EP3156756B1 - Missile guide et procede de fabrication d'un missile guide - Google Patents

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

Info

Publication number
EP3156756B1
EP3156756B1 EP16186326.1A EP16186326A EP3156756B1 EP 3156756 B1 EP3156756 B1 EP 3156756B1 EP 16186326 A EP16186326 A EP 16186326A EP 3156756 B1 EP3156756 B1 EP 3156756B1
Authority
EP
European Patent Office
Prior art keywords
support structure
guided missile
missile
filler material
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.)
Active
Application number
EP16186326.1A
Other languages
German (de)
English (en)
Other versions
EP3156756A1 (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 EP3156756A1 publication Critical patent/EP3156756A1/fr
Application granted granted Critical
Publication of EP3156756B1 publication Critical patent/EP3156756B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

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 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 publication DE 10 2011 109 693 B3 describes a structural component for an operational missile system comprising a metal foam body.
  • the object is achieved by a missile according to claim 1, comprising a support structure.
  • 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. Furthermore, it is envisaged that all Gaps of the support structure are completely filled with a filler.
  • the guided missile is characterized in that the filler material is a fast-setting foam material which fully cures in less than five minutes. Under interstices, all subvolumes are to be regarded within a volume encompassed by the carrier structure, which are not provided with components of the guided missile. 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 are the warhead and / or the sensor module and / or the electronics protected from external influences.
  • the support structure has a first end and a second end. Furthermore, the support structure preferably has structural elements which connect the first 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 curable 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 according to claim 11.
  • the collection of elements comprises a support structure as well as a seeker head and / or a Electronics and / or a warhead and / or a sensor module and / or a drive and steering module and a filler. 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. Furthermore, it is provided that with the filling material all intermediate spaces of the support structure are completely refillable.
  • the filling material here is a fast-curing foam material, which cures completely in less than five minutes. In this way, in particular a guided missile as described above can be manufactured.
  • 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 material is a fast-setting foam material that cures completely in less than five minutes, more preferably in less than one minute.
  • the invention relates to a method for producing a guided missile according to claim 13.
  • 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 interstices of the support structure are completely filled with a filling material, wherein the filling material is a fast-curing foam material, which cures completely in less than five minutes. 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 support structure 2, which serves as a carrier for all other components of the missile 1 is used.
  • 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 to the second end 12, on the other hand, a connection of the individual structural elements 13 is present with 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 Inertialnavigationssystem, wherein the Inertialnavigationssystem can each have a 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 carrier structures 2 may be provided, the different carrier structures 2 permitting 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 conditions may in particular be those with regard to buoyancy, drag coefficient, in particular the air brakes, wings or stub wings.
  • 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 is for this purpose in particular a hardenable foam material, so that the filling material 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 is trained.
  • 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.

Landscapes

  • 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)

Claims (15)

