EP1192406B1 - Device for neutralising a payload - Google Patents

Device for neutralising a payload Download PDF

Info

Publication number
EP1192406B1
EP1192406B1 EP01958138A EP01958138A EP1192406B1 EP 1192406 B1 EP1192406 B1 EP 1192406B1 EP 01958138 A EP01958138 A EP 01958138A EP 01958138 A EP01958138 A EP 01958138A EP 1192406 B1 EP1192406 B1 EP 1192406B1
Authority
EP
European Patent Office
Prior art keywords
rocket
payload
vector
satellite
charge
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP01958138A
Other languages
German (de)
French (fr)
Other versions
EP1192406A1 (en
Inventor
Michel Vives
Jean-Paul Duparc
Patrick Sylvain
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.)
Giat Industries SA
Original Assignee
Giat Industries 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 Giat Industries SA filed Critical Giat Industries SA
Publication of EP1192406A1 publication Critical patent/EP1192406A1/en
Application granted granted Critical
Publication of EP1192406B1 publication Critical patent/EP1192406B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42AMMUNITION; BLASTING
    • F42BEXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B15/00Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • F42B15/36Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means

Definitions

  • the technical field of the invention is that of devices for neutralizing a payload transported by a vector.
  • the payloads thus carried can be dangerous or toxic. It is therefore necessary in case vector theft incident to destroy them.
  • liquid propellants extremely toxic and explosive (hydrazine, peroxide nitrogen). It is essential to destroy these thrusters by incident in order to avoid a fall to the ground of a large quantity of these materials.
  • the envelope of the thrusters is destroyed. so as to release the propellants. These destroy themselves in interacting with each other as well than in contact with the atmosphere.
  • the weapon is also a complex mechanism likely to fail when launching the rocket.
  • the hollow charge jets have a reduced effectiveness against propellants with liquid propellants.
  • the jet is consumed quickly by the liquid and the diameter drain holes made is low (of the order of mm).
  • the geometry of the payload can differ greatly from one vector shot to another.
  • the thrusters are no longer placed at the same locations and the vector needs to be changed in depth to allow the establishment of a new neutralization.
  • the neutralization device ensures destruction in a simple and reliable way of a payload carried by a vector.
  • This device is easily adaptable to different types payloads, it therefore simplifies adaptation of the vector to the load to be carried.
  • the subject of the invention is a device for neutralization of a payload transported by a vector, like a rocket, characterized in that it comprises at least one explosive charge generating nucleus, returned charge integral with the vector by positioning means ensuring an orientation of its direction of action towards the payload.
  • the positioning means may be adjustable to allow adaptation of the neutralization device at different structures and / or payload locations.
  • the positioning means may also be fixed.
  • the device may include at least two charges explosive nucleus generators.
  • the core-generating charge (s) will have preferably a caliber greater than 50 mm.
  • the neutralization device according to the invention applies more particularly to the destruction of the thrusters of a satellite embarked by a rocket.
  • a vector 1 such as a rocket ballistics (of which only the head is represented) includes a housing 2 inside its warhead 3, housing receiving a payload 4 constituted by a satellite.
  • Satellite 4 is linked to the vector warhead by flanges 5a, 5b. In a known manner, it is intended to be released on trajectory by the rocket at a given altitude ensuring its launch into Earth orbit.
  • the means ensuring the opening of the warhead and the satellite release is not shown here and they don't are not part of the present invention.
  • Satellite 4 contains one or more tanks liquid propellants.
  • the satellite shown in Figure 1 comprises two tanks 6a and 6b superimposed and arranged substantially at the axis 7 of the rocket.
  • the tanks 6a, 6b are connected to a nozzle 8.
  • means are provided to neutralize the propellants contained in the tanks 6a, 6b by breaking their tanks allowing thus their release.
  • the neutralization means have two charges explosives 9a, 9b generating the nucleus. Each charge 9 is secured to rocket 1 by means of positioning 10a, 10b which ensure a orientation of the direction of action 11a, 11b towards the load useful 4.
