EP2082183A1 - Stabilized projectile used over a trajectory, particularly decoy - Google Patents

Stabilized projectile used over a trajectory, particularly decoy

Info

Publication number
EP2082183A1
EP2082183A1 EP07820558A EP07820558A EP2082183A1 EP 2082183 A1 EP2082183 A1 EP 2082183A1 EP 07820558 A EP07820558 A EP 07820558A EP 07820558 A EP07820558 A EP 07820558A EP 2082183 A1 EP2082183 A1 EP 2082183A1
Authority
EP
European Patent Office
Prior art keywords
aerodynamic
initiation
active element
trajectory
ammunition
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.)
Withdrawn
Application number
EP07820558A
Other languages
German (de)
French (fr)
Inventor
Marc Pignol
Olivier Estibals
Cyril Montacq
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.)
Etienne LaCroix Tous Artifices SA
Original Assignee
Etienne LaCroix Tous Artifices SA
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 Etienne LaCroix Tous Artifices SA filed Critical Etienne LaCroix Tous Artifices SA
Publication of EP2082183A1 publication Critical patent/EP2082183A1/en
Withdrawn legal-status Critical Current

Links

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
    • F42B10/02—Stabilising arrangements
    • F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
    • F42B10/18—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel using a longitudinally slidable support member
    • 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
    • F42B12/70—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 for dispensing radar chaff or infrared material
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C15/00—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges
    • F42C15/20—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein a securing-pin or latch is removed to arm the fuze, e.g. removed from the firing-pin
    • F42C15/21—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein a securing-pin or latch is removed to arm the fuze, e.g. removed from the firing-pin using spring action
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C15/00—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges
    • F42C15/34—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein the safety or arming action is effected by a blocking-member in the pyrotechnic or explosive train between primer and main charge

