EP0388264A1 - Zielmarkierungsvorrichtung zum Anziehen von zielsuchenden Geschossen - Google Patents

Zielmarkierungsvorrichtung zum Anziehen von zielsuchenden Geschossen Download PDF

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Publication number
EP0388264A1
EP0388264A1 EP90400636A EP90400636A EP0388264A1 EP 0388264 A1 EP0388264 A1 EP 0388264A1 EP 90400636 A EP90400636 A EP 90400636A EP 90400636 A EP90400636 A EP 90400636A EP 0388264 A1 EP0388264 A1 EP 0388264A1
Authority
EP
European Patent Office
Prior art keywords
marker
pyrotechnic
propulsion
barrel
casing
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.)
Withdrawn
Application number
EP90400636A
Other languages
English (en)
French (fr)
Inventor
Guy Le Parquier
Jean Dansac
Jean-Pierre Murgue
Paul Sergent
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.)
Thales SA
Original Assignee
Thomson CSF SA
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 Thomson CSF SA filed Critical Thomson CSF SA
Publication of EP0388264A1 publication Critical patent/EP0388264A1/de
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22—Homing guidance systems
    • F41G7/226—Semi-active homing systems, i.e. comprising a receiver and involving auxiliary illuminating means, e.g. using auxiliary guiding missiles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22—Homing guidance systems
    • F41G7/2273—Homing guidance systems characterised by the type of waves
    • F41G7/2293—Homing guidance systems characterised by the type of waves using electromagnetic waves other than radio waves
    • 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

