EP2128559A2 - Initiateur - Google Patents
Initiateur Download PDFInfo
- Publication number
- EP2128559A2 EP2128559A2 EP09002559A EP09002559A EP2128559A2 EP 2128559 A2 EP2128559 A2 EP 2128559A2 EP 09002559 A EP09002559 A EP 09002559A EP 09002559 A EP09002559 A EP 09002559A EP 2128559 A2 EP2128559 A2 EP 2128559A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- initiator
- pressure
- threshold temperature
- reaching
- initiator according
- Prior art date
- 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.)
- Granted
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
- F42C15/00—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges
- F42C15/36—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein arming is effected by combustion or fusion of an element; Arming methods using temperature gradients
-
- 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
Definitions
- the invention relates to an initiator, in particular for solid rocket motors and warheads, which is triggered upon reaching a threshold temperature to reduce the effect of the ignition of the propellant or explosive of the solid rocket engine or warhead above the threshold 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. If a solid rocket motor, however, is heated by a fire, for example, to a threshold temperature of, for example 160 ° and more, a deflagration may possibly also occur explosion, the z. B. can have devastating consequences on a ship.
- the threshold temperature is significantly lower than with an airbag propellant.
- a low threshold firing powder for solid rocket engines is not available. The same applies to warheads.
- the object of the invention is therefore to provide an initiator which is triggered upon reaching a threshold temperature in order to reduce the effect of inflammation of the propellant or explosive in particular a solid rocket motor or warhead over, so beyond the threshold temperature.
- a pressure device is provided, the pressure of which is released when the threshold temperature is reached in order to trigger the initiator by converting the pressure into kinetic energy.
- the initiator ignites the propellant or explosive before it reaches the threshold temperature and thus by violent reaction (deflagration or detonation) causes great damage in the environment. Exceeding the threshold temperature is thus prevented according to the invention.
- the threshold temperature is the temperature at which a solid propellant deflagrates or explodes instead of a controlled burnup, or an explosive deflagrates or explodes. This temperature can depending on the fuel or explosive z. B. between 120 to 200 ° C, in particular between 140 and 180 ° C.
- the triggering temperature ie the temperature at which the initiator according to the invention is triggered, should be as close as possible to the threshold temperature. Preferably, however, a safety margin is met, the z. B. a maximum of 50 ° C, in particular a maximum of 30 ° C below the threshold temperature.
- the pressure device can be formed by a pressure chamber which is closed with a closure and contains a substance which, upon reaching the threshold temperature, generates a pressure which is sufficient to open the closure. The released pressure is then converted into kinetic energy, which leads to the triggering of the initiator.
- the substance in the pressure chamber may be water or another substance that has such a high vapor pressure at the threshold temperature that the closure of the pressure chamber is opened.
- the substance of the pressure chamber may also be a substance which decomposes at threshold temperature to form gas and thereby builds up a pressure which leads to the opening of the closure of the pressure chamber.
- the closure of the pressure chamber can be configured as desired, for example a plug. Preferably, however, it is formed by a rupture disk.
- the initiator may be an electrically controllable initiator, for.
- an initiator in which an ignition charge is ignited by an electrically heated wire (“Semi-conductor bridge initiators, SCB”). Possibly.
- the ignition charge can also be exploded electrically (“Exploding bridgewire initiators, EBW").
- a generator may be provided for power generation, which is driven with the released pressure. With the current generated by the generator then the initiator is driven. It can be z. B. to drive the generator, a turbine may be provided, which is driven by the released pressure.
- the generator which generates the current for driving the initiator, may also have a permanent magnet, which is movably guided in a coil.
- the permanent magnet is set in motion by the released pressure to produce a current pulse in the coil to drive the initiator.
- the initiator may also include a striker which causes an impact-sensitive primer, such as a primer, to ignite upon impact.
- a striker which causes an impact-sensitive primer, such as a primer, to ignite upon impact.
- the required for the impact of the firing pin to ignite the ignition charge can be applied by the pressure in the pressure chamber, which is released when the closure of the pressure chamber opens, so for example by rupture of the rupture disk.
