WO2013004259A1 - Vorrichtung zum abbrennen von treibstoffen oder explosivstoffen - Google Patents
Vorrichtung zum abbrennen von treibstoffen oder explosivstoffen Download PDFInfo
- Publication number
- WO2013004259A1 WO2013004259A1 PCT/EP2011/003376 EP2011003376W WO2013004259A1 WO 2013004259 A1 WO2013004259 A1 WO 2013004259A1 EP 2011003376 W EP2011003376 W EP 2011003376W WO 2013004259 A1 WO2013004259 A1 WO 2013004259A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- substance
- temperature
- pressure
- fuel
- tight barrier
- Prior art date
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B39/00—Packaging or storage of ammunition or explosive charges; Safety features thereof; Cartridge belts or bags
- F42B39/14—Explosion or fire protection arrangements on packages or ammunition
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
- F02K9/38—Safety devices, e.g. to prevent accidental ignition
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/95—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by starting or ignition means or arrangements
Definitions
- the invention relates to a device for burning off fuels or explosives according to the preamble of claim 1.
- Trigger temperature however, passively, so behave without any risk of unwanted inflammation.
- Substance determines the triggering temperature and, at the same time, the extent of the exothermic reaction. However, there are only a few substances that meet these requirements. This applies a fortiori, if both substances only react exothermically to the required extent in the molten state.
- Ignition temperatures is suitable.
- a device for burning off fuels and explosives having a release temperature which is below the autoignition temperature of the fuel and explosive.
- the device according to the invention has at least two mutually exothermic
- At least one first substance is present below the triggering temperature of the device in a liquid state of aggregation.
- the first substance is separated from at least one second substance by at least one pressure-tight barrier.
- the second substance may be in the solid state at the initiation temperature. It then preferably has a large surface area and can then be powdered, for example.
- the first substance is preferably at room temperature, in particular even at the maximum allowable storage and operating temperature of the rocket, so the fuel, or the maximum allowable storage and operating temperature of
- the melting point of the first substance may also be only a few degrees Celsius, ie, for example, only 10 ° C or less below the triggering temperature.
- the solid propellant of a rocket motor is designed to burn approximately continuously when the mass of the propellant is at a relatively low temperature.
- a hard rocket engine for example, by a fire on the
- Auto-ignition temperature of, for example, 160 ° or more is heated, a deflagration may also occur explosion.
- the triggering temperature ie the temperature at which the device according to the invention is triggered, should be as far as possible from the maximum permissible storage and operating temperature of the fuel or explosive, for example + 70 ° C, but also as far as possible from the autoignition temperature of the fuel or explosive lie away. at
- the desired release temperature is at least 90 ° C, in particular at least 100 ° C and at most 150 ° C, in particular at most 130 ° C. The more one man when the triggering temperature reaches the autoignition temperature, the more violent a potential explosive reaction can be. This will ensure that the fuel or
- Front side so are arranged opposite the nozzle of the rocket, located in the rocket fuel can be specifically ignited at a certain temperature.
- Tripping temperature is therefore preferably below the
- pressure-tight barrier at least one material whose
- Melting temperature is at least equal to the operating temperature of the device.
- the material of the barrier melts, whereby the liquid of the first substance flows to the second substance, mixes with the second substance and there is an exothermic reaction in which heat, hot particles and / or a hot gas flow to Ignition of the fuel or
- the pressure-tight barrier has at least one through-flow opening.
- the fusible material preferably has a melting temperature equal to the release temperature of the device.
- the material melts, so that the first substance comes into contact with the second substance through the flow-through opening and mixes with it, resulting in an exothermic reaction of the two substances.
- heat is released and / or hot particles and / or a hot
- the pressure-tight barrier is formed by at least one membrane which comprises a piercing device.
- the membrane is pierced when moving the membrane by means of the piercing device, whereby the first substance, which is in the liquid state at the triggering temperature comes in contact with the second substance, mixed with this and it comes to an exothermic reaction, in which heat, hot particles and / or a hot gas flow are released.
- the pressure-tight barrier is formed by a seal.
- Sealing has at least one through-flow opening, which is closed up to the release temperature of the device by a respective piston.
- the seal is preferably designed to be movable and separates the first substance below the triggering temperature of the second substance.
- the one or more pistons are firmly connected to the device in one embodiment and close below the release temperature of the device, the flow-through opening of the seal. If the internal pressure in the area of the first substance increases, the Seal moved so that the piston the
- Substance comes into contact with the second substance.
