EP3156757B1 - Système d'arme et procédé de fonctionnement d'un système d'arme - Google Patents

Système d'arme et procédé de fonctionnement d'un système d'arme Download PDF

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Publication number
EP3156757B1
EP3156757B1 EP16187955.6A EP16187955A EP3156757B1 EP 3156757 B1 EP3156757 B1 EP 3156757B1 EP 16187955 A EP16187955 A EP 16187955A EP 3156757 B1 EP3156757 B1 EP 3156757B1
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EP
European Patent Office
Prior art keywords
magazine
weapon
guided missile
carrier
carrier structure
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EP16187955.6A
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German (de)
English (en)
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EP3156757A1 (fr
Inventor
Dieter Wagner
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MBDA Deutschland GmbH
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MBDA Deutschland GmbH
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Publication of EP3156757A1 publication Critical patent/EP3156757A1/fr
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B33/00—Manufacture of ammunition; Dismantling of ammunition; Apparatus therefor
    • F42B33/001—Devices or processes for assembling ammunition, cartridges or cartridge elements from parts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles

Definitions

  • the present invention relates to a weapon system.
  • the invention relates to a weapon system comprising a guided missile.
  • the invention further relates to a method for operating a weapon system.
  • missiles From the prior art missiles are known. In this case, missiles must always be stored after production. If guided missiles are used, a guided missile can be taken from the bearing in order to launch it for acting on a target. Existing missiles are built for a specific target spectrum and adapted to different weapon carriers. Adjustments can only be made in the context of new developments of guided missiles, which is associated with considerable costs and long development times.
  • the US Pat. No. 7,506,587 B1 describes a modular weapon system with a selection of seekers, a selection of payloads, a selection of drive modules, and a selection of rod-shaped cores. A seeker head, a payload and a drive module can each be plugged onto the core.
  • the US 6,227,096 B1 describes an adapter for constructing a missile with a tubular sleeve body. Inside the sleeve body a warhead is mountable. Further, a rear part and a front part can be mounted at opposite ends of the sleeve body.
  • a weapon system comprising a first magazine, a second magazine and a third magazine and a storage device.
  • the first magazine comprises a plurality of seekers for a missile.
  • the second magazine includes a plurality of drive and steering modules for a missile.
  • the third magazine includes a variety of electronics for a guided missile.
  • a plurality of support structures for a missile is storable. It is provided that a carrier structure can be removed from the storage device, to which a search head which can be output from the first magazine, a drive and steering module which can be output from the second magazine, and electronics which can be output from the third magazine can be attached in order to obtain a guided missile.
  • the weapon system according to the invention thus a plurality of individual components for a guided missile is vorhaltbar.
  • the first magazine, the second magazine, and the third magazine may be magazines, each comprising a wide variety of different seekers, drive and steering modules, and electronics.
  • magazines each comprising a wide variety of different seekers, drive and steering modules, and electronics.
  • the missile is assembled according to a modular principle. In this way, the missile is in particular assembled shortly before its use, whereby the missile can be optimally adapted to a planned mission.
  • the individual magazines also the individual components of the missile are safely and reliably stored. By attaching to the support structure of the missile is fast, easy and inexpensive to produce.
  • the weapon system further comprises a filler material and a mold for inserting at least the carrier structure.
  • a filler material With the form a volume is umschffybar, which can be filled with the filling material.
  • the partially made of support structure and at least from seeker, drive and steering module, electronics and support structure missile can be provided with an additional filler.
  • the filling material permits protection of the individual components of the guided missile against external influences.
  • the dependent claims have advantageous developments of the invention to the content.
  • the weapon system preferably has a fourth magazine.
  • the fourth magazine comprises a plurality of warheads and / or sensor modules, wherein at the From the storage device removable support structure a dispensable from the fourth magazine warhead and / or a dispensable sensor module can be attached.
  • the guided missile obtainable by means of the weapon system can thus either fly a reconnaissance mission by not providing a warhead or a sensor module, or alternatively or additionally act on a target by using a corresponding warhead from the fourth repository.
