EP2295927A2 - Corps volant doté d'une charge pyrotechnique - Google Patents

Corps volant doté d'une charge pyrotechnique Download PDF

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Publication number
EP2295927A2
EP2295927A2 EP10009315A EP10009315A EP2295927A2 EP 2295927 A2 EP2295927 A2 EP 2295927A2 EP 10009315 A EP10009315 A EP 10009315A EP 10009315 A EP10009315 A EP 10009315A EP 2295927 A2 EP2295927 A2 EP 2295927A2
Authority
EP
European Patent Office
Prior art keywords
missile
mixture
density
fuel
oxidizing agent
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
Application number
EP10009315A
Other languages
German (de)
English (en)
Other versions
EP2295927A3 (fr
EP2295927B8 (fr
EP2295927B1 (fr
Inventor
Arno Hahma
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Diehl Defence GmbH and Co KG
Original Assignee
Diehl BGT Defence GmbH and Co KG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Diehl BGT Defence GmbH and Co KG filed Critical Diehl BGT Defence GmbH and Co KG
Publication of EP2295927A2 publication Critical patent/EP2295927A2/fr
Publication of EP2295927A3 publication Critical patent/EP2295927A3/fr
Application granted granted Critical
Publication of EP2295927B1 publication Critical patent/EP2295927B1/fr
Publication of EP2295927B8 publication Critical patent/EP2295927B8/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41J—TARGETS; TARGET RANGES; BULLET CATCHERS
    • F41J2/00—Reflecting targets, e.g. radar-reflector targets; Active targets transmitting electromagnetic or acoustic waves
    • F41J2/02—Active targets transmitting infrared radiation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
    • F42B12/38—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information of tracer type
    • F42B12/382—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information of tracer type emitting an electromagnetic radiation, e.g. laser beam or infrared emission
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
    • F42B12/40—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information of target-marking, i.e. impact-indicating type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
    • F42B12/44—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information of incendiary type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/72—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the material
    • F42B12/74—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the material of the core or solid body
    • 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

