EP2009387A1 - Steuerverfahren zur Auslösung eines Angriffsmoduls und Vorrichtung zur Umsetzung eines solchen Verfahrens - Google Patents

Steuerverfahren zur Auslösung eines Angriffsmoduls und Vorrichtung zur Umsetzung eines solchen Verfahrens Download PDF

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Publication number
EP2009387A1
EP2009387A1 EP08290608A EP08290608A EP2009387A1 EP 2009387 A1 EP2009387 A1 EP 2009387A1 EP 08290608 A EP08290608 A EP 08290608A EP 08290608 A EP08290608 A EP 08290608A EP 2009387 A1 EP2009387 A1 EP 2009387A1
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EP
European Patent Office
Prior art keywords
driving module
action
projectile
terrestrial reference
triggering
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EP08290608A
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English (en)
French (fr)
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EP2009387B1 (de
Inventor
Thierry Bredy
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Nexter Munitions SA
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Nexter Munitions SA
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Publication of EP2009387A1 publication Critical patent/EP2009387A1/de
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C15/00—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges
    • F42C15/40—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein the safety or arming action is effected electrically
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/34—Direction control systems for self-propelled missiles based on predetermined target position data
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/34—Direction control systems for self-propelled missiles based on predetermined target position data
    • F41G7/346—Direction control systems for self-propelled missiles based on predetermined target position data using global navigation satellite systems, e.g. GPS, GALILEO, GLONASS
    • 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 devices for controlling the triggering of a driver module having at least one determined direction of action.
  • attack module having a determined direction of action is meant a projectile or subproject which acts in a preferential manner in a given direction of space.
  • the initiation of this charge projects a sheaf of fragments in a given direction which is the axis of the charge.
  • the chips scatter slightly around the projection axis and result in an impact surface on a target that has a given area (depending on the charge / target distance).
  • the patent EP1045222 describes such a load projecting splinters in a given direction.
  • the projectiles or sub-projectiles thus having a determined direction of action are particularly interesting because they allow a control of the risk zone. Collateral damage can be minimized, only the targeted target is in principle destroyed.
  • attack modules thus make it possible to limit the effects to a well-defined sector, which was not the case with conventional projectiles or projectiles, for example explosive artillery shells that generate bursts in all directions of the space surrounding the axis of the shell.
  • attack modules having a determined direction of action is however that it is necessary to orient them towards the desired target.
  • Projectiles are thus known that are brought into contact with or near the target, either by direct fire (shell-shaped shells fired in tight fire without guidance) or by indirect fire.
  • sub-projectiles devoid of control means but which are designed to scan a field area with a target sensor (for example an infrared sensor). In this case the shot is fired when the sub-projectile detects a target having the desired silhouette characteristics.
  • a target sensor for example an infrared sensor
  • these sub-projectiles have the risk of inadvertent triggering by false targets (lures or targets already reached by another sub-projectile) or by friendly targets.
  • the object of the invention is to propose a device for triggering an attack module (such as a projectile or a sub-projectile) making it possible to increase the control of the risk zone.
  • an attack module such as a projectile or a sub-projectile
  • the device according to the invention can be implemented with projectiles or under projectiles devoid of control means and also lacking target detection means, which makes it possible to reduce the susceptibilities of these projectiles or under projectiles to jamming or masking. .
  • the device nevertheless ensures that these projectiles or sub-projectiles have a perfect control of the dimensions of the risk zone.
  • the invention can also be implemented in a projectile or under projectile which is already provided with detection means.
  • the invention makes it possible to provide an additional firing condition that leads to improving the overall control of the efficiency zone of the driving modules.
  • the determination of the orientation of the direction of action relative to the fixed terrestrial reference will be performed by measuring the orientation of the drive module with respect to at least two components of the Earth's magnetic field, the components of the Earth's magnetic field. otherwise known in the fixed terrestrial reference.
  • a target / target module distance from the coordinates of the target in the fixed terrestrial frame, programmed before firing or on trajectory, and measurements of the coordinates of the driver module in the fixed terrestrial reference system, measurements made on the trajectory by a satellite positioning system or transmitted to the driver module from a platform equipped with tracking means .
