EP2226605B1 - Vorrichtung zur Lenkung eines Flugkörpers oder eines Projektils - Google Patents

Vorrichtung zur Lenkung eines Flugkörpers oder eines Projektils Download PDF

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Publication number
EP2226605B1
EP2226605B1 EP10002119A EP10002119A EP2226605B1 EP 2226605 B1 EP2226605 B1 EP 2226605B1 EP 10002119 A EP10002119 A EP 10002119A EP 10002119 A EP10002119 A EP 10002119A EP 2226605 B1 EP2226605 B1 EP 2226605B1
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EP
European Patent Office
Prior art keywords
projectile
piston
bore
missile
combustion chamber
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.)
Active
Application number
EP10002119A
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English (en)
French (fr)
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EP2226605A1 (de
Inventor
Fabrice Ciszek
Marc Comet
Frédéric Sourgen
Denis Spitzer
Christian Baras
Barbara Baschung
Claude Steinbach
Daniel Mura
Henri Moulard
Auguste Ritter
Christophe Bissel
Dominique Hassler
Friedrich Leopold
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.)
Institut Franco Allemand de Recherches de Saint Louis ISL
Original Assignee
Institut Franco Allemand de Recherches de Saint Louis ISL
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.)
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Publication of EP2226605A1 publication Critical patent/EP2226605A1/de
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Publication of EP2226605B1 publication Critical patent/EP2226605B1/de
Active 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
    • 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
    • F42B10/60—Steering arrangements
    • F42B10/66—Steering by varying intensity or direction of thrust
    • F42B10/661—Steering by varying intensity or direction of thrust using several transversally acting rocket motors, each motor containing an individual propellant charge, e.g. solid charge

