EP0805333B1 - Verfahren zum Bereitstellen eines Scheinziels - Google Patents

Verfahren zum Bereitstellen eines Scheinziels Download PDF

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Publication number
EP0805333B1
EP0805333B1 EP97105393A EP97105393A EP0805333B1 EP 0805333 B1 EP0805333 B1 EP 0805333B1 EP 97105393 A EP97105393 A EP 97105393A EP 97105393 A EP97105393 A EP 97105393A EP 0805333 B1 EP0805333 B1 EP 0805333B1
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EP
European Patent Office
Prior art keywords
projectile
ignition
decoy
active substance
blow
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.)
Expired - Lifetime
Application number
EP97105393A
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German (de)
English (en)
French (fr)
Other versions
EP0805333A3 (de
EP0805333A2 (de
Inventor
Heinz Bannasch
Fritz Greindl
Martin Fegg
Johannes Grundler
Günther Lenniger
Rudolf Salzeder
Helmut Pröschkowitz
Martin Wegscheider
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.)
Buck Neue Technologien GmbH
Original Assignee
Buck Neue Technologien GmbH
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
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Application filed by Buck Neue Technologien GmbH filed Critical Buck Neue Technologien GmbH
Priority to EP00108677A priority Critical patent/EP1026473B1/de
Publication of EP0805333A2 publication Critical patent/EP0805333A2/de
Publication of EP0805333A3 publication Critical patent/EP0805333A3/de
Application granted granted Critical
Publication of EP0805333B1 publication Critical patent/EP0805333B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41H—ARMOUR; ARMOURED TURRETS; ARMOURED OR ARMED VEHICLES; MEANS OF ATTACK OR DEFENCE, e.g. CAMOUFLAGE, IN GENERAL
    • F41H11/00—Defence installations; Defence devices
    • F41H11/02—Anti-aircraft or anti-guided missile or anti-torpedo defence installations or systems
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41H—ARMOUR; ARMOURED TURRETS; ARMOURED OR ARMED VEHICLES; MEANS OF ATTACK OR DEFENCE, e.g. CAMOUFLAGE, IN GENERAL
    • F41H9/00—Equipment for attack or defence by spreading flame, gas or smoke or leurres; Chemical warfare equipment
    • 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
    • F42B12/56—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 for dispensing discrete solid bodies
    • F42B12/70—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 for dispensing discrete solid bodies for dispensing radar chaff or infrared material