  • the coordinates of the attack / target module vector calculated from the preprogrammed target coordinates as well as from the target coordinates, are calculated on a trajectory and in a fixed terrestrial reference. of those measured of the drive module and determined by means of a triaxial magnetic compass the orientation of the direction of action of the drive module in a fixed terrestrial reference.
  • the coefficients of a matrix of passage of a reference linked to the driving module towards the fixed terrestrial reference will be calculated, these components being calculated by associating, for the points of the trajectory considered, the measurement of the components of the earth's magnetic field in a reference frame linked to the driving module and the values of the components of the magnetic field in the terrestrial frame, the latter values being known and preprogrammed in the driver module, the calculation indetermination being raised by the determination of at least one direction in the terrestrial reference of one of the axes of a reference linked to the driving module.
  • a determination of the orientation of the direction of action in the fixed terrestrial reference will be made from the measurement of the components of the magnetic field in a horizontal plane, which plane is defined by two magnetic sensors carried by the driving module, the orientation of the direction of action relative to this plane being otherwise known as well as the orientation of the magnetic field in the fixed terrestrial reference.
  • target detection means at the level of the driving module and the triggering of the attack module will only be triggered if the authorization conditions are fulfilled and a target is otherwise detected.
  • the invention also relates to a device for controlling the triggering of an attack module having at least one determined direction of action, and implementing such a method.
  • This device is characterized in that it comprises means for storing the coordinates of at least one target in a fixed terrestrial reference, means for measuring the coordinates of the drive module in the fixed terrestrial reference, as well as calculation means making it possible to determine, on a trajectory, the orientation of the direction of action of the driving module in the fixed terrestrial reference, the means ensuring the triggering of the driving module being coupled to the calculation means so as not to allow such a trigger that if the direction of action is oriented toward the target.
  • the means for measuring the coordinates of the driver module in the fixed terrestrial fixture may include a GPS receiver and / or a location data receiver transmitted from a remote platform.
  • the device may comprise at least two fixed magnetic sensors for determining the orientation of the direction of action of the driver module relative to the earth's magnetic field, memory means providing in addition, the components of the Earth's magnetic field in the fixed terrestrial reference.
  • the device When it is more particularly suited to a projectile having a non-vertical trajectory, the device is characterized in that the driving module incorporates at least three magnetic sensors and memory means making it possible to know the values of the terrestrial magnetic field in a reference frame. fixed earth for the different points of the trajectory, calculation means making it possible to determine from the different values of the earth magnetic field, the orientation of the reference linked to the driving module with respect to the terrestrial reference as well as the coordinates of the vector module attack / target in a fixed terrestrial reference, and those of the direction of action of the attack module.
  • the device When it is more particularly adapted to a sub-projectile intended to be dispersed over a terrain zone by a carrier and animated after dispersion of a downward movement along a substantially vertical axis and a rotational movement around this vertical axis (the direction of action is also inclined relative to the vertical axis of a given angle), the device is characterized in that the drive module comprises at least two magnetic sensors arranged in two directions. axes of a reference linked to the driving module, the two axes defined by these sensors thus determining a plane which will be perpendicular to the expected vertical fall axis, the orientation of the direction of action of the drive module by relative to this horizontal plane being known.
  • the figure 1 shows a weapon system or shooting platform 1 (here a self-propelled artillery) which sends a projectile 2 to a target 3 in order to destroy it.
  • This projectile 2 constitutes a driving module having a determined direction of action W H which forms here an angle with the axis 19 of the projectile 2.
  • the latter follows a ballistic trajectory 5 and it also turns around its axis.
  • FIG. 1 a fixed terrestrial reference 4 of XYZ axes.
  • the coordinates of the firing platform 1 are X w Y W Z W
  • the coordinates of the projectile 2 are X p Y p Z p
  • those of the target 3 are X t Y t Z t .
  • point coordinates target, platform, projectile
  • the targeted targets have a certain ground surface and that the target point corresponds for example to the center of gravity of the real target.
  • the coordinates of the projectile are for example those of its center of gravity or those of the focus of its military head.
