CN110156547A - A kind of high intensity low pressure index HTPB composite propellant and preparation method thereof - Google Patents
A kind of high intensity low pressure index HTPB composite propellant and preparation method thereof Download PDFInfo
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- CN110156547A CN110156547A CN201910594244.XA CN201910594244A CN110156547A CN 110156547 A CN110156547 A CN 110156547A CN 201910594244 A CN201910594244 A CN 201910594244A CN 110156547 A CN110156547 A CN 110156547A
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- composite propellant
- low pressure
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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
- 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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- Engineering & Computer Science (AREA)
- Organic Chemistry (AREA)
- Inorganic Chemistry (AREA)
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- Metallurgy (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Combustion & Propulsion (AREA)
- Adhesives Or Adhesive Processes (AREA)
Abstract
The invention belongs to composite solidpropellant manufacturing fields, disclose a kind of high-intensitive low pressure index HTPB composite propellant, component including following mass percent: oxidant 73%-73.5%, metal powder 14%, binding system 5.95%, plasticizer 3.5%, burningrate catalyst 2%, Pressure Exponent regulator 0.5%-1%, bonding agent and reinforcing agent 0.4%, curing catalysts and anti-aging agent 0.15%；Preparation method is also disclosed, solid raw material preliminary drying: ammonium perchlorate and aluminium powder are sieved；It weighs, premix: by quality proportioning requirement, being premixed, aluminium powder premix is then added；Mixing: being added oxidant in premix medicine slurry by several times and be uniformly mixed, and curing agent mixing is added；Casting: Composite Propellant Slurry is poured using vacuum pouring method；Solidify: the mold that Composite Propellant Slurry is housed and motor body are heating and curing.The present invention, be applicable to high overload, High Voltage working condition rocket projectile, guided missile solid engines powder charge demand.
Description
Technical field
The present invention relates to composite solidpropellant manufacturing field, specifically a kind of high intensity low pressure index fourth hydroxyl composite solid
Body propellant and preparation method thereof.
Background technique
Rocket projectile, guided missile are in high overload flight course, to prevent solid rocket motor grain in high overload, generate
Deformation, or even the case where cracking, it is desirable that propellant has high-modulus, high-tensile performance.
With rocket projectile, the development of missilery level, increasingly higher demands are proposed to solid engines energy.It is more next
More multiple-motor designing unit, which takes, improves engine operation pressure, improves the technological approaches of propellant energy.HTPB propellant
As operating pressure improves, propellant Pressure Exponent increases, and shows that burning velocity increases with pressure and quicklyd increase, causes to send out
Motivation pressure further increases, and generates harm to structural intergrity in engine working process.
Summary of the invention
The purpose of the present invention is to provide a kind of high-intensitive low pressure index HTPB composite propellant and its preparation sides
Method, technical problems to be solved improve propellant tensile strength, reduce Pressure Exponent.Improve the technical solution that tensile strength is taken
It is to be applied in combination by bonding agent and reinforcing agent, on the one hand improves liquid phase component and solid particle active force in propellant, it is another
Aspect introduces polyfunctional group component, improves HTPB/IPDI curing system crosslinking points, increases crosslink density, to improve propellant
Tensile strength.Reducing the technological approaches that Pressure Exponent is taken is to reduce Pressure Exponent using new and effective Pressure Exponent regulator,
The Pressure Exponent regulator is organic alkaline earth metal salts, utilizes alkali earth metal compound easy-clear carbon distribution and elimination
The decomposition segment of the easy second-time burning of CXHY class, reduces the combustion heat of reaction zone, its transmitting heat to cohesion item is reduced, thus real
Now to effective control of high-pressure section burn rate, reduce Pressure Exponent.
Propellant curing agent uses isophorone diisocyanate (IPDI), with conventional solidified dose of toluene di-isocyanate(TDI)
(TDI) it compares, Composite Propellant Slurry initial viscosity is low, and viscosity build is slow, and medicine slurry processing performance is excellent, is conducive to improve propellant
Casting quality.Since end hydroxy butadiene (HTPB) and isophorone diisocyanate (IPDI) reaction speed are lower than and toluene
Diisocyanate (TDI) needs to add suitable curing catalysts triphenyl bismuth (TPB) in formula, to solve above-mentioned background technique
The problem of middle proposition.
