KR101661152B1 - Propellant Compositions for Two Color Infrared Flares Comprising Carbon Nanotubes - Google Patents
Propellant Compositions for Two Color Infrared Flares Comprising Carbon Nanotubes Download PDFInfo
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- KR101661152B1 KR101661152B1 KR1020160021463A KR20160021463A KR101661152B1 KR 101661152 B1 KR101661152 B1 KR 101661152B1 KR 1020160021463 A KR1020160021463 A KR 1020160021463A KR 20160021463 A KR20160021463 A KR 20160021463A KR 101661152 B1 KR101661152 B1 KR 101661152B1
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- infrared
- propellant
- propellant composition
- intensity
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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
- C06B31/02—Compositions containing an inorganic nitrogen-oxygen salt the salt being an alkali metal or an alkaline earth metal nitrate
- C06B31/08—Compositions containing an inorganic nitrogen-oxygen salt the salt being an alkali metal or an alkaline earth metal nitrate with a metal oxygen-halogen salt, e.g. inorganic chlorate, inorganic perchlorate
- C06B31/10—Compositions containing an inorganic nitrogen-oxygen salt the salt being an alkali metal or an alkaline earth metal nitrate with a metal oxygen-halogen salt, e.g. inorganic chlorate, inorganic perchlorate with carbon or sulfur
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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
- C06B45/02—Compositions or products which are defined by structure or arrangement of component of product comprising particles of diverse size or shape
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B4/00—Fireworks, i.e. pyrotechnic devices for amusement, display, illumination or signal purposes
- F42B4/26—Flares; Torches
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B4/00—Fireworks, i.e. pyrotechnic devices for amusement, display, illumination or signal purposes
- F42B4/30—Manufacture
Abstract
The present invention relates to propellant compositions having a high dichroic ratio and their use. The propellant composition of the present invention comprising 2.0 wt% or more of carbon nanotubes not only causes a maximum infrared intensity of at least 5,000 W / Sr during combustion, but also results in a medium infrared intensity / near infrared ray intensity ratio of 6 or more. Accordingly, the propellant composition of the present invention can be effectively applied to two-color infrared ray flares to be used for an infrared ray liberation book (IRCCM).
Description
TECHNICAL FIELD The present invention relates to a propellant composition for a two-color infrared scintillation charcoal using carbon nanotubes.
Fighters, transporters and helicopters emit infrared rays that make them vulnerable to missiles equipped with infrared navigators. This infrared emission results from the exhaust gas from the combustion of aviation oil which produces high temperature carbon dioxide (CO 2 ), water vapor (H 2 O), carbon monoxide (CO) and carbon particles (Soot). Infrared intensity of an aircraft is known to depend on variables such as engine structure, angle of attack, range, altitude and atmospheric conditions. After the advent of first-generation air-to-air missiles and surface-to-air missiles, we became aware of the importance of the infrared radios, such as the widely deployed MTV (Mg / Teflon / Viton) Various explorers have been studied endlessly to cope with IRCCM.
Infrared ray scintillation based on Mg / Teflon / Viton (MTV) mixture emits high temperature (about 2200K) infrared rays, so it is used as infrared ray scintillation to deceive existing explorer. However, with the development of infrared threat-to-infrared countermeasures, more and more improved threats have emerged. They use a color ratio (CR), which is an energy ratio between 3-5 μm and 2-3 μm, to distinguish between intense target and degenerated infrared flare.
Basically, the composition of the two-color infrared ray scintillation can be classified into a composition based on only temperature radiation or selective radiation (see FIG. 1). Emitters based on temperature emitters consist of a self-igniting foil or a thin coated metal foil. However, due to undesirable kinetics, the debris is easily distinguished by an improved explorer. On the other hand, the preferred selective emitter for the pyrotechnic packing in descending order of the intensity of the infrared emission by wavelength is CO 2 >FBO> HBO 2 >HBO>CO> HCl (see Table 1). In other words, the hydrocarbons are mixed with an oxidizing agent in an appropriate ratio and burned to maximize the CO 2 content in the combustion products to maximize the two-color ratio. The undesirable selective radiators to be avoided in decreasing order of the intensity of infrared emission by wavelength are HF> CH 4 > H 2 O (see Table 2).
