EP0918205A1 - Projektil mit radialer Wirkrichtung - Google Patents

Projektil mit radialer Wirkrichtung Download PDF

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Publication number
EP0918205A1
EP0918205A1 EP98120293A EP98120293A EP0918205A1 EP 0918205 A1 EP0918205 A1 EP 0918205A1 EP 98120293 A EP98120293 A EP 98120293A EP 98120293 A EP98120293 A EP 98120293A EP 0918205 A1 EP0918205 A1 EP 0918205A1
Authority
EP
European Patent Office
Prior art keywords
projectile
target
payload
rotation
projectile according
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP98120293A
Other languages
English (en)
French (fr)
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EP0918205B1 (de
Inventor
Thierry Bredy
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.)
Giat Industries SA
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Giat Industries SA
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Filing date
Publication date
Application filed by Giat Industries SA filed Critical Giat Industries SA
Publication of EP0918205A1 publication Critical patent/EP0918205A1/de
Application granted granted Critical
Publication of EP0918205B1 publication Critical patent/EP0918205B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • 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
    • F42B12/04—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of armour-piercing type
    • F42B12/10—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of armour-piercing type with shaped or hollow charge
    • F42B12/14—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of armour-piercing type with shaped or hollow charge the symmetry axis of the hollow charge forming an angle with the longitudinal axis of the projectile
    • 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
    • F41G7/222—Homing guidance systems for spin-stabilized missiles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C13/00—Proximity fuzes; Fuzes for remote detonation
    • F42C13/006—Proximity fuzes; Fuzes for remote detonation for non-guided, spinning, braked or gravity-driven weapons, e.g. parachute-braked sub-munitions