Definitions

  • the invention relates to the field of provisions for improving the control of projectiles and more particularly to a device for controlling a missile and an associated missile.
  • the patent application US2005 / 0103925 which forms a starting point for the preamble of claim 1, describes a device for guiding a projectile comprising a combustion chamber closed by a cover attached to the projectile and containing a powder capable of igniting, as well as electrical means priming of this powder. Inflammation of the powder produces gases generating an increase in the pressure in the combustion chamber until the rupture of the fixation between the projectile and the lid and thus the expulsion of the lid.
  • Such a device has the disadvantage of producing a gaping hole in the projectile capable of modifying its trajectory and then requiring the use in cascade of the other guide means arranged in a ring.
  • One of the aims of the invention is to propose a piloting mode that can be used both for missiles and for small caliber projectiles, in particular of the order of 40 mm, and that introduces no lasting and continuous modification of the trajectory. missile.
  • the solution provided is a device for controlling a missile or projectile, for example of small caliber in particular of the order of 40 mm, having a main lateral face with a nose at one of its ends, this device comprising at least one cavity constituting a combustion chamber and filled, at least partially, with an explosive powder, and means for initiating this explosive powder, characterized in that the explosive powder comprises nanothermites, these nanothermites being preferably associated with a conventional fuel such for example propellant or being of the gas generating type.
  • Thermites are energetic materials composed of a metal oxide associated with a reducing metal.
  • the combustion of thermites is carried out according to a mechanism of transfer of oxygen, from the oxide towards the metal leading to the formation of liquid or solid species. This explains that unlike explosives, thermites burn quickly without detonating.
  • Conventional thermites are characterized by high density, high insensitivity to thermal and mechanical stresses and relatively low combustion rates.
  • nanothermites new generation thermites
  • new generation thermites can be easily combusted, for example under the effect a detonated wire with a combustion rate much higher than that of conventional thermites and sufficient to allow the direct or indirect guidance of a projectile
  • nanothermites also called superthermites or metastable interstitial composites are for example described in the article of Marc Cornet and Denis Spitzer entitled "Classical thermites with metastable interstitial composites" chemical news - July 2006 - n ° 299 .
  • the shaping of the nanothermite powders is carried out by simple compression and does not require a binder.
  • the compressed objects have a remarkable cohesion, their apparent density can be adjusted in a very wide range by varying the intensity of the compression.
  • the gas- generating nanothermites constitute a new concept particularly suited to propulsive driving because they contain, in varying proportions, nanoparticles of explosive, which makes it possible to adjust the pressure produced by the combustion.
  • the gas generation makes it possible to eject the liquid or solid material formed by the combustion of the thermite and to increase the combustion rate in a semi-confined medium.
  • the decomposition of the nanothermites generating gas in a confined environment is carried out by deflagration. The transition to a detonation regime can not occur as long as the explosive nanoparticles are discontinuously distributed in the material.
  • Gas generating nanothermites can be prepared by physically mixing a nanocomposite material with commercial aluminum nanoparticles (eg Al 50P, Novacentrix).
  • the physical mixture is typically made by simultaneously dispersing the two products in a non-dissolving liquid phase such as hexane.
  • a second type of nanocomposite material can be prepared by infiltrating the porosity of manganese dioxide (IV) by varying proportions of hexogen as described by M. Cornet, V. Pichot, D. Spitzer, B. Siegert. F. Ciszek, N. Piazzon, P. Gibot, Elaboration and characterization of manganese oxide (MnO2) based "green" nanothermites, 39th International Annual Conference of ICT, Düsseldorf, Germany, June 24-27, 2008, V 38-1 to V 38-B .
  • a device comprises a nozzle disposed in the extension of said combustion chamber and, preferably, opening near the main lateral face of the projectile or missile.
  • a device comprises a piston having a rod and a head and able to slide inside a bore and one of the surfaces defining the combustion chamber. is constituted by the head of the piston or by an element disposed opposite this head, a rudder being advantageously disposed at the free end of the piston rod and, preferably, the device comprises means. possibly reversible locking the position of the piston within said bore, which may, for example be constituted by a retractable stop.
  • a device comprises two cylindrical elements disposed respectively on one side and on the other side of the piston head and each comprising at least one cavity, and preferably at least two, constituting a combustion chamber and having a shutter at one of its ends, for example constituted by a membrane.
  • said powder initiation means comprise control means 18, a power supply 5 and a platinum wire.
  • the invention also relates to a projectile or a missile comprising a guiding device according to the invention.
  • the figure 1 shows a general diagram of a device according to a first embodiment of the invention.
  • the cavity 10a formed by the first bore 10 and the nozzle 14 constitutes a combustion chamber. It is wholly or partially filled, during the production of the guiding device, with powder 10b comprising nanothermites, and this, depending on the desired deviation of the trajectory.
  • control means 18, the power supply 5 and the platinum wire B constitute means for initiating said powder comprising nanothermites.
  • This guiding device is thus a micropropellant.
