CN106938965A - A kind of nitric acid ammonium low burn temperature clean fuel gas propellant - Google Patents
A kind of nitric acid ammonium low burn temperature clean fuel gas propellant Download PDFInfo
- Publication number
- CN106938965A CN106938965A CN201610891074.8A CN201610891074A CN106938965A CN 106938965 A CN106938965 A CN 106938965A CN 201610891074 A CN201610891074 A CN 201610891074A CN 106938965 A CN106938965 A CN 106938965A
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- CN
- China
- Prior art keywords
- nitric acid
- fuel gas
- acid ammonium
- clean fuel
- low burn
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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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
- C06B31/00—Compositions containing an inorganic nitrogen-oxygen salt
- C06B31/28—Compositions containing an inorganic nitrogen-oxygen salt the salt being ammonium nitrate
-
- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B21/00—Apparatus or methods for working-up explosives, e.g. forming, cutting, drying
- C06B21/0033—Shaping the mixture
- C06B21/0058—Shaping the mixture by casting a curable composition, e.g. of the plastisol type
-
- 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
Abstract
A kind of nitric acid ammonium low burn temperature clean fuel gas propellant, includes ammonium nitrate：65% ~ 80%, the warm conditioning agent of combustion：0%~15%；Special additive：0% ~ 2%, adhesive：10% ~ 20%, curing agent：0.5% ~ 2.0%, other additives：2.0% ~ 6.0%, special additive is one kind or the combination of chrome green or vanadic anhydride, adhesive is terminal hydroxy group PEO tetrahydrofuran, and curing agent is one kind or the combination of IPDI or toluene di-isocyanate(TDI) or modified six methine polyisocyanates.The gas generator propellant that the present invention is produced, raw material are free of metal powder, the features such as can easily be accommodated with low burn temperature, combustion gas cleaning and non-corrosiveness gas, low residue and performance, available for the conventional weapon auxiliary power source of wide Acclimation temperature scope, the auxiliary power source for having particular/special requirement to combustion gas is especially applicable for.
Description
Technical field
The invention belongs to composite solidpropellant gas generator propellant field, in particular it relates to which a kind of be used for combustion gas
The low burn temperature clean fuel gas propellant of generator and other gas generators.
Background technology
Gas generator propellant is a branch of composite solidpropellant, and the combustion gas produced of burning is as driving auxiliary power dress
The working medium put, converts chemical energy into mechanical or electrical energy.Because gas generator is simple in construction, it is light weight, easy to use, it
It is widely used in liquid rocket turbine starter, booster, solid-rocket guided missile Thrust vector control, body and bullet are rolled
The servo-drive system of control, catapult-launching gear, the upender of car launcher, the field such as last boosting and turbo-dynamo and servos control.
Now conventional weapon auxiliary power unit in part proposes requirements at the higher level to gas generator propellant, is in particular in and requires combustion gas
Propellant has that ignition temperature is low, combustion gas is clean and the low performance characteristics of non-corrosiveness hydrogen chloride gas, residue simultaneously, and performance
It can easily be accommodated, for meeting the design requirement of increasingly complicated gas generator propellant.
The content of the invention
The present invention solve the problem of be：The deficiencies in the prior art are overcome to provide a kind of without metal powder, low combustion temperature, combustion
The nitric acid ammonium low burn temperature clean fuel gas propellant that gas cleaning and non-corrosiveness gas, low residue and performance can easily be accommodated.
Present invention also offers the preparation method of above-mentioned nitric acid ammonium low burn temperature clean fuel gas propellant.
In addition to being described, the ratio used in the present invention is quality proportioning.
The present invention technical solution be：A kind of nitric acid ammonium low burn temperature clean fuel gas propellant, including following masses
Percentage component：
Ammonium nitrate：65% ~ 80%,
The warm conditioning agent of combustion：0% ~ 15%,
Special additive：0% ~ 2%,
Adhesive：10% ~ 20%,
Curing agent：0.5% ~ 2.0%,
Other additives：2.0%~6.0%.
