EP0438343B1 - Penetratormunition für Ziele mit hohem mechanischem Widerstand - Google Patents

Penetratormunition für Ziele mit hohem mechanischem Widerstand Download PDF

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Publication number
EP0438343B1
EP0438343B1 EP91400072A EP91400072A EP0438343B1 EP 0438343 B1 EP0438343 B1 EP 0438343B1 EP 91400072 A EP91400072 A EP 91400072A EP 91400072 A EP91400072 A EP 91400072A EP 0438343 B1 EP0438343 B1 EP 0438343B1
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EP
European Patent Office
Prior art keywords
munition
ammunition
front part
parachute
munition 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.)
Expired - Lifetime
Application number
EP91400072A
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English (en)
French (fr)
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EP0438343A3 (en
EP0438343A2 (de
Inventor
Jean Deffayet
Alain Lepicard
André Winaver
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.)
TDA Armements SAS
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TDA Armements SAS
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
Priority claimed from FR9000430A external-priority patent/FR2658283A1/fr
Priority claimed from FR9000432A external-priority patent/FR2657157B1/fr
Priority claimed from FR9000431A external-priority patent/FR2657158B1/fr
Application filed by TDA Armements SAS filed Critical TDA Armements SAS
Publication of EP0438343A2 publication Critical patent/EP0438343A2/de
Publication of EP0438343A3 publication Critical patent/EP0438343A3/fr
Application granted granted Critical
Publication of EP0438343B1 publication Critical patent/EP0438343B1/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
    • F42B12/20—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of high-explosive type
    • F42B12/201—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of high-explosive type characterised by target class
    • F42B12/204—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of high-explosive type characterised by target class for attacking structures, e.g. specific buildings or fortifications, ships or vehicles
    • 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
    • F42B10/02—Stabilising arrangements
    • F42B10/22—Projectiles of cannelured type
    • 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
    • F42B10/56—Range-reducing, destabilising or braking arrangements, e.g. impact-braking arrangements; Fall-retarding means, e.g. balloons, rockets for braking or fall-retarding of parachute or paraglider type
    • 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
    • F42B12/20—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of high-explosive type
    • F42B12/22—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of high-explosive type with fragmentation-hull construction
    • F42B12/24—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of high-explosive type with fragmentation-hull construction with grooves, recesses or other wall weakenings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • F42B15/36—Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means