Definitions

  • the invention relates to a missile with a pyrotechnic composition, wherein the missile is designed so that the pyrotechnic composition is deflagratively brought to combustion under normal use of the missile.
  • a missile As a decoy, which simulates the trajectory of a real aircraft as closely as possible and thereby generates a strong infrared radiation (IR radiation). Regardless of whether it is a kinematic or powered decoy target, this must be aerodynamically stable, so that the trajectory of a real aircraft can be replicated as accurately as possible and thereby the desired illusion effect is achieved.
  • IR radiation infrared radiation
  • a disadvantage of this missile is that the nasal weight usually contributes more than 50% to the mass of the missile to be accelerated and at the end of the mission falls to the ground at high speed and can cause great damage.
  • the object of the present invention is to provide an alternative aerodynamically stable missile.
  • a missile is provided with a pyrotechnic composition, wherein the missile is designed such that the pyrotechnic composition is deflagratively burned when the missile is used as intended, wherein the pyrotechnic composition comprises a mixture comprising at least one metal or metal alloy as fuel and containing at least one metal oxide as the oxidizing agent, wherein the fuel and the oxidizing agent are selected so that they can react by burning together, the mixture being compressed to a density of at least 85% of the theoretical density of the mixture, wherein the fuel, the oxidizing agent and the ratio between the fuel and the oxidizing agent is chosen so that the density of the mixture is at least 6 g / cm 3 .
  • the focus of the missile can be adjusted by the positioning of the mixture so that good flight characteristics are achieved.
  • the non-reactive nose weight frequently provided in the prior art can be dispensed with.
  • the payload of the missile is thereby increased simultaneously because the pyrotechnic composition contained therein, in contrast to the nose weight is not an inert mass.
  • it can be avoided by the burning of the pyrotechnic rate that a greater cause when falling to the ground damage arranging inert mass.
  • the missile according to the invention can be designed by the provision of a corresponding ignition means so that the pyrotechnic composition is deflagratively brought to combustion under normal use of the missile.
  • the ignition means may either be a conventional igniter or a further pyrotechnic composition which burns off before the pyrotechnic composition, the combustion of which initiates the combustion of the pyrotechnic composition.
  • the missile can be designed so that when striking a designated target ignition of the pyrotechnic set takes place. Irrespective of whether the mixture is ignited by impact or by an ignition means, it is known to the person skilled in the art how to design the missile such that the pyrotechnic composition is deflagrated when the missile is used as intended.
  • the fuel and the oxidant so that they can react with each other by burning.
  • it combines a metal or a metal alloy as fuel with a metal oxide as the oxidizing agent, wherein the metal of the metal oxide has a higher normal potential than the metal or the metal alloy, d. H. the metal of the metal oxide in the voltage series is above the fuel metal or the metal alloy serving as fuel.
  • the fuel may be present as a powder of at least one metal or at least one metal alloy or as a mixture of powders of at least one metal and at least one metal alloy.
  • the oxidizing agent may be present as a powder of at least one metal oxide or at least one composite oxide of metals or as a mixture of powders of at least one metal oxide and at least one composite oxide of metals.
  • the mixture may additionally contain at least one binder.
  • binder is particularly useful when it turns out during compaction that the mixture does not have good cohesion.
  • Particularly suitable binders are polytetrafluoroethylene (PTFE Teflon) and / or fluorine rubber (Viton), because these polymers themselves have a relatively high density and at the same time serve as further oxidizing agents because of the fluorine contained therein to about 70 wt .-%.
  • PTFE Teflon polytetrafluoroethylene
  • Viton fluorine rubber
  • the binder should be used in the least amount possible to still have a high density of the mixture.
  • the mixture may contain graphite, bentonite, lead powder, tin powder, bismuth powder, indium, glycerol and / or phenolic resin.
  • the mixture does not contain tungsten or does not contain tungsten as the sole fuel.
  • tungsten has relatively poor burn-off properties. It is particularly unsuitable as a fake target as the sole fuel in one embodiment of the missile because it burns too slow and not enough IR radiation is emitted during its combustion.
  • tungsten is well suited as an addition to a further metal or metal alloy with good burn-off properties, because it has a high density of 19.3 g / cm 3 and its admixture can achieve a high density of the mixture.
  • the density of the mixture may be at least 7 g / cm 3 , in particular at least 7.85 g / cm 3 , in particular at least 8 g / cm 3 , in particular at least 9 g / cm 3 , in particular at least 10 g / cm 3 .
  • 7.85 g / cm 3 is the density of ordinary steel.
  • the nasal weight which is usually made of steel, can be replaced by the mixture without the missile geometry having to be substantially changed.
  • missiles according to the invention can increase the range and the duration of the stable flight by increasing the density of the mixture and thereby possibly be increased with the missile to achieve target accuracy.
