EP2083238A2 - Folding fin with unfolding device - Google Patents
Folding fin with unfolding device Download PDFInfo
- Publication number
- EP2083238A2 EP2083238A2 EP09000744A EP09000744A EP2083238A2 EP 2083238 A2 EP2083238 A2 EP 2083238A2 EP 09000744 A EP09000744 A EP 09000744A EP 09000744 A EP09000744 A EP 09000744A EP 2083238 A2 EP2083238 A2 EP 2083238A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- wing
- folding
- root
- wing surface
- folding wing
- 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
Links
- 238000009434 installation Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000002411 adverse Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000004146 energy storage Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 230000002441 reversible effect Effects 0.000 description 1
- 230000001960 triggered effect Effects 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
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
- F42B10/16—Wrap-around fins
-
- 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
- a deployment system for folding wings in which an actuator causes a pulling operation on a rope, whereby the pivotally mounted part of the folding wing is transferred from the transport to the functional position.
- the actuator works hydraulically or electromagnetically.
- the triggering of the actuator leads to a linear movement of an actuating means, wherein the pull rope is deflected both at the free end of the actuating means and on a deflection roller.
- the folding wing consists of a wing root, an inner wing surface and an outer wing surface, wherein the wing root is connected to the trunk via a rotating device, that the inner wing surface at its root via a first axis of rotation with the wing root is connected, that the outer wing surface is articulated via a further axis of rotation at the outer edge of the inner wing surface, both axes of rotation approximately parallel to each other and in the direction of flight, that a coil spring to which a pull rope is fixed, biased in the rest position of the folding wing in the inner wing surface is arranged, that the traction cable is guided by the coil spring via a first guide roller, which is connected transversely but not longitudinally movable by means of a first fastening means with the wing root, and is then guided over a second deflection roller welc he he he means of a second fastener is transverse but not longitudinally movably attached to the root of the outer wing
- Such a device for folding wing unfolding can be easily integrated in the interior of a part of the folding wing due to their flat and compact design.
- the device also requires no additional resources that would otherwise have to be accommodated in the folding wing or in the fuselage.
- this device is also much easier than known embodiments. It is only a device for releasing the prestressed coil spring required. Thus, it is easily possible to accommodate this device in a slim folding wing. It continues advantageous that this device requires no auxiliary devices for energy storage and thus is easier than known devices. This can be avoided especially in aerodynamic active surfaces unwanted additional weight.
- This tensile force is sufficient for the deployment of the folding wing 9, 12, 13 in any case. This applies to environmental conditions, such as air and water.
- FIG. 3 finally shows the fully unfolded folding wing from the view side as in FIG. 1 ,
- the coil spring 20 and a part of the traction cable 21 have been angled to the drive device 1 during the unfolding process and are still under pretension.
- the latches 7, 8 are locked.
- the pulleys 2, 3 are located locally much closer together than in the FIG. 1 ,
- the unfolded folding wing is in a stable, resilient and without aids no longer reversible locking state.
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Aerials With Secondary Devices (AREA)
- Storing, Repeated Paying-Out, And Re-Storing Of Elongated Articles (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
Description
Die Erfindung betrifft einen Klappflügel mit einem innerhalb des Klappflügels angeordneten Betätigungsmittel, welches mit einem Zugseil verbunden ist, das über wenigstens eine Vorrichtung zur Richtungsänderung geführt wird und das am anderen Ende an einem Teil des Klappflügels befestigt ist.The invention relates to a folding wing with an actuating means arranged within the folding wing, which is connected to a pull rope, which is guided via at least one device for changing direction and which is fastened at the other end to a part of the folding wing.
Flugkörper sind üblicherweise bis zu ihrem Start in einer Abschussvorrichtung gelagert. Diese Abschussvorrichtung ist bei der Dimensionierung des Innenraums so bemessen, dass der Flugkörper nur mit angeklappten Tragflügeln oder Leitwerksflügeln darin untergebracht werden kann. Dies hat zur Entwicklung verschiedenartiger Ausführungsformen von Klappflügeln und entsprechenden Einrichtungen zur Entfaltung der Klappflügel geführt.Missiles are usually stored in a launcher until their launch. This launcher is dimensioned in the dimensioning of the interior so that the missile can only be accommodated therein with hinged wings or tail wings. This has led to the development of various embodiments of folding wings and corresponding devices for the deployment of the folding wings.
