydrofuran
(being abbreviated as PET) is that the nitrate of adhesive is plasticized propellant (II).
NEPE propellant (I) oxidant is ammonium perchlorate (being abbreviated as AP) and octogen (being abbreviated as HMX) or heisuojin
(being abbreviated as RDX), fuel are aluminium powder Al, (are abbreviated as using large dosage of nitroglycerine (being abbreviated as NG), butanetriol trinitrate
BTTN) mixture makees plasticizer, is plasticized ratio 2.5~3.0, PEG is adhesive, and wherein PEG degree of functionality f=2, number-average molecular weight are
6000~12000, solidified using polyfunctionality isocyanates N-100.The characteristic of this kind of propellant is high-energy strong mechanical performance,
Mechanical property normal temperature strength is 0.8~1.2MPa, and room temperature elongation is that static burn rate is greater than 8mm/ under 85~120%, 6.86MPa
When s, propellant actual measurement standard specific impulse can be stablized in~255s, when requiring static burn rate under propellant 6.86MPa to be less than 8mm/s
When, the addition reduction of speed agent means for influencing energy must be used in formula, propellant actual measurement standard specific impulse start to be greatly reduced, such as push away
When static burn rate is down to 7~7.5mm/s under into agent 6.86MPa, propellant actual measurement standard specific impulse is down to 250~252s.
NEPE propellant (II) oxidant is ammonium perchlorate and heisuojin, and fuel is aluminium powder Al, uses PET for adhesive,
Degree of functionality has f=2 and two kinds of f=3, and number-average molecular weight is 3000~7000, solid using two degree of functionality toluene di-isocyanate(TDI) TDI
Change.In PET molecule segment tetrahydrofuran THF polarity it is low due to, PET with highly polar, high-energy nitrate NG, BTTN is molten
Spend parameter differ larger, poor compatibility, can only in highly polar nitrate diethylene glycol nitrate (being abbreviated as DEGDN), three second
Glycol dinitrate (being abbreviated as TEGDN), NG/TEGDN mix nitrate mixing, and to prevent nitrate from oozing out, plasticising is than general
No more than 2.0, cause propellant energy level relatively low.Because PET number-average molecular weight is relatively low, mechanical properties of propellant integral level
Relatively low, normal temperature strength is 0.5~0.8MPa, when room temperature elongation is that static burn rate is greater than 8mm/s under 50~80%, 6.86MPa,
Propellant, which surveys standard specific impulse, can stablize in 252s, and burn rate further decreases, since there is PET first heat absorption before decomposition to melt, easily
Flowing is covered on the characteristic of solid particles surface, and the oxidability of nitrate used in system is weaker in addition, and content is pushed away less than NEPE
Into agent (I) formula system, when NEPE propellant (II) burn rate is reduced to 7~7.5mm/s, propellant energy is greatly reduced, and is promoted
Agent actual measurement standard specific impulse is down to 242~248s.
1989, U.S. Russell Reed (US4799980) researched and developed polyfunctionality polyether-type adhesive ---
Delta/Y shape and four star-like polyoxygenated alkene (PAO) adhesives, molecular weight are 20000~30000, can significantly improve NEPE high
The mechanical property of energy solid propellant, and it has the star-like skeleton structure for absorbing energy, so as to drop to a certain extent
The sensitivity of low propellant improves security performance.Experimental studies have found that polyfunctionality PAO replaces the PEG in NEPE propellant (I)
Adhesive cooperates two degree of functionality isocyanate curing agents, and propellant normal temperature strength is suitable with PEG propellant, and room temperature elongation is exhausted
50% or more is improved to value, combustibility and energy characteristics are consistent with PEG propellant.
In addition, external report insensitiveness HTCE adhesive, is terminal hydroxy group caprolactone PCL and tetrahydrofuran THF copolyether, f=
2, number-average molecular weight is 2000 or so.Experimental studies have found that PET adhesive replaces PEG adhesive, propellant burning rate is reduced
10%, HTCE adhesive replace PET adhesive, and propellant burning rate reduces by 5%.Compare both HTCE adhesive and PET adhesive
Structural formula it can be found that in addition to common THF segment, illustrate the burn rate of PCL lower than CH2-CH2-O segment.Because HTCE is bonded
Agent number-average molecular weight is too low, poor using rear mechanical properties of propellant, especially elongation only 30~40%.THF segment is deposited
, HTCE adhesive also can only same polarity slightly weak TEGDN, NG/TEGDN mix nitrate mixing.PCL ontology and it is highly polar,
High-energy nitrate NG, BTTN and in it is highly polar, middle high-energy nitrate TEGDN compatibility is good, in segment C-H-O match
It is consistent with PEG structural unit, Propellant warp is influenced unanimously, i.e., to substitute PEG adhesive using PCL adhesive, is promoted
Agent energy is constant, and burn rate reduces, and usually uses 1%PCL adhesive equivalent substitution PEG adhesive, and propellant burning rate reduces by 0.3
~0.4mm/s.When shortcoming is that PCL bulk polymerization molecular weight is more than 8000, fusing point is more than 55 DEG C.NG, BTTN are opened at 50 DEG C
Begin to volatilize and slow Autocatalytic decomposition occurs, usual NG, BTTN and adhesive are usually no more than 55 DEG C, are when being mixed with glue
Guarantee that safe preparation process performance, high-energy propellant mixing, casting, solidification temperature are generally controlled at 50 DEG C or so.Therefore, divide
Son poly- PCL of the amount more than 10000, f=2, and is difficult to dissolve in nitrate in 50 DEG C of preparation process of NG, BTTN, cannot be in height
It can be applied in propellant.