The present invention optimization formula be：
Ammonium nitrate：70% ~ 75%,
The warm conditioning agent of combustion：5%~10%,
Special additive：0% ~ 2%,
Adhesive：12% ~ 16%,
Curing agent：1.0% ~ 1.5%,
Other additives：3%~5.0%.
The special additive is one kind or the combination of chrome green or vanadic anhydride.
Described adhesive is terminal hydroxy group PEO-tetrahydrofuran.
Described curing agent is IPDI or toluene di-isocyanate(TDI) or modified six methine polyisocyanates
One kind of cyanate or combination.
Described other additives are ATEC or lecithin or triphenyl bismuth or carbon black or three
[1,-（2- methylaziridines）] phosphine oxide or triethanolamine or N, N- diphenyl-para-phenylene diamine combination.
The preparation technology of the present invention includes：
（1）The component is weighed by above-mentioned selected formula rate；
（2）Said components are put into vertical mixer and mixed, 40 DEG C ~ 60 DEG C of mixing temperature, incorporation time 70min ~
110min, obtains slurry；
（3）Slime vacuum spray is poured into mould or is poured into engine, is then placed in 60 DEG C ~ 70 DEG C oil bath baking ovens
Solidification 5 ~ 7 days.
Present invention advantage compared with prior art is：
（1）Oxidant used by the present invention is common ammonium nitrate, the fuel gas temperature that nitric acid ammonium gas generator propellant is produced when burning
Low, burn rate is low, gas forming amount is big, low cost, it is safe the advantages of, while do not have in combustion gas perchloric acid ammonium type gas generator propellant produce
Hydrogen-chloride etching gas.
（2）Special additive used by the present invention is one kind or the combination of chrome green or vanadic anhydride, three oxidations
The addition of two chromium or vanadic anhydride can effectively reduce burn rate pressure while burn rate under improving gas generator propellant formula low pressure
Strong index；Formula burn rate can be made under 6.86MPa by using the regulation of amount, it is adjustable in the range of burn rate 0.5mm/s ~ 6mm/s,
Pressure Exponent（3MPa~9MPa）Less than 0.5 can be reduced to.
（3）The present invention can fire the ignition temperature with when addition regulation system of warm additive by adjusting, thus, have
Broader ignition temperature adjustable range, the conventional weapon auxiliary power source available for wide Acclimation temperature scope.
（4）The present invention is free of metal powder, and auxiliary agent used is the easy organic matter for decomposing aerogenesis in addition to special additive,
So as to obtain low residue formula.
The present invention solve processing performance of the nitric acid ammonium low burn temperature clean fuel gas propellant in wide ambient humidity range,
Mechanical property and the problem of combustibility regulation are there is provided one kind without metal powder, low combustion temperature, combustion gas cleaning and non-corrosiveness
The gas generator propellant that gas, low residue and performance can easily be accommodated, the conventional weapon auxiliary power available for wide Acclimation temperature scope
Source, is especially applicable for the auxiliary power source for having particular/special requirement to combustion gas.
Embodiment
With reference to embodiment, the present invention is described in detail, but the present invention is not limited only to embodiment.
Embodiment 1
（1）Gas generator propellant is constituted
| Formula composition | Mass percent（%） |
| Terminal hydroxy group PEO-tetrahydrofuran | 11.44 |
| Modified six methine polyisocyanates | 1.72 |
| Ammonium nitrate | 80 |
| Chrome green | 1.5 |
| Vanadic anhydride | 0.5 |
| ATEC | 4.54 |
| Carbon black | 0.1 |
| Lecithin | 0.1 |
| Three [1 ,-（2- methylaziridines）] phosphine oxide | 0.1 |
Preparation technology：
1st, said components are weighed by above-mentioned selected formula rate；
2nd, said components are put into vertical mixer and mixed, 40 DEG C of mixing temperature, incorporation time 110min obtains slurry；
3rd, slime vacuum spray is poured into mould or is poured into engine, be then placed in 60 DEG C ~ 70 DEG C oil bath baking ovens
Solidification 6 days.
