EP0589746A1 - Sub-Munition mit kontrollierter Aktivierung - Google Patents

Sub-Munition mit kontrollierter Aktivierung Download PDF

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Publication number
EP0589746A1
EP0589746A1 EP93402200A EP93402200A EP0589746A1 EP 0589746 A1 EP0589746 A1 EP 0589746A1 EP 93402200 A EP93402200 A EP 93402200A EP 93402200 A EP93402200 A EP 93402200A EP 0589746 A1 EP0589746 A1 EP 0589746A1
Authority
EP
European Patent Office
Prior art keywords
axis
submunition
detection
target
angle
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
EP93402200A
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English (en)
French (fr)
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EP0589746B1 (de
Inventor
Chirstophe Redaud
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 EP0589746A1 publication Critical patent/EP0589746A1/de
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Expired - Lifetime legal-status Critical Current

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Classifications

    • 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
    • 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
    • F42C13/02—Proximity fuzes; Fuzes for remote detonation operated by intensity of light or similar radiation

Definitions

  • the present invention relates to a directed effect munition intended to be launched, by means of a vector, over an area containing a target, this ammunition comprising a military head consisting of a formed charge and a device for detection actuating a firing device.
  • the invention relates in particular to a submunition intended to be projected by means of a mine or a vector, the latter being itself launched by an aircraft or an artillery piece, in such a way that the submarine ammunition is driven by a translation speed v with a substantially vertical axis V and a rotation speed r with substantially the same axis.
  • Such a weapon system is known from US Pat. No. 4,858,532.
  • the axis of the detection device is inclined about 30 ° relative to the axis of rotation of the submunition, so that , during the downward movement of such a submunition, the fraction of surface covered by the detector device at a given instant moves in a spiral over the area, thus increasing the probability of detection of the target.
  • a signal produces the triggering of the formed charge, which acts vertically from top to bottom, while the submunition is in a substantially vertical part descending from its trajectory, but it can be observed that a head Military of this type could operate equally well in an upward trajectory, as in the case of the first part of the trajectory of a submunition launched by a landmine.
  • Such a system has the advantage of being able to engage targets at a distance, without requiring guidance and thanks to simple detection means.
  • the object of the present invention is to remedy the drawbacks of known submunitions and to propose a submunition making it possible to substantially reduce the inaccuracy of fire resulting from the translation and rotation speeds imparted to the submunition, and this by means of relatively inexpensive and space-saving simple means.
  • the device of the invention it becomes possible, by simple means to appreciably increase the accuracy of detection since, by an appropriate arrangement of the detection axes corresponding to the various angles u i , it is possible to largely correct the sources of imprecision of known submunitions.
  • the submunition is characterized in that the calculation means include means for comparing the minimum value of said deviation obtained for said angle with a threshold and for prohibiting the triggering of the military charge in the event of detection of a target if the minimum deviation is greater than said threshold.
  • the detection device comprises at least two detection units and can comprise at least two sensors, associated with a single optic and arranged so as to define detection axes with different orientations, these sensors being capable of being activated individually.
  • the different detection units consist of the same sensor with which an optic from a group of several optics can be associated.
  • the detectors are of the infrared or millimeter wave type.
  • the submunition applied to a submunition intended to be launched from the ground with a substantially vertical movement upwards before descending substantially vertically, the submunition comprises two detection units having one an average orientation for the ascending phase and the other an average orientation for the fallout phase, and means for recognizing the transition between the first and the second phase and for activating in each phase the appropriate detection unit.
  • FIGS. 1 to 5 relating to a conventional submunition, there is a submunition 1 comprising a shaped charge 2 which moves with a translation speed v along a substantially vertical axis V, and a rotation speed r around an axis substantially coincident with V, in the vicinity of a plane 3 containing a target 5, such as a land vehicle.
  • the charge formed 2 has a symmetry of revolution about an axis D making an angle t with the axis V.
  • a detector 7, of detection axis d substantially parallel to the axis D, can act on an igniter 8 placed at the rear of the formed charge 2.
  • the detection axis d rotates around the axis V by scanning a surface whose intersection with the plane 3 containing the target 5 forms a spiral 9.
  • the detection takes place in a solid angle of axis d, resting in plane 3 on a surface 4.
  • FIG. 1 shows a spiral 10, somehow encompassing spiral 9, and corresponding to the envelope in plane 3 of contour of the instant detection surface 4.
  • Figure 3 shows schematically the impact point deviation resulting from the single rotation of the load.
  • the plane of Figure 3 is parallel to the plane of the target, assumed to be horizontal.
