EP1766323B1 - Geschoss, insbesondere eine infrastruktur durchschlagende bombe und wanddurchschlagverfahren für das geschoss - Google Patents

Geschoss, insbesondere eine infrastruktur durchschlagende bombe und wanddurchschlagverfahren für das geschoss Download PDF

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Publication number
EP1766323B1
EP1766323B1 EP05752648A EP05752648A EP1766323B1 EP 1766323 B1 EP1766323 B1 EP 1766323B1 EP 05752648 A EP05752648 A EP 05752648A EP 05752648 A EP05752648 A EP 05752648A EP 1766323 B1 EP1766323 B1 EP 1766323B1
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EP
European Patent Office
Prior art keywords
projectile
perforating
tube
bomb
pyrotechnic charge
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 - Fee Related
Application number
EP05752648A
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English (en)
French (fr)
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EP1766323A1 (de
Inventor
Denis Salignon
Claude Georget
Dominique Lesne
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
Application filed by TDA Armements SAS filed Critical TDA Armements SAS
Publication of EP1766323A1 publication Critical patent/EP1766323A1/de
Application granted granted Critical
Publication of EP1766323B1 publication Critical patent/EP1766323B1/de
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
    • F42B12/56—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information for dispensing discrete solid bodies
    • F42B12/58—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles
    • F42B12/62—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles the submissiles being ejected parallel to the longitudinal axis of the projectile
    • F42B12/625—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles the submissiles being ejected parallel to the longitudinal axis of the projectile a single submissile arranged in a carrier missile for being launched or accelerated coaxially; Coaxial tandem arrangement of missiles which are active in the target one after the other
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C11/00—Electric fuzes
    • F42C11/06—Electric fuzes with time delay by electric circuitry

