CN108586176A - A kind of propellant - Google Patents
A kind of propellant Download PDFInfo
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- CN108586176A CN108586176A CN201810636007.0A CN201810636007A CN108586176A CN 108586176 A CN108586176 A CN 108586176A CN 201810636007 A CN201810636007 A CN 201810636007A CN 108586176 A CN108586176 A CN 108586176A
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- Prior art keywords
- parts
- propellant
- added
- mixing
- toluene
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Classifications
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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
-
- 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)
- Engineering & Computer Science (AREA)
- Organic Chemistry (AREA)
- Inorganic Chemistry (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Combustion & Propulsion (AREA)
- Adhesives Or Adhesive Processes (AREA)
Abstract
The invention discloses a kind of propellants, including following components by weight：0.05 ~ 0.1 part of 69 70 parts of oxidant, 18 19 parts of metal powder, 8.0 8.3 parts of adhesive, 3 parts of plasticizer, 0.7 1.0 parts of burningrate catalyst, 0.2 part of process auxiliaries and bonding agent；Described adhesive is by end hydroxy butadiene, toluene di-isocyanate(TDI), antioxidant H, three（2 methyl, 1 aziridine）Phosphorous oxide forms.The present invention reduces the formula cost of raw material by using novel burningrate catalyst, cheap, high catalytic efficiency；It is the 1/2 of raw catalyst cost.And the propellant prepared reaches high intensity by the component proportion of adjusting adhesive composition（≥1.3MPa）Effect is suitable for heavy launcher piecemeal powder charge.In addition, the performance of propellant prepared is stablized, processing performance is good, wide market.
Description
Technical field
The invention belongs to composite solidpropellant manufacturing technology fields, and in particular to a kind of propellant.
Background technology
The continuous development in the civil aerospace technologies such as commercial satellite, space tourism market, the progress of especially micro-nano satellite technology,
So that low orbit space is increasingly crowded, space trash is continuously increased so that low orbit space resources is increasingly deficient.Either space
The contention of military strategy advantage or the commercial competition of civil aerospace technology market fierceness, the contention of high orbit space resources increasingly carry
Upper agenda.
The contention of high orbit space resources is the game of various countries' heavy type carrying capacity after all.Solid propellant rocket has
There is the features such as thrust is big, simple in structure, manufacturing cost is low, fast response time, either faces war emergency state, or peace
Period fast-changing market environment, advantage is had more compared with liquid-propellant rocket engine.
Traditional composite solidpropellant shows charge process：Dispensing-mixing machine kneading-vacuum pouring-hot setting molding,
General solidification 7~10 days.But for heavy launcher, explosive payload is up to tons up to a hundred, and such as according to traditional mode, medicine slurry is poured
During note, the medicine slurry that bottom is first poured into a mould may have been cured, and product quality can not ensure.Domestic and international heavy launcher powder charge
Mostly use the modes such as decking, multistage docking.Though decking can reduce labor intensity and equipment continuation rate, every time
Decking is that band medicine operates, and there are certain security risks.Though multistage docking can make overall thrust reach expected requirement,
Per stage motor shell and heat insulation layer etc., passive quality increases, and is also unfavorable for the production of heavy launcher.
For heavy launcher, the country proposes the powder charge thinking of " piecemeal powder charge, combination bond ", by heavy type delivery fire
The powder charge of arrow is divided into several independent powder columns, then these powder columns are combined and are bonded, and eventually forms complete powder charge combustion chamber, meets
The thrust requirements of heavy launcher.According to this mentality of designing, piecemeal medicine block must have enough intensity, to ensure to bond
In the process, it not by pressure break, drawing crack, and does not avoid bonding dimensional discrepancy, the size Control of each medicine block is also more stringent, needs
A kind of composite solidpropellant of high intensity.
Invention content
In order to solve the above technical problem, the present invention provides a kind of propellant, it is made to meet heavy launcher explosive payload
Big requirement.
