EP1947415B1 - Vorrichtung zur Tragflächenentfaltung - Google Patents

Vorrichtung zur Tragflächenentfaltung Download PDF

Info

Publication number
EP1947415B1
EP1947415B1 EP08000525A EP08000525A EP1947415B1 EP 1947415 B1 EP1947415 B1 EP 1947415B1 EP 08000525 A EP08000525 A EP 08000525A EP 08000525 A EP08000525 A EP 08000525A EP 1947415 B1 EP1947415 B1 EP 1947415B1
Authority
EP
European Patent Office
Prior art keywords
wing
folding
longitudinal axis
base body
support surface
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.)
Not-in-force
Application number
EP08000525A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1947415A1 (de
Inventor
Michael Feuerstein
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.)
Diehl BGT Defence GmbH and Co KG
Original Assignee
Diehl BGT Defence GmbH and Co KG
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 Diehl BGT Defence GmbH and Co KG filed Critical Diehl BGT Defence GmbH and Co KG
Publication of EP1947415A1 publication Critical patent/EP1947415A1/de
Application granted granted Critical
Publication of EP1947415B1 publication Critical patent/EP1947415B1/de
Not-in-force 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
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/02—Stabilising arrangements
    • F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel

Definitions

  • the invention relates to a device for wing deployment and a folding wing with such a device, in particular for a missile.
  • a missile such as a guided missile for use in a defense system, typically has wings or stabilizing surfaces projecting from its longitudinal body which provide the aerodynamic characteristics required for the flight phase. Such supporting or stabilizing surfaces are more hindering for the storage, for the transport or for the launch of such a missile. For this reason, folding wings are used, which are folded in the ground state of the missile and are deployed only in the flight phase.
  • Such a folding wing usually comprises a pivotable wing and is provided with a device which triggers the unfolding or deployment of the wing at the beginning of the flight phase.
  • a folding wing with such a device for airfoil deployment is subject to boundary conditions in terms of size and mass, since the folding wing in the folded state may increase the predetermined outer contour of the missile at most only insignificantly. Also, the wing of the missile may not increase the mass of the missile to an extent detrimental to the flight phase or range.
  • Such a device for wing deployment is from the document EP 06 902 84 B1 known.
  • a device for wing deployment for a folding wing of a guided missile wherein the wing belonging to the wing is stored in a longitudinally applied to the missile wing pocket.
  • the wing is swung out by using mechanical and / or pyrotechnic aids.
  • a first object of the invention is to provide a device by which the deployment process of a folding wing under the restriction of the low integration volume is effected as reliably as possible, if possible to effect without affecting the flow behavior after the deployment process.
  • Another object of the invention is to provide a folding wing, which shows the most reliable deployment during the flight phase and requires the lowest possible integration volume.
  • a third object of the invention comprises the representation of a missile which has the aerodynamic properties required under conditions of use.
  • the first object is achieved according to the invention by providing a device for aerofoil deployment, in particular for a missile, with a base body extending along a longitudinal axis, with a fastening means, with a number of movable flaps and with a number of lateral recesses, wherein the fastening means for Positioning of the base body is formed on a front end side of a support surface, wherein the or each movable flap for influencing the flow resistance of the support surface or the control surface is formed, and the or each lateral recess for self-releasable attachment of the body to the support surface or the control surface set in an end position is.
  • the invention is based in a first step on the idea of using flaps on the wings, which increase the flow resistance of the wing and thereby effectively support their unfolding up to the final position. This causes a reliable unfolding.
  • the invention recognizes that the enlargement of the flow resistance, which is advantageous in itself for the unfolding process, is disadvantageous for the aerodynamic properties of the flying object.
  • the flight behavior of the missile is significantly affected. The missile slows down, slows down, and reduces range, or increases fuel requirements to compensate for reduced range and speed.
  • the invention is based on the idea of triggering a self-solution of the attachment of the device to the support surface when the end position is reached.
  • An increase in the flow resistance is thus selectively and effectively used only for the deployment process.
  • the wing performance parameters are determined by the device, i. in particular, no longer adversely affected by the valves arranged thereon, since it is then no longer present.
  • the use of pyrotechnic elements is unnecessary.
  • the detached from the wing when reaching the intended end position device is lifted by their increased flow resistance of the wing in a controlled manner and moves away in the desired manner from the missile. A collision with the missile is not to be feared.
  • the device for airfoil unfolding is advantageously characterized in that the fastening means comprises a longitudinal recess, which has a corresponding to the front end of the support surface negative mold. With such a longitudinal recess, the base body can fit accurately on the front end side of the support surface.
  • the base body advantageously on one end side on a Entrastungssch, in particular a bevel, which / s gives the base body a pulse along its longitudinal axis, in particular in the direction of the opposite end side of the body.
