EP3667226A1 - Dispositif de commande d'un projectile avec unité de freinage activable - Google Patents

Dispositif de commande d'un projectile avec unité de freinage activable Download PDF

Info

Publication number
EP3667226A1
EP3667226A1 EP19211897.4A EP19211897A EP3667226A1 EP 3667226 A1 EP3667226 A1 EP 3667226A1 EP 19211897 A EP19211897 A EP 19211897A EP 3667226 A1 EP3667226 A1 EP 3667226A1
Authority
EP
European Patent Office
Prior art keywords
projectile
braking
control device
flight
trajectory
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.)
Pending
Application number
EP19211897.4A
Other languages
German (de)
English (en)
Inventor
Daniel Schmid
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Diehl Defence GmbH and Co KG
Original Assignee
Diehl Defence GmbH and Co KG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Diehl Defence GmbH and Co KG filed Critical Diehl Defence GmbH and Co KG
Publication of EP3667226A1 publication Critical patent/EP3667226A1/fr
Pending legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
    • F42B10/48—Range-reducing, destabilising or braking arrangements, e.g. impact-braking arrangements; Fall-retarding means, e.g. balloons, rockets for braking or fall-retarding
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
    • F42B10/48—Range-reducing, destabilising or braking arrangements, e.g. impact-braking arrangements; Fall-retarding means, e.g. balloons, rockets for braking or fall-retarding
    • F42B10/50—Brake flaps, e.g. inflatable
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/60—Steering arrangements
    • F42B10/66—Steering by varying intensity or direction of thrust