  • the percentage of nanothermites dispersed in the powder inserted into the combustion chamber, the nature of these nanothermites, their confinement rate, their compression ratio and the dimensions of the gas ejector nozzle are chosen according to the initiation time, the duration of the action and the intensity of the desired action.
  • the gas generating nanothermite is placed in a micro-combustion chamber whose size relative to the nanothermite (filling ratio) corresponds to the selected confinement. Its value can be close to 1.
  • the nozzle At the top of the micro-propeller is placed the nozzle through which the gas is ejected.
  • the nozzle may be a simple narrowing section, a frustoconical nozzle or a profiled nozzle.
  • the platinum wire is connected to the connector which seals between the combustion chamber and the amplification means.
  • the power supply here consists of two LiPo type batteries embedded in the projectile.
  • the micro-propeller can be placed at any convenient place between the front and the rear of the projectile, and several thrusters can be embarked.
  • the figure 2 shows a more detailed diagram of a section of the assembly formed by the plug 16, the cylindrical element 9, the nozzle 14 and its arrangement within the projectile.
  • the plug 16 has a thread 27 on its side face 28 adapted to cooperate with the tapping 22 so as to allow its attachment to the projectile.
  • the nozzle 14 has a thread 29 on its side face 30 adapted to cooperate with the thread 21 so as to allow its attachment to the projectile.
  • the cylindrical element 9 is inserted between the plug 16 and the nozzle 14 so that the connector placed in said second transverse bore 11 of the element 9 is opposite the third bore 26 of the projective, thus making it possible to connect the amplifier 6 to the connector 7.
  • the cylindrical element is held in position by the projectile at its lateral face 12 and respectively by the plug and the nozzle via its respective transverse faces 15 and 13.
  • This difference in potential generates a heating of the platinum wire which in turn produces the explosion of the nanothermite powder.
  • This explosion occurs in a very short time and generates, almost in real time, gases that escape from the high-speed guide device via the nozzle 14.
  • the escape of these gases from the projectile in an extremely short time produces a variation the trajectory of the projectile in a direction opposite to that of the escape of gases.
  • This variation in direction is a function of the gas flow rate released, in particular the percentage of nanothermites dispersed in the powder inserted into the combustion chamber, the nature of these nanothermites, their confinement rate, their compression ratio and the dimensions of the ejector gas nozzle 14.
  • the figure 3 shows a portion of the guide device according to this first embodiment of the invention but disposed at a rear level of a projectile.
  • the control, power and amplification means are not shown to improve the clarity of the figure.
  • FIGS. 4a and 4b show a device for controlling a missile or a projectile according to a second embodiment of the invention and comprising an active steering wheel in the active position on the figure 4a and returned to the passive position on the figure 4b .
  • This projectile portion 50 comprises a first half-opening radial bore 51 and a second collinear radial bore 52 and of smaller diameter than the first and connecting the bottom 53 of the first bore to a groove 54 formed on the peripheral surface of the first bore. projectile and intended to accommodate a rudder 56 secured to the projectile by a movable link 85.
  • This projectile portion 50 also includes a first axial bore 56 situated at the bottom 53 of the first radial bore 51 and a second axial bore 57 opening into the upper portion of the first bore 51.
  • Das control means 60, a power supply 61 and means 62 for amplifying the voltage generated by the power supply are inserted into the first axial bore 56.
  • This cylindrical element 63 also has a transverse bore 66 at its second tubular portion 65 and located opposite the first axial bore 56.
  • a connector 67, disposed in the transverse bore 66, is electrically connected on the one hand to the amplification means 62 and on the other hand to a platinum wire 68 resting partly on the bottom 69 of the first tubular portion 64.
  • a stop 70 secured to an electric actuator 71 controlled by the control means 60 and supplied by the supply means 61 is disposed in the second axial bore 57.
  • This cylindrical element 63 has a bore 80 disposed opposite the exhaust duct 58.
  • a piston 72 comprises a head 73 of diameter substantially equal to the internal diameter D1 of the first bore of the cylindrical element 63 and a rod 74 of diameter substantially equal to the diameter D2.
  • the head 73 is located inside the first tubular portion 64 of the cylindrical member 63 while the rod 74 is partly inside this first portion 64, partly inside the second tubular portion 65 and partly inside the second radial bore 52. Its free end is integral with a hinge 75 fixed on the rudder 55.
  • the upper portion 76 of the first radial bore 51 comprises a tapping 77 and a metal plug 78 having a thread adapted to cooperate with said tapping and disposed on the cylindrical piece 63 so as to plug the corresponding end of said first tubular portion 84.
  • the cavity 81 delimited by the inside of the cylindrical piece 63, the head 73 of the piston 72, the bottom 69 of the first tubular portion 64 of this cylindrical piece 63 is partially filled with powder 79 at least partially containing nanothermites and constitutes a combustion chamber.
  • the control means 60, the power supply 61 and the platinum wire 68 constitute means for initiating said powder comprising nanothermites.
  • the shot produces a gyration of the projectile, this gyration being sufficient, by the centrifugal force exerted on the piston 72, to deploy the rudder 55 out of the groove 54 as shown on FIG. figure 4a .
  • control means 60 For example from an external control signal, control the generation, by the power supply 61, of a potential difference which is then amplified by the means of control. amplifier 62 and applied to the ends of the platinum wire 68 via the connector 67.