  • This stop is in particular to be coupled with the achievement of the predetermined end position. If the support surface is unfolded during the unfolding process up to the end position, the unlocking means runs against the stop when the end position is reached, whereby the unlocking means is released. If the unlocking by a pulse along the longitudinal direction, the device for wing deployment is moved away from the missile. The triggering by a longitudinal movement of the body is additionally supported by the inertia of the body.
  • the unlocking means is effected in that the or each lateral recess is designed such that a displacement of the device from a predetermined end position along the longitudinal axis, a solution of the attachment is triggered.
  • the or each recess is hook-shaped, so that the device can be fixed in particular in the end position with locking bolts.
  • the locking bolts are suitably assigned to the wing.
  • the hook shape of the or each recess allows a longitudinal displacement of the base body such that in a holding position of the base body is fixed to the support surface and in a relation to the holding position by a minimum length in the longitudinal shifted position, the fixation is achieved.
  • a plurality of recesses are provided which have a different length and shape depending on the position with respect to the longitudinal axis. For example, can be achieved with two lateral recesses of different lengths, which are positioned spaced apart along the longitudinal axis, that the detachment of the support surface from the side recesses takes place at different times, so that the main body at the moment of detachment from the wing to this a certain Angle forms.
  • pairs movable flaps along the longitudinal axis are arranged opposite one another. If the device is mounted on a support surface, these movable flaps serve to symmetrically increase the flow resistance of the support surface on both sides of the surface. By deliberately increasing the flow resistance of the wing, the wing is unfolded reliably in the unfolding process.
  • the flaps are provided with a spring mechanism, which is set up at a release for setting up the flaps. Since the flaps are placed by their flow resistance, a relatively simple spring mechanism, for example, using a mechanical compression or tension spring, to complete setting up the flaps to increase sufficient the flow resistance and thus to achieve the deployment of the folding wing or the wing.
  • the choice of a suitable material is advantageous, which has the properties required for use, but which is still inexpensive to produce. Above all, plastics are suitable for this purpose.
  • a folding wing is specified, in particular for a missile, with a support surface, with a pivot mechanism for extending the wing to an end position, with a wing pocket for longitudinal recording of the wing in a retracted state, and with a arranged at the front end of the wing device for wing deployment of the aforementioned type.
  • such a folding wing is designed such that the support surface is not completely enclosed by the pocket in the retracted state and the device for aerofoil deployment is applied to the projecting from the pocket front end.
  • a number of locking bolts are preferably arranged for fixing the device to the support surface.
  • Each of these locking bolts engages in the respective corresponding lateral recess of the device for aerodynamic development positively or positively.
  • the or each locking bolt may be resiliently mounted. In this way, and furthermore advantageously, constraints can be imposed by the interaction of the or each locking bolt with the or each corresponding lateral recess of the device, so that the movement of the device during the detachment process is guided in a desired manner. In an application during the detachment process, for example, the device rather dissolves from those locking bolts which are closer to the pivot point of the support surface than from further spaced locking bolts.
  • the device rotates during the detachment process to the more distant locking bolt before it dissolves completely.
  • This process is supported by flaps which increase the flow resistance.
  • a partial rotation of the body are coupled with its translational detachment movement so that the main body includes in the separation of the support surface with this a certain angle.
  • a controlled release which is achieved by specifying the coupling of the degrees of freedom of the detachment movement, is advantageous to prevent irregular movements of the body during the detachment and thus a possible collision with the flying object.
  • the flap relate to its interaction and arrangement to the or each movable flap of the device for wing deployment.
  • a flap engages in the retracted state of the support surface in the wing pocket and is held there in particular under bias, so that the flap is retracted itself.
  • the flap In the erected state, the flap lies substantially in the plane of the longitudinal axis of the device and is perpendicular to the support surface.
  • the folding wing advantageously has a suitable release mechanism by which the support surface is quickly moved out of the wing pocket so far that the or each movable flap is no longer in interaction with the wing pocket and is no longer biased by the latter.
  • a triggering mechanism can be realized via an actuator or a spring mechanism. In particular, this does not have to be designed to open the wing up to the end position and can therefore be designed to save space and integrated in the area of the wing pocket.
  • the folding wing is advantageously equipped with a sensor-actuator system which triggers a release pulse in the extended state of the support surface in the region of the end position, which is transmitted to the base body of the device for airfoil unfolding.
  • a sensor-actuator system can act in addition.