Definitions

  • the present invention relates to a penetrating projectile, including an anti-infrastructure penetration bomb. It is particularly applicable for traversing very thick walls of non-metallic material such as concrete for example.
  • a bomb is carried by a rocket.
  • a rocket has essentially three parts. At the front it contains its guidance system and at the rear its engine for propulsion. Between these two elements is the military charge, in other words essentially the bomb.
  • the size and weight of the rockets are fixed and their speed. It follows that the volume, the weight and the speed of the bomb are also fixed, whatever the required performances. In particular, the kinetic energy can not be increased in order to obtain new performances, even more advanced.
  • the first solution prevents in particular to make a bomb body versatile with respect to surface threats or buried.
  • the second solution leads to a bomb body very expensive and actually a bomb very inefficient because the explosive mass on board is then reduced by more than half compared to a normal body of steel.
  • a patent application FR 2 472 168 A presents a sub-projectile launcher where the latter are accelerated at the end of the trajectory.
  • the piercing projectile comprises for example a system which determines its position inside the target as a function of time and which triggers the detonation of its pyrotechnic charge at a predetermined time.
  • This system determines for example the position of the perforator from its characteristics of the deceleration levels in the target material and its speed at the point of impact on the target.
  • the inner tube comprises at least two sections of different calibres, the smaller gauge section being oriented towards the exit of the tube, the body of the projectile perforator being adapted to the output caliber of the tube, the propulsion body being wedged at the transition of the two sections during the ejection of the piercing projectile body.
  • the transition between the two sections forms for example a cone so that the casing of the propellant body is welded by friction on the cone.
  • the body of the piercing projectile can be fixed to the casing of the propellant body by pins.
  • the main advantages of the invention are that it can be implemented at a constant volume, mass and speed with respect to the current solutions, that it makes it possible to increase the range of arrival angle of the body. a bomb on a wall, and that it increases the load of explosive board.
  • the figure 1 represents the structure of a rocket 1. As indicated above, it consists essentially of three parts 2, 3, 4. The front of the rocket comprises the guide means 2 and the rear comprises the means 3. Between the two is the penetrating projectile 4, for example a military load such as a bomb. The fact that the envelope of the rocket is frozen as well as the overall mass results in the volume and the mass devoted to the penetrating projectile 4 are also fixed, to the extent that it is also not possible to reduce the allocated parts the guide means and the propulsion means. The structural mechanical strength of the penetrating body can not therefore be significantly increased. Likewise the speed of the penetrating body is fixed by the speed of the rocket 1.
  • the figure 2 presents, by a cross-sectional view, an exemplary embodiment of a projectile according to the invention.
  • the projectile is a bomb.
  • the figure 2 so has a bomb 10 that can be contained in the space allocated to the penetrating body 4 in the rocket of the figure 1 while having great penetration performance.
  • the bomb comprises a body 21 inside which a tube 22 is placed.
  • the tube 22 comprises, for example, a wedging cone 221 making the transition between a first tube section 222 and an outlet section 223 of smaller caliber, oriented forward of the bomb body.
  • the bomb body 21 being symmetrical with revolution, the axis 20 of the tube 22 merges for example with the axis of the body 21.
  • the pyrotechnic charge 23 is disposed inside the bomb body 21 around the tube 22.
  • the load 23 is contained inside a sheath 24, placed between the inner face of the bomb body 21 and the tube 22.
  • a priming relay 25, for example of toric shape, located inside the pyrotechnic charge 23 allows to start the firing of the latter.
  • a base 20 closes the rear of the bomb body 21.
  • a striker 26 is placed in the base opposite the ignition relay 25, through the wall 27. The striker 26 is controlled by an electronic block 28, for example of toric form, also contained in the base 20.
  • a shock attenuator 29 is placed in front of the pyrotechnic charge, wedged between the sheath 24 and the inside of the bomb body 21. Inside the tube is arranged a projectile puncher hyper velocity 30 pyrotechnic charge.
  • This perforator allows in particular the prior creation of a conduit in the wall to be crossed. For this purpose, at the approach of the wall, the perforator leaves the tube, thanks to its own propulsion means, with a speed much higher than that of the bomb body 21. Then it detonates once introduced inside the wall.
  • the figure 3 presents, by a cross section, an exemplary embodiment of the projectile projectile 30.
  • This projectile comprises a body 31. This body has for example at the front a tip 32 to facilitate penetration. Inside the body is placed a pyrotechnic charge. ignition relay 34 is placed inside the load 33. A support 35 closes the space at the rear of the pyrotechnic charge 33. This support 35 comprises a striker 39 located opposite the ignition relay 34 for performing a percussion initiation which causes the ignition of the pyrotechnic charge 33. The striker 39 is controlled by an electronic block 36 also placed in the support 35. A cover 37 closes the rear of the body. A propellant body 301 is placed behind the body of the projectile 31.
  • This propellant body 301 is held in the body of the projectile by means of pins 38.
  • the outer wall of the propellant body 301 is extended inside a body. wall portion of the body of the projectile extending itself beyond the cover 37.
  • the pins pass through the two walls facing each other through holes provided for this purpose.
  • the propellant body has inside its envelope 303 a pyrotechnic charge 302.
  • This load 302 is for example composed of plastic loaves.
  • a cap 304 closes the rear of the propulsion body.
  • the cap 304 comes for example to screw on the casing 303 of the propellant body.
  • One or more lids 305 are pierced in the plug to pass a control link 306.
  • This connection is for example connected to an ignition pad 307 placed in contact with the pyrotechnic charge 302.
  • Calibration means 308 are for example placed between the cap 304 and the loading of the propulsion body 302.
  • the firing of the propulsion body 301 causes the tube 31 to be ejected from the tube of the piercing projectile 30.
  • the figure 4 presents the rocket 1 in two places of its trajectory to a concrete wall 42 in an x, y axis system.
  • the positions relative to the ground are indicated on an x-axis.
  • the y-axis represents the altitude of the rocket.
  • the scales of distances and altitudes are reduced compared to the scales of representation of the rocket and the slab.