（2）Gas generator propellant performance
| Specific impulse, N*s/kg | 2013 |
| Characteristic velocity, m/s | 1274 |
| Combustion gas mean molecule quantity, g/mol | 21.8 |
| Gas forming amount, L/kg | 1101 |
| Burn rate（6.86MPa）, mm/s | 4.5 |
| Pressure Exponent n（7MPa~13MPa） | 0.45 |
| Combustion temperature, K | 1714 |
| Residue content, % | 2.1 |
Embodiment 2
（1）Gas generator propellant is constituted
| Formula composition | Mass percent（%） |
| Terminal hydroxy group PEO-tetrahydrofuran | 11.62 |
| IPDI | 1.08 |
| Ammonium nitrate | 75 |
| Oxamides | 5 |
| Triphenyl bismuth | 0.1 |
| Vanadic anhydride | 2.0 |
| ATEC | 5.0 |
| Lecithin | 0.1 |
| Triethanolamine | 0.1 |
Preparation technology：
1st, said components are weighed by above-mentioned formula rate；
2nd, said components are put into vertical mixer and mixed, 60 DEG C of mixing temperature, incorporation time 70min obtains slurry；
3rd, slime vacuum spray is poured into mould or is poured into engine, be then placed in 60 DEG C ~ 70 DEG C oil bath baking ovens
Solidification 7 days.
（2）Gas generator propellant performance
| Specific impulse, N*s/kg | 1928 |
| Characteristic velocity, m/s | 1208 |
| Combustion gas mean molecule quantity, g/mol | 21.5 |
| Gas forming amount, L/kg | 1080 |
| Burn rate（6.86MPa）, mm/s | 3.5 |
| Pressure Exponent n（7MPa~13MPa） | 0.35 |
| Combustion temperature, K | 1522 |
| Residue content, % | 2.3 |
Embodiment 3
（1）Gas generator propellant is constituted
| Formula composition | Mass percent（%） |
| Terminal hydroxy group PEO-tetrahydrofuran | 13.23 |
| Toluene di-isocyanate(TDI) | 0.93 |
| Ammonium nitrate | 65 |
| Dihydroxy glyoxime | 15.0 |
| Chrome green | 1.0 |
| Vanadic anhydride | 1.0 |
| ATEC | 3.54 |
| Lecithin | 0.1 |
| N, N- diphenyl-para-phenylene diamine | 0.2 |
Gas generator propellant is prepared by the preparation method of embodiment 1.
（2）Gas generator propellant performance
| Specific impulse, N*s/kg | 1905 |
| Characteristic velocity, m/s | 1186 |
| Combustion gas mean molecule quantity, g/mol | 21.7 |
| Gas forming amount, L/kg | 1050 |
| Burn rate（6.86MPa）, mm/s | 4.75 |
| Pressure Exponent n（7MPa~13MPa） | 0.26 |
| Combustion temperature, K | 1467 |
| Residue content, % | 2.6 |
Embodiment 4
（1）Gas generator propellant is constituted
| Formula composition | Mass percent（%） |
| Terminal hydroxy group PEO-tetrahydrofuran | 16.23 |
| Toluene di-isocyanate(TDI) | 0.57 |
| Modified six methine polyisocyanates | 1.20 |
| Ammonium nitrate | 70 |
| Dihydroxy glyoxime | 5.0 |
| Oxamides | 5.0 |
| ATEC | 1.80 |
| Lecithin | 0.1 |
| Carbon black | 0.1 |
Gas generator propellant is prepared by the preparation method of embodiment 2.
