EP3156756A1 - Missile guide et procede de fabrication d'un missile guide - Google Patents

Missile guide et procede de fabrication d'un missile guide Download PDF

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Publication number
EP3156756A1
EP3156756A1 EP16186326.1A EP16186326A EP3156756A1 EP 3156756 A1 EP3156756 A1 EP 3156756A1 EP 16186326 A EP16186326 A EP 16186326A EP 3156756 A1 EP3156756 A1 EP 3156756A1
Authority
EP
European Patent Office
Prior art keywords
support structure
guided missile
filling material
missile
warhead
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
EP16186326.1A
Other languages
German (de)
English (en)
Other versions
EP3156756B1 (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
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MBDA Deutschland GmbH
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Filing date
Publication date
Application filed by MBDA Deutschland GmbH filed Critical MBDA Deutschland GmbH
Publication of EP3156756A1 publication Critical patent/EP3156756A1/fr
Application granted granted Critical
Publication of EP3156756B1 publication Critical patent/EP3156756B1/fr
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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
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/72—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the material
    • 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 guided missile. Furthermore, the invention relates to a method for producing a guided missile. Finally, the invention relates to a collection of elements from which in particular a guided missile can be produced.
  • Guided missiles are known from the prior art.
  • the individual components of a guided missile must be designed so that they are resistant to all environmental factors that affect them.
  • heat influences, vibration influences, sound effects and electromagnetic influences must be considered individually in each component of the guided missile.
  • Most of the components are housed in their own enclosures, which protect the actual components from these influences.
  • the components are subsequently combined in a carrier structure, the carrier structure itself providing additional protection.
  • the missile is surrounded by an outer shell that provides further protection.
  • the object is achieved by the features of the independent claim.
  • a guided missile comprising a support structure. It is provided that a seeker head and / or a warhead and / or a sensor module and / or an electronics and / or a drive and steering module is attached to the support structure.
  • all intermediate spaces of the carrier structure are completely filled with a filling material. Intermediate spaces are to be understood as meaning all subvolumes within a volume encompassed by the carrier structure, which components do not correspond to components of the invention Missile are provided. This means, in particular, that the entire volume encompassed by the carrier structure is filled up either with components of the guided missile or with the filling material by introducing filling material.
  • the support structure is refillable, so that the missile is always a full-volume missile regardless of the modules used.
  • external influences such as in particular heat influences, sound influences, electromagnetic influences or vibration influences.
  • the missile is thus easy and inexpensive to manufacture and at the same time has a high robustness against external influences.
  • warhead and sensor module are alternatively used.
  • a missile with warhead can act on a target, while a missile with a sensor module can undertake a reconnaissance flight.
  • For the invention is therefore irrelevant whether a warhead or a sensor module are present.
  • the filling material is a complete housing for the warhead and / or the sensor module and / or the electronics. There are no further housing for the electronics or the warhead and / or the sensor module mandatory, so that the missile is very weight-saving composable.
  • the production of the warhead and / or the sensor module and / or the electronics is simplified, since no attention must be paid to the protection against external influences.
  • the filling material protects the warhead and / or the sensor module and / or the electronics from external influences.
  • the support structure has a first end and a second end. Furthermore, the support structure preferably has structural elements which are the first Connect end and the second end.
  • the support structure advantageously represents a frame on which said modules of the missile are arranged.
  • the seeker head is attached to the first end.
  • the seeker head is mounted at the first end on the opposite side of the support structure from the second end.
  • the seeker head forms a termination of the missile at the first end of the support structure.
  • the drive and steering module is attached to the second end of the support structure.
  • the drive and steering module is attached to the second end on the opposite side of the first end of the support structure.
  • the drive and steering module advantageously forms a conclusion of the missile at the second end of the support structure.
  • the warhead and / or the sensor module and / or the electronics of the missile is advantageously mounted between the first end and the second end.
  • the warhead and / or the sensor module and / or the electronics are arranged on the said structural elements of the carrier structure.
  • all intermediate spaces between the first end and the second end of the carrier structure are filled with the filling material.
  • the filling material in particular a full-volume missile is realized.
  • components arranged between the first end and the second end it is not necessary for components arranged between the first end and the second end to have their own housing or their own protective measures against external influences.
  • An outer skin of the guided missile is formed in particular between the first end and the second end of the carrier structure by the filling material.
  • the outer skin of the guided missile between the first end and the second end of the support structure is additionally formed by an outer surface of the structural elements.
  • the filling material is advantageously a hardenable foam material.
  • the foam material can be introduced into all intermediate spaces of the carrier structure in a simple manner and with little effort. At the same time, the foam material can be brought into different shapes.