Definitions

  • the technical field of the invention is that of projectiles, in particular anti-shooters, acting radially from their target.
  • Known projectiles include a military head explosive, generally with a nucleating charge, of which initiation is triggered by the detection of a target at by means of a sensor.
  • the sensors usually used are of technology infrared or radar. Usually these projectiles have means for controlling their roll position so as to keep their load oriented in the direction desired.
  • Patent FR2406800 thus describes a projectile provided with a load formed with radial action.
  • the downside of such projectile is that it is necessary to provide means complex ensuring its roll control so that the charge can hit a target.
  • These means of control do can only be ordered after processing of target detection provided by a high-performance warhead sensor, sensor able to detect the target in particular before passing over it by the projectile.
  • the projectile according to the invention therefore has an area efficiency and can, in a simple way and without impair flight stability, ensure detection and destruction of a target placed on the ground or possibly at above him or laterally.
  • the subject of the invention is a projectile, in particular an anti-tank missile projectile and comprising at least one payload combining at least one explosive military head and at least one target sensor, military head having a direction of action inclined relative to the axis of the projectile and whose initiation is triggered as a result of detection of a target by the sensor, the latter having a direction of observation close to the direction of action, projectile characterized in that it comprises means for scanning to ensure for the payload at a instant on trajectory, a ratio of speed longitudinal V on the speed of rotation ⁇ which is less than or equal to a limit value so as to ensure a sweep of the ground by the direction of observation with a step sufficiently reduced to allow detection of the target.
  • the limit value will advantageously be chosen equal to 3 m.
  • the scanning means include a device for increase the speed of rotation of the payload to a instant on trajectory and / or a device ensuring the payload translational braking.
  • the device allowing to increase the load rotation speed useful comprises at least one pyrotechnic impeller whose direction of action is oriented so that it causes a rotation of the payload around its axis.
  • the device for translational braking comprises at least one impeller pyrotechnics, the direction of action for all impellers being substantially confused with the axis of the payload.
  • the device for translational braking includes a means of increasing the aerodynamic drag of the payload.
  • the payload is a submunition ejected from the projectile on its trajectory, under ammunition carrying a braking device and / or a device for rotating relative to the projectile.
  • the payload may be integral with the projectile which includes a braking device and / or a rotation.
  • the projectile may include a proximity rocket intended to trigger the scanning means on approach of a target.
  • the projectile may also include means for chronometry intended to trigger the scanning means a some time after firing the projectile.
  • the projectile may finally include a receiver of a remote control signal, signal intended to trigger the scanning means.
  • a projectile 1 according to a first embodiment comprises an envelope 2 containing a payload 3 and extended at its part rear with deployable tail 4.
  • the payload essentially comprises a head explosive military 5 and a target sensor 6.
  • the military head has an inclined direction of action 7 relative to the axis 8 of the projectile. This direction here is substantially perpendicular to the axis 8 of the projectile.
  • the military head is a nucleus-generating charge comprising in a known manner, an explosive charge 9 placed in a containment envelope 11, loading on which a coating 10 is applied.
  • Sensor 6 is an infrared sensor operating in the range of 3 to 5 micrometers for example it is arranged at neighborhood of a window 13, transparent to infrared and arranged in the envelope 2 of the projectile. Sensor 6 has a observation direction 12 which is parallel to the direction of action 7 of the load.
  • Envelope 2 of the projectile also contains a unit computer 14 which receives the signals supplied by a clock 15 and by the sensor 6.
  • This calculation unit is intended for control, on the one hand the triggering of a device pyrotechnic 16 allowing the speed of rotation of the projectile (and its payload) and other part of causing the initiation of the explosive charge 9.
  • the calculation unit is linked by a first connection 17 to an igniter 18 which ignites a gas pyrotechnic generator 19.
  • the pyrotechnic device 16 is also visible on the sectional view of Figure 1b.
  • the gas generator 19 is connected by radial pipes 22a, 22b to nozzles gas ejection 23a, 23b. These nozzles are oriented by relative to the shell 2 of the projectile so as to eject the gas in two directions 24a and 24b which are symmetrical relative to the axis 8 of the projectile and in a plane perpendicular to this one. The effect of the gases generated by the generator 19 will therefore rotate the projectile and its payload around its axis 8.
  • An infantryman 25 is equipped with a recoilless fire system 26 for launching a projectile 1 according to the invention.
  • This firing system will be conventionally equipped with a laser rangefinder (not shown) for determining the distance D1 separating the shooter from a target, such as a tank 27a or a helicopter 27b (here D1 is the average distance).
  • a laser rangefinder not shown for determining the distance D1 separating the shooter from a target, such as a tank 27a or a helicopter 27b (here D1 is the average distance).
  • the firing line secured to the launcher 26 contains in different memories or registers the characteristics ballistic of the projectile (initial speed, coefficient of ballistic train), characteristics introduced in the form firing tables. She deduces from these tables, depending on the distance D1 at which the target is located, an instant to which the gas generator 19 must be initiated so that the projectile is rotated at a distance D from the shooter.