- the piston by a solder body to a shift
- this has a plurality of pressure-tight barriers, which in one or more of the embodiments of the barrier described above
- the device has several
- Barrier comprises a material whose melting temperature is at least equal to the release temperature of the device, and at least one second barrier, which is formed by a membrane comprising a piercing device, wherein at least a third barrier has a seal with a flow opening, which below the
- At least one further barrier has at least one through opening, which is closed with a material which is a
- the pressure-tight barriers can be in different
- the device has a high security against unwanted triggering of the device. Also at Combination of multiple barriers is a trip secured on reaching the trip temperature, so that the
- Fuels or explosives can burn off in a controlled manner.
- At least one first substance below the triggering temperature of the device has a higher pressure than at least one second substance.
- first substance may come in case of elimination of the barrier or upon opening of the barrier in contact with the second substance and mix with the second substance, wherein it to a
- the device is in one
- Combustion chamber of a rocket arranged in particular a solid rocket.
- Combustion chamber of the rocket of fuel or explosive arranged so that the fuel through the exothermic
- the device has an opening provided with a closure.
- the closure preferably comprises a material which is used in the
- the opening is released and hot particles of the substances located inside the device can escape from the device.
- the escaping hot particles ignite the fuels or explosives present in the combustion chamber of the rocket. It is possible to use the device described above also in other pyrotechnic components in which an early targeted inflammation is desirable at external slow heating.
- Figure 1 shows a section through an embodiment of the
- Figure 2 is a section through a rocket motor
- FIG. 1 shows schematically a section through a device 1, in which the housing 2 of the device 1 is divided by means of a partition wall 3 into two separate chambers. In the left chamber there is a first substance 5, in the right chamber a second substance 6. The first substance 5 is below the triggering temperature as a liquid.
- the exothermic reaction of the first substance with the second substance may be, for example, an oxidation reaction, a neutralization or a hydration. So can
- a reducing agent for example, a sugar melting below the triggering temperature, glycerine or the like with an oxidizing agent such as a sugar
- a Acid such as hydrochloric acid or a mixture of an acid with another substance, which is below the
- Triggering temperature is liquid, with a base, such as an alkali metal hydroxide, such as sodium hydroxide, react, so take place an exothermic neutralization reaction. It is also possible, for example, water or an aqueous mixture z. B. with an alkali or alkaline earth metal oxide, such as calcium oxide implement, so an exothermic hydration reaction
- Propellant for example, water below the
- Triggering temperature is present as water vapor to the first
- the dividing wall 3 has two flow-through openings 14, which are closed by pressure-tight barriers 7.
- the pressure-tight barriers 7 are preferably made of a material that melts at the release temperature of the device 1 and the flow openings 14 releases.
- the pressure-tight barrier 7 may consist of a low-melting solder, for example, a bismuth and / or lead-containing solder.
- the first substance 5 and the second substance 6 can be combined
- the device 1 has an outlet opening 12 in the region of the outer wall of the right chamber, which in the ground state with a closure. 4
- the shutter 4 is made of a material that melts at the triggering temperature of the device 1.
- This may be a low-melting, for example bismuth and / or lead-containing solder.
- This may be a low-melting, for example bismuth and / or lead-containing solder.
- FIG. 2 is a schematic section through a
- Rocket motor 9 shown.
- a device 1 is arranged in the end region of the combustion chamber 8, as shown for example in Figures 1, 3 and 4.
- the device 1 is in the immediate vicinity of that in the
- Combustion chamber 8 of the rocket motor 9 arranged fuel 13 is positioned. Due to the exothermic reaction inside the device 1, the arranged in the combustion chamber 8 of the rocket motor 9 fuel 13 below the
- Rocket motor 9 can come from the outside.
- the present in the combustion chamber 8 of the rocket motor 9 fuel 13 can be any one of the rocket motor 9 fuel 13.
- the Fuel 13 ignited by the hot housing 2 of the device 1.
- FIG. 3 schematically shows a further embodiment of the device 1, in which the pressure-tight barrier is formed by a membrane 10 which separates the first substance 5 from the second substance 6. Upon reaching the release temperature of the device 1, the first substance 5 has expanded so far that the membrane 10 in contact with a
- Penetration device 11 comes, wherein the membrane 10 is at least partially pierced. After piercing the membrane 10, the first substance 5 present in the liquid state of aggregation comes into contact with the second substance 6. The first 5 and the second 6 substance react exothermically with one another, wherein heat is generated.