  • the foam material is very versatile, all interstices of the support structure can be filled and at the same time an outer skin of the missile is arbitrarily malleable. Due to the hardening property of the foam material a fully voluminous and rigid missile is available after curing. The cured foam material also allows protection of the components of the missile against external influences.
  • the support structure includes a wiring of the missile.
  • the support structure comprises a complete wiring of the missile.
  • the guided missile preferably comprises an interface.
  • the interface is arranged in particular on the support structure.
  • a mechanical and electrical connection to a weapon carrier can be produced via the interface.
  • the invention further relates to a collection of elements.
  • the collection of elements comprises a support structure as well as a seeker head and / or an electronics and / or a warhead and / or a sensor module and / or a drive and steering module and a filling material. It is provided that the seeker head, the warhead, the sensor module, the electronics and / or the drive and steering module are attachable to the support structure. It is further provided that interstices of the carrier structure can be filled with the filling material. On In this way, in particular, a guided missile can be manufactured as described above. It will be appreciated that the collection of elements may advantageously comprise a plurality of different elements.
  • the collection of elements may include a variety of different support structures, seekers, electronics, warheads, and / or drive and steering modules.
  • the collection of elements may include a variety of different fillers. This makes it possible, according to the modular principle, to assemble a guided missile adapted to a specific mission. In this case, the production of the missile by the possibility of assembling the individual components and the subsequent surrounding at least the support structure with a filler material is very simple and low in effort.
  • the collection of elements advantageously additionally comprises a shape for inserting at least the support structure.
  • the mold with the inserted carrier structure can be filled with the filling material.
  • an outer skin of the missile can be determined by the contour of the shape.
  • the mold allows the complete filling of gaps of the support structure with the filler material.
  • the filling material can be held in its intended position with the mold until the filling material has hardened.
  • the filler is a fast-setting foam material which cures completely, in particular, in less than five minutes, more preferably in less than one minute.
  • the invention relates to a method for producing a guided missile.
  • the method comprises the following steps: First, provision is made of a support structure and a seeker head and / or a warhead and / or a sensor module and / or an electronics and / or a drive and steering module. Subsequently, attaching the seeker head, the warhead, the sensor module, the electronics and / or the drive and steering module to the support structure. Finally, the interspaces of the support structure are filled with a filler. In this way, a guided missile can advantageously be manufactured as described above.
  • the step of filling the carrier structure with the filling material comprises the following steps: First, at least the carrier structure is inserted into a mold. With the shape of a particular contour of the outer skin of the missile is specified. Then the mold is filled up with the filling material. In this way, in particular, a filling of all intermediate spaces of the carrier structure with the filling material takes place. The next step is hardening of the filling material.
  • the filling material is advantageously a curable foam material, in particular a rapidly curable foam material, which cures completely in less than five minutes, more preferably in less than one minute.
  • the mold is removed.
  • the shape dictates the contour of the outer skin of the missile.
  • the mold allows the filling of all intermediate spaces of the carrier structure with the filling material.
  • the support structure preferably has an interface.
  • the steering missile can be mounted on a weapon carrier via the interface.
  • the interface advantageously allows both an electrical and a mechanical connection.
  • FIG. 1 shows a guided missile 1 according to an embodiment of the invention.
  • the guided missile 1 comprises a carrier structure 2 which serves as a carrier for all further components of the guided missile 1.
  • the support structure 2 has a first end 11 and a second end 12.
  • the first end 11 and the second end 12 are connected by structural elements 13.
  • the support structure 2 is cylindrical in the illustrated embodiment of the missile 1, wherein the first end 11 and the second end 12 each correspond to an end face of the cylinder.
  • the structural elements 13 connect on the one hand the first end 11 with the second end 12, on the other hand, a connection of the individual structural elements 13 is present among each other.
  • the support structure 2 has an interface 14, via which a connection to a weapon carrier can be produced.
  • the steering missile 1 is mechanically connected to the weapon carrier via interface 14.
  • a seeker 4 of the missile 1 is mounted at the first end 11.
  • a drive and steering module 6 (see. FIG. 2 ) appropriate.
  • a warhead 3 and an electronics 5 is mounted between the first end 11 and the second end 12.
  • a sensor module can be attached.
  • the guided missile 1 is intended for a reconnaissance flight.
  • a wiring 8 is provided, with the electronics 5, the seeker 4, the warhead 3 and the drive and steering module 6 (see. FIG. 2 ) are electrically connected to each other.
  • the electronics 5 can issue control commands to all components of the guided missile 1 in order to ensure safe and reliable operation of the guided missile 1.
  • the steering missile 1 is electrically connected to the weapon carrier via the interface 14.
  • the seeker 4 may be an infrared seeker, a TV seeker, a radar seeker, a 3D seeker, and / or a mixed seeker.
  • the warhead may in particular be a penetrator, a shaped charge, a fragmentation charge or a gas charge. It is also possible to dispense with a charge and to use a sensor module, in which case the guided missile 1 has only a reconnaissance function and no active function.