Definitions

  • the invention relates to the control of a target object or target.
  • the target object is particularly heavily armored (especially in the front or on the side / at the rear), but weaker armored on its top.
  • Such combat is known from practice on the comparatively weaker armored top of the target z. B. with ammunition SMArt 155 ( Wikipedia, 'SMArt 155', https://de.wikipedia.org/ wiki / SMArt_155, accessed November 20, 2018 ).
  • the projectile is fired with a conventional propellant charge from an artillery gun and releases the submunition after a preset flight time and thus distance.
  • the warhead is designed as a projectile-forming charge with a tantalum liner similar to a shaped charge projectile. Its capabilities enable it to combat all combat vehicles, including reactive armor. However, such ammunition is complex and expensive.
  • the object of the present invention is to improve the abovementioned control.
  • the control device can be assembled to form the projectile or assembled in an assembled state.
  • the assembled projectile can be fired from a gun barrel by means of a propellant charge.
  • Alternative transportation options are also possible (e.g. Railgun or similar).
  • the projectile has a proper direction of flight (after the launch or after the acceleration phase, i.e. in flight).
  • “In accordance with the intended purpose” means that the projectile is fired according to its dimensions from a weapon provided for this purpose to an intended target location or target object and has a specific direction of flight. The flight of the projectile thus follows its firing from the weapon.
  • the control device contains at least one braking element.
  • the braking element is initially in a state of rest after the launch and during a flight of the projectile. In the idle state, the braking element has a smaller one (than in a braking state, see below), in particular no braking force or braking effect for the projectile against the direction of flight.
  • the braking element can be put into a braking state during the flight. In this braking state, it has a greater braking force or braking effect for the projectile than in the idle state, in particular, therefore, a noticeable braking force or braking effect at all.
  • the control device contains an activation module. This is used to move the braking element after firing from the idle state to the braking state. The shipment takes place only when a braking criterion is met. After the launch, the braking criterion is checked (permanently or repeatedly). If this is not fulfilled, the idle state is maintained; if it is fulfilled, the braking status is triggered or activated.
  • the control device In an intended assembly state, the control device is therefore assembled with the base body.
  • "Intended” means that the control device is structurally matched to a specific or a specific type of base body or floor and is intended for use there; e.g. B. is designed for the geometry requirements determined thereby, etc.
  • the control device assumes the idle state in particular from the moment of completion, in particular from installation in the base body, in particular at the latest when it is fired.
  • a braking force or braking effect on the projectile is brought about in flight.
  • a main battle tank that fires a corresponding projectile has an improved possibility to combat heavily (actively / passively) armored targets (also behind cover).
  • a projectile that is conventionally used in direct fire in particular tank ammunition, e.g. 120mm smooth barrel or 155mm steering ammunition
  • tank ammunition e.g. 120mm smooth barrel or 155mm steering ammunition
  • the braking mechanism bringing the braking element into the braking state
  • steep (shortened) trajectory are brought.
  • This allows a warhead of the projectile to act on the target from above.
  • sensors and steering can optimize the target approach with regard to accuracy.
  • the invention offers the advantage of a low price compared to guided missiles. There is the advantage of faster access, that is, shorter flight time than indirect fire of the artillery. There is direct feedback on mission success through direct observation. And there is the advantage that hard targets can be fought even behind cover with tank ammunition.
  • a braking mechanism direct, especially armor-piercing ammunition (hollow / P-load, see below) is transferred from a frontal hit to a top attack scenario.
  • the invention makes it possible to combat heavily armored targets (especially in the front) through the projectile, in particular a hollow or P charge (or combination) on the weakly armored upper side of the target (e.g. main battle tank).
  • the invention is suitable for both spin-stabilized and wing-stabilized projectiles.
  • the braking element is a passive braking element.
  • the braking element When the projectile is in flight, the braking element has an aerodynamic effect which can be changed between the idle state and the braking state (no or noticeable braking force or braking effect which varies in strength).
  • the braking element can be extended and / or moved in particular from the projectile and / or its aerodynamically effective cross section can be changed.
  • Such brake elements are structurally particularly simple and inexpensive to implement.
  • the braking element is movable relative to the base body.
  • the brake element can be extended and / or folded out, in particular it is a brake flap or a brake wing.
  • This relates in particular to an outline shape of the projectile in the idle state.
  • additional brake flaps open as braking elements after a programmed time (braking criterion) and increase the air resistance of the projectile considerably.
  • the braking element is an active braking element (at least in the braking state).
  • the braking element is therefore in some way energy-operated or uses energy to brake the projectile. It is conceivable to drive energy, stored in the control device, for braking purposes, etc. In this way, the braking force or braking effect can be increased compared to passively acting braking elements.
  • the braking element contains an activatable recoil device. This releases chemically stored energy in particular.
  • the recoil device serves to generate a recoil force against the direction of flight of the projectile. At least the recoil force has a component against the direction of flight.
  • a corresponding recoil device can be used particularly easily and effectively for braking.
