EP0151480A2 - Lasereinrichtung zur Lenkung eines Geschosses zu einem Ziel - Google Patents

Lasereinrichtung zur Lenkung eines Geschosses zu einem Ziel Download PDF

Info

Publication number
EP0151480A2
EP0151480A2 EP85101158A EP85101158A EP0151480A2 EP 0151480 A2 EP0151480 A2 EP 0151480A2 EP 85101158 A EP85101158 A EP 85101158A EP 85101158 A EP85101158 A EP 85101158A EP 0151480 A2 EP0151480 A2 EP 0151480A2
Authority
EP
European Patent Office
Prior art keywords
missile
circuit
laser
frequency
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.)
Granted
Application number
EP85101158A
Other languages
English (en)
French (fr)
Other versions
EP0151480B1 (de
EP0151480A3 (en
Inventor
Patrice Jano
Michèle Tron
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.)
Compagnie Industriel des Lasers CILAS SA
Original Assignee
Compagnie Industriel des Lasers CILAS SA
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 Compagnie Industriel des Lasers CILAS SA filed Critical Compagnie Industriel des Lasers CILAS SA
Publication of EP0151480A2 publication Critical patent/EP0151480A2/de
Publication of EP0151480A3 publication Critical patent/EP0151480A3/fr
Application granted granted Critical
Publication of EP0151480B1 publication Critical patent/EP0151480B1/de
Expired 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
    • F41G7/30—Command link guidance systems