  • the electronics 5 may be a GPS system, a low precision inertial navigation system, a high precision inertial navigation system, or a combination of GPS and inertial navigation system, where the inertial navigation system may each have low or high precision.
  • a power supply can be included in the electronics as well as in the steering module.
  • the drive and steering modules 6 can in particular be such modules for a short range, for a medium range or for a high range.
  • various support structures 2 may be provided, wherein the different carrier structures 2 allows a connection to different weapon carriers.
  • the guided missile 1 also has a filling material 10. With the filling material 10, all intermediate spaces of the support structure 2, in particular all interspaces between the first end 11 and the second end 12, filled.
  • the filling material 10 is for this purpose advantageously a curable foam, wherein the foam between the first end 11 and the second end 12 can be introduced, so that the foam between the first end 11 and the second end 12 of the support structure 2 hardens, whereby all spaces between the support structure. 2 between the first end 11 and the second end 12 are filled with the filling material 10.
  • the filling material 10 thus represents a protection at least of the warhead 3 and the electronics 5 from external influences.
  • the warhead 3 and the electronics 5 need no additional protective measures to protect these components from external influences. On the one hand, this simplifies the manufacture of the electronics 5 and of the warhead 3 and, on the other hand, permits a reduction in the weight of the guided missile 1.
  • An outer skin 9 of the guided missile 1 at least in the region of the carrier structure 2 is advantageously formed by the filling material 10.
  • the outer skin 9 is additionally formed by an outer surface of the structural elements 13.
  • a shape of the outer skin 9 can be fixed differently, so that by applying the filling material 10, the outer skin 9 can be adapted to different conditions on the guided missile 1.
  • the different prerequisites may in particular be those relating to buoyancy, Drag coefficient, in particular the air brakes, wings or stub wings act.
  • FIG. 2 schematically shows a method for producing a guided missile 1, in particular of the guided missile 1 as in FIG. 1 shown.
  • a collection of elements is used, the collection of elements comprising a plurality of support structures 2, warheads 3, seekers 4, electronics 5, and / or drive and steering modules 6.
  • the individual elements can be used as they are related to FIG. 1 have been described.
  • the inventive method is divided into several steps.
  • a first step provision is made of a carrier structure 2.
  • the selection of a carrier structure 2 from the collection of elements takes place, wherein the carrier structure 2 is selected, in particular, according to a weapon carrier, with which the guided missile 1 to be manufactured is to be used.
  • the individual carrier structures 2 from the collection of elements are adapted to different weapon carrier systems.
  • an attachment 200 of the seeker 4 After providing 100 of the support structure 2 is an attachment 200 of the seeker 4, the electronics 5, the drive and steering module 6 and in particular the warhead 3. As described above, instead of the warhead 3, an additional sensor module are used to a guided missile 1 for To receive educational purposes.
  • the mounting step 200 advantageously also includes a test of the missile 1 so that faulty components can be identified. Since no filling material 10 has yet been introduced at this point in time, it is easy to remove individual components, in particular defective components, and optionally to replace them with functioning components.
  • filling 300 of spaces between the carrier structure 2 with a filling material takes place.
  • at least the support structure 2 is inserted into a mold 7, the mold 7 completely enclosing the support structure 2.
  • the mold 7 is filled with the filling material 10.
  • the filling material 10 for this purpose, in particular, a curable foam material, so that the filler 10 can be easily introduced into all spaces between the first end 11 and the second end 12 of the support structure 2.
  • the filling material 10 is held in the mold 7 until the filling material 10 is completely cured. This is advantageously after a maximum of five minutes, especially after a maximum of one minute, the case.
  • an annealing step takes place in which the filling material 10 is kept above a predefined temperature for a predefined time. In this way maximum strength is achieved.
  • a contour of the outer skin 9 of the guided missile 1 can be predetermined with the form 7.
  • the collection of elements comprises a plurality of different shapes 7, wherein during the filling step 300, a shape 7 adapted to the mission of the guided missile 1 is selected.
  • the guided missile 1 After removing the mold 7, the guided missile 1 is completed and ready for use. It can be seen that the guided missile 1 can be manufactured quickly and optimally adapted to the mission by the modular design. In addition, it is ensured by the filling material 10 that all components of the guided missile 1 are protected against external influences.
  • the invention eliminates the need for component housings.
  • complicated support structures and the manufacture of an outer shell are simplified by the simple application of the filling material, in particular the curable foam.
  • the individual components of the guided missile 1 are protected from all environmental influences by the enveloping foam as filling material.
  • a full-volume structure is created so that the guided missile 1 is very stable.
  • no cavities are present within the guided missile 1, particularly preferably within the carrier structure 2.
  • a final contour of the outer skin 9 of the guided missile 1 is determined by the contour of the mold 7, in which the filling with the filling material 10 takes place.
  • the outer skin 9 is determined by the inner surface of the mold 7.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
EP16186326.1A 2015-10-15 2016-08-30 Missile guide et procede de fabrication d'un missile guide Active EP3156756B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102015013350.0A DE102015013350A1 (de) 2015-10-15 2015-10-15 Lenkflugkörper und Verfahren zum Herstellen eines Lenkflugkörpers