  • the recoil device contains at least one outlet channel.
  • the outlet channel serves to discharge a recoil.
  • the outlet channel extends along an outlet direction, the outlet direction having at least one direction component in the flight direction.
  • Recoil means or medium which flows out of the outlet channel and thus also along the outlet direction, therefore likewise has a braking direction component against the flight direction.
  • the outlet direction is in particular the central longitudinal axis of the outlet channel and in particular a straight line.
  • Recoil means are, for example, compressed air, engine, fire or explosion gases, particles, the product of a (rocket) propellant, etc.
  • the recoil device contains an activatable (in particular rocket) propellant.
  • the propellant serves to generate and / or release the recoil in the form of the propellant's product.
  • the projectile can be braked particularly easily and effectively by means of an appropriate propellant charge.
  • the propellant charge is ignited after or at a programmed time after the projectile has been fired.
  • the propellant charge then generates a backward thrust through the outlets (outer ends of the outlet ducts) facing forwards (in the direction of flight), which leads to the projectile being braked.
  • the braking criterion is an expiry of a predefinable flight duration after the projectile has been fired. In other words, a period of time between firing and activation of the braking state is set in the projectile. With the known flight speed of the projectile, the braking and thus the targeted deflection of the projectile can take place in a simple manner on a desired shortened trajectory to a desired destination.
  • the control device contains a steering module for controlling and / or regulating the trajectory of the projectile after it has been fired.
  • the steering module can, for example, air guiding means such as movable steering wings, Including lateral acceleration devices such as thrusters, etc. in order to specifically change the shortened trajectory of the projectile at least within certain limits.
  • the projectile can be brought to a shortened target trajectory or can be held there.
  • the steering can take place, for example, on the basis of the position of the projectile, the position of a target, on the basis of control signals received, etc. The floor can thus be guided to a destination in a particularly precise location.
  • the steering module uses active or aerodynamic steering mechanisms such as. B. adjustable steering wing, thruster or the like.
  • the braking therefore causes in particular the determination of the basic trajectory of the projectile or the definition on a large scale
  • the steering module serves rather a fine correction around the uncorrected trajectory or in the vicinity.
  • the steering module therefore contains a route guidance module for guiding the projectile to a predefinable destination.
  • the route guidance module is oriented, for example, to a target marking applied to a target object at the target location, to target coordinates, etc.
  • the steering module regulates the projectile to a desired shortened trajectory.
  • the control device contains a sensor module.
  • Any sensor technology for obtaining sensor data e.g. B. position, direction, speed sensors, etc.
  • Target search sensors such as. B. laser, radar, camera sensors, etc. sensors in the form of communication receivers or transmitters for communicating the projectile with a control center or the like are also conceivable. Properties of any complexity can thus be assigned to the projectile, in particular, for example, to improve route guidance, prevent self-bombardment, establish security mechanisms, etc.
  • the sensor module therefore contains a position module for determining a current position of the projectile, at least during its flight.
  • the current current one useful for route guidance Position, speed, direction, location, etc., i.e. the location of the floor in the floor itself is known and can be processed there directly and quickly.
  • the object of the invention is also achieved by a projectile according to claim 13.
  • the projectile has already been mentioned above and contains the control device according to the invention and the base body mentioned in connection with this.
  • the control device is assembled with the base body to form a floor.
  • the projectile is in particular an armor-piercing projectile or part of an armor-piercing ammunition or tank ammunition.
  • the projectile is in particular a 120mm smooth-tube projectile or a 155mm steering projectile.
  • the projectile contains in particular a shaped charge and / or a P charge (projectile-forming charge).
  • the object of the invention is also achieved by ammunition with the projectile and the above-mentioned propellant charge.
  • the same advantages and embodiments result for the ammunition as have already been mentioned above for the projectile.
  • the object of the invention is also achieved by a method according to claim 14 for operating a projectile according to the invention.
  • the projectile is fired from a weapon.
  • at least one of the braking elements is brought into the braking state during the flight.
  • the object of the invention is also achieved by a method according to claim 15 for combating a target object at a target location with the aid of the method according to the invention.
  • the projectile is first fired from the weapon onto a regular trajectory.
  • An elevation of the weapon is chosen which is increased with respect to an elevation for a direct trajectory of the projectile directed towards the target object.
  • the direct flight path is the one that would fly through a conventional projectile or the projectile according to the invention if it remained completely in the idle state. This can be an imaginary trajectory if, for example, there is actually a cover or an obstacle in this direct trajectory and the target object cannot therefore be bombarded conventionally on the direct trajectory.
  • the projectile is fired on a regular trajectory elevated to the direct trajectory.
  • the destination would not be hit at the target object along the regular trajectory.
  • the regular trajectory is the one that would go through the projectile if the hibernation were maintained.