Definitions

  • the present invention relates to a laser device for guiding a missile at a target.
  • the present invention aims to provide an improvement to the device described in document FR-A-2 525 339, to allow it to perform all the functions mentioned above using a single laser transmitter.
  • FIG. 1 shows a carbon dioxide laser emitter 1 emitting a continuous beam 2 of infrared radiation with a wavelength of 10.6 microns.
  • the beam 2 enters a modulator 30 connected to a control circuit 29.
  • Two beams 51 and 52 exit from the modulator 30.
  • the beam 51 is received on a mirror 3 mounted in rotation, in elevation and in bearing, around a ball joint 4 fixed on a support 23, the rotation of the mirror 3 being. driven by electric motors such as 5.
  • the mirror 3 reflects the beam 51 along a beam 6 illuminating a missile 7.
  • the latter preferably equipped at the rear with retroreflectors such as 8, returns in a reverse direction a beam 9 of laser radiation towards the mirror 3.
  • the beam 9 is reflected by the mirror 3 in a beam 10, itself reflected by a deflecting mirror 11 in a beam 12 towards a variometric reception system 13.
  • the system 13 comprises a lens 14 for concentrating the beam 12 on the sensitive surface d '' a four-quadrant photoelectric receiver 15.
  • the mirror 3 is an adaptive mirror, the reflecting surface 16 of which is deformable under the action of a plurality of piezoelectric transducers such as 17.
  • Each transducer 17 comprises two electrodes which are connected to an electrical bias circuit 18 by connections such as 19.
  • a control circuit 20 is connected to the motors 5.
  • a telemetry circuit 21 is connected to circuit 29 and to an electrical output 37 of the receiver 15.
  • An orientable telescopic sight 22 is mounted on a base 24 around a ball joint 25.
  • the beam 52 leaving the modulator 30 is returned along a beam 53, by a mirror 54 fixed on the telescope 22, to a target 55 such as a tank.
  • a telemetric reception system 56 fixed to the telescope 22 receives along a reception axis 57 part of the laser energy of the beam 53 returned by the target 55.
  • the reception axis 57 is parallel to the optical axis 34 of the bezel 22.
  • An angular measurement system 27 determines the orientation of the mirror 3 relative to that of the telescope 22.
  • a computer 28 has five inputs 39, 60, 38, 41, 40 respectively connected to circuit 21, to output 37 of the receiver - 15, to another output 36 of the receiver 15, to the system 27 and to the circuit 56.
  • the computer 28 has three outputs 61, 62 and 63 connected respectively to circuit 18, circuit 20 and circuit 29.
  • the missile 7 is equipped with a reception circuit comprising a photoelectric detector 31 disposed at the rear of the missile, the electrical output of the detector 31 being connected to the input of a processing 32.
  • the output of circuit 32 is connected to a control member 33 capable of causing a change in the direction of the missile.
  • the missile 7 further comprises an explosive charge 58 near which is disposed a system 59 capable of triggering the explosion of the charge 58 at the time of the impact of the missile on the target.
  • the elements referenced from 1 to 5, from 10 to 30 from 38 to 41, 56 and from 60 to 63 are gathered in a guide station 35 which can be located on the ground or on a military vehicle.
  • the missile 7 is launched towards a mobile target to be destroyed illustrated in FIG. 1 by the opposing tank 55.
  • the emission laser beam 6 is oriented towards the missile 7 using an acquisition device not shown.
  • the beam 9 returned by the retroreflectors 8 fixed on the missile is, after reflection on the movable mirror 3 and the fixed mirror 11, concentrated by the lens 14 on the receiver 15 with four quadrants.
  • On the electrical output 37 of the receiver 15 is delivered a signal representative of the intensity of the laser radiation returned by the missile.
  • a signal representative of the angular difference between the position of the missile and the axis of the laser beam is delivered to the eoartometric output 36 of the receiver 15.
  • the deviation signal is sent to the computer 28 which can thus calculate the direction of the missile taking into account the orientation of the mirror 3 and deliver the information corresponding to the circuit 20.
  • the electrical output 37 is connected to the input 60 of the computer 28 which develops orders for polarizing the electrodes of the transducers 17 of the adaptive mirror 3. This results in a deformation of the reflecting surface 16 of the mirror 3, this deformation tending increasing the concentration of the laser beam 6 on the missile 7. The amplitude of the electrical signal delivered on the output 37 of the receiver 15 is thus increased.
  • An embodiment 30A of the modulator 30 is shown in the FIG. 2. It comprises a crystal 64 with a BRAGG effect arranged on the path of the beam 2 emitted by the laser transmitter 1. Against the crystal 64 are applied the mechanical outputs of two piezoelectric electromechanical transducers 65 and 66. Two rocker circuits 67 and 68 are connected to the control circuit 29 of the modulator and respectively to the electrical inputs of the transducers 65 and 66. The rocker circuits 67 and 68 each have an input, and these inputs are connected to the output of a current generator 69 of frequency acoustic f 2 .
  • the modulator 30A shown in Figure 2 operates as follows.