- the firing pin for example, operate a switch to electrically control the initiator.
- the pressure device can also be formed by a prestressed spring, which is released upon reaching the threshold temperature.
- the firing pin but also z. B. the mentioned guided in a coil permanent magnet for generating electrical energy by a prestressed compression spring are set in motion.
- a bimetallic element may be provided, which engages over the prestressed spring and thus holds in the prestressed state and releases the preloaded spring when the threshold temperature is reached, for example by bending.
- the biased spring may be locked in a different manner, for example, by a holder made of a metal or other material that melts when the threshold temperature is reached.
- the forces can also be amplified by lever or otherwise. For example, it is possible with the pressure device to release a lock for a preloaded firing pin.
- the initiator according to the invention is thus actuated automatically when the threshold temperature is reached in order to prevent deflagration or detonation.
- a conventionally constructed main initiator is generally provided in order to start the solid rocket or to fire the warhead.
- the printing device z. B. to be provided with a heater to the invention Initiator to ignite the propellant or the explosive at ambient temperature, ie below the threshold temperature.
- the initiator according to the invention can also take over the function of the main initiator by being triggered by heating the pressure device to the threshold temperature.
- the initiator according to the invention is thus - in its passive function - triggered upon reaching the threshold temperature without any activation from the outside. It is characterized by a high level of insensitivity to electromagnetic waves, radiation, pulses, mechanical shocks and vibrations. Since it is also executable in a closed design, there is generally a high degree of insensitivity to environmental influences.
- the initiator according to the invention can be used without mechanical interruption of the pyrotechnic functional chain, which is normally necessary in order to prevent unintentional ignition due to disturbing influences.
- the initiator according to the invention can be used in a variety of ways, such as temperature-triggering initiator of a lighter of solid rocket engines, especially in the case of unintentional fast (“fast cook off, FCO”) and slower (“slow cook off, SCO”) heating.
- FCO fast cook off
- SCO slow cook off
- the firing pin or other set by the printing device in motion element can also trigger other functions and z.
- B. a switch for triggering active mitigating measures For example, in the manner of the following function chain:
- the element set in motion activates a thermal battery when a given threshold temperature is reached.
- a control logic can be operated, for example, evaluates the results of several mounted on the rocket engine temperature sensor and sets the last possible ignition, in which either by the pre-ignition of the propellant a violent reaction is avoided or another device, eg. B. initiation of a cutting cord to open the combustion chamber is set in motion.
- a mitigating action can be initiated on the warhead.
- the initiator can be designed so that when a predetermined threshold temperature initiates a cutting charge and thus z.
- B. opens the shell of the warhead by means of a cutting charge, thereby triggering a silent burning of the explosive charge.
- initiators according to the invention trigger in all cases when the permissible threshold temperature is reached. It can also be triggered functions that are not performed directly on the rocket motor or warhead, such as the triggering of mitigating measures during storage or transport, for example by release of an extinguishing agent z. B. in an arranged on the storage or transport container extinguishing agent container.
- the initiator 1 which is provided on the combustion chamber 2 of a solid rocket motor, has a pressure chamber 3 in which a substance or active medium 4, for example a liquid, is located.
- the pressure chamber 3 has an opening 5 which is closed by a rupture disk 6.
- the rupture disk 6 is provided with a firing pin 7, which is guided in a channel 8.
- a primer 9 is provided on a transfer charge 10, which communicates with a booster charge 11 which ignites the propellant charge 12 of the rocket motor.
- the channel 8, the transfer charge 10 with the primer 9 and the booster charge 11 are enclosed by a housing 14 which is provided for connecting the booster charge 11 to the combustion chamber 2 with an opening 13 and connected at the other end to the pressure chamber 3.
- the rupture disk 6 is held at the periphery between the housing 14 and the pressure chamber housing and weakened with a circular notch 6 'whose diameter corresponds to the diameter of the channel 8.
- the active medium 4 builds when heated to a temperature of z. B. 10 ° C below the predetermined threshold temperature, for example, 160 ° of the propellant charge 12 in the pressure chamber 3 to a pressure that leads to rupture of the rupture disk 6.