  • a nucleus-generating charge is well known to the Man of the Trade. We can for example consult the patents FR2627580, FR2740212 and FR2741142 which describe a such charge. It includes an explosive charge 13 placed in an envelope 14 and to which is applied a metallic coating 12 in the shape of a cap.
  • the explosive charge 13 is initiated by a means detonator 15 which is connected to a control means 16.
  • the positioning means 10a, 10b which are described here are designed to give one or two degrees of freedom to the envelope 14 of the load they bear.
  • stirrup 17 defining a direction 18a, 18b parallel to the axis 7 of the rocket.
  • This stirrup will be pivotally mounted relative to a base 20 fixed to the rocket. The pivoting will thus take place around the direction 18a or 18b (arrow Z).
  • the load 9 will be fixed inside the stirrup 17 by via a base 19 and it can therefore itself be tilted relative to the bracket 17.
  • each load 9 makes it possible to give each load 9 an optimal orientation which will be adapted in depending on the nature and structure of the payload 4. Concretely we will tilt each load in such a way that its direction of action 11 meets one of the reservoirs 6 of the satellite 4.
  • the bracket 17 may be fixed by compared to the base 20, the only degree of freedom of the load will then be its tilting with respect to the stirrup 17.
  • the load 9a thus has a direction of action 11a which is inclined at an angle ⁇ to the direction 18a parallel to the axis of the rocket 1. This direction of action 11a meets the upper reservoir 6b.
  • the load 9b has a direction of action 11b which is inclined by an angle ⁇ relative to the direction 18b parallel to the axis of the rocket 1. This direction of action 11b meets the lower reservoir 6a.
  • the charges 9a and 9b are connected to the control means 16 which is intended to cause their initiation at a time given.
  • This control means can advantageously be consisting of part of the control electronics / rocket guidance.
  • the initiation of charge (s) 9 will be caused on trajectory at a given time. This initiation may advantageously be remotely controlled from the ground in case of detection of a serious event (rupture of the rocket, loss of path).
  • the initiation may also be triggered automatically by the rocket electronics in case of loss of ground connection (loss of guidance and / or control).
  • the charges 9a, 9b have a diameter of the order of 50 to 150mm (for example 80mm).
  • Their coating may be of iron or nickel. They generate as a result of their initiation a homokinetic metal core of approximately 100 g which is driven at a speed of around 2000 m / s.
  • Such a nucleus is stable up to distances of the order 25 m, i.e. distances far greater than the maximum distance separating a load from one of the tanks propellant.
  • the tanks 6 are therefore perforated by the cores thus generated. This results in a dynamic overpressure which blew up the tanks.
  • the device according to the invention can be placed in the rocket at a location relatively distant from the payload.
  • the speed and stability of the cores allows reliably destroy the payload despite the distance.
  • the device according to the invention therefore allows, with a simple structure, compact and easy to integrate into the rocket, to ensure the safe destruction of the payload and especially liquid propellants contained in the tanks 6.
  • the reliability of the device is higher than that of existing devices and at lower cost.
  • Figure 2 shows a rocket 1 identical to that previously described but carrying a satellite 4 which has a different structure.
  • This satellite comprises two tanks 6a, 6b of propellants which are arranged parallel to each other and both and across axis 7.
  • the positioning means 10a and 10b make it possible to modify the orientations of action directions 11a and 11b loads so that each direction of action meets a reservoir 6a or 6b.
  • the directions of action 11a and 11b are inclined by the same angle ⁇ with respect to the directions 18a / 18b defined by the stirrups 17 and parallel to the axis 7 of the rocket 1.
  • Load adjustment will be carried out during payload integration.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Position Fixing By Use Of Radio Waves (AREA)
  • Small-Scale Networks (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Monitoring And Testing Of Transmission In General (AREA)
  • Monitoring And Testing Of Nuclear Reactors (AREA)
  • Radio Relay Systems (AREA)
  • Catching Or Destruction (AREA)
  • Selective Calling Equipment (AREA)
  • Toys (AREA)