  • the circle C with center O is the location of the points detected (intersection between the detection axis d and the ground), the circle C 'is the location of the points of impact with the ground.
  • the angle s1 is equal to r.a and it is induced by the rotation of the load during the calculation time. It matches point M with point M "on circle C.
  • the angle s2 is equal to arctg (n.r / Vnoy.sin t), Vnoy being the supposed constant speed of the nucleus after firing. This angle is induced by the driving speed n.r of the load on the speed of the core. It corresponds to point M "a point M 'of circle C'. The total error is equal to MM '.
  • the compensation for the difference could be effected by shifting the detection axis d forward by an equal value, but the error M1M 'would still have to be compensated.
  • this error depends on the direction of movement of the submunition. When climbing, the impact is offset towards the outside of the spiral, and when descending, the impact is offset towards the inside of the spiral.
  • the impact deviation is shown diagrammatically in FIG. 4 in the case of an ascending trajectory, of the load, the Z axis representing the vertical axis and the R axis representing the axis of the radial distances from the point d impact designated here by P.
  • the point Q symbolizing the position of the charge moves from a x v and passes to Q1.
  • a first correction could be made in a simple manner, passing from P to P1, the line Q1P1 being parallel to QP, but there would remain an error P subsP '.
  • Figures 6 to 11 relate to an embodiment of the invention applying to a shaped load similar to that of Figure 2, but allowing to overcome to a large extent the drawbacks explained above.
  • the detection device comprises a strip of four sensors or detectors 21 to 24 arranged radially with respect to the axis D of the charge formed. With these detectors is associated a single optic 26 defining with each of them respective detection axes d1 to d4, to which correspond respective angles u1 to u4 with the axis d, parallel to the axis D of the charge formed 2.
  • the detection axes d1 to d4 correspond to trace detection brushes 11 to 14 respectively on the target plane (see Figure 8).
  • the means for calculating the submunition have also been shown diagrammatically at 29. These means operate under conditions which will be specified below, during the description of the operation of the submunition with reference to FIGS. 9 to 11.
  • FIG. 7 represents a variant of the device of FIG. 6 in which the detectors 21 to 24 are distributed in a substantially symmetrical manner with respect to the axis D of the charge formed.
  • An optic 26 is required here for each pair of detectors 21, 22 and 23, 24.
  • the distances of the two optics 26 to the axis D must be adapted so that the elementary detection zones 11 to 14 are correctly arranged ( figure 8).
  • the speed v is known, either indirectly from the measurement of the altitude above the ground, symbolized at 31, or directly by the means 28 (see FIG. 9).
  • v we determine the value of u i best suited to trigger firing, by circuit 30. If no value of u i is suitable, firing is prohibited, otherwise the corresponding axis d i is selected by the circuit 32. If a target is detected by this axis, circuit 35 transmits the signal triggering of firing on circuit 38. Otherwise, we go back to a new calculation of speed v.
  • the choice of the value of u i best suited to trigger the firing may consist in calculating the point of impact deviation for each u i and in retaining the value which minimizes this deviation and which is less than a threshold u s .
  • This operating mode corresponds to the diagram in FIG. 10.
  • Another embodiment may consist (see FIG. 11) of defining a priori several ranges of speeds, for example four ranges limited by v1, v2, v3, v4, v5, with which particular detection axes d1, d2 are associated respectively. d3, d4.
  • the means 28 provides at each instant an estimated value of the speed v.
  • the circuit 41 selects the direction detector d1. If v is not included in the first range of speeds, we go to circuit 42 and possibly to circuits 43 then 44, the latter corresponding to the fourth range of speeds (v4 ⁇ v ⁇ v5) When one of the speed ranges suitable, the corresponding detection axis is selected. Under these conditions, if circuit 37 detects the target, there is triggering of the shot by the circuit 38, otherwise we come back to a new determination of the speed.
  • the number of detection means, or of detection axes is not limiting; the higher the number, the better the correction.
  • the detection means are not used simultaneously, it is possible to envisage a single sensor but with several associated optics making it possible to obtain different detection axes.
  • the speed measuring means for example an accelerometer, can control the step-by-step movement of a shutter which allows only the beam coming from a specific optic to pass. This solution has the advantage of having only one sensor, thereby saving space and reducing costs.
  • One direction will correspond to a particular minimization of the aiming error for the rising phase of the submunition and the other direction will correspond to a minimization for the falling phase.
  • the choice of one or the other detector will be made by the calculation means 28 on the basis of the “maximum altitude” information (therefore corresponding to the passage of the rising phase in the downward phase).
  • This information can be provided by an accelerometer (whether or not coupled to an integrator). It can also be given by an altimeter followed by a diverter.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Automotive Seat Belt Assembly (AREA)
  • Motorcycle And Bicycle Frame (AREA)
EP93402200A 1992-09-21 1993-09-09 Sub-Munition mit kontrollierter Aktivierung Expired - Lifetime EP0589746B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9211220 1992-09-21
FR9211220A FR2695992B1 (fr) 1992-09-21 1992-09-21 Sous munition à effet dirigé.