Definitions

  • the present invention relates to a method for providing a dummy target for Protection of land, air or water vehicles or the like from missiles, the one in the infrared (IR) or radar (RF) range or one in both wavelength ranges have simultaneous or serial target search head, according to the preamble of claim 1.
  • IR infrared
  • RF radar
  • a threat from modern, autonomously operating missiles will increase significantly, because even missiles with the most modern homing systems by the collapse of the former Great power of the Soviet Union and in particular through generous export regulations Asian countries are widespread.
  • the targeting systems of such missiles work mainly in the radar range (RF) and in the infrared range (IR). Both the radar backscatter behavior and the radiation of specific infrared radiation from targets, such as. Ships, planes, tanks etc., used for target finding and target tracking.
  • RF radar range
  • IR infrared range
  • targets such as. Ships, planes, tanks etc.
  • Multispectral IR homing heads work with two detectors in the short- and long-wave infrared range are sensitive, to differentiate wrong targets.
  • So-called dual mode homing heads work in the radar and infrared range. Missiles with such seekers are in the Approach and search phases are radar-controlled and switch to an IR seeker head in the tracking phase around or switch him to it.
  • a target criterion of dual mode homing heads is the co-location of the RF backscatter and the IR radiation center of gravity. By the Possible target coordinate comparison can be wrong targets (e.g. clutter, like decoys old Species) can be better sorted out.
  • a generic method is, for example, from “Le ancestral franco-britannique Sibyl”, Revue International De Defense, Cointrin-Genève, Volume 15, No. 10, 1982, pages 1405 to 1408, (basis for the preamble of claim 1) "Cartouche-leurre Gemini”, Revue International De Defense, Cointrin-Genève, Volume 10, No. 3, 1997, page 500, "Wallop élargit sa Jur de materials de boat opposition", Revue International De Defense, Cointrin-Genève, Volume 15, No. 12, 1982, page 1741 to 1744, and US-A-3,841,219.
  • the invention is based on the object of further developing the generic method in such a way that that IR and / or RF guided missiles are safe from an actual one Aim, that is, an object to be protected, directed away and directed towards an apparent target become.
  • the invention is based on the surprising finding that when used simultaneously an IR and an RF active mass, which simultaneously and at the same place (co-location) Be brought into effect, thereby providing an effective dummy target, the dual-mode seekers, but also only in one wavelength range (IR or RF range) Working seekers distracted from an object to be protected that the projectile is set in rotation, on the one hand to stabilize the projectile in the trajectory and to the other home reaching the destination by the centrifugal force an effective Ensure turbulence and disassembly of the active masses.
  • the active masses with a projectile sleeve surrounding them is shot through a special embodiment of the method according to the invention, in which the active substances together with the Activation and distribution device ejected from the projectile sleeve and only subsequently activated and distributed, also a good 3-dimensional distribution in the air reached.
  • Fig. 1 shows the phases II to IV schematically.
  • the ignition and the Phase I shoot goes as it is of technology.
  • the decoy shows a spin-stabilized flight phase in order to define a defined phase To reach the inflow of the RF and IR active mass.
  • the Angular momentum remains largely until the active masses are distributed received and is transferred to the active mass, which in turn an improved distribution of the active mass results.
  • the active substances including an activation and in-flight distribution mechanism ejected the projectile sleeve of the camouflage body to a subsequent one Distribution of the active masses without achieving insulation, which has the advantage that the distribution of Active masses do not exert excessive pressure on the active masses.
  • phase IV there will be an effective distribution of active substances through rotation and air flow as well as a central one Blow out achieved.
  • Fig. 2 shows a longitudinal section through a decoy, the according to the particular embodiment of the inventive method works.
  • the secondary part 1 consists of magnetic Material, preferably iron.
  • the windings of the secondary coil 2 consist of copper wire treated with insulating varnish. The number of windings preferably corresponds to that a primary coil, but with a transformation is possible in principle.
  • a preferably flanged bottom cover 3 serves as the lower fuse closure of the decoy.
  • the bottom cover 3 is preferably made of metal.
  • a version made of glass or carbon fiber reinforced plastic is also possible.
  • the outer launching body forms a housing sleeve 4, which is preferably made of pure aluminum an aluminum content of more than 99%.