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The tracking principle of the two-color infrared flare is to track the IR source with the highest intensity of the middle infrared ray (3.5-4.8 μm) on the field of view (FOV) of the navigator, If the intensity ratio CR is greater than 1, it is recognized by the aircraft and continues to be tracked. If it is less than 1, it is recognized as infrared flares (debris) and another infrared ray is re-detected and tracked. .
Therefore, in order to avoid the tracking of the two-color infrared scintillator tracker, it is very important to have a composition of a two-color infrared scintillator having a larger infrared ray source and simultaneously having a color ratio greater than 1. Accordingly, There is an urgent need for a more efficient composition capable of solving the above problems.
The present inventors have sought to develop a propellant composition that can be effectively used for infrared radial release (IRCCM) for infrared seekers (e.g., surface and air-to-air missiles). As a result, the present inventors have found that the propellant composition in which the oxidizer and the carbon nanotube are added in an appropriate ratio significantly increases the amount of CO 2 produced during combustion (that is, maximizes the content ratio of CO 2 / H 2 O in the combustion product) By confirming that the tracking of the two-color searcher with respect to the target can be easily and efficiently interrupted by creating a ratio of the color ratio, that is, the ratio of the medium-infrared intensity to the near-infrared intensity, to at least 3 or more, Thereby completing the present invention.
Accordingly, it is an object of the present invention to provide a propellant composition for infrared flares.
It is another object of the present invention to provide a propellant grain.
Other objects and advantages of the present invention will become more apparent from the following detailed description of the invention, claims and drawings.
According to one aspect of the present invention, there is provided a propellant composition for infrared flare-uptake comprising 2.0 wt% or more of carbon nanotubes.
According to another aspect of the present invention, the present invention provides a propellant grain comprising the above-described propellant composition.
The present inventors have sought to develop a propellant composition that can be effectively used in the infrared ray disassembly of infrared detectors. As a result, the present inventors have found that the propellant composition in which the oxidizer and the carbon nanotube are added in an appropriate ratio significantly increases the amount of CO 2 produced during combustion (that is, maximizes the content ratio of CO 2 / H 2 O in the combustion product) It is confirmed that the tracking of the two-color searcher to the target can be easily and efficiently prevented by not only increasing the wavelength intensity significantly but also raising the ratio of the color ratio, that is, the ratio of the medium-infrared intensity to the near- infrared intensity to at least three.
Usually, the infrared scintillating carbon includes propellant grains composed of a propellant composition, an ignition agent, other additives, and the like.
The propellant composition can be conveniently prepared according to a conventionally known method. For simplicity, the propellant composition can be prepared by mixing each component and then extruding. Typically, the propellant composition comprises a binder, an oxidizing agent, an additive, and the like.
The binder is a material forming a matrix structure in the propellant composition, and the cross-linking reversibly changes depending on the temperature. Binders that may be used in the present invention may include thermoplastic elastomers (TPE), nitrocellulose, nitroglycerin, and the like.