Definitions

  • the present invention relates to an objective marker for attracting projectiles provided with a seeker.
  • the invention relates to the field of homing heads, in order to improve their precision and their efficiency towards objectives, in particular mobile land objectives, such as vehicles on wheels or tracks.
  • a known technique consists in illuminating the objective, generally with a laser beam. This requires, for an air-to-ground attack, the implementation of a complex system, mounted on board a nacelle under the carrier aircraft. The seeker is guided by the laser wave reflected by the terrestrial objective.
  • This technique was used in the present invention but modified so that the illuminator is no longer located at a distance from the objective, but on it.
  • This illuminator is constituted by a marker which comes to rest on the objective, without the knowledge of the operating personnel on board the objective.
  • the marking device is dropped or projected above the area comprising an objective to be marked. It is designed to be able to fix on this objective after a research phase, and to then activate a transmitter.
  • the waves emitted can be microwave waves, or infrared waves.
  • the marking thus obtained makes it possible to significantly increase the precision and the efficiency of guidance by seeker, and to reduce the price of the latter.
  • an objective marker for attracting projectiles provided with a seeker, is characterized in that it comprises: - an ovoid-shaped envelope having a flat end located near the center of gravity of the marker, so that the marker has only one stable position and that it always comes to rest on this end; - propulsion means, the propulsion being able to be stopped by an electrical control signal; - fixing means; - Means for transmitting a signal capable of attracting seekers, activatable by an electrical control signal; - control means for detecting a variation in magnetic flux and then supplying a control signal to the propulsion means and to the means for transmitting.
  • the goal is to launch towards a formation of objectives, for example armored vehicles, markers which are fixed on them then activate a transmitter, either microwave or infrared.
  • the markers according to the invention are designed to perform a search phase after release and impact on the ground.
  • the technique of multiple jumping mine is used. The marker moves several times, until it has found a target.
  • the total number of jumps achievable can be a few tens.
  • the marker detects its presence by its magnetic field, or by the vibrations it produces.
  • the marker can be considered as a submunition dropped by an air carrier which can be a missile, a bomb, a rocket, etc.
  • the carrier drops a hundred or more of these submunitions.
  • Figures 1 and 2 schematically represent a first embodiment of the marker according to the invention, and which is fixed on the objective by a magnet.
  • the marker has an ovoid outer shell 15 having a flat end 7, and its internal mass is distributed so that its center of gravity G is close to the flat end 7, so that the marker has a single stable position. After a fall, it always returns to this position of equilibrium.
  • This first exemplary embodiment comprises: a permanent magnet 1 flush with the flat end 7, a barrel of impellers 2 opening into a single nozzle 3 passing through the magnet 1, an explosive cord 4 for ejecting the barrel 2, an electronic circuit 5, and a power supply 6.
  • the elements 5 and 6 are located between the magnet 1 and the barrel 2.
  • the electronic circuit 5 comprises a microwave or infrared transmitter.
  • the magnet 1 comprises a magnetic core with a strong coercive field and a magnetic circuit. This can be either rigid or flexible to better stick to a wall and stay there despite vibrations.
  • a coil 11 Around the core is disposed a coil 11 whose purpose is to detect a variation in flux upon impact on a magnetic surface, in order to stop the jumps of the marker as soon as it is fixed on a target.
  • the winding 11 is, for example, circular and housed in a recessed part of the magnet 1, which is formed in the external face applying to the magnetic surface of the objective.
  • the impellers are distributed in a barrel 2 because they cannot be placed simply around the marking device, unless they are triggered in pairs, which would be an additional easement on ignition and would consume too much energy.
  • the distribution of the impellers in the barrel 2 is: either radial or vertical, in one or more layers, simple or in tandem.
  • FIG. 2 represents a section of this first exemplary embodiment, showing a barrel 2 made up of 19 charges of 3 elements 13, connected by pyrotechnic retarders 12.
  • FIG. 3 represents the forces acting on the marker: P represents the weight passing through G the center of gravity, -F represents the force of the gases leaving the nozzle 3, F1 represents the thrust applied to the center of gravity G, and FR represents the resulting force, according to which the marker is launched.
  • the angle ⁇ of the nozzle 3 with the longitudinal axis Z of the casing 15 is approximately 30 °, so that the resulting force FR is inclined.
  • a ground impact detector for example of the piezoelectric type, would provide insufficient energy during successive landings on soft ground. An electrical amplification and firing by each impeller would lead to significant electrical consumption.
  • the charges 13 are connected by pyrotechnic delay devices 12 each having a duration slightly greater than that of a jump, so as to give the electronic circuit 5 time to make a decision to continue the search. or not.
  • a firing device controllable by an electrical signal, ignites the first charge during the initial shock and then the charges 13 are triggered successively.
  • FIG. 4 illustrates the operation of this first exemplary embodiment when it touches an objective having a magnetic wall.
  • the magnet 1 sticks to the magnetic wall SM.
  • the coil 11 records the variation in flow and produces a signal which is processed by the electronic circuit 5 to trigger the firing of an explosive cord 4 which goes around the envelope 15, to cut it in two.
  • This firing ejects the barrel of impellers 2, and the upper part of the casing 15.
  • a part 8 which ensures the centered mounting of the barrel and its connection with the casing is also ejected.
  • the propulsion of the marker is thus stopped.
  • the marker is lightened by about half its weight and remains easily fixed on the magnetic surface SM.
  • the transmitter is put into service.