Definitions

  • the present invention relates to the field of devices comprising a stabilized projectile designed to generate a technical effect on trajectory.
  • the present invention finds in particular, but not exclusively, application in the field of decoys. It applies in particular to the protection by infrared and / or electromagnetic lures of aircraft of all types (weapon aircraft, transport aircraft, helicopters or civil aircraft).
  • the objective of the present invention is to further improve their efficiency by controlling their trajectory, in order to allow a maximum flight time of the lure in the vicinity of the aircraft to be protected.
  • the present invention aims to provide a new device that improves the efficiency of the device while preserving the environmental safety of the device implemented.
  • a device comprising an active element, for example a composition charge capable of emitting in the infrared range or an electromagnetic decoy, adapted to generate a controlled technical effect on a trajectory, means aerodynamic drag reduction system, deployable axially between a retracted position of storage rest and an operational deployed position on the trajectory and security means interposed between an initiation means and the element active, to prohibit the initiation of the latter before the deployment of aerodynamic means.
  • an active element for example a composition charge capable of emitting in the infrared range or an electromagnetic decoy, adapted to generate a controlled technical effect on a trajectory
  • means aerodynamic drag reduction system deployable axially between a retracted position of storage rest and an operational deployed position on the trajectory and security means interposed between an initiation means and the element active, to prohibit the initiation of the latter before the deployment of aerodynamic means.
  • the present invention ensures optimum efficiency. Indeed, by ensuring that the active element is implemented before deployment of the aerodynamic means, the present invention ensures an optimal operational time for the active element.
  • the present invention prohibits an implementation of the active element in storage position and therefore provides environmental protection, particularly in the context of a setting. implemented from an airplane.
  • FIG. 1 represents a view in longitudinal section of an assembly comprising a launcher and an ammunition according to a first embodiment of the present invention
  • FIG. 2 represents a similar view in longitudinal section of the same ammunition illustrated in FIG. 1 in its position at the outlet of the launcher tube;
  • FIG. 3 represents a view in longitudinal section of the same munition after deployment of the aerodynamic means
  • FIG. 4 represents a longitudinal sectional view of an assembly comprising a magazine and a plurality of ammunition, according to a second embodiment of the present invention, as referenced IV-IV in FIG. 5;
  • FIG. 5 represents a view from above of the same assembly according to the view shown V in FIG. 4;
  • FIG. 6 represents a longitudinal sectional view along the sectional plane of FIG. 4 of an individual ammunition,
  • FIGS. 7 and 8 show respectively front and rear views at the end of the same ammunition
  • FIG. 9 represents a view similar to FIG. 6 of the same ammunition after deployment of the aerodynamic means
  • FIG. 10 represents a view from above of the same munition in the orientation referenced V in FIG. 4;
  • FIG. 11 represents a side view of the same munition in a plane parallel to FIGS. 4, 6 and 9 and perpendicular to FIG. plane of Figure 10 as referenced XI in Figure 10,
  • FIG. 12 represents a longitudinal sectional view of the same munition along a sectional plane orthogonal to the plane of FIG. 6;
  • FIG. 13 represents a view of the same assembly along the section plane referenced XIII-XIII in FIG. , and
  • FIG. 14 represents a view from below of the same loader as referenced XIV in FIG. 13.
  • the launcher 100 comprises a bush or tube 110 centered on a 0-0 axis, and adapted to receive the projectile 200.
  • the bushing 110 is provided at one end with a base 120 which houses means capable of ensuring the ejection of the projectile 200 out of the socket 100, for example an ejection charge 124 associated with a primer 122.
  • the bushing 110 is provided with a plug 130 itself ejected during the ejection of the load 200 and provided with an annular peripheral seal 132.
  • the bushing 110 may have a circular section of revolution about the axis 0-0 or a polygonal section, for example square or rectangular.
  • the projectile 200 essentially comprises in combination a payload 210, a safety base 220 and aerodynamic means 230.
  • the projectile 200 is also centered on an axis AA which coincides, on storage, with the axis OO.
  • the payload 210 is formed of an annular roll of composition capable of emitting, during its combustion, a radiation in the infrared electromagnetic field.
  • the payload 210 could be replaced and / or supplemented by a load of electromagnetic decoys, for example reflective flakes.
  • the composition of a bread capable of emitting in the infrared range and / or such electromagnetic decoys, especially based on flakes, are well known to those skilled in the art and will not be described in detail by the following.
  • the base 220 comprises a set of channels 222 providing communication between the outer rear face 202 of the munition and the front face 212 of the payload 210, more specifically, a rod 240 centered on the axis AA and engaged in a channel central station of the payload 210.
  • the base 220 also houses a slide 224 placed in one of these channels 222 and mounted in translation in a generally radial direction relative to the axis AA between a security position illustrated on the Figure 1 in which the slide 224 defines an interruption in the transmission chain defined by the channels 222, by closing at least one of the segments thereof, and a release position illustrated in Figures 2 and 3 in which the drawer 224 completely frees the channels 222 between the outer rear face 202 of the munition and the front face 212 of the payload 210.
  • the slide 224 is biased in the extended position illustrated in Figures 2 and 3 by a spring 226 or equivalent elastic means placed in the bottom of one of the channels 222 receiving the slide 224 translation.
  • a spring 226 or equivalent elastic means placed in the bottom of one of the channels 222 receiving the slide 224 translation.
  • the radially outer end of the slide 224 rests on the inner face of the sleeve 210. This therefore prohibits any deployment of the drawer 224 and therefore any release of the channels 222 as the ammunition 200 is placed in the sleeve 110 of the launcher.
  • the aerodynamic means 230 may be the subject of many embodiments.
  • they comprise a set of fins or equivalent 232 carried by the rear end of a rectilinear mast 234 centered on the axis AA and mounted in translation in the cane 240.
  • means are provided to limit the deployment of the aerodynamic means 230 relative to the rod 240.
  • Such means may be formed for example of a localized enlargement 236 formed on the front end of the mast 234 and cooperating with a narrowing 204 formed in the vicinity the rear end of the munition, for example at a plate, preferably steel, provided on the rear end of the payload 210 and referenced 250 in the drawings.
  • the deployment of the aerodynamic means 230 between the retracted storage position illustrated in FIG. 1 and the deployed position shown in FIG. 3 is preferably obtained by the release of gas under pressure in the rod 240 by a pellet of pyrotechnic composition 238. for example black powder, placed in a housing formed on the front end of the mast 234.
  • a pellet of pyrotechnic composition 238 for example black powder
  • the front end of the mast 234 is advantageously provided with an annular seal 237 complementary to the inner section of the rod 240.
  • the composition 238 is itself initiated by a primer or equivalent 228 carried by the base 220 in one of the channels 222 upstream of the safety slide 224.
  • the composition 238 is implemented only after deployment safety slide 224, that is to say after exit of the ammunition out of the launcher 100.
  • the means according to the present invention shown in Figures 1 to 3 and previously described ensure that the payload 210 is not implemented before deployment of the aerodynamic means 230. Indeed, the safety slide 224 prohibits any transmission of fire to the payload 210 as long as the munition 200 is inside the launcher tube 100. When the ammunition leaves the safety drawer
  • the aerodynamic means 230 are automatically deployed by initiation of the load 238 and the initiation of the payload 210 is allowed.
  • the aerodynamic means specifically the fins 232 comprise four fins extending in radial planes with respect to the axis A-A and 90 ° from each other.
  • the fins 232 may be replaced by any other equivalent means.