  • the projectile or at least one of the braking elements is then brought into the braking state during the flight, in particular at such a point in time after the launch, that the braking projectile is decelerated by braking from its regular trajectory, which it would continue to fly in the idle state , is deflected ballistically or by gravity downward to a target location at the target object.
  • the projectile therefore describes an overall shortened trajectory that deviates from the regular trajectory.
  • the target location at the target object is in particular one that could not be reached by direct shelling with the projectile in the direct trajectory.
  • the projectile is first "shot over the target", i.e. H. on a currently higher regular trajectory, which is higher than the direct trajectory (which leads to the target in the case of direct shelling on an imaginary trajectory).
  • the target becomes compared to Direct bombardment hit more from above.
  • a direct fire on the direct trajectory would lower the target; H. rather hit sideways.
  • z. B. a battle tank is heavily armored in its front section, but is weaker armored on the top. An increased firing angle and a trajectory that is heavily curved (shortened) due to braking helps to hit the target from above. Also covers and Obstacles that would prevent an actual direct fire are overcome.
  • Figure 1 shows a spin-stabilized projectile 2, which contains a base body 4 and a control device 6.
  • Base body 4 and control device 6 are assembled to the floor 2.
  • the floor 2 is in one Figure 4 indicated gun barrel 8 can be fired by means of a propellant charge, not shown.
  • the projectile 2 has an intended direction of flight 10 (indicated by an arrow), in which it moves after being fired.
  • the control device 6 contains two braking elements 12.
  • Figure 1a are the braking elements 12 in an idle state R.
  • the braking element initially does not produce any braking force F for the projectile 2 against the flight direction 10.
  • Floor 2 is now braked in flight.
  • the control device 6 contains an activation module 14, which is only symbolically indicated here and which serves to bring the braking elements 12 from the idle state R into the braking state B.
  • the shipment takes place after the projectile has been fired, fulfilling a braking criterion K.
  • the braking element 12 is a passive, namely aerodynamically acting braking element whose aerodynamic effect here is from a zero effect Figure 1a to an actual braking force F in Figure 1b is changeable or is changed.
  • the braking element 12 In order to move from the idle state R to the braking state B, the braking element 12 is movable relative to the base body 4, here it is about a pivot axis 16 in the direction of FIG Fig. 1a shown arrows pivotable.
  • the brake elements are 12 brake flaps.
  • the activation module 14 is set up or programmed in such a way that the brake flaps open after the programmed time or duration or flight duration t0 after the launch, i. H. move from the resting state R to the braking state B and thus considerably increase the air resistance of the projectile 2.
  • Figure 2 shows an alternative floor 2, which differs from that Figure 1 differs only in that it is not spin-stabilized, but wing-stabilized by wing 18. Otherwise, the same statements apply as for Figure 1 .
  • FIG 3 shows an alternative floor 2, which differs from that Figure 2 only differs in that it contains an alternative braking element 12.
  • the braking element 12 is an active braking element that contains an activatable recoil device 20 instead of the brake flaps.
  • the recoil device 20 serves to generate a recoil force or braking force F against the direction of flight 10.
  • the recoil device 20 contains two outlet channels 22 for a recoil means 24, here exhaust gas from a propellant 26, here a rocket propellant.
  • the outlet channels 22 run along a respective outlet direction 28, here a respective central longitudinal axis of the outlet channels 22 in Straight line.
  • the outlet direction 28 each has a direction component in the direction of flight 10.
  • the propellant charge 26 is inactive or ignited.
  • the latter is activated or fired and from now on releases the recoil means 24 in order to develop the braking force F.
  • the activation module 14 is set up in such a way that it ignites the propellant charge 26 after a programmed time t0 after the projectile 2 has been fired the braking force F, which leads to the braking of the projectile 2.
  • FIG. 3b shows further details of the control device 6, which contains a steering module 30 for regulating the trajectory of the projectile 2 after it has been fired.
  • the steering module 30 includes a route guidance module 32 for guiding the projectile 2 to a predetermined destination Z.
  • control device 6 here contains a sensor module 34 which is connected to the steering module 30.
  • FIG. 4 shows a deployment scene for the projectile 2 according to the invention.
  • a weapon 38 here a gun of a main battle tank, with the gun barrel 8 for firing the projectile 2 is located in a terrain 40.
  • a target object 44 here an enemy battle tank, is located in relation to the Weapon 38 behind a cover 42.
  • Target 44 is to be fought with the aid of projectile 2. Due to the cover 42, a conventional direct bombardment of the target object 44 with a conventional projectile on a direct flight path 46 is not possible.
  • An elevation E0 of the gun barrel 8 is assigned to the direct trajectory.
  • the direct flight path 46 therefore corresponds to a conventional direct flight path. Elevation E0 would thus also bring floor 2 to direct flight path 46.
  • the braking state B in the projectile 2 is activated, as is shown in FIG Figures 1 to 3 was explained.
  • FIG. 5 shows V in detail Fig. 4 the target object 44 Figure 4 in detail.
  • the floor 2 is only indicated symbolically here. Here, however, a shaped charge for combating target 44 is shown, which is contained in floor 2. If the projectile 2 were hit conventionally by the projectile 2 or a conventional projectile on the direct flight path 46, the projectile would hit the heavily armored front part 52 of the main battle tank. According to the invention, however, the shortened trajectory 50 results, so that the projectile 2 actually hits the target location Z on the upper side 54 of the target object 44. The invention thus brings the effect of the projectile 2 from above onto the weakly armored upper side 54 of the target object 44, which armor is weaker compared to the front part 52. The target location Z could not be reached by a projectile on the direct trajectory 46.

