EP2608313A1 - Antenna pointing system - Google Patents

Antenna pointing system Download PDF

Info

Publication number
EP2608313A1
EP2608313A1 EP12008604.6A EP12008604A EP2608313A1 EP 2608313 A1 EP2608313 A1 EP 2608313A1 EP 12008604 A EP12008604 A EP 12008604A EP 2608313 A1 EP2608313 A1 EP 2608313A1
Authority
EP
European Patent Office
Prior art keywords
payload
pointing system
antenna pointing
mounting structure
movably
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP12008604.6A
Other languages
German (de)
French (fr)
Other versions
EP2608313B1 (en
Inventor
Richard O. Horth
Marc-André GODIN
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.)
MacDonald Dettwiler and Associates Corp
Original Assignee
MacDonald Dettwiler and Associates Corp
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 MacDonald Dettwiler and Associates Corp filed Critical MacDonald Dettwiler and Associates Corp
Publication of EP2608313A1 publication Critical patent/EP2608313A1/en
Application granted granted Critical
Publication of EP2608313B1 publication Critical patent/EP2608313B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • HELECTRICITY
    • H01ELECTRIC ELEMENTS
    • H01QANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00Details of, or arrangements associated with, antennas
    • H01Q1/12Supports; Mounting means
    • H01Q1/125Means for positioning
    • HELECTRICITY
    • H01ELECTRIC ELEMENTS
    • H01QANTENNAS, i.e. RADIO AERIALS
    • H01Q3/00Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system
    • H01Q3/02Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system using mechanical movement of antenna or antenna system as a whole
    • H01Q3/08Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system using mechanical movement of antenna or antenna system as a whole for varying two co-ordinates of the orientation

Definitions

  • the present invention relates to the field of antenna systems, and is more particularly concerned with pointing systems for steerable antennas.
  • steerable antennas it is well known in the art to use steerable (or tracking) antennas to communicate with a relatively moving target over a scan angle.
  • steerable RF (Radio Frequency signal) antennas preferably need to have precise pointing, high gain, low mass, and high reliability.
  • Satellites often contain two (2) degree of freedom pointing devices to communicate, sense, etc. with other satellites or bodies. Since the distances are large, the pointing accuracy and resolution is critical.
  • the payload of these pointing devices is variable. Some payloads are full antennas, portions of an antenna, sensors, etc.
  • the above first three (3) points are main advantages when using rotary actuators.
  • an antenna pointing system for selectively moving a payload relative to a mounting surface, said system comprising:
  • the flexible mounting structure is a universal joint, including bearings, flexures or the like, preferably located near a geometric center of the payload.
  • first and second rotary actuators connecting to respective said connecting rod with said second ends of said connecting rods movably connecting to corresponding first and second attachment points of the payload.
  • first and second attachment points are angularly spaced from one another relative to a rotation center of the flexible mounting structure, and the first and second attachment points are substantially adjacent a perimeter of the payload.
  • first and second attachment points are substantially 90 degrees apart from one another relative to the rotation center of the flexible mounting structure.
  • Figures 1a and 1b are side and rear elevation views, respectively, of an antenna reflector mounted with a prior art two-axis gimbal pointing system
  • Figure 2 is a top perspective view of an embodiment of an antenna pointing system in accordance with the present invention movably supporting an antenna reflector payload;
  • Figure 3 is an enlarged top perspective view of a rotary actuator of the embodiment of Figure 2 ;
  • Figure 4 is a partially broken enlarged top perspective view of a universal joint of the embodiment of Figure 2 ;
  • Figure 5 is a partially broken top plan view of the embodiment of Figure 2 .
  • FIG. 2 there is shown a schematic diagram of an embodiment of the low profile high resolution and torque antenna pointing system 10.
  • the pointing system 10 points a reflector, part of an RF (Radio Frequency signal) antenna 12 mounted on board of a spacecraft, represented by the mounting surface 14 situated in orbit.
  • the pointing system 10 consists of using rotary actuators 20 in conjunction with cranks 22 and connecting rods 24 to impart rotations to a payload structure 26, such as an antenna reflector assembly, which is movably held in place by a flexible mounting structure 28 as a universal joint structure or the like.
  • An example of the complete system 10 is shown in Figure 2 .
  • the RF performance is improved because the generally orthogonal first 30 and second 31 rotation axes of the universal joint 28 intersects a point proximate the geometric center of the reflector 26, to define the rotation center R thereof.
  • the system 10 uses two rotary actuators 20 to drive two degrees of freedom. Both rotary actuators 20 have their fixed part secured to the base plate 14 eliminating any mobile harnessing, such as RF rotary joint, electrical wiring, etc.
  • a crank 22 is assembled on the output of the moving part of both rotary actuators 20.
  • a rotary actuator 20 with its crank 22 is shown in Figure 3 .
  • An elongated connecting rod 24 has a first proximal end 32 movably connected to the shaft 23 of the crank 22 and the opposite second distal end 34 movably connected to the payload 26, at an attachment point 27 typically adjacent a perimeter thereof.
  • both ends 32, 34 are connected through spherical bearings 35, flexures or the like in order to allow angular displacements thereof between respective connecting elements.
  • the payload 26 is movably mounted on the surface 14 using the universal joint 28 typically consisting of one to two (1-2) static brackets 36 securable to the surface 14 and movably supporting a cross 38 about the first rotation axis 30 via at least one first bearing 40, flexure or the like, and one to two (1-2) moving brackets 42 extending from or secured to the payload 26 and movably supported by the cross 38 about the second rotation axis 31 via at least one second bearing 44, flexure or the like, as shown in Figure 4 .
  • the universal joint 28 typically consisting of one to two (1-2) static brackets 36 securable to the surface 14 and movably supporting a cross 38 about the first rotation axis 30 via at least one first bearing 40, flexure or the like, and one to two (1-2) moving brackets 42 extending from or secured to the payload 26 and movably supported by the cross 38 about the second rotation axis 31 via at least one second bearing 44, flexure or the like, as shown in Figure 4 .
  • the two attachment points 27 connecting to the two second distal ends 34 of the respective connecting rods 24 are typically angularly spaced from one another relative to the rotation center R of the flexible mounting structure 28, as illustrated by angle A.
  • Angle A is typically sufficient to make use of the full angular displacement range of the payload 26 about the flexible mounting structure 28. To this end, angle A is preferably around 90 degrees.