Publications (2)

Publication Number Publication Date
EP3156756A1 true EP3156756A1 (fr) 2017-04-19
EP3156756B1 EP3156756B1 (fr) 2019-05-08

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP16186326.1A Active EP3156756B1 (fr) 2015-10-15 2016-08-30 Missile guide et procede de fabrication d'un missile guide

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Country Link
EP (1) EP3156756B1 (fr)
DE (1) DE102015013350A1 (fr)
ES (1) ES2732899T3 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102018005406B3 (de) 2018-07-06 2019-09-05 TDW Gesellschaft für verteidigungstechnische Wirksysteme mbH Penetrator
KR102337300B1 (ko) 2021-06-29 2021-12-08 국방과학연구소 화포용 유도 비행체 및 그것을 위한 무선 주파수 방향 탐색기

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4941627A (en) * 1975-12-16 1990-07-17 The United States Of America As Represented By The Secretary Of The Navy Guidance and control fin
US20050230535A1 (en) * 2004-04-13 2005-10-20 Lockheed Martin Corporation Immersible unmanned air vehicle and system for launch, recovery, and re-launch at sea
DE102011109693B3 (de) * 2011-08-06 2012-09-13 Lfk-Lenkflugkörpersysteme Gmbh Strukturkomponente für ein operationelles Flugkörpersystem

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2272047B (en) * 1989-12-14 1994-07-27 British Aerospace Stand-off weapons
FR2656081B1 (fr) * 1989-12-19 1992-02-28 Thomson Brandt Armements Enveloppe peripherique pour une munition guidee tiree par effet canon.
DE19655109C2 (de) * 1996-04-30 2000-06-15 Diehl Stiftung & Co Mörser-Munition
FR2803911B1 (fr) * 2000-01-19 2002-11-29 Giat Ind Sa Conteneur pour munitions de gros calibre
SI1316774T1 (sl) * 2001-11-28 2006-12-31 Rheinmetall Waffe Munition Izstrelek z mocnim penetracijskim in lateralnim ucinkom z integrirano pripravo za razkroj delcev
US7506587B1 (en) * 2007-02-20 2009-03-24 The United States Of Americas As Represented By The Secretary Of The Navy Modular projectile system

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4941627A (en) * 1975-12-16 1990-07-17 The United States Of America As Represented By The Secretary Of The Navy Guidance and control fin
US20050230535A1 (en) * 2004-04-13 2005-10-20 Lockheed Martin Corporation Immersible unmanned air vehicle and system for launch, recovery, and re-launch at sea
DE102011109693B3 (de) * 2011-08-06 2012-09-13 Lfk-Lenkflugkörpersysteme Gmbh Strukturkomponente für ein operationelles Flugkörpersystem

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102018005406B3 (de) 2018-07-06 2019-09-05 TDW Gesellschaft für verteidigungstechnische Wirksysteme mbH Penetrator
KR102337300B1 (ko) 2021-06-29 2021-12-08 국방과학연구소 화포용 유도 비행체 및 그것을 위한 무선 주파수 방향 탐색기

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Publication number Publication date
DE102015013350A1 (de) 2017-04-20
ES2732899T3 (es) 2019-11-26
EP3156756B1 (fr) 2019-05-08

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