Summary of the invention
Technology of the invention solves the problems, such as: overcoming the above-mentioned deficiency of the prior art, provides a kind of suitable solidification of cooperation
System, reach NEPE propellant reduce burn rate, energy characteristics do not lose, mechanical property remain unchanged effect low burning rate high energy it is high
Mechanical property composite solidpropellant.
Technical solution of the invention contains the following parts by weight:
Adhesive: 6~7；
Plasticizer: 17~19；
Oxidant: 10~15；
The explosive containing energy: 42~47；
Metal fuel: 15~18；
Curing agent: 0.15~0.25；
Curing catalysts: 0.05；
Stabilization agent: 0.3；
Bonding agent: 0.2；
Described adhesive is PAO-PCL copolyether, degree of functionality f=3 or f=4, Mn=20000~30000；
The oxidant is ammonium perchlorate (AP)；
The metal fuel is aluminium powder (Al)；
The curing catalysts are triphenyl bismuth (TPB)；
The stabilization agent is N- methyl paranitroaniline (MNA)；
The bonding agent is neutral polymer NPBA.
Polyoxygenated alkene (PAO) degree of functionality f=3 or f=4, Mn in polyoxygenated alkene-caprolactone copolyether of the present invention
=10000~20000, the ratio between polyethers section polyoxygenated alkene (PAO) and polyester segments caprolactone (PCL) monomeric unit PAO in molecule:
PCL=1:1~2:1.
Plasticizer of the present invention is the mixture of nitroglycerine (NG) and butanetriol trinitrate (BTTN), NG and BTTN
Proportion be 1:1.
The explosive of the present invention containing energy is octogen (HMX), heisuojin (RDX).
Curing agent of the present invention is toluene di-isocyanate(TDI) (TDI) or hexamethylene-diisocyanate (HDI).
Preparation process of the invention are as follows: mixed using vertical mixer, by propellant each component according to specific blend
Technique sequentially adds mixing machine, and mixing forms the uniform medicine slurry of component after a certain period of time, is started using the realization of vacuum pouring system
Machine powder column and the production for testing test specimen.
The present invention provides a kind of pair of adhesive and carries out the method that modification reduces burn rate, minimum burn rate under 6.86MPa of the present invention
Can reach 7mm/s, actual measurement standard specific impulse, which is stablized, is greater than 255s, solve high-energy propellant burn rate further decrease, propellant energy
The technical problem being greatly reduced realizes the technology of current weapon model propellant high-energy, more low burning rate and strong mechanical performance
It is required that.
Compared with prior art, the present invention has the following advantages:
(1) invention adhesives are using macromolecule branching PAO (f=3 or f=4, Mn=10000~20000) and PCL
The PAO-PCL polyether polyester block polymer of degree of functionality f=3 or f=4, Mn=20000~30000 that monomer copolymerization generates, dash forward
Low burning rate is broken, macromolecular PCL may not apply to NEPE propellant (I), small molecule PCL and macromolecular PEG co-mixing system mechanics
Two bad big technical problems of performance, the binder molecule amount is big, the submissive no side group of chain, and mechanical properties of propellant is better than macromolecular
PEG and small molecule PCL co-mixing system, with former individually suitable, the propellant burning rate using NEPE propellant (I) mechanical property of PEG
While further decreasing, propellant energy is not lost.
(2) present invention make full use of macromolecular PAO polyfunctionality, high-flexibility have high-intensitive and high elongation characteristics,
Macromolecular PCL has low burning rate and moderate mechanical property and PAO-PCL adhesive and highly polar nitrate NG, BTTN compatibility
Good feature, by PAO-PCL adhesive, substitution PEG is used directly in NEPE propellant (I), the propellant densification nothing of preparation
Hole, good mechanical performance and stabilization meet engine structural integrity requirement, in propellant formulation content composition, grain size distribution
Deng not influencing to realize the further of propellant burning rate in terms of adhesive under conditions of Propellant warp means all use up
It reduces, while having no adverse effect to Propellant warp.