Definitions

  • the invention relates to a perforating ammunition for high mechanical resistance targets.
  • Rodwell, Flight International - December 14, 1967 ammunition launched from an aerial vehicle with horizontal speed and attitude and intended to attack a target with horizontal development said munition comprising a system of braking positioned at the rear of the ammunition, said braking system being equipped with a parachute, which when deployed, gives the trajectory of the ammunition a curvature as close as possible to the vertical, ammunition further comprising a back-propelling means positioned on the ammunition so as to reduce the curvature of the trajectory of the ammunition for increase the effectiveness of said munition by reducing its obliquity and a propulsion means then being put into service to increase the speed of the ammunition and thus penetrate the target.
  • the object of the invention is to remedy the aforementioned drawbacks by proposing a solution allowing the use of a braking system with acceptable dimensions.
  • the subject of the invention is a munition launched from an air vehicle with horizontal speed and attitude and intended to attack a horizontal development target, said munition comprising a system of braking positioned at the rear of the ammunition, said braking system being equipped with a parachute, which when deployed, gives the trajectory of the ammunition a first curvature as close as possible to the vertical, ammunition further comprising a back-propelling means positioned on the ammunition so as to reduce the first curvature of the trajectory of the ammunition obtained thanks to the parachute, which means of retropropulsion is ignited after deployment of the parachute, to increase the efficiency of said ammunition by reducing its obliquity, the back-propelling means being stopped at the end of the braking phase, and a propulsion means then being put in service to increase the speed of the ammunition and thus penetrate the target.
  • the invention also relates to a piercing munition comprising a front part formed by an envelope containing a charge explosive and a rear part, fixed to the front part by a means of fixing and comprising a set of modules ensuring operation ammunition, characterized in that at least one of the modules is placed annularly around part of the front part of the ammunition for limit the size of the ammunition by ensuring its effectiveness.
  • the present invention also relates to ammunition for target with high mechanical resistance, of the anti-track bomb type, capable of penetrate sufficiently even in very thick slabs.
  • the external surface of the part front has longitudinal grooves which have for function, on the one hand, to reduce the friction forces which oppose the entry into the track and, on the other hand, increase the transverse stiffness of the ammunition so as to reduce, during an oblique impact, the risk of flexion of the ammunition and ricochet thereof.
  • the envelope of the front body is further made so that the splines form longitudinal hollow charges which pre-fracture, during the explosion, the concrete surrounding the front body.
  • Figure 2 shows a first embodiment ammunition equipped with the device according to the invention.
  • This ammunition has two parts: a part front 1 intended to deteriorate a high resistance surface mechanical, for example a concrete track, or by entering it preferably over its entire length, either by crossing it and exploding below, and, a rear part 2 which may be, or no, with a diameter greater than that of the front part 1 and intended to provide a set of ballistic functions of the ammunition.
  • a part front 1 intended to deteriorate a high resistance surface mechanical, for example a concrete track, or by entering it preferably over its entire length, either by crossing it and exploding below
  • a rear part 2 which may be, or no, with a diameter greater than that of the front part 1 and intended to provide a set of ballistic functions of the ammunition.
  • the front part 1 is, for example, in the form cylindrical. It consists of an envelope 3, by steel example, which ends at the front with a warhead 4, by conical example, and contains an explosive charge 5. Others elements can constitute the front part 1, for example a ballast respectively improving the power of penetration of the ammunition and shift the center of gravity ammunition or a priming rocket to fire the charge explodes and can be extended by a channel priming; these elements are not shown in the figure 1 and do not prevent the device from operating according to the invention.
  • the front part 1 of the ammunition extends, in the embodiment example, inside the rear part 2 which thus covers it annularly.
  • a fastening system 6 holds the rear part 2 on the front part 1 so that the rear part 2 does not not oppose the penetration of the front part 1 into the track concrete.
  • the rear part 2 comprises, among other things, a propellant 7 part of which can engage in space ring between front part 1 and rear part 2, a tail made up of fins 8 fixed for example on the periphery of a nozzle 9 positioned at the rear of the propellant 7 and a braking system comprising, for example, a box 10 inside which is placed a parachute 11 and fixed to the nozzle 9 of propellant 7, for example, by a system of unlockable mechanical fastener 12.
  • the thrust given by the retropulsor can be spread over a relatively long time with a date earlier ignition.
  • FIG. 3 represents the comparison between the trajectory of a munition without back-propulsion SR and the trajectory of a munition with back-propulsion R.
  • the device according to the invention applies to armor-piercing ammunition for high resistance targets mechanical but it applies to all ammunition having a almost vertical impact with minimal impact difficult to obtain by the sole use of a parachute.
  • FIG. 4 represents the diagram of a first mode of production of the ammunition according to the invention.
  • Ammunition has two parts: a front part 101 intended for deteriorate a surface with high mechanical resistance, by example a concrete track, preferably by entering it, along its entire length, either by crossing it and exploding in underside and a rear part 102 intended to ensure an assembly of ballistic functions of the ammunition.
  • This rear part 102 integral with the front part 101, before the impact of the ammunition on the target, is detached at the time of impact so as not to slow down the penetration of the front part 101 in the target.