Publications (2)

Publication Number Publication Date
EP0589746A1 true EP0589746A1 (de) 1994-03-30
EP0589746B1 EP0589746B1 (de) 1996-09-25

Family

ID=9433708

Family Applications (1)

Application Number Title Priority Date Filing Date
EP93402200A Expired - Lifetime EP0589746B1 (de) 1992-09-21 1993-09-09 Sub-Munition mit kontrollierter Aktivierung

Country Status (5)

Country Link
US (1) US5341743A (de)
EP (1) EP0589746B1 (de)
CA (1) CA2106499C (de)
DE (1) DE69305041T2 (de)
FR (1) FR2695992B1 (de)

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2693265B1 (fr) * 1992-07-02 1994-09-16 Giat Ind Sa Munition comportant des moyens de détection de cibles.
SE501082C2 (sv) * 1993-03-30 1994-11-07 Bofors Ab Sätt och anordning för att ge en luftburen stridsdel ett önskat rörelsemönster
DE4410326C2 (de) * 1994-03-25 1998-07-02 Rheinmetall Ind Ag Geschoß mit einer Vorrichtung zur Flugbahnkorrektur
DE19654865A1 (de) 1995-06-28 2015-06-25 Giat Industries Munition
SE508651C2 (sv) * 1995-10-05 1998-10-26 Bofors Ab För eldrörsvapen avsedd granat
DE69706738T2 (de) * 1996-04-05 2002-07-04 Luchaire Defense Sa Geschoss dessen Sprengladung durch einen Zielanzeiger ausgelöst wird
FR2810856B1 (fr) 2000-06-29 2002-09-27 Laetitia Lagardere Bijou lumineux et odoriferant
USH2236H1 (en) 2006-09-29 2010-04-06 The United States Of America As Represented By The Secretary Of The Navy Method for defeating a warhead that carries submunitions
DE102007025258A1 (de) * 2007-05-30 2008-12-04 Rheinmetall Waffe Munition Gmbh Gefechtskopf
US8979031B2 (en) * 2008-06-10 2015-03-17 Roy L. Fox, Jr. Aerial delivery system with munition adapter and latching release
US20110059421A1 (en) * 2008-06-25 2011-03-10 Honeywell International, Inc. Apparatus and method for automated feedback and dynamic correction of a weapon system
US8046203B2 (en) 2008-07-11 2011-10-25 Honeywell International Inc. Method and apparatus for analysis of errors, accuracy, and precision of guns and direct and indirect fire control mechanisms
US8434411B2 (en) 2011-01-19 2013-05-07 Raytheon Company Cluster explosively-formed penetrator warheads