(3) PAO-PCL adhesive of the present invention is used for NEPE propellant (I), all replaces PEG adhesive, is further dropping
Under the conditions of low propellant 6.86MPa burn rate 1mm/s, NEPE propellant (I) actual measurement standard specific impulse is made to play stably, experiments have shown that:
Burn rate 7mm/s, BSF Φ 315 surveys standard specific impulse and stablizes greater than 255s under NEPE high-energy propellant 6.86MPa of the present invention.
(4) present invention realize composite solidpropellant high-energy, further decrease burn rate, strong mechanical performance effectively melt
It closes, adapts to the propellant low burning rate continued to develop, energetic, strong mechanical performance requirement, be suitable for strategy, tactical weapon type
Number with high-energy solid propellant formula improve, be particularly suitable for the strategic arms model with Far Range, packing factor high request.
Specific embodiment
The present invention is described in further detail combined with specific embodiments below.
Embodiment 1
(1) propellant forms
| Component | PAO-PCL | NG/BTTN | AP | HMX | Al |
| Content (%wt) | 7 | 18.3 | 15 | 42 | 18 |
| Component | TPB | MNA | NPBA | TDI | |
| Content (%wt) | 0.05 | 0.3 | 0.2 | 0.15 |
Wherein: PAO-PCL is to make initiator with f=3, the PAO of Mn=10000, and in molar ratio prepared by PAO:PCL=1:1
The PAO-PCL adhesive of f=3 out, Mn=20000,50.1 DEG C of fusing point.
(2) performance of propellant
Energy characteristics (6.86MPa surveys specific impulse): 255.2s
Burn rate: r6.86MPa=7mm/s
Mechanical property: 25 DEG C of σm=0.91MPa, εm=115%
+70℃ εm=87%
-30℃ εm=92%
Embodiment 2
(1) propellant forms
| Component | PAO-PCL | NG/BTTN | AP | HMX | Al |
| Content (%wt) | 6 | 19 | 12.25 | 47 | 15 |
| Component | TPB | MNA | NPBA | HDI | |
| Content (%wt) | 0.05 | 0.3 | 0.2 | 0.2 |
Wherein: PAO-PCL is to make initiator with f=3, the PAO of Mn=15000, and PAO:PCL=2:1 feeds intake in molar ratio,
Prepare f=3, the PAO-PCL adhesive of Mn=22500,50.2 DEG C of fusing point.
(2) performance of propellant
Energy characteristics (6.86MPa surveys specific impulse): 255.3s
Burn rate: r6.86MPa=7.3mm/s
Mechanical property: 25 DEG C of σm=0.91MPa, εm=125%
+70℃ εm=97%
-30℃ εm=98%
Embodiment 3
(1) propellant forms
| Component | PAO-PCL | NG/BTTN | AP | HMX | Al |
| Content (%wt) | 6.3 | 19 | 12 | 46 | 16 |
| Component | TPB | MNA | NPBA | TDI | |
| Content (%wt) | 0.05 | 0.3 | 0.2 | 0.15 |
Wherein: PAO-PCL is to make initiator with f=3, the PAO of Mn=20000, and PAO:PCL=2:1 feeds intake in molar ratio,
Prepare f=3, the PAO-PCL adhesive of Mn=30000,51.2 DEG C of fusing point.
(2) performance of propellant
Energy characteristics (6.86MPa surveys specific impulse): 255.3s
Burn rate: r6.86MPa=7.4mm/s
Mechanical property: 25 DEG C of σm=0.91MPa, εm=129%
+70℃ εm=102%
-30℃ εm=90%
Embodiment 4
(1) propellant forms
| Component | PAO-PCL | NG/BTTN | AP | RDX | Al |
| Content (%wt) | 6.25 | 17 | 15 | 43 | 18 |
| Component | TPB | MNA | NPBA | TDI | |
| Content (%wt) | 0.05 | 0.3 | 0.2 | 0.20 |
Wherein: PAO-PCL is to make initiator with f=4, the PAO of Mn=15000, and PAO:PCL=1:1 feeds intake in molar ratio,
Prepare f=4, the PAO-PCL adhesive of Mn=30000,51.5 DEG C of fusing point.