  • This potential difference generates a heating of the platinum wire which in turn produces the explosion of the nanothermite powder 79.
  • This explosion occurs in a very short time and generates, almost in real time, gases that exert pressure on the piston head which moves almost instantaneously towards the plug 78 to reach the position of the piston. figure 4b .
  • the generated gases then escape through the exhaust duct while the control means 60 control the deployment of the actuator 71 and therefore the output of the stop 70 of the second axial bore 57, a portion of this stop 70 being located then inside the first tubular portion 64 of the cylindrical element 63.
  • this stop 70 prevents the rudder 55 from emerging by the centrifugal force due to the projectile's gyration as long as another control signal does not control the retraction of the actuator 71.
  • This device therefore acts as a single-acting actuator operating only once.
  • the figures 5a and 5b show a device for controlling a missile or a projectile according to a third embodiment of the invention and comprising a double-acting actuator that can be used several times.
  • FIGS. 1-10 show the rear part 90 of a projectile which has a radial bore 91 of diameter D3 in its Intermediate part 92 and of larger diameter D4 at the second and third parts 93 and 94 which are respectively on one side and on the other side of the middle part 92 and which each open at the side surface 95 of the projectile.
  • the difference in diameter between the intermediate portion 92 and the second and third parts 93 and 94 forms reference shoulders respectively 100 and 101.
  • the intermediate portion 92 has two axial bores 96 and 97 located respectively close to said second and third parts 93 and 94. It also comprises an axial conduit 123 for discharging gases.
  • a stop 111 associated with a spring 110 are disposed inside each of the two axial bores 96 and 97, so that only a portion of spherical shape of the abutment 111 protrudes inside the intermediate portion 92.
  • cylindrical elements 98 and 99 of diameter substantially equal to D4 are respectively disposed against the shoulders 100 and 101 and so that their axis of symmetry and that of the radial bore 91 are coaxial.
  • One of these cylindrical elements comprises an axial bore 102 while the two each comprise at least one cavity 103 opening at said intermediate portion 92 and connected to the part in which the cylindrical element in question is located, by a channel of small diameter 104.
  • Each of the cavities is associated with a platinum wire 105 resting partly on the bottom of the cavity and connected, via said channel 104, to a connector 106 which is itself connected to means 107 for amplifying voltage, means for electrical power supply 108 and control means 109.
  • a connector 106 which is itself connected to means 107 for amplifying voltage, means for electrical power supply 108 and control means 109.
  • these cavities 103 are completely or partially filled with compacted powder comprising at least partly nanothermites and these cavities are closed by a membrane 130 adapted to maintain the powder in position before use.
  • Each of these cavities 103 constitutes a combustion chamber.
  • a rudder 112 is associated with the previously described elements.
  • One of its ends 113 is secured to the projectile via a movable link 114 and has a hinge 115 in its intermediate portion, this hinge being connected to an end 116 of the rod 117 of a piston 118.
  • the head 119 of the piston 118 is disposed within said intermediate portion 92 and slidable therein. This head 119 comprises in the median portion of its peripheral face 120 a hemispherical throat 121 of diameter slightly greater than that of the emerging end of the stop and adapted to cooperate with the latter to maintain the piston in a stable position.
  • the rod 117 of the piston 118 has a diameter substantially equal to that of the axial bore 102 formed in one of the cylindrical element and can slide inside this bore 102.
  • the control means 108, the power supply 109 and the platinum wire 105 constitute means for initiating said powder comprising nanothermites.
  • the operation of this device is as follows;
  • the rudder 112 When the projectile is fired, the rudder 112 is in the passive position retracted inside the groove 122 made on the surface of the projectile as shown in FIG. figure 5b .
  • the shot produces a gyration of the projectile, this gyration exerting a force on the piston lower than that of the stop on the head 119 of the piston 118. Therefore, after firing, the rudder remains in the passive position.
  • control means 109 for example from an external control signal, control the generation, by the power supply 108, of a potential difference which is then amplified by the amplification means 107 and applied, via the connector 106, to the ends of one of the platinum wires 105 situated partially in one of the cavities 103 of the cylindrical element 99.
  • This potential difference generates a heating platinum wire 105 which in turn produces the explosion of the powder containing nanothermites.
  • This explosion occurs in a very short time and generates, almost in real time gases that detonate said membrane and exert a force on the head 119 of the piston 118 greater than that of the abutment 111, the piston head then moving almost instantaneously towards the other cylindrical member 98 to be pressed against it.
  • the rudder 112 is then substantially in the position of the figure 5a .
  • the combustion gases escaping through the exhaust pipe 123, the pressure exerted on the piston head decreases. Meanwhile, the hydrodynamic pressure exerted on the rudder tends to push the piston towards the cylindrical element 99.
  • the abutment 111 enters the hemispherical groove of the piston head and then blocks its movement.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Radar Systems Or Details Thereof (AREA)
  • Feeding, Discharge, Calcimining, Fusing, And Gas-Generation Devices (AREA)
  • Air Bags (AREA)
  • Portable Nailing Machines And Staplers (AREA)
  • Actuator (AREA)
  • Manipulator (AREA)