  • Toggle circuits 67 and 68 identical to each other, each have two positions of stable equilibrium. In a first equilibrium position of the circuit 67 (or 68), the electrical input of the transducer 65 (or 66) is not connected to the output of the generator 69; in the second equilibrium position of the circuit 67 (or 68), the electrical input of the transducer 65 (or 66) is connected to the output of the generator 69.
  • the control circuit 29 of the modulator 30A makes it possible to switch the two rocker circuits sequentially to their equilibrium positions.
  • the transducers 65 and 66 are not supplied by the generator 69 and the laser beam 2 emitted by the emitter 1 is refracted normally in the crystal and leaves it -this according to the beam 51.
  • the beam 51 leaves parallel to the beam 2.
  • the frequency of the radiation of the beam 51 is equal to the frequency F of the beam 2 radiation.
  • the transducers 65 and 66 are both supplied by the generator 69. These transducers are arranged on the surface of the crystal so that the acoustic waves which they emit in the crystal cause the formation of an output beam 52 parallel to the beam 51 but different from the latter.
  • the frequency F 2 of the radiation of the beam 52 is offset with respect to the frequency F 1 of the beam 51 by the value f 2 of the acoustic frequency emitted by the generator 69.
  • the modulation of the continuous beam 2 emitted by the laser transmitter 1 is effected by causing, by the control circuit 29, a sequential switching of the two flip-flop circuits 67 and 68 to their positions of stable equilibrium.
  • the control circuit 29 causes alternating switching of the circuit 68 to its first and second equilibrium positions, at a rate which makes it possible to cutting short pulses from the continuous laser beam, so that the beam 51 is formed of a sequence of pulses.
  • these pulses are sent to the missile 7, after reflection on the mirror 3 along the beam 6.
  • the pulses are returned by the missile and received by the receiver 15 which delivers a return signal on its output 37 connected to circuit 21.
  • the latter has a clock for measuring the time interval which elapses between the emission of a laser pulse towards the missile and its reception on the receiver 15.
  • the telemetry circuit 21 delivers therefore when it leaves the missile distance information.
  • Sequential switching of flip-flop circuits 67 and 68 can also include, circuit 68 for example remaining on its second equilibrium position, alternating switching of circuit 67 to its first and second equilibrium positions. This. alternating switching makes it possible to cut short-duration pulses from the continuous laser beam, so that the beam 52 is also formed of a series of pulses (see FIG. 2).
  • the beam 52 is reflected by the mirror 54 in a beam 53.
  • the operator directs the telescopic sight 22 towards the target and, at the same time, directs the beam 53, parallel to the axis 34 of the telescopic sight, also towards the target.
  • the target 55 sends back to the reception circuit 56, similar to the circuit 21, part of the energy of the pulses of the beam 53 and the circuit 56 delivers, at the desired times and at regular time intervals, the information of the distance from target.
  • the measurement system 27 delivers at its output two pieces of information defining the angular position of the missile relative to a reference trihedron linked to the orientable telescope 22.
  • the computer 28 receives on its inputs 39 and 40 the information of the respective distances from the station 35 to the missile and to the target, and on its input 41, the two information defining the angular position of the missile.
  • the computer 28 is capable of determining from these two pieces of information the angle which the direction of the missile makes with that of the target.
  • the computer 28 therefore has all the elements for solving the triangle formed by the points which correspond respectively to station 35, missile 7 and the target.
  • This computer is capable of determining a trajectory of the missile, starting from its current position and ending at the target. Preferably, this trajectory is determined so that the laser beam remains above the target, then returns to it only at the end of the journey. In this way, the guidance station is difficult to detect by the opponent.
  • the computer 28 is also capable of developing piloting signals capable of controlling the adjustment of the members 33 of the missile 7, so as to guide the missile on the determined trajectory.
  • control signals are transmitted to the control circuit 29 of the modulator 30A in order to cause a modulation, according to these signals of piloting of the laser pulse sequence of the beam 51.
  • This pulse sequence is modulated in position, the modulation consisting in shifting the instant of emission of the successive pulses.
  • FIGS. 3A, 3B, 3C and 3D are diagrams established for a given sequential switching of the flip-flop circuits 67 and 68.
  • FIG. 3A shows, as a function of time, the amplitude A 51 of the energy of the beam 51, when, the circuit 67 remaining in its first equilibrium position, an alternating switching of the circuit 68 is caused to its two positions. This switching is carried out so as to obtain a series of short duration pulses, these pulses being modulated in position, that is to say shifted in time according to the control signals produced by the computer.