Landscapes

  • Variable-Direction Aerials And Aerial Arrays (AREA)
  • Aerials With Secondary Devices (AREA)

Abstract

An antenna pointing system (10) for selectively moving a payload (26) relative to a mounting surface (14) includes at least one rotary actuator (20) having a moving part (22) movable relative to a fixed part mounted on the surface (14). A connecting rod (24) movably connects to the moving part (22) and to the payload (26). A flexible mounting structure (28) movably attaches the payload (26) to the mounting surface (14).

Description

    FIELD OF THE INVENTION
  • The present invention relates to the field of antenna systems, and is more particularly concerned with pointing systems for steerable antennas.
  • BACKGROUND OF THE INVENTION
  • It is well known in the art to use steerable (or tracking) antennas to communicate with a relatively moving target over a scan angle. Especially in the aerospace industry when the antenna is on board of a spacecraft, such steerable RF (Radio Frequency signal) antennas preferably need to have precise pointing, high gain, low mass, and high reliability.
  • Satellites often contain two (2) degree of freedom pointing devices to communicate, sense, etc. with other satellites or bodies. Since the distances are large, the pointing accuracy and resolution is critical.
  • The payload of these pointing devices is variable. Some payloads are full antennas, portions of an antenna, sensors, etc.
  • Many different pointing devices have been devised in the past. The simplest one being two rotary actuators (RA) assembled in a sequential chain and holding the payload, such as a reflector, as shown in Figures 1a and 1b. Especially when relatively small scan angles are required, such as below +/- 30 degrees for example, these types of pointing devices have many disadvantages, or at least a few, among the following list:
    • high profile;
    • heavy mass, structurally inefficient;
    • high cost;
    • low accuracy;
    • low resolution;
    • low reliability;
    • need for Hold down and Release Mechanisms (HRM);
    • requires fixed predetermined stowed position for launch;
    • need for moving harness (RF rotary joint, electrical wiring, etc.); and/or
    • reduced RF performance in the case of a reflector pointing mechanism.
  • Accordingly, there is a need for an improved antenna pointing system.
  • SUMMARY OF THE INVENTION
  • It is therefore a general object of the present invention to provide an improved antenna pointing system that solves the above-mentioned problems.
  • Advantages of the antenna pointing system of the present invention are:
    1. 1. lower profile;
    2. 2. lower mass, structurally efficient;
    3. 3. lower cost;
    4. 4. higher accuracy;
    5. 5. higher resolution;
    6. 6. higher reliability;
    7. 7. eliminates need for Hold down and Release Mechanisms (HRM);
    8. 8. allows for last minute selection of stowed position for launch;
    9. 9. eliminated need for moving harness (RF rotary joint, electrical wiring, etc.): and/or
    10. 10. improved RF performance in the case of a reflector pointing mechanism.
  • The above first three (3) points are main advantages when using rotary actuators.
  • According to an aspect of the present invention there is provided an antenna pointing system for selectively moving a payload relative to a mounting surface, said system comprising:
    • at least one rotary actuator having a moving part being movable relative to a fixed part adapted for mounting on the surface;
    • a connecting rod movably connecting to the moving part at a first end thereof and adapted for movably connecting to the payload at a second end thereof; and
    • a flexible mounting structure for movably attaching the payload to the mounting surface.
  • Conveniently, the flexible mounting structure is a universal joint, including bearings, flexures or the like, preferably located near a geometric center of the payload.
  • In one embodiment, there are two rotary actuators with essentially the two second ends of the connecting rods connecting adjacent a perimeter of the payload, the two actuators being angularly spaced from one another relative to a rotation center of the flexible mounting structure, typically by an angle sufficient to make use of the full angular displacement range of the payload about the flexible mounting structure.
  • In one embodiment, there are first and second rotary actuators connecting to respective said connecting rod with said second ends of said connecting rods movably connecting to corresponding first and second attachment points of the payload.