  • FIGS. 4 and following show a device comprising in combination a launcher 100 and a plurality of ammunition 300.
  • the munition 200 is ejected in a 0-0 direction parallel to FIGS. its longitudinal direction AA.
  • each munition 300 is ejected in a direction O orthogonal to its longitudinal direction A-A.
  • the launcher 100 is formed of a parallelepipedal envelope cartridge which houses a plurality of projectiles 300, plus precisely three rows of three ammunition 300 according to the particular non-limiting embodiment shown here.
  • this cartridge 100 preferably comprises mechanical keying means to ensure its correct positioning and orientation on a complementary launcher base, for example in the form of two pads 140, 142 of different lengths provided on the upper face. 141.
  • the individual projectiles 300 are provided to be ejected by the opposite lower face 145 of the cartridge 100.
  • FIG. 5 also shows electrical connectors 160 carried on the upper face 141 of the cartridge and designed to supply electrical power to primers or igniters or equivalents 260 respectively associated with each munition 300.
  • the igniters 260 are connected to each other. connectors 160 by any appropriate means, for example by flexible electrical connections.
  • At least one of the lateral faces 146 of the cartridge is formed by a plate 150 or a number of plates 150 equal to the number of rows of ammunition 300 placed in the cartridge 100, fixed by any suitable means, for example by screwing on the housing of the cartridge 100 and comprising mechanical means 152, for example tenons, mechanically engaging with the rear axial end of the ammunition 300 in storage position thereof and in front of therefore be broken during the ejection of ammunition 300 out of the launcher 100.
  • Such means 152 ensure the maintenance of ammunition 300 in the storage position in the launcher.
  • each ammunition is centered on an individual axis AA orthogonal to the direction O of ejection.
  • the ammunition section 300 can be the subject of many embodiments. It can be cylindrical of revolution around the axis AA. However, preferably, as illustrated in the accompanying figures, in particular in Figures 7 and 8, each munition 300 has a polygonal cross section, typically rectangular.
  • Each munition 300 comprises a case or sheath 360 centered on the axis A-A which houses a payload 310, for example a bread composition capable of emitting in the electromagnetic field and / or a charge of electromagnetic decoys.
  • the payload 310 is traversed by a central rod 340.
  • Each munition 300 also has a safety base 320 at its front end and aerodynamic means 330 for one part at its front end, and for another part at its rear end. At the front end, each munition 300 comprises aerodynamic means called spikes formed of a disk 332 orthogonal to the axis A-A and secured to a sleeve 334 slidably mounted in the rod 340.
  • This aerodynamic means before 330 reduces the drag, just like the rear aerodynamic means 330.
  • the present invention is not limited to this particular drag reduction means. It can exploit conventional means of drag reduction, for example a non-telescopic conventional warhead.
  • the sleeve 334 comprises at least one orifice (preferably a series of orifices) 341.
  • the base 320 has a radial channel 322 which starts from the upper surface of the munition and opens into the rod 340 opposite the orifices 341 of the sleeve 334. In the storage position, as seen in FIG. 6, the channel 322 therefore communicates with the internal volume of the sleeve 334.
  • a seal 339 provided on the outer periphery of the sleeve 334 at the rear end thereof provides a seal between the sleeve 334 and the rod 340 to prohibit an initiation of the active load 310 in the storage position.
  • the base 320 also has a seal 321 in contact with the outer periphery of the sleeve 334 immediately downstream of the orifices 341.
  • the cane 340 has radial through-holes 342 which open on the outer periphery of the sleeve
  • a pellet 338 of pyrotechnic composition for example black powder or equivalent, is provided on the rear end of the sleeve 334.
  • the gases developed by the ejection charge 380 initiate the pellet 338 via the channel 322 of the orifices 341 and the internal volume of the sleeve 334.
  • the release of the gases generated by this pellet 338 ensures the simultaneous deployment of the aerodynamic means before 330 and aerodynamic means 330 rear.
  • non-pyrotechnic deployment modes for the aerodynamic means 230 and 330, for example deployment by elastic means or a spring.
  • This initiation can not, however, be transmitted to the active load 310 through the seals 321 and 339.
  • the rear end of the sleeve 334 and the pellet 338 are placed upstream of the orifices 342.
  • the initiation can then be transmitted to the active load 310.
  • the front end of a mast 354 belonging to the aerodynamic rear means 330 also carries on its outer periphery an annular seal 359 resting against the inner surface of the rod 340.
  • the orifices 342 are placed facing a machining or recess 312 formed on the front end of this load 310.
  • the rear means 330 comprise fins 352 or equivalent integral with the longitudinal mast 354 centered on the axis AA and mounted in translation in the central rod 340.
  • means limiting the translational movement of the front aerodynamic means and rear aerodynamic means in the rod 340 may be formed by enlargements or equivalents provided on the longitudinally inner ends of the sleeve 334 and the mast 354 cooperating with narrowing provided respectively on both ends of the payload 310.
  • the immobilization of the sleeve 334 and the mast 354 in the deployed position can be provided by any appropriate means, for example by a knurling or equivalent referenced schematically under the reference
  • sealing plates 370 made of elastomer, for example rubber on the faces of each orthogonal cartridge.
  • these plates referenced 370 have a central housing 372, preferably oblong, which houses an ejection charge 380.
  • the plates 370 also preferably have near each end of their housing receiving slots.
  • Pieces of rigid material 390 preferably made of metal, in contact with the case 360 and serving as a force-absorbing pin in order to avoid the deterioration of the joints 370 during the loading of the projectiles 300 in ejection.
  • the plates 370 additionally each have an orifice 373 placed opposite the channel 322. More specifically, the ejection charge 380 is placed in the chamber 372 of the joints 370 provided on the upper face of the ammunition. The chamber 372 provided in the joint 370 placed on the face The lower part of the adjacent superimposed ammunition is used as a relaxation chamber.
  • the case 360 has side plates 362 parallel to the ejection direction O having a large slot 364, for example oblong, through the thickness of the plates to allow the release of the infrared radiation and / or the deployment of electromagnetic decoys.
  • the side plates 360 have, for example mid-length, and over their entire height a rectilinear groove 366 engaged on a complementary rib or tenon integral with the launcher to ensure a guide of the ammunition 300 parallel to the axis O.
  • the associated ejection charge 380 develops propellant gases in the expansion chamber 372 placed opposite.
  • the corresponding projectile is displaced towards the outside of the launcher along the axis O.
  • the gases initiate the pellet 338 via the channel 322 of the orifices 341 and the internal volume of the sleeve 334.
  • the aerodynamic means 330 front and rear are deployed by the pressure of the gases generated by the pellet 338, as illustrated in FIG. 9.
  • the pellet 338 then being located upstream of the orifices 342, the initiation is transmitted to the active load 310.
  • the various munitions 300 can be implemented thus successively in any desired sequence.
  • the means proposed by the present invention make it possible to optimize the efficiency of the active load 310 by ensuring that it can be implemented only after deployment of the aerodynamic means 330.
  • the invention also guarantees the safety of the environment by prohibiting the initiation of active charges 310 storage position.
  • the present invention is not limited to the particular embodiments which have just been described but extends to any variant within its spirit.
  • the rigid masts 234, 334 and 354 shown in the figures may be replaced by flexible or resilient means, for example a spring.
  • these masts 234, 334 and 354 may be formed of telescopic structures to lengthen the length of these means.
  • the disks 332 or fins 232, 352 may be replaced by any equivalent means of the type empennage, ring, etc ...
  • the device according to the present invention makes it possible to guarantee the stability of the flight of the object, in a configuration that minimizes its aerodynamic drag.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Toys (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Abstract