（2）Gas generator propellant performance
| Specific impulse, N*s/kg | 1894 |
| Characteristic velocity, m/s | 1171 |
| Combustion gas mean molecule quantity, g/mol | 21.4 |
| Gas forming amount, L/kg | 1080 |
| Burn rate（6.86MPa）, mm/s | 1.18 |
| Pressure Exponent n（7MPa~13MPa） | 0.72 |
| Combustion temperature, K | 1396 |
| Residue content, % | 0.9 |
The above, is only the optimal embodiment of the present invention, but protection scope of the present invention is not limited thereto, any
Those familiar with the art the invention discloses technical scope in, the change or replacement that can be readily occurred in, all should
It is included within the scope of the present invention.
The content not being described in detail in description of the invention belongs to the known technology of professional and technical personnel in the field.
Claims (8)
1. a kind of nitric acid ammonium low burn temperature clean fuel gas propellant, it is characterised in that including following masses percentage component：
Ammonium nitrate：65% ~ 80%,
The warm conditioning agent of combustion：0%~15%
Special additive：0% ~ 2%,
Adhesive：10% ~ 20%,
Curing agent：0.5% ~ 2.0%,
Other additives：2.0%~6.0%.
2. nitric acid ammonium low burn temperature clean fuel gas propellant according to claim 1, it is characterised in that：Each component is matched
For：
Ammonium nitrate：70% ~ 75%,
The warm conditioning agent of combustion：5%~10%,
Special additive：0% ~ 2%,
Adhesive：12% ~ 16%,
Curing agent：1.0% ~ 1.5%,
Other additives：3%~5.0%.
3. a kind of nitric acid ammonium low burn temperature clean fuel gas propellant according to claim 1, it is characterised in that：The combustion temperature
Conditioning agent is oxamide, or dihydroxy glyoxime one kind or combination.
4. a kind of nitric acid ammonium low burn temperature clean fuel gas propellant according to claim 1, it is characterised in that：It is described special
Additive is one kind or the combination of chrome green or vanadic anhydride.
5. a kind of nitric acid ammonium low burn temperature clean fuel gas propellant according to claim 1, it is characterised in that：The bonding
Agent is terminal hydroxy group PEO-tetrahydrofuran.
6. a kind of nitric acid ammonium low burn temperature clean fuel gas propellant according to claim 1, it is characterised in that：The solidification
Agent is one kind or the combination of IPDI or toluene di-isocyanate(TDI) or modified six methine polyisocyanates.
7. a kind of nitric acid ammonium low burn temperature clean fuel gas propellant according to claim 1, it is characterised in that：It is described other
Additive be ATEC or lecithin or triphenyl bismuth or carbon black or three [1 ,-（2- methylaziridines）] oxygen
Change phosphine or one kind or combination of triethanolamine or N, N- diphenyl-para-phenylene diamine.
8. the preparation method of nitric acid ammonium low burn temperature clean fuel gas propellant described in a kind of claim 1, it is characterised in that including：
（1）The component is weighed by above-mentioned selected formula rate；
（2）Said components are put into vertical mixer and mixed, 40 DEG C ~ 60 DEG C of mixing temperature, incorporation time 70min ~
110min, obtains slurry；
（3）Slime vacuum spray is poured into mould or is poured into engine, is then placed in 60 DEG C ~ 70 DEG C oil bath baking ovens
Solidification 5 ~ 7 days.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610891074.8A CN106938965B (en) | 2016-10-13 | 2016-10-13 | A kind of nitric acid ammonium low burn temperature clean fuel gas propellant |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610891074.8A CN106938965B (en) | 2016-10-13 | 2016-10-13 | A kind of nitric acid ammonium low burn temperature clean fuel gas propellant |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106938965A true CN106938965A (en) | 2017-07-11 |