Aus der
Außerdem benötigt der vorgeschlagene Aktuator in jedem Fall zusätzlichen Einbauraum für die zur Auslösung benötigten weiteren Einrichtungen. Im Fall eines hydraulischen Aktuators ist dies der Vorratsraum für die Hydraulikflüssigkeit und die Einrichtung zur Erzeugung des benötigten Druckes. Im Fall des elektromagnetischen Aktuators muss eine entsprechend dimensionierte Energiequelle bereitgestellt werden. Darüber hinaus kann der durch die Art der Umlenkung bedingte Verlust an Zugkraft sich im praktischen Betrieb nachteilig auswirken,In addition, the proposed actuator requires in any case additional installation space for the required for triggering other facilities. In the case of a hydraulic actuator, this is the reservoir for the hydraulic fluid and the means for generating the required pressure. In the case of the electromagnetic actuator, an appropriately sized power source must be provided. In addition, by the nature of the Deflection-related loss of traction in the practical operation adversely affect
Es ist deshalb Aufgabe der Erfindung, eine besonders kompakte und funktionssichere Einrichtung für die Klappflügelentfaltung bereit zu stellen, welche die vorgenannten Nachteile vermeidet.It is therefore an object of the invention to provide a particularly compact and reliable device for the folding wing deployment, which avoids the aforementioned disadvantages.
Die erfindungsgemäße Lösung dieser Aufgabe besteht darin, dass der Klappflügel aus einer Flügelwurzel, einer inneren Flügelfläche und einer äußeren Flügelfläche besteht, wobei die Flügelwurzel mit dem Rumpf über eine Dreheinrichtung verbunden ist, dass die innere Flügelfläche an ihrer Wurzel über eine erste Drehachse mit der Flügelwurzel verbunden ist, dass die äußere Flügelfläche über eine weitere Drehachse am äußeren Rand der inneren Flügelfläche angelenkt ist, wobei beide Drehachsen etwa zueinander parallel und in Flugrichtung verlaufen, dass eine Spiralfeder, an der ein Zugseil befestigt ist, in der Ruhestellung des Klappflügels vorgespannt in der inneren Flügelfläche angeordnet ist, dass das Zugseil von der Spiralfeder kommend über eine erste Umlenkrolle geführt wird, welche mittels eines ersten Befestigungsmittels quer- aber nicht längsbeweglich mit der Flügelwurzel verbunden ist, und anschließend über eine zweite Umlenkrolle geführt wird, welche mittels eines zweiten Befestigungsmittels queraber nicht längsbeweglich an der Wurzel der äußeren Flügelfläche befestigt ist, und wobei das freie Ende des Zugseils fest mit der inneren Flügelfläche verbunden ist.The solution of this problem according to the invention is that the folding wing consists of a wing root, an inner wing surface and an outer wing surface, wherein the wing root is connected to the trunk via a rotating device, that the inner wing surface at its root via a first axis of rotation with the wing root is connected, that the outer wing surface is articulated via a further axis of rotation at the outer edge of the inner wing surface, both axes of rotation approximately parallel to each other and in the direction of flight, that a coil spring to which a pull rope is fixed, biased in the rest position of the folding wing in the inner wing surface is arranged, that the traction cable is guided by the coil spring via a first guide roller, which is connected transversely but not longitudinally movable by means of a first fastening means with the wing root, and is then guided over a second deflection roller welc he he he means of a second fastener is transverse but not longitudinally movably attached to the root of the outer wing surface, and wherein the free end of the traction cable is firmly connected to the inner wing surface.
Eine derartige Einrichtung zur Klappflügelentfaltung kann aufgrund ihrer flachen und kompakten Bauweise leicht im Inneren eines Teils des Klappflügels baulich integriert werden. Die Einrichtung benötigt darüber hinaus keine zusätzlichen Betriebsmittel, die sonst im Klappflügel oder im Rumpf untergebracht werden müssten. Damit ist diese Einrichtung auch wesentlich leichter als bekannte Ausführungsformen. Es ist lediglich eine Vorrichtung zur Freigabe der vorgespannten Spiralfeder erforderlich. Somit ist es leicht möglich, diese Einrichtung auch in einem schlanken Klappflügel unterzubringen. Weiterhin ist es von Vorteil, dass diese Einrichtung ohne Hilfseinrichtungen für die Energiespeicherung auskommt und somit leichter als bekannte Einrichtungen ist. Damit kann gerade in aerodynamischen Wirkflächen unerwünschtes Zusatzgewicht vermieden werden.Such a device for folding wing unfolding can be easily integrated in the interior of a part of the folding wing due to their flat and compact design. The device also requires no additional resources that would otherwise have to be accommodated in the folding wing or in the fuselage. Thus, this device is also much easier than known embodiments. It is only a device for releasing the prestressed coil spring required. Thus, it is easily possible to accommodate this device in a slim folding wing. It continues advantageous that this device requires no auxiliary devices for energy storage and thus is easier than known devices. This can be avoided especially in aerodynamic active surfaces unwanted additional weight.