The present invention relates to a device comprising at least one stabilized projectile (200, 300) housing an active element (210, 310) designed to generate a controlled technical effect over a trajectory, aerodynamic means (230, 330) that can be deployed between a rest retracted position in storage and deployed operational position over the trajectory, and safety means (224, 234) inserted between an initiation means (228, 280) and the active element (210, 310) to prevent the latter from being initiated until after the aerodynamic means (230, 330) have been deployed.

Description

PROJECTILE STABILISE MIS EN OEUVRE SUR TRAJECTOIRE, NOTAMMENT LEURRE STABILIZED PROJECTILE IMPLEMENTED ON TRAJECTORY, IN PARTICULAR LURE
La présente invention concerne le domaine des dispositifs comprenant un projectile stabilisé conçu pour générer un effet technique sur trajectoire.The present invention relates to the field of devices comprising a stabilized projectile designed to generate a technical effect on trajectory.
La présente invention trouve notamment, mais non exclusivement, application dans le domaine des leurres. Elle s'applique en particulier, à la protection par leurres infrarouges et/ou électromagnétiques, d'aéronefs de tous types (avions d'armes, avions de transports, hélicoptères ou avions civils).The present invention finds in particular, but not exclusively, application in the field of decoys. It applies in particular to the protection by infrared and / or electromagnetic lures of aircraft of all types (weapon aircraft, transport aircraft, helicopters or civil aircraft).
L'homme de l'art sait que différents types de leurres pour la protection d'aéronefs ont déjà été proposés.Those skilled in the art know that different types of lures for the protection of aircraft have already been proposed.
La plupart de ces systèmes sont conçus pour déployer sur commande, en cas de détection d'une menace, un leurre infrarouge et/ou électromagnétique à proximité de l'avion. Pour être efficace, ces leurres doivent présenter une signature infrarouge et/ou électromagnétique contrôlée. L'objectif de la présente invention est d'améliorer encore leur efficacité en maîtrisant de surcroît leur trajectoire, ceci afin de permettre un temps de vol maximal du leurre à proximité de l'aéronef à protéger.Most of these systems are designed to deploy on command, in case of detection of a threat, an infrared and / or electromagnetic decoy near the aircraft. To be effective, these lures must have a signature infrared and / or electromagnetic controlled. The objective of the present invention is to further improve their efficiency by controlling their trajectory, in order to allow a maximum flight time of the lure in the vicinity of the aircraft to be protected.
Dans ce contexte, la présente invention a pour objectif de proposer un nouveau dispositif qui permette d'améliorer l'efficacité du dispositif tout en préservant la sécurité de l'environnement du dispositif mis en oeuvre.In this context, the present invention aims to provide a new device that improves the efficiency of the device while preserving the environmental safety of the device implemented.
Ce but est atteint dans le cadre de la présente invention grâce à un dispositif comprenant un élément actif, par exemple une charge de composition apte à émettre dans le domaine infrarouge ou un leurre électromagnétique, adapté pour générer un effet technique contrôlé sur trajectoire, des moyens aérodynamiques de réduction de traînée, déployables axialement entre une position escamotée de repos au stockage et une position déployée opérationnelle sur trajectoire et des moyens de sécurité interposés entre un moyen d'initiation et l'élément actif, pour interdire l'initiation de ce dernier avant le déploiement des moyens aérodynamiques.This object is achieved in the context of the present invention by means of a device comprising an active element, for example a composition charge capable of emitting in the infrared range or an electromagnetic decoy, adapted to generate a controlled technical effect on a trajectory, means aerodynamic drag reduction system, deployable axially between a retracted position of storage rest and an operational deployed position on the trajectory and security means interposed between an initiation means and the element active, to prohibit the initiation of the latter before the deployment of aerodynamic means.
La présente invention garantit une efficacité optimale. En effet, en assurant que l'élément actif ne soit mis en oeuvre avant déploiement des moyens aérodynamiques, la présente invention garantit une durée opérationnelle optimale pour l'élément actif.The present invention ensures optimum efficiency. Indeed, by ensuring that the active element is implemented before deployment of the aerodynamic means, the present invention ensures an optimal operational time for the active element.
De surcroît, comme on le verra plus en détail par la suite, la présente invention interdit une mise en oeuvre de l'élément actif en position de stockage et par conséquent assure une protection de l'environnement, notamment dans le cadre d'une mise en oeuvre à partir d'un avion.In addition, as will be seen in more detail below, the present invention prohibits an implementation of the active element in storage position and therefore provides environmental protection, particularly in the context of a setting. implemented from an airplane.
D'autres caractéristiques, buts et avantages de la présente invention apparaîtront à la lecture de la description détaillée qui va suivre, et en regard des dessins annexés, donnés à titre d'exemples non limitatifs et sur lesquels :Other features, objects and advantages of the present invention will appear on reading the detailed description which follows, and with reference to the appended drawings, given by way of non-limiting examples and in which:
- la figure 1 représente une vue en coupe longitudinale d'un ensemble comprenant un lanceur et une munition conforme à un premier mode de réalisation de la présente invention,FIG. 1 represents a view in longitudinal section of an assembly comprising a launcher and an ammunition according to a first embodiment of the present invention,
- la figure 2 représente une vue similaire en coupe longitudinale de la même munition illustrée sur la figure 1 dans sa position en sortie du tube lanceur,FIG. 2 represents a similar view in longitudinal section of the same ammunition illustrated in FIG. 1 in its position at the outlet of the launcher tube;
- la figure 3 représente une vue en coupe longitudinale de la même munition après déploiement des moyens aérodynamiques,FIG. 3 represents a view in longitudinal section of the same munition after deployment of the aerodynamic means,
- la figure 4 représente une vue en coupe longitudinale d'un ensemble comprenant un chargeur et une pluralité de munitions, conforme à un deuxième mode de réalisation de la présente invention, comme référencé IV-IV sur la figure 5,FIG. 4 represents a longitudinal sectional view of an assembly comprising a magazine and a plurality of ammunition, according to a second embodiment of the present invention, as referenced IV-IV in FIG. 5;
- la figure 5 représente une vue de dessus du même ensemble selon la vue représentée V sur la figure 4, - la figure 6 représente une vue en coupe longitudinale selon le plan de coupe de la figure 4 d'une munition individuelle,FIG. 5 represents a view from above of the same assembly according to the view shown V in FIG. 4; FIG. 6 represents a longitudinal sectional view along the sectional plane of FIG. 4 of an individual ammunition,
- les figures 7 et 8 représentent respectivement des vues avant et arrière en bout de la même munition, - la figure 9 représente une vue similaire à la figure 6 de la même munition après déploiement des moyens aérodynamiques,FIGS. 7 and 8 show respectively front and rear views at the end of the same ammunition, FIG. 9 represents a view similar to FIG. 6 of the same ammunition after deployment of the aerodynamic means,
- la figure 10 représente une vue de dessus de la même munition selon l'orientation référencée V sur la figure 4, - la figure 11 représente une vue latérale de la même munition selon un plan parallèle aux figures 4, 6 et 9 et perpendiculairement au plan de la figure 10 tel que référencé XI sur la figure 10,FIG. 10 represents a view from above of the same munition in the orientation referenced V in FIG. 4; FIG. 11 represents a side view of the same munition in a plane parallel to FIGS. 4, 6 and 9 and perpendicular to FIG. plane of Figure 10 as referenced XI in Figure 10,
- la figure 12 représente une vue en coupe longitudinale de la même munition selon un plan de coupe orthogonal au plan de la figure 6, - la figure 13 représente une vue du même ensemble selon le plan de coupe référencé XIII-XIII sur la figure 5, etFIG. 12 represents a longitudinal sectional view of the same munition along a sectional plane orthogonal to the plane of FIG. 6; FIG. 13 represents a view of the same assembly along the section plane referenced XIII-XIII in FIG. , and
- la figure 14 représente une vue de dessous du même chargeur tel que référencé XIV sur la figure 13.FIG. 14 represents a view from below of the same loader as referenced XIV in FIG. 13.
On va tout d'abord décrire l'ensemble conforme au premier mode de réalisation de la présente invention, illustré sur les figures 1, 2 et 3 annexées, comprenant un lanceur 100 et un ensemble à éjecter ou projectile 200, pour le largage des projectiles 200 à partir d'un aéronef à protéger portant le lanceur 100.We will first describe the assembly according to the first embodiment of the present invention, illustrated in Figures 1, 2 and 3 appended, comprising a launcher 100 and a set to eject or projectile 200 for the release of the projectiles 200 from an aircraft to be protected carrying the launcher 100.
Le lanceur 100 comprend une douille ou tube 110 centré sur un axe 0-0, et adapté pour recevoir le projectile 200. La douille 110 est munie à une première extrémité d'un culot 120 qui loge des moyens aptes à assurer l'éjection du projectile 200 hors de la douille 100, par exemple une charge d'éjection 124 associée à une amorce 122.The launcher 100 comprises a bush or tube 110 centered on a 0-0 axis, and adapted to receive the projectile 200. The bushing 110 is provided at one end with a base 120 which houses means capable of ensuring the ejection of the projectile 200 out of the socket 100, for example an ejection charge 124 associated with a primer 122.
A sa seconde extrémité, la douille 110 est munie d'un bouchon 130 lui-même éjecté lors de l'éjection de la charge 200 et pourvu d'un joint annulaire périphérique d'étanchéité 132.At its second end, the bushing 110 is provided with a plug 130 itself ejected during the ejection of the load 200 and provided with an annular peripheral seal 132.