  • FIG. 5 schematically represents the electronic circuit 5 and the associated pyrotechnic device. They comprise: a ground impact detector 51, for example of the type piezoelectric, which triggers a device 12.1 for igniting the first charge 13.1. A second charge is then ignited automatically via the first pyrotechnic retarder 12.2, and so on until the last charge, 13.N.
  • the pyrotechnic device supplies a total of N successive pulses corresponding to the N charges that compose it. If the landing on a magnetic surface occurs before the end of these N pulses, the flux variation detected by the coil 11 produces a signal Sd which controls a device 52 for firing the cord 4 to stop the propulsion. This firing is accompanied by the activation of a transmitter 53.
  • a processor circuit 50 performs these various functions but some can be performed by other, simpler means. For example, the discharge of a capacitor, directly controlled by the detector 51, can be used to trigger the first firing device 12.1
  • the first being the variation in flux detected by the coil 11; and the second being the state of the vehicle (when driving or stopped), to avoid marking inert objects, for example: sheets, hangars, fences, destroyed vehicles.
  • the piezoelectric sensor 51 is in this case used to also detect the vibrations of the vehicle and take this second criterion into account. With a prior selection, for example by programming the processor 50, the marker will be able to take into account a single criterion or both. When the selected criteria are satisfied the detonating cord 4 is ignited.
  • each impeller contains one gram of powder, with a specific pulse 2500. If the whole of the marker weighs approximately 200 g, the initial speed is 12.5 m / s. With a thrust orientation at 30 ° from the vertical, the jumps are approximately 6 m high, 14 m long, and have a duration of 2 seconds, approximately.
  • the projectile to be guided is equipped with an antenna of 1 square decimetre and the band, when hooked up, is 100 kHz, a microwave transmitter of 10 mW is sufficient to ensure a signal to noise ratio equal to 20dB for a hanging at 10 km, and 40dB for hanging at 1 km.
  • the choice of wavelength is a compromise between the desired selectivity to avoid countermeasures and the precision necessary for hooking.
  • an omnidirectional radiation marker device may include integrated laser circuits, or light emitting diodes and diffractive optics.
  • the transmitted power can also be from 10 to 100 mW depending on the expected range and the cost envisaged for the marker.
  • the power supply 6 may consist of a bootable battery, a solution which offers great security.
  • the firing of the first charge is not triggered at the time of arrival on the ground, but subsequently, by an electromagnetic remote control signal, or by a proximity detector (acoustic, vibratory, etc. ).
  • the marker thus constitutes a pending marker, known as "dormant". It is possible to place or drop such markers in an area where the objectives to be reached may pass. The markers will then land on the vehicles during a passage nearby. The power supply will be determined, in this type of operation, to take into account the energy necessary for the proximity detectors for a certain period.
  • This variant can in particular be used at sea to attract not missiles but torpedoes, powered mines, etc.
  • the markers are fired from a shooting station, for example that of anti-tank weapons, and their supply is not ensured by a battery but via a wire connecting to a supply circuit located at the shooting station.
  • the system thus constituted by the shooting station and the remote markers then requires no human intervention to ensure the illumination function.
  • the fixing means consist of a net intended to make the marker integral with a vehicle whose wall is not magnetic: for example, a vehicle having a plastic bodywork or having shields reactive.
  • the magnetic fixing device is then partially replaced by a net folded inside the envelope 15.
  • FIG. 6 schematically shows a section of a second embodiment of the marker according to the invention, comprising, in addition to the elements described above, a thread 20 folded inside the envelope 15, and impellers 21 intended for propel the net, just after the upper part of the envelope 15 has been expelled by firing the cord 4.
  • this second example comprises a magnet 1 and a coil 11. They cannot detect a non-magnetic wall, nor fix the marker on it, but they can detect disturbances in the magnetic flux caused by elements other than the wall of the vehicle. This detection makes it possible to control the ejection of the net to grip the objective.
  • FIG. 7 shows the arrangement of the barrel of impellers 2, for propelling the marker, and the arrangement of six impellers 21 intended to project the net.
  • the impellers 21 are regularly arranged in a ring around the barrel 2. Openings 22 are regularly cut in the part 8 to allow ejection of the thread 20.
  • FIG. 9 shows the shape of the net 20 after it has been ejected from the marker.
  • the net has 6 strands radiating regularly around the marker 23, these strands being connected by strands of hexagonal shape having a center of symmetry centered on marker 23.
  • the net thus has the shape of a spider's web.
  • the total mass of the net is thus equivalent to that of magnet 1 of the first embodiment. If the attachment to the objective is only carried out by a net, only a small magnet remains, intended only to perceive variations in flux in metal parts. The total mass of the net and of this magnet can then be equal to that of the magnet 1 of the first exemplary embodiment. The total mass is then unchanged compared to the first embodiment.
  • the diameter of the deployed net is provided in relation to the size of the objectives on which the markers must be fixed. This diameter can be for example ten meters.
  • FIG. 8 illustrates the operating phase during which the upper part of the casing 15 is ejected and the net is deployed by igniting the impellers 21. Simultaneously, the barrel 2 is ejected and continues its jumps if the impellers it contains have not all been used.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Electromagnetism (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Geophysics And Detection Of Objects (AREA)
EP90400636A 1989-03-14 1990-03-09 Zielmarkierungsvorrichtung zum Anziehen von zielsuchenden Geschossen Withdrawn EP0388264A1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8903312 1989-03-14
FR8903312A FR2644575B1 (fr) 1989-03-14 1989-03-14 Marqueur d'objectif pour attirer des projectiles munis d'un autodirecteur