Ein Ausführungsbeispiel der Erfindung ist in der Zeichnung schematisch vereinfacht dargestellt und wird im Folgenden näher beschrieben. Es zeigen:
-
Fig. 1 : einen geöffneten Klappflügel in der Ruhestellung, -
Fig. 2 : einen Klappflügel in der entfalteten Stellung, -
Fig. 3 : einen teilweise geöffneten Klappflügel in der entfalteten Stellung.
-
Fig. 1 : an open folding wing in the rest position, -
Fig. 2 a folding wing in the unfolded position, -
Fig. 3 : a partially opened folding wing in the unfolded position.
Die
Eine weitere, ebenfalls außen liegende Drehachse 11 bildet in gleicher Weise die Verbindung zwischen der inneren Flügelfläche 12 und der äußeren Flügelfläche 9. Nach Entfaltung des Klappflügels erfolgt bei Erreichen der Arbeitsstellung, die in den
Die Entfaltvorrichtung für den Klappflügel ist im Wesentlichen im Innenraum der inneren Flügelfläche 12 untergebracht. Zur Veranschaulichung deren Einbaulage ist in der
An der Spiralfeder 20 ist ein Zugseil 21 befestigt, welches nacheinander über die Umlenkrollen 2, 3 nach Art eines Flaschenzuges geführt wird und schließlich etwa in der Mitte der inneren Flügelfläche an einem geeigneten Punkt beispielsweise verschraubt 30 wird. Die erste Umlenkrolle 2 ist mittels eines ersten Befestigungsmittels 31 an der Flügelwurzel 13 befestigt 19. Als Befestigungsmittel 31 eignet sich beispielsweise ein Drahtseil, das zwar in Querrichtung flexibel, aber in Längsrichtung nicht dehnbar ist. Das Gleiche gilt auch für das weitere Befestigungsmittel 32, mit dem die weitere Umlenkrolle 3 an der Wurzel des äußeren Klappflügels 9 befestigt 18 ist.On the
Die Spiralfeder weist den Vorteil eines langen Federweges auf, mit dessen Hilfe ab der Auslösung der Befestigung 5 des Klappflügels das Zugseil eingezogen und in der Antriebsvorrichtung 1 aufgewickelt wird. Dabei wirkt ein gleichmäßiger kräftiger Zug über das Zugseil 21 auf die beiden Umlenkrollen 2, 3. Die von der Antriebseinrichtung 1 aufgewickelte Weglänge des Zugseils 21 verteilt sich derart auf die Umlenkrollen, dass jede von beiden sich etwa ein Viertel des vom Zugseil zurückgelegten Wegs auf die andere Umlenkrolle zu bewegt. Die dabei von den Umlenkrollen 2, 3 auf die Befestigungsmittel 31, 32 ausgeübte Kraft erhöht sich dabei umgekehrt proportional. Auf diese Weise entsteht ein kräftiger Zug zwischen den Befestigungspunkte 18, 19 der beiden Befestigungsmittel 31, 32.The coil spring has the advantage of a long spring travel, with the help from the triggering of the
Diese Zugkraft reicht zur Entfaltung des Klappflügels 9, 12, 13 in jedem Fall aus. Dies gilt für Umgebungsbedingungen sowohl wie Luft als auch Wasser.This tensile force is sufficient for the deployment of the folding
Die Vorspannung und die Weglänge der Spiralfeder und des Zugseils sind so ausreichend dimensioniert, dass unter allen Umständen die Arbeitsstellung des Klappflügels, die in den
Es wird noch darauf hingewiesen, dass in der
In der
Die
Claims (2)
dadurch gekennzeichnet,
characterized,
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE200810005705 DE102008005705A1 (en) | 2008-01-24 | 2008-01-24 | Folding wing with unfolding device |
Publications (3)
Publication Number | Publication Date |
---|---|
EP2083238A2 true EP2083238A2 (en) | 2009-07-29 |
EP2083238A3 EP2083238A3 (en) | 2013-05-22 |
EP2083238B1 EP2083238B1 (en) | 2014-01-08 |
Family
ID=40578683
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP20090000744 Active EP2083238B1 (en) | 2008-01-24 | 2009-01-21 | Folding fin with unfolding device |
Country Status (2)
Country | Link |
---|---|
EP (1) | EP2083238B1 (en) |
DE (2) | DE202008018033U1 (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN108688793A (en) * | 2018-07-27 | 2018-10-23 | 中国工程物理研究院总体工程研究所 | Cartridge type emits unmanned plane wing-folding unfolding mechanism |
US10429158B2 (en) | 2015-11-06 | 2019-10-01 | Mbda Deutschland Gmbh | Folding wing for a missile and a missile having at least one folding wing arranged thereon |
RU2770956C1 (en) * | 2021-12-21 | 2022-04-25 | Акционерное общество "Машиностроительное конструкторское бюро "Факел" имени академика П.Д. Грушина | Mechanism for opening and locking handlebars with two folding sections |