The technical solution used in the present invention is a kind of propellant, including following components by weight：Oxidant
70 parts of 69-, 18-19 parts of metal powder, 8.0-8.3 parts of adhesive, 3 parts of plasticizer, 0.7-1.0 parts of burningrate catalyst, process auxiliaries
0.2 part and 0.05~0.1 part of bonding agent；Described adhesive is by end hydroxy butadiene (HTPB), toluene di-isocyanate(TDI)
(TDI), antioxidant H (FH), three (2- methyl-1s-aziridine) phosphorous oxides (MAPO) composition,
Further, the oxidant is ammonium perchlorate (AP)；Metal powder is metallic aluminium powder (Al).The burningrate catalyst
It is pungent (Fe-C) for Otto, it is provided by Shanghai Organic Chemistry Institute, Chinese Academy of Sciences, internal code is the FC-1601 products
Patent applied for, application No. is 201818001444.6.
Further, the ammonium perchlorate is I type, III type and self-control, and self-control is the ultrafine ammonium perchlorate after crushing, grain
≤ 10 μm of degree；Ratio between specific three is adjusted according to the performance requirement of propellant.Aluminium powder is FLQT2 types.
Further, end hydroxy butadiene and toluene di-isocyanate(TDI) are 7.75~8.10 parts, prevent in described adhesive
Old agent H is 0.10 part, three (2- methyl-1s-aziridine) phosphorous oxides are 0.10~0.15 part.
Further, the end hydroxy butadiene is III type, and toluene di-isocyanate(TDI) is II type.
Further, the plasticizer is Plexol 201 (DOS), and process auxiliaries are methyl stearate (YZSZ),
Bonding agent be alcamines LBA-303, be it is a kind of have excellent performance, cheap bonding agent.
The invention further relates to the methods for preparing the propellant, include the following steps：
1) end hydroxy butadiene, three (2- methyl-1s-aziridine) phosphorous oxide, process auxiliaries, bonding agent and burn rates are urged
Agent is premixed；
2) part plasticizer mixing is added, antioxidant H and metal powder mixing is then added, sequentially adds partial oxidation agent
Mixing, remaining plasticizer mixing, residual oxidizing agent mixing；It is eventually adding toluene di-isocyanate(TDI) and is uniformly mixed so as to obtain grout, pour into a mould
To die for molding, up to propellant medicine block after solidification.
Further, the temperature that step 1) premix is is 50 ± 2 DEG C, incorporation time 20-40min.
Further, the temperature mixed in step 2) is 50 ± 2 DEG C, and the incorporation time being added after plasticizer is 10-
20min, the incorporation time being added after oxidant are 30-60min, and it is 20- that the time mixed after antioxidant H and metal powder, which is added,
30min, the incorporation time being added after toluene di-isocyanate(TDI) are 25-40min.
Further, vacuum condition when cast, temperature are 50 ± 2 DEG C, and solidification temperature is 50 ± 2 DEG C, time 6-10
It.
In propellant formulation, end hydroxy butadiene, toluene di-isocyanate(TDI), antioxidant H, three (2- methyl-1s-nitrogen are selected
Third pyridine) phosphorous oxide combination, formed composite solidpropellant cure cross-linked network system.Improve medicine slurry craftsmanship by plasticizer
Energy.The oxidant used is ammonium perchlorate, technical maturity, and supply channel is stablized.Burningrate catalyst Otto is pungent with the pungent effect of Kato
Quite, but it is cheap.Process auxiliaries can reduce binder molecule intermolecular forces, promote the locomitivity of adhesive, increase
Solid phase, the effect of impregnation of liquid phase.Bonding agent enhances the interface interaction power of oxidant and adhesive composition, promotes the mechanics of propellant
Performance.
In propellant formulation, HTPB selects III type, has lower viscosity, and hydroxyl value is high, easily reaches high intensity, mechanics
Performance is stablized compared with IV type.TDI selects II type, and solidification point is high, need not keep the temperature, be conducive to pharmaceutical technology.DOS is that propellant is common
Plasticizer, can effectively reduce the viscosity of HTPB, be easily mixed uniformly.Al granularities use FLQT2 types, combustibility to stablize, and
Conducive to dispersion.Fe-C is burn rate high catalytic efficiency and the novel burningrate catalyst of price inexpensively.
In preparation process,
1) since MAPO, YZSZ, LBA-303, Fe-C dosage are less, to ensure uniformity, first by different materials and HTPB
It is mixed evenly, ensures stability.
2) plus 2/3DOS is to be conducive to subsequently add solid packing to reduce the viscosity of adhesive composition, reduces mixing
Machine torque.
3) part AP is added in batches, repeatedly mediates, ensures mixing uniformity.
