CN106938965B - 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
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- CN106938965B CN106938965B CN201610891074.8A CN201610891074A CN106938965B CN 106938965 B CN106938965 B CN 106938965B CN 201610891074 A CN201610891074 A CN 201610891074A CN 106938965 B CN106938965 B CN 106938965B
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- combination
- gas
- nitric acid
- fuel gas
- acid ammonium
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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, including ammonium nitrate：65% ~ 80%, fire warm conditioning agent：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 polyethylene oxide tetrahydrofuran, and curing agent is one kind or the combination of isophorone diisocyanate or toluene di-isocyanate(TDI) or modified six methine polyisocyanates.The gas generator propellant that the present invention produces, raw material are free of metal powder, have the characteristics that low burn temperature, combustion gas cleaning and non-corrosive gas, low residue and performance can easily be accommodated, the conventional weapon auxiliary power source that can be used for wide Acclimation temperature range, is especially applicable for the auxiliary power source for having particular/special requirement to combustion gas.
Description
Technical field
The invention belongs to composite solidpropellant gas generator propellant fields, in particular it relates to which a kind of being 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 for generation of burning is as driving auxiliary power dress
The working medium set, converts chemical energy into mechanical or electrical energy.Since gas generator is simple in structure, 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 roll
The servo-drive system of control, the upender of catapult-launching gear, car launcher, last boosting and the fields such as 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 the performance characteristics such as ignition temperature is low, combustion gas is clean and non-corrosive hydrogen chloride gas, residue are low, and performance simultaneously
It can easily be accommodated, for meeting the design requirement of increasingly complicated gas generator propellant.
Invention content
Problems solved by the invention is：Overcome the deficiencies in the prior art provides 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-corrosive gas, low residue and performance can easily be accommodated.
The present invention also provides the preparation methods 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.
Technical solution of the invention is：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.
The adhesive is terminal hydroxy group polyethylene oxide-tetrahydrofuran.
The curing agent is isophorone diisocyanate or toluene di-isocyanate(TDI) or modified six methine polyisocyanates
One kind of cyanate or combination.
Other additives are acetyl triethyl citrate 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 present invention preparation process include：
（1）The component is weighed by above-mentioned selected formula rate；
（2）Said components are put into vertical mixer and are mixed, 40 DEG C ~ 60 DEG C of mixing temperature, incorporation time 70min
~ 110min, obtains slurry；
（3）Slime vacuum spray is poured into mold or is poured into engine, 60 DEG C ~ 70 DEG C oil baths is then placed on and dries
Cure 5 ~ 7 days in case.
The advantages of the present invention over the prior art are that：
（1）Oxidant used in the present invention is common ammonium nitrate, the combustion gas that nitric acid ammonium gas generator propellant generates when burning
The advantages that temperature is low, burn rate is low, gas forming amount is big, at low cost, safe, while there is no the production of perchloric acid ammonium type gas generator propellant in combustion gas
Raw hydrogen-chloride etching gas.
（2）Special additive used in 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；It can make formula burn rate at 6.86MPa by using the adjusting of amount, it is adjustable within the scope of burn rate 0.5mm/s ~ 6mm/s,
Pressure Exponent（3MPa~9MPa）0.5 or less can be reduced to.
（3）The present invention can by adjusting the ignition temperature with when additive amount regulation system of the warm additive of combustion, thus, have
Broader ignition temperature adjustable range, the conventional weapon auxiliary power source of wide Acclimation temperature range is can be used for.
（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,
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,
The problem that mechanical property and combustibility are adjusted provides a kind of clean and non-corrosive without metal powder, low combustion temperature, combustion gas
The gas generator propellant that gas, low residue and performance can easily be accommodated can be used for the conventional weapon auxiliary power of wide Acclimation temperature range
Source is especially applicable for the auxiliary power source for having particular/special requirement to combustion gas.
Specific implementation mode
The present invention is described in detail With reference to embodiment, but the present invention is not limited only to embodiment.
Embodiment 1
（1）Gas generator propellant forms
| Formula composition | Mass percent（%） |
| Terminal hydroxy group polyethylene oxide-tetrahydrofuran | 11.44 |
| Modified six methine polyisocyanates | 1.72 |
| Ammonium nitrate | 80 |
| Chrome green | 1.5 |
| Vanadic anhydride | 0.5 |
| Acetyl triethyl citrate | 4.54 |
| Carbon black | 0.1 |
| Lecithin | 0.1 |
| Three [1 ,-（2- methylaziridines）] phosphine oxide | 0.1 |
Preparation process：
1, said components are weighed by above-mentioned selected formula rate；
2, said components are put into vertical mixer and are mixed, 40 DEG C of mixing temperature, incorporation time 110min must expect
Slurry；
3, slime vacuum spray is poured into mold or is poured into engine, be then placed on 60 DEG C ~ 70 DEG C oil baths and dry
Cure 6 days in case.