To achieve the above object, the invention provides the following technical scheme:
A kind of high intensity low pressure index HTPB composite propellant, the component including following mass percent: oxidant 73%
~ 73.5%, metal powder 14%, binding system 5.95%, plasticizer 3.5%, burningrate catalyst 2%, Pressure Exponent regulator 0.5% ~
1%, bonding agent and reinforcing agent 0.4%, curing catalysts and anti-aging agent 0.15%.
As a further solution of the present invention: the oxidant is ammonium perchlorate, and metal powder is aluminium powder.
As a further solution of the present invention: there are three types of specifications for the ammonium perchlorate, are GJB617A-2003 " ammonium perchlorate
Specification " in II type of B grade, III type and use II type ammonium perchlorate air-flow crushing after fine granularity ammonium perchlorate；Aluminium powder is
FLQT1 type in GJB1738A-2005 " special atomized aluminium specification ".
As a further solution of the present invention: the binding system includes adhesive and curing agent, and adhesive is terminal hydroxy group
Polybutadiene, I or II type in GJB1327A-2003 " end hydroxy butadiene specification "；Curing agent is two isocyanide of isophorone
Acid esters, AR grades.
As a further solution of the present invention: the plasticizer is decanedioic acid two (2- ethyl hexyl) ester, meets GJB1967-
1994 " decanedioic acid two (2- ethyl hexyl) ester specifications " requirement.
As a further solution of the present invention: the burningrate catalyst is octyl ferrocene, and it is " pungent to meet GJB5970-2007
Base ferrocene specification " it requires.
As a further solution of the present invention: the curing catalysts are triphenyl bismuth, meet GJB5276-2003 " triphen
Base bismuth specification " it requires.
As a further solution of the present invention: the anti-aging agent is DPPD N,N' diphenyl p phenylene diamine.
A kind of preparation method of high intensity low pressure index HTPB composite propellant, includes the following steps:
(1) solid raw material preliminary drying: ammonium perchlorate and aluminium powder are sieved, and ammonium perchlorate is put in 60 DEG C ~ 70 DEG C baking ovens, and aluminium powder is put in
50 DEG C ~ 60 DEG C baking ovens, preliminary drying 12h or more；
(2) it weighs, premix: by quality proportioning requirement, various raw material are weighed, by Pressure Exponent regulator, adhesive, plasticising
Agent, burningrate catalyst bonding agent, reinforcing agent, curing catalysts and anti-aging agent are premixed, and aluminium powder premix is then added；
(3) it mixes: oxidant being added by several times in premix medicine slurry and is uniformly mixed, curing agent mixing is added, using vertical mixer
It is mixed and made into the excellent Composite Propellant Slurry of processing performance；
(3) it is poured: Composite Propellant Slurry being poured at 50 DEG C ~ 60 DEG C using vacuum pouring method, is poured overbottom pressure≤10mmHg in cylinder；
(4) solidify: the mold that Composite Propellant Slurry is housed and motor body are heating and curing, solidification temperature is 55 ± 2 DEG C, solidification
Time 6 ~ 7 days.
As further scheme of the invention: premix temperature in step (2): 55 ± 2 DEG C, doing time in advance: 30 ~ 40min；
50 ~ 60min of incorporation time in step (3) plus before curing agent, adds 40 ~ 50min of incorporation time after curing agent, and mixing temperature is 60 ±
2℃。
Compared with prior art, the beneficial effects of the present invention are:
The present invention is applied in combination by bonding agent (JHJ) and reinforcing agent (BQJ), can be made at+20 DEG C of composite solidpropellant, tension
Intensity is greater than 2.5Mpa, is used by efficient Pressure Exponent regulator, reaches+20 DEG C, and under 10 ~ 22MPa, dynamic pressure index is small
In 0.20.The propellant is applicable to high overload, High Voltage working condition rocket projectile, the powder charge of guided missile solid engines (especially
End combustion Grain with liner) demand.
Detailed description of the invention
Fig. 1 is a kind of preparation method flow diagram of high-intensitive low pressure index HTPB composite propellant.
Fig. 2 is burn rate and operating pressure in a kind of preparation method of high-intensitive low pressure index HTPB composite propellant
Relation schematic diagram.
Specific embodiment
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation description, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts every other
Embodiment shall fall within the protection scope of the present invention.
