EP1196733B1 - Geschosslenkung mittels einer ringanordnung und optisch ausgelösten ablenkvorrichtungen - Google Patents

Geschosslenkung mittels einer ringanordnung und optisch ausgelösten ablenkvorrichtungen Download PDF

Info

Publication number
EP1196733B1
EP1196733B1 EP00986176A EP00986176A EP1196733B1 EP 1196733 B1 EP1196733 B1 EP 1196733B1 EP 00986176 A EP00986176 A EP 00986176A EP 00986176 A EP00986176 A EP 00986176A EP 1196733 B1 EP1196733 B1 EP 1196733B1
Authority
EP
European Patent Office
Prior art keywords
projectile
sensing elements
photoconductive sensing
course
target
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.)
Expired - Lifetime
Application number
EP00986176A
Other languages
English (en)
French (fr)
Other versions
EP1196733A2 (de
EP1196733A4 (de
Inventor
Tibor G. Horwath
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.)
General Dynamics Ordnance and Tactical Systems Inc
Original Assignee
General Dynamics Ordnance and Tactical Systems Inc
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 General Dynamics Ordnance and Tactical Systems Inc filed Critical General Dynamics Ordnance and Tactical Systems Inc
Publication of EP1196733A2 publication Critical patent/EP1196733A2/de
Publication of EP1196733A4 publication Critical patent/EP1196733A4/de
Application granted granted Critical
Publication of EP1196733B1 publication Critical patent/EP1196733B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22—Homing guidance systems
    • F41G7/226—Semi-active homing systems, i.e. comprising a receiver and involving auxiliary illuminating means, e.g. using auxiliary guiding missiles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22—Homing guidance systems
    • F41G7/2273—Homing guidance systems characterised by the type of waves
    • F41G7/2293—Homing guidance systems characterised by the type of waves using electromagnetic waves other than radio waves
    • 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
    • F42B10/60—Steering arrangements
    • F42B10/66—Steering by varying intensity or direction of thrust
    • F42B10/661—Steering by varying intensity or direction of thrust using several transversally acting rocket motors, each motor containing an individual propellant charge, e.g. solid charge