（2）Gas generator propellant performance
| Specific impulse, N*s/kg | 2013 |
| Characteristic velocity, m/s | 1274 |
| Combustion gas average molecular weight, 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 forms
| Formula composition | Mass percent（%） |
| Terminal hydroxy group polyethylene oxide-tetrahydrofuran | 11.62 |
| Isophorone diisocyanate | 1.08 |
| Ammonium nitrate | 75 |
| Oxamides | 5 |
| Triphenyl bismuth | 0.1 |
| Vanadic anhydride | 2.0 |
| Acetyl triethyl citrate | 5.0 |
| Lecithin | 0.1 |
| Triethanolamine | 0.1 |
Preparation process：
1, said components are weighed by above-mentioned formula rate；
2, said components are put into vertical mixer and are mixed, 60 DEG C of mixing temperature, incorporation time 70min must expect
Slurry；
3, slime vacuum spray is poured into mold or is poured into engine, be then placed on 60 DEG C ~ 70 DEG C oil baths and dry
Cure 7 days in case.
（2）Gas generator propellant performance
| Specific impulse, N*s/kg | 1928 |
| Characteristic velocity, m/s | 1208 |
| Combustion gas average molecular weight, 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 forms
| Formula composition | Mass percent（%） |
| Terminal hydroxy group polyethylene oxide-tetrahydrofuran | 13.23 |
| Toluene di-isocyanate(TDI) | 0.93 |
| Ammonium nitrate | 65 |
| Dihydroxy glyoxime | 15.0 |
| Chrome green | 1.0 |
| Vanadic anhydride | 1.0 |
| Acetyl triethyl citrate | 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 average molecular weight, 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 forms
| Formula composition | Mass percent（%） |
| Terminal hydroxy group polyethylene oxide-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 |
| Acetyl triethyl citrate | 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 average molecular weight, 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, best specific implementation mode only of the invention, but scope of protection of the present invention is not limited thereto,
Any one skilled in the art in the technical scope disclosed by the present invention, the change or replacement that can be readily occurred in,
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 known technology of professional and technical personnel in the field.
Claims (2)
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：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 warm conditioning agent of combustion is one kind or the combination of oxamide or dihydroxy glyoxime；
The special additive is one kind or the combination of chrome green or vanadic anhydride；
Described adhesive is terminal hydroxy group polyethylene oxide-tetrahydrofuran；
The curing agent is isophorone diisocyanate or toluene di-isocyanate(TDI) or modified six methine polyisocyanates
One kind or combination；
Other additives be acetyl triethyl citrate or lecithin or triphenyl bismuth or carbon black or three [1 ,-（2- first
Base aziridine）] phosphine oxide or triethanolamine or N, N- diphenyl-para-phenylene diamine one kind or combination.
2. 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 are mixed, 40 DEG C ~ 60 DEG C of mixing temperature, incorporation time 70min ~
110min obtains slurry；
（3）Slime vacuum spray is poured into mold 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)
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| CN201610891074.8A CN106938965B (en) | 2016-10-13 | 2016-10-13 | A kind of nitric acid ammonium low burn temperature clean fuel gas propellant |
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|---|---|---|---|
| CN201610891074.8A CN106938965B (en) | 2016-10-13 | 2016-10-13 | A kind of nitric acid ammonium low burn temperature clean fuel gas propellant |
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| CN106938965A CN106938965A (en) | 2017-07-11 |
| CN106938965B true CN106938965B (en) | 2018-08-14 |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
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 (4)
| Title |
|---|
| GAP/AN燃气发生剂研制;柴玉萍，等;《固体火箭技术》;19991231;第22卷(第4期);第50-53页 * |
| 复合型燃气发生剂研究进展;黄海涛，等;《化学推进剂与高分子材料》;20160928;第14卷(第5期);第9-12页 * |
| 硝酸铵基绿色洁净固体推进剂的研究进展;赵庆华，等;《化学推进剂与高分子材料》;20121125;第30-33页 * |
| 非叠氮燃气发生剂配方研制进展;柴玉萍，等;《宇航材料工艺》;20070228(第1期);第11-15页 * |
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