In the present invention, a kind of high intensity low pressure index HTPB composite propellant, by mass percentage, formula is matched
Than being shown in Table 1:
The high-intensitive low pressure index HTPB composite propellant formulation ratio of table 1
The solid content of the propellant is the sum of oxidant and metal powder, and mechanical properties of propellant passes through formulation parameter tune
Section, formulation parameter calculation formula are as follows: RI = n(NCO - )/n(OH - ) × 100%, in which: n(NCO - ): isocyano in curing agent IPDI
Molal quantity；n(OH - ): hydroxyl moles in adhesive HTPB and bonding agent.
The ammonium perchlorate there are three types of specification, be II type of B grade in GJB617A-2003 " ammonium perchlorate specification ", III type with
And using the fine granularity ammonium perchlorate after II type ammonium perchlorate air-flow crushing；Aluminium powder is GJB1738A-2005 " special atomized aluminium rule
Model " in FLQT1 type.Adhesive is I or II type in GJB1327A-2003 " end hydroxy butadiene specification "；Curing agent is
Isophorone diisocyanate, AR grades；The plasticizer meets GJB1967-1994 " decanedioic acid two (2- ethyl hexyl) ester specification "
It is required that；The burningrate catalyst meets GJB5970-2007 " octyl ferrocene specification " requirement；The curing catalysts meet
GJB5276-2003 " triphenyl bismuth specification " requirement.
Formula in the present invention about Pressure Exponent regulator is shown in an other patent that our company applies on the same day, specially
Sharp title are as follows: a kind of Pressure Exponent regulator of composite solidpropellant, the Pressure Exponent regulator by oxamides (OA) with
Strontium carbonate (SrCO3) compounds.
A kind of preparation method of high intensity low pressure index HTPB composite propellant, includes the following steps:
(1) solid raw material preliminary drying: ammonium perchlorate and aluminium powder are sieved, and ammonium perchlorate is put in 60 DEG C ~ 70 DEG C baking ovens, and aluminium powder is put in
50 DEG C ~ 60 DEG C baking ovens, preliminary drying 12h or more；
(2) it weighs, premix: by quality proportioning requirement, weighing various raw material.By Pressure Exponent regulator, terminal hydroxy group polybutadiene
Alkene, decanedioic acid two (2- ethyl hexyl) ester, octyl ferrocene, bonding agent, reinforcing agent, curing catalysts and anti-aging agent are premixed,
Then aluminium powder premix is added.Premix temperature: it 55 ± 2 DEG C, does time in advance: 30 ~ 40min；
(3) it mixes: perchloric acid is added by several times in premix medicine slurry by being uniformly mixed, curing agent isophorone diisocyanate is added
Mixing, is mixed and made into the excellent Composite Propellant Slurry of processing performance using vertical mixer.Add incorporation time 50 before curing agent ~
60min, adds 40 ~ 50min of incorporation time after curing agent, and mixing temperature is 60 ± 2 DEG C；
(3) it is poured: Composite Propellant Slurry being poured at 50 DEG C ~ 60 DEG C using vacuum pouring method, is poured overbottom pressure≤10mmHg in cylinder；
(4) solidify: the mold that Composite Propellant Slurry is housed and motor body are heating and curing, solidification temperature is 55 ± 2 DEG C, solidification
Time 6 ~ 7 days.
In the present invention, a kind of high intensity low pressure index HTPB composite propellant, using 2 kinds of embodiments to the application
The formula of middle solid propellant is illustrated, and specific proportion is shown in Table 2:
The high-intensitive low pressure index HTPB composite propellant formulation ratio of table 2
Preparation technology flow chart in refering to fig. 1, now in conjunction with a kind of 2 pairs of embodiment inexpensive inertia HTPB composite propellants
Preparation method be illustrated, FG-XX engine (powder charge lot number 2018-01-01 ~ 10) is using 2 powder charge of embodiment in table 2.Through
The defects of X-ray check, powder column pore-free, crackle, charge constitution integrality are good.Room temperature (+20 DEG C) tensile strength 2.79MPa；+20
DEG C, it under 9 ~ 21MPa, is tested by 118 standard testing motor of Φ, dynamic pressure index is 0.1714.Specific performance is shown in Table 3
3 FG-XX engine of table (powder charge lot number 2018-01-01 ~ 10) performance of propellant
Referring to Fig.2 ,+20 DEG C, under 9-21MPa, propellant dynamic pressure index is 0.1714, burn rate and operating pressure relationship.