  • the housing sleeve 4 remains in the magazine.
  • a bottom ring 5 represents a distance to a pressure chamber 6 ago.
  • the pressure chamber 6 takes that Propellant gas, which when a propellant charge 8 burns off Ejection of the decoy floor is created. Furthermore the pressure chamber 6 is necessary to complete a To form pressure chamber for the ignition of a rotary engine.
  • the Propellant charge 8 is ignited by means of a squib 7 and exists preferably from a powder driving set, preferably Black powder or black powder-like propellants such as nitrocellulose powder.
  • Rotational charges 9 preferably consist of pressed powder fuel with additional binder for mechanical Stabilization, e.g. Black powder with plastic binder, or from a commercial solid rocket propellant. Density, shape, surface and depth of the rotating charges 9 determine the erosion parameters such as the erosion duration and pulse / time unit. The specific impulse is through the choice of Propellant set.
  • the rotational charges 9 are preferred tablet-shaped and preferably in Combustion chambers (see reference number 10) pressed. This Pressing the rotary charges 9 is mainly used for Stabilization of the erosion behavior, since that of the metal and Areas of the rotary charges not facing the combustion chamber 9 don't burn. There is also the possibility that Controlling erosion behavior by passivating the surfaces.
  • the amount of the rotary charge 9 is dependent of the erosion behavior and the desired pulse-time behavior. For this embodiment, there was a burn-up time of about 1.5 seconds.
  • the reference number 10 denotes Rotation nozzles including those already mentioned above Combustion chamber.
  • the rotary nozzles consist of one Nozzle neck and a nozzle cone, both of which are preferably made be milled or drilled in a full aluminum casting.
  • the nozzle cone preferably has an incline of approximately 10 ° to 20 ° from the nozzle axis.
  • the nozzle neck length is preferred smaller than the nozzle cone length.
  • the combustion chamber is preferably cylindrical.
  • the combustion chambers are connected by an annular channel to equalize pressure to achieve, which causes a uniform burn.
  • the nozzle axis is inclined radially to the projectile. Preferably the nozzle axis should be more than 30 ° to the radius of the projectile be inclined, since otherwise the impulse to generate little contributes to the rotation. Angles greater than 80 ° to the radius cause excessive turbulence at the transition from the combustion chamber to the Nozzle neck and thus a weakening of the thrust.
  • An ignition retarder 11 is used to determine the route to Ejection of an IR active mass 19 and an RF active mass 21.
  • the Ignition delay 11 is pyrotechnic and has one Burning time of 2 seconds. Such ignition retarders are commercially available.
  • Connecting part 12 connects the rotary motor to a spreading part 14 for the active masses 19 and 21.
  • the connecting part 12 includes the ignition retarder 11 and an ejection propellant 13 for ejecting the spreading part 14.
  • the connecting part 12 is preferably made of metal.
  • the ejection propellant 13 comprises a powder driving set, preferably black powder or black powder-like propellants such as nitrocellulose.
  • the Discharge part 14 serves as a sabot for the ejection propellant 13 and is designed such that it as a holder for an ignition retarder 15 and for a blow-out pipe 16.
  • the application part 14 is preferably made of a cast aluminum or milled part.
  • the ignition delay 15 includes a pyrotechnic delay piece, which is an ignition / disassembly kit 18 ignites when the application part 14 the projectile sleeve has left.
  • the ignition delay 15 has a burning time of about 0.1 seconds.
  • the blow-out pipe 16 serves as a sensor for the ignition / disassembly kit 18 and for controlling the blow-out speed.
  • the blowing speed depends on the Length of the blow pipe 16 and the ratio of the total cross section from blow-out openings 17 to the amount of ignition / dismantling kit 18. In general it can be said that the higher the amount of ignition / dismantling kit 18 and the smaller the The total cross section of the blow-out openings 17 is the larger the blowing speed is.
  • the ratio is preferably chosen so that a blow-out time of 0.1 seconds is reached.
  • the blow-out pipe 16 must be manufactured in this way be that if possible no plastic deformation during of the blowing process occurs.
  • the exhaust pipe 16 was made of steel.
  • the exhaust openings 17 must be attached so that a uniform Distribution of the RF and IR active masses 19 and 21 reached becomes. This is preferably achieved in such a way that one Blow-out opening 17 meets a position of the RF active mass 21.
  • the ignition / disassembly set 18 comprises a pyrotechnic set, a comparable amount of gas as a burn-up product delivers. Magnesium barium nitrate is preferred for this purpose or aluminum perchlorate.
  • the amount of kindling / disassembly kit 18 depends on the blow-out pipe 16.