Abstract

A neutralization device for a payload carried by a vector, such as a rocket. This device incorporates at least one explosively-formed charge, where such charge is made integral with the vector by a positioning device ensuring the orientation of its direction of action towards the payload.

Description

Le domaine technique de l'invention est celui des dispositifs permettant la neutralisation d'une charge utile transportée par un vecteur.The technical field of the invention is that of devices for neutralizing a payload transported by a vector.

Les charges utiles ainsi emportées peuvent être dangereuses ou toxiques. Il est donc nécessaire en cas d'incident de vol du vecteur de procéder à leur destruction.The payloads thus carried can be dangerous or toxic. It is therefore necessary in case vector theft incident to destroy them.

Ainsi, les satellites qui sont emportés par des fusées balistiques comportent généralement des propulseurs liquides extrêmement toxiques et explosifs (hydrazine, peroxyde d'azote). Il est indispensable de détruire ces propulseurs en cas d'incident afin d'éviter une retombée au sol d'une grande quantité de ces matériaux.So the satellites that are carried by rockets ballistics generally include liquid propellants extremely toxic and explosive (hydrazine, peroxide nitrogen). It is essential to destroy these thrusters by incident in order to avoid a fall to the ground of a large quantity of these materials.

Concrètement on détruit l'enveloppe des propulseurs de façon à libérer les ergols. Ces derniers se détruisent en réagissant mutuellement au contact l'un avec l'autre ainsi qu'au contact de l'atmosphère.Concretely, the envelope of the thrusters is destroyed. so as to release the propellants. These destroy themselves in interacting with each other as well than in contact with the atmosphere.

Il est connu de mettre en oeuvre à l'intérieur des fusées des canons à poudre tirant un ou plusieurs projectiles perforants en direction des propulseurs.It is known to operate inside rockets powder cannons firing one or more projectiles perforating towards the propellants.

Une telle solution est coûteuse, encombrante et lourde.Such a solution is expensive, cumbersome and cumbersome.

Elle impose la réalisation de projectiles explosifs dotés de systèmes de sécurité et d'un déclenchement à retard.It requires the production of explosive projectiles with security systems and delay release.

L'arme est par ailleurs une mécanique complexe susceptible de défaillance lors du lancement de la fusée.The weapon is also a complex mechanism likely to fail when launching the rocket.

La fiabilité de tels systèmes est donc réduite.The reliability of such systems is therefore reduced.

Il a été proposé de mettre en oeuvre des charges creuses ou des charges explosives pour assurer la destruction des propulseurs, voir à ce dernier sujet le document US-A-550 7231 qui couvre le préambule de la revendication 1.It has been proposed to use shaped charges or explosive charges to ensure the destruction of propellants, see on this last subject document US-A-550 7231 which covers the preamble of claim 1.

Cependant ces charges doivent être positionnées proches, voire au contact des propulseurs à détruire.However these loads must be positioned close, or even in contact with the propellants to be destroyed.

Il se pose donc alors des problèmes d'intégration dans le vecteur. Par ailleurs les jets de charge creuse ont une efficacité réduite contre les propulseurs à ergols liquides. Le jet est consommé rapidement par le liquide et le diamètre des trous de vidange réalisés est faible (de l'ordre du mm). There are therefore problems of integration in the vector. Furthermore, the hollow charge jets have a reduced effectiveness against propellants with liquid propellants. The jet is consumed quickly by the liquid and the diameter drain holes made is low (of the order of mm).

Enfin, la géométrie de la charge utile (satellite) peut différer fortement d'un tir de vecteur à un autre.Finally, the geometry of the payload (satellite) can differ greatly from one vector shot to another.

Les propulseurs ne sont plus alors placés aux mêmes endroits et le vecteur doit être modifié en profondeur pour permettre la mise en place d'un nouveau système de neutralisation.The thrusters are no longer placed at the same locations and the vector needs to be changed in depth to allow the establishment of a new neutralization.

C'est le but de l'invention que de proposer un dispositif de neutralisation ne présentant pas de tels inconvénients.It is the object of the invention to propose a device neutralization not having such drawbacks.

Ainsi le dispositif de neutralisation selon l'invention permet d'assurer d'une façon simple et fiable la destruction d'une charge utile emportée par un vecteur.Thus the neutralization device according to the invention ensures destruction in a simple and reliable way of a payload carried by a vector.

Ce dispositif est facilement adaptable à différents types de charges utiles, il permet donc de simplifier l'adaptation du vecteur à la charge à emporter.This device is easily adaptable to different types payloads, it therefore simplifies adaptation of the vector to the load to be carried.

Ainsi l'invention a pour objet un dispositif de neutralisation d'une charge utile transportée par un vecteur, tel une fusée, caractérisé en ce qu'il comporte au moins une charge explosive génératrice de noyau, charge rendue solidaire du vecteur par des moyens de positionnement assurant une orientation de sa direction d'action vers la charge utile.Thus the subject of the invention is a device for neutralization of a payload transported by a vector, like a rocket, characterized in that it comprises at least one explosive charge generating nucleus, returned charge integral with the vector by positioning means ensuring an orientation of its direction of action towards the payload.

Avantageusement, les moyens de positionnement pourront être réglables de façon à permettre une adaptation du dispositif de neutralisation à différentes structures et/ou localisations de la charge utile.Advantageously, the positioning means may be adjustable to allow adaptation of the neutralization device at different structures and / or payload locations.

Les moyens de positionnement pourront également être fixes.The positioning means may also be fixed.

Le dispositif pourra comporter au moins deux charges explosives génératrices de noyau.The device may include at least two charges explosive nucleus generators.

La ou les charges génératrices de noyau auront de préférence un calibre supérieur à 50 mm.The core-generating charge (s) will have preferably a caliber greater than 50 mm.

Le dispositif de neutralisation selon l'invention s'applique plus particulièrement à la destruction du ou des propulseurs d'un satellite embarqué par une fusée.The neutralization device according to the invention applies more particularly to the destruction of the thrusters of a satellite embarked by a rocket.