  • the front part 101 is, for example, in the form cylindrical. It consists of an envelope 103, by steel example, which ends at the front with a warhead 104, for example conical and at the rear for example by a rocket ignition device 105 placed behind an explosive charge 106 contained inside the envelope 103 and allowing trigger the charge explosion when the perforation is carried out, the initiation of the explosive charge being transmitted, by example at the front of the munition, by a priming channel 150 to increase the destructive power of the ammunition.
  • the outer surface of the envelope is, for example, smooth but it can be of any other form, for example formed of splines to, on the one hand, reduce friction forces during penetration and on the other hand increase the stiffness transverse of the ammunition to limit the bending of the ammunition during its impact on the target.
  • the front part 101 of the ammunition may include other elements. Indeed, in this figure 5, we find all the elements described in Figure 4 and constituting the ammunition. However a additional element has been added to the front of the game before 101.
  • This element constituting a ballast 107 is placed, by example, in the warhead 104 and on part of the front part 101.
  • This ballast 107 made of a dense material for example the tungsten allows, on the one hand, to improve the power of penetration of the front part 101 by increasing its mass, and, on the other hand, to reposition the center of gravity of the ammunition by moving it forward so as to reduce risk of rotation and bending of the ammunition when impact on the target.
  • the maximum diameter of the front part 101 has a value lower than that of the rear part 102 so that the front part 101 extends inside the rear part 102. In this way the rear part 102 covers a part of the front part 101 annularly.
  • the effect penetration of the ammunition, in particular of the front part 101 being due mainly to kinetic energy it is essential to transmit the pushing force of the part rear 102 to the front part 101 during the first part of penetration.
  • the rear structure of the envelope 103 of the front part 101 presents, for example, a narrowing of conical type 108 on its periphery so that a fixing means, for example a fixing asymmetrical, for example a fixing ring 110 fixed to the rear part 102, for example, by laser welding after setting propellant loading place at a stop 113 of the fixing ring or by thread at the same stop, comes to bear on an oblique element 109 of the narrowing 108.
  • a fixing means for example a fixing asymmetrical, for example a fixing ring 110 fixed to the rear part 102, for example, by laser welding after setting propellant loading place at a stop 113 of the fixing ring or by thread at the same stop
  • This asymmetrical fixing makes it possible, on the one hand, to transmit the thrust from the rear part 102 of the ammunition to the front part 101 of the ammunition before the impact of the ammunition on the target, and, on the other hand to release, to the impact of the ammunition on the target, the front part 101 of the rear part 102 to facilitate penetration of the front part 101 of the ammunition in the target.
  • This fixing ring 110 including a mode of embodiment is shown in detail in the figure 6, allows the front part 101 to be secured to the part rear 102 thanks to screws 111 positioned, for example, in holes 112, for example six in number, made in the ring 110.
  • screws 111 penetrate to the inside of the envelope 103 on a much smaller thickness to the thickness of the envelope 103 to avoid any disturbance leading to a deterioration of the front part 101.
  • These screws 111 are, for example, shear screws which, when the ammunition penetrates the target, are sheared, allowing the front part to slide freely 101.
  • the size of the ammunition must be limited by a particular arrangement of all the modules contained in the rear part 102 of the ammunition, each of modules fulfilling a function essential to efficiency desired ammunition.
  • the translational movement of the cover 139 is produced, for example, along an axis substantially parallel to X'X.
  • the pushing force separating the cover 139 is generated, for example, by gases from, for example, thruster 116 when it is on.
  • the use of this thruster 116 to give the necessary thrust force simplifies the unlockable fixing system by using elements specific to the ammunition, in this case propellant gases 116 having the initial function of giving to the ammunition a determined speed to increase its efficiency, to trigger the separation of the elements.
  • the casing 123 of the braking system 119 has, for example, a square section to increase the available volume of the parachute necessary to obtain an incidence sufficiently low ammunition; in the example of realization, the incidence is around 30 °. To decrease this incidence, it would be necessary to increase the dimensions of the volume parachute which seems difficult considering the dimensions imposed for ammunition.
  • the square section of the box 123 also facilitates the storage of ammunition inside the holds of an aerial vehicle which can be for example a cargo ship stand-off carrying ammunition as shown in the figure 8.
  • This air vehicle 141 carries numerous ammunition A, B, C comprising the various modules described previously.
  • Ammunition A includes in its rear part the box 123 of square section containing the braking parachute not shown, the propellant whose casing 115 has by example a circular section and the tail unit comprising by example four fins 121 which, in the folded position, are housed in the space between the envelope 115 and the section prism square of box 123 and in its front part, the front part whose casing 103 is cylindrical.
  • the operation of the munition according to the invention, illustrated in FIG. 9, in an application intended for the deterioration of a horizontal target is as follows: ammunition is dropped, for example, from an air vehicle onto a concrete track on ground 142 of thickness E and which must be deteriorated.
  • This ammunition includes the braking system 119 to the interior of which is placed the parachute, not shown, the empennage 120 to ensure the balance of the ammunition.
  • the release of the thruster 116 allows the release of the system braking 119 and the front part 101 extending into the propellant 116 and containing the explosive charge necessary for the deterioration of the target and not shown in this figure 9.
  • phase II After a free fall flight time, represented by phase I and where the ammunition is subjected to terrestrial gravitation, to the resistance of the air and the speed acquired during ejection, the ammunition braking parachute is deployed, in phase II, to bend the trajectory of the ammunition towards the target, in this case the concrete track 142.