  • the driver module 2 incorporates a device 6 for controlling its tripping. This device ensures that the trigger will intervene only when optimal conditions are met, conditions to limit collateral damage.
  • the attack module 2 may include one or more formed charges (not shown) which will be projected in the direction of action W H. It may also include a load projecting a sheaf of splinters in the mean direction W H.
  • a burst charge projects splinters in a substantially conical sheaf centered on this direction of action.
  • the principles to be described can be easily adapted to the determination of the surfaces reached at ground level and to the comparison of this theoretically achieved surface with the global footprint (known and programmed) of a target to be treated.
  • the pyrotechnic means ensuring the end effect are not the subject of the present invention and will not be described in detail.
  • the figure 2 schematically represents the structure of the control device 6.
  • This device essentially comprises calculation means 7 which incorporate different calculation modules made in the form of algorithms stored in memories or registers.
  • calculation means 7 are connected to means 20 for triggering the firing of the pyrotechnic charge of the driver module 2 (for example an electronic fuse causing the initiation of a detonator). These known means are not the subject of the present invention and will therefore not be described in detail.
  • the control device 6 also comprises memory means or registers (incorporated in the calculation means 7) for storing the coordinates X t Y t Z t of at least one target 3 in the fixed terrestrial reference 4.
  • the coordinates of the target or targets 3 are introduced into the calculation means 7 from an appropriate interface 8. They are provided by a programming means 9 which is integral with the shooting platform 1.
  • a transmitter means 10 integral with the platform 1 for example a radio signal transmitter.
  • the interface 8 will then include a receiving antenna (not shown).
  • the device 6 also comprises means 11 making it possible to measure the X p Y p Z p coordinates of the driver module in the fixed terrestrial reference frame 4.
  • These means 11 may be constituted by a receiver of a satellite positioning system (or GPS).
  • the GPS receiver embedded in the projectile 2 can be replaced by a simple receiver 12 of signals supplied by a transmitter 10 (identical or different from that previously described) and integral with the platform 1. This transmitter 10 will then be coupled to a trajectory means 13 also secured to the platform 1.
  • the device according to the invention also comprises fixed magnetic sensors 14 (for example magneto resistors). These sensors make it possible to measure the components of the Earth's magnetic field along two or three axes of a marker linked to the projectile 2.
  • calculation means 7 also comprise memory means or registers for memorizing the components of the terrestrial magnetic field H in a fixed terrestrial reference 4 and in all points of the trajectory provided for the projectile 2.
  • the magnetic field H thus has, in this reference linked to the projectile, the three components H Xm , H Ym and H Zm which are measured along the trajectory 5.
  • the same magnetic field H has also in the fixed terrestrial reference 4, positioned at the point G of the trajectory 5, components H X , H Y and H Z.
  • the vector Vt is the velocity vector of the projectile 2 on its trajectory 5.
  • the components of this vector in the fixed reference frame 4 as well as the coordinates of the point G at which the projectile 2 is located are known thanks to the positioning means 11 (or to the means tracking).
  • the calculation means 7 can therefore at any time calculate, in the fixed reference frame 4, the coordinates of the vector ⁇ which connects the attack module. 2 to target 3 (vector whose standard expresses the distance from the attack module to the target).
  • the vector W H which is the one defining the direction of action of the projectile (or module of attack) 2.
  • This direction of action W H is a fixed data in the reference XmYmZm related to the projectile. This data is determined during the construction of the projectile 2. It is known, for a given projectile or attack module, how the magnetic sensors 14 are placed with respect to the military head and the direction of action of the projectile is also known. the military head with respect to the projectile body 2. The coordinates of the vector W H in the reference linked to the projectile 2 are incorporated in memory in the calculation means 7.
  • the orientation of this direction of action W H in the fixed terrestrial reference 4 will be determined on a trajectory.
  • the drive / target module distance which is the norm of the vector ⁇ , is also determined by calculation.
  • attack modules incorporating shaped charges or focussed flashes
  • the norm of the vector ⁇ is less than or equal to a programmed value which is the radius of action Ra for the drive module considered and which corresponds to a suitable distance for controlling the triggering with respect to a target.
  • the long range attack modules are for example those equipped with core generating charges.