The present invention is applied in combination by bonding agent (JHJ) and reinforcing agent (BQJ), is adjusted using new and effective Pressure Exponent
Agent improves propellant tensile strength, reduces Pressure Exponent under High Voltage, is applicable to high overload, High Voltage working condition rocket
Bullet, guided missile solid engines powder charge (especially end combustion Grain with liner) demand.
The present invention is applied in combination by using bonding agent, addition reinforcing agent, raising propellant tensile strength, and+20 DEG C
Under, tensile strength is greater than 2.5MPa.It is used by Pressure Exponent regulator, reduction propellant Pressure Exponent ,+20 DEG C, 10 ~
Under 22MPa, dynamic pressure index is less than 0.20.The propellant can meet high overload solid engines end combustion Grain with liner powder charge need
It asks.Under High Voltage, propellant Pressure Exponent is low, flameholding, can satisfy High Voltage work solid engines powder charge demand.
It is obvious to a person skilled in the art that invention is not limited to the details of the above exemplary embodiments, Er Qie
In the case where without departing substantially from spirit or essential attributes of the invention, the present invention can be realized in other specific forms.Therefore, no matter
From the point of view of which point, the present embodiments are to be considered as illustrative and not restrictive, and the scope of the present invention is by appended power
Benefit requires rather than above description limits, it is intended that all by what is fallen within the meaning and scope of the equivalent elements of the claims
Variation is included within the present invention.
In addition, it should be understood that although this specification is described in terms of embodiments, but not each embodiment is only wrapped
Containing an independent technical solution, this description of the specification is merely for the sake of clarity, and those skilled in the art should
It considers the specification as a whole, the technical solutions in the various embodiments may also be suitably combined, forms those skilled in the art
The other embodiments being understood that.
Claims (10)
1. a kind of high intensity low pressure index HTPB composite propellant, which is characterized in that including following mass percent
Component: oxidant 73% ~ 73.5%, metal powder 14%, binding system 5.95%, plasticizer 3.5%, burningrate catalyst 2%, pressure refers to
Number regulator 0.5% ~ 1%, bonding agent and reinforcing agent 0.4%, curing catalysts and anti-aging agent 0.15%.
2. a kind of high-intensitive low pressure index HTPB composite propellant according to claim 1, which is characterized in that institute
Stating oxidant is ammonium perchlorate, and metal powder is aluminium powder.
3. a kind of high-intensitive low pressure index HTPB composite propellant according to claim 2, which is characterized in that institute
Ammonium perchlorate is stated there are three types of specification, is II type of II type of B grade, III type and use in GJB617A-2003 " ammonium perchlorate specification "
Fine granularity ammonium perchlorate after ammonium perchlorate air-flow crushing；Aluminium powder is the FLQT1 in GJB1738A-2005 " special atomized aluminium specification "
Type.
4. a kind of high-intensitive low pressure index HTPB composite propellant according to claim 1, which is characterized in that institute
Stating binding system includes adhesive and curing agent, and adhesive is end hydroxy butadiene, GJB1327A-2003 " the poly- fourth of terminal hydroxy group
Diene specification " in I or II type；Curing agent is isophorone diisocyanate, AR grades.
5. a kind of high-intensitive low pressure index HTPB composite propellant according to claim 1, which is characterized in that institute
Stating plasticizer is decanedioic acid two (2- ethyl hexyl) ester, meets GJB1967-1994 " decanedioic acid two (2- ethyl hexyl) ester specification " and wants
It asks.
6. a kind of high-intensitive low pressure index HTPB composite propellant according to claim 1, which is characterized in that institute
Stating burningrate catalyst is octyl ferrocene, meets GJB5970-2007 " octyl ferrocene specification " requirement.
7. a kind of high-intensitive low pressure index HTPB composite propellant according to claim 1, which is characterized in that institute
Stating curing catalysts is triphenyl bismuth, meets GJB5276-2003 " triphenyl bismuth specification " requirement.
8. a kind of high-intensitive low pressure index HTPB composite propellant according to claim 1, which is characterized in that institute
Stating anti-aging agent is DPPD N,N' diphenyl p phenylene diamine.