  • the braking system is disconnected from the ammunition following phase III through the unlockable fixing under the action of gases from the propellant 116 which, on the other hand, make it possible to give, to the ammunition, a speed necessary for the penetration of the part before 101 in the concrete runway 142.
  • phase IV during the impact of the front part 101 on the concrete track, the ring fixing not shown now the front part 101 to rest of the ammunition is detached allowing to penetrate only the front part 101 of the ammunition in the runway concrete, taking advantage of all the kinetic energy of the ammunition.
  • the perforating power must be defined so that the depth of penetration of the "center” of the explosion (in general the point of initiation of the explosive charge) or actually at the "h” position.
  • only one sequencer and part of the propellant are arranged so annular around the front part 101; this embodiment is particular and it is possible to place other modules necessary for the operation of ammunition around the front part 101 of the ammunition to respect the dimensions imposed on ammunition.
  • the arrangement of the modules in the ammunition according to the invention is particularly applicable to ammunition anti-tracks but can be used on any ammunition in front meet cost, transport and employment constraints and designed to punch a target with a high surface mechanical resistance before damaging it by explosion.
  • Figure 10 shows schematically another embodiment of the ammunition according to the invention.
  • This munition essentially comprises two parts: a front body C A intended to perforate the material, for example concrete, forming the target, preferably penetrating it over its entire length, and a rear body C which may or may not be of greater diameter to that of the front body as shown in the figure.
  • the rear body C comprises the various mechanical, electronic or pyrotechnic organs necessary for propelling, guiding, piloting or braking the ammunition; for this purpose it carries, for example, as shown in the figure, fins A forming a tail and a propulsion nozzle T.
  • the front body C A is, in this embodiment, of substantially cylindrical shape and it is terminated at the front by a warhead O G , substantially conical.
  • FIG. 11 represents a cross-sectional view, taken along an axis AA in the cylindrical part of the front body C A.
  • the body C A is constituted by an EN envelope of material having good mechanical resistance (steel, for example), enclosing an explosive charge C H.
  • the outer surface of the envelope EN in its cylindrical part, has longitudinal grooves C N , preferably over its entire length.
  • the grooves C N are shown in FIG. 12 as being of rectangular section but they can have other shapes, such as square, semi-circular, triangular, etc.
  • the operation of the ammunition according to the invention is the following.
  • the kinetic energy imparted to the ammunition is such that it allows it to perforate the target concrete mass, typically an aerodrome runway, by sinking, preferably over the entire length of the body before C A.
  • This perforation can in practice be a complete perforation of the thickness of concrete or, only, a semi-perforation.
  • a priming rocket not shown for example contained in the rear body C, triggers the explosion of the charge C H.
  • the splines C N produced in the front body C A have the effect in particular, on the one hand, of reducing the frictional forces during the penetration of the body C A into the concrete and, on the other hand, of increasing the stiffness transverse of the ammunition during the impact on the concrete, in order to reduce the risks of bending of the body before the engagement of the warhead.
  • the parameters (dimensions, material) of the casing and of the grooves are chosen so that each of the grooves functions as a longitudinal hollow charge when the charge C H explodes, making thus a pre-fracturing of the concrete mass surrounding the body C A ; this allows the improvement of the mucking power of the quantity of explosive charge contained in the ammunition and, consequently, the enlargement of the crater thus formed.
  • FIG. 12 represents a fractional cross-sectional view of an alternative embodiment of the grooved casing (EN) of the front body (C A ) of the munition according to the invention.
  • the inner surface of the envelope EN also has longitudinal grooves, marked C I , alternated with the grooves C N.
  • the dimensions of these grooves C I are chosen to favor the hollow charge effect mentioned above.
  • these extend over all or part of the warhead O G.
  • Figure 13 shows a diagram similar to that of Figure 10, on which are illustrated different variants of the munition according to the invention.
  • the front body C A is formed by the envelope EN ' having splines C N and containing an explosive charge C H.
  • the grooved front body C A which is recalled that it is intended to perforate the target concrete over its entire length, extends inside the rear body C, which thus covers it annularly.
  • the attachment of the rear body C to the front body C A is then such that the body C is not significantly opposed to the penetration of the front body (C A ) into the target concrete.
  • This variant has the advantage of increasing the length of the front body C A , for a given total length of ammunition, thereby notably increasing the amount of explosive charge C H or, conversely, of reducing the total length of the ammunition to length of body C A given: in fact, the annular space between the bodies C A and C can be used to arrange at least some of the elements which are contained in the body C.
  • the rocket for initiating the load C H , marked F is placed in the front body C A , behind the load C H.
  • the front part of the body C A namely the warhead O G and possibly a part of the cylindrical portion of the body C A
  • a dense material L constituting a ballast.
  • This material consists for example of tungsten.
  • the presence of this ballast has the function, on the one hand, of improving the power of penetration of the body C A by increasing its mass, at given section, and, on the other hand, of displacing the center of gravity ammunition forward, which reduces the risk of tilting, bending and ricochet of the munition at the time of engagement of the warhead.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Physical Vapour Deposition (AREA)
  • Powder Metallurgy (AREA)
  • Earth Drilling (AREA)