Definitions

  • This invention relates to a guidance seeker system effective to guide a projectile to a target. Moreover, it relates to a method to effect a course correction in a projectile. More particularly, the munition includes a plurality of photoconductive sensing elements that both enable calculation of a variance between the flight axis of the munition and an illuminated target and trigger at least one on-board diverter to reduce that variance.
  • Projected munitions frequently include a guidance seeker system that enables the projectile to calculate a variance from a target and to make one or more in-flight course corrections to increase the likelihood of the projectile disabling or destroying the target.
  • a guidance seeker system is disclosed in United States Patent No. 5,529,262 by Horwath that discloses a guidance seeker system actuated via a continuous beam of ultraviolet, visible or infrared light.
  • This seeker system includes a reticle with concentric; alternating, bands of light transmitting and light non-transmitting rings. The beam generates pulses as the target moves across the reticle field. The periodisity of these pulses is used to determine deviation of the target from a center line of the reticle. Circumferential thrusters on the projectile are then used to effect a necessary course change.
  • U.S.-A- 6,076,765 by Horwath utilizes a reticle having a pattern discontinuity effective to generate a singly periodic pulse once each projectile revolution.
  • the periodisity of pulses generated by the target sweeping across the reticle field enables the projectile to determine the line of flight variance between the projectile and the target.
  • the singly periodic pulse enables the projectile to determine its rotation position. Utilizing this information, an appropriate ring diverter is fired to reduce or eliminate the variance.
  • US-A-5,695,152 discloses a system and a method for correcting the course of a projectile, wherein the projectile spins during flight.
  • the projectile is launched by a launcher device.
  • sensors provided on the projectile sense light emitted from target markers associated with the launcher device.
  • a thruster provided on the projectile is activated if a largest permissible deviation angle of the projectile is detected.
  • Spinning reticle-based guidance seeker systems require a constant light source.
  • light is not limited to the visible spectrum, but includes infrared, ultra-violet as well as other portions of the spectrum.
  • an infrared source on the target is utilized, i.e. a "heat seeking" missile.
  • passive guidance systems Such systems where the seeker is drawn to a light source originating on the target are referred to as passive guidance systems.
  • a semi-active guidance system guides a projectile to a target that is externally illuminated.
  • external illumination is by a laser beam.
  • the laser generating this laser beam may be mounted on the projectile, or alternatively, located on a separate platform, such as a helicopter or spotter plane.
  • One semi-active guidance seeker system is disclosed in US-A-5,102,065 to Couderc et al. This patent discloses a homing system utilizing a laser that tracks both a target and a missile. The homing system determines the variance between the two and transmits course correction instructions to the missile that are then effected by small explosive charges or rudder adjustments.
  • US-A-5,835,204 to Urbach discloses pulsed laser systems utilized to determine the distance to a target.
  • the above mentioned guidance seeker systems require a steady state target signal or a steady state illumination signal from a target designator. They may also be amenable to pulsed signals having a repetition rate much faster than the highest frequency signal generated by the seekers.
  • the guidance seeker system of the invention is described with particular emphasis on projected munitions whereby the projectile includes an explosive charge that is intended to detonate either on contact with a target or proximate to the target thereby disabling or destroying that target, the guidance seeker system is equally applicable to nondestructive applications where it is desirable to direct a projectile to a desired target.
  • One method of identifying a target illuminates the target with an external light source. This is referred to as “designating” the target and the light source referred to as the "designator.”
  • a guidance seeker system on-board a projectile locates the illuminated target and directs the projectile to that target.
  • a highly focused coherent beam of light such as a beam generated by a laser, is particularly useful for target designation.
  • the laser it is preferable for the laser to generate short duration pulses at a relatively slow repetition rate.
  • an exemplary pulse duration 10 is between about 15 nanoseconds and 100 nanoseconds.
  • the pulse spacing 12 is from about 0.033 seconds to about 0.05 seconds, generating between about 20 and 30 pulses per second (i.e. a pulse frequency of between 20 Hertz and 30 Hertz).
  • Any laser capable of generating pulses meeting the above requirements may be utilized.
  • One preferred laser is a neodymium/YAG (yttrium, aluminum, garnet) laser.
  • the laser 14 is preferably mounted on a platform other than the projectile.
  • the laser 14 may be mounted on a helicopter or spotting aircraft.
  • the laser 14 generates a pulsed beam 16 that is reflected from a target 18.
  • a reflected pulse 20 is collected by lens 22 and transmitted onto at least one of a plurality of photoconductive sensing elements 24 contained within a photodetector 26.
  • the photoconductive sensing elements 24 are preferably symmetrically disposed about a central axis 28 of the photo detector 26.
  • the central axis 28 is aligned with the line of flight of the projectile, such that if the line of flight is aligned with the line of the reflected pulse, the reflected pulse strikes the central axis and does not strike any one of the photoconductive sensing elements thereby indicating that no course correction is required.
  • reflected pulse 20 strikes at least one photoconductive sensing element. Illumination of the photoconductive sensing element 24 generates an electric pulse that effects a projectile course correction.
  • the course correctors are a plurality of diverter elements 44 encircling the center of gravity of the projectile 32.
  • Each diverter is a small, on the order of one gram charge, explosive that when detonated creates an impulse that nudges the projectile to change the line of flight to one more likely to impact the target.
  • from detonation of one diverter until the projectile is ready for a second course correction is on the order of 0.100 seconds.
  • An exemplary number of diverters for a 69.85 mm (2.75 inch) rocket is from about 16 to 32.
  • diverters are a preferred course corrector for the projectiles
  • other course correctors such as small thrusters or rudders may also be employed with the invention.
  • the photodetector 26 is mounted rearward, relative to the forward end 36, of the lens 22 such that lens 22 is disposed between the target and the photo-detector 26.
  • a distance, D, between the lens 22 and photodetector 26 may be equal to the focal length of that lens, for a focused beam embodiment or may be a distance other than the focal length for a defocused beam.
  • Output signals from the photoconductive elements mounted on photodetector 26 are pre-amplified and conditioned by electronics package 46 and then applied to the appropriate filing circuit associated with a desired diverter 44. Wires 48 may be utilized to transmit the output signal to the appropriate firing circuit.
  • the projectile 32 may be either a spinning projectile or a non-spinning projectile. If a spinning projectile, the rate of spin is typically on the order of 1000 revolutions per second.
  • output signals 50 from the photoconductive sensing elements 24, are typically voltage pulses having a voltage on the order of millivolts.
  • the output signals 50 are passed through an amplifier 52 where the signal is pre-amplified and conditioned to 100 millivolts.
  • a recirculating shift register 54 is clocked to a frequency, f, that is a multiple of the spin frequency of the projectile.
  • a multiplication factor, n is equal to the number of photoconductive sensing elements in the ring.
  • Shift register 54 transmits the conditioned output signal 50 1 via an appropriate firing circuit to the diverter 44 aligned with an irradiated photoconductive sensing element 24. Generation of the firing pulse and activation of the diverter occurs almost instantaneously and is effective to nudge the projectile to a line of flight closer to the target. It is anticipated that the next laser impacting the photodetector will strike closer to central axis 28.
  • a focused designator beam applies a high intensity of light to a single photoconductive sensing element generating a high voltage pulse from that element.
  • D it is desirable that D not equal the focal length of lens 22.
  • photoconductive sensing elements 24 are irradiated with a defocused beam 56.
  • Defocused beam 56 is sufficiently large to irradiate a plurality of photoconductive sensing elements 24.

