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

• Projectile in particular anti-infrastructure penetration bomb and method of penetrating such a projectile through a wall
• the present invention relates to a penetrating projectile, in particular an anti-infrastructure penetration bomb. It is particularly applicable for crossing very thick walls made of non-metallic material such as concrete for example.
• the invention also relates to a method of penetration applied to the above-mentioned projectile.
• a bomb is carried by a rocket.
• a rocket basically has three parts. At the front it contains its guidance system and at the rear its engine for propulsion. Between these two elements lies the military charge, in other words essentially the bomb.
• the military charge in other words essentially the bomb.
• the dimensions and weight of the rockets are fixed as well as their speed. It follows that the volume, weight and speed of the bomb are also frozen, whatever the performance required. In particular, the kinetic energy cannot be increased in order to obtain new, even more advanced performances.
• One solution could consist in strengthening the structural strength of the body of the bomb, for example by tripling its thickness. Another solution could also use a dense material with significant reduction in diameter. These solutions nevertheless have drawbacks.
• the first solution notably prevents making a general purpose bomb body against surface or buried threats.
• the second solution leads to a very expensive bomb body and in fact to a very ineffective bomb because the mass of on-board explosive is then reduced by more than half compared to a normal steel body.
• An object of the invention is in particular to allow a bomb of relatively low structural mechanical strength to pass through increasingly thick or resistant walls.
• the subject of the invention is a penetrating projectile comprising: - an inner tube in which is placed a perforating projectile comprising at least one body equipped with a pyrotechnic charge and a propellant body, the body of the perforating projectile being ejected out the tube by firing the propellant body; a system for controlling the firing of the propellant body before the impact of the projectile penetrating a target.
• the perforating 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 instant.
• 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 calibers, the smaller caliber section being oriented towards the exit of the tube, the body of the perforating projectile being adapted to the exit caliber of the tube, the propellant body wedging at the transition of the two sections during the ejection of the body of the perforating projectile.
• the transition between the two sections for example forms a cone so that the envelope of the propellant body is welded by friction on the cone.
• the body of the perforating projectile can be fixed to the casing of the propellant body by pins.
• the projectile comprises in particular a pyrotechnic charge placed between its body and the tube containing the perforating projectile.
• the invention also relates to a method of penetrating a projectile according to the preceding characteristics, inside a target, in particular a concrete wall.
• a target in particular a concrete wall.
• the perforating projectile is ejected from the tube by firing its propellant body when the projectile is located at a given distance d from the target; the perforating projectile penetrating before the projectile into the target, the perforating projectile detonates inside the target by firing its pyrotechnic charge to create an orifice for passage to the body of the projectile.
• the perforating projectile detonates for example in the middle of the target.
• the main advantages of the invention are that it can be implemented at constant volume, mass and speed compared to current solutions, that it makes it possible to increase the angle of arrival angle of arrival of the body. a bomb on a wall, and that it increases the charge of on-board explosive.
• FIG. 1 an example of rocket structure
• FIG. 2 a possible embodiment of a projectile according to the invention
• - Figure 3 an embodiment of a perforating projectile contained inside the previous projectile
• FIG. 4 the situation of the rocket containing a projectile according to the invention, when the rocket is launched and when the projectile is ejected from the rocket
• FIGS. 5a to 5f an illustration of the penetration method according to the invention
• FIG. 6 the propellant body of the perforating projectile stuck at the exit of the projectile preventing debris from penetrating inside
• FIG. 7 an illustration of the wide range of incidence of a projectile according to the invention on a wall.
• FIG. 1 represents the structure of a rocket 1. As indicated above, it essentially consists of three parts 2, 3, 4. The front of the rocket comprises the guide means 2 and the rear comprises the propulsion means 3. Between the two is located the penetrating projectile 4, for example a military charge such as a bomb.
• the fact that the rocket envelope is frozen as well as the overall mass means that the volume and the mass devoted to the penetrating projectile 4 are also fixed, insofar as it is hardly possible moreover to reduce the allocated parts the guide means and the propulsion means.
• the structural mechanical strength of the penetrating body cannot therefore be appreciably increased.
• the speed of the penetrating body is fixed by the speed of the rocket 1.
• FIG. 2 shows, in a cross-sectional view, an embodiment of a projectile according to the invention.
• the projectile is a bomb.
• FIG. 2 therefore presents a bomb 10 which can be contained in the space allocated to the penetrating body 4 in the rocket of FIG. 1 while exhibiting great penetration performance.