- FIG. 4 shows a further embodiment of the device 1, in which the pressure-tight barrier is formed by a piston 16 and a seal 15.
- the seal 15 separates the first substance 5 from the second substance 6.
- the flow-through opening 14 of the seal 15 is closed in the ground state by a piston 16. Upon reaching the
- Throughflow opening 14 is opened from a certain expansion volume of the first substance 5.
- the first substance 5 comes in contact with the second substance 6, wherein an exothermic
- Reaction occurs in which heat, hot particles and / or a hot gas flow are released.
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Air Bags (AREA)
- Safety Valves (AREA)
- Physical Or Chemical Processes And Apparatus (AREA)
Abstract
Description
Claims
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PCT/EP2011/003376 WO2013004259A1 (de) | 2011-07-07 | 2011-07-07 | Vorrichtung zum abbrennen von treibstoffen oder explosivstoffen |
JP2014517469A JP5760148B2 (ja) | 2011-07-07 | 2011-07-07 | 燃料又は爆発物の制御された燃焼をするための装置 |
US14/131,274 US9803588B2 (en) | 2011-07-07 | 2011-07-07 | Device for burning off propellants or explosive substances |
KR1020147003174A KR101679133B1 (ko) | 2011-07-07 | 2011-07-07 | 추진연료 또는 폭발성 물질을 연소시키는 장치 |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PCT/EP2011/003376 WO2013004259A1 (de) | 2011-07-07 | 2011-07-07 | Vorrichtung zum abbrennen von treibstoffen oder explosivstoffen |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2013004259A1 true WO2013004259A1 (de) | 2013-01-10 |
Family
ID=44653228
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2011/003376 WO2013004259A1 (de) | 2011-07-07 | 2011-07-07 | Vorrichtung zum abbrennen von treibstoffen oder explosivstoffen |
Country Status (4)
Country | Link |
---|---|
US (1) | US9803588B2 (de) |
JP (1) | JP5760148B2 (de) |
KR (1) | KR101679133B1 (de) |
WO (1) | WO2013004259A1 (de) |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5466537A (en) * | 1993-04-12 | 1995-11-14 | The United States Of America As Represented By The Secretary Of The Navy | Intermetallic thermal sensor |
US5959235A (en) | 1995-02-16 | 1999-09-28 | Royal Ordnance Public Limited Company | Fire mitigation device |
EP2128559A2 (de) * | 2008-05-27 | 2009-12-02 | Bayern-Chemie Gesellschaft für flugchemische Antriebe mbH | Initiator |
EP2372299A2 (de) * | 2010-03-30 | 2011-10-05 | Bayern-Chemie Gesellschaft für flugchemische Antriebe mbH | Vorrichtung zum Abbrennen von Treibstoffen oder Explosivstoffen |
Family Cites Families (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB9503080D0 (en) * | 1995-02-16 | 1995-04-05 | Royal Ordnance Plc | Fire mitigation device |
-
2011
- 2011-07-07 JP JP2014517469A patent/JP5760148B2/ja active Active
- 2011-07-07 KR KR1020147003174A patent/KR101679133B1/ko active IP Right Grant
- 2011-07-07 WO PCT/EP2011/003376 patent/WO2013004259A1/de active Application Filing
- 2011-07-07 US US14/131,274 patent/US9803588B2/en active Active
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5466537A (en) * | 1993-04-12 | 1995-11-14 | The United States Of America As Represented By The Secretary Of The Navy | Intermetallic thermal sensor |
US5959235A (en) | 1995-02-16 | 1999-09-28 | Royal Ordnance Public Limited Company | Fire mitigation device |
EP2128559A2 (de) * | 2008-05-27 | 2009-12-02 | Bayern-Chemie Gesellschaft für flugchemische Antriebe mbH | Initiator |
EP2372299A2 (de) * | 2010-03-30 | 2011-10-05 | Bayern-Chemie Gesellschaft für flugchemische Antriebe mbH | Vorrichtung zum Abbrennen von Treibstoffen oder Explosivstoffen |
Also Published As
Publication number | Publication date |
---|---|
KR101679133B1 (ko) | 2016-11-23 |
KR20140051938A (ko) | 2014-05-02 |
JP2014525023A (ja) | 2014-09-25 |
US9803588B2 (en) | 2017-10-31 |
JP5760148B2 (ja) | 2015-08-05 |
US20140338306A1 (en) | 2014-11-20 |
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