EP0805333B1 - Method for creating a decoy target - Google Patents

Description

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.

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. At most modern missiles, the development clearly goes in the direction of multispectral homing systems, that work simultaneously or in series in the radar and infrared range in order to to be able to carry out an improved misdiagnosis. 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. The co-location of RF and IR effectiveness is accordingly a mandatory requirement for a dual mode decoy to use modern dual mode homing heads being able to effectively deceive, i.e. from an object to be protected to a To steer the apparent target. It is only the smallest possible resolution cell of the target seeker (RF and IR) relevant for the co-location.

A generic method is, for example, from "Le système 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 gamme de materials de guerre électronique", 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.

This object is achieved by a method according to claim 1.

Subclaims 2 to 14 describe preferred embodiments according to the invention.

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. If 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

eine Prinzipskizze zu einer Ausführungsform des erfindungsgemäßen Verfahrens;

Fig. 2

eine Schnittansicht einer Ausführungsform eines nach dem erfindungsgemäßen Verfahren arbeitenden Täuschkörpers;

Fig. 3

eine schematische Ansicht einer RF-Wirkmasse des Täuschkörpers von Fig. 2; und

Fig. 4

eine Schnittansicht einer weiteren Ausführungsform eines gemäß der vorliegenden Erfindung arbeitenden Täuschkörpers.

Further features and advantages of the invention will become apparent from the appended claims and the following description, in which the basic process sequence and two exemplary embodiments for decoys working according to the method according to the invention are explained with the aid of the accompanying drawings. It shows:

Fig. 1

a schematic diagram of an embodiment of the method according to the invention;

Fig. 2

a sectional view of an embodiment of a decoy working according to the inventive method;

Fig. 3

a schematic view of an RF active mass of the decoy of Fig. 2; and

Fig. 4

a sectional view of another embodiment of a decoy operating according to the present invention.

Phase I

Abschuß eines Täuschkörpers

Phase II

drallstabilisierte Flugphase des Täuschkörpers

Phase III

Ausstoß der IR- und RF-Wirkmasse und

Phase IV

Aktivierung und Verteilung der Wirkmassen

Fig. 1 serves to illustrate the basic process flow according to a particular embodiment of the invention. The method according to the invention can best be represented by the time course from the firing of a decoy working according to the method according to the invention to the distribution of the active masses. The course over time can be roughly divided into four phases:

Phase I

Firing a decoy

Phase II

spin-stabilized flight phase of the decoy

Phase III

Ejection of the IR and RF active mass and

Phase IV

Activation and distribution of the active masses

Fig. 1 shows the phases II to IV schematically. The ignition and the Phase I shoot goes as it is of technology. In phase II 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. In phase III, 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. This causes the distribution of the IR active mass, however in particular, the distribution of the RF active mass is sustainably improved becomes. In 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. With 1 is a complete Secondary part for inductive ignition energy absorption by one Primary part marked. The secondary part 1 consists of magnetic Material, preferably iron. In a secondary coil 2 the ignition energy is induced. 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. Another way to control the burning behavior consists in the known method of shaping, such as e.g. Star burner. 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 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. The use is also conceivable a freely programmable electronic ignition delay for variable determination of the flight duration. On 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. In the embodiment 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. In the embodiment 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. As 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 λ 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. In addition, 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. As material for the windings and through the entire RF active mass continuous protective films 31 and protective films 32 Capton® is preferred to prevent the dipoles from slipping into each other or Milinex® used. As 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.

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 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. Furthermore, 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.

Reference list

1

Secondary part for inductive ignition energy consumption

2nd

Secondary coil

3rd

Bottom cover

4th

Housing sleeve

5

Bottom ring

6

Pressure chamber

7

Squib

8th

Propellant charge

9

Rotational charge

9a

Rotary motor

10th

Rotary nozzle

11

Ignition retarders

12th

Connecting part

13

Ejection propellant

14

Spreading part for active masses

15

Ignition retarders

16

Exhaust pipe

17th

Discharge opening

18th

Ignition / disassembly kit

19th

IR active mass

20th

Cutting disc

21

RF active mass

22

Projectile sleeve

23

cover

24th

Sealing ring

25th

Closure piece

30th

dipole

31

Protective film

32

Protective film

33

Aluminum cover

33a

Paper sleeve

34

Securing element

Claims (14)

1. A method of preparing a decoy target for protection of land, air or water vehicles or the like from missiles comprising a target search head operating simultaneously or serially in the infrared (IR) or radar (RF) range or in both wavelength ranges, wherein a substance transmitting radiation in the IR range (IR active substance) and a substance reflecting RF radiation (RF active substance) are brought into operation in the correct position as a decoy target, wherein the IR active substance and the RF active substance are brought into operation simultaneously and at the same place, characterised in that

   after ignition and launching from a projectile cup, the active substances are positioned by a spin-stabilised decoy member projectile set in rotation and

   the IR active substance is then activated and distributed and the RF active substance is swirled and distributed by an activating and distributing device in the form of an ignition and blow-out unit disposed centrally in the decoy member projectile and around which the active substances are disposed one behind the other in the longitudinal direction of the decoy member projectile.
2. A method according to claim 1, characterised in that ignition and blow-out are effected by a pyrotechnic charge which is ignited by an ignition retarder which is ignited by combustion of a propellant charge for the decoy member projectile.
3. A method according to claim 2, characterised in that the pyrotechnic charge for the ignition and blow-out unit is burnt inside a tube disposed centrally in the projectile and with defined blow-out openings.
4. A method according to any of the preceding claims, characterised by use of an RF active substance, the surface of which is surrounded by a paper, cardboard or plastic sheet casing.
5. A method according to any of the preceding claims, characterised in that, in a spin-stabilised flight phase with defined oncoming flow against the active substances, the active substances including the activating and distributing device are simultaneously ejected from a projectile casing by means of a production part.
6. A method according to claim 5, characterised in that the production part is ejected by a propellant charge ignited by the ignition retarder, which is preferably pyrotechnic.
7. A method according to any of the preceding claims, characterised in that the ignition member projectile is set in rotation by a pyrotechnic rotation rotor.
8. A method according to any of claims 1 to 7, characterised in that the ignition member projectile is set in rotation by suitably designed pulling means in the projectile cup.
9. A method according to any of claims 1 to 7, characterised in that the decoy member projectile is set in rotation by suitably designed spoiler surfaces on the decoy member projectile.
10. A method according to any of the preceding claims, characterised in that the RF active substance comprises rolled-together radar dipoles (chaff) of aluminium-coated or silver-coated glass fibre threads having a thickness in the range from about 10 to 100 µm.
11. A method according to any of the preceding claims, characterised by use of dipole packets so disposed that they open immediately on blow-out.
12. A method according to any of the preceding claims, characterised by use of dipole packets protected by at least one heat shield from the blow-out heat.
13. A method according to claim 12, characterised in that the or each heat shell is at least one elastic foil or sheet which extends through the entire RF active substance.
14. A method according to any of the preceding claims, characterised by use of dipole packets which are protected from slipping into one another by at least one heat-resistant foil or sheet between respective packets.

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