Claims (11)

  1. Vorrichtung zur Steuerung eines beispielsweise kleinkalibrigen Flugkörpers bzw. Geschosses, insbesondere in einem Kaliber von ca. 40 mm, mit einer seitlichen Hauptfläche und einer an einem der Enden angeordneten Geschossnase, wobei diese Vorrichtung mindestens einen Hohlraum (10a, 81, 103) bestehend aus einer Brennkammer aufweist, in der sich zumindest teilweise Sprengstoff (10b, 79) und Mittel (18, 5, 8, 60, 61, 68, 108, 109, 105) zur Sprengstoffzündung befinden, dadurch gekennzeichnet, dass Nanothermite als Sprengstoff (10b, 79) eingesetzt werden.
  2. Vorrichtung nach Anspruch 1, dadurch gekennzeichnet, dass sie eine Düse (14) in Verlängerung der Brennkammer (10a, 81, 103) besitzt.
  3. Vorrichtung nach Anspruch 2, dadurch gekennzeichnet, dass die Düse zur seitlichen Hauptfläche (3) des Flugkörpers bzw. Geschosses führt.
  4. Vorrichtung nach Anspruch 1, dadurch gekennzeichnet, dass sie einen Kolben (72, 118) mit einer Stange und einem Kopfende (73, 119) zwecks Führung in einer Bohrung (64, 91) aufweist, und dass eine der Grenzflächen der Brennkammer aus dem Kopfende (73, 119) zweck Führung in einer Bohrung (64, 91) besteht und dass eine der Grenzflächen der Brennkammer aus dem Kopfende (73, 119) des Kolbens (72, 118) oder aus einem Element (130) gegenüber dem Kopfende (73, 119) besteht.
  5. Vorrichtung nach Anspruch 4, dadurch gekennzeichnet, dass sie ein Ruder (55, 112) am freien Ende der Kolbenstange (74, 117) besitzt.
  6. Vorrichtung nach einem beliebigen der vorhergehenden Ansprüche 4 oder 5, dadurch gekennzeichnet, dass sie zwei zylindrische Elemente (98, 99) beidseitig am Kolbenkopf (119) mit jeweils mindestens einem Hohlraum (103), vorzugsweise mindestens zwei Hohlräumen, besitzt, der aus einer Brennkammer besteht und an einem der Enden ein Verschluss-System (130), beispielsweise in Form einer Membran, aufweist.
  7. Vorrichtung nach einem beliebigen der vorhergehenden Ansprüche 4 bis 6, dadurch gekennzeichnet, dass sie Mittel (71, 72, 110, 111) zur Verriegelung der Kolbenstellung in der Bohrung aufweisen.
  8. Vorrichtung nach Anspruch 7, dadurch gekennzeichnet, dass die Mittel zur Blockierung des Kolbens (71, 72, 110, 111) reversibel sind.
  9. Vorrichtung nach Anspruch 8, dadurch gekennzeichnet, dass die Mittel zur Blockierung des Kolbens einen einschiebbaren Anschlag (72, 111) aufweisen.
  10. Vorrichtung nach einem beliebigen der vorhergehenden Ansprüche 1 bis 9, dadurch gekennzeichnet, dass die Mittel zur Sprengstoffzündung aus Antriebsmitteln (18, 60, 108) 18, einem Netzgerät (5, 61, 109) 5 und einem Platindraht (8, 68, 105) bestehen.
  11. Geschoss oder Flugkörper, das/der eine Vorrichtung nach einem beliebigen der vorhergehenden Ansprüche 1 bis 10 besitzt.
EP10002119A 2009-03-06 2010-03-02 Vorrichtung zur Lenkung eines Flugkörpers oder eines Projektils Active EP2226605B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0901037A FR2942871B1 (fr) 2009-03-06 2009-03-06 Dispositif de pilotage d'un missile ou d'un projectile

Publications (2)

Publication Number Publication Date
EP2226605A1 EP2226605A1 (de) 2010-09-08
EP2226605B1 true EP2226605B1 (de) 2012-01-18

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US (1) US8716640B2 (de)
EP (1) EP2226605B1 (de)
FR (1) FR2942871B1 (de)
IL (1) IL204296A (de)
RU (1) RU2526407C2 (de)

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Also Published As

Publication number Publication date
EP2226605A1 (de) 2010-09-08
US20110068220A1 (en) 2011-03-24
FR2942871B1 (fr) 2011-04-01
RU2526407C2 (ru) 2014-08-20
IL204296A (en) 2014-01-30
FR2942871A1 (fr) 2010-09-10
US8716640B2 (en) 2014-05-06
RU2010108247A (ru) 2011-09-10

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