  • Typically, the first and second attachment points are angularly spaced from one another relative to a rotation center of the flexible mounting structure, and the first and second attachment points are substantially adjacent a perimeter of the payload.
  • Conveniently, the first and second attachment points are substantially 90 degrees apart from one another relative to the rotation center of the flexible mounting structure.
  • Other objects and advantages of the present invention will become apparent from a careful reading of the detailed description provided herein, within appropriate reference to the accompanying drawings.
  • BRIEF DESCRIPTION OF THE DRAWINGS
  • In the annexed drawings, like reference characters indicate like elements throughout.
  • Figures 1a and 1b are side and rear elevation views, respectively, of an antenna reflector mounted with a prior art two-axis gimbal pointing system;
  • Figure 2 is a top perspective view of an embodiment of an antenna pointing system in accordance with the present invention movably supporting an antenna reflector payload;
  • Figure 3 is an enlarged top perspective view of a rotary actuator of the embodiment of Figure 2;
  • Figure 4 is a partially broken enlarged top perspective view of a universal joint of the embodiment of Figure 2; and
  • Figure 5 is a partially broken top plan view of the embodiment of Figure 2.
  • DETAILED DESCRIPTION OF THE INVENTION
  • With reference to the annexed drawings the preferred embodiments of the present invention will be herein described for indicative purpose and by no means as of limitation.
  • Referring to Figures 2 and 3, there is shown a schematic diagram of an embodiment of the low profile high resolution and torque antenna pointing system 10. In the case presented, the pointing system 10 points a reflector, part of an RF (Radio Frequency signal) antenna 12 mounted on board of a spacecraft, represented by the mounting surface 14 situated in orbit. The pointing system 10 consists of using rotary actuators 20 in conjunction with cranks 22 and connecting rods 24 to impart rotations to a payload structure 26, such as an antenna reflector assembly, which is movably held in place by a flexible mounting structure 28 as a universal joint structure or the like. An example of the complete system 10 is shown in Figure 2.
  • In the embodiment 10, the RF performance is improved because the generally orthogonal first 30 and second 31 rotation axes of the universal joint 28 intersects a point proximate the geometric center of the reflector 26, to define the rotation center R thereof. The system 10 uses two rotary actuators 20 to drive two degrees of freedom. Both rotary actuators 20 have their fixed part secured to the base plate 14 eliminating any mobile harnessing, such as RF rotary joint, electrical wiring, etc. A crank 22 is assembled on the output of the moving part of both rotary actuators 20. A rotary actuator 20 with its crank 22 is shown in Figure 3.
  • An elongated connecting rod 24 has a first proximal end 32 movably connected to the shaft 23 of the crank 22 and the opposite second distal end 34 movably connected to the payload 26, at an attachment point 27 typically adjacent a perimeter thereof. Typically, both ends 32, 34 are connected through spherical bearings 35, flexures or the like in order to allow angular displacements thereof between respective connecting elements. The payload 26 is movably mounted on the surface 14 using the universal joint 28 typically consisting of one to two (1-2) static brackets 36 securable to the surface 14 and movably supporting a cross 38 about the first rotation axis 30 via at least one first bearing 40, flexure or the like, and one to two (1-2) moving brackets 42 extending from or secured to the payload 26 and movably supported by the cross 38 about the second rotation axis 31 via at least one second bearing 44, flexure or the like, as shown in Figure 4.
  • As best seen in Figure 5, the two attachment points 27 connecting to the two second distal ends 34 of the respective connecting rods 24 are typically angularly spaced from one another relative to the rotation center R of the flexible mounting structure 28, as illustrated by angle A. Angle A is typically sufficient to make use of the full angular displacement range of the payload 26 about the flexible mounting structure 28. To this end, angle A is preferably around 90 degrees.