  • D will be chosen less than D1 by a few meters (about 15 m) to ensure stabilization of the new rotation regime before approaching or overflying the target.
  • This instant of initiation is introduced into the unity of calculation 14 in the form of a flight time of the projectile.
  • a sensor not shown, for example an accelerometer
  • the calculation unit 14 takes into account the signals provided by the clock 15 to continuously determine the duration of flight of the projectile.
  • the projectile is animated at its exit from the launcher 26 of a moderate speed (around 10 t / s) which allows to ensure its stability on the trajectory. This rotation is obtained in a conventional manner by bending the fins of the tail 4.
  • the unit 14 calculates the ignition of the gas generator 19.
  • This is dimensioned so as to cause a increased speed of rotation of projectile 1 around of its axis 8.
  • the speed increase should be such that the ratio V / ⁇ of the longitudinal velocity V of the projectile on its rotation speed ⁇ is less than or equal to a value limit so as to ensure a sweep of the ground by the direction of observation with a step (P) sufficiently reduced to allow target detection.
  • the limit value (called scanning step) will be generally chosen equal to 3 m so as to ensure at least two scans of a land target such as a tank.
  • Figures 2a and 2b show traces 28 of observation direction 12 intersections with the ground or a target plan.
  • Traces 28 are substantially straight for a projectile whose direction of observation 12 is perpendicular to the axis of projectile 8 (as shown here). They would be hyperbolic if the direction of observation was tilted towards the front of the projectile.
  • the pitch P is sufficiently reduced to ensuring the detection of an appropriate target such as a tank.
  • sensor 6 When sensor 6 detects a target whose signature infrared corresponds to that stored in the unit computation 14, the latter causes the initiation of the primer 21 and the military head shot 5.
  • the projectile's rotational movement ensures scanning by the direction of observation 12 of all the space around the projectile.
  • the projectile can also detect and attack a aerial target such as a helicopter 27b.
  • the calculation unit 14 will advantageously contain in memory the characteristics infrared of the different targets that the projectile is likely to attack. It will then be possible to program before firing the type of target sought (tank or helicopter), in this case the calculation unit will not cause the firing of the charge only when a detected target will match actually to the desired target.
  • means will be provided ensuring the non taking into account the signals delivered by the sensor 6 during the flight time of the projectile up to distance D. This in order to avoid false target detection.
  • the invention therefore makes it possible, with a relatively structure simple to define a multi-purpose projectile (anti-tank or anti helicopter).
  • a proximity detector will be provided, for example of radar, infrared, acoustic or magnetometric, arranged in the projectile warhead (instead of and place of the clock marked 15 in FIG. 1a) and capable of detect the approach of a target at a distance of the order of 15 m.
  • the calculation unit will use the signal supplied by this detector to initiate the initiation of the gas generator 19.
  • a signal transmitter (of laser or radio optical technology) on the firing system and an appropriate receiver will be placed in the projectile.
  • the fire control will then determine the optimal moment of triggering by measuring the distance from the target and the target at which the projectile is located.
  • the projectile is provided with scanning means which allow to ensure for the payload, at a given time on trajectory, a ratio of the longitudinal speed V to the rotation speed ⁇ which is less than or equal to one limit value.
  • These scanning means are constituted by a device pyrotechnic 16 for rotation which includes a gas generator 19 allowing, for a speed longitudinal V given, to increase the speed of rotation ⁇ of the projectile.
  • a gas generator 19 allowing, for a speed longitudinal V given, to increase the speed of rotation ⁇ of the projectile.
  • the scanning means will be constituted by a braking device.
  • FIG. 3 describes such an embodiment of the projectile according to the invention.
  • This projectile differs from that previously described in this that it has at its rear part in place of the pyrotechnic device for rotating a device 39 in translational braking.
  • This device comprises a pyrotechnic composition gas generator 37 initiated by an igniter 38 connected to the calculation unit 14 by a connection 33.
  • the rest of the internal projectile payload 3 is identical to that of the projectile previously described.
  • the projectile therefore contains an explosive military head 5, a target sensor 6, a computing unit 14 and a clock 15.
  • the gases generated by composition 37 are directed by pipes 40 to ejection nozzles 41 regularly distributed radially and arranged in the envelope 2 of the projectile. These nozzles have axes which materialize directions of ejection 42, inclined relative to the axis 8 of the projectile, and oriented towards the front of the latter.
  • the calculation unit 14 will cause at the desired time ignition of the gas generator 37 which will have the effect of braking the longitudinal speed V of the projectile.
  • Projectile 1 is again fired by a firing system without recoil 26 implemented by an infantryman.
  • the calculation unit is programmed by the infantryman to from data supplied by the fire control (not shown).
  • Projectile 1 is then fired, it is animated during firing with a longitudinal speed of the order of 200 m / s and with a rotation speed of the order of 35 t / s.
  • the calculation unit causes the initiation of the gas generator 37.
  • the axial speed of the projectile decreases about 50% and approaches 100 m / s. This results in a V / ⁇ ratio which becomes lower than the limit P allowing sweep the ground by the observation direction with a sufficiently small pitch to allow detection of the target.