Families Citing this family (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN104677199B (en) * | 2015-01-21 | 2016-07-13 | 浙江理工大学 | A kind of single driving folds rudder face synchronous expansion mechanism more |
DE102015014367B4 (en) | 2015-11-06 | 2020-07-16 | Mbda Deutschland Gmbh | Folding wing for a missile and missile with at least one folding wing arranged thereon |
DE102017113058B4 (en) | 2017-06-14 | 2023-04-27 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | space transport aircraft |
US11685510B2 (en) | 2018-11-01 | 2023-06-27 | Viettel Group | Wing deployment mechanism and design method using pneumatic technique |
RU2730903C1 (en) * | 2019-09-10 | 2020-08-26 | Акционерное общество "Машиностроительное конструкторское бюро "Факел" имени Академика П.Д. Грушина" | Opening and locking mechanism of aerodynamic rudder with two axes of folding |
CN112985190A (en) * | 2021-04-13 | 2021-06-18 | 西安航天动力技术研究所 | Volute spiral spring type folding missile wing unfolding mechanism |
Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2369177A (en) | 1989-06-02 | 2002-05-22 | British Aerospace | Aerofoil deployment system |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE2045687C2 (en) * | 1970-09-16 | 1982-08-12 | Technisch-Mathematische Studiengesellschaft mbH, 5300 Bonn | Time delayed aircraft function trigger - has thin holder disc secured to jet engine nozzle by adhesion or solder in nozzle groove, with tie line for function triggering |
GB2140136B (en) * | 1983-05-14 | 1987-05-07 | British Aerospace | Folding fin assembly for missiles |
DE3838735C2 (en) * | 1988-11-15 | 1997-12-18 | Diehl Gmbh & Co | Folding wing, especially for one floor |
US5762294A (en) * | 1997-03-31 | 1998-06-09 | The United States Of America As Represented By The Secretary Of The Army | Wing deployment device |
US7040210B2 (en) * | 2003-02-18 | 2006-05-09 | Lockheed Martin Corporation | Apparatus and method for restraining and releasing a control surface |
-
2008
- 2008-01-24 DE DE202008018033U patent/DE202008018033U1/en not_active Expired - Lifetime
- 2008-01-24 DE DE200810005705 patent/DE102008005705A1/en not_active Ceased
-
2009
- 2009-01-21 EP EP20090000744 patent/EP2083238B1/en active Active
Patent Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2369177A (en) | 1989-06-02 | 2002-05-22 | British Aerospace | Aerofoil deployment system |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10429158B2 (en) | 2015-11-06 | 2019-10-01 | Mbda Deutschland Gmbh | Folding wing for a missile and a missile having at least one folding wing arranged thereon |
CN108688793A (en) * | 2018-07-27 | 2018-10-23 | 中国工程物理研究院总体工程研究所 | Cartridge type emits unmanned plane wing-folding unfolding mechanism |
CN108688793B (en) * | 2018-07-27 | 2023-11-24 | 中国工程物理研究院总体工程研究所 | Folding and unfolding mechanism for wings of barrel-type launching unmanned aerial vehicle |
RU2770956C1 (en) * | 2021-12-21 | 2022-04-25 | Акционерное общество "Машиностроительное конструкторское бюро "Факел" имени академика П.Д. Грушина | Mechanism for opening and locking handlebars with two folding sections |
Also Published As
Publication number | Publication date |
---|---|
DE102008005705A1 (en) | 2009-07-30 |
EP2083238B1 (en) | 2014-01-08 |
DE202008018033U1 (en) | 2011-04-14 |
EP2083238A3 (en) | 2013-05-22 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP2083238B1 (en) | Folding fin with unfolding device | |
EP2255109B1 (en) | Parking lock system for an automatic transmission | |
DE112014002381T5 (en) | Closing plate counterweight mechanism with friction device | |
DE202008011513U1 (en) | A door stay | |
DE202011109983U1 (en) | Belt drive for tensile and compressive stress | |
DE69722026T2 (en) | END PIECE OF A CASE FOR A BOWDENZUG | |
DE3838738A1 (en) | PROJECTILE WITH FOLD-OUT WINGS | |
DE102015014368A1 (en) | Folding wing for a missile and a missile with at least one folding wing arranged thereon | |
DE2206116C3 (en) | Pulling device with two locking mechanisms that can be moved back and forth at the same time | |
DE1506024B1 (en) | Equipment in aircraft for the lateral and vertical guidance and fixing of decks in the hold | |
DE102015004703B4 (en) | Folding wing system | |
DE102016115622A1 (en) | Locking system for locking a lid in a motor vehicle | |
EP3032213A1 (en) | Folging fin system | |