  • the distance x 1 - x 0 is, for example, the order of 20 meters.
  • the separation is carried out by an internal firing, the bomb 10 is then ejected from the rocket.
  • the position of the rocket relative to the wall 42 is for example determined by a proximity sensor located at the front of the rocket with the guide means.
  • FIGS. 5a to 5f illustrate the method according to the invention by presenting different phases of a bomb according to the invention in approach phase and through the wall 42.
  • the figure 5a presents the moment of firing of the loading 302 of the propellant body of the perforator 30 to the immediate approach of the target in this case the wall 42.
  • the bomb is at a distance d less than the distance x 1 - x 0 .
  • This distance d is for example of the order of 10 meters.
  • the distances x 1 - x 0 and d may be substantially the same.
  • the perforator 30 is ejected from the bomb body 21 with a very high speed relative to this body. For example, if the bomb moves at a speed of the order of 300 m / s, the perforator can exit with a relative speed of this order.
  • the bomb body may for example calculate a delay between the moment of ejection of the bomb body of the rocket and the moment of priming of the propellant body of the perforator, the moment of ejection of the bomb body being determined him for example by the guide means 2 located in front of the rocket 1.
  • the control of the electronic unit 28 to the thruster body of the perforator is done for example by means of an electrical connection 306.
  • An active electrical signal for example the ignition pad 307 which triggers the firing of the pyrotechnic charge 302.
  • the figure 5b presents the flight of the perforator 30 to the wall 42, followed by the bomb body 21.
  • the ignition pad 307, the electrical connection 306 and the electronic block compose a system for controlling the firing of the propulsion body 301 before the impact of the bomb 10 on a target, the wall 42 in the example of Figures 5a to 5f .
  • Another type of system could be used.
  • the figure 5c the penetration of the perforator 30 in the wall 42.
  • the relative speed of the latter relative to the bomb body allows it to firstly impact the wall 42.
  • the figure 5d has the detonation of the perforator 30 inside the wall, preferably in the middle, creating an orifice 51 passing through the wall 42.
  • the perforator comprises a system which determines its position inside the wall in function of time and which triggers the detonation of its pyrotechnic charge at a predetermined time.
  • This system is for example contained in the electronic block 36.
  • the detonation is caused by the firing of the pyrotechnic charge 33.
  • the invention advantageously uses the fact that the concretes do not hold the tensile stress. This allows them to be destructured relatively easily by a detonation of the perforator inside the wall, this internal detonation creating high tensile stresses.
  • An internal processor located in the electronic block 36 of the perforator can determine the moment of detonation of the perforator corresponding to its most effective position inside the wall, for example in the middle thereof. For this purpose a table is for example stored in the processor. This table contains the characteristics of the deceleration levels of an object penetrating into a material. It can take into account several types of materials including of course concrete and even different types of concrete.
  • the figure 5e has the penetration of the bomb body 21 in the orifice 51 created by the perforator.
  • the amount of charge conveyed by the perforator 30 may be calculated to obtain an orifice adapted to the caliber of the bomb body 21, that is, to say in practice close to the caliber of the body of bomb.
  • the invention thus makes it possible to considerably reduce the stresses seen by the bomb body during its phase of penetration into the wall and therefore allows a bomb of relatively low structural mechanical strength to pass through walls that are thicker and thicker. resistant.
  • the figure 5f presents the bomb body 21 after crossing the wall 42. At this time the bomb body can for example detonate by firing its pyrotechnic charge 23.
  • the figure 6 highlights an advantage provided by the jamming cone 221 of the inner tube to the bomb body.
  • the figure 6 shows the maintenance of the propellant body of the perforator 30, in particular of the casing 303 of the propellant body 301, in the tube by jamming of the latter at the jamming cone 221.
  • the casing 303 whose diameter is greater than the caliber of the output section of the tube, under the effect of the speed, is soldered by friction on the internal jamming cone of the tube. This avoids any potential intrusion of rubble into the body of the bomb.
  • the maintenance of the propellant body is reinforced by the confinement within the tube of all the propulsion gases.
  • the envelope 303 remains welded to the tube while the body 31 of the perforator, adapted to the output caliber of the tube 22, is ejected from the tube.
  • the body 31 of the perforator is detached from the casing 303 of the propulsion body by shearing the pins 38 which fix the two bodies together.
  • the casing of the propellant body thus forms a protective wall. Indeed, as just indicated above, it thus prevents any intrusion of rubble or debris 52 inside the bomb body during the phase of penetration of the latter in the wall. Such debris, generated in particular during the detonation of the perforator 30 inside the wall as shown in FIG. figure 5 e , could indeed cause parasitic explosions.
  • the resistance of the wall to external intrusions is enhanced by the internal pressure generated by the combustion gases in the tube 22.
  • the function of sealing provided to the propellant body keeps the combustion gases within the tube which, by their thrust, strengthen the strength of the weld.
  • the figure 7 illustrates another advantage of the invention.
  • this figure shows that the invention makes it possible to increase the angle of arrival angle range of the bomb body 21 on a wall 71.
  • the orifice 72 created by the perforator in the wall 71 creates there even an entry face 73 normal to the speed vector V of the body of the bomb.
  • This inlet face 73 in particular avoids the ricochets of the bomb body on the wall when the angle of incidence ⁇ of its velocity vector on the wall is too low. If this angle ⁇ is nevertheless much too weak, there will nevertheless be an incidence.
  • the perforator 30 which is thinner and faster than the bomb body can penetrate the wall even for low angles of incidence, the bomb body benefiting from the orifice created by the perforator and thereby having a range of increased incidence.
  • the invention has been described for the realization of a penetration bomb inside an infrastructure. It can, however, apply to other types of projectiles intended to penetrate into infrastructure through a thick wall.
  • the invention makes it possible in particular to pass through concrete walls with a high modulus of rupture to compression, which can reach, for example, 200 MPa.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Drilling And Exploitation, And Mining Machines And Methods (AREA)