Claims (11)

  1. Zielsuchsystem zum Leiten eines Projektils (32) in ein Ziel (18), gekennzeichnet durch:
    eine Optikbaugruppe (40), die an einem vorderen Ende (36) des Projektils (32) angeordnet ist und eine Mehrzahl von fotoleitenden Sensorelementen (24) aufweist, welche symmetrisch in einer gemeinsamen Ebene um eine Achse (28) angeordnet sind, die mit einer Flugbahn (34) des Projektils (32) fluchtet, und eine Linse (22) aufweist, die zwischen dem Ziel (18) und den fotoleitenden Sensorelementen (24) mit einem Abstand (D) von den photoleitenden Sensorelementen (24) angeordnet ist;
    mehrere Kurskorrektoren (44), die an einer Außenfläche (38) des Projektils (32) angebracht sind, wobei die Beleuchtung von einem oder mehreren der fotoleitenden Sensorelemente (24) bewirkt, dass die mehreren Kurskorrektoren (44) eine Abweichung (30) zwischen der derzeitigen Flugbahn des Projektils (34) und dem Ziel (18) verringern, dadurch gekennzeichnet, dass
    ein Umlauf-Schieberegister (54) zwischen den fotoleitenden Sensorelementen (24) und den Kurskorrektoren (44) angeordnet ist, welches mit einer Frequenz (F x N) getaktet wird, wobei F ein Vielfaches der Drehfrequenz des Projektils (32) und N die Anzahl von fotoleitenden Sensorelementen (24) ist.
  2. System nach Anspruch 1, dadurch gekennzeichnet, dass
    die fotoleitenden Sensorelemente (24) in einem Fotodetektor (28) gehäust sind, der ein Metallgehäuse enthält, welches als gemeinsame Kathode fungiert.
  3. System nach Anspruch 1, mit vier bis zwanzig fotoleitenden Sensorelementen (24).
  4. System nach Anspruch 1, dadurch gekennzeichnet, dass D im wesentlichen der Brennweite der Linse (24) entspricht.
  5. System nach Anspruch 1, dadurch gekennzeichnet, dass D wesentlich verschieden ist von der Brennweite der Linse (26).
  6. System nach Anspruch 4 oder 5, dadurch gekennzeichnet, dass jedem fotoleitenden Sensorelement (24) ein lineares Array (58) aus mehreren Kurskorrektur-Ableitern (44) zugeordnet ist.
  7. System nach Anspruch 6, dadurch gekennzeichnet, dass mindestens einer der mehreren Kurskorrekturableitern (44''') in seinem Impulsvektor einen Versatz aufweist, der die Wirkung hat, einen Projektilspin (32) hervorzurufen.
  8. Verfahren zum Bewirken einer Kurskorrektur eines Projektils (32), gekennzeichnet durch folgende Schritte:
    Austatten des Projektils (32) mit einer Mehrzahl von fotoleitenden Sensorelementen (24), die symmetrisch in einer gemeinsamen Ebene um eine Achse (28) angeordnet sind, welche mit einer Flugbahn (34) des Projektils (32) fluchtet;
    Anstrahlen eines Ziels (18) mit einem von einem gepulsten Laser (14) erzeugten Bestimmungslicht (16), wobei die Laserpulsdauer (10) wesentlich kürzer ist als ein zwischen den Laserpulsen (12) liegendes Intervall;
    Empfangen von durch das Ziel (18) reflektiertem Bestimmungslicht auf einem oder mehreren der fotoieitenden Sensorelemente (24); und
    Übertragen eines Spannungsimpulses (50) von dem einen oder mehreren fotoleitenden Sensorelement (24), um mindestens einen der mehreren Kurskorrektoren (40) zu aktivieren, die sich an dem Projektil (32) befinden, um dadurch eine Kurskorrektur vorzunehmen, dadurch gekennzeichnet, dass
    zwischen den fotoleitenden Sensorelementen (24) und den mehreren Kurskorrektoren (44) ein Umlauf-Schieberegister (54) angeordnet ist, wodurch, wenn ein ausgewählter Kurskorrektor der mehreren Kurskorrektoren (44) inaktiv ist, die Aktivierung solange verzögert wird, bis ein anderer Kurskorrektor der mehreren Kurskorrektoren (44) zur Ausführung der Kurskorrektur wirksam ist, wobei das Schieberegister mit einer Frequenz (F x N) getaktet wird, wobei F ein Vielfaches der Drehfrequenz des Projektils (32) und N die Anzahl von fotoleitenden Sensorelemente (24) ist.
  9. Verfahren nach Anspruch 8, dadurch gekennzeichnet, dass das Intervall zwischen Pulsen (12) abhängig von einem voreingestellten Code variiert wird.
  10. Verfahren nach Anspruch 8, enthaltend den Schritt des Fokussierens der Laserpulse (20) derart, dass diese zu gegebener Zeit auf einzelnes fotoleitendes Sensorelement auftreffen.
  11. Verfahren nach Anspruch 8, enthaltend den Schritt des Defokussierens der Laserpulse (20) zum Treffen mehrerer einzelner fotoleitender Sensorelemente gleichzeitig.
EP00986176A 1999-07-21 2000-07-20 Geschosslenkung mittels einer ringanordnung und optisch ausgelösten ablenkvorrichtungen Expired - Lifetime EP1196733B1 (de)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US14491899P 1999-07-21 1999-07-21
US144918P 1999-07-21
PCT/US2000/019925 WO2001016547A2 (en) 1999-07-21 2000-07-20 Ring array projectile steering with optically-triggered diverter elements