  • the pyrotechnic composition in the direction of flight of the missile is arranged only in its front half, in particular only in the front third, in particular only in the front quarter, in particular only in the front fifth.
  • the direction of flight of the missile is determined by the design of the missile, in particular its aerodynamic shape. The further the center of gravity of the missile is shifted to the front, the better are its flight characteristics.
  • the missile is formed as in flight by burning of the pyrotechnic IR radiation emitting decoy or bullet, especially small caliber bullet.
  • the pyrotechnic IR radiation emitting decoy or bullet especially small caliber bullet.
  • the amount of the mixture is preferably such that it can burn off completely in the air.
  • One Deceleration of the missile by its air resistance is lower than in missiles with pyrotechnic masses of lower density.
  • the IR radiation emitted by the burning of the pyrotechnic charge may be blackbody radiation.
  • the missile is a projectile, such.
  • a projectile such.
  • the pyrotechnic composition may be contained in the projectile or at least partially form the projectile. In the latter case, the pyrotechnic set is not surrounded by a metal shell, but also forms the outside of the projectile itself.
  • the pyrotechnic composition may be coated, for example with a lacquer, in order to protect it from environmental influences, such as moisture.
  • the effect of the projectile can be adjusted so that the bullet transfers kinetic energy when hitting a soft target just like a conventional bullet, and the pyrotechnic set is impinged upon a hard target by the bullet inflicted with the impact striking and thereby burned in the target is brought.
  • a fire can be set in motion at the finish. Avoiding the reaction when hitting a soft target also prevents such a bullet from violating the Geneva Convention.
  • the missile may have another pyrotechnic set, which emits IR radiation during combustion. If this further pyrotechnic composition emits a spectral IR radiation during combustion, it is advantageous if this further pyrotechnic composition is burned off before the pyrotechnic composition. Otherwise, a blackbody radiation produced during the burning down of the pyrotechnic composition would mask the spectral radiation and thus prevent a desired effect of the decoying target. However, if the further pyrotechnic composition emits blackbody radiation like the pyrotechnic composition, the missile may also be designed such that the pyrotechnic composition and the further pyrotechnic composition at least partially burn off simultaneously. This can cause a very strong emission of IR radiation.
  • the missile is designed as a dummy target with a further pyrotechnic composition for generating IR radiation
  • the ratio of the density of the pyrotechnic composition to the density of the further pyrotechnic composition is at least 1.9, in particular at least 3, in particular at least 4 .
  • the missile according to the invention may have a tip formed from the pyrotechnic composition.
  • the tip is currently usually made of steel.
  • the high density pyrotechnic material is so strong that it can replace this steel tip. This can be avoided that the tip remains after the burning of the pyrotechnic charge. Furthermore, material can be saved and the missile thereby made cheaper.
  • the tip can be coated. For this purpose, it may be coated, for example, with a lacquer, in particular a lacquer based on phenolic resin or chloroprene. This protects the tip, for example against moisture or mechanical damage. Furthermore, persons handling the missile are protected from toxic substances which may be contained in the pyrotechnic composition.
  • a massive reaction product is meant a reaction product which is solid and can fall to the ground and thereby cause significant damage.
  • No massive reaction product within the meaning of the invention are a liquid reaction product, ash, dust, smoke and particles whose size and / or density are so low that they are slowed down so much by falling through their air resistance that they cause no significant damage on the ground can do by transmitting kinetic energy.
  • the fuel, the oxidizing agent, if present, the binder and the ratio between the fuel and the oxidizing agent and the binder, if present, are selected such that only gaseous and / or fumed reaction products remain when the mixture burns off.
  • the fuel may be zirconium.
  • the pyrotechnic composition may additionally contain an impact-ignitable substance as an igniter.
  • the substance may be, for example, a mixture of barium peroxide and magnesium or zirconium and another oxidizing agent.
  • the fuel, the oxidizing agent, if present, the binder and the amount ratio between the fuel and the oxidizing agent and the binder, if present, are selected so that the energy density of the mixture is at least 1 kJ / cm 3 , especially at least 4 kJ / cm 3 , in particular at least 8 kJ / cm 3 , in particular at least 12 kJ / cm 3 , is.
  • the higher the energy density of the mixture the more intense is the redox reaction between the fuel and the oxidant associated with the burnup, and the more IR radiation is emitted and the less solid residues are formed.
  • the quantitative ratio between the fuel and the oxidant is selected so that the oxygen balance of the mixture is zero. This maximizes the energy density of the mixture for a given fuel and oxidant. Unless such a high energy density is required, the component of the mixture having the highest density may be used in excess to increase the density of the mixture.
  • the mixture is compressed to a density of at least 90%, in particular at least 95%, in particular at least 97%, in particular at least 98%, of the theoretical density of the mixture.