Claims (11)

  1. Penetrationsfähiges Geschoss (10), das Folgendes umfasst:
    - einen Körper (21);
    - eine innere Röhre (22), in der sich ein perforierendes Geschoss (30) befindet, das wenigstens einen mit einer pyrotechnischen Ladung (33) versehenen Körper (31) umfasst, wobei der Körper (31) des perforierenden Geschosses durch Zünden eines Treibkörpers (301) aus der Röhre ausgestoßen wird;
    - ein System (28, 306, 307) zum Steuern des Zündens des Treibkörpers (301) des perforierenden Geschosses (30) vor dem Auftreffen des penetrationsfähiges Geschosses (10) auf ein Ziel (42), wobei das penetrationsfähige Geschoss (10) eine pyrotechnische Ladung (23) zwischen seinem Körper (21) und der Röhre (22) aufweist;
    dadurch gekennzeichnet, dass der Treibkörper (301) in dem perforierenden Geschoss enthalten ist, wobei die Röhre (22) wenigstens zwei Sektionen mit unterschiedlichen Kalibern umfasst, wobei die Sektion mit dem kleineren Kaliber auf den Ausgang der Röhre (22) gerichtet ist, wobei der Körper (21) des perforierenden Geschosses (30) an das Ausgangskaliber der Röhre angepasst ist, wobei sich der Treibkörper (301, 303) am Übergang (221) der zwei Sektionen beim Ausstoßen des Körpers (21) des perforierenden Geschosses verklemmt, wobei der Übergang zwischen den beiden Sektionen einen Kegel (221) bildet, so dass sich der Mantel (30) des Treibkörpers durch Reibung auf den Kegel aufschweißt.
  2. Geschoss nach Anspruch 1, dadurch gekennzeichnet, dass das perforierende Geschoss (30) ein System (36) umfasst, das seine Position im Innern des Ziels in Abhängigkeit von der Zeit bestimmt und die Detonation seiner pyrotechnischen Ladung (33) zu einem vorbestimmten Zeitpunkt auslöst.
  3. Geschoss nach Anspruch 2, dadurch gekennzeichnet, dass das System die Position des Perforators anhand seiner Charakteristiken von den Verlangsamungsniveaus im Material des Ziels und von seiner Geschwindigkeit am Auftreffpunkt auf dem Ziel ermittelt.
  4. Geschoss nach einem der vorherigen Ansprüche, dadurch gekennzeichnet, dass der Körper (31) des perforierenden Geschosses (30) mit Stiften am Mantel (303) des Treibkörpers (301) befestigt ist.
  5. Geschoss nach einem der vorherigen Ansprüche, dadurch gekennzeichnet, dass ein Zündrelais (34) im Innern der pyrotechnischen Ladung (33) des perforierenden Geschosses (30) vorgesehen ist.
  6. Geschoss nach Anspruch 5, dadurch gekennzeichnet, dass das perforierende Geschoss (30) einen Träger (35) aufweist, der den Raum hinter der pyrotechnischen Ladung (33) verschließt, wobei dieser Träger einen Schlagbolzen (39) aufweist, der sich gegenüber dem Zündrelais (34) befindet.
  7. Geschoss nach einem der Ansprüche 2 bis 6, dadurch gekennzeichnet, dass das perforierende Geschoss (30) einen Elektronikblock (36) umfasst, der das System zum Ermitteln der Position des Perforators im Ziel (42) enthält, wobei der Elektronikblock auch die Zündung der pyrotechnischen Ladung (33) steuert.
  8. Geschoss nach Anspruch 6 oder 7, dadurch gekennzeichnet, dass der Elektronikblock (36) des perforierenden Geschosses (30) an dem Träger (35) platziert ist.
  9. Geschoss nach einem der vorherigen Ansprüche, dadurch gekennzeichnet, dass das System, mit dem die Zündung des Treibkörpers (301) des perforierenden Geschosses (30) gesteuert werden kann, einen Elektronikblock (28) und wenigstens eine Zündpille (307) umfasst, wobei ein elektrisches Signal von dem Elektronikblock (28) über eine elektrische Verbindung (306) zu der Zündpille (307) gesendet wird.
  10. Geschoss nach Anspruch 9, dadurch gekennzeichnet, dass der Elektronikblock (28) eine torische Form hat und sich in einer Hülse (20) befindet, die den Körper (21) des Geschosses verschließt.
  11. Geschoss nach einem der vorherigen Ansprüche, dadurch gekennzeichnet, dass es rotationssymmetrisch ist und seine Symmetrieachse mit der Achse (20) der Röhre zusammenfällt.
EP05752648A 2004-06-08 2005-05-31 Geschoss, insbesondere eine infrastruktur durchschlagende bombe und wanddurchschlagverfahren für das geschoss Expired - Fee Related EP1766323B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0406184A FR2871226B1 (fr) 2004-06-08 2004-06-08 Projectile, notamment bombe de penetration anti- infrastructure et procede de penetration d'un tel projectile a travers une paroi
PCT/EP2005/052483 WO2005124270A1 (fr) 2004-06-08 2005-05-31 Projectile, notamment bombe de penetration anti-infrastructure et procede de penetration d'un tel projectile a travers une paroi