  • the device is released from its anchorage in addition to the inertia of the body.
  • the third object of the invention is achieved by a missile which is equipped with a number of folding wings of the type described above.
  • a device for wing deployment and a folding wing of the type described above are in principle also suitable for use on underwater projectiles or diving vehicles, the concrete shape of the device and acting as a rudder flap are to be adapted to the specific hydrodynamic requirements.
  • Fig. 1 shows a device V for wing deployment with a base body 1 and with movable flaps 2, which is applied to a pivotable support surface 3 of a folding wing 4.
  • the folding wing 4 comprises in addition to the pivotable support surface 3, a wing pocket 5, which includes the pivotable support surface 3 in the folded state shown here.
  • the region of the end face 6, on which the device 1 rests projects out of the wing pocket 5 and the movable flaps 2 of the device engage in the wing pocket 5 at the end.
  • the movable flaps 2 are provided with a spring mechanism for unfolding so as to be biased by the wing pocket 5 in the illustration shown.
  • the folding wing 4 comprises a fastening strip 7, on which the folding wing 4 is mounted on the missile. The folding wing 4 is thus mounted longitudinally on a missile, not shown, so that the folding wing 4 unfolds with respect to the missile in the radial direction to the outside.
  • Fig. 2 is the folding wing 4 with the device V to Fig. 1 shown with initial swung-out wing 3 in a side view.
  • the support surface 3 during the flight phase of the in Fig. 1 shown folded state blown out.
  • the leverage of the spring mechanism is not sufficient to swing out the wing 3 completely.
  • the illustration shows the flaps 2 at the moment of unfolding, with the wing just enclose an angle of about 45 °.
  • Fig. 3 shows the folding wing 4 with the device V for wing deployment after Fig. 1 with swung-out wing 3 just before reaching the End position in perspective view according to Fig. 1 , Visible are the unfolded hinged flaps 2 on both sides of the support surface 3, which is almost perpendicular to the wing pocket 5.
  • the longitudinal direction 10 of the wing pocket 5 corresponds to the inflow direction of the wing 3, so that the movable flaps 2 generate a maximum flow resistance in the unfolded state.
  • the support surface 3 from the in Fig. 2 illustrated pivot state erected to the state shown here. It can be seen that such a flow resistance after the opening process affects the flight behavior of the missile.
  • Fig. 4 now adjusts the folding wing 4 with the device V.
  • Fig. 1 in the too Fig. 3 identical configuration in side view. More details are Fig. 2 removable.
  • the lower end side 1A of the base body 1 of the device V runs against a stop 11.
  • a beveled ramp surface at the lower end of the base body 1 of the device V this is a pulse along the direction 12, ie in the longitudinal direction of the basic body 1, which is reinforced by the inertia of the device V even more.
  • Fig. 5 adjusts the folding wing with initial detaching device Fig. 1 with fully swung-out wing in the final position in lateral view. Further details of the presentation are Fig. 4 such as Fig. 2 removable. The situation presented here follows directly on in Fig. 4 illustrated situation. As a result of the pulse triggered toward the stop, the device V on the lower lateral recesses 8A is disengaged from the corresponding lower locking pins 9A, which are arranged on both surface sides of the support surface 3.
  • the base body 1 By notching the recesses 8B from the locking pin 9B, the base body 1 is rotated further, thereby rotating on the upper recesses 8C about the upper, spring-mounted locking pin 9C. After a predetermined angle of rotation, which is determined by the shape of the recesses 8C, the device V latches off the support surface 3 completely and is carried away by the flow. Due to the detachment, in which the longitudinal axis of the main body 1 forms a certain angle with the longitudinal axis of the supporting surface 3, a collision of the device V with the flying object on which the folding wing 4 is mounted is avoided after detachment.
  • Fig. 7 is the folding wing 4 with the device for Tragentertfaltung after Fig. 1 after triggering the detachment pulse with detailed representations of the detachment process shown.
  • the overall presentation corresponds to the situation directly related to the in Fig. 4 The situation shown follows, in the moment in which the release pulse was triggered.
  • the wing 3 is already in its final position.
  • the partial figures A and B show details of the recesses 8A and 8B, 8C, respectively, with the corresponding locking bolts 9A, 9B, 9C.
  • a chamfer 13 is visible on the lower end side 1A of the base body 1 of the device V as the unlocking means, which deflects the impact impulse of the base body 1 against the stop 11 into a detachment pulse along the longitudinal direction of the base body.
  • the end side of the recess 8A is already shifted relative to the corresponding locking pin 9A.
  • the corresponding displacement of the recess 8B is visible relative to the locking bolt 9B.
  • the base body 1 is further connected via the locking bolt 9C with the support surface 3.
  • Fig. 8 is the folding wing 4 with initially peeling device after Fig. 5 shown with detailed representations of the detachment process.
  • the overall presentation corresponds to the situation in Fig. 5 ,
  • the subfigures Detail C and Detail D show the same details of the subfigures Detail A and Detail B Fig. 7 but at the time of the in Fig. 5 equivalent.
  • the unlatching movement of the locking bolt 9B begins from the recess 8B, visible in partial detail D.
  • the device V rotates by the lever effect of the flow resistance on the erected movable flaps 2 on the recess 8C to the locking pin 9C.
  • the main body 1 of the device V detaches from the support surface 3.