  • the fourth magazine may in turn have a plurality of different elements, in particular a plurality of different warheads and / or sensor modules, so that a plurality of different missiles can be produced.
  • the weapon system is preferably characterized by a gripper arm, wherein the gripper arm makes it possible to attach the seeker head and / or the drive and steering module and / or the electronics and / or the warhead and / or sensor module to the carrier structure.
  • each magazine has its own gripping arm.
  • a gripping arm is provided for removing carrier structures from the storage device and / or for further transporting the guided missile.
  • the weapon system has a plurality of gripping arms, so that assembly of the missile from the seeker head, the drive and steering module, the electronics and / or the warhead and / or sensor module is performed fully automatically on the support structure.
  • At least one intermediate space of the carrier structure can be filled with the filling material.
  • all intermediate spaces of the carrier structure with the filling material can be filled.
  • an outer skin of the guided missile is at least partially formed by outer surfaces of the support structure or by the filling element.
  • a shape of the outer skin of the missile is adaptable by different shaping of the filling material. This allows the missile to design very flexible.
  • the filling material is advantageously a hardenable foam material.
  • the curable foam material allows for easy filling of gaps of the support structure, so that all interstices of the support structure can be filled safely and reliably. In this way it is ensured that a steering missile is manufacturable, which in particular has no cavities.
  • the hardenability of the foam material ensures that a robust missile is present.
  • the curable foam material forms a safe and reliable insulation of the components of the guided missile against external environmental influences.
  • each carrier structure is designed to be attached to a special weapon carrier system.
  • at least one carrier structure per weapon carrier system can be stored in the storage device.
  • the carrier structure has in particular a mechanical and an electrical interface to the weapon carrier system. About the mechanical interface of the missile with the weapon carrier system is mechanically, via the electrical interface of the missile is electrically connected to the weapon carrier system.
  • the invention further relates to a method for operating a weapon system.
  • the weapon system is particularly advantageous the weapon system described above.
  • the method comprises the following steps: First, the selection of a support structure, a seeker head, a drive and steering module and an electrical system takes place. In particular, said elements are selected after a planned mission for a future guided missile. As a further step the provision of the support structure takes place.
  • the carrier structure is particularly advantageously removed from the storage device and provided for further assembly. Subsequently, the attachment of the seeker head, the drive and steering module and the electrics, which were previously selected, takes place on the support structure.
  • a semi-finished missile is present in a shell.
  • This missile under construction is advantageously already testable for its functionality, so that defective components may be interchangeable.
  • the carrier body is inserted into a mold. Subsequently, filling of a volume enclosed by the mold with a filling material and thereby filling of gaps of the support structure with a filling material takes place. In addition, hardening of the filling material is particularly advantageous. In this way, a missile is created.
  • the guided missile is ready to use and can be used to combat a target.
  • the guided missile is used for acting on a target.
  • the inventive method advantageously allows the final assembly of the missile only immediately before the actual use for acting on a target.
  • the weapon system can be used to combat different targets because of the possibility of manufacturing different missiles.
  • the described steps are advantageously carried out in less than five minutes. This ensures that a goal can be tackled quickly and effectively.
  • the method comprises the following steps: Before selecting, an environment is clarified, as well as an identification of a destination.
  • the enlightenment step can be carried out, in particular, by transmitting reconnaissance data to the weapon system.
  • the use of the guided missile comprises the following steps: First of all, the steering missile is attached to a weapon carrier system.
  • the weapon carrier system may be equipped with the guided missile manufactured by the weapon system.
  • Mariaffysystem may in particular be an airborne or ground-based vehicle, as well as a stationary start unit for the missile. Subsequently, the guided missile is launched by the weapon carrier system for acting on the target.
  • the step of selecting comprises selecting a carrier structure, a seeker head, a drive and steering module, and electronics as well as selecting a warhead.
