EP3156757A1 - Systeme d'arme et procede de fonctionnement d'un systeme d'arme - Google Patents

Systeme d'arme et procede de fonctionnement d'un systeme d'arme Download PDF

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Publication number
EP3156757A1
EP3156757A1 EP16187955.6A EP16187955A EP3156757A1 EP 3156757 A1 EP3156757 A1 EP 3156757A1 EP 16187955 A EP16187955 A EP 16187955A EP 3156757 A1 EP3156757 A1 EP 3156757A1
Authority
EP
European Patent Office
Prior art keywords
magazine
support structure
missile
weapon
weapon system
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.)
Granted
Application number
EP16187955.6A
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German (de)
English (en)
Other versions
EP3156757B1 (fr
Inventor
Dieter Wagner
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.)
MBDA Deutschland GmbH
Original Assignee
MBDA Deutschland GmbH
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 MBDA Deutschland GmbH filed Critical MBDA Deutschland GmbH
Publication of EP3156757A1 publication Critical patent/EP3156757A1/fr
Application granted granted Critical
Publication of EP3156757B1 publication Critical patent/EP3156757B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • 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.
  • 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, on 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.
  • 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 preferably has a fourth magazine.
  • the fourth magazine comprises a multiplicity of combat bodies and / or sensor modules, it being possible to attach a warhead and / or a dispensable sensor module which can be issued from the fourth magazine to the carrier structure which can be removed from the storage device.
  • the guided missile obtainable by means of the weapon system can thus either fly a reconnaissance mission by providing no warhead or 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 for the removal of support structures the storage device and / or for further transporting the missile is provided.
  • 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.
  • the weapon system is further characterized by a shape for inserting at least the support structure.
  • a volume is umsch Whitneybar, which can be filled with a 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.
  • 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. That way is ensures that a guided 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.
  • the provision of the support structure As a further step, the provision of the support structure.
  • the carrier structure is particularly advantageously removed from the storage device and provided for further assembly.
  • 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.
  • a filling of gaps of the support structure with a filling material is particularly advantageous.
  • hardening of the filling material is particularly advantageous.
  • a missile is created.
  • the guided missile is ready for 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.
  • the weapon carrier system may in particular be an air-bound or ground-based vehicle, as well as a stationary launch unit for the guided 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. Should only one Enlightenment flight are performed with the missile, so selecting and attaching the warhead is not necessary and it is advantageously mounted instead of the warhead, an additional sensor module.
  • 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.
  • a plurality of sensor modules may be present. 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, each different drive and steering module. 8 at least once exists.
  • 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 support structures 9 are in particular Such support structures are available, which are suitable for different Whylea systeme.
  • a power supply is integrated in the electronics 12 or in the drive and steering modules 8.
  • 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, filling the volume enclosed by the mold 6 with the filling material 13 will fill all interstices of the support structure 9 with the filling material 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 is the outer skin 15 different in their shape and can therefore be adapted to a planned mission of the 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, 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. Thus, a missile is almost completely manufactured. By assembling the individual components it is already possible that 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 guided missile 10 is electrically supplied via the electrical interface to the weapon carrier system 17 of the support structure 9 and tested by means of a test 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 cover 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 number 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 characteristics, and made into a finished missile composed.
  • 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)
  • Chemical & Material Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • Manufacturing & Machinery (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
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

Publications (2)

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

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ID=56893830

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Application Number Title Priority Date Filing Date
EP16187955.6A Active EP3156757B1 (fr) 2015-10-15 2016-09-09 Système d'arme et procédé de fonctionnement d'un système d'arme

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EP (1) EP3156757B1 (fr)
DE (1) DE102015013349B4 (fr)

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6227096B1 (en) * 1999-06-22 2001-05-08 The Boeing Company Universal warhead adapter, and missile and method incorporating same
US7506587B1 (en) * 2007-02-20 2009-03-24 The United States Of Americas As Represented By The Secretary Of The Navy Modular projectile system
DE102010052202A1 (de) * 2010-07-08 2012-01-12 Diehl Bgt Defence Gmbh & Co. Kg Verfahren zum Steuern eines Gefechtsflugkörpers
US20150247714A1 (en) * 2012-04-25 2015-09-03 Wilcox Industries Corp. Modular rocket system

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA1059487A (fr) 1976-05-18 1979-07-31 Stephen J. Lane Charpente de faible poids et de grande resistance
US6260797B1 (en) * 1998-01-13 2001-07-17 Science Applications International Corporation Transformable gun launched aero vehicle
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
DE102006013402B4 (de) * 2006-03-23 2011-04-21 Deutsches Zentrum für Luft- und Raumfahrt e.V. Modulares unbemanntes Fluggerät
EP2377757B1 (fr) 2010-04-19 2013-05-29 Gatewing NV Drone
DE102010025202A1 (de) 2010-06-26 2011-12-29 Gm Global Technology Operations Llc (N.D.Ges.D. Staates Delaware) Karosserie für ein Kraftfahrzeug
DE102011109693B3 (de) 2011-08-06 2012-09-13 Lfk-Lenkflugkörpersysteme Gmbh Strukturkomponente für ein operationelles Flugkörpersystem

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6227096B1 (en) * 1999-06-22 2001-05-08 The Boeing Company Universal warhead adapter, and missile and method incorporating same
US7506587B1 (en) * 2007-02-20 2009-03-24 The United States Of Americas As Represented By The Secretary Of The Navy Modular projectile system
DE102010052202A1 (de) * 2010-07-08 2012-01-12 Diehl Bgt Defence Gmbh & Co. Kg Verfahren zum Steuern eines Gefechtsflugkörpers
US20150247714A1 (en) * 2012-04-25 2015-09-03 Wilcox Industries Corp. Modular rocket system

Also Published As

Publication number Publication date
DE102015013349B4 (de) 2023-05-17
DE102015013349A1 (de) 2017-04-20
EP3156757B1 (fr) 2018-11-14

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