  • FIG. 3B shows as a function of time the amplitude A 52 of the energy of the beam 52 when, the circuit 68 remaining in its second equilibrium position, the circuit 67 is switched alternately to its two positions. This switching is carried out so as to obtain a series of short duration pulses arranged between the successive pulses of the beam 51.
  • FIGS. 3C and 3D show as a function of time the acoustic frequency of the supply current of the transducers 66 and 65. It can be seen in these last two diagrams that the frequency f 2 of the current delivered by the generator 69 varies as a function of time, when this current is applied to the input of the transducer 65. This variation takes place along an upward ramp followed by a downward ramp; these ramps are linear and of the same duration, and their slopes are equal and of opposite sign.
  • the variation of the frequency f 2 makes it possible to incorporate in the reception circuit 56 means for measuring the speed of the target by Doppler effect. Thanks to the symmetrical ramp shape of this frequency variation, it is possible to compress the duration of the pulses at reception using a known technique, which improves the performance of telemetry and speed measurement of the target.
  • the beam 51 is sent to the missile by reflection on the mirror 3, along the beam 6.
  • the receiver 31 of the missile picks up the series of pulses modulated in position carried by the beam 6, and the processing circuit 32 delivers at its output the steering signals which are transmitted to the piloting member 33, so as to progressively guide the missile towards the target.
  • the device described above with reference to Figures 1 and 2 is therefore capable of guiding a missile at a target.
  • This device uses a single laser 1 from which, thanks to a modulator 30, two separate beams (51 and 52) are formed.
  • the beam 51 makes it possible to perform the functions of deviation measurement, telemetry and transmission of orders to the missile.
  • the beam 52 makes it possible to measure the distance from the target and possibly its speed.
  • the type 30A of modulator represented in FIG. 2, which comprises two transducers, has the advantage of forming two beams (51 and 52) parallel to each other and of direction independent of the frequency of the generator, which facilitates the optical exploitation of the beams from the modulator.
  • FIG. 4 Another embodiment 30B of the modulator 30 is shown in FIG. 4. It comprises a Bragg crystal 73 arranged on the path of the beam 2 emitted by the laser emitter 1. Against this crystal, the mechanical output of a single piezoelectric electromechanical transducer 74. A rocker circuit 75 is connected to the electrical input of the transducer 74 and to the control circuit 29 of the modulator. The flip-flop circuit 75 has two inputs connected respectively to two current generators 76 and 77 of acoustic frequency f1 and f 2 .
  • the rocker circuit 75 comprises three positions of stable equilibrium, a first position in which the electrical input of the transducer 74 is not connected to any of the current generators, a second position in which the electrical input of the transducer 74 does not is connected only to the generator 76 of frequency f i , and a third position in which the electrical input of the transducer 74 is only connected to the generator 77 of frequency f 2 .
  • the control circuit 29 of the modulator 30B sequentially switches the flip-flop circuit 75 to its three equilibrium positions.
  • the laser radiation 2 leaves the crystal in a beam 51 of frequency F1 equal to the frequency of the radiation emitted by the laser transmitter 1.
  • the laser beam 78 which leaves the crystal is deflected angularly relative to the beam 51.
  • This beam 78 is not used in the operation of the device; it is closed by an absorbent material 79.
  • the deflection angle depends on the frequency of the transducer supply current and as f is different from f 2 , the three beams 51, 78 and 52 are distinct from each other.
  • pulses are formed in the beam 51.
  • the successive pulses thus formed are shifted in time so as to effect modulation in the following position the control signals produced by the computer.
  • FIG. 5A represents the variations as a function of time of the amplitude A S1 of the radiation of the beam 51.
  • pulses are formed in beam 52. These pulses are illustrated by FIG. 5B which represents the variations as a function of time of the amplitude A 52 of the beam radiation 52.
  • FIGS. 5A, 5B and 5C relate to an example of sequential switching of the rocker circuit
  • FIG. 5C shows the variations as a function of time of the frequency f of the supply current of the transducer 74.
  • This frequency oscillates between the frequency f 1 and the frequency f 2 .
  • the frequency f 2 varies in time along a linear ramp of ascent followed by a linear ramp of descent of the same duration, in order to allow the measurement of the speed of the target and to use a reception circuit 56 capable of performing compression of the duration of the pulses.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Optical Radar Systems And Details Thereof (AREA)
EP85101158A 1984-02-07 1985-02-05 Lasereinrichtung zur Lenkung eines Geschosses zu einem Ziel Expired EP0151480B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8401842A FR2559252B2 (fr) 1984-02-07 1984-02-07 Dispositif laser pour guider un missile sur une cible
FR8401842 1984-02-07