L'invention sera mieux comprise à la lecture de la description qui va suivre d'un mode particulier de réalisation, description faite en référence aux dessins annexés et dans lesquels :

  • la figure 1 représente schématiquement une vue partielle d'une fusée emportant un satellite et équipée d'un dispositif de neutralisation selon l'invention,
  • la figure 2 est une vue de la même fusée emportant un satellite d'architecture interne différente.
The invention will be better understood on reading the description which follows of a particular embodiment, description made with reference to the appended drawings and in which:
  • FIG. 1 schematically represents a partial view of a rocket carrying a satellite and equipped with a neutralization device according to the invention,
  • Figure 2 is a view of the same rocket carrying a satellite of different internal architecture.

En se reportant à la figure 1, un vecteur 1 tel une fusée balistique (dont seule la tête est représentée) comporte un logement 2 à l'intérieur de son ogive 3, logement recevant une charge utile 4 constituée par un satellite.Referring to Figure 1, a vector 1 such as a rocket ballistics (of which only the head is represented) includes a housing 2 inside its warhead 3, housing receiving a payload 4 constituted by a satellite.

Le satellite 4 est lié à l'ogive du vecteur par des brides 5a, 5b. D'une façon connue, il est destiné à être libéré sur trajectoire par la fusée à une altitude donnée assurant sa mise en orbite terrestre.Satellite 4 is linked to the vector warhead by flanges 5a, 5b. In a known manner, it is intended to be released on trajectory by the rocket at a given altitude ensuring its launch into Earth orbit.

Les moyens assurant l'ouverture de l'ogive et la libération du satellite ne sont pas représentés ici et ils ne font pas partie de la présente invention.The means ensuring the opening of the warhead and the satellite release is not shown here and they don't are not part of the present invention.

Le satellite 4 renferme un ou plusieurs réservoirs d'ergols liquides. Le satellite représenté à la figure 1 comporte deux réservoirs 6a et 6b superposés et disposés sensiblement au niveau de l'axe 7 de la fusée.Satellite 4 contains one or more tanks liquid propellants. The satellite shown in Figure 1 comprises two tanks 6a and 6b superimposed and arranged substantially at the axis 7 of the rocket.

Les réservoirs 6a, 6b sont reliés à une tuyère 8.The tanks 6a, 6b are connected to a nozzle 8.

Conformément à l'invention des moyens sont prévus permettant de neutraliser les ergols contenus dans les réservoirs 6a, 6b en rompant leurs réservoirs permettant ainsi leur libération.In accordance with the invention, means are provided to neutralize the propellants contained in the tanks 6a, 6b by breaking their tanks allowing thus their release.

Ces moyens sont déclenchés automatiquement en cas d'incident au niveau de la fusée et par exemple en même temps que les moyens classique assurant l'autodestruction de la fusée elle même.These means are triggered automatically in the event incident at the rocket and for example at the same time that the conventional means ensuring the self-destruction of rocket itself.

Les moyens de neutralisation comportent deux charges explosives 9a, 9b génératrices de noyau. Chaque charge 9 est rendue solidaire de la fusée 1 par des moyens de positionnement 10a, 10b qui permettent d'assurer une orientation de la direction d'action 11a, 11b vers la charge utile 4.The neutralization means have two charges explosives 9a, 9b generating the nucleus. Each charge 9 is secured to rocket 1 by means of positioning 10a, 10b which ensure a orientation of the direction of action 11a, 11b towards the load useful 4.

Une charge génératrice de noyau est bien connue de l'Homme du Métier. On pourra par exemple consulter les brevets FR2627580, FR2740212 et FR2741142 qui décrivent une telle charge. Elle comprend un chargement explosif 13 disposé dans une enveloppe 14 et sur lequel est appliqué un revêtement 12 métallique en forme de calotte.A nucleus-generating charge is well known to the Man of the Trade. We can for example consult the patents FR2627580, FR2740212 and FR2741142 which describe a such charge. It includes an explosive charge 13 placed in an envelope 14 and to which is applied a metallic coating 12 in the shape of a cap.

Le chargement explosif 13 est initié par un moyen détonateur 15 qui est relié à un moyen de commande 16.The explosive charge 13 is initiated by a means detonator 15 which is connected to a control means 16.

Les moyens de positionnement 10a, 10b qui sont décrits ici sont conçus de façon à donner un ou deux degrés de liberté à l'enveloppe 14 de la charge qu'ils supportent.The positioning means 10a, 10b which are described here are designed to give one or two degrees of freedom to the envelope 14 of the load they bear.