La douille 110 peut présenter une section circulaire de révolution autour de l'axe 0-0 ou une section polygonale, par exemple carrée ou rectangulaire. Le projectile 200 comprend essentiellement en combinaison une charge utile 210, une embase de sécurité 220 et des moyens aérodynamiques 230. Le projectile 200 est également centré sur un axe A-A lequel coïncide, au stockage, avec l'axe O-O.The bushing 110 may have a circular section of revolution about the axis 0-0 or a polygonal section, for example square or rectangular. The projectile 200 essentially comprises in combination a payload 210, a safety base 220 and aerodynamic means 230. The projectile 200 is also centered on an axis AA which coincides, on storage, with the axis OO.
Selon le mode de réalisation particulier représenté sur les figures annexées 1 à 3, la charge utile 210 est formée d'un pain annulaire de composition apte à émettre, lors de sa combustion, un rayonnement dans le domaine électromagnétique infrarouge. En variante, la charge utile 210 pourrait être remplacée et/ou complétée par une charge de leurres électromagnétiques, par exemple de paillettes réfléchissantes. En soi, la composition d'un pain apte à émettre dans le domaine infrarouge et/ou de tels leurres électromagnétiques, notamment à base de paillettes, sont bien connus de l'homme de l'art et ne seront pas décrits dans le détail par la suite.According to the particular embodiment shown in the accompanying figures 1 to 3, the payload 210 is formed of an annular roll of composition capable of emitting, during its combustion, a radiation in the infrared electromagnetic field. Alternatively, the payload 210 could be replaced and / or supplemented by a load of electromagnetic decoys, for example reflective flakes. In itself, the composition of a bread capable of emitting in the infrared range and / or such electromagnetic decoys, especially based on flakes, are well known to those skilled in the art and will not be described in detail by the following.
L'embase 220 comprend un ensemble de canaux 222 assurant une communication entre la face arrière externe 202 de la munition et la face avant 212 de la charge utile 210, plus précisément, une canne 240 centrée sur l'axe A-A et engagée dans un canal central de la charge utile 210. L'embase 220 loge par ailleurs un tiroir 224 placé dans l'un de ces canaux 222 et monté à translation dans une direction générale radiale par rapport à l'axe A-A entre une position de sécurité illustrée sur la figure 1 dans laquelle le tiroir 224 définit une interruption dans la chaîne de transmission définie par les canaux 222, en obturant au moins l'un des segments de ceux-ci, et une position de libération illustrée sur les figures 2 et 3 dans laquelle le tiroir 224 libère complètement les canaux 222 entre la face arrière externe 202 de la munition et la face avant 212 de la charge utile 210.The base 220 comprises a set of channels 222 providing communication between the outer rear face 202 of the munition and the front face 212 of the payload 210, more specifically, a rod 240 centered on the axis AA and engaged in a channel central station of the payload 210. The base 220 also houses a slide 224 placed in one of these channels 222 and mounted in translation in a generally radial direction relative to the axis AA between a security position illustrated on the Figure 1 in which the slide 224 defines an interruption in the transmission chain defined by the channels 222, by closing at least one of the segments thereof, and a release position illustrated in Figures 2 and 3 in which the drawer 224 completely frees the channels 222 between the outer rear face 202 of the munition and the front face 212 of the payload 210.
Le tiroir 224 est sollicité dans la position déployée illustrée sur les figures 2 et 3 par un ressort 226 ou tout moyen élastique équivalent placé dans le fond de l'un des canaux 222 recevant le tiroir 224 à translation. En position de stockage comme illustré sur la figure 1, l'extrémité radialement externe du tiroir 224 repose sur la face interne de la douille 210. Celle-ci interdit par conséquent tout déploiement du tiroir 224 et donc toute libération des canaux 222 tant que la munition 200 est placée dans la douille 110 du lanceur.The slide 224 is biased in the extended position illustrated in Figures 2 and 3 by a spring 226 or equivalent elastic means placed in the bottom of one of the channels 222 receiving the slide 224 translation. In the storage position as illustrated in Figure 1, the radially outer end of the slide 224 rests on the inner face of the sleeve 210. This therefore prohibits any deployment of the drawer 224 and therefore any release of the channels 222 as the ammunition 200 is placed in the sleeve 110 of the launcher.
L'homme de l'art comprendra que les moyens précités interdisent toute initiation de la charge utile 210 tant que la munition est placée à l'intérieur du lanceur 100.Those skilled in the art will understand that the aforementioned means prohibit any initiation of the payload 210 as the ammunition is placed inside the launcher 100.
Les moyens aérodynamiques 230 peuvent faire l'objet de nombreux modes de réalisation.The aerodynamic means 230 may be the subject of many embodiments.
Selon le mode de réalisation particulier représenté sur les figures annexées, ils comprennent un ensemble d'ailettes ou équivalents 232 portées par l'extrémité arrière d'un mât rectiligne 234 centré sur l'axe A-A et monté à translation dans la canne 240. Des moyens sont prévus pour limiter le déploiement des moyens aérodynamiques 230 par rapport à la canne 240. De tels moyens peuvent être formés par exemple d'un élargissement localisé 236 formé sur l'extrémité avant du mât 234 et coopérant avec un rétrécissement 204 formé au voisinage de l'extrémité arrière de la munition, par exemple au niveau d'une plaque, avantageusement en acier, prévue sur l'extrémité arrière de la charge utile 210 et référencée 250 sur les dessins.According to the particular embodiment shown in the appended figures, they comprise a set of fins or equivalent 232 carried by the rear end of a rectilinear mast 234 centered on the axis AA and mounted in translation in the cane 240. means are provided to limit the deployment of the aerodynamic means 230 relative to the rod 240. Such means may be formed for example of a localized enlargement 236 formed on the front end of the mast 234 and cooperating with a narrowing 204 formed in the vicinity the rear end of the munition, for example at a plate, preferably steel, provided on the rear end of the payload 210 and referenced 250 in the drawings.
Le déploiement des moyens aérodynamiques 230 entre la position rétractée de stockage illustrée sur la figure 1 et la position déployée représentée sur la figure 3, est de préférence obtenu par le dégagement de gaz sous pression dans la canne 240 par une pastille de composition pyrotechnique 238, par exemple de poudre noire, placée dans un logement formé sur l'extrémité avant du mât 234. Pour éviter l'évacuation sur l'extérieur de la munition de tels gaz et garantir un déploiement optimal des moyens aérodynamiques, l'extrémité avant du mât 234 est avantageusement munie d'un joint annulaire 237 complémentaire de la section interne de la canne 240.The deployment of the aerodynamic means 230 between the retracted storage position illustrated in FIG. 1 and the deployed position shown in FIG. 3 is preferably obtained by the release of gas under pressure in the rod 240 by a pellet of pyrotechnic composition 238. for example black powder, placed in a housing formed on the front end of the mast 234. To avoid the evacuation on the outside of the munition such gases and ensure optimum deployment of the aerodynamic means, the front end of the mast 234 is advantageously provided with an annular seal 237 complementary to the inner section of the rod 240.
La composition 238 est elle-même initiée par une amorce ou équivalent 228 portée par l'embase 220 dans l'un des canaux 222 en amont du tiroir de sécurité 224. Ainsi, la composition 238 n'est mise en oeuvre qu'après déploiement du tiroir de sécurité 224, c'est-à-dire après sortie de la munition hors du lanceur 100. L'homme de l'art comprendra que les moyens conformes à la présente invention représentés sur les figures 1 à 3 et précédemment décrits, permettent de garantir que la charge utile 210 n'est pas mise en oeuvre avant déploiement des moyens aérodynamiques 230. En effet, le tiroir de sécurité 224 interdit toute transmission de feu à la charge utile 210 tant que la munition 200 est à l'intérieur du tube lanceur 100. Lors de la sortie de la munition, le tiroir de sécuritéThe composition 238 is itself initiated by a primer or equivalent 228 carried by the base 220 in one of the channels 222 upstream of the safety slide 224. Thus, the composition 238 is implemented only after deployment safety slide 224, that is to say after exit of the ammunition out of the launcher 100. Those skilled in the art will understand that the means according to the present invention shown in Figures 1 to 3 and previously described, ensure that the payload 210 is not implemented before deployment of the aerodynamic means 230. Indeed, the safety slide 224 prohibits any transmission of fire to the payload 210 as long as the munition 200 is inside the launcher tube 100. When the ammunition leaves the safety drawer
224 étant déployé comme illustré sur les figures 2 et 3, les moyens aérodynamiques 230 sont automatiquement déployés par initiation de la charge 238 et l'initiation de la charge utile 210 est autorisée.224 being deployed as illustrated in Figures 2 and 3, the aerodynamic means 230 are automatically deployed by initiation of the load 238 and the initiation of the payload 210 is allowed.
Selon le mode de réalisation particulier représenté sur les figures 1 à 3, les moyens aérodynamiques, plus précisément les ailettes 232, comprennent quatre ailettes s'étendant dans des plans radiaux par rapport à l'axe A-A et à 90° les unes des autres. Bien entendu, de telles ailettes 232 peuvent être remplacées par tout autre moyen équivalent.According to the particular embodiment shown in Figures 1 to 3, the aerodynamic means, specifically the fins 232 comprise four fins extending in radial planes with respect to the axis A-A and 90 ° from each other. Of course, such fins 232 may be replaced by any other equivalent means.