  • this can also ensure that the strength of the mixture is so high that in that at least part of the outer surface of the missile can be formed by the mixture.
  • the metal or metal alloy may include hafnium, zirconium, tungsten, tantalum, nickel, niobium, titanium, aluminum, boron, and / or silicon.
  • the oxidizing agent comprises cupric oxide (CuO), lead dioxide (PbO 2 ), samarium trioxide (Sm 2 O 3 ), indium trioxide (In 2 O 3 ), tungsten trioxide (WO 3 ), tin dioxide (SnO 2 ), nickel oxide (NiO ), Lanthanum trioxide (La 2 O 3 ), cobalt oxide (CoO), iron trioxide (Fe 2 O 3 ), manganese dioxide (MnO 2 ), bismuth subnitrate (Bi 2 O 2 NO 3 ), molybdenum trioxide (MoO 3 ), barium chromate (BaCrO 4 ) , Strontium chromate (SrCrO 4 ), barium nitrate (Ba (NO 3 ) 2 ), potassium perchlorate (KCIO 4 ) and / or bismuth trioxide (Bi 2 O 3 ).
  • CuO cupric oxide
  • PbO 2 samarium trioxide
  • the metal oxide may also be a mixed oxide.
  • the mixture in particular with a paint or resin, in particular a phenolic resin or chloroprene, be coated.
  • the coating can also be achieved in addition to protection against moisture or other environmental influences and protection of persons handling the missile from toxic substances contained that the mixture is ignited delayed. This can be advantageous depending on the application.
  • Sham targets are missiles that are burned during the flight and thereby emit IR radiation and thereby distract enemy missiles from their actual target, such as an airplane. Burning usually only takes a few seconds.
  • the missile is stored in a sleeve 12.
  • the sleeve 12 can also serve as a launching device.
  • the also referred to as a pulse cartridge sleeve 12 is in Fig. 1 to be seen only in the rear view, but not in the sectional view. In Fig. 2 the sleeve is also not shown.
  • the further pyrotechnic phrase 1 of in Fig. 1 The missile shown represents its main active mass.
  • This main active mass essentially consists of a mixture of eg magnesium, Teflon and fluoro rubber (Viton) emitted during the burnup of black body radiation.
  • This active material often referred to as MTV, has a density of about 1.9 g / cm 3 .
  • the density of the further pyrotechnic composition should not exceed 2 g / cm 3, or not significantly, in order to achieve a weight distribution between the pyrotechnic composition 2 and the further pyrotechnic composition 1 that is favorable for the flight characteristics of the missile.
  • the pyrotechnic composition 2 comprises a mixture of a metal or a metal alloy as a fuel, a metal oxide as an oxidant and a binder, the mixture being compressed to a density of at least 85% of the theoretical density and the density of the mixture at least 6 g / cm 2 is.
  • the pyrotechnic composition 2 can be used as nose weight and an aspect ratio between the pyrotechnic composition 2 and the further pyrotechnic composition 1 of about 1 to 2 can be realized, ie the length of the heavy component is about one third of the total length of both pyrotechnic compositions 1 and 2. This has proved to be particularly favorable for the flight characteristics.
  • the missile also has an active mass 4 with the same composition as the main active mass in the further pyrotechnic composition 1. Outside the active mass 4, the wings 5 of a tail are arranged in Fig. 2 are clearly visible and stabilize the attitude of the missile.
  • conventional sliding safety 3 is arranged to prevent accidental ignition.
  • a seal 10 is provided in a groove. The seal 10 serves to prevent hot combustion gases from flowing past the sliding safety device 3 in the sleeve 12 when the missile is completed, thereby igniting the active mass 4, the further pyrotechnic composition 1 and / or the pyrotechnic composition 2 prematurely. Furthermore, by preventing the combustion gases from flowing past, a higher muzzle velocity at the completion can be achieved.
  • the tail forming the wings 5 and the anti-sliding device 3 with the seal 10 the entire in Fig. 2 illustrated missile from the pyrotechnic composition 2, the further pyrotechnic composition 1 and the active mass 4.
  • the active mass 4 and / or at least part of the further pyrotechnic composition 1 may be coated.
  • a paint also protects against the influence of moisture.
  • the attitude of the decoy shown here is kept stable.
  • the further pyrotechnic composition 1 and the pyrotechnic composition 2 are ignited in flight by an ignition device, not shown here, and emit infrared radiation.
  • the active mass 4 is ignited by the already burning further pyrotechnic composition 1.
  • the pyrotechnic composition 2 is preferably dimensioned and optionally ignited by a coating so delayed that it is at least partially preserved during the entire combustion process. So he can bring about the stabilization of the attitude caused by its high density until the end of the burning process.
  • the pyrotechnic composition 2, the further pyrotechnic composition 1 and the active mass 4 are completely burnt down in flight, so that only the anti-sliding device 3 with the seal 10 and the vanes 5 remain as small unburnt masses, which fall on the ground can not cause any material damage.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Electromagnetism (AREA)
  • Health & Medical Sciences (AREA)
  • Optics & Photonics (AREA)
  • Toxicology (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Thermal Sciences (AREA)
  • Air Bags (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
EP10009315.2A 2009-09-11 2010-09-08 Corps volant doté d'une charge pyrotechnique Active EP2295927B8 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102009041366A DE102009041366A1 (de) 2009-09-11 2009-09-11 Flugkörper mit einem pyrotechnischen Satz