Publications (3)

Publication Number Publication Date
EP0151480A2 true EP0151480A2 (de) 1985-08-14
EP0151480A3 EP0151480A3 (en) 1985-09-11
EP0151480B1 EP0151480B1 (de) 1988-09-21

Family

ID=9300819

Family Applications (1)

Application Number Title Priority Date Filing Date
EP85101158A Expired EP0151480B1 (de) 1984-02-07 1985-02-05 Lasereinrichtung zur Lenkung eines Geschosses zu einem Ziel

Country Status (4)

Country Link
US (1) US4634271A (de)
EP (1) EP0151480B1 (de)
DE (1) DE3565177D1 (de)
FR (1) FR2559252B2 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2627269A1 (fr) * 1988-02-17 1989-08-18 Thomson Csf Systeme de correction de la trajectoire d'un projectile
US20160195365A1 (en) * 2015-01-06 2016-07-07 Teledyne Scientific & Imaging, Llc Moving object command link system and method

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2567275B1 (fr) * 1984-07-09 1986-07-25 Giravions Dorand Procede et dispositif de reperage spatial d'un objet et application en simulation de tir
FR2603695B1 (fr) * 1986-09-09 1990-10-19 Thomson Csf Procede et dispositif de visualisation des cibles et/ou des positions des cibles utilisant des moyens d'acquisition des donnees d'un systeme d'armes
US5008836A (en) * 1989-07-20 1991-04-16 Motorola, Inc. Method of recognizing selected objects
GB2393056B (en) * 1992-10-24 2004-09-01 British Aerospace Tracking systems
US5348249A (en) * 1993-01-11 1994-09-20 Hughes Missile Systems Company Retro reflection guidance and control apparatus and method
DE4425285C2 (de) * 1994-07-16 1997-04-17 Rheinmetall Ind Ag Vorrichtung zur Flugbahnkorrektur von drallstabilisierten Geschossen
CA2161045A1 (en) * 1994-11-15 1996-05-16 Michael L. Wells Error detector apparatus with digital coordinate transformation
US5651512A (en) * 1995-09-28 1997-07-29 Hughes Electronics Missile tracking system with a thermal track link
US7175130B2 (en) * 2004-09-03 2007-02-13 Her Majesty The Queen In Right Of Canada, As Represented By The Minister Of National Defence Of Her Majesty's Canadian Government Missile steering using laser scattering by atmosphere
CN101815922B (zh) * 2007-09-21 2012-09-26 莱茵金属武器弹药有限公司 用于光学地控制射弹的方法和装置
US8829401B1 (en) * 2011-06-16 2014-09-09 The Boeing Company Projectile and associated method for seeking a target identified by laser designation
DE102012009512A1 (de) * 2012-05-14 2013-11-14 Mbda Deutschland Gmbh Positionsbestimmung und Datenübertragung mittels Laser
IL236338B (en) * 2014-12-18 2018-12-31 Israel Aerospace Ind Ltd Guidance system and method

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4234141A (en) * 1970-03-10 1980-11-18 The United States Of America As Represented By The Secretary Of The Army Range gated retroreflective missile guidance system
FR2109488A5 (de) * 1970-10-22 1972-05-26 Telecommunications Sa
DE2533697A1 (de) * 1975-07-28 1977-02-03 Precitronic Einrichtung zur signaluebertragung zwischen einer abschussbasis und einem flugkoerper mittels einer lichtuebertragungsstrecke
DE2853695C2 (de) * 1978-12-13 1985-05-02 Diehl GmbH & Co, 8500 Nürnberg Vorrichtung zum selbsttätigen Nachführen eines Laserstrahls
US4516853A (en) * 1982-03-31 1985-05-14 United Technologies Corporation Laser radar adaptive tracking system
FR2525339B1 (fr) * 1982-04-20 1986-10-10 Cilas Alcatel Dispositif laser pour guider un missile sur une cible

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2627269A1 (fr) * 1988-02-17 1989-08-18 Thomson Csf Systeme de correction de la trajectoire d'un projectile
WO1989007744A1 (fr) * 1988-02-17 1989-08-24 Thomson-Csf Systeme de correction de la trajectoire d'un projectile
US5102065A (en) * 1988-02-17 1992-04-07 Thomson - Csf System to correct the trajectory of a projectile
US20160195365A1 (en) * 2015-01-06 2016-07-07 Teledyne Scientific & Imaging, Llc Moving object command link system and method
US9739571B2 (en) * 2015-01-06 2017-08-22 Teledyne Scientific & Imaging, Llc Moving object command link system and method