Il est possible alors de donner à la direction d'action 11 de la charge considérée (qui est confondue avec l'axe de l'enveloppe 14 de la charge) une orientation quelconque par rapport à l'axe 7 de la fusée.It is then possible to give the direction of action 11 of the load considered (which is confused with the axis of the envelope 14 of the load) any orientation by in relation to axis 7 of the rocket.

On pourra à titre d'exemple réaliser des moyens de positionnement comprenant un étrier 17 définissant une direction 18a,18b parallèle à l'axe 7 de la fusée. Cet étrier sera monté pivotant par rapport à une embase 20 fixée à la fusée. Le pivotement s'effectuera ainsi autour de la direction 18a ou 18b (flèche Z).By way of example, it is possible to make means of positioning comprising a stirrup 17 defining a direction 18a, 18b parallel to the axis 7 of the rocket. This stirrup will be pivotally mounted relative to a base 20 fixed to the rocket. The pivoting will thus take place around the direction 18a or 18b (arrow Z).

La charge 9 sera fixée à l'intérieur de l'étrier 17 par l'intermédiaire d'un socle 19 et elle pourra donc elle même être basculée par rapport à l'étrier 17.The load 9 will be fixed inside the stirrup 17 by via a base 19 and it can therefore itself be tilted relative to the bracket 17.

Ainsi ces moyens de positionnement permettent de donner à chaque charge 9 une orientation optimale qui sera adaptée en fonction de la nature et de la structure de la charge utile 4. Concrètement on inclinera chaque charge d'une façon telle que sa direction d'action 11 rencontre un des réservoirs 6 du satellite 4.Thus these positioning means make it possible to give each load 9 an optimal orientation which will be adapted in depending on the nature and structure of the payload 4. Concretely we will tilt each load in such a way that its direction of action 11 meets one of the reservoirs 6 of the satellite 4.

A titre de variante l'étrier 17 pourra être fixe par rapport à l'embase 20, le seul degré de liberté de la charge sera alors son basculement par rapport à l'étrier 17.As a variant, the bracket 17 may be fixed by compared to the base 20, the only degree of freedom of the load will then be its tilting with respect to the stirrup 17.

La charge 9a a ainsi une direction d'action 11a qui est inclinée d'un angle α par rapport à la direction 18a parallèle à l'axe de la fusée 1. Cette direction d'action 11a rencontre le réservoir supérieur 6b.The load 9a thus has a direction of action 11a which is inclined at an angle α to the direction 18a parallel to the axis of the rocket 1. This direction of action 11a meets the upper reservoir 6b.

La charge 9b a une direction d'action 11b qui est inclinée d'un angle β par rapport à la direction 18b parallèle à l'axe de la fusée 1. Cette direction d'action 11b rencontre le réservoir inférieur 6a. The load 9b has a direction of action 11b which is inclined by an angle β relative to the direction 18b parallel to the axis of the rocket 1. This direction of action 11b meets the lower reservoir 6a.

Les charges 9a et 9b sont reliées au moyen de commande 16 qui est destiné à provoquer leur initiation à un instant donné. Ce moyen de commande pourra avantageusement être constitué par une partie de l'électronique de commande / guidage de la fusée.The charges 9a and 9b are connected to the control means 16 which is intended to cause their initiation at a time given. This control means can advantageously be consisting of part of the control electronics / rocket guidance.

L'initiation de la ou des charges 9 sera provoquée sur trajectoire à un instant donné. Cette initiation pourra avantageusement être télécommandée à partir du sol en cas de détection d'un événement grave (rupture de la fusée, perte de trajectoire).The initiation of charge (s) 9 will be caused on trajectory at a given time. This initiation may advantageously be remotely controlled from the ground in case of detection of a serious event (rupture of the rocket, loss of path).

L'initiation pourra également être déclenchée automatiquement par l'électronique de la fusée en cas de perte de la liaison sol (perte du guidage et/ou du contrôle).The initiation may also be triggered automatically by the rocket electronics in case of loss of ground connection (loss of guidance and / or control).

Les charges 9a, 9b ont un diamètre de l'ordre de 50 à 150mm (par exemple 80mm). Leur revêtement pourra être en fer ou en nickel. Elles engendrent comme suite à leur initiation un noyau de métal homocinétique d'environ 100 g et qui est animé d'une vitesse d'environ 2000 m/s.The charges 9a, 9b have a diameter of the order of 50 to 150mm (for example 80mm). Their coating may be of iron or nickel. They generate as a result of their initiation a homokinetic metal core of approximately 100 g which is driven at a speed of around 2000 m / s.

Un tel noyau est stable jusqu'à des distances de l'ordre de 25 m, soit des distances largement supérieures à la distance maximale séparant une charge d'un des réservoirs d'ergol.Such a nucleus is stable up to distances of the order 25 m, i.e. distances far greater than the maximum distance separating a load from one of the tanks propellant.