Claims (7)

  1. An antenna pointing system (10) for selectively moving a payload (26) relative to a mounting surface (14), said system (10) comprising:
    - at least one rotary actuator (20) having a moving part (22) being movable relative to a fixed part adapted for mounting on the surface (14);
    - a connecting rod (24) movably connecting to the moving part (22) at a first end (32) thereof and adapted for movably connecting to the payload (26) at a second end (34) thereof; and
    - a flexible mounting structure (28) for movably attaching the payload (26) to the mounting surface (14).
  2. The antenna pointing system (10) of claim 1. wherein the at least one rotary actuator includes first and second rotary actuators (20) connecting to respective said connecting rod (24) with said second ends (34) of said connecting rods (24) movably connecting to corresponding first and second attachment points (27) of the payload (26).
  3. The antenna pointing system (10) of claim 2, wherein the first and second attachment points (27) are angularly spaced (A) from one another relative to a rotation center (R) of the flexible mounting structure (28).
  4. The antenna pointing system (10) of claim 3, wherein the first and second attachment points (27) are substantially adjacent a perimeter of the payload (26).
  5. The antenna pointing system (10) of claim 2, wherein the first and second attachment points (27) are substantially 90 degrees apart (A) from one another relative to the rotation center (R) of the flexible mounting structure (28).
  6. The antenna pointing system (10) of claim 1, wherein the flexible mounting structure (28) is located adjacent a geometric center of the payload (26).
  7. The antenna pointing system (10) of claim 1, wherein the flexible mounting structure is a universal joint structure (28).
EP12008604.6A 2011-12-23 2012-12-23 Antenna pointing system Active EP2608313B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US201161630985P 2011-12-23 2011-12-23

Publications (2)

Publication Number Publication Date
EP2608313A1 true EP2608313A1 (en) 2013-06-26
EP2608313B1 EP2608313B1 (en) 2019-02-13

Family

ID=47632672

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12008604.6A Active EP2608313B1 (en) 2011-12-23 2012-12-23 Antenna pointing system

Country Status (2)

Country Link
EP (1) EP2608313B1 (en)
JP (1) JP6068129B2 (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109649697A (en) * 2019-01-14 2019-04-19 上海卫星工程研究所 Connection method between a kind of satellite capsule under overconstrained condition
WO2020079290A1 (en) 2018-10-17 2020-04-23 Airbus Defence And Space, S.A. Articulated mechanism and articulated aiming system comprising the mechanism

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH04266203A (en) * 1991-02-20 1992-09-22 Fujitsu General Ltd Mount for antenna system
JP2004064195A (en) * 2002-07-25 2004-02-26 Toshiba Corp Driver and antenna assembly
DE102009030239A1 (en) * 2009-06-23 2010-12-30 Eads Deutschland Gmbh Holder for a movable sensor
US20110043433A1 (en) * 2009-08-24 2011-02-24 Jurgen Zimmermann Positioning equipment for aligning a device
US20110234464A1 (en) * 2010-03-23 2011-09-29 Lockheed Martin Corporation Pivot radar

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3262321A (en) * 1963-09-16 1966-07-26 Jr George E Moul Two-rod seeker head
US4251819A (en) * 1978-07-24 1981-02-17 Ford Aerospace & Communications Corp. Variable support apparatus