  • the advantage of this embodiment is that the translational braking device does not use any moving part and therefore has excellent reliability.
  • Figures 5a and 5b show a projectile in a third embodiment.
  • This mode differs from the previous ones in that the payload 3 consists of an ejectable submunition outside the envelope 2 of the projectile 1 at a given time on path.
  • the casing 2 of the projectile 1 thus comprises a part rear cylindrical 2a and a front ogivated part 2b which contains a chronometric rocket 43 connected to a charge of unloading 44.
  • the stripping charge is isolated from the submunition 3 by a piston 45.
  • the submunition is made integral by rotation of the casing by pins (not shown) which will be sheared when ejected.
  • the rear part of the envelope 2a is closed by a bottom 46 bearing the tail 4.
  • the submunition 3 comprises a case 47 closed by two covers 48 and 49.
  • Case 47 contains a military head explosive 5 as well as a target sensor 6.
  • head military and sensor respectively have directions of action and detection substantially perpendicular to axis 8 of the projectile which coincides with the axis of the sub ammunition.
  • the submunition 3 also contains a calculation unit 14 which receives the signals supplied by the sensor 6 and which commands the initiation of the detonator 21 of the military head 5 and the igniter 18 of a pyrotechnic gas generator 19.
  • the calculation unit is also connected to a sensor acceleration 50 which is intended to detect the instant ejecting the submunition from the envelope 2.
  • the gas generator 19 is also visible in section at Figure 5b. It is structurally analogous to that described previously with reference to Figures 1a, 1b.
  • radial tubes 22a, 22b connecting the pyrotechnic composition 19 to gas ejection nozzles 23a, 23b.
  • These nozzles are oriented relative to the envelope 47 of submunition 3 so as to eject the following gases two directions 24a and 24b which are symmetrical with respect to axis 8 of the projectile and submunition and in a plane perpendicular to this one.
  • the effect of the gases generated by the generator 19 will therefore rotate the submunition around its axis 8.
  • FIGS 6a and 6b show two successive phases of the operation of this particular embodiment.
  • the projectile is fired by a non-weapon system shown and rocket 43 received (as for the modes of previous productions) a program such as the initiation of the decanting composition 44 takes place at a distance D from the shooter less than the distance D1 shooter / target.
  • the gas pressure of the stripping composition is exerted on the piston 45 which pushes the submunition 3 in the direction of what causes the shearing of pins for retaining the bottom 46 of the projectile.
  • the submunition 3 therefore separates from the envelope 2 of the projectile (fig 6a). It continues its trajectory longitudinal with a speed V in the same direction as that that she previously had inside the projectile and substantially the same value (the mass of the submunition being much higher than that of the envelope 2 carrying the rocket 43).
  • Acceleration sensor 50 detects acceleration ejecting the submunition which has the effect to initialize the operation of the computing unit 14 which, after a fixed delay that it has in memory, will cause ignition of the gas generator 19 (fig 6b).
  • the submunition is then animated with a speed of upper rotation.
  • the speed increase will again be chosen such that the V / ⁇ ratio of the longitudinal speed V of the sub ammunition on its rotation speed ⁇ is less than or equal at a limit value P so as to ensure a sweep of the ground by the direction of observation 12 with a step (P) sufficiently small to allow detection of the target 27a.
  • This embodiment can, like the previous ones, ensure detection of aerial targets such as helicopters.
  • the advantage of using one or more submunitions is that the roll damping of the submunition (s) is weaker than that of the complete projectile. It results in maintaining a high ⁇ for the payload.
  • Another advantage of such an embodiment is that it allows by the use of several submunitions to increase the area of effectiveness of the projectile.
  • Figure 7 shows the implementation of a submunition 3 according to such an alternative embodiment.
  • This submunition differs from the previous one in that it comprises at its rear part a housing 51 to the interior of which is disposed a deployable parachute 52.
  • the submunition 3 is rotated and in translation by the projectile thanks to pins shearable (not shown).
  • Parachute 52 is automatically deployed when ejection as a result of aerodynamic forces. We will be able to possibly to promote and accelerate the extraction of parachute have a tearable link between it. and the bottom 46 which closes the projectile.
  • This link (not shown) will be chosen sufficiently fragile to break as soon as the bottom begins to exert a pull on him. This avoids any interference between the bottom and the parachute deployed.
  • the parachute 52 is connected to the submunition by a means link 53 which leaves the submunition free to rotate, for example a fixed axis relative to the submunition and on which turns a ring secured to the parachute.
  • the unit of calculation does not control the deployment of the braking means aerodynamic.
  • This braking means is deployed automatically after the deposition of the submunition, itself triggered at the appropriate time by the rocket chronometric of the projectile.
  • the submunition always contains a sensor acceleration 50 which detects the unloading instant and which initializes the calculation unit which is then operational.
  • a projectile comprising several military heads and several sensors target or projectile whose military head is a charge generating bursts in a direction of action particular.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Radar Systems Or Details Thereof (AREA)
EP98120293A 1997-11-20 1998-10-27 Projektil mit radialer Wirkrichtung Expired - Lifetime EP0918205B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9714549 1997-11-20
FR9714549A FR2771166B1 (fr) 1997-11-20 1997-11-20 Projectile ayant une direction d'action radiale