Publications (1)

Publication Number Publication Date
EP0388264A1 true EP0388264A1 (de) 1990-09-19

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EP90400636A Withdrawn EP0388264A1 (de) 1989-03-14 1990-03-09 Zielmarkierungsvorrichtung zum Anziehen von zielsuchenden Geschossen

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US (1) US5070790A (de)
EP (1) EP0388264A1 (de)
CA (1) CA2012106A1 (de)
FR (1) FR2644575B1 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2667139A1 (fr) * 1990-09-21 1992-03-27 Dornier Gmbh Systeme de barrage d'espace pour la reconnaissance et respectivement la lutte contre des objectifs terrestres, des objectifs aeriens ou analogues.
EP0848227A1 (de) * 1996-12-13 1998-06-17 Daimler-Benz Aerospace Aktiengesellschaft System zur Endphasenführung gelenkter autonomer Flugkörper

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5703314A (en) * 1996-11-20 1997-12-30 The United States Of America As Represented By The Secretary Of The Navy Infrared projector countermeasure system
FR2769154B1 (fr) * 1997-09-30 1999-12-03 Thomson Csf Dispositif de synchronisation precise
US20060132643A1 (en) * 2001-07-11 2006-06-22 Chang Industry, Inc. Deployable monitoring device having self-righting housing and associated method
US6831699B2 (en) * 2001-07-11 2004-12-14 Chang Industry, Inc. Deployable monitoring device having self-righting housing and associated method
EP1716386A2 (de) * 2003-09-27 2006-11-02 Diffraction Ltd. Geschoss mit zielzuweisung
WO2006086527A1 (en) * 2005-02-07 2006-08-17 Bae Systems Information And Electronic Systems Integration Inc. Radiation homing tag
US8556173B1 (en) 2010-03-17 2013-10-15 The United States Of America As Represented By The Secretary Of The Navy Apparatus and system for navigating in GPS denied environments

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3835749A (en) * 1962-10-26 1974-09-17 P Joneaux Weapon launching rockets and method to use the same
GB2029943A (en) * 1978-09-13 1980-03-26 Rheinmetall Gmbh Method of attacking ground targets
US4281809A (en) * 1979-12-13 1981-08-04 The United States Of America As Represented By The Secretary Of The Navy Method of precision bombing
US4448106A (en) * 1978-07-05 1984-05-15 Mcdonnell Douglas Corporation Method of identifying hard targets
DE3421607A1 (de) * 1984-06-09 1985-12-12 Dynamit Nobel Ag, 5210 Troisdorf Aufklaerungssystem
GB2201494A (en) * 1987-02-20 1988-09-01 Diehl Gmbh & Co Marking target objects

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3156185A (en) * 1960-12-20 1964-11-10 Hermann Joachim Triggering device for a movable body
GB1050490A (de) * 1961-12-23
US3983817A (en) * 1975-05-19 1976-10-05 Remington Arms Company, Inc. Spotting projectile
DE3304070A1 (de) * 1983-02-07 1984-08-09 Rheinmetall GmbH, 4000 Düsseldorf Sensortraeger
DE3508453A1 (de) * 1985-03-09 1986-09-11 Rheinmetall GmbH, 4000 Düsseldorf Nutzlastgeschoss
US4969398A (en) * 1989-12-04 1990-11-13 The United States Of America As Represented By The Secretary Of The Navy Lane marker

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3835749A (en) * 1962-10-26 1974-09-17 P Joneaux Weapon launching rockets and method to use the same
US4448106A (en) * 1978-07-05 1984-05-15 Mcdonnell Douglas Corporation Method of identifying hard targets
GB2029943A (en) * 1978-09-13 1980-03-26 Rheinmetall Gmbh Method of attacking ground targets
US4281809A (en) * 1979-12-13 1981-08-04 The United States Of America As Represented By The Secretary Of The Navy Method of precision bombing
DE3421607A1 (de) * 1984-06-09 1985-12-12 Dynamit Nobel Ag, 5210 Troisdorf Aufklaerungssystem
GB2201494A (en) * 1987-02-20 1988-09-01 Diehl Gmbh & Co Marking target objects

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2667139A1 (fr) * 1990-09-21 1992-03-27 Dornier Gmbh Systeme de barrage d'espace pour la reconnaissance et respectivement la lutte contre des objectifs terrestres, des objectifs aeriens ou analogues.
EP0848227A1 (de) * 1996-12-13 1998-06-17 Daimler-Benz Aerospace Aktiengesellschaft System zur Endphasenführung gelenkter autonomer Flugkörper

Also Published As

Publication number Publication date
FR2644575B1 (fr) 1991-05-31
US5070790A (en) 1991-12-10
CA2012106A1 (fr) 1990-09-14
FR2644575A1 (fr) 1990-09-21

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