DE60212897T2 (en) | Quick release device for an electric bus door | |
DE202013104879U1 (en) | Locking system for multi-point locking of doors | |
DE102017100731A1 (en) | Unlocking device for opening a door with a panic lock, in particular a touchbar, with a drive for automatically opening the panic lock | |
DE102020102207A1 (en) | Device for moving a sliding door or folding-sliding door | |
DE4025516C2 (en) | Missile wing locking device | |
DE102019201047A1 (en) | Unlocking mechanism for a cover of a trunk of a motor vehicle | |
DE1801344B2 (en) | Opposing claw latch | |
EP3835710B1 (en) | Missile with pyrotechnic unlocking | |
DE3101436A1 (en) | Device for automatic unfolding and locking of components | |
EP3335592B1 (en) | Locking device for a locking fitting for a frame and frame with a locking fitting | |
DE102020200646A1 (en) | Espagnolette fitting for a secondary sash of a double sash window | |
AT224465B (en) | Vehicle door with two or more leaves, in particular for vehicles with a curved outer wall |
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 |
|
AK | Designated contracting states |
Kind code of ref document: A2 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 MK MT NL NO PL PT RO SE SI SK TR |
|
AX | Request for extension of the european patent |
Extension state: AL BA RS |
|
RAP1 | Party data changed (applicant data changed or rights of an application transferred) |
Owner name: MBDA DEUTSCHLAND GMBH |
|
PUAL | Search report despatched |
Free format text: ORIGINAL CODE: 0009013 |
|
AK | Designated contracting states |
Kind code of ref document: A3 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 MK MT NL NO PL PT RO SE SI SK TR |
|
AX | Request for extension of the european patent |
Extension state: AL BA RS |
|
RIC1 | Information provided on ipc code assigned before grant |
Ipc: F42B 10/16 20060101AFI20130418BHEP Ipc: F42B 10/14 20060101ALN20130418BHEP |
|
17P | Request for examination filed |
Effective date: 20130613 |
|
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
RIC1 | Information provided on ipc code assigned before grant |
Ipc: F42B 10/16 20060101AFI20130716BHEP Ipc: F42B 10/14 20060101ALN20130716BHEP |
|
INTG | Intention to grant announced |
Effective date: 20130805 |
|
GRAS | Grant fee paid |
Free format text: ORIGINAL CODE: EPIDOSNIGR3 |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): DE FR GB NO |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: FG4D Free format text: NOT ENGLISH |
|
AKX | Designation fees paid |
Designated state(s): DE FR GB NO |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R096 Ref document number: 502009008618 Country of ref document: DE Effective date: 20140220 |
|
REG | Reference to a national code |
Ref country code: NO Ref legal event code: T2 Effective date: 20140108 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R097 Ref document number: 502009008618 Country of ref document: DE |
|
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: 20141009 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R097 Ref document number: 502009008618 Country of ref document: DE Effective date: 20141009 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 8 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 9 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 10 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: GB Payment date: 20220119 Year of fee payment: 14 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: NO Payment date: 20220121 Year of fee payment: 14 Ref country code: FR Payment date: 20220119 Year of fee payment: 14 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: DE Payment date: 20230131 Year of fee payment: 15 |
|
P01 | Opt-out of the competence of the unified patent court (upc) registered |
Effective date: 20230510 |
|
REG | Reference to a national code |
Ref country code: NO Ref legal event code: MMEP |
|
GBPC | Gb: european patent ceased through non-payment of renewal fee |
Effective date: 20230121 |
|
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 NON-PAYMENT OF DUE FEES Effective date: 20230131 Ref country code: GB Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20230121 |
|
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: 20230131 |