Landscapes

  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Air Bags (AREA)
  • Toys (AREA)
  • Transmission Devices (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Refuge Islands, Traffic Blockers, Or Guard Fence (AREA)
EP08000525A 2007-01-19 2008-01-12 Vorrichtung zur Tragflächenentfaltung Not-in-force EP1947415B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102007002948A DE102007002948B4 (de) 2007-01-19 2007-01-19 Vorrichtung zur Tragflächenentfaltung

Publications (2)

Publication Number Publication Date
EP1947415A1 EP1947415A1 (de) 2008-07-23
EP1947415B1 true EP1947415B1 (de) 2010-06-23

Family

ID=39290535

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08000525A Not-in-force EP1947415B1 (de) 2007-01-19 2008-01-12 Vorrichtung zur Tragflächenentfaltung

Country Status (5)

Country Link
US (1) US7919740B2 (es)
EP (1) EP1947415B1 (es)
AT (1) ATE472086T1 (es)
DE (1) DE102007002948B4 (es)
ES (1) ES2346484T3 (es)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102017113058A1 (de) 2017-06-14 2018-12-20 Deutsches Zentrum für Luft- und Raumfahrt e.V. Raumtransport-Fluggerät und Wiedereintritts-Fluggerät

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
IL189785A (en) * 2008-02-26 2013-07-31 Elbit Systems Ltd Foldable and layout board
RU2682152C1 (ru) * 2018-04-02 2019-03-14 Акционерное общество "Военно-промышленная корпорация "Научно-производственное объединение машиностроения" Устройство складывания аэродинамической поверхности летательного аппарата
CN109631684A (zh) * 2018-11-28 2019-04-16 成都云鼎智控科技有限公司 一种单轴式机翼机构以及具备该机翼机构的发射体
CN109625243B (zh) * 2018-12-24 2021-08-17 湖南云箭集团有限公司 一种折叠翼面展开气动辅助驱动装置
CN111994266B (zh) * 2020-09-02 2023-05-30 广西大学 折叠翼扑翼机
US11592272B2 (en) 2021-01-26 2023-02-28 Raytheon Company Aero-assisted missile fin or wing deployment system