On va maintenant décrire le dispositif conforme au deuxième mode de réalisation de la présente invention illustré sur les figures 4 et suivantes. On retrouve sur les figures 4 et suivantes un dispositif comprenant en combinaison un lanceur 100 et une pluralité de munitions 300.We will now describe the device according to the second embodiment of the present invention illustrated in Figures 4 and following. FIGS. 4 and following show a device comprising in combination a launcher 100 and a plurality of ammunition 300.
Différents aspects distinguent ce second mode de réalisation de celui précédemment décrit en regard des figures 1 à 3. En particulier, selon le premier mode de réalisation représenté sur les figures 1 à 3, la munition 200 est éjectée dans une direction 0-0 parallèle à sa direction longitudinale A-A.Various aspects distinguish this second embodiment from that previously described with reference to FIGS. 1 to 3. In particular, according to the first embodiment shown in FIGS. 1 to 3, the munition 200 is ejected in a 0-0 direction parallel to FIGS. its longitudinal direction AA.
Au contraire, selon le second mode de réalisation représenté sur les figures 4 et suivantes, chaque munition 300 est éjectée dans une direction O orthogonale à sa direction longitudinale A-A.In contrast, according to the second embodiment shown in Figures 4 and following, each munition 300 is ejected in a direction O orthogonal to its longitudinal direction A-A.
Selon le mode de réalisation représenté sur les figures 4 et suivantes, le lanceur 100 est formé d'une cartouche d'enveloppe parallélépipédique qui loge une pluralité de projectiles 300, plus précisément trois rangées de trois munitions 300 selon le mode de réalisation particulier non limitatif ici représenté.According to the embodiment shown in FIGS. 4 and following, the launcher 100 is formed of a parallelepipedal envelope cartridge which houses a plurality of projectiles 300, plus precisely three rows of three ammunition 300 according to the particular non-limiting embodiment shown here.
La cartouche ou lanceur 100 représenté sur les figures annexées, ne sera pas décrite dans le détail par la suite dans la mesure où elle peut faire l'objet de nombreuses variantes de réalisation.The cartridge or launcher 100 shown in the accompanying figures, will not be described in detail later since it can be the subject of many variants.
On notera cependant, que cette cartouche 100 comprend de préférence des moyens mécaniques de détrompage afin de garantir son positionnement et son orientation corrects sur une embase de lanceur complémentaire, par exemple sous forme de deux plots 140, 142 de longueur différente prévus sur la face supérieure 141.However, it will be noted that this cartridge 100 preferably comprises mechanical keying means to ensure its correct positioning and orientation on a complementary launcher base, for example in the form of two pads 140, 142 of different lengths provided on the upper face. 141.
Les projectiles individuels 300 sont prévus pour être éjectés par la face inférieure opposée 145 de la cartouche 100.The individual projectiles 300 are provided to be ejected by the opposite lower face 145 of the cartridge 100.
On aperçoit par ailleurs sur la figure 5, des connecteurs électriques 160 portés sur la face supérieure 141 de la cartouche et conçus pour assurer l'alimentation électrique d'amorces ou inflammateurs ou équivalents 260 associés respectivement à chaque munition 300. Les inflammateurs 260 sont reliés aux connecteurs 160 par tout moyen approprié, par exemple par des liaisons électriques flexibles. Selon une autre caractéristique préférentielle de l'invention, l'une au moins des faces latérales 146 de la cartouche est formée par une plaque 150 ou un nombre de plaques 150 égal au nombre de rangées de munitions 300 placées dans la cartouche 100, fixées par tout moyen approprié, par exemple par vissage sur le carter de la cartouche 100 et comprenant des moyens mécaniques 152, par exemple des tenons, venant en prise mécaniquement avec l'extrémité axiale arrière des munitions 300 en position de stockage de celles-ci et devant par conséquent être rompues lors de l'éjection de munitions 300 hors du lanceur 100. De tels moyens 152 assurent le maintien des munitions 300 en position de stockage dans le lanceur.FIG. 5 also shows electrical connectors 160 carried on the upper face 141 of the cartridge and designed to supply electrical power to primers or igniters or equivalents 260 respectively associated with each munition 300. The igniters 260 are connected to each other. connectors 160 by any appropriate means, for example by flexible electrical connections. According to another preferred feature of the invention, at least one of the lateral faces 146 of the cartridge is formed by a plate 150 or a number of plates 150 equal to the number of rows of ammunition 300 placed in the cartridge 100, fixed by any suitable means, for example by screwing on the housing of the cartridge 100 and comprising mechanical means 152, for example tenons, mechanically engaging with the rear axial end of the ammunition 300 in storage position thereof and in front of therefore be broken during the ejection of ammunition 300 out of the launcher 100. Such means 152 ensure the maintenance of ammunition 300 in the storage position in the launcher.
Chaque munition est centrée sur un axe individuel A-A orthogonal à la direction O d'éjection. La section des munitions 300 peut faire l'objet de nombreux modes de réalisation. Elle peut être cylindrique de révolution autour de l'axe A-A. Cependant, de préférence, comme illustré sur les figures annexées, notamment sur les figures 7 et 8, chaque munition 300 présente une section droite polygonale, typiquement rectangulaire.Each ammunition is centered on an individual axis AA orthogonal to the direction O of ejection. The ammunition section 300 can be the subject of many embodiments. It can be cylindrical of revolution around the axis AA. However, preferably, as illustrated in the accompanying figures, in particular in Figures 7 and 8, each munition 300 has a polygonal cross section, typically rectangular.
Chaque munition 300 comprend un étui ou fourreau 360 centré sur l'axe A-A qui loge une charge utile 310 par exemple un pain de composition apte à émettre dans le domaine électromagnétique infrarouge et/ou une charge de leurres électromagnétiques. La charge utile 310 est traversée par une canne centrale 340.Each munition 300 comprises a case or sheath 360 centered on the axis A-A which houses a payload 310, for example a bread composition capable of emitting in the electromagnetic field and / or a charge of electromagnetic decoys. The payload 310 is traversed by a central rod 340.
Chaque munition 300 possède par ailleurs une embase de sécurité 320 à son extrémité avant et des moyens aérodynamiques 330 pour une part à son extrémité avant, et pour une autre part à son extrémité arrière. A l'extrémité avant, chaque munition 300 comporte des moyens aérodynamiques dénommés spike formés d'un disque 332 orthogonal à l'axe A-A et solidaire d'un manchon 334 monté à coulissement dans la canne 340.Each munition 300 also has a safety base 320 at its front end and aerodynamic means 330 for one part at its front end, and for another part at its rear end. At the front end, each munition 300 comprises aerodynamic means called spikes formed of a disk 332 orthogonal to the axis A-A and secured to a sleeve 334 slidably mounted in the rod 340.
Ce moyen aérodynamique avant 330 réduit la traînée, tout comme le moyen aérodynamique arrière 330.This aerodynamic means before 330 reduces the drag, just like the rear aerodynamic means 330.
Bien entendu la présente invention n'est pas limitée à ce moyen particulier de réduction de traînée. Elle peut exploiter des moyens conventionnels de réduction de traînée, par exemple une ogive classique non téléscopique. Le manchon 334 comprend au moins un orifice (de préférence une série d'orifices) 341.Of course, the present invention is not limited to this particular drag reduction means. It can exploit conventional means of drag reduction, for example a non-telescopic conventional warhead. The sleeve 334 comprises at least one orifice (preferably a series of orifices) 341.
L'embase 320 possède un canal radial 322 qui part de la surface supérieure de la munition et débouche dans la canne 340 en regard des orifices 341 du manchon 334. En position de stockage, comme on le voit sur la figure 6, le canal 322 communique par conséquent avec le volume interne du manchon 334.The base 320 has a radial channel 322 which starts from the upper surface of the munition and opens into the rod 340 opposite the orifices 341 of the sleeve 334. In the storage position, as seen in FIG. 6, the channel 322 therefore communicates with the internal volume of the sleeve 334.
Cependant, un joint 339 prévu sur la périphérie extérieure du manchon 334 à l'extrémité arrière de celui-ci assure une étanchéité entre le manchon 334 et la canne 340 pour interdire une initiation de la charge active 310 en position de stockage.However, a seal 339 provided on the outer periphery of the sleeve 334 at the rear end thereof provides a seal between the sleeve 334 and the rod 340 to prohibit an initiation of the active load 310 in the storage position.
L'embase 320 possède également un joint d'étanchéité 321 en contact avec la périphérie extérieure du manchon 334 immédiatement en aval des orifices 341. La canne 340 possède des orifices radiaux traversant 342 qui débouchent sur la périphérie extérieure du manchonThe base 320 also has a seal 321 in contact with the outer periphery of the sleeve 334 immediately downstream of the orifices 341. The cane 340 has radial through-holes 342 which open on the outer periphery of the sleeve
334 entre les joints 321 et 339.334 between seals 321 and 339.
Une pastille 338 de composition pyrotechnique, par exemple poudre noire ou équivalent, est prévue sur l'extrémité arrière du manchon 334.A pellet 338 of pyrotechnic composition, for example black powder or equivalent, is provided on the rear end of the sleeve 334.
Lors de l'éjection d'un projectile ou munition 300, les gaz développés par la charge d'éjection 380 initient la pastille 338 par l'intermédiaire du canal 322 des orifices 341 et du volume interne au manchon 334. Le dégagement des gaz générés par cette pastille 338 assure le déploiement simultané des moyens aérodynamiques avant 330 et des moyens aérodynamiques 330 arrière.During the ejection of a projectile or ammunition 300, the gases developed by the ejection charge 380 initiate the pellet 338 via the channel 322 of the orifices 341 and the internal volume of the sleeve 334. The release of the gases generated by this pellet 338 ensures the simultaneous deployment of the aerodynamic means before 330 and aerodynamic means 330 rear.