  • the figure 4 is a logic diagram that summarizes the main steps of the method according to the invention.
  • Step A corresponds to the calculation of the coordinates of the vector ⁇ in the fixed terrestrial reference 4 (distance vector attack module / target).
  • the standard of this vector ⁇ will be calculated at the same stage.
  • Step B corresponds to calculating the coordinates of the vector W H (orientation of the direction of action) in the fixed terrestrial frame 4. This calculation implements steps which will be detailed later.
  • test C verifies the collinearity and the same direction of the vectors W H and ⁇ .
  • the test D satisfies (possibly) that the norm of the vector ⁇ is less than or equal to a reference value (radius of action Ra).
  • step E corresponds to the triggering authorization of the attack module 2.
  • step B will determine the orientation of the direction of action W H relative to the fixed terrestrial reference 4 by measuring the orientation of the driving module 2 by ratio to at least two components of the Earth's magnetic field.
  • Calculations of moving from a movable marker to a fixed marker implement the Euler angles which are well known to those skilled in the art. They intervene in the determination of the coefficients of a transition matrix T allowing the computation of the coordinates of points or vectors in the fixed reference frame from the known coordinates in the movable reference linked to the projectile 2.
  • H X , H Y , H Z being the coordinates of the terrestrial magnetic field vector in the fixed reference frame and (H Xm , H Ym , H zm ) being the coordinates of this same vector in the reference linked to the projectile.
  • the coefficients of the matrix T depend, of course, on the attitude of the projectile 2 on trajectory, and therefore flight conditions. They vary on trajectory and must be determined in a continuous (or periodic) way.
  • these Euler angles and the coefficients of the transit matrix T are determined using inertial systems associating gyrometers and accelerometers, which are fragile and expensive equipments (which do not resist firing by a cannon).
  • the components of the Earth's magnetic field may be considered constant over the entire trajectory 5 of the projectile 2 and during flight time.
  • this indetermination will be solved by calculating the orientation of the axis GXm of the reference linked to the projectile 2.
  • the axis 19 of the projectile 2 itself will be chosen as axis GXm and a conventional flight mechanics calculation will be used to determine the orientation of this axis in the terrestrial reference frame 4.
  • the knowledge of the trajectory 5 and the speed Vt makes it possible to know the curvature of the trajectory and the acceleration to which the projectile 2 is subjected.
  • the latter also has an aerodynamic transfer function Fta which depends on its geometry. , its mass and its matrix of inertia and which is fixed to the construction.
  • the implementation of the aerodynamic and flight mechanics equations allows to determine the angle of incidence Inc which separates the vectors Vt and Gxm from the transfer function Fta and the components of the acceleration calculated on trajectory.
  • This angle Inc is a resultant angle of incidence which is measured in the plane of the vectors Vt and Gxm, which plane is perpendicular to the vector of instantaneous rotation of the projectile on its trajectory.
  • the figure 5 is a logic diagram that details step B corresponding to the calculation of the coordinates of the vector W H (orientation of the direction of action) in the fixed terrestrial reference 4.
  • the block F corresponds to the measurement by the positioning means 11, and in the terrestrial frame 4, coordinates of the vector Vt associated with the different points of the trajectory 5 located as well as calculation by derivation, (or else by determination of the radius curvature of the trajectory) accelerations to which the projectile is subjected.
  • the block G corresponds to the calculation of the coordinates in the fixed terrestrial reference 4 of the main axis of the projectile GXm. This calculation implements the calculations resulting from the block F as well as the aerodynamic transfer function (Fta) of the projectile 2.
  • the block H M corresponds to the measurement by the sensors 14 of the components of the magnetic field in the marker of the projectile 2.
  • the block H RT corresponds to the determination (by reading in memories or registers of the computer 7) of the components of the terrestrial magnetic field in the terrestrial reference point at the point considered on the trajectory.
  • this block is connected to the block F to remind that the memory of the data of the magnetic field must be read with reference to the coordinates of the point considered on the trajectory of the projectile (coordinates provided by the positioning means 11).
  • the T block is that of calculating the coefficients of the matrix T allowing the passage of a marker linked to the projectile to a fixed terrestrial reference.