  • the step of mounting the electronics, the seeker head, and the drive and steering module also includes attaching the warhead to the support structure. In this way, a warhead adapted to a current mission can be used. If only an reconnaissance flight is to be carried out with the guided missile, selecting and attaching the warhead is not necessary and an additional sensor module is advantageously installed instead of the warhead.
  • FIG. 1 schematically shows an image of a weapon system 1 according to an embodiment of the invention.
  • the weapon system 1 comprises a first magazine 2, a second magazine 3, a third magazine 4 and a fourth magazine 5.
  • a plurality of seekers 7 is present, in the second magazine 3, a plurality of drive and steering modules eighth , in the third magazine 4 a plurality of electronics 12 and in the fourth magazine 5 a plurality of warheads 11.
  • the fourth magazine 5 may alternatively or additionally be present a plurality of sensor modules. In this way, either a warhead 11 or a sensor module can be used, whereby either a mission for acting on a target or a recon mission can be performed.
  • the weapon system 1 has a bearing device, not shown, in which a plurality of support structures 9 are storable.
  • the first magazine 2 comprises a plurality of different seekers 7, each different seeker 7 is present at least once in the first magazine 2.
  • the second magazine 3 has a plurality of different drive and steering modules 8, wherein each different drive and steering module 8 is present at least once.
  • a plurality of different electronics 12 are present, each of the different electronics 12 is present at least once.
  • the fourth magazine 5 a plurality of different warheads 11 and / or sensor modules is present, each different warhead 11 and / or each sensor module is present at least once.
  • a multiplicity of different carrier structures 9 are present in the storage device, each different carrier structure 9 being present at least once.
  • the weapon system 1 allows the production of different missiles 10 (see. FIG. 2 ).
  • the different seekers 7 may be infrared seekers, TV seekers, radar seekers, 3D seekers, or mixed seekers, with mixed seekers comprising at least two of the aforementioned seeker head systems.
  • the warheads 11 provision is made in particular for shaped charges, penetrators, splinter charges, gas charges or no charges whatsoever. In the latter case, only a mass dummy is present, which serves as a balance weight.
  • the warhead 11 and / or the sensor module can be adapted to different goals. If the guided missile 10 only fly a reconnaissance flight, then no warhead 11 is necessary, using a sensor module instead.
  • the sensor module can be an HD camera, a 3D camera or an indulgent camera.
  • the electronics 12 provision is made in particular for GPS navigation electronics or inertial navigation electronics to be present. In inertial navigation systems, in particular, such systems with low precision and such systems with high precision are available. In addition, it is preferably provided that combinations of GPS navigation electronics and Inertialnavigationselektroniken, optionally with low precision or with high precision, are available.
  • the third magazine 4 on a variety of different electronics 12, which are usable for the manufacture of the missile 10.
  • the drive and steering modules 8 in particular, such modules are available for short ranges, for medium ranges and for long ranges.
  • the carrier structures 9 in particular those carrier structures are present which are suitable for different weapon carrier systems.
  • a power supply in the electronics 12 or in the drive and steering modules 8 is integrated.
  • the first magazine 2, the second magazine 3, the third magazine 4 and the fourth magazine 5 are advantageously in the order, in particular immediately, juxtaposed, in which the seeker 7, the drive and steering module 8, the electronics 12 and the warhead 11 are arranged on the guided missile 10.
  • the said components are not to be transported over long distances, but can be attached to the carrier structure 9 immediately after being dispensed from the respective magazine 2, 3, 4, 5.
  • the bearing device for the support structure 9 is in particular mounted above or below said magazines 2, 3, 4, 5.
  • the weapon system 1 also has a mold 6. At least the support structure 9 can be inserted into the mold 6. In addition, with the mold 6, a volume can be enclosed, which can be filled with a filling material 13. If the support structure 9 is inserted into the mold 6, then filling the volume enclosed by the mold 6 with the filling material 13 will fill all the gaps between the molds Carrier structure 9 with the filler 13. This is off FIG. 2 seen. So is in FIG. 2 a section through a guided missile 10 is shown, wherein it can be seen that all interspaces of the support structure 9 are filled with the filling material 13. In this way, a guided missile 10 is present, which is in particular full-volume and has no voids. Thus, the guided missile 10 has a high stability.