Claims (25)

  1. Von einem Luftfahrzeug mit einer Geschwindigkeit und einer waagrechten Bewegungskomponente abgeworfene Munition, die ein sich im wesentlichen waagrecht erstreckendes Ziel angreifen soll und ein am hinteren Ende der Munition legendes Bremssystem mit einem Fallschirm (11) enthält, der bei seiner Entfaltung der Flugbahn der Munition eine erste Krümmung verleiht, die der Vertikalen möglichst nahekommt, wobei die Munition weiter ein Gegenschubmittel (13) enthält, das so an der Munition angebracht ist, daß die erste Krümmung der durch den Fallschirm erzielten Bahn der Munition verringert wird, und so nach dem Entfalten des Fallschirms gezündet wird, daß die Wirksamkeit der Munition durch Verringerung ihrer Schräglage erhöht wird, wobei das Gegenschubmittel am Ende der Bremsphase stillgelegt wird und dann ein Antriebsmittel (116) zur Vergrößerung der Geschwindigkeit der Munition und zum Eindringen in das Ziel gezündet wird.
  2. Munition nach Anspruch 1, dadurch gekennzeichnet, daß das Gegenschubmittel ein Gegentreibsatz (13) ist, der mit einem Teil der Munition fest verbunden ist.
  3. Munition nach Anspruch 2, dadurch gekennzeichnet, daß der Gegentreibsatz (13) ringförmig um ein vorderes Teil (1) der Munition angeordnet ist.
  4. Munition nach Anspruch 2, dadurch gekennzeichnet, daß der Gegentreibsatz (13) Düsen (14) besitzt, die symmetrisch bezüglich einer Längsachse XX' der Munition angeordnet sind und einen Schub parallel zu dieser Achse XX' liefern.
  5. Munition nach Anspruch 1, dadurch gekennzeichnet, daß das Bremssystem einen Behälter (10) mit quadratischem Querschnitt aufweist, in dem der Fallschirm (11) untergebracht ist, welcher die Munition zuerst umlenkt.
  6. Munition nach Anspruch 1, dadurch gekennzeichnet, daß das Bremssystem mit einer Düse (9) des Triebwerks (7) der Munition durch ein entriegelbares Befestigungssystem gekoppelt ist.
  7. Munition nach Anspruch 3, dadurch gekennzeichnet, daß das vordere Teil (1) zumindest teilweise ringförmig vom hinteren Teil (2) bedeckt wird.
  8. Munition nach einem der Ansprüche 1 bis 7 mit einem vorderen Teil (101), das eine Hülle (103) und eine darin enthaltene Explosivladung (106) enthält, und mit einem hinteren Teil (102), das am vorderen Teil (101) durch ein Befestigungsmittel (110) befestigt ist und eine Gruppe von Moduln enthält, die den Betrieb der Munition gewährleisten, dadurch gekennzeichnet, daß mindestens einer der Moduln ringförmig um einen Bereich des vorderen Teils (101) der Munition angeordnet ist, um den Platzbedarf der Munition zu begrenzen und ihre Wirksamkeit zu gewährleisten.
  9. Munition nach Anspruch 8, dadurch gekennzeichnet, daß die im hinteren Teil ringförmig um das vordere Teil (101) herum angeordneten Moduln eine Folgesteuerung (114) und eine Ergänzung (117) eines Triebwerks (116) sind.
  10. Munition nach Anspruch 8, dadurch gekennzeichnet, daß das Mittel zur Befestigung des hinteren Teils (102) am vorderen Teil (101) eine unsymmetrische Befestigung ist, mit der das vordere und das hintere Teil (101, 102) der Munition vor dem Auftreffen auf dem Ziel zusammengehalten werden und die nach dem Auftreffen auf dem Ziel das vordere Teil (101) vom hinteren Teil (102) löst.