First, the thermoplastic elastomer may be prepared from various rubber materials and may be, for example, a natural rubber, a butadiene rubber, an isoprene rubber, a butyl rubber, an ethylene-propylene rubber, a styrene-butadiene rubber (SBR), an EPDM (ethylene propylene diene monomer) Acrylonitrile-butadiene rubber (NBR), epichlorohydrin rubber, polychloroprene rubber, chlorobutyl rubber, and the like, but are not limited thereto. But may in particular contain a nitrile group. Thereafter, the rubber material and the thermoplastic resin are melt-mixed to produce a thermoplastic elastomer. The thermoplastic resin may be any resin having an appropriate compatibility with the rubber material, for example, a thermoplastic polyolefin resin. In some embodiments of the present invention, the thermoplastic polyolefin-based resin is selected from the group consisting of polyethylene or chlorinated polyethylene; Hypalon ® (Du Pont); A copolymer obtained by polymerizing at least one comonomer selected from the group consisting of homo-polypropylene (Homo-PP), propylene, ethylene, butylene and octene; A block copolymer in which an ethylene-propylene rubber is blended with polypropylene; And high melt strength PP (HMSPP) with a polypropylene branch. However, the present invention is not limited thereto.
Also, other materials having a nitrate group may be used as the binder. The binder having a nitrate group that can be used in the present invention is at least one selected from the group consisting of nitrocellulose (NC), nitroglycerin (NG), pentaerythritol tetranitrate (PETN), trimethanolethanetrinate (TMETN), dipentaerythritol hexa (NMP), nitrites (DiPEHN), trimethylolpropane trinitrate (TMPTN), nitroisobutylglycerol trinitrate (NIBGT), erythritol tetranitrate (ETN), xylitol pentanitrate (XPN), sorbitol hexanitrate (SHN), and mannitol hexanitrate (MHN). However, the present invention is not limited thereto. In some embodiments of the present invention, the binders having a nitrate group that can be used in the present invention are nitrocellulose (NC) and nitroglycerin (NG).
The infrared scintillation charcoal of the present invention may contain conventional igniters / oxidants used in the art, for example, boron; Ammonium perchlorate (AP); Potassium perchlorate; Binders such as nitrocellulose; Metal powders such as Mg, Al and Ti; And the like may be used, but the present invention is not limited thereto. For example, the oxidizing agent used in the propellant composition of the present invention may be selected from a variety of materials known in the art and specifically include cyclotrimethylenetrithinilamine (RDX), cyclotetramethylenetetronitramine (HMX) (DNNC), trans-1,2-dinitrocyclopropane (DNCP), and the like. , 1,3,3,5,7,7-hexanitro-1,5-diazacyclooctane (HNDZ), 1,3,3-trinitroazetidine (TNAZ), and 1- 3,5,7-trinitro-l, 3,5,7-tetraazacyclooctane (AZTC). More specifically, the oxidizing agent used in the present invention is ammonium perchlorate (AP).
According to the present invention, the propellant composition of the present invention maximizes the content of CO 2 in the combustion products by controlling the ratio of the carbon nanotubes to the oxidizing agent. In some embodiments of the present invention, the ratio of carbon nanotube to oxidant in the propellant composition of the present invention is at least 1: 20 but is not limited thereto.
On the other hand, the nitrate group can decompose naturally over time, resulting in decomposition products of the nitrate group further promoting decomposition and eventually igniting. In order to prevent this, a stabilizer may be further included in the propellant composition of the present invention. For example, stabilizers that may be included in the propellant compositions of the present invention include diphenylamine (DPA), 2-nitrophenylamine (2-NPA), 2-nitrophenylamine (2-NDPA), 4-nitrophenyl (4-NDPA), para-N-methylnitroaniline (MNA), para-nitro-N-methylmethoxyaniline (pNMA), ethylcentralite, methylentralite, ) I, < / RTI > acadid II, and carbamite.
Meanwhile, the propellant composition of the present invention may contain minor amounts (e.g., less than 3 weight percent) of additives such as metal powders such as aluminum powder; A burn rate modifier; Binders such as TEPANOL (the reaction product of tetraethylenepentamine nitrile (TEPAN) and glycidol); Combustion stabilizers such as carbon black or zirconium carbide (ZrC); And an anti-inflammatory agent may be further included.