  • the filling material 13 By the filling material 13, at least the warhead 11 and the electronics 12 are completely enclosed. In this way, the filling material 13 is an insulation for the warhead 11 and for the electronics 12 against external environmental influences.
  • an outer skin 15 of the guided missile 10 is formed at least in the region of the support structure 9 by the filling material. In this way, the outer skin 15 can be fixed differently in shape and can therefore be adapted to a planned mission of the guided missile 10.
  • the shape of the outer skin 15 is determined in particular by the surface of the inner side of the mold 6.
  • the support structure 9 advantageously has a wiring 14 of the guided missile 10. Thus, it is provided in particular that no additional wiring must be made. Particularly advantageous is done with the attachment of the seeker head 7, the drive and steering module 8, the electronics 12 and the warhead 11 is an automatic contacting of the respective elements with the wiring 14.
  • the wiring 14 is also advantageously, in particular completely surrounded by the filler 13 so that the wiring 14 is protected from environmental influences.
  • the support structure 9 advantageously has an electrical interface to the weapon support system 17, which is connected via the wiring 14 to the electronics 12. The transmission of the mission information to the guided missile 10 is particularly advantageous via this interface.
  • the carrier structure 9 advantageously has a mechanical interface to the weapon carrier system 17.
  • the mechanical attachment advantageously has a triggering mechanism which is designed so that the guided missile 10, in particular through the weapon carrier system 17, can be released from the weapon carrier system 17.
  • FIG. 3 schematically shows the sequence of a method according to an embodiment of the invention.
  • the method is carried out with the weapon system 1 as described above.
  • an enlightenment 100 of an area to be monitored takes place.
  • Different educational methods can be used.
  • a drone 19 flies over the reconnaissance area.
  • a target 18 is identified. This target 18 should be fought by the weapon system 1.
  • the next step is to select 200 a support structure 9, a seeker head 7, a drive and steering module 8, an electronics 12 and a warhead 11. From all these components, a missile 10 is to be assembled.
  • the weapon system 1 proposes, based on reconnaissance data from the reconnaissance step 100, an optimum composition of the individual components for manufacturing the guided missile 10.
  • the support structure 9 is selected according to specification of a weapon carrier system 17 which is to carry the guided missile 10.
  • the attachment 400 of the seeker head 7, the warhead 11 and / or the sensor module, the electronics 12 and the drive and steering module 8, which were selected in the selection step 200, takes place. All of these components are attached to the support structure 9.
  • a missile is almost completely manufactured.
  • a functional test can be carried out. In this way, defective elements can be identified so that they can be replaced in the event of a fault.
  • the missile 10 is about the electrical interface to the weapon carrier system 17 of the support structure 9 is electrically supplied and tested by means of a testing software.
  • the testing software preferably runs in the storage device or in the first magazine 2 or the second magazine 3 or the third magazine 4 or the fourth magazine 5.
  • a filling 500 of spaces of the support structure 9 is carried out with a filling material.
  • a filling material 13 For this purpose, at least the support structure 9 is inserted into a mold 6, wherein the volume enclosed by the mold 6 is filled with the filling material 13. In this way, all the interstices of the support structure 9 can be filled, so that a full-volume missile 10 is formed.
  • the filling material 13 also forms a protective covering for at least the warhead 11 and the electronics 12, which are advantageously completely surrounded by the filling material 13.
  • the filling material 13 forms, at least in sections, an outer skin 15 of the guided missile 10, at least in the region of the carrier structure 9, so that the outer skin 15 of the guided missile 10 can be fixed by means of a surface of the mold 6.
  • a curable foam material is used in particular.
  • the attachment 600 of the guided missile 10 to a weapon carrier system 17 is carried out.