  11. Munition nach Anspruch 8, dadurch gekennzeichnet, daß das Mittel zur Befestigung des hinteren Teils (102) am vorderen Teil (101) ein Befestigungsring (110) ist, der einerseits am vorderen Teil (101) durch Scherschrauben (111) und andrerseits am hinteren Teil (102) durch eine Laserschweißung befestigt ist.
  12. Munition nach Anspruch 8, dadurch gekennzeichnet, daß das vordere Teil (101) eine Ballastmasse (107) enthält.
  13. Munition nach Anspruch 12, dadurch gekennzeichnet, daß die Ballastmasse (107) aus einem dichten Material besteht.
  14. Munition großer Durchschlagskraft nach Anspruch 9, dadurch gekennzeichnet, daß Moduln der Gruppen von Moduln des hinteren Teils (102) ein Bremssystem, das mithilfe eines entriegelbaren Befestigungssystems gegenüber dem Triebwerk (116) positioniert ist, und ein Leitwerk aufweisen, das am Umfang eines divergierenden Rands (122) des Triebwerks (116) befestigt ist.
  15. Munition nach Anspruch 14, dadurch gekennzeichnet, daß das von einem Fallschirm (124) gebildete Bremssystem einen Behälter (123) mit quadratischem Querschnitt aufweist, um das Volumen des Fallschirms (124) zu vergrößern.
  16. Munition nach Anspruch 8, dadurch gekennzeichnet, daß das vordere Teil einen Zünder (105) enthält, der im hinteren Bereich des vorderen Teils liegt und durch einen Zündkanal (150) verlängert ist, um das Zentrum der Explosion zu verschieben und so die Wirksamkeit der Munition zu erhöhen.
  17. Munition nach Anspruch 8, dadurch gekennzeichnet, daß der Durchmesser des vorderen Teils geringer als der Durchmesser des hinteren Teils ist, sodaß das vordere Teil über eine bestimmte Länge in das hintere Teil eindringt.
  18. Munition nach einem der vorstehenden Ansprüche, dadurch gekennzeichnet, daß sie ein vorderes Teil oder einen vorderen Körper (CA) aufweist, der in das Ziel eindringen soll und eine Hülle (E) sowie darin eine Explosivladung (CH) enthält, wobei die äußere Oberfläche der Hülle Längsrinnen (CN) aufweist, und daß das Material der Hülle (E), ihre Geometrie und die Rinnen (CN) so gewählt sind, daß die Rinne längliche Hohlladungen bilden.
  19. Munition nach einem der vorstehenden Ansprüche, dadurch gekennzeichnet, daß der vordere Körper in einer im wesentlichen konischen Spitze (OG) endet.
  20. Munition nach Anspruch 19, dadurch gekennzeichnet, daß die Rinnen (CN) sich bis zur Spitze (OG) verlängern.
  21. Munition nach einem der vorstehenden Ansprüche, dadurch gekennzeichnet, daß die innere Oberfläche der Hülle (E) Längsrinnen (CI) abwechselnd mit den Rinnen (CN) auf der äußeren Oberfläche aufweist.
  22. Munition nach einem der vorstehenden Ansprüche, dadurch gekennzeichnet, daß die Spitze (OG) und/oder der vordere Körper (CA) ein dichtes Material enthalten, das eine Ballastmasse (L) bildet.
  23. Munition nach einem der vorstehenden Ansprüche, dadurch gekennzeichnet, daß der vordere Körper (CA) im wesentlichen zylindrisch ist.
  24. Munition nach einem der vorstehenden Ansprüche, dadurch gekennzeichnet, daß sie ein hinteres Teil oder einen hinteren Körper (C) aufweist, der die Antriebsmittel, die Führungsmittel, die Lenkmittel oder die Bremsmittel der Munition enthält.
  25. Munition nach Anspruch 24, dadurch gekennzeichnet, daß der vordere Körper (CA) zumindest teilweise ringförmig vom hinteren Körper (C) bedeckt ist.
EP91400072A 1990-01-16 1991-01-15 Penetratormunition für Ziele mit hohem mechanischem Widerstand Expired - Lifetime EP0438343B1 (de)