According to the present invention, the conventional infrared-ray flare charcoal generates a medium-infrared intensity higher than the intensity of the middle infrared ray generated from a large amount of exhaust gas of the aircraft with a relatively small amount of scintillation amount (about 250 g) It is used to mislead the tracker to track deceptions (see Figure 1). Plank's law is that the higher the temperature, the more infrared rays are emitted. The lower the temperature is below 700K, the higher infrared intensity is obtained. It is difficult. Therefore, in order to obtain a high infrared ray intensity with a small amount of scintillation, it is necessary to design so that CO 2 gas is emitted to the combustion product of scintillant, which is a selective spinning method. In fact, in order to release a gas mixture with a CO 2 / H 2 O ratio of 4 or more, the exhaust gas is a relatively small amount of infrared scintillation agent that is greater than the exhaust gas of the aircraft, it is essential to design the reactor composition so that it contains a large amount of easily combustible carbon to be.
In order to produce a more effective two-color infrared ray scintillation charcoal, the present invention uses a carbon nanotube (CNT) as an additive for a scintillation photocatalyst to constitute a propellant composition for infrared ray scintillation, Of CO 2 It was possible to maximize the generation. That is, the propellant composition of the present invention produced a higher CO 2 / H 2 O ratio during combustion, thereby creating a higher infrared intensity from infrared flare than the infrared intensity derived from aircraft such as fighter aircraft, transport aircraft and helicopters : Examples 1 and 2).
In some embodiments of the present invention, the amount of carbon nanotubes used in the propellant composition of the present invention is at least 2.0 wt%, more specifically 2.0 wt% to 10 wt%, even more specifically 2.0 wt% To 5.0% by weight and most specifically from 2.0% by weight to 3.5% by weight.
In some embodiments of the present invention, the medium to infrared intensity / near-infrared intensity ratio that can be caused by the propellant composition of the present invention is on average at least 3, more specifically at least 4, even more specifically at least 5, Is 6 or more.
In some embodiments of the present invention, the propellant composition of the present invention has a maximum infrared intensity of at least 4,000 W / Sr, more specifically at least 5,000 W / Sr and more particularly at least 6,000 W / Sr, .
In addition, the propellant grains of the present invention generally have a structure in which a plurality of grooves for applying an igniter are applied to the outer surface (see FIG. 2), and can be designed in various shapes. The propellant grains of the present invention are mainly made of materials capable of exhibiting a higher intensity of near infrared rays than those of near infrared rays, and examples thereof include nitrocellulose (NC), nitroglycerin (NG), diethylene glycol dinitrate (DEGDN) But is not limited thereto.
In some embodiments of the present invention, the propellant grains of the present invention are designed in a neutral burning configuration.
The features and advantages of the present invention are summarized as follows:
(a) The present invention relates to propellant compositions having a high dichroic ratio and uses thereof.
(b) The propellant composition of the present invention comprising 2.0 wt.% or more of carbon nanotubes not only causes a maximum infrared intensity of at least 5,000 W / Sr during combustion, but also results in a medium infrared intensity / near infrared ray intensity ratio of 6 or more.
(c) Therefore, the propellant composition of the present invention can be effectively applied to two-color infrared ray flares to be used for an infrared ray liberation book (IRCCM).
1 is a flow chart illustrating a method for obtaining an excellent color ratio in a two-color infrared flare.
2 is a schematic diagram of a propellant grain applied with an igniter.
Hereinafter, the present invention will be described in more detail with reference to Examples. It is to be understood by those skilled in the art that these embodiments are only for describing the present invention in more detail and that the scope of the present invention is not limited by these embodiments in accordance with the gist of the present invention .
Example
Example 1: propellant composition using thermoplastic propellant
The first composition is a mixture of Ammonium Perchlorate (AP) (Hanwha, Korea), carbon nanotubes (Carbon Nanotech, Korea) as an oxidizing agent, thermoplastic elastomer (TPE) And the composition was designed. Details composition TPE 20%, AP 75%, CNT 2% binder (HX752; Cowon Technology, Republic of Korea) 1.5% antioxidant (AO 246; ATK-Thiokol, USA) 0.25%, the catalyst (Fe 2 O 3; EG (Formerly Samyang Industry), Korea) is 1.25%. As a result of the combustion test, the maximum infrared ray intensity was 5,000 W / Sr and the color ratio was 6.2.