  • the block W H corresponds to the computation of the coordinates of the direction of action vector W H with respect to the fixed terrestrial reference 4.
  • the invention may advantageously be implemented for an attack module which is constituted by a sub-projectile dispersed over a terrain zone by a carrier, for example a cargo shell of artillery, drone or rocket (not shown).
  • a carrier for example a cargo shell of artillery, drone or rocket (not shown).
  • the direction of action W H is inclined with respect to the vertical axis 16 of a given angle ⁇ which is fixed by construction.
  • (Xf, Yf, Zf) are the coordinates of the point of intersection with the ground of the vector direction of action W H of the sub-projectile 15. This point corresponds to the point of theoretical impact 18 on the ground of the nucleus or the sheaf of splinters generated during the initiation of the sub-projectile 15.
  • the coordinates of this vector in the terrestrial reference frame are easily calculated from the coordinates (Xp, Yp, Zp) of the sub-projectile 15 (measured by the positioning means 11) and those (Xt, Yt, Zt) of the target 3 (programmed before shooting).
  • the standard of this vector ⁇ will be the value of a distance of attack / target module.
  • a test complementary to the collinearity measurement of the vectors W H and ⁇ may nevertheless be provided. This test will make it possible to verify that the value of the norm of the vector ⁇ is less than or equal to a predefined radius of action Ra.
  • the altitude of the sub-projectile relative to the ground could be tested (using an altimeter).
  • the sub-projectile follows a vertical trajectory and is not subject to any lateral acceleration. It is then easy to remove the indeterminacy in the calculation of the passage matrix T allowing to go from the reference linked to the sub-projectile to the terrestrial reference. It is sufficient to consider that the axis GZm of the reference linked to the projectile is vertical.
  • the coordinates of the axis GZm in the terrestrial reference are easily known from the sole determination of the coordinates of the point G (data by the positioning means 11).
  • the figure 7 shows the sub-projectile 15 as well as the positioning of two sensors 14 of the magnetic field.
  • the reference GXmYmZm linked to sub-projectile 15 has a privileged axis GZm which is the vertical axis.
  • the magnetic sensors 14 are arranged in the sub-projectile 15 so as to materialize two directions GXm and GYm which define a horizontal plane during the fall of the sub-projectile (plane perpendicular to the direction GZm).
  • the location of the direction of action W H with respect to the sub-projectile 15, so compared to the sensors 14 is a fixed construction data.
  • the matrix of passage T allowing the change of reference is thus easily defined.
  • the determination is all the easier with the choice of a marker linked to the projectile and having a vertical axis and a horizontal plane, it is sufficient to know a single angle of Euler, the angle ⁇ of rotation to pass from the fixed terrestrial axis GX (centered at G to the sub-projectile 15) to the axis GXm, to determine the orientation in the terrestrial reference of the sub-projectile 15 (hence its direction of action W H ).
  • Two magnetic sensors 14 are sufficient to calculate the value of the angle ⁇ n formed by the projection N of the magnetic field vector with the axis GXm.
  • figure 8 shows how it is possible to easily calculate the orientation of the action direction W H and to check the conditions allowing to allow or not the trigger of the attack module.
  • the figure 8 thus shows the different vectors in projection in the horizontal plane. It has been arbitrarily chosen to confuse the axis GXm of the marker linked to the sub-projectile 15 with the projection W HN of the direction of action W H on this plane.
  • ⁇ r is the angle that makes (in the horizontal plane) the projection N of the magnetic field vector H with respect to the axis GX of the fixed reference. This value is deduced from the coordinates of the magnetic field in the terrestrial frame as preprogrammed for the considered point G of the trajectory. We see that it would be possible in this case to simply memorize in the calculation means 7 only the angles ⁇ r and not the complete components of the magnetic field vector.
  • the angle ⁇ n formed by the projection N of the magnetic field vector with the axis GXm is measured using the sensors 14.
  • the vector ⁇ N (projection of the vector connecting the sub-projectile 15 to the target 3) is easily determined from the coordinates Xp, Yp of the sub-projectile (given by the positioning means 11 and those Xt, Yt of the target 3 ( preprogrammed).