Publications (3)

Publication Number Publication Date
EP1196733A2 EP1196733A2 (de) 2002-04-17
EP1196733A4 EP1196733A4 (de) 2003-07-02
EP1196733B1 true EP1196733B1 (de) 2005-10-05

Family

ID=22510742

Family Applications (1)

Application Number Title Priority Date Filing Date
EP00986176A Expired - Lifetime EP1196733B1 (de) 1999-07-21 2000-07-20 Geschosslenkung mittels einer ringanordnung und optisch ausgelösten ablenkvorrichtungen

Country Status (4)

Country Link
EP (1) EP1196733B1 (de)
AU (1) AU2245801A (de)
DE (1) DE60023007T2 (de)
WO (1) WO2001016547A2 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102007002336A1 (de) * 2007-01-16 2008-07-17 Lfk-Lenkflugkörpersysteme Gmbh Suchkopf für einen Lenkflugkörper zur Erfassung und Verfolgung eines Zieles und Verfahren zu dessen Anwendung
DE102009016147A1 (de) 2009-04-03 2010-10-07 Rheinmetall Soldier Electronics Gmbh Zerlegendes Geschoss

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10147837A1 (de) * 2001-09-27 2003-04-24 Rheinmetall Landsysteme Gmbh Wurfsystem für einen Gefechtskopf mit einer Richtvorrichtung zur Neutralisierung von Minen
DE102004029343B4 (de) * 2004-06-17 2009-04-30 Diehl Bgt Defence Gmbh & Co. Kg Zielführungsvorrichtung für ein Fluggerät
US8164037B2 (en) * 2009-09-26 2012-04-24 Raytheon Company Co-boresighted dual-mode SAL/IR seeker including a SAL spreader

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3000307A (en) * 1953-08-04 1961-09-19 Jr Herbert Trotter Device for correcting the course of a missile
US4006356A (en) * 1961-10-27 1977-02-01 Aeronutronic Ford Corporation Radiant energy tracking device
GB1605228A (en) * 1970-10-01 1985-03-20 British Aerospace Missiles
US4231533A (en) * 1975-07-09 1980-11-04 The United States Of America As Represented By The Secretary Of The Air Force Static self-contained laser seeker system for active missile guidance
US5102065A (en) 1988-02-17 1992-04-07 Thomson - Csf System to correct the trajectory of a projectile
US5127604A (en) * 1989-08-18 1992-07-07 Raytheon Company Optical system
DE4007712A1 (de) * 1990-03-10 1991-09-12 Tzn Forschung & Entwicklung Geschoss mit einem bugseitig angeordneten ir-suchsystem
US5529262A (en) 1993-06-23 1996-06-25 Horwath; Tibor G. Guidance seeker for small spinning projectiles
US5456429A (en) * 1993-08-02 1995-10-10 Loral Corp. Thrust maneuver system
DE4408085C2 (de) * 1994-03-10 1999-08-12 Rheinmetall W & M Gmbh Vorrichtung zur Lenkung eines nicht um seine Längsachse rotierenden Flugkörpers
DE4410326C2 (de) * 1994-03-25 1998-07-02 Rheinmetall Ind Ag Geschoß mit einer Vorrichtung zur Flugbahnkorrektur
DE4443134C2 (de) * 1994-12-03 2001-07-05 Diehl Stiftung & Co Sensoreinrichtung für einen Flugkörper
IL116438A (en) 1995-12-18 2000-01-31 Israel State Laser sensor
US5695152A (en) * 1996-09-18 1997-12-09 Israel Aircraft Industries Ltd. System for correcting flight trajectory of a projectile
EP0950165A4 (de) 1997-01-02 2000-03-22 Tibor G Horwath Zielfernrohr für ein drallprojektil