Publications (2)

Publication Number Publication Date
EP1766323A1 EP1766323A1 (de) 2007-03-28
EP1766323B1 true EP1766323B1 (de) 2012-04-11

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EP05752648A Expired - Fee Related EP1766323B1 (de) 2004-06-08 2005-05-31 Geschoss, insbesondere eine infrastruktur durchschlagende bombe und wanddurchschlagverfahren für das geschoss

Country Status (5)

Country Link
US (1) US8151712B2 (de)
EP (1) EP1766323B1 (de)
FR (1) FR2871226B1 (de)
IL (1) IL179902A (de)
WO (1) WO2005124270A1 (de)

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EP2496908B1 (de) * 2009-11-04 2013-09-11 Diehl BGT Defence GmbH & Co.KG Fliegerbombe
BG66449B1 (bg) * 2010-01-28 2014-09-30 Любомир ТОМОВ Аеродинамично стабилизирана муниция
RU2514014C2 (ru) * 2012-07-17 2014-04-27 Константин Сергеевич Колобов Бронебойный снаряд
IL221460A (en) * 2012-08-14 2016-11-30 Rafael Advanced Defense Systems Ltd Bullet acceleration
US11573068B1 (en) * 2020-06-19 2023-02-07 The United States Of America As Represented By The Secretary Of The Army Payload protection and deployment mechanism
US11867487B1 (en) * 2021-03-03 2024-01-09 Wach Llc System and method for aeronautical stabilization

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Also Published As

Publication number Publication date
US20080072782A1 (en) 2008-03-27
WO2005124270A1 (fr) 2005-12-29
FR2871226B1 (fr) 2006-08-18
IL179902A (en) 2013-08-29
US8151712B2 (en) 2012-04-10
EP1766323A1 (de) 2007-03-28
FR2871226A1 (fr) 2005-12-09
IL179902A0 (en) 2007-05-15

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