Landscapes

  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
EP19211897.4A 2018-12-14 2019-11-27 Dispositif de commande d'un projectile avec unité de freinage activable Pending EP3667226A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102018009843.6A DE102018009843A1 (de) 2018-12-14 2018-12-14 Abgebremster Direktbeschuss mit Geschoss

Publications (1)

Publication Number Publication Date
EP3667226A1 true EP3667226A1 (fr) 2020-06-17

Family

ID=68731707

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19211897.4A Pending EP3667226A1 (fr) 2018-12-14 2019-11-27 Dispositif de commande d'un projectile avec unité de freinage activable

Country Status (2)

Country Link
EP (1) EP3667226A1 (fr)
DE (1) DE102018009843A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20230045482A1 (en) * 2021-06-07 2023-02-09 The Boeing Company Guided projectile and countermeasure systems and methods for use therewith
EP4227634A1 (fr) 2022-02-11 2023-08-16 Diehl Defence GmbH & Co. KG Guidage de projectiles stabilisés en rotation par oscillation cyclique de surfaces de guidage

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB821935A (en) * 1954-09-15 1959-10-14 Metallbau Semler G M B H Improvements in or relating to the propulsion and/or control of flying bodies
DE3904684A1 (de) * 1989-02-16 1990-09-20 Asea Brown Boveri Verfahren zur korrektur der flugbahn aus einer rohrwaffe abgefeuerten oder selbststangetriebenen explosivgeschosses sowie geschoss, auf das das verfahren angewendet wird
DE19824288A1 (de) * 1998-05-29 1999-12-02 Rheinmetall W & M Gmbh GPS-gestützes Geschoß
EP1288608A1 (fr) * 2001-09-04 2003-03-05 Diehl Munitionssysteme GmbH & Co. KG Dispositif de freinage pour projectile stabilisé par rotation à trajectoire corrigée
DE19916028A1 (de) * 1998-06-24 2003-07-17 Royal Ordnance Plc Einrichtung zur Luftwiderstandserzeugung

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3442083A (en) * 1967-07-21 1969-05-06 Avco Corp Adjustable variable thrust propulsion device
FR2657687B1 (fr) * 1990-01-26 1994-05-27 Thomson Brandt Armements Munition anti-char et son procede d'utilisation.
FR2786561B1 (fr) * 1998-11-30 2001-12-07 Giat Ind Sa Dispositif de freinage en translation d'un projectile sur trajectoire
US7350744B1 (en) * 2006-02-22 2008-04-01 Nira Schwartz System for changing warhead's trajectory to avoid interception
US20080223246A1 (en) * 2007-03-13 2008-09-18 Dindl Frank J Burping projectile
SK1062007A3 (sk) * 2007-08-13 2009-03-05 Štefan Kemenyík Spôsob progresívneho hasenia požiaru a zariadenie na aplikáciu prachového média
US8049149B2 (en) * 2008-05-16 2011-11-01 Raytheon Company Methods and apparatus for air brake retention and deployment
US8193476B2 (en) * 2008-06-13 2012-06-05 Raytheon Company Solid-fuel pellet thrust and control actuation system to maneuver a flight vehicle
SE1230014A1 (sv) * 2012-02-06 2013-07-23 Bae Systems Bofors Ab Bromspanel för ett tändrör eller en projektil