  • ⁇ NOT 2 ( xt - xp ⁇ ) 2 + ( yt - yp ⁇ ) 2
  • the shooting accuracy obtained is remarkable while the sub-projectile 15 is totally devoid of target detection means.
  • the method according to the invention can be implemented for a driver module that is already provided with target detection means, for example an infrared sensor.
  • step E of the figure 4 will be followed by another test which will correspond to the verification of the presence of a target having the expected infrared characteristics (such a detection means is conventional and already implemented today).
  • the method according to the invention does not itself control the triggering of the attack module but it brings an additional condition to the simple target detection.
  • the examples described have referred to the determination of a direction of action W H whose intersection at ground level is punctual. It is of course possible, in particular when the drive module incorporates a chip load, to determine, in addition to the mean orientation of the vector W H , the value of the ground level surface that is covered by the sheaf. splinters. This surface is easy to calculate by introducing into the projectile or under projectile the value of the opening angle of the cone of the generated sheaf (solid angle centered on the direction W H ).

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
EP08290608.2A 2007-06-27 2008-06-25 Steuerverfahren zur Auslösung eines Angriffsmoduls und Vorrichtung zur Umsetzung eines solchen Verfahrens Active EP2009387B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0704613A FR2918168B1 (fr) 2007-06-27 2007-06-27 Procede de commande du declenchement d'un module d'attaque et dispositif mettant en oeuvre un tel procede.

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EP2009387A1 true EP2009387A1 (de) 2008-12-31
EP2009387B1 EP2009387B1 (de) 2014-08-27

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* Cited by examiner, † Cited by third party
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EP2600097A1 (de) 2011-11-29 2013-06-05 Nexter Munitions Kontrollverfahren zur Auslösung eines Gefechtskopfes, Kontrollvorrichtung und Zünder eines Geschosses, in dem ein solches Verfahren zur Anwendung kommt
FR2999697A1 (fr) * 2012-12-17 2014-06-20 Nexter Systems Procede d'acquisition des coordonnees d'un point de declenchement d'un projectile et conduite de tir mettant en oeuvre un tel procede
WO2019211716A1 (fr) 2018-05-02 2019-11-07 Nexter Munitions Projectile propulsé par statoréacteur

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US9518807B2 (en) * 2014-07-16 2016-12-13 Rosemount Aerospace Inc. Projectile control systems and methods
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US11573069B1 (en) 2020-07-02 2023-02-07 Northrop Grumman Systems Corporation Axial flux machine for use with projectiles
CN111895864B (zh) * 2020-08-06 2022-05-10 西安睿高测控技术有限公司 一种无加速度计的卫星制导弹药的过载驾驶仪构建方法
US12092432B2 (en) * 2020-10-02 2024-09-17 United States Of America, As Represented By The Secretary Of The Navy Glide trajectory optimization for aerospace vehicles
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EP2600097A1 (de) 2011-11-29 2013-06-05 Nexter Munitions Kontrollverfahren zur Auslösung eines Gefechtskopfes, Kontrollvorrichtung und Zünder eines Geschosses, in dem ein solches Verfahren zur Anwendung kommt
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WO2014096686A1 (fr) * 2012-12-17 2014-06-26 Nexter Systems Procédé d'acquisition des coordonnées d'un point de déclenchement d'un projectile et conduite de tir mettant en oeuvre un tel procédé
KR20150103687A (ko) * 2012-12-17 2015-09-11 넥스터 시스템즈 발사체의 발사 지점의 좌표를 얻는 방법 및 이러한 방법을 구현하는 발사 제어 시스템
US9593914B2 (en) 2012-12-17 2017-03-14 Nexter Systems Method for acquiring the coordinates of a trigger point of a projectile and fire-control system implementing the method
WO2019211716A1 (fr) 2018-05-02 2019-11-07 Nexter Munitions Projectile propulsé par statoréacteur

Also Published As

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FR2918168B1 (fr) 2009-08-28
FR2918168A1 (fr) 2009-01-02
EP2009387B1 (de) 2014-08-27
US20090001215A1 (en) 2009-01-01
US7989742B2 (en) 2011-08-02

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