4) when medicine slurry is more dry, residue DOS is added, avoids mixing machine torque excessive, reduce security risk.
The present invention is by using novel burningrate catalyst, cheap, high catalytic efficiency, reduce formula raw material at
This；It is the 1/2 of raw catalyst cost.And the propellant prepared reaches high intensity by the component proportion of adjusting adhesive composition
(>=1.3MPa) effect, it is suitable for heavy launcher piecemeal powder charge.In addition, the performance of propellant prepared is stablized, processing performance
It is good, wide market.
Description of the drawings
Fig. 1 is the preparation technology flow chart of propellant.
Specific implementation mode
It is further illustrated the present invention with reference to embodiment, but the scope of protection of present invention is not limited to implement
The range of example statement.
Propellant formulation in embodiment 1-4 is specifically shown in the following table 1.
Table 1
Shown in specific preparation technology flow chart 1.The medicine blocks of certain XX-67/S001~006 use the formula powder charge in upper table 1, medicine
Rod structure integrality is good, internal zero defect, room temperature tensile strength >=1.3MPa, and density, burn rate etc. are satisfied by requirement.Specific performance
It see the table below：
Table 2
The above embodiments are only the preferred technical solution of the present invention, and are not construed as the limitation for the present invention, this hair
Technical characteristic in the technical solution that bright protection domain should be recorded with claim, including the technical solution of claim record
Equivalents are protection domain.Equivalent replacement i.e. within this range is improved, also within protection scope of the present invention.
Claims (10)
1. a kind of propellant, which is characterized in that including following components by weight：69-70 parts of oxidant, metal powder 18-
19 parts, 8.0-8.3 parts of adhesive, 3 parts of plasticizer, 0.7-1.0 parts of burningrate catalyst, 0.2 part of process auxiliaries and bonding agent 0.05 ~
0.1 part；Described adhesive is by end hydroxy butadiene, toluene di-isocyanate(TDI), antioxidant H, three（2- methyl-1s-aziridine）Oxygen
Change phosphorus composition.
2. propellant according to claim 1, it is characterised in that：The oxidant is ammonium perchlorate；Metal powder is metal
Aluminium powder.
3. propellant according to claim 2, it is characterised in that：The ammonium perchlorate is I type, III type and self-control, wherein
Make ammonium perchlorate particle size≤10 μm by oneself；Aluminium powder is FLQT2 types.
4. propellant according to claim 1, it is characterised in that：End hydroxy butadiene and toluene two in described adhesive
Isocyanates is 7.75 ~ 8.10 parts, antioxidant H is 0.10 part, three（2- methyl-1s-aziridine）Phosphorous oxide is 0.10 ~ 0.15 part.
5. propellant according to claim 4, it is characterised in that：The end hydroxy butadiene is III type, and toluene two is different
Cyanate is II type.
6. propellant according to claim 1, it is characterised in that：The plasticizer is Plexol 201, and technique helps
Agent is methyl stearate, and bonding agent is alcamines LBA-303.
7. the method for preparing propellant described in claim 1-6 any one, which is characterized in that include the following steps：
1）By end hydroxy butadiene, three（2- methyl-1s-aziridine）Phosphorous oxide, process auxiliaries, bonding agent and burningrate catalyst
It is premixed；
2）Part plasticizer mixing is added, antioxidant H and metal powder mixing is then added, it is mixed to sequentially add partial oxidation agent
Even, remaining plasticizer mixing, residual oxidizing agent mixing；It is eventually adding toluene di-isocyanate(TDI) and is uniformly mixed so as to obtain grout, be poured into
Die for molding, up to propellant medicine block after solidification.
8. according to the method described in claim 7, it is characterised in that：Step 1）Temperature when premix is 50 ± 2 DEG C, when mixing
Between be 20-40min.
9. according to the method described in claim 7, it is characterised in that：Step 2）The temperature of middle mixing is 50 ± 2 DEG C, is added and increases
It is 10-20min to mould the incorporation time after agent, and the incorporation time being added after oxidant is 30-60min, and antioxidant H and metal is added
The time mixed after powder is 20-30min, and the incorporation time being added after toluene di-isocyanate(TDI) is 25-40min.