Applications Claiming Priority (6)

Application Number Priority Date Filing Date Title
FR9000430A FR2658283A1 (fr) 1990-01-16 1990-01-16 Munition perforante cannelee, notamment anti-beton.
FR9000431 1990-01-16
FR9000430 1990-01-16
FR9000432A FR2657157B1 (fr) 1990-01-16 1990-01-16 Dispositif de correction de courbure d'un trajectoire d'une munition perforante pour des cibles a haute resistance mecanique.
FR9000432 1990-01-16
FR9000431A FR2657158B1 (fr) 1990-01-16 1990-01-16 Munition perforante pour cible a haute resistance mecanique.

Publications (3)

Publication Number Publication Date
EP0438343A2 EP0438343A2 (de) 1991-07-24
EP0438343A3 EP0438343A3 (en) 1991-09-25
EP0438343B1 true EP0438343B1 (de) 1998-07-22

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Application Number Title Priority Date Filing Date
EP91400072A Expired - Lifetime EP0438343B1 (de) 1990-01-16 1991-01-15 Penetratormunition für Ziele mit hohem mechanischem Widerstand

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US (1) US5189248A (de)
EP (1) EP0438343B1 (de)
AT (1) ATE168768T1 (de)
DE (1) DE69129815T2 (de)
ES (1) ES2118744T3 (de)

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AU755039B2 (en) * 1999-03-25 2002-11-28 Rafael-Armament Development Authority Ltd. An armor piercing projectile
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EP1167914A1 (de) * 2000-06-19 2002-01-02 SM Schweizerische Munitionsunternehmung AG Selbstangetriebenes Geschoss mit einem Durchschlagskern
DE10130324B4 (de) * 2001-06-22 2005-03-24 TDW Gesellschaft für wehrtechnische Wirksysteme mbH Splittererzeugender Gefechtskopf
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WO2008033170A2 (en) * 2006-05-16 2008-03-20 Textron Systems Corporation Controlled dispense system for deployment of components into desired pattern and orientation
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RU2642197C2 (ru) * 2016-07-01 2018-01-24 Российская Федерация, от имени которой выступает Министерство промышленности и торговли Российской Федерации (Минпромторг России) Высотный активно-реактивный снаряд и способ его функционирования
DE102016015042B4 (de) * 2016-12-16 2018-08-23 Diehl Defence Gmbh & Co. Kg Munitionsmodul, Gefechtskopf und Munition
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Also Published As

Publication number Publication date
EP0438343A3 (en) 1991-09-25
ES2118744T3 (es) 1998-10-01
EP0438343A2 (de) 1991-07-24
DE69129815T2 (de) 1998-12-03
ATE168768T1 (de) 1998-08-15
DE69129815D1 (de) 1998-08-27
US5189248A (en) 1993-02-23

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