  • the weapon carrier system 17 may in particular be a stationary or a mobile weapon carrier system.
  • the weapon carrier system 17 is a mobile aircraft.
  • the launch 700 of the guided missile takes place from the weapon carrier system.
  • the weapon system 1 allows rapid and safe combat of the target 18, since the missile 10 is tailored specifically to the mission to combat the specific target 18.
  • the final assembly of the missile 10 immediately prior to the use of the missile 10 is also avoided that a large variety of different missiles 10 must be provided. Thus, in particular storage capacities are relieved.
  • the invention achieves a new flexibility with regard to the possible use which does not make possible previous missiles.
  • seekers, active agents, engines, so that in particular speed and / or range, and / or control systems of different types can be combined task-oriented.
  • the individual components are taken from magazines, equipped with the different forms, and assembled into a finished guided missile.
  • the different carrier structures 9 make it possible to shoot the guided missile 10 from different weapon carrier systems 17.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Manufacturing & Machinery (AREA)
  • Chemical & Material Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Claims (14)

  1. Système d'arme (1) comprenant :
    - un premier chargeur (2) comprenant une pluralité de têtes de détection (7) pour un missile téléguidé (10),
    - un deuxième chargeur (3) comprenant une pluralité de modules d'entraînement et de guidage (8) pour un missile téléguidé (10),
    - un troisième chargeur (4) comprenant une pluralité d'unités électroniques (12) pour un missile téléguidé (10),
    - un dispositif de stockage pour une pluralité de structures porteuses (9) pour un missile téléguidé (10), une structure porteuse (9) étant extractible du dispositif de stockage, sur laquelle une tête de détection (7) apte à être sortie hors du premier chargeur (2), un module d'entraînement et de guidage (8) apte à être sorti hors du deuxième chargeur (3) et une unité électronique (12) apte à être sortie du troisième chargeur (4) peuvent être placés afin d'obtenir un missile téléguidé (10),
    - un matériau de remplissage (13),
    - un moule (6) destiné au montage d'au moins la structure porteuse (9), dans lequel un volume peut être entouré par le moule (6), lequel est remplissable avec le matériau de remplissage (13).
  2. Systèmes d'arme (1) selon la revendication 1, caractérisé par un quatrième chargeur (5) comprenant une pluralité de têtes de combat (11) et/ou de modules de capteur et/ou de dummies de masse, une tête de combat (11) apte à être sortie du quatrième chargeur (5) et/ou un module de capteur apte à être sorti du quatrième chargeur (5) et/ou un dummy de masse apte à être sorti du quatrième chargeur (5) pouvant être montés sur la structure porteuse (9) extractible du dispositif de stockage.
  3. Système d'arme (1) selon l'une quelconque des revendications précédentes, caractérisé en ce que le premier chargeur (2), le deuxième chargeur (3), le troisième chargeur (4) et le quatrième chargeur (5) sont disposés dans l'ordre, notamment directement l'un à côté de l'autre, dans lequel la tête de détection (7), le module d'entraînement et de guidage (8), l'unité électronique (12) et la tête de combat (11) sont disposés sur le missile téléguidé (10).
  4. Système d'arme (1) selon l'une quelconque des revendications précédentes, caractérisé par au moins un bras préhenseur (16) destiné à monter la tête de détection (7) et/ou le module d'entraînement et de guidage (8) et/ou l'unité électronique (12) et/ou la tête de combat (11) sur la structure porteuse (9).
  5. Système d'arme (1) selon l'une quelconque des revendications précédentes, caractérisé en ce que des espaces intermédiaires de la structure porteuse (9) peuvent être remplis avec le matériau de remplissage (13) .
  6. Système d'arme (1) selon l'une quelconque des revendications précédentes, caractérisé en ce qu'une peau extérieure (15) du missile téléguidé (10) peut être fabriquée au moins par sections par des surfaces extérieures de la structure porteuse (9) ou par le matériau de remplissage (13).