  • the IR active mass 19 contains the from German patent DE-PS 43 27 976 known IR active mass with MWIR flares. Are basically however, all IR active materials can be used, which are characterized by an ignition charge activate. In the embodiment disc-shaped MWIR flares with 1/3 division used.
  • a cutting disc 20 protects the RF active mass 21 from the burning MWIR flares of the IR active mass 19.
  • the cutting disc 20 can be made of metal or preferably fire-resistant foil be made. The design of the RF active mass 21 is more detailed shown in Fig. 3.
  • RF active mass 21 Radar dowels rolled up with dipoles for heat protection reasons made of aluminum or silver coated glass fiber threads used with a thickness in the range of about 10 to 100 microns.
  • the dipole length is 17.9 mm. But they are also dipole lengths Possible and planned from approx. 1 mm to approx. 25 mm.
  • the number the wraps of the individual dipole packages (chaff packages) variable from 1 upwards. Preferably for the packages 1.5 windings used.
  • the output of the active masses before Activation and distribution as well as the appropriate "packaging" the dipole serves to avoid clumping and merging and a dipole to dipole distance of about 7 to 10 ⁇ and thus to generate a high radar backscatter cross section.
  • the packaging must always be flexible enough, the dipoles and release them without external influence before the heat from the ignition and blow-out charge protect.
  • the packaging of the dipoles is based on the distribution principle coordinated, i.e. the packaged dipoles are like this arranged that they open immediately when blowing out.
  • Capton® is preferred to prevent the dipoles from slipping into each other or Milinex® used.
  • intermediate foils 32 can aluminum foils of various thicknesses can also be used.
  • a thin aluminum shell 33, but also a paper or Cardboard sleeve can be that the RF active mass 21 after Ejection from the projectile sleeve is not immediately distributed, but instead remains together until the ignition / splitter charge 18 burns. This ensures that the total energy of the Charge can act on the RF active mass 21.
  • a lid 23 serves to complete a projectile sleeve 22 and fixed from above the blow-out pipe 16.
  • the cover 23 can be made of heavy metals, such as. Cast iron or brass, to be manufactured Center of gravity of the decoy as far forward as possible move. This allows stabilization in addition to rotation of the flight.
  • the lid 23 is through sealed a sealing ring 24 to the projectile sleeve 22, the preferably made of aluminum with a purity of over 99% is drawn.
  • 25 represents a closure piece of the blow-out pipe 16 represents and ensures that the relatively dangerous fragmentation charge introduced as the last step in the decoy can be.
  • FIG. 4 is another embodiment of a decoy shown that according to a particular embodiment of the method works. 4 are the same reference numerals as used in Fig. 2. In the following, i.w. only on the differences to be entered into the decoy according to FIG. 2. An essential difference is that the projectile no projectile sleeve (identified by reference number 22 in FIG. 2) having. The IR active mass 19 and RF active mass 21 is not sufficient before it is activated and distributed a projectile sleeve are ejected and are thus the ejection propellant (marked with reference number 13 in FIG. 2) for the application part 14 and the ignition retarder (with Reference number 15 in Fig. 2) is no longer necessary and therefore not available.
  • the projectile no projectile sleeve identified by reference number 22 in FIG. 2 having.
  • the IR active mass 19 and RF active mass 21 is not sufficient before it is activated and distributed a projectile sleeve are ejected and are thus the ejection propellant (marked with reference
  • the application part 14 also serves no longer for ejecting the active masses 19, 21 from a projectile sleeve.
  • the RF active mass 21 is from a paper or Cardboard sleeve 33a instead of an aluminum sleeve (reference number 33 in Fig. 3) surrounded.
  • This paper or cardboard sleeve 33a is sufficient together with the central exhaust pipe 16, the RF active mass 21 despite the inflow of air in the flight phase before to hold the actual activation and distribution together.
  • On Securing element 15, ensures front pipe safety.
  • the Rotational charge (reference numeral 9 in Fig. 2) and rotary nozzle (Reference number 10 in Fig. 2) by a rotary motor 9a replaced.
  • the decoy shown in Fig. 4 has the missing bullet sleeve has the advantage that it is in proportion to make a decoy with bullet sleeve easier and is much cheaper.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Optical Radar Systems And Details Thereof (AREA)
EP97105393A 1996-05-03 1997-04-01 Verfahren zum Bereitstellen eines Scheinziels Expired - Lifetime EP0805333B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP00108677A EP1026473B1 (de) 1996-05-03 1997-04-01 Verfahren zum Bereitstellen eines Scheinziels und darin verwendbares Teilkörpergeschoss