Publications (2)

Publication Number Publication Date
EP0918205A1 true EP0918205A1 (de) 1999-05-26
EP0918205B1 EP0918205B1 (de) 2003-01-22

Family

ID=9513573

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98120293A Expired - Lifetime EP0918205B1 (de) 1997-11-20 1998-10-27 Projektil mit radialer Wirkrichtung

Country Status (6)

Country Link
US (1) US6216597B1 (de)
EP (1) EP0918205B1 (de)
DE (1) DE69810879T2 (de)
ES (1) ES2187874T3 (de)
FR (1) FR2771166B1 (de)
IL (1) IL127136A (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2914054A1 (fr) * 2007-03-19 2008-09-26 Nexter Systems Sa Dispositif de protection rapprochee

Families Citing this family (8)

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US6980958B1 (en) * 2000-01-11 2005-12-27 Zycare, Inc. Apparatus and methods for monitoring and modifying anticoagulation therapy of remotely located patients
SE519758C2 (sv) * 2000-07-03 2003-04-08 Bofors Weapon Sys Ab Arrangemang för att bekämpa mål med eller utav RSV- effektuerande verkan
FR2848657B1 (fr) * 2002-12-13 2005-01-28 Tda Armements Sas Charge generatrice de noyau
DE102005043078B4 (de) * 2005-09-10 2007-06-14 Diehl Bgt Defence Gmbh & Co. Kg Suchzündermunition
US8563910B2 (en) * 2009-06-05 2013-10-22 The Charles Stark Draper Laboratory, Inc. Systems and methods for targeting a projectile payload
US20170307334A1 (en) * 2016-04-26 2017-10-26 Martin William Greenwood Apparatus and System to Counter Drones Using a Shoulder-Launched Aerodynamically Guided Missile
US10539403B2 (en) * 2017-06-09 2020-01-21 Kaman Precision Products, Inc. Laser guided bomb with proximity sensor
US20240219159A1 (en) * 2023-01-03 2024-07-04 Simmonds Precision Products, Inc. High speed actuation systems

Citations (6)

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Publication number Priority date Publication date Assignee Title
FR2406800A1 (fr) 1977-10-18 1979-05-18 Aerospatiale Missile d'attaque en survol
US4160415A (en) * 1978-05-05 1979-07-10 The United States Of America As Represented By The Secretary Of The Army Target activated projectile
FR2552871A1 (fr) 1981-04-28 1985-04-05 France Etat Armement Projectile antichar agissant en vitesse defilante
FR2590973A1 (fr) 1985-11-29 1987-06-05 France Etat Armement Dispositif de basculement de projectile sur trajectoire
DE3216142C1 (en) * 1982-04-30 1988-06-30 Messerschmitt Boelkow Blohm Fast-flying projectile with direction-forming charges
US5669581A (en) * 1994-04-11 1997-09-23 Aerojet-General Corporation Spin-stabilized guided projectile

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DE3000007A1 (de) * 1979-01-02 1980-09-18 Raytheon Co Kampffahrzeug-abwehrsystem
DE2741984C2 (de) * 1977-09-17 1984-01-26 Franz Rudolf Prof.Dr.Dipl.-Ing. West Vancouver Thomanek Gefechtskopf für einen Panzerabwehrflugkörper mit mindestens einer stachelbildenden Hohlladung
US4245560A (en) * 1979-01-02 1981-01-20 Raytheon Company Antitank weapon system and elements therefor
GB8417706D0 (en) * 1984-07-11 1994-01-26 British Aerospace Spin rate variation of spinning bodies
US4614317A (en) * 1985-06-07 1986-09-30 The Singer Company Sensor for anti-tank projectile
FR2736424B1 (fr) * 1995-07-07 1997-08-08 Giat Ind Sa Tete militaire a charge formee
US5932833A (en) * 1997-03-03 1999-08-03 The United States Of America As Represented By The Secretary Of The Army Fly over homing guidance for fire and forget missile systems

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2406800A1 (fr) 1977-10-18 1979-05-18 Aerospatiale Missile d'attaque en survol
US4160415A (en) * 1978-05-05 1979-07-10 The United States Of America As Represented By The Secretary Of The Army Target activated projectile
FR2552871A1 (fr) 1981-04-28 1985-04-05 France Etat Armement Projectile antichar agissant en vitesse defilante
DE3216142C1 (en) * 1982-04-30 1988-06-30 Messerschmitt Boelkow Blohm Fast-flying projectile with direction-forming charges
FR2590973A1 (fr) 1985-11-29 1987-06-05 France Etat Armement Dispositif de basculement de projectile sur trajectoire
US5669581A (en) * 1994-04-11 1997-09-23 Aerojet-General Corporation Spin-stabilized guided projectile

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2914054A1 (fr) * 2007-03-19 2008-09-26 Nexter Systems Sa Dispositif de protection rapprochee

Also Published As

Publication number Publication date
EP0918205B1 (de) 2003-01-22
DE69810879D1 (de) 2003-02-27
ES2187874T3 (es) 2003-06-16
US6216597B1 (en) 2001-04-17
IL127136A (en) 2001-10-31
FR2771166B1 (fr) 1999-12-17
IL127136A0 (en) 1999-09-22
FR2771166A1 (fr) 1999-05-21
DE69810879T2 (de) 2003-08-21

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