Les capacités perforantes de ces noyaux ne sont pratiquement pas perturbées par les tôles métallique ou composites ou les protections entourant le satellite.The perforating capacities of these cores are only practically undisturbed by metal sheets or composites or protections surrounding the satellite.

Les réservoirs 6 se trouvent donc perforés par les noyaux ainsi engendrés. Il en résulte une surpression dynamique qui fait exploser les réservoirs.The tanks 6 are therefore perforated by the cores thus generated. This results in a dynamic overpressure which blew up the tanks.

On voit que le dispositif selon l'invention peut être disposé dans la fusée à un endroit relativement éloigné de la charge utile. La vitesse et la stabilité des noyaux permet d'assurer de façon fiable la destruction de la charge utile malgré la distance.It can be seen that the device according to the invention can be placed in the rocket at a location relatively distant from the payload. The speed and stability of the cores allows reliably destroy the payload despite the distance.

Il n'est par ailleurs pas nécessaire de modifier la structure de la charge utile, les noyaux étant suffisamment stables et énergétiques pour assurer la neutralisation des réservoirs au travers des parois du satellite. There is also no need to change the payload structure, the cores being sufficiently stable and energetic to ensure neutralization of tanks through the walls of the satellite.

Le dispositif selon l'invention permet donc, avec une structure simple, compacte et facile à intégrer dans la fusée, d'assurer la destruction sûre de la charge utile et notamment des ergols liquides renfermés dans les réservoirs 6. La fiabilité du dispositif est supérieure à celle des dispositifs existants et à moindre coût.The device according to the invention therefore allows, with a simple structure, compact and easy to integrate into the rocket, to ensure the safe destruction of the payload and especially liquid propellants contained in the tanks 6. The reliability of the device is higher than that of existing devices and at lower cost.

La figure 2 montre une fusée 1 identique à celle précédemment décrite mais emportant un satellite 4 qui a une structure différente.Figure 2 shows a rocket 1 identical to that previously described but carrying a satellite 4 which has a different structure.

Ce satellite comporte deux réservoirs 6a, 6b d'ergols qui sont disposés parallèlement l'un à l'autre et de part et d'autre de l'axe 7.This satellite comprises two tanks 6a, 6b of propellants which are arranged parallel to each other and both and across axis 7.

Les moyens de positionnement 10a et 10b permettent de modifier les orientations des directions d'action 11a et 11b des charges de façon à ce que chaque direction d'action rencontre un réservoir 6a ou 6b.The positioning means 10a and 10b make it possible to modify the orientations of action directions 11a and 11b loads so that each direction of action meets a reservoir 6a or 6b.

Ici, du fait de la position symétrique des réservoirs 6a et 6b par rapport à l'axe 7, les directions d'action 11a et 11b sont inclinées du même angle γ par rapport aux directions 18a/18b définies par les étriers 17 et parallèles à l'axe 7 de la fusée 1.Here, due to the symmetrical position of the tanks 6a and 6b with respect to axis 7, the directions of action 11a and 11b are inclined by the same angle γ with respect to the directions 18a / 18b defined by the stirrups 17 and parallel to the axis 7 of the rocket 1.

On voit donc que grâce à l'invention il est facile d'adapter le dispositif de neutralisation à une structure de charge utile donnée.So we see that thanks to the invention it is easy to adapt the neutralization device to a structure of given payload.

Le réglage des charges sera effectué lors de l'intégration de la charge utile.Load adjustment will be carried out during payload integration.

A titre de variante on pourra bien entendu prévoir un nombre de charges différent.As a variant, it is of course possible to provide a different number of charges.

On pourra également prévoir des moyens de positionnement fixes non réglables assurant une orientation donnée pour la direction d'action de chaque charge.We can also provide positioning means fixed non-adjustable ensuring a given orientation for direction of action of each charge.

Claims (6)

  1. A neutralisation device for a payload (4) carried by a vector (1), such as a rocket, characterised in that it incorporates at least one explosively-formed charge (9a, 9b), such charge made integral with the vector (1) by positioning means (10a, 10b) ensuring the orientation of its direction of action (11a, 11b) towards the payload (4).
  2. A neutralisation device according to Claim 1, wherein the positioning means (10a, 10b) are adjustable to as to allow the neutralisation device to be adapted to different structures and/or locations of the payload (4).
  3. A neutralisation device according to Claim 1, wherein the positioning means (10a, 10b) are immobile.
  4. A neutralisation device according to one of Claims 1 to 3, wherein it incorporates at least two explosively-formed charges (9a, 9b).
  5. A neutralisation device according to one of Claims 1 to 4, wherein the explosively-formed charge or charges (9a, 9b) are of a calibre greater than 50 mm.
  6. Application of a neutralisation device according to one of Claims 1 to 5 to the destruction of the booster or boosters of a satellite (4) carried on board a rocket (1).
EP01958138A 2000-07-26 2001-07-17 Device for neutralising a payload Expired - Lifetime EP1192406B1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR0009813 2000-07-26
FR0009813A FR2812384B1 (en) 2000-07-26 2000-07-26 DEVICE FOR NEUTRALIZING A PAYLOAD
PCT/FR2001/002317 WO2002008684A1 (en) 2000-07-26 2001-07-17 Device for neutralising a payload