9. a kind of preparation method of high intensity low pressure index HTPB composite propellant, which is characterized in that including walking as follows
It is rapid:
(1) solid raw material preliminary drying: ammonium perchlorate and aluminium powder are sieved, and ammonium perchlorate is put in 60 DEG C ~ 70 DEG C baking ovens, and aluminium powder is put in
50 DEG C ~ 60 DEG C baking ovens, preliminary drying 12h or more；
(2) it weighs, premix: by quality proportioning requirement, various raw material are weighed, by Pressure Exponent regulator, adhesive, plasticising
Agent, burningrate catalyst bonding agent, reinforcing agent, curing catalysts and anti-aging agent are premixed, and aluminium powder premix is then added；
(3) it mixes: oxidant being added by several times in premix medicine slurry and is uniformly mixed, curing agent mixing is added, using vertical mixer
It is mixed and made into the excellent Composite Propellant Slurry of processing performance；
(3) it is poured: Composite Propellant Slurry being poured at 50 DEG C ~ 60 DEG C using vacuum pouring method, is poured overbottom pressure≤10mmHg in cylinder；
(4) solidify: the mold that Composite Propellant Slurry is housed and motor body are heating and curing, solidification temperature is 55 ± 2 DEG C, solidification
Time 6 ~ 7 days.
10. a kind of preparation method of high-intensitive low pressure index HTPB composite propellant according to claim 9,
It is characterized in that, premix temperature in step (2): 55 ± 2 DEG C, does time in advance: 30 ~ 40min；It is mixed in step (3) plus before curing agent
50 ~ 60min of time, adds 40 ~ 50min of incorporation time after curing agent, and mixing temperature is 60 ± 2 DEG C.
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110689640A (en) * | 2019-09-20 | 2020-01-14 | 华中科技大学 | Risk judgment method for composite propellant mixed torque |
| CN110713428A (en) * | 2019-11-06 | 2020-01-21 | 湖北航天化学技术研究所 | Casting type high polymer bonded explosive |
| CN110885280A (en) * | 2019-12-05 | 2020-03-17 | 西北工业大学 | Composite solid propellant based on nitramine oxidant coated aluminum powder and preparation method thereof |
| CN111632326A (en) * | 2020-06-10 | 2020-09-08 | 湖北航天化学技术研究所 | Thermal runaway detection device and application thereof |
| CN111704516A (en) * | 2020-05-20 | 2020-09-25 | 湖北三江航天江河化工科技有限公司 | Hydroxyl-terminated aluminum-free propellant and preparation method thereof |
| CN111747805A (en) * | 2020-07-24 | 2020-10-09 | 湖北航天化学技术研究所 | High-temperature condensed phase particle generating agent and preparation method thereof |
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| US4597811A (en) * | 1985-07-03 | 1986-07-01 | The United States Of America As Represented By The Secretary Of The Army | Prevention of unwanted cure catalysis in isocyanate cured binders |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110689640A (en) * | 2019-09-20 | 2020-01-14 | 华中科技大学 | Risk judgment method for composite propellant mixed torque |
| CN110713428A (en) * | 2019-11-06 | 2020-01-21 | 湖北航天化学技术研究所 | Casting type high polymer bonded explosive |
| CN110713428B (en) * | 2019-11-06 | 2021-07-23 | 湖北航天化学技术研究所 | Casting type high polymer bonded explosive |
| CN110885280A (en) * | 2019-12-05 | 2020-03-17 | 西北工业大学 | Composite solid propellant based on nitramine oxidant coated aluminum powder and preparation method thereof |
| CN110885280B (en) * | 2019-12-05 | 2024-01-05 | 西北工业大学 | Composite solid propellant based on nitramine oxidant coated aluminum powder and preparation method thereof |
| CN111704516A (en) * | 2020-05-20 | 2020-09-25 | 湖北三江航天江河化工科技有限公司 | Hydroxyl-terminated aluminum-free propellant and preparation method thereof |
| CN111704516B (en) * | 2020-05-20 | 2022-01-18 | 湖北三江航天江河化工科技有限公司 | Hydroxyl-terminated aluminum-free propellant and preparation method thereof |
| CN111632326A (en) * | 2020-06-10 | 2020-09-08 | 湖北航天化学技术研究所 | Thermal runaway detection device and application thereof |
| CN111747805A (en) * | 2020-07-24 | 2020-10-09 | 湖北航天化学技术研究所 | High-temperature condensed phase particle generating agent and preparation method thereof |
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Application publication date: 20190823 |