  1. Missile guidé (1) comprenant une structure porteuse (2), dans lequel une tête chercheuse (4) et/ou une tête militaire (3) et/ou un module capteur et/ou une électronique (5) et/ou un module d'entraînement et de guidage (6) sont montés sur la structure porteuse (2), dans lequel tous les espaces intermédiaires de la structure porteuse (2) sont complètement remplis avec un matériau de remplissage (10), le matériau de remplissage (10) étant une mousse à durcissement rapide qui durcit complètement en moins de 5 minutes.
  2. Missile guidé (1) selon la revendication 1, caractérisé en ce qu'au moins la tête militaire (3) et/ou le module capteur et/ou l'électronique (5) sont entourés, en particulier complètement, par le matériau de remplissage (10).
  3. Missile guidé (1) selon l'une des revendications précédentes, caractérisé en ce que la structure porteuse (2) présente une première extrémité (11) et une seconde extrémité (12), des éléments structurels (13) reliant la première extrémité (11) et la seconde extrémité (12).
  4. Missile guidé (1) selon la revendication 3, caractérisé en ce que la tête chercheuse est montée à la première extrémité (11) du côté de la structure porteuse (2) opposé à la seconde extrémité (12).
  5. Missile guidé (1) selon la revendication 3 ou 4, caractérisé en ce que le module d'entraînement et de guidage (6) est monté sur la structure porteuse (2) à la seconde extrémité (12) du côté opposé à la première extrémité (11).
  6. Missile guidé (1) selon l'une des revendications 3 à 5, caractérisé en ce que la tête militaire (3) et/ou le module capteur et/ou l'électronique (5) sont montés entre la première extrémité (11) et la seconde extrémité (12) de la structure porteuse (2).
  7. Missile guidé (1) selon l'une des revendications 3 à 6, caractérisé en ce que tous les espaces intermédiaires entre la première extrémité (11) et la seconde extrémité (12) de la structure porteuse (2) sont remplis avec le matériau de remplissage (10).
  8. Missile guidé (1) selon l'une des revendications 3 à 7, caractérisé en ce qu'une enveloppe extérieure (9) du missile guidé (1) entre la première extrémité (11) et la deuxième extrémité (12) est formée par le matériau de remplissage (10) et en particulier une surface extérieure des éléments structurels (13).
  9. Missile guidé (1) selon l'une des revendications précédentes, caractérisé en ce que la structure porteuse (2) contient un câblage (8) du missile guidé (1).
  10. Missile guidé (1) selon l'une des revendications précédentes, caractérisé par une interface (14) qui est montée en particulier sur la structure porteuse (2), laquelle interface (14) permet d'établir une liaison mécanique et électrique avec un support d'arme.
  11. Collection d'éléments comprenant une structure porteuse (2) ainsi qu'une tête chercheuse (4) et/ou une électronique (5) et/ou une tête militaire (3) et/ou un module capteur et/ou un module d'entraînement et de guidage (6), ainsi qu'un matériau de remplissage (10), dans lequel la tête chercheuse (4), la tête militaire (3), le module capteur, l'électronique (5) et/ou le module d'entraînement et de guidage (6) peuvent être montés sur la structure porteuse (2), et dans lequel tous les espaces intermédiaires de la structure porteuse (2) peuvent être complètement remplis avec le matériau de remplissage (10), la collection étant configurée pour réaliser un missile guidé (1) selon l'une des revendications précédentes, le matériau de remplissage (10) étant une mousse à durcissement rapide qui durcit complètement en moins de cinq minutes.
  12. Collection d'éléments selon la revendication 11, caractérisée par un moule (7) pour y insérer au moins la structure porteuse (2), le moule (7) avec la structure porteuse insérée (2) pouvant être rempli avec le matériau de remplissage (10).
  13. Procédé de fabrication d'un missile guidé (1), comprenant les étapes consistant à :
    - fournir (100) une structure porteuse (2) ainsi qu'une tête chercheuse (4) et/ou une tête militaire (3) et/ou un module capteur et/ou une électronique (5) et/ou un module d'entraînement et de guidage (6),
    - monter (200) la tête chercheuse (4), la tête militaire (3), le module capteur, l'électronique (5) et/ou le module entraînement et guidage (6) sur la structure porteuse (2) et
    - remplir complètement (300) tous les espaces intermédiaires de la structure porteuse (2) avec un matériau de remplissage (10), le matériau de remplissage (10) étant une mousse à durcissement rapide qui durcit complètement en moins de cinq minutes.
  14. Procédé selon la revendication 13, caractérisé en ce que l'étape de remplissage (300) comprend les étapes consistant à :
    - insérer au moins la structure porteuse (2) dans un moule (7),
    - remplir le moule (7) avec le matériau de remplissage (10),
    - laisser durcir le matériau de remplissage (10) et
    - retirer le moule (7).
  15. Procédé selon la revendication 13 ou 14, caractérisé en ce qu'un contour de l'enveloppe extérieure (9) du missile guidé (1) peut être défini au moins autour de la structure porteuse (2) au moyen du moule (7).
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 EP3156756A1 (fr) 2017-04-19
EP3156756B1 true EP3156756B1 (fr) 2019-05-08

Family

ID=56876924

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

Country Status (3)

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

Families Citing this family (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

Family Cites Families (9)

* 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
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.
DE19617221C2 (de) * 1996-04-30 1999-07-01 Diehl Stiftung & Co Als Mörsergeschoß verbringbares Lenkprojektil
FR2803911B1 (fr) * 2000-01-19 2002-11-29 Giat Ind Sa Conteneur pour munitions de gros calibre
ES2264958T3 (es) * 2001-11-28 2007-02-01 Rheinmetall Waffe Munition Gmbh Proyectiles con elevado efecto de penetracion y lateral con dispositivo de disgregacion integrado.
US7097136B2 (en) * 2004-04-13 2006-08-29 Lockheed Martin Corporation Immersible unmanned air vehicle and system for launch, recovery, and re-launch at sea
US7506587B1 (en) * 2007-02-20 2009-03-24 The United States Of Americas As Represented By The Secretary Of The Navy Modular projectile system
DE102011109693B3 (de) * 2011-08-06 2012-09-13 Lfk-Lenkflugkörpersysteme Gmbh Strukturkomponente für ein operationelles Flugkörpersystem

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
EP3156756A1 (fr) 2017-04-19
ES2732899T3 (es) 2019-11-26
DE102015013350A1 (de) 2017-04-20