Publications (2)

Publication Number Publication Date
EP1192406A1 EP1192406A1 (en) 2002-04-03
EP1192406B1 true EP1192406B1 (en) 2004-11-17

Family

ID=8852948

Family Applications (1)

Application Number Title Priority Date Filing Date
EP01958138A Expired - Lifetime EP1192406B1 (en) 2000-07-26 2001-07-17 Device for neutralising a payload

Country Status (7)

Country Link
US (1) US6718883B2 (en)
EP (1) EP1192406B1 (en)
AT (1) ATE282814T1 (en)
AU (1) AU2001279875A1 (en)
DE (1) DE60107181T2 (en)
FR (1) FR2812384B1 (en)
WO (1) WO2002008684A1 (en)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7690287B2 (en) * 2006-07-18 2010-04-06 Maegerlein Stephen D Explosive neutralizer and method
WO2009045619A1 (en) * 2007-07-30 2009-04-09 Thomas Blake K Shaped charge fuse booster system for dial lethality in reduce collateral damage bombs (rcdb) that include penetrating warheads of warheads with high explosives that are difficult to ignite
DE102012110450B4 (en) * 2012-10-31 2014-07-17 Deutsches Zentrum für Luft- und Raumfahrt e.V. Object for a mission into space
DE102016219627A1 (en) * 2016-10-10 2018-04-12 Bayerische Motoren Werke Aktiengesellschaft UNMANUFACTURED AIRCRAFT, ENERGY STORAGE MODULE AND METHOD FOR CONTROLLING AN UNMANUFACTURED AIRCRAFT

Family Cites Families (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3382800A (en) * 1964-11-09 1968-05-14 Navy Usa Linear-shaped charge chemical agent disseminator
CH526764A (en) * 1970-07-17 1972-08-15 Oerlikon Buehrle Ag Bullet with a bullet jacket
US3707918A (en) * 1971-02-26 1973-01-02 Susquehanna Corp Aerosol disseminator
US3913483A (en) * 1972-08-11 1975-10-21 Us Army Grenade with fuze
CH580798A5 (en) * 1974-05-24 1976-10-15 Contraves Ag
US3995549A (en) * 1975-03-17 1976-12-07 The United States Of America As Represented By The Secretary Of The Navy Rocket/missile motor explosive insert detonator
DE3048617A1 (en) * 1980-12-23 1982-07-22 Dynamit Nobel Ag, 5210 Troisdorf COMBAT HEAD WITH SECONDARY BODIES AS A PAYLOAD
US4459915A (en) * 1982-10-18 1984-07-17 General Dynamics Corporation/Convair Div. Combined rocket motor warhead
US4961382A (en) * 1986-05-27 1990-10-09 Motorola, Inc. Penetrating projectile having a self-destructing piercing front end
USH345H (en) * 1987-03-30 1987-10-06 The United States Of America As Represented By The Secretary Of The Army Missile canting shaped charge warhead
FR2627580B1 (en) 1988-02-18 1993-02-19 France Etat Armement PROCESS FOR OBTAINING A CORE COMPRISING STABILIZING FINS AND APPLIED MILITARY LOAD
US5203844A (en) * 1989-10-05 1993-04-20 Leonard Byron P Multiple payload/failure mode launch vehicles
US5565647A (en) * 1991-05-24 1996-10-15 Giat Industries Warhead with sequential shape charges
US5271330A (en) * 1991-09-27 1993-12-21 General Dynamics Corporation, Convair Division Oxygen enhanced cruise missile weapon system
US5817969A (en) * 1994-08-26 1998-10-06 Oerlikon Contraves Pyrotec Ag Spin-stabilized projectile with payload
US5507231A (en) * 1994-10-13 1996-04-16 Thiokol Corporation Solid fuel launch vehicle destruction system and method
FR2740212B1 (en) 1995-10-20 1997-12-05 Giat Ind Sa EXPLOSIVE CHARGE GENERATOR OF CORE
FR2741142B1 (en) 1995-11-13 1998-01-02 Giat Ind Sa CORE GENERATOR LOAD HAVING IMPROVED ACCELERATION RESISTANCE
EP0794405B1 (en) * 1996-03-08 2001-09-05 Diehl Stiftung & Co. Method and device for dispersing a large caliber payload above a target
US6279482B1 (en) * 1996-07-25 2001-08-28 Trw Inc. Countermeasure apparatus for deploying interceptor elements from a spin stabilized rocket