(2) performance of propellant
Energy characteristics (6.86MPa surveys specific impulse): 255.1s
Burn rate: r6.86MPa=7.0mm/s
Mechanical property: 25 DEG C of σm=1.12MPa, εm=125%
+70℃ εm=107%
-30℃ εm=90%
Embodiment 5
(1) propellant forms
| Component | PAO-PCL | NG/BTTN | AP | RDX | Al |
| Content (%wt) | 6.25 | 18 | 10 | 47 | 18 |
| Component | TPB | MNA | NPBA | HDI | |
| Content (%wt) | 0.05 | 0.3 | 0.2 | 0.20 |
Wherein: PAO-PCL is to make initiator with f=4, the PAO of Mn=20000, and PAO:PCL=2:1 feeds intake in molar ratio,
Prepare f=4, the PAO-PCL adhesive of Mn=30000,50.8 DEG C of fusing point.
(2) performance of propellant
Energy characteristics (6.86MPa surveys specific impulse): 255.2s
Burn rate: r6.86MPa=7.3mm/s
Mechanical property: 25 DEG C of σm=1.0MPa, εm=135%
+70℃ εm=117%
-30℃ εm=100%
Embodiment 6
(1) propellant forms
Wherein: PAO-PCL is to make initiator with f=4, the PAO of Mn=10000, and PAO:PCL=1:1 feeds intake in molar ratio,
Prepare f=4, the PAO-PCL adhesive of Mn=20000,50.8 DEG C of fusing point.
(2) performance of propellant
Energy characteristics (6.86MPa surveys specific impulse): 255.3s
Burn rate: r6.86MPa=7.0mm/s
Mechanical property: 25 DEG C of σm=1.1MPa, εm=105%
+70℃ εm=93%
-30℃ εm=86%
The above, optimal specific embodiment only of the 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 the well-known technique of professional and technical personnel in the field.
Claims (4)
1. a kind of low burning rate high energy strong mechanical performance composite solidpropellant, it is characterised in that contain the following parts by weight:
Adhesive: 6 ~ 7；
Plasticizer: 17 ~ 19；
Oxidant: 10 ~ 15；
The explosive containing energy: 42 ~ 47；
Metal fuel: 15 ~ 18；
Curing agent: 0.15 ~ 0.25；
Curing catalysts: 0.05；
Stabilization agent: 0.3；
Bonding agent: 0.2；
Described adhesive is polyoxygenated alkene-caprolactone copolyether PAO-PCL, degree of functionality f=3 or f=4, Mn=20000 ~ 30000；
Polyoxygenated alkene PAO degree of functionality f=3 or f=4 in polyoxygenated alkene-caprolactone copolyether, Mn=10000 ~ 20000 are gathered in molecule
The ratio between ether section polyoxygenated alkene PAO and polyester segments caprolactone PCL monomeric unit PAO:PCL=1:1 ~ 2:1；
The oxidant is ammonium perchlorate AP；
The metal fuel is aluminium powder Al；
The curing catalysts are triphenyl bismuth TPB；
The stabilization agent is N- methyl paranitroaniline MNA；
The bonding agent is neutral polymer NPBA.
2. low burning rate high energy strong mechanical performance composite solidpropellant according to claim 1, it is characterised in that: plasticizer
For the mixture of nitroglycerine NG and butanetriol trinitrate BTTN, the proportion of NG and BTTN are 1:1.
3. low burning rate high energy strong mechanical performance composite solidpropellant according to claim 1, it is characterized in that containing that can fry
Medicine is octogen HMX, heisuojin RDX.
4. low burning rate high energy strong mechanical performance composite solidpropellant according to claim 1, it is characterized in that curing agent
For toluene di-isocyanate(TDI) TDI or hexamethylene-diisocyanate HDI.
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| CN110759800A (en) * | 2018-07-27 | 2020-02-07 | 南京理工大学 | High-energy high-mechanical-property electronic control solid propellant |
| CN110156548B (en) * | 2019-05-23 | 2022-05-20 | 北京理工大学 | Casting type high-energy insensitive explosive and preparation method thereof |
| CN110963874B (en) * | 2019-11-28 | 2021-03-23 | 湖北航天化学技术研究所 | Solid propellant with polyester-butylated hydroxyanisole block polymer as adhesive |
| CN112028723B (en) * | 2020-07-23 | 2021-09-07 | 湖北航天化学技术研究所 | High-mechanical-property solid propellant containing biological BTTN and preparation process thereof |
| CN114804983B (en) * | 2022-04-27 | 2023-08-11 | 中北大学 | Preparation method of skeleton type energetic material |
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| US4216039A (en) * | 1978-11-20 | 1980-08-05 | The United States Of America As Represented By The Secretary Of The Army | Smokeless propellant compositions having polyester or polybutadiene binder system crosslinked with nitrocellulose |
| US4799980A (en) * | 1988-01-28 | 1989-01-24 | Reed Jr Russell | Multifunctional polyalkylene oxide binders |
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