10. according to the method described in claim 7, it is characterised in that：Vacuum condition when cast, temperature are 50 ± 2 DEG C, solidification
Temperature is 50 ± 2 DEG C, and the time is 6-10 days.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810636007.0A CN108586176A (en) | 2018-06-20 | 2018-06-20 | A kind of propellant |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810636007.0A CN108586176A (en) | 2018-06-20 | 2018-06-20 | A kind of propellant |
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| Publication Number | Publication Date |
|---|---|
| CN108586176A true CN108586176A (en) | 2018-09-28 |
Family
ID=63628792
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810636007.0A Pending CN108586176A (en) | 2018-06-20 | 2018-06-20 | A kind of propellant |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109305869A (en) * | 2018-10-31 | 2019-02-05 | 湖北航天化学技术研究所 | A kind of carborane propellant and preparation method thereof |
| CN109438147A (en) * | 2018-12-26 | 2019-03-08 | 湖北航天化学技术研究所 | A kind of HTPB base casting composite explosives formula that processing performance improves |
| CN110204408A (en) * | 2019-07-03 | 2019-09-06 | 江西航天经纬化工有限公司 | A kind of low cost inertia HTPB composite propellant and preparation method thereof |
| CN110330395A (en) * | 2019-08-06 | 2019-10-15 | 湖北航天化学技术研究所 | A kind of high intensity HTPB propellant and preparation method thereof |
| 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 |
| CN114371122A (en) * | 2021-12-13 | 2022-04-19 | 湖北三江航天江河化工科技有限公司 | Method for improving interface bonding performance of IPDI (isophorone diisocyanate) type butylated hydroxytoluene propellant and lining |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3879322A (en) * | 1972-12-25 | 1975-04-22 | Nissan Motor | Fuel binder for composite propellant |
| CN104277754A (en) * | 2013-07-29 | 2015-01-14 | 湖北航天化学技术研究所 | Combustion-restricted layer material applied to NEPE (Nitrate Ester Plasticized Polyether) propellant and preparation method of combustion-restricted layer material |
| CN107867961A (en) * | 2017-08-18 | 2018-04-03 | 湖北航天化学技术研究所 | Improve the method for HTPB propellant mechanical property and the HTPB propellant of preparation |
-
2018
- 2018-06-20 CN CN201810636007.0A patent/CN108586176A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3879322A (en) * | 1972-12-25 | 1975-04-22 | Nissan Motor | Fuel binder for composite propellant |
| CN104277754A (en) * | 2013-07-29 | 2015-01-14 | 湖北航天化学技术研究所 | Combustion-restricted layer material applied to NEPE (Nitrate Ester Plasticized Polyether) propellant and preparation method of combustion-restricted layer material |
| CN107867961A (en) * | 2017-08-18 | 2018-04-03 | 湖北航天化学技术研究所 | Improve the method for HTPB propellant mechanical property and the HTPB propellant of preparation |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109305869A (en) * | 2018-10-31 | 2019-02-05 | 湖北航天化学技术研究所 | A kind of carborane propellant and preparation method thereof |
| CN109305869B (en) * | 2018-10-31 | 2021-04-30 | 湖北航天化学技术研究所 | Carborane propellant and preparation method thereof |
| CN109438147A (en) * | 2018-12-26 | 2019-03-08 | 湖北航天化学技术研究所 | A kind of HTPB base casting composite explosives formula that processing performance improves |
| CN110204408A (en) * | 2019-07-03 | 2019-09-06 | 江西航天经纬化工有限公司 | A kind of low cost inertia HTPB composite propellant and preparation method thereof |
| CN110330395A (en) * | 2019-08-06 | 2019-10-15 | 湖北航天化学技术研究所 | A kind of high intensity HTPB propellant and preparation method thereof |
| CN110330395B (en) * | 2019-08-06 | 2021-06-22 | 湖北航天化学技术研究所 | High-strength butylated hydroxytoluene propellant and preparation method thereof |
| 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 |
| CN114371122A (en) * | 2021-12-13 | 2022-04-19 | 湖北三江航天江河化工科技有限公司 | Method for improving interface bonding performance of IPDI (isophorone diisocyanate) type butylated hydroxytoluene propellant and lining |
| CN114371122B (en) * | 2021-12-13 | 2024-09-06 | 湖北三江航天江河化工科技有限公司 | Method for improving interfacial adhesion performance of IPDI type butyl hydroxy propellant and lining |
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Application publication date: 20180928 |