Publications (4)

Publication Number Publication Date
EP2295927A2 true EP2295927A2 (fr) 2011-03-16
EP2295927A3 EP2295927A3 (fr) 2014-04-02
EP2295927B1 EP2295927B1 (fr) 2017-04-05
EP2295927B8 EP2295927B8 (fr) 2017-05-31

Family

ID=43108038

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10009315.2A Active EP2295927B8 (fr) 2009-09-11 2010-09-08 Corps volant doté d'une charge pyrotechnique

Country Status (3)

Country Link
US (1) US8518196B2 (fr)
EP (1) EP2295927B8 (fr)
DE (1) DE102009041366A1 (fr)

Cited By (3)

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WO2017029303A1 (fr) * 2015-08-17 2017-02-23 Ruag Ammotec Ag Matériau composite et procédé de fabrication correspondant pour projectiles
AT516929B1 (de) * 2015-03-10 2018-05-15 Hirtenberger Automotive Safety Gmbh & Co Kg Pyrotechnischer Gasgenerator
CN110749241A (zh) * 2019-10-22 2020-02-04 百特（福建）智能装备科技有限公司 一种亮珠定量灌装机

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US8418619B1 (en) * 2008-01-03 2013-04-16 Kilgore Flares Company, Llc Kinematic countermeasure
DE102011116594B4 (de) 2011-10-21 2022-02-03 Diehl Defence Gmbh & Co. Kg Verwendung von Zirkonium oder eines Zirkonium enthaltenden Gemischs
CN103694066A (zh) * 2013-12-30 2014-04-02 贵州久联民爆器材发展股份有限公司 一种固体粒状物料的过筛和定量分装方法及装置
US20150337414A1 (en) * 2014-05-22 2015-11-26 Aerojet Rocketdyne, Inc. Composition for reactive material
DE102017007747A1 (de) * 2017-08-16 2019-04-18 Diehl Defence Gmbh & Co. Kg Flugkörper und dessen Verwendung
DE102018104333A1 (de) * 2018-02-26 2019-08-29 Rwm Schweiz Ag Geschoss mit pyrotechnischer Wirkladung
CN111348979A (zh) * 2018-12-20 2020-06-30 南京理工大学 一种燃烧剂及其制备方法
US10970852B2 (en) 2019-04-01 2021-04-06 Alloy Surfaces Company, Inc. Systems and methods for multi-signature countermeasure testing
US11015906B2 (en) * 2019-10-17 2021-05-25 Sharon Lulay Aerial reconnaissance marking projectile

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Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AT516929B1 (de) * 2015-03-10 2018-05-15 Hirtenberger Automotive Safety Gmbh & Co Kg Pyrotechnischer Gasgenerator
WO2017029303A1 (fr) * 2015-08-17 2017-02-23 Ruag Ammotec Ag Matériau composite et procédé de fabrication correspondant pour projectiles
EP3736524A1 (fr) * 2015-08-17 2020-11-11 RUAG Ammotec AG Matière composite et procédé correspondant pour balles
CN110749241A (zh) * 2019-10-22 2020-02-04 百特（福建）智能装备科技有限公司 一种亮珠定量灌装机
CN110749241B (zh) * 2019-10-22 2022-08-16 百特（福建）智能装备科技有限公司 一种亮珠定量灌装机

Also Published As

Publication number Publication date
EP2295927A3 (fr) 2014-04-02
EP2295927B8 (fr) 2017-05-31
DE102009041366A1 (de) 2011-05-26
EP2295927B1 (fr) 2017-04-05
US20110168047A1 (en) 2011-07-14
US8518196B2 (en) 2013-08-27

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