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0033283A2 (de) * 1980-01-29 1981-08-05 SOCIETE EUROPEENNE DE PROPULSION (S.E.P.) Société Anonyme dite: Vereinfachtes Selbststeuerungssystem für Flugkörper, wie z.B. Granaten und Raketen
EP0252036A2 (de) * 1986-03-27 1988-01-07 Aktiebolaget Bofors Zielsuchende Submunition
EP0306391A1 (de) * 1987-08-21 1989-03-08 Intertechnique Verfahren und Gerät zur Auffindung eines Infrarot ausstrahlenden Zieles und dessen Anwendung für Munition
GB2224173A (en) * 1988-10-21 1990-04-25 Tzn Forschung & Entwicklung Target seeking from rotating missile

Family Cites Families (9)

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Publication number Priority date Publication date Assignee Title
FR2517818A1 (fr) * 1981-12-09 1983-06-10 Thomson Brandt Methode de guidage terminal et missile guide operant selon cette methode
FR2623897B1 (fr) * 1982-05-12 1990-09-28 Trt Telecom Radio Electr Perfectionnement a un dispositif de neutralisation d'objectifs militaires
DE3427227A1 (de) * 1984-07-24 1986-01-30 Diehl GmbH & Co, 8500 Nürnberg Endphasen-steuerbarer munitionsartikel und verfahren zu seiner zielnavigation
DE3516673A1 (de) * 1985-05-09 1986-11-13 Diehl GmbH & Co, 8500 Nürnberg Endphasen-korrigierbare suchzuender-munition und verfahren zum bekaempfen gepanzerter zielobjekte
FR2646232B1 (fr) * 1989-04-25 1994-03-11 Thomson Brandt Armements Systeme d'armes automatise pour la defense de zone
DE3936064A1 (de) * 1989-10-28 1991-05-02 Dynamit Nobel Ag Verfahren und einrichtung zum schnelleren automatischen oeffnen eines fallschirms
DE4017353A1 (de) * 1990-05-30 1991-12-05 Rheinmetall Gmbh Flugkoerper mit einer zieldetektionseinrichtung
DE4023069A1 (de) * 1990-07-20 1992-01-23 Diehl Gmbh & Co Mine, insbes. panzerabwehrmine
US5076511A (en) * 1990-12-19 1991-12-31 Honeywell Inc. Discrete impulse spinning-body hard-kill (disk)

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0033283A2 (de) * 1980-01-29 1981-08-05 SOCIETE EUROPEENNE DE PROPULSION (S.E.P.) Société Anonyme dite: Vereinfachtes Selbststeuerungssystem für Flugkörper, wie z.B. Granaten und Raketen
EP0252036A2 (de) * 1986-03-27 1988-01-07 Aktiebolaget Bofors Zielsuchende Submunition
EP0306391A1 (de) * 1987-08-21 1989-03-08 Intertechnique Verfahren und Gerät zur Auffindung eines Infrarot ausstrahlenden Zieles und dessen Anwendung für Munition
GB2224173A (en) * 1988-10-21 1990-04-25 Tzn Forschung & Entwicklung Target seeking from rotating missile

Also Published As

Publication number Publication date
CA2106499A1 (fr) 1994-03-22
FR2695992A1 (fr) 1994-03-25
EP0589746B1 (de) 1996-09-25
DE69305041T2 (de) 1997-02-06
DE69305041D1 (de) 1996-10-31
US5341743A (en) 1994-08-30
FR2695992B1 (fr) 1994-12-30
CA2106499C (fr) 1996-01-16

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