Similar Documents

Publication Publication Date Title
EP2310797B1 (fr) Projectile
EP2071270B1 (fr) Dispositif d'allumage en nutation
EP3156756B1 (fr) Missile guide et procede de fabrication d'un missile guide
DE102013011378A1 (de) Rahmen für einen Flugkörper
DE102009010261A1 (de) Schockdämpfer
DE102009012424B4 (de) Frachtraumboden für einen Frachtraum eines Flugzeugs sowie Verfahren zur Montage eines solchen
WO2011054361A1 (fr) Bombe aérienne
DE102016123352A1 (de) Aufprallabsorptionseinheit, Herstellungsverfahren der Aufprallabsorptionseinheit und Aufprallabsorptionsverstärkung
DE102016226007A1 (de) Verfahren zum Herstellen einer Komponente eines Fahrzeugs
EP3710341B1 (fr) Dispositif de renforcement, d'étanchéité ou d'amortissement d'un élément structurel
EP0800052A2 (fr) Système de reconnaissance
EP2557389B1 (fr) Composant structurel pour un système de corps volant opérationnel
DE69100643T2 (de) Vorrichtung zur zeitlichen Halterung eines Objektes an einem Träger mit einer auf Zugkräfte kalibrierten Sollbruchstelle.
EP3156757B1 (fr) Système d'arme et procédé de fonctionnement d'un système d'arme
DE2616359A1 (de) Energieabsorber
DE3427165A1 (de) Uebungsmunitionssystem
DE102016007976A1 (de) Vorfragmentierung eines Sprengkopfes
DE102008023678B4 (de) Fliegerbombe
DE102019111001A1 (de) Toleranzausgleichsbaugruppe, damit versehene Luftfahrzeugkomponente sowie Luftfahrzeug
EP1617169B1 (fr) Régulateur de profondeur pour un flotteur porté par une bobine
DE102014014952B4 (de) Flugkörper
DE102014104294A1 (de) Verfahren zur Herstellung eines Strukturbauteils eines Kraftfahrzeugs
DE102014003377B3 (de) Karosserieteil für ein Kraftfahrzeug
DE3902761C2 (fr)
DE2726133C2 (de) Militärischer Flugkörper

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

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

Free format text: STATUS: THE APPLICATION HAS BEEN PUBLISHED

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

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

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20170524

RBV Designated contracting states (corrected)

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

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

Free format text: STATUS: EXAMINATION IS IN PROGRESS

17Q First examination report despatched

Effective date: 20171201

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

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

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20190108

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

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

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

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

Ref country code: AT

Ref legal event code: REF

Ref document number: 1130847

Country of ref document: AT

Kind code of ref document: T

Effective date: 20190515

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502016004532

Country of ref document: DE

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20190508

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

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

Ref country code: NO

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: 20190808

Ref country code: LT

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: 20190508

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: 20190508

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: 20190508

Ref country code: HR

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: 20190508

Ref country code: PT

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: 20190908

Ref country code: AL

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: 20190508

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: 20190508

REG Reference to a national code

Ref country code: ES

Ref legal event code: FG2A

Ref document number: 2732899

Country of ref document: ES

Kind code of ref document: T3

Effective date: 20191126

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

Ref country code: LV

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: 20190508

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: 20190809

Ref country code: BG

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: 20190808

Ref country code: RS

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: 20190508

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

Ref country code: CZ

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: 20190508

Ref country code: SK

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: 20190508

Ref country code: RO

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: 20190508

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: 20190508

Ref country code: EE

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: 20190508

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502016004532

Country of ref document: DE

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

Ref country code: SM

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: 20190508

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

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

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: 20190508

26N No opposition filed

Effective date: 20200211

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

Ref country code: PL

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: 20190508

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

Ref country code: CH

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

Effective date: 20190831

Ref country code: LU

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

Effective date: 20190830

Ref country code: MC

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: 20190508

Ref country code: LI

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

Effective date: 20190831

Ref country code: SI

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: 20190508

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20190831

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

Ref country code: IE

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

Effective date: 20190830

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

Ref country code: BE

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

Effective date: 20190831

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

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: 20190508

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

Ref country code: IS

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: 20190908

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

Ref country code: HU

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

Effective date: 20160830

Ref country code: MT

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: 20190508

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

Ref country code: MK

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: 20190508

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 1130847

Country of ref document: AT

Kind code of ref document: T

Effective date: 20210830

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 NON-PAYMENT OF DUE FEES

Effective date: 20210830

P01 Opt-out of the competence of the unified patent court (upc) registered

Effective date: 20230509

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

Ref country code: IT

Payment date: 20230825

Year of fee payment: 8

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

Ref country code: ES

Payment date: 20231027

Year of fee payment: 8

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

Ref country code: DE

Payment date: 20240830

Year of fee payment: 9

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

Ref country code: GB

Payment date: 20240826

Year of fee payment: 9

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

Ref country code: FR

Payment date: 20240829

Year of fee payment: 9