  7. Système d'arme (1) selon l'une quelconque des revendications précédentes, caractérisé en ce que le matériau de remplissage (13) est un matériau en mousse durcissable.
  8. Système d'arme (1) selon l'une quelconque des revendications précédentes, caractérisé en ce que différentes structures porteuses (9) sont stockées dans le dispositif de stockage, les différentes structures porteuses (9) pouvant être montées sur différents systèmes de support d'arme (17).
  9. Système d'arme (1) selon la revendication 8, caractérisé en ce que la structure porteuse (9) présente une interface électrique vers un système respectif de support d'arme (17).
  10. Système d'arme (1) selon la revendication 8 ou 9, caractérisé en ce que la structure porteuse (9) présente une interface mécanique vers un système respectif de support d'arme (17) doté d'un mécanisme de verrouillage et de déclenchement.
  11. Système d'arme (1) selon l'une quelconque des revendications précédentes, caractérisé en ce que le dispositif de stockage est monté au-dessus ou en dessous du premier chargeur (2) et/ou du deuxième chargeur (3) et/ou du troisième chargeur (4) et/ou notamment du quatrième chargeur (5).
  12. Procédé de fonctionnement d'un système d'arme (1), notamment du système d'arme (1) selon l'une quelconque des revendications précédentes, caractérisé par les étapes de :
    - sélection (200) d'une structure porteuse (9), d'une tête de détection (7), d'un module d'entraînement et de guidage (8) et d'une unité électronique (12),
    - fourniture (300) de la structure porteuse (9) sélectionnée,
    - montage (400), sur la structure porteuse (9) fournie, de la tête de détection (8) sélectionnée, du module d'entraînement et de guidage (8) sélectionné et de l'unité électronique (12) sélectionnée,
    - insertion de la structure porteuse (9) dans un moule (6),
    - remplissage, avec un matériau de remplissage (13), d'un volume entouré par le moule (6) et ainsi remplissage (500) d'espaces intermédiaires de la structure porteuse (9) avec le matériau de remplissage (13),
    - durcissement du matériau de remplissage (13), sur quoi un missile téléguidé (10) est obtenu, et
    - utilisation du missile téléguidé (10) pour agir sur une cible (18).
  13. Procédé selon la revendication 12, caractérisé
    - en ce qu'avant la sélection (200), une reconnaissance (100) d'environs et une identification d'une cible (18) ont lieu, et
    - l'utilisation du missile téléguidé (10) comprenant :
    montage (600) du missile téléguidé (10) sur un système de support d'arme (17), et
    démarrage (700) du missile téléguidé (10) du système de support d'arme (17) pour agir sur la cible (18).
  14. Procédé selon l'une quelconque des revendications 12 ou 13, caractérisé
    - en ce que l'étape de la sélection (200) comprend la sélection supplémentaire d'une tête de combat (11) et/ou d'un module de capteur et/ou d'un dummy de masse, et
    - en ce que l'étape du montage (400) comprend le montage supplémentaire sur la structure porteuse (9) fournie de la tête de combat (11) sélectionnée et/ou du module de capteur sélectionné et/ou du dummy de masse sélectionné.
EP16187955.6A 2015-10-15 2016-09-09 Système d'arme et procédé de fonctionnement d'un système d'arme Active EP3156757B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102015013349.7A DE102015013349B4 (de) 2015-10-15 2015-10-15 Verfahren zum Betreiben eines Waffensystems

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EP3156757A1 EP3156757A1 (fr) 2017-04-19
EP3156757B1 true EP3156757B1 (fr) 2018-11-14

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FR2803911B1 (fr) 2000-01-19 2002-11-29 Giat Ind Sa Conteneur pour munitions de gros calibre
US7418905B2 (en) 2003-12-19 2008-09-02 Raytheon Company Multi-mission payload system
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EP3156757A1 (fr) 2017-04-19
DE102015013349B4 (de) 2023-05-17
DE102015013349A1 (de) 2017-04-20

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