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3978790A (en) * 1975-10-23 1976-09-07 The Boeing Company High altitude sonobuoy
DE8438296U1 (de) * 1984-12-31 1989-04-06 Heide, Marion, 4030 Ratingen Klappleitwerk für flügelstabilisierte Raketengeschosse
DE3447852A1 (de) 1984-12-31 1986-08-28 Heide, Marion, 4030 Ratingen Klappleitwerk fuer fluegelstabilisierte raketengeschosse
US5014931A (en) * 1990-08-29 1991-05-14 The United States Of America As Represented By The Secretary Of The Army Kinetic energy projectile with impact-ejected fins
DE4105142A1 (de) * 1991-02-20 1992-08-27 Diehl Gmbh & Co Projektil mit ausklappbarem leitwerk
FR2721702B1 (fr) * 1994-06-28 1996-08-14 Luchaire Defense Sa Dispositif de déploiement d'une ailette de projectile.
US5668347A (en) * 1996-09-13 1997-09-16 The United States Of America As Represented By The Secretary Of The Army Kinetic energy projectile with fin leading edge protection mechanisms
US6152041A (en) * 1998-05-29 2000-11-28 Leigh Aerosystems Corporation Device for extending the range of guided bombs
DE19906969B4 (de) * 1999-02-19 2004-10-14 Rheinmetall W & M Gmbh Aus einem Waffenrohr verschießbares leitwerkstabilisiertes Geschoß
DE10015514B4 (de) * 2000-03-30 2007-10-04 Rheinmetall Waffe Munition Gmbh Flügelstabilisiertes Geschoß
US6581871B2 (en) * 2001-06-04 2003-06-24 Smiths Aerospace, Inc. Extendable and controllable flight vehicle wing/control surface assembly
DE102004039770A1 (de) * 2004-08-16 2006-03-02 Diehl Bgt Defence Gmbh & Co. Kg Flügelanordnung
US7429017B2 (en) * 2005-07-21 2008-09-30 Raytheon Company Ejectable aerodynamic stability and control

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102017113058A1 (de) 2017-06-14 2018-12-20 Deutsches Zentrum für Luft- und Raumfahrt e.V. Raumtransport-Fluggerät und Wiedereintritts-Fluggerät
DE102017113058B4 (de) 2017-06-14 2023-04-27 Deutsches Zentrum für Luft- und Raumfahrt e.V. Raumtransport-Fluggerät

Also Published As

Publication number Publication date
DE102007002948B4 (de) 2009-04-02
DE102007002948A1 (de) 2008-07-31
ATE472086T1 (de) 2010-07-15
US20090008496A1 (en) 2009-01-08
ES2346484T3 (es) 2010-10-15
US7919740B2 (en) 2011-04-05
EP1947415A1 (de) 2008-07-23

Similar Documents

Publication Publication Date Title
EP1947415B1 (de) Vorrichtung zur Tragflächenentfaltung
DE102004062105B4 (de) Vorrichtung zum Schutz von Personen bei einem Frontalaufprall auf ein Kraftfahrzeug durch aktives Aufstellen dessen Fronthaube
DE102015101765A1 (de) Vortexgeneratoranordnung
DE102009025382A1 (de) Dekompressionseinrichtung für ein Luftfahrzeug
DE102015010395B3 (de) Frontklappenscharnier und zugehöriges Kraftfahrzeug
AT511710B1 (de) Vorrichtung zum anstellen einer motorhaube
DE3215434C2 (de) Riegelmechanismus für entfaltbare Solargeneratoren von Satelliten
DE102008022452A1 (de) Flugzeug mit aktiv steuerbaren Hilfsflügeln
DE2452053A1 (de) Einrichtung zum starten von raketengetriebenen flugkoerpern
DE19916028B4 (de) Einrichtung zur Luftwiderstandserzeugung
EP1857332A2 (de) Überrollschutzsystem für Kraftfahrzeuge mit mindestens einem aktiv aufstellbaren Überrollkörper
EP0178467B1 (de) Unbemannter Flugkörper mit einem Fallschirmbergesystem
EP1818646B1 (de) Wickelflügel für einen Flugkörper
EP2417023B1 (de) Flügel eines flugzeugs oder eines raumfahrzeugs mit einem beweglichen strömungskörper
EP1855076A1 (de) Wickelflügeln eines Flugkörpers
DE202015004305U1 (de) Vorrichtung zum Öffnen und Schließen ein oder mehrerer Bugklappen, insbesondere für Schienenfahrzeuge
DE3874706T2 (de) Vorfluegel eines flugzeuges.
DE2649643A1 (de) Raketengetriebener flugkoerper mit entfaltbaren stabilisierungsflaechen
WO2011026811A1 (de) Scharnier und verfahren zum betreiben eines scharniers
DE2723860A1 (de) Steueranordnung fuer ein ballistisches geschoss
DE102020105188A1 (de) Flugkörper-Finnenausklappeinrichtung, Flugkörper und Verfahren zum Betrieb eines Flugkörpers
DE102017113058A1 (de) Raumtransport-Fluggerät und Wiedereintritts-Fluggerät
DE102005006688A1 (de) Anordnung einer Klappe an einem Fahrzeug
DE102022003754B4 (de) Flugkörper
EP0459188B1 (de) Von einem Flugkörper wegklappbarer Flügel