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19617701 1996-05-03
DE19617701A DE19617701C2 (de) 1996-05-03 1996-05-03 Verfahren zum Bereitstellen eines Scheinziels

Related Child Applications (1)

Application Number Title Priority Date Filing Date
EP00108677A Division EP1026473B1 (de) 1996-05-03 1997-04-01 Verfahren zum Bereitstellen eines Scheinziels und darin verwendbares Teilkörpergeschoss

Publications (3)

Publication Number Publication Date
EP0805333A2 EP0805333A2 (de) 1997-11-05
EP0805333A3 EP0805333A3 (de) 1998-01-14
EP0805333B1 true EP0805333B1 (de) 2000-11-08

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ID=7793179

Family Applications (2)

Application Number Title Priority Date Filing Date
EP00108677A Expired - Lifetime EP1026473B1 (de) 1996-05-03 1997-04-01 Verfahren zum Bereitstellen eines Scheinziels und darin verwendbares Teilkörpergeschoss
EP97105393A Expired - Lifetime EP0805333B1 (de) 1996-05-03 1997-04-01 Verfahren zum Bereitstellen eines Scheinziels

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EP00108677A Expired - Lifetime EP1026473B1 (de) 1996-05-03 1997-04-01 Verfahren zum Bereitstellen eines Scheinziels und darin verwendbares Teilkörpergeschoss

Country Status (7)

Country Link
US (1) US5835051A (da)
EP (2) EP1026473B1 (da)
JP (1) JP3181240B2 (da)
DE (3) DE19617701C2 (da)
DK (2) DK0805333T3 (da)
SG (1) SG55308A1 (da)
TW (1) TW355204B (da)

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DE102005020159B4 (de) * 2005-04-29 2007-10-04 Rheinmetall Waffe Munition Gmbh Tarn- und Täuschmunition zum Schutz von Objekten gegen Lenkflugkörper
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DE102011120929A1 (de) 2011-12-14 2013-06-20 Rheinmetall Waffe Munition Gmbh Schutzsystem, insbesondere für Schiffe, gegen radargelenkte Bedrohungen
DE102012010378A1 (de) 2012-05-29 2013-12-05 Rheinmetall Waffe Munition Gmbh Munition mit Wirkmitteln
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RU2542688C1 (ru) * 2013-07-01 2015-02-20 Денис Борисович Дубинин Устройство для запуска гранат
US20150323296A1 (en) * 2013-10-01 2015-11-12 Omnitek Partners Llc Countermeasure Flares
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RU2651319C1 (ru) * 2017-01-27 2018-04-19 Федеральное государственное казенное военное образовательное учреждение высшего образования "ВОЕННАЯ АКАДЕМИЯ МАТЕРИАЛЬНО-ТЕХНИЧЕСКОГО ОБЕСПЕЧЕНИЯ имени генерала армии А.В. Хрулева" Способ защиты объектов бронетанковой техники и устройство для его реализации
CN108310765B (zh) * 2017-12-14 2021-07-27 腾讯科技（深圳）有限公司 图像的显示方法和装置、存储介质、电子装置
US11255643B2 (en) 2018-02-05 2022-02-22 Advanced Material Engineering Pte Ltd System for countering an unmanned aerial vehicle (UAV)
CN108830023B (zh) * 2018-07-26 2022-07-15 北京理工大学 一种炮射导弹增速发动机点火过程的预测方法
RU191978U1 (ru) * 2019-05-23 2019-08-29 Федеральное государственное бюджетное учреждение "Центральный научно-исследовательский испытательный институт инженерных войск" Министерства обороны Российской Федерации Имитатор тепловой цели
DE102019117801A1 (de) 2019-07-02 2021-01-07 Rheinmetall Waffe Munition Gmbh Scheinziel, System und Verfahren zum Schützen eines Objekts

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2019206485A2 (de) 2018-04-27 2019-10-31 Rheinmetall Waffe Munition Gmbh Verfahren und vorrichtung zum schutz eines fahrzeugs vor einer bedrohung

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SG55308A1 (en) 1998-12-21
JPH112499A (ja) 1999-01-06
JP3181240B2 (ja) 2001-07-03
TW355204B (en) 1999-04-01
DE19617701C2 (de) 2000-01-13
EP1026473B1 (de) 2002-08-07
US5835051A (en) 1998-11-10
EP0805333A3 (de) 1998-01-14
EP0805333A2 (de) 1997-11-05
DK199900457U1 (da) 1999-12-30
DE59707940D1 (de) 2002-09-12
DE59702585D1 (de) 2000-12-14
EP1026473A1 (de) 2000-08-09
DE19617701A1 (de) 1997-11-20

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