- the rupture disk 6 can also consist of a material whose strength is temperature-dependent. In any case, the rupture disk 6 is designed to burst at a pressure when a predetermined peeling temperature is reached.
- the gas After rupture of the rupture disk 6, the gas expands and accelerates in the channel 8 the firing pin 7, which strikes the primer 9 and thus on the transfer charge 10 and the boost charge 11 leads to the ignition of the propellant 12.
- the dimensions of the pressure chamber 3, the cross section of the channel 8 and its length and the mass of the firing pin 7 result from the energy required to ignite the primer 9, the threshold temperature and the active medium used. 4
- a (not shown) main detonator can be provided, with which the booster charge 11 is ignited.
- the initiator 1 after FIG. 1 also be designed as the main initiator.
- an electric heater with a heating element 16 with a holder and bushing 17 is provided.
- FIGS. 3 and 4 are provided for a (not shown) electrically controllable initiator.
- the embodiment differs FIG. 3 from the after FIGS. 1 and 2 essentially from the fact that the firing pin 7 is replaced by a rod-shaped permanent magnet 18 which is guided in a coil 19 to generate a current pulse for driving the initiator.
- the channel 8 is provided with a nozzle 19 which drives a turbine 20.
- the turbine 20 drives a generator 21, which generates the current pulse necessary for driving the initiator.
- FIGS. 5 and 6 differs from the one after Figure 1 to 4 essentially in that instead of the pressure chamber 3 to the channel 8, in which the firing pin 7 'is guided, a holder 25 is connected to a compression spring 26, the firing pin 7' in the biased position according to FIG. 5 loaded.
- a bimetallic element 27 is fixed, which in the in FIG. 5 shown locking position with a hook-shaped projection 28 in a retaining groove 29 on the firing pin 7 'engages.
- the bimetallic element 27 bends according to FIG. 6 , whereby the hook-shaped Projection 28 pulled out of the retaining 29 and thus the spring-loaded firing pin 7 'is released.
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Feeding, Discharge, Calcimining, Fusing, And Gas-Generation Devices (AREA)
- Air Bags (AREA)
- Toys (AREA)
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE200810025218 DE102008025218B3 (de) | 2008-05-27 | 2008-05-27 | Initiator |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| EP2128559A2 true EP2128559A2 (fr) | 2009-12-02 |
| EP2128559A3 EP2128559A3 (fr) | 2013-05-29 |
| EP2128559B1 EP2128559B1 (fr) | 2016-05-25 |
Family
ID=40765471
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP09002559.4A Not-in-force EP2128559B1 (fr) | 2008-05-27 | 2009-02-24 | Initiateur |
Country Status (2)
| Country | Link |
|---|---|
| EP (1) | EP2128559B1 (fr) |
| DE (1) | DE102008025218B3 (fr) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2372299A3 (fr) * | 2010-03-30 | 2012-04-18 | Bayern-Chemie Gesellschaft für flugchemische Antriebe mbH | Dispositif de combustion de propergols ou de matières explosives |
| WO2013004259A1 (fr) * | 2011-07-07 | 2013-01-10 | Bayern-Chemie Gesellschaft Für Flugchemische Antriebe Bmh | Dispositif pour faire se consumer des matières propulsives ou explosives |