• the bomb has a body 21 inside which a tube 22 is placed.
• the tube 22 comprises for example a wedge cone 221 making the transition between a first section 222 of tube and an outlet section 223 of smaller caliber, oriented towards the front of the bomb body.
• the bomb body 21 being symmetrical in revolution, the axis 20 of the tube 22 merges, for example, with the axis of the body 21.
• the pyrotechnic charge 23 is placed inside the bomb body 21 around the tube 22.
• the charge 23 is contained inside a sheath 24, placed between the interior face of the bomb body 21 and the tube 22.
• a priming relay 25, for example of toric shape, located inside the charge pyrotechnic 23 enables the firing of the latter.
• the rear of the pyrotechnic charge 23 and closed by a wall 27 occupying the space between the interior face of the bomb body and the tube.
• 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 unit 28, for example toroidal, also contained in the base 20.
• a shock attenuator 29 is placed at the front of the pyrotechnic charge, wedged between the sheath 24 and the interior of the bomb body 21.
• a hyperpunching perforator projectile 30 with pyrotechnic charge Inside the tube is arranged a hyperpunching perforator projectile 30 with pyrotechnic charge.
• This perforator allows in particular the prior creation of a conduit in the wall to be crossed. To this end, when approaching the wall, the perforator comes out of the tube, thanks to its own propulsion means, with a speed significantly higher than that of the bomb body 21. Then it detonates once introduced inside the wall.
• FIG. 3 shows, in a cross section, a possible embodiment of the perforating projectile 30.
• This projectile has a co ⁇ s 31.
• This body has for example at the front a .point 32 to facilitate penetration.
• a pyrotechnic charge 33 Inside the body is placed a pyrotechnic charge 33.
• a priming relay 34 is placed inside the charge 33.
• a support 35 closes the space behind the pyrotechnic charge 33.
• This support 35 comprises a striker 39 located opposite the priming relay 34 to achieve percussion priming which causes the ignition of the pyrotechnic charge 33.
• the striker 39 is controlled by an electronic unit 36 also placed in the support 35.
• a cover 37 closes the back of the body.
• a propellant co 30s 301 is placed at the rear of the body of the projectile 31.
• This propellant co ⁇ s 301 is held in the body of the projectile by means of pins 38.
• the outer wall of the propellant body 301 extends inside a part of the wall of the projectile body itself extending beyond the cover 37.
• the pins pass through the two walls opposite one another by means of holes provided for this purpose.
• the propellant co comportes has a charge inside its casing 303 pyrotechnic 302.
• This charge 302 is for example composed of plastic bars.
• a cap 304 closes the rear of the propellant.
• the plug 304 comes for example to screw on the casing 303 of the propellant co ⁇ s.
• One or more lids 305 are pierced in the plug to allow a control link 306 to pass. This link is for example connected to an ignition pad 307 placed in contact with the pyrotechnic charge 302.
• Wedging means 308 are for example placed between the plug 304 and the loading of the propellant co 30s 302.
• the firing of the propellant co ⁇ s 301 causes the ejector projectile 30 to eject from the body tube 31.
• FIG. 4 shows the rocket 1 in two places on its trajectory towards a concrete wall 42 in a system of x, y axes.
• the positions relative to the self 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 xi - x 0 is for example of 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 the approach and crossing phase of the wall 42.
• FIG. 5a shows the moment of ignition of the charge 302 of the propellant body of the perforator 30 at the immediate approach of the target, in this case the wall 42.
• the bomb is at a distance d less than distance xi - xn.
• This distance d is for example of the order of 10 meters. Possibly the distances Xi - xo and d can be substantially the same.
• the perforator 30 is therefore ejected from the bomb body 21 with a very high speed relative to this cost. For example, if the bomb moves at a speed of the order of 300 m / s, the perforator can go out with a relative speed of this order.
• a timer placed for example in the electronic unit 28 of the body of the bomb can for example calculate a delay between the instant of ejection of the body of the bomb from the rocket and the instant of priming of the propellant body of the perforator, the instant of ejection of the cost of the bomb being itself determined for example by the guide means 2 located at the front of the rocket 1.
• the control of the electronic unit 28 to the propellant body of the perforator is done for example by means of an electrical connection 306.
• An electrical signal activates for example the ignition pad 307 which triggers the ignition of the pyrotechnic charge 302.