Also Published As

Publication number Publication date
US20020134271A1 (en) 2002-09-26
EP1192406A1 (en) 2002-04-03
US6718883B2 (en) 2004-04-13
AU2001279875A1 (en) 2002-02-05
DE60107181T2 (en) 2005-12-08
DE60107181D1 (en) 2004-12-23
FR2812384A1 (en) 2002-02-01
ATE282814T1 (en) 2004-12-15
FR2812384B1 (en) 2002-12-06
WO2002008684A1 (en) 2002-01-31

Similar Documents

Publication Publication Date Title
EP3150957B1 (en) Artillery projectile having a piloted phase
EP2923171B1 (en) Spin-stabilised projectile that expels a payload
EP0800054B1 (en) Projectile the warhead of which is triggered by means of a target designator
EP1045221B1 (en) Aerodynamic brake for reducing the velocity of a projectile on its trajectory
EP0438343B1 (en) Penetrator ammunition for targets with high mechanical resistance
FR2873194A1 (en) DEVICE FOR SHOOTING PROJECTILES
EP1192406B1 (en) Device for neutralising a payload
EP0918205B1 (en) Projectile having radial direction of action
EP2522895B1 (en) Device for bleeding a tank of a space system
FR2789484A1 (en) Non-lethal self-defense weapon, for person under attack, consists of projectile containing inflatable balloon, which is deployed by explosive charge on hitting target
EP0943887B1 (en) Conversion kit enabling the conversion of an explosive projectile to a concrete piercing projectile and projectile obtained by conversion
EP1521053B1 (en) Anti-bunker ammunition
FR2552871A1 (en) Anti-tank projectile acting at the deviation speed
EP0724132B1 (en) Safety and arming device for a projectile fuse
EP1000312B1 (en) Countermeasure ammunition
EP1302741B1 (en) High explosive projectile
EP3462121A1 (en) Ammunition for non-lethal protection of a platform and non-lethal protection device using such ammunition
EP3910280A1 (en) Device for detecting absence of mechanical barrier for a missile and missile comprising such a device
WO2003040645A1 (en) Explosive device comprising numerous components
FR2742539A1 (en) Multi-purpose explosive charge, e.g. for detonating mines
CA2179929C (en) Missile launching and steering system
EP2383539B1 (en) Priming device with electric initiation for a projectile
FR2832498A1 (en) Anti-missile launcher for armored vehicle has launcher tubes releasably mounted on turntable attached to the vehicle that is controlled in response to hostile missile detection
EP1565703A2 (en) Method of correcting the trajectory of a spin-stabilised projectile and projectile implementing one such method
FR2856788A1 (en) Multiple-effect munition with shaped explosive charges, primer systems and fragmentation casing, includes second annular explosive charge initiated by second primer system

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20020109

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE TR

AX Request for extension of the european patent

Free format text: AL;LT;LV;MK;RO;SI

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AT BE CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE TR

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20041117

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT;WARNING: LAPSES OF ITALIAN PATENTS WITH EFFECTIVE DATE BEFORE 2007 MAY HAVE OCCURRED AT ANY TIME BEFORE 2007. THE CORRECT EFFECTIVE DATE MAY BE DIFFERENT FROM THE ONE RECORDED.

Effective date: 20041117

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20041117

Ref country code: GB

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20041117

Ref country code: IE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20041117

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20041117

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20041117

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: FRENCH

REF Corresponds to:

Ref document number: 60107181

Country of ref document: DE

Date of ref document: 20041223

Kind code of ref document: P

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20050217

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20050217

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20050217

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20050228

NLV1 Nl: lapsed or annulled due to failure to fulfill the requirements of art. 29p and 29m of the patents act
GBV Gb: ep patent (uk) treated as always having been void in accordance with gb section 77(7)/1977 [no translation filed]

Effective date: 20041117

REG Reference to a national code

Ref country code: IE

Ref legal event code: FD4D

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20050717

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20050717

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20050731

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20050731

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20050731

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20050731

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20050818

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

BERE Be: lapsed

Owner name: *GIAT INDUSTRIES

Effective date: 20050731

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20050417

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20090721

Year of fee payment: 9

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20090707

Year of fee payment: 9

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20110331

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20110201

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 60107181

Country of ref document: DE

Effective date: 20110201

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20100802