| CN115585297A (zh) * | 2022-10-28 | 2023-01-10 | 大连船舶重工集团有限公司 | 一种适用于b型舱的温度敏感型爆破片 |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102010015047B4 (de) | 2010-04-15 | 2012-01-12 | Bayern-Chemie Gesellschaft Für Flugchemische Antriebe Mbh | Frühzündvorrichtung zum Abbrennen von Treibstoffen und Explosivstoffen |
| DE102010052150A1 (de) * | 2010-11-22 | 2012-05-24 | Bayern-Chemie Gesellschaft Für Flugchemische Antriebe Mbh | Rotationsenergiebereitsstellungsvorrichtung, Notstromaggregat und Luftfahrzeug |
| CN113187623B (zh) * | 2021-03-31 | 2022-09-27 | 上海新力动力设备研究所 | 一种固体火箭发动机用温度激励型自启动安全泄压装置 |
| DE102022000309A1 (de) | 2021-10-14 | 2023-04-20 | Rolf Schillinger | Sprengzünder mit einer Thermalbatterie |
Family Cites Families (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1294704B (de) * | 1961-01-20 | 1969-05-08 | Electronique Appliquee | Anordnung zur temperaturabhaengigen Ausloesung von elektrischen Vorgaengen |
| DE2217054A1 (de) * | 1972-04-08 | 1973-10-18 | Bayern Chemie Gmbh Flugchemie | Loescheinrichtung fuer feststoffgasgeneratoren und -raketentriebwerke |
| DE2756727C3 (de) * | 1977-12-20 | 1980-09-18 | Messerschmitt-Boelkow-Blohm Gmbh, 8000 Muenchen | Berstscheiben-Anordnung |
| US4262273A (en) * | 1979-11-29 | 1981-04-14 | Emerson Electric Co. | Thermostatic electrical switch |
| US4597261A (en) * | 1984-05-25 | 1986-07-01 | Hughes Aircraft Company | Thermally actuated rocket motor safety system |
| US5200574A (en) * | 1991-04-05 | 1993-04-06 | Morton International, Inc. | Universal squib connector |
| FR2707752B1 (fr) * | 1993-06-28 | 1995-09-22 | Giat Ind Sa | Chaîne d'amorçage de sécurité pour charge explosive. |
| US5494312A (en) * | 1994-05-31 | 1996-02-27 | Morton International, Inc. | Autoignition of a fluid fueled inflator |
| DE19709584A1 (de) * | 1997-03-08 | 1998-09-10 | Dynamit Nobel Ag | Gasgenerator |
| DE19805976C1 (de) * | 1998-02-13 | 1999-04-29 | Nigu Chemie Gmbh | Frühzündpulver für thermische Sicherungen für Airbag-Gasgeneratoren |
-
2008
- 2008-05-27 DE DE200810025218 patent/DE102008025218B3/de not_active Expired - Fee Related
-
2009
- 2009-02-24 EP EP09002559.4A patent/EP2128559B1/fr not_active Not-in-force
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2372299A3 (fr) * | 2010-03-30 | 2012-04-18 | Bayern-Chemie Gesellschaft für flugchemische Antriebe mbH | Dispositif de combustion de propergols ou de matières explosives |
| WO2013004259A1 (fr) * | 2011-07-07 | 2013-01-10 | Bayern-Chemie Gesellschaft Für Flugchemische Antriebe Bmh | Dispositif pour faire se consumer des matières propulsives ou explosives |
| KR20140051938A (ko) * | 2011-07-07 | 2014-05-02 | 바이에른-케미 게젤샤프트 퓌어 플루그케미쉐 안트리베 엠베하 | 추진연료 또는 폭발성 물질을 연소시키는 장치 |
| JP2014525023A (ja) * | 2011-07-07 | 2014-09-25 | バイエルン− ヒエミー・ゲゼルシヤフト・フユール・フルークヒエミッシエ・アントリーベ・ミト・ベシユレンクテル・ハフツング | 燃料又は爆発物の制御された燃焼をするための装置 |
| KR101679133B1 (ko) | 2011-07-07 | 2016-11-23 | 바이에른-케미 게젤샤프트 퓌어 플루그케미쉐 안트리베 엠베하 | 추진연료 또는 폭발성 물질을 연소시키는 장치 |
| US9803588B2 (en) | 2011-07-07 | 2017-10-31 | Bayern-Chemie Gesellschaft Fur Flugchemische Antriebe Mbh | Device for burning off propellants or explosive substances |
| CN115585297A (zh) * | 2022-10-28 | 2023-01-10 | 大连船舶重工集团有限公司 | 一种适用于b型舱的温度敏感型爆破片 |
Also Published As
| Publication number | Publication date |
|---|---|
| EP2128559A3 (fr) | 2013-05-29 |
| DE102008025218B3 (de) | 2009-11-12 |
| EP2128559B1 (fr) | 2016-05-25 |
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