• the figure 5b shows 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 unit make up a system for controlling the firing of the propellant body 301 before the impact of the bomb 10 on a target, the wall 42 in the example of FIGS. 5a to 5f. Another type of system could be used.
• FIG. 5c shows the penetration of the perforator 30 into the wall 42.
• the relative speed of the latter relative to the bomb body allows it to impact the wall 42 first.
• FIG. 5d shows 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 at inside the wall as a function of time and which triggers the detonation of its pyrotechnic charge at a predetermined instant.
• This system is for example contained in the electronic unit 36.
• the detonation is caused by the ignition of the pyrotechnic charge 33.
• the invention advantageously uses the fact that the concretes do not hold the tensile stress. This therefore allows them to be relatively easily destructured 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.
• a table is for example stored in the processor. This table contains the characteristics of the deceleration levels of an object entering a material. It can take into account several types of materials including of course concrete and even different types of concrete. Thus knowing the initial speed of the perforator 30 at the entry into the wall, at the point of impact, and the deceleration curve of the material of the latter, it is possible to know the penetration distance inside the wall in function and therefore its position.
• An impact intelligence module of the “caiman” type is for example used.
• FIG. 5e shows the penetration of the bomb shell 21 into the orifice 51 created by the perforator.
• the amount of charge conveyed by the perforator 30 can be calculated to obtain an orifice adapted to the caliber of the bomb cost 21, that is to say ie in practice close to the caliber of the bomb cost.
• 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 thereby allows a bomb of relatively low structural mechanical strength to pass through increasingly thick walls or resistant.
• By reducing the resistance of the mechanical structure of the bomb body it is then possible to increase the mass of on-board explosive, hence a stronger destructive power after crossing the wall.
• FIG. 5f presents the bomb cost 21 after crossing the wall 42.
• the bomb body can for example detonate by firing its pyrotechnic charge 23.
• FIG. 6 highlights an advantage provided by the wedge cone 221 of the inner tube to the bomb shell. More particularly, FIG. 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 wedging the latter at the level of the wedging cone 221.
• the casing 303 the diameter is greater than the gauge of the outlet section of the tube, under the effect of speed, comes to weld by friction on the internal cone of the tube. This avoids any potential intrusion of rubble into the shell of the bomb.
• the maintenance of the propellant body is reinforced by the confinement within the tube of all of the propellant gases.
• the envelope 303 remains welded to the tube while the shell 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 propellant body by shearing of the pins 38 which fix the two bodies together.
• the casing of the propellant co ⁇ s therefore forms a protective wall. Indeed, as has just been indicated previously, it thus prevents any intrusion of rubble or debris 52 inside the bomb body during the phase of penetration of the latter into the wall. Such debris, generated in particular during the detonation of the perforator 30 inside the wall as illustrated in FIG. 5 e , could indeed cause parasitic explosions. Furthermore, the resistance of the wall to external intrusions, in addition to the effect of friction welding, is reinforced by the internal pressure generated by the combustion gases in the tube 22. In other words, the function d sealing provided to the propellant body makes it possible to conserve the combustion gases within the tube which, by their thrust, reinforce the resistance of the weld.
• Figure 7 illustrates another advantage of the invention.
• this figure shows that the invention makes it possible to increase the angle of incidence angle of arrival of the bomb cost 21 on a wall 71.
• This entry face 73 in particular avoids the ricochets of the bomb body on the wall when the angle of incidence ⁇ of its speed vector on the wall is too small. If this angle ⁇ is still much too small there will nevertheless be an impact.
• the perforator 30 which is thinner and faster than the bomb cost can penetrate the wall even for small angles of incidence, the bomb body benefiting from the orifice created by the perforator and therefore having a range of expanded incidence.
• the invention has been described for the production of a penetration bomb inside an infrastructure. It can nevertheless be applied to other types of projectiles intended to penetrate an infrastructure by crossing a thick wall.
• the invention makes it possible in particular to pass through concrete walls with a high modulus of rupture in 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)

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• 2004
  • 2004-06-08 FR FR0406184A patent/FR2871226B1/fr not_active Expired - Lifetime
• 2005
  • 2005-05-31 US US11/628,859 patent/US8151712B2/en not_active Expired - Fee Related
  • 2005-05-31 WO PCT/EP2005/052483 patent/WO2005124270A1/fr active Application Filing
  • 2005-05-31 EP EP05752648A patent/EP1766323B1/de not_active Ceased
• 2006
  • 2006-12-07 IL IL179902A patent/IL179902A/en not_active IP Right Cessation

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