Example 2: Propellant composition using a propellant
The second composition was designed by adding carbon nanotubes (CNT) to nitrocellulose (NC) (Poongsan, Korea) and nitroglycerin (NG) (Poongsan, Korea). The detailed composition is NC 53%, NG 42%, CNT 3.5% and antioxidant 1.5%. As a result of the combustion test, the infrared ray intensity was 6,000 W / Sr and the color ratio was 9.2 on average.
As described above, propellant compositions were prepared by adding carbon nanotubes to two kinds of cannon-propellant binders and oxidants, and a neutron-burning propellant grain was designed using the same. Through the combustion experiments using the designed propellant grains, it was confirmed that when the propellant grains were used, the two color ratio was at least 3 or more.
While the present invention has been particularly shown and described with reference to exemplary embodiments thereof, it will be understood by those skilled in the art that various changes and modifications may be made without departing from the spirit and scope of the invention as defined in the appended claims. It will be obvious. Accordingly, the actual scope of the present invention will be defined by the appended claims and their equivalents.
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| Application Number | Priority Date | Filing Date | Title |
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| KR1020160021463A KR101661152B1 (en) | 2016-02-23 | 2016-02-23 | Propellant Compositions for Two Color Infrared Flares Comprising Carbon Nanotubes |
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| KR1020160021463A KR101661152B1 (en) | 2016-02-23 | 2016-02-23 | Propellant Compositions for Two Color Infrared Flares Comprising Carbon Nanotubes |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115215710A (en) * | 2022-08-08 | 2022-10-21 | 陕西师范大学 | Composite burning rate catalyst of carbon nano tube filled with copper acetylacetonate and hexogen mixture |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5470408A (en) * | 1993-10-22 | 1995-11-28 | Thiokol Corporation | Use of carbon fibrils to enhance burn rate of pyrotechnics and gas generants |
| JPH1151598A (en) * | 1997-07-30 | 1999-02-26 | Asahi Chem Ind Co Ltd | Infrared flare bullet |
| JP2000028299A (en) * | 1998-07-07 | 2000-01-28 | Nof Corp | Infrared ray flare |
| KR20070012780A (en) * | 2006-06-08 | 2007-01-29 | 쵸이 알렉산드르 | Method for production of spiral-shaped carbon coated with nano-crystalline structred carbon layer and infrared emitter comprising spiral-shaped carbon |
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2016
- 2016-02-23 KR KR1020160021463A patent/KR101661152B1/en active IP Right Grant
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5470408A (en) * | 1993-10-22 | 1995-11-28 | Thiokol Corporation | Use of carbon fibrils to enhance burn rate of pyrotechnics and gas generants |
| JPH1151598A (en) * | 1997-07-30 | 1999-02-26 | Asahi Chem Ind Co Ltd | Infrared flare bullet |
| JP2000028299A (en) * | 1998-07-07 | 2000-01-28 | Nof Corp | Infrared ray flare |
| KR20070012780A (en) * | 2006-06-08 | 2007-01-29 | 쵸이 알렉산드르 | Method for production of spiral-shaped carbon coated with nano-crystalline structred carbon layer and infrared emitter comprising spiral-shaped carbon |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115215710A (en) * | 2022-08-08 | 2022-10-21 | 陕西师范大学 | Composite burning rate catalyst of carbon nano tube filled with copper acetylacetonate and hexogen mixture |
| CN115215710B (en) * | 2022-08-08 | 2023-10-24 | 陕西师范大学 | Composite burning rate catalyst of copper acetylacetonate and black soldier mixture filled with carbon nano tube |
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