Legal Events

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

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20080510

AK Designated contracting states

Kind code of ref document: A1

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

AX Request for extension of the european patent

Extension state: AL BA MK RS

AKX Designation fees paid

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

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

RTI1 Title (correction)

Free format text: APPARATUS FOR FIN DEPLOYMENT

GRAJ Information related to disapproval of communication of intention to grant by the applicant or resumption of examination proceedings by the epo deleted

Free format text: ORIGINAL CODE: EPIDOSDIGR1

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

RBV Designated contracting states (corrected)

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

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

REG Reference to a national code

Ref country code: DE

Ref legal event code: 8566

AK Designated contracting states

Kind code of ref document: B1

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

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

REG Reference to a national code

Ref country code: SE

Ref legal event code: TRGR

REG Reference to a national code

Ref country code: ES

Ref legal event code: FG2A

Ref document number: 2346484

Country of ref document: ES

Kind code of ref document: T3

REG Reference to a national code

Ref country code: GR

Ref legal event code: EP

Ref document number: 20100402198

Country of ref document: GR

REG Reference to a national code

Ref country code: NL

Ref legal event code: VDEP

Effective date: 20100623

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: 20100923

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: 20100623

LTIE Lt: invalidation of european patent or patent extension

Effective date: 20100623

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

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: 20100623

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: 20100623

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: 20100623

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: 20100623

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: 20100623

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

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: 20100623

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: 20100623

REG Reference to a national code

Ref country code: IE

Ref legal event code: FD4D

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

Ref country code: 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: 20100623

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: 20100623

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: 20100623

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: 20101023

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: 20100623

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

Ref country code: DK

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

Effective date: 20100623

Ref country code: IE

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

Effective date: 20100623

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

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

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

26N No opposition filed

Effective date: 20110324

BERE Be: lapsed

Owner name: DIEHL BGT DEFENCE G.M.B.H. & CO.KG

Effective date: 20110131

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

Ref country code: MC

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

Effective date: 20110131

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: 20110131

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

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: 20100623

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

Ref country code: TR

Payment date: 20120214

Year of fee payment: 5

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

Ref country code: IT

Payment date: 20120123

Year of fee payment: 5

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

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

Ref country code: LI

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

Effective date: 20120131

Ref country code: CH

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

Effective date: 20120131

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

Ref country code: SE

Payment date: 20130122

Year of fee payment: 6

Ref country code: ES

Payment date: 20130128

Year of fee payment: 6

Ref country code: GB

Payment date: 20130122

Year of fee payment: 6

Ref country code: FR

Payment date: 20130213

Year of fee payment: 6

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

Ref country code: LU

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

Effective date: 20110112

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

Ref country code: GR

Payment date: 20130117

Year of fee payment: 6

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

Ref country code: PT

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

Effective date: 20100623

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

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: 20100923

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

Effective date: 20100623

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 472086

Country of ref document: AT

Kind code of ref document: T

Effective date: 20130112

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: 20130112

REG Reference to a national code

Ref country code: SE

Ref legal event code: EUG

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20140112

REG Reference to a national code

Ref country code: GR

Ref legal event code: ML

Ref document number: 20100402198

Country of ref document: GR

Effective date: 20140801

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

Ref country code: GR

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

Effective date: 20140801

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20140930

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

Ref country code: FR

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

Effective date: 20140131

Ref country code: GB

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

Effective date: 20140112

Ref country code: SE

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

Effective date: 20140113

REG Reference to a national code

Ref country code: ES

Ref legal event code: FD2A

Effective date: 20150703

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

Ref country code: ES

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

Effective date: 20140113

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

Ref country code: IT

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

Effective date: 20140112

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 NON-PAYMENT OF DUE FEES

Effective date: 20140112