| CN106938965B CN106938965B (en) | 2018-08-14 |
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ID=59469373
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610891074.8A Active CN106938965B (en) | 2016-10-13 | 2016-10-13 | A kind of nitric acid ammonium low burn temperature clean fuel gas propellant |
Country Status (1)
| Country | Link |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107311825A (en) * | 2017-07-20 | 2017-11-03 | 湖北航天化学技术研究所 | A kind of compositions of additives and gas generator propellant for polyethers gas generator propellant |
| CN108395361A (en) * | 2018-05-11 | 2018-08-14 | 湖北航天化学技术研究所 | A kind of clean fuel gas propellant and preparation method thereof |
| CN113979817A (en) * | 2021-11-22 | 2022-01-28 | 中国人民解放军国防科技大学 | Oxygen-enriched solid propellant and preparation method thereof |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1644574A (en) * | 2004-12-16 | 2005-07-27 | 中国航天科技集团公司第四研究院第四十二研究所 | Non-nitrine gas generating agent and production thereof |
| CN1651360A (en) * | 2005-03-28 | 2005-08-10 | 张根发 | Gas producing composition and its preparation method |
| WO2007026235A1 (en) * | 2005-09-02 | 2007-03-08 | Socoen Sviluppo S.R.L. | Chemical compound for combustion catalysis, and apparatus utilizing said compound |
| CN103204753A (en) * | 2012-10-16 | 2013-07-17 | 湖北航天化学技术研究所 | Solid gas generator and preparation method thereof |
| CN105198681A (en) * | 2014-06-10 | 2015-12-30 | 湖北航天化学技术研究所 | Room-temperature-cured-type clean solid propellant |
| CN105777459A (en) * | 2014-12-26 | 2016-07-20 | 湖北航天化学技术研究所 | Low pressure exponent and low residue fuel gas generating agent and preparing method thereof |
-
2016
- 2016-10-13 CN CN201610891074.8A patent/CN106938965B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1644574A (en) * | 2004-12-16 | 2005-07-27 | 中国航天科技集团公司第四研究院第四十二研究所 | Non-nitrine gas generating agent and production thereof |
| CN1651360A (en) * | 2005-03-28 | 2005-08-10 | 张根发 | Gas producing composition and its preparation method |
| WO2007026235A1 (en) * | 2005-09-02 | 2007-03-08 | Socoen Sviluppo S.R.L. | Chemical compound for combustion catalysis, and apparatus utilizing said compound |
| CN103204753A (en) * | 2012-10-16 | 2013-07-17 | 湖北航天化学技术研究所 | Solid gas generator and preparation method thereof |
| CN105198681A (en) * | 2014-06-10 | 2015-12-30 | 湖北航天化学技术研究所 | Room-temperature-cured-type clean solid propellant |
| CN105777459A (en) * | 2014-12-26 | 2016-07-20 | 湖北航天化学技术研究所 | Low pressure exponent and low residue fuel gas generating agent and preparing method thereof |
Non-Patent Citations (5)
| Title |
|---|
| 柴玉萍，等: "GAP/AN燃气发生剂研制", 《固体火箭技术》 * |
| 柴玉萍，等: "非叠氮燃气发生剂配方研制进展", 《宇航材料工艺》 * |
| 谭惠民: "《固体推进剂化学与技术》", 3 September 2015 * |
| 赵庆华，等: "硝酸铵基绿色洁净固体推进剂的研究进展", 《化学推进剂与高分子材料》 * |
| 黄海涛，等: "复合型燃气发生剂研究进展", 《化学推进剂与高分子材料》 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107311825A (en) * | 2017-07-20 | 2017-11-03 | 湖北航天化学技术研究所 | A kind of compositions of additives and gas generator propellant for polyethers gas generator propellant |
| CN107311825B (en) * | 2017-07-20 | 2019-01-11 | 湖北航天化学技术研究所 | A kind of compositions of additives and gas generator propellant for polyethers gas generator propellant |
| CN108395361A (en) * | 2018-05-11 | 2018-08-14 | 湖北航天化学技术研究所 | A kind of clean fuel gas propellant and preparation method thereof |
| CN113979817A (en) * | 2021-11-22 | 2022-01-28 | 中国人民解放军国防科技大学 | Oxygen-enriched solid propellant and preparation method thereof |
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| Publication number | Publication date |
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| CN106938965B (en) | 2018-08-14 |
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