Dans le cadre de la présente invention, on peut également retenir des modes de déploiement non pyrotechniques pour les moyens aérodynamiques 230 et 330, par exemple un déploiement par des moyens élastiques ou un ressort.In the context of the present invention, it is also possible to use non-pyrotechnic deployment modes for the aerodynamic means 230 and 330, for example deployment by elastic means or a spring.
Cette initiation ne peut cependant être transmise à la charge active 310 grâce aux joints 321 et 339.This initiation can not, however, be transmitted to the active load 310 through the seals 321 and 339.
Une fois placée en position déployée l'extrémité arrière du manchon 334 et la pastille 338 sont placés en amont des orifices 342. L'initiation peut alors être transmise à la charge active 310.Once placed in the deployed position the rear end of the sleeve 334 and the pellet 338 are placed upstream of the orifices 342. The initiation can then be transmitted to the active load 310.
L'extrémité avant d'un mât 354 appartenant aux moyens arrières aérodynamiques 330, porte également sur sa périphérie externe un joint annulaire d'étanchéité 359 reposant contre la surface interne de la canne 340. Pour faciliter l'amorçage de la charge active 310 les orifices 342 sont placés en regard d'un usinage ou décrochement 312 formé sur l'extrémité avant de cette charge 310. Pour l'essentiel, les moyens arrières 330 comprennent des ailettes 352 ou équivalents solidaires du mât longitudinal 354 centré sur l'axe A-A et monté à translation dans la canne centrale 340.The front end of a mast 354 belonging to the aerodynamic rear means 330, also carries on its outer periphery an annular seal 359 resting against the inner surface of the rod 340. To facilitate the priming of the active load 310 the orifices 342 are placed facing a machining or recess 312 formed on the front end of this load 310. Essentially, the rear means 330 comprise fins 352 or equivalent integral with the longitudinal mast 354 centered on the axis AA and mounted in translation in the central rod 340.
Là encore, il est prévu des moyens limitant le déplacement à translation des moyens aérodynamiques avant et des moyens aérodynamiques arrières dans la canne 340. De tels moyens peuvent être formés par des élargissements ou équivalents prévus sur les extrémités longitudinalement internes du manchon 334 et du mât 354 coopérant avec des rétrécissements prévus respectivement sur les deux extrémités de la charge utile 310.Again, there are provided means limiting the translational movement of the front aerodynamic means and rear aerodynamic means in the rod 340. Such means may be formed by enlargements or equivalents provided on the longitudinally inner ends of the sleeve 334 and the mast 354 cooperating with narrowing provided respectively on both ends of the payload 310.
L'immobilisation du manchon 334 et du mât 354 en position déployée peut être assurée par tout moyen approprié, par exemple par un moletage ou équivalent référencé schématiquement sous la référenceThe immobilization of the sleeve 334 and the mast 354 in the deployed position can be provided by any appropriate means, for example by a knurling or equivalent referenced schematically under the reference
355 sur les figures annexées, pour le mât 354 et 335 pour le manchon 334.355 in the accompanying figures, for the mast 354 and 335 for the sleeve 334.
Afin d'assurer l'étanchéité au niveau de chaque munition, quelque soit le nombre de munitions présent dans la cartouche 100, il est de préférence prévu des plaques d'étanchéité 370 en élastomère, par exemple en caoutchouc sur les faces de chaque cartouche orthogonales à la direction d'éjection O. Ces plaques référencées 370 possèdent un logement central 372, de préférence oblong, qui loge une charge d'éjection 380. Les plaques 370 possèdent par ailleurs de préférence au voisinage de chacune de leurs extrémités des logements recevant des pions en matériau rigide 390, de préférence en métal, en contact avec l'étui 360 et servant de pion de reprise d'effort afin d'éviter la détérioration des joints 370 lors de la sollicitation des projectiles 300 en éjection.To ensure the seal at each munition, whatever the number of ammunition present in the cartridge 100, it is preferably provided sealing plates 370 made of elastomer, for example rubber on the faces of each orthogonal cartridge. these plates referenced 370 have a central housing 372, preferably oblong, which houses an ejection charge 380. The plates 370 also preferably have near each end of their housing receiving slots. Pieces of rigid material 390, preferably made of metal, in contact with the case 360 and serving as a force-absorbing pin in order to avoid the deterioration of the joints 370 during the loading of the projectiles 300 in ejection.
Les plaques 370 possèdent de plus chacune un orifice 373 placé en regard du canal 322. Plus précisément encore, la charge d'éjection 380 est placée dans la chambre 372 des joints 370 prévus sur la face supérieure des munitions. La chambre 372 prévue dans le joint 370 placé sur la face inférieure de la munition adjacente superposée tient lieu quant à elle de chambre de détente.The plates 370 additionally each have an orifice 373 placed opposite the channel 322. More specifically, the ejection charge 380 is placed in the chamber 372 of the joints 370 provided on the upper face of the ammunition. The chamber 372 provided in the joint 370 placed on the face The lower part of the adjacent superimposed ammunition is used as a relaxation chamber.
Comme on le voit sur les figures 10 à 12, l'étui 360 possède des plaques latérales 362 parallèles à la direction d'éjection O possédant une large lumière 364, par exemple oblongue, traversante selon l'épaisseur de plaques pour permettre le dégagement du rayonnement infrarouge et/ou le déploiement des leurres électromagnétiques.As seen in Figures 10 to 12, the case 360 has side plates 362 parallel to the ejection direction O having a large slot 364, for example oblong, through the thickness of the plates to allow the release of the infrared radiation and / or the deployment of electromagnetic decoys.
Par ailleurs, les plaques latérales 360 possèdent, par exemple à mi longueur, et sur toute leur hauteur une gorge rectiligne 366 engagée sur une nervure ou tenon complémentaire solidaire du lanceur afin d'assurer un guidage des munitions 300 parallèlement à l'axe O.Furthermore, the side plates 360 have, for example mid-length, and over their entire height a rectilinear groove 366 engaged on a complementary rib or tenon integral with the launcher to ensure a guide of the ammunition 300 parallel to the axis O.
Le fonctionnement du lanceur représenté sur les figures 4 et suivantes et essentiellement le suivant. En position de stockage, comme illustré sur la figure 4, une initiation des charges actives 310 est interdite par les joints 370 et par les joints 321 et 339.The operation of the launcher shown in Figures 4 and following and essentially the following. In the storage position, as illustrated in FIG. 4, initiation of the active charges 310 is prohibited by the joints 370 and by the joints 321 and 339.
Lors de l'initiation d'une amorce choisie 260, la charge d'éjection associée 380 développe des gaz de propulsion dans la chambre de détente 372 placée en regard. Le projectile correspondant est déplacé vers l'extérieur du lanceur selon l'axe O. Les gaz initient la pastille 338 par l'intermédiaire du canal 322 des orifices 341 et du volume interne du manchon 334. En sortie du lanceur, les moyens aérodynamiques 330 avant et arrière sont déployés par la pression des gaz générés par la pastille 338, comme illustré sur la figure 9.During the initiation of a selected primer 260, the associated ejection charge 380 develops propellant gases in the expansion chamber 372 placed opposite. The corresponding projectile is displaced towards the outside of the launcher along the axis O. The gases initiate the pellet 338 via the channel 322 of the orifices 341 and the internal volume of the sleeve 334. At the exit of the launcher, the aerodynamic means 330 front and rear are deployed by the pressure of the gases generated by the pellet 338, as illustrated in FIG. 9.
La pastille 338 étant alors située en amont des orifices 342, l'initiation est transmise à la charge active 310. Les différentes munitions 300 peuvent être mises en oeuvre ainsi successivement selon toute séquence souhaitée. Là encore, les moyens proposés par la présente invention permettent une optimisation de l'efficacité de la charge active 310 en assurant une mise en oeuvre de celle-ci seulement après déploiement des moyens aérodynamiques 330. L'invention garantit de plus la sécurité de l'environnement en interdisant l'initiation des charges actives 310 en position de stockage. Bien entendu la présente invention n'est pas limitée aux modes de réalisation particuliers qui viennent d'être décrits mais s'étend à toute variante conforme à son esprit.The pellet 338 then being located upstream of the orifices 342, the initiation is transmitted to the active load 310. The various munitions 300 can be implemented thus successively in any desired sequence. Here again, the means proposed by the present invention make it possible to optimize the efficiency of the active load 310 by ensuring that it can be implemented only after deployment of the aerodynamic means 330. The invention also guarantees the safety of the environment by prohibiting the initiation of active charges 310 storage position. Of course, the present invention is not limited to the particular embodiments which have just been described but extends to any variant within its spirit.
Par exemple, les mâts rigides 234, 334 et 354 représentés sur les figures pourront être remplacés par des moyens souples ou élastiques, par exemple un ressort.For example, the rigid masts 234, 334 and 354 shown in the figures may be replaced by flexible or resilient means, for example a spring.
Si nécessaire, ces mâts 234, 334 et 354 pourront être formés de structures télescopiques permettant d'allonger la longueur de ces moyens. De plus, les disques 332 ou ailettes 232, 352 pourront être remplacés par tout moyen équivalent du type empennage, anneau, etc ...If necessary, these masts 234, 334 and 354 may be formed of telescopic structures to lengthen the length of these means. In addition, the disks 332 or fins 232, 352 may be replaced by any equivalent means of the type empennage, ring, etc ...
L'homme de l'art comprendra que le dispositif conforme à la présente invention permet de garantir la stabilité du vol de l'objet, dans une configuration qui minimalise sa traînée aérodynamique. Those skilled in the art will understand that the device according to the present invention makes it possible to guarantee the stability of the flight of the object, in a configuration that minimizes its aerodynamic drag.