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH04266203A (en) * 1991-02-20 1992-09-22 Fujitsu General Ltd Mount for antenna system
JP2004064195A (en) * 2002-07-25 2004-02-26 Toshiba Corp Driver and antenna assembly
DE102009030239A1 (en) * 2009-06-23 2010-12-30 Eads Deutschland Gmbh Holder for a movable sensor
US20110043433A1 (en) * 2009-08-24 2011-02-24 Jurgen Zimmermann Positioning equipment for aligning a device
US20110234464A1 (en) * 2010-03-23 2011-09-29 Lockheed Martin Corporation Pivot radar

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2020079290A1 (en) 2018-10-17 2020-04-23 Airbus Defence And Space, S.A. Articulated mechanism and articulated aiming system comprising the mechanism
CN113169439A (en) * 2018-10-17 2021-07-23 空中客车防务及航天股份有限公司 Articulated mechanism and articulated pointing system comprising said mechanism
US11652269B2 (en) 2018-10-17 2023-05-16 Airbus Defence and Space S.A. Articulated mechanism and articulated aiming system comprising the mechanism
CN113169439B (en) * 2018-10-17 2024-05-07 空中客车防务及航天股份有限公司 Hinge mechanism and hinge pointing system comprising said mechanism
CN109649697A (en) * 2019-01-14 2019-04-19 上海卫星工程研究所 Connection method between a kind of satellite capsule under overconstrained condition
CN109649697B (en) * 2019-01-14 2020-10-09 上海卫星工程研究所 Satellite cabin connection method under over-constrained condition

Also Published As

Publication number Publication date
JP2013146059A (en) 2013-07-25
EP2608313B1 (en) 2019-02-13
JP6068129B2 (en) 2017-01-25

Similar Documents

Publication Publication Date Title
US9172128B2 (en) Antenna pointing system
US9212692B2 (en) Compact flexible cardan joint and spacecraft comprising such a joint
JP6495452B2 (en) antenna
JP2012531144A (en) Movable sensor holder
JP4690610B2 (en) Positioning device and positioning system
EP2996197A1 (en) Wide scan steerable antenna
US6987492B1 (en) Tetrahedral positioner for an antenna
JP5732689B2 (en) Through pivot with web
EP2608313B1 (en) Antenna pointing system
US9676502B2 (en) Assembly for aiming an instrument
RU2765769C1 (en) Articulated mechanism and articulated orientation system containing this mechanism
CN112373736A (en) Satellite device for omnidirectional observation
JP6361229B2 (en) Radar apparatus and control method thereof
RU2314607C1 (en) Stabilizing device
JP2002043820A (en) Antenna- or radar-mounted driving unit
US10351265B1 (en) Rotating gimbal system
JP6349870B2 (en) Radar antenna device
US11993406B2 (en) Device for orienting a load in two orthogonal axes of rotation
JPH08107305A (en) Antenna reflecting mirror
JP2000187150A (en) Movable mirror controller

Legal Events

Date Code Title Description
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

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: 20131011

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

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: 20180822

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

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: 1096730

Country of ref document: AT

Kind code of ref document: T

Effective date: 20190215

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602012056589

Country of ref document: DE

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20190213

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 FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190613

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: 20190513

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: 20190213

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: 20190213

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: 20190213

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: 20190213

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: 20190213

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: 20190213

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: 20190513

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: 20190613

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: 20190514

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: 20190213

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 1096730

Country of ref document: AT

Kind code of ref document: T

Effective date: 20190213

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: 20190213

Ref country code: IT

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: 20190213

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: 20190213

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: 20190213

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: 20190213

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: 20190213

Ref country code: ES

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: 20190213

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: 20190213

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602012056589

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: 20190213

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: 20190213

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: AT

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: 20190213

26N No opposition filed

Effective date: 20191114

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

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: 20190213

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: 20190213

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 602012056589

Country of ref document: DE

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20191231

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 FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190213

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

Effective date: 20191223

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: 20191223

Ref country code: IE

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

Effective date: 20191223

Ref country code: GB

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

Effective date: 20191223

Ref country code: DE

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

Effective date: 20200701

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: 20191231

Ref country code: BE

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

Effective date: 20191231

Ref country code: CH

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

Effective date: 20191231

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: 20190213

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: 20121223

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: 20190213

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: 20190213

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

Effective date: 20230531

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

Ref country code: FR

Payment date: 20231211

Year of fee payment: 12