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB821935A (en) * 1954-09-15 1959-10-14 Metallbau Semler G M B H Improvements in or relating to the propulsion and/or control of flying bodies
DE3904684A1 (de) * 1989-02-16 1990-09-20 Asea Brown Boveri Verfahren zur korrektur der flugbahn aus einer rohrwaffe abgefeuerten oder selbststangetriebenen explosivgeschosses sowie geschoss, auf das das verfahren angewendet wird
DE19824288A1 (de) * 1998-05-29 1999-12-02 Rheinmetall W & M Gmbh GPS-gestützes Geschoß
DE19916028A1 (de) * 1998-06-24 2003-07-17 Royal Ordnance Plc Einrichtung zur Luftwiderstandserzeugung
EP1288608A1 (fr) * 2001-09-04 2003-03-05 Diehl Munitionssysteme GmbH & Co. KG Dispositif de freinage pour projectile stabilisé par rotation à trajectoire corrigée

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20230045482A1 (en) * 2021-06-07 2023-02-09 The Boeing Company Guided projectile and countermeasure systems and methods for use therewith
US11835319B2 (en) * 2021-06-07 2023-12-05 The Boeing Company Guided projectile and countermeasure systems and methods for use therewith
EP4227634A1 (fr) 2022-02-11 2023-08-16 Diehl Defence GmbH & Co. KG Guidage de projectiles stabilisés en rotation par oscillation cyclique de surfaces de guidage
DE102022000529A1 (de) 2022-02-11 2023-08-17 Diehl Defence Gmbh & Co. Kg Lenkung drallender Geschosse durch zyklischen Stellflächenausschlag

Also Published As

Publication number Publication date
DE102018009843A1 (de) 2020-06-18

Similar Documents

Publication Publication Date Title
DE19740888C2 (de) Verfahren zum autonomen Lenken eines drallstabilisierten Artilleriegeschosses und autonom gelenktes Artilleriegeschoß zur Durchführung des Verfahrens
DE69411514T2 (de) Flugabwehrsystem und Flugabwehrkörper dafür
DE4325218C2 (de) Artillerie-Rakete und Verfahren zur Leistungssteigerung einer Artillerie-Rakete
DE69121427T2 (de) Geschoss und sein Verwendungsverfahren
EP3667226A1 (fr) Dispositif de commande d'un projectile avec unité de freinage activable
EP2213975B1 (fr) Projectile cargo
EP2413086A2 (fr) Procédé de commande d'un corps volent articlé guidé par turbine
EP2482026B1 (fr) Procédé de défense contre l'attaque d'un missile
DE102012005682B4 (de) Verfahren zum Lenken eines Wirkelements durch einen Schützen
DE3013405C2 (de) Verfahren zum Vermeiden des Nachrichtens von Abschußgeräten für ballistische Flugkörper
EP2594891B1 (fr) Procédé destiné à repousser une fusée balistique se rapprochant en volant et système d'interception
DE102010053896A1 (de) Zielbekämpfungssystem
DE102020007514A1 (de) Waffensystem für ein Gefechtsfahrzeug, Gefechtsfahrzeug mit dem Waffensystem sowie Verfahren zum Überwinden einer Reaktivpanzerung
DE3142742C2 (fr)
EP3376154B1 (fr) Procédé de protection d'un missile de croisière
DE3221039C2 (de) Aus einem Abschußrohr abschießbarer Flugkörper
DE102016101560A1 (de) Querschubeinrichtung zur aktiven Bahn- und Lagesteuerung von Flugkörpern
EP1612504B1 (fr) Tête militaire pour munition d'artillerie
DE965185C (de) Aerodynamisch stabilisierter, unsteuerbarer Flugkoerper
DE3529897C2 (fr)
EP0049778B1 (fr) Procédé pour distribuer des munitions de combat
DE1578077C2 (de) Gefechtskopf fuer ein Panzerabwehrgeschoss
DE2815206C2 (de) Verfahren, Lenkflugkörper sowie Waffensystem zur Bekämpfung von Bodenzielen
DE102016015619A1 (de) steuerung eines projektils ohne einbau von elektronik gun-fired rocket-assisted laser-guided projectile --smart bullet--
DE3438305A1 (de) Unbemanntes fluggeraet fuer die bekaempfung von bodenzielen

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION HAS BEEN PUBLISHED

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20200930

RBV Designated contracting states (corrected)

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: EXAMINATION IS IN PROGRESS

17Q First examination report despatched

Effective date: 20221118