Claims

REVENDICATIONS
1. Dispositif comprenant au moins un projectile stabilisé (200, 300) qui loge un élément actif (210, 310) adapté pour générer un effet technique contrôlé sur trajectoire, des moyens aérodynamiques (230, 330) de réduction de traînée, déployables axialement entre une position escamotée de repos au stockage et une position déployée opérationnelle sur trajectoire et des moyens de sécurité (224, 234) interposés entre un moyen d'initiation (228, 280) et l'élément actif (210, 310), pour interdire l'initiation de ce dernier avant le déploiement des moyens aérodynamiques (230, 330).1. Device comprising at least one stabilized projectile (200, 300) which houses an active element (210, 310) adapted to generate a controlled technical effect on trajectory, aerodynamic drag reduction means (230, 330), axially deployable between a retracted position of storage rest and an operational deployed position on the trajectory and security means (224, 234) interposed between an initiation means (228, 280) and the active element (210, 310), to prohibit the initiation of the latter before deployment of the aerodynamic means (230, 330).
2. Dispositif selon la revendication 1, caractérisé par le fait que l'élément actif (210, 310) comprend une composition apte à émettre un rayonnement infrarouge par combustion après son initiation. 2. Device according to claim 1, characterized in that the active element (210, 310) comprises a composition capable of emitting infrared radiation by combustion after its initiation.
3. Dispositif selon l'une des revendications 1 ou 2, caractérisé par le fait que l'élément actif (210, 310) comprend une charge de réflecteur électromagnétique, déployée après son initiation.3. Device according to one of claims 1 or 2, characterized in that the active element (210, 310) comprises an electromagnetic reflector charge, deployed after its initiation.
4. Dispositif selon l'une des revendications 1 à 3, caractérisé par le fait qu'il comprend en outre un lanceur (100). 4. Device according to one of claims 1 to 3, characterized in that it further comprises a launcher (100).
5. Dispositif selon l'une des revendications 1 à 4, caractérisé par le fait que le projectile (200) est éjecté selon une direction (O) parallèle à son axe longitudinal (A-A).5. Device according to one of claims 1 to 4, characterized in that the projectile (200) is ejected in a direction (O) parallel to its longitudinal axis (A-A).
6. Dispositif selon l'une des revendications 1 à 4, caractérisé par le fait que le projectile (300) est éjecté selon une direction (O) perpendiculairement à son axe longitudinal (A-A).6. Device according to one of claims 1 to 4, characterized in that the projectile (300) is ejected in a direction (O) perpendicular to its longitudinal axis (A-A).
7. Dispositif selon l'une des revendications 1 à 6, caractérisé par le fait qu'il comprend des moyens aérodynamiques (330) à son extrémité arrière formés d'un empennage (232, 352) solidaire d'un mât télescopique (234, 354). 7. Device according to one of claims 1 to 6, characterized in that it comprises aerodynamic means (330) at its rear end formed of a stabilizer (232, 352) integral with a telescopic mast (234, 354).
8. Dispositif selon l'une des revendications 1 à 7, caractérisé par le fait qu'il comprend des moyens aérodynamiques (330) à son extrémité avant formés d'un disque (332) solidaire d'un mât télescopique (334). 8. Device according to one of claims 1 to 7, characterized in that it comprises aerodynamic means (330) at its front end formed of a disc (332) integral with a telescopic mast (334).
9. Dispositif selon les revendications 7 et 8 prises en combinaison, caractérisé par le fait qu'il comprend des moyens (338) adaptés pour déployer simultanément les moyens aérodynamiques (330) avant et arrière. 9. Device according to claims 7 and 8 taken in combination, characterized in that it comprises means (338) adapted to deploy simultaneously the aerodynamic means (330) front and rear.
10. Dispositif selon l'une des revendications 7 à 9, caractérisé par le fait que le mât télescopique (234, 334, 354) est rigide.10. Device according to one of claims 7 to 9, characterized in that the telescopic mast (234, 334, 354) is rigid.
11. Dispositif selon l'une des revendications 7 à 9, caractérisé par le fait que le mât télescopique (234, 334, 354) est souple.11. Device according to one of claims 7 to 9, characterized in that the telescopic mast (234, 334, 354) is flexible.
12. Dispositif selon l'une des revendications 1 à 11, caractérisé par le fait que les moyens de sécurité comprennent un tiroir coulissant12. Device according to one of claims 1 to 11, characterized in that the security means comprise a sliding drawer
(224, 334) qui assure une interruption de chaînes pyrotechniques en position de stockage.(224, 334) which ensures an interruption of pyrotechnic chains in the storage position.
13. Dispositif selon la revendication 12, caractérisé par le fait que le tiroir de sécurité (334) constitue un mât télescopique support de moyens aérodynamiques (332).13. Device according to claim 12, characterized in that the safety slide (334) is a telescopic support mast aerodynamic means (332).
14. Dispositif selon la revendication 13, caractérisé par le fait que le tiroir de sécurité (334) porte une pastille pyrotechnique (338) apte à dégager des gaz assurant le déploiement d'un moyen aérodynamique (330). 14. Device according to claim 13, characterized in that the safety slide (334) carries a pyrotechnic pellet (338) capable of releasing gases ensuring the deployment of an aerodynamic means (330).
15. Dispositif selon l'une des revendications 1 à 14, caractérisé par le fait qu'il comprend un lanceur (100) qui loge plusieurs munitions (300).15. Device according to one of claims 1 to 14, characterized in that it comprises a launcher (100) which houses several ammunition (300).
16. Dispositif selon la revendication 15, caractérisé par le fait qu'un joint (370) est placé entre chaque paire adjacente de munitions (300).16. Device according to claim 15, characterized in that a seal (370) is placed between each adjacent pair of ammunition (300).
17. Dispositif selon la revendication 16, caractérisé par le fait qu'une charge d'éjection (380) est placée dans un logement du joint (370).17. Device according to claim 16, characterized in that an ejection charge (380) is placed in a housing of the joint (370).
18. Dispositif selon l'une des revendications 16 ou 17, caractérisé par le fait que le joint (370) comporte des pions de reprise d'effort (390) dans son épaisseur. 18. Device according to one of claims 16 or 17, characterized in that the seal (370) comprises force recovery pins (390) in its thickness.
EP07820558A 2006-09-27 2007-09-25 Stabilized projectile used over a trajectory, particularly decoy Withdrawn EP2082183A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0608459A FR2906359A1 (en) 2006-09-27 2006-09-27 STABILIZED PROJECTILE IMPLEMENTED ON TRAJECTORY, IN PARTICULAR LURE.
PCT/EP2007/060162 WO2008037713A1 (en) 2006-09-27 2007-09-25 Stabilized projectile used over a trajectory, particularly decoy

Publications (1)

Publication Number Publication Date
EP2082183A1 true EP2082183A1 (en) 2009-07-29

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EP07820558A Withdrawn EP2082183A1 (en) 2006-09-27 2007-09-25 Stabilized projectile used over a trajectory, particularly decoy

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EP (1) EP2082183A1 (en)
FR (1) FR2906359A1 (en)
WO (1) WO2008037713A1 (en)

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Publication number Priority date Publication date Assignee Title
FR2977867B1 (en) * 2011-07-12 2013-08-09 Mbda France COUNTERMEASURE SANDING SYSTEM FOR MOUNTING ON AN AIRCRAFT

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Publication number Priority date Publication date Assignee Title
US3855933A (en) * 1967-05-11 1974-12-24 Us Army Dual purpose grenade
US3635162A (en) * 1970-07-09 1972-01-18 Us Navy Practice bomb
FR2508624A1 (en) * 1981-06-26 1982-12-31 Luchaire Sa AMMUNITION SUCH AS HAND GRENADE, PARTICULARLY FOR THE FIGHT AGAINST ARMORED
US5631441A (en) * 1996-04-02 1997-05-20 Her Majesty The Queen In Right Of Canada, As Represented By The Minister Of National Defence Of Her Majesty's Canadian Government XDM pyrophoric countermeasure flare

Non-Patent Citations (1)

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Title
See references of WO2008037713A1 *

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WO2008037713A1 (en) 2008-04-03
FR2906359A1 (en) 2008-03-28

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