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102007002336A1 (de) * 2007-01-16 2008-07-17 Lfk-Lenkflugkörpersysteme Gmbh Suchkopf für einen Lenkflugkörper zur Erfassung und Verfolgung eines Zieles und Verfahren zu dessen Anwendung
DE102009016147A1 (de) 2009-04-03 2010-10-07 Rheinmetall Soldier Electronics Gmbh Zerlegendes Geschoss

Also Published As

Publication number Publication date
DE60023007T2 (de) 2006-07-13
WO2001016547A2 (en) 2001-03-08
EP1196733A2 (de) 2002-04-17
EP1196733A4 (de) 2003-07-02
WO2001016547A3 (en) 2001-06-21
DE60023007D1 (de) 2006-02-16
AU2245801A (en) 2001-03-26

Similar Documents

Publication Publication Date Title
US5669581A (en) Spin-stabilized guided projectile
US5662291A (en) Device for self-defense against missiles
US8371201B2 (en) Method and apparatus for efficiently targeting multiple re-entry vehicles with multiple kill vehicles
US6832740B1 (en) Missile system and method of missile guidance
US6817569B1 (en) Guidance seeker system with optically triggered diverter elements
US3028807A (en) Guidance system
US6565036B1 (en) Technique for improving accuracy of high speed projectiles
US5747720A (en) Tactical laser weapon system for handling munitions
JP3142881B2 (ja) 誘導発射体により使用されるインパルスレーダ誘導装置および方法
US3868883A (en) Guidance system
US6626396B2 (en) Method and system for active laser imagery guidance of intercepting missiles
US5695152A (en) System for correcting flight trajectory of a projectile
EP0899586A3 (de) Zielverfolgungslaseranweiser
CA1299016C (en) Spin-stabilized projectile with pulse receiver and method of use
US4951901A (en) Spin-stabilized projectile with pulse receiver and method of use
US4678142A (en) Precision guided antiaircraft munition
US3072055A (en) Gun launched, terminal guided projectile
US5831724A (en) Imaging lidar-based aim verification method and system
KR100301633B1 (ko) 화학 및 생물학 무기에 대항하는 단거리/중거리 레이저 방어 시스템
EP1196733B1 (de) Geschosslenkung mittels einer ringanordnung und optisch ausgelösten ablenkvorrichtungen
US3485461A (en) Firing control system for laser-guided projectiles
US4269121A (en) Semi-active optical fuzing
RU2722711C1 (ru) Способ наведения управляемого боеприпаса и устройство для его осуществления
RU2805094C1 (ru) Способ лазерной защиты воздушного судна
EP0371007A2 (de) Mit einem Empfänger versehenes Geschoss und sein Anwendungsverfahren

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: 20020115

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AT BE CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL

Kind code of ref document: A2

Designated state(s): AT BE CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE

AX Request for extension of the european patent

Free format text: AL;LT;LV;MK;RO;SI

RIC1 Information provided on ipc code assigned before grant

Free format text: 7F 41G 7/26 A, 7F 41G 7/22 B, 7F 42B 10/66 B, 7G 01S 3/784 B

A4 Supplementary search report drawn up and despatched

Effective date: 20030513

RBV Designated contracting states (corrected)

Designated state(s): DE FR GB

17Q First examination report despatched

Effective date: 20040701

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

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

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

REF Corresponds to:

Ref document number: 60023007

Country of ref document: DE

Date of ref document: 20060216

Kind code of ref document: P

ET Fr: translation filed
PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20060717

Year of fee payment: 7

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

Ref country code: GB

Payment date: 20060726

Year of fee payment: 7

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: 20060706

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

Ref country code: DE

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

Effective date: 20070201

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

Effective date: 20070720

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

Ref country code: GB

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

Effective date: 20070720

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20080331

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: 20070731