Also Published As

Publication number Publication date
FR2559252B2 (fr) 1986-12-05
FR2559252A2 (fr) 1985-08-09
EP0151480B1 (de) 1988-09-21
EP0151480A3 (en) 1985-09-11
US4634271A (en) 1987-01-06
DE3565177D1 (en) 1988-10-27

Similar Documents

Publication Publication Date Title
EP0151480B1 (de) Lasereinrichtung zur Lenkung eines Geschosses zu einem Ziel
EP0033679B1 (de) System zur Andeutung eines Objektes mittels eines Lasers
FR2472167A1 (fr) Dispositif de guidage optique a distance d'un projectile
FR2677834A1 (fr) Systeme d'imagerie laser a barrette detectrice.
FR2594959A1 (fr) Procede et dispositif de mesure optique de la distance et de la vitesse d'une cible
FR2696838A1 (fr) Dispositif de pointage d'une cible mobile.
EP0485292B1 (de) Optische Vorrichtung zum Messen des Rollwinkels eines Projektils
FR2505505A1 (fr) Dispositif laser pour detecter et neutraliser l'optique d'un appareil de reperage adverse
FR2495797A1 (fr) Systeme de pilotage automatique d'un vehicule terrestre autonome
FR2686312A1 (fr) Vehicule spatial d'observation laser, notamment pour vitesse de vents, et instrument d'observation adapte a en faire partie.
FR2483067A1 (fr) Procede et dispositif destines a eviter des coups defectueux d'appareils de tir automatiques
EP0127870B1 (de) Vorrichtung zum Entdecken einer feindlichen Infrarotkamera
EP0702246B1 (de) Tragbares Gerät zum Messen der Rückstreuung von Licht
CA2300577C (fr) Dispositif d'emission d'images video numeriques
FR2729748A2 (fr) Dispositif laser pour guider un missile sur une cible
EP0033279A1 (de) Leitsystem für Raketen mittels eines optischen Strahles
FR2525339A1 (fr) Dispositif laser pour guider un missile sur une cible
FR2548796A1 (fr) Dispositif optique pour determiner la position et la forme de la surface d'un objet
FR2681143A1 (fr) Procede d'identification iff protege contre les intrusions et systeme de mise en óoeuvre.
FR2655140A1 (fr) Systeme a fusee declenchee a distance.
FR2547405A2 (fr) Dispositif laser pour guider un missile sur une cible
FR2503857A1 (fr) Dispositif pour guider un engin mobile
FR2458823A1 (fr) Detecteur de proximite
WO2025061494A1 (fr) Drone autoguide par dispositif optronique d'ecartometrie a double usage
FR2618893A1 (fr) Perfectionnements apportes aux appareils de reconnaissance de forme et/ou de detection de position d'un objet dans l'espace

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

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Designated state(s): DE FR GB IT SE

AK Designated contracting states

Designated state(s): DE FR GB IT SE

17P Request for examination filed

Effective date: 19860306

17Q First examination report despatched

Effective date: 19871103

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 IT SE

REF Corresponds to:

Ref document number: 3565177

Country of ref document: DE

Date of ref document: 19881027

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)
ITF It: translation for a ep patent filed
PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 19881223

Year of fee payment: 5

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

Ref country code: GB

Payment date: 19890131

Year of fee payment: 5

ITTA It: last paid annual fee
PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: SE

Payment date: 19890228

Year of fee payment: 5

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

Ref country code: GB

Effective date: 19900205

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

Ref country code: SE

Effective date: 19900206

GBPC Gb: european patent ceased through non-payment of renewal fee
PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Effective date: 19901101

EUG Se: european patent has lapsed

Ref document number: 85101158.5

Effective date: 19901107

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

Ref country code: FR

Payment date: 20040223

Year of fee payment: 20