EP0025739A1 - Primär- und Sekundär-Radarantenne - Google Patents

Primär- und Sekundär-Radarantenne Download PDF

Info

Publication number
EP0025739A1
EP0025739A1 EP80401242A EP80401242A EP0025739A1 EP 0025739 A1 EP0025739 A1 EP 0025739A1 EP 80401242 A EP80401242 A EP 80401242A EP 80401242 A EP80401242 A EP 80401242A EP 0025739 A1 EP0025739 A1 EP 0025739A1
Authority
EP
European Patent Office
Prior art keywords
primary
radar
channel
interrogation
monopulse
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
EP80401242A
Other languages
English (en)
French (fr)
Other versions
EP0025739B1 (de
Inventor
Georges Cohen
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.)
Thales SA
Original Assignee
Thomson CSF 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 Thomson CSF SA filed Critical Thomson CSF SA
Priority to AT80401242T priority Critical patent/ATE5836T1/de
Publication of EP0025739A1 publication Critical patent/EP0025739A1/de
Application granted granted Critical
Publication of EP0025739B1 publication Critical patent/EP0025739B1/de
Expired legal-status Critical Current

Links

Images

Classifications

    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q21/00—Antenna arrays or systems
    • H01Q21/28—Combinations of substantially independent non-interacting antenna units or systems
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q25/00—Antennas or antenna systems providing at least two radiating patterns
    • H01Q25/02—Antennas or antenna systems providing at least two radiating patterns providing sum and difference patterns
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q5/00—Arrangements for simultaneous operation of antennas on two or more different wavebands, e.g. dual-band or multi-band arrangements
    • H01Q5/40—Imbricated or interleaved structures; Combined or electromagnetically coupled arrangements, e.g. comprising two or more non-connected fed radiating elements
    • H01Q5/45—Imbricated or interleaved structures; Combined or electromagnetically coupled arrangements, e.g. comprising two or more non-connected fed radiating elements using two or more feeds in association with a common reflecting, diffracting or refracting device

Definitions

  • the present invention relates to an aerial for primary radar and for secondary radar. It also covers radar equipment using such aerial, equipment used in air traffic monitoring stations.
  • the primary radar aims to detect the presence in the sky of an object and to give information concerning it such as its distance, its azimuth, and / or its site and possibly its speed depending on the type of antenna used.
  • the secondary radar associated in the station with the primary radar makes it possible to obtain for this object identification information and a possible knowledge of its altitude when the latter is equipped with an answering machine designed for this purpose.
  • the aerial of such a radar station comprises an antenna for the primary radar and one or two antennas for the secondary radar. Indeed the current secondary radars must be able to transmit and receive two different signals.
  • the first is called interrogation signal, it is transmitted and received by a first antenna, the second is called control signal, its purpose is to inhibit all interrogations made in directions other than that of the main lobe of the diagram of radiation from the interrogation antenna.
  • an antenna for transmitting and receiving interrogation signals has a radiation diagram having a main lobe and secondary lobes.
  • the control signals are transmitted and received either by another antenna or by the same antenna as the interrogation antenna.
  • the radiation pattern of the control channel may be, in the reservoir plan, of the omnidirectional or difference type; in all cases the control diagram covers the interrogation diagram except in a small zone centered on the main lobe of the interrogation and called the interrogation arc.
  • An air traffic monitoring station comprising a secondary radar whose aerial conforms to what has been described above above, that is to say radiating a diagram of the difference in azimuth type works in a manner deemed satisfactory.
  • the azimuth resolution of such a radar that is to say its ability to distinguish two objects relatively close to each other, is not very fine; this may cause discomfort to the station's radar operators in the identification of the objects or targets questioned, mainly in the nearby area.
  • This lack of resolution is mainly due to the width of the interrogation arc, width which is imposed and on which it is difficult to act.
  • An object of the invention is to remedy this drawback and to define means allowing the level of the secondary radar to have an azimuth resolution higher than that given by the control channel.
  • the antenna of the secondary radar comprising interrogation means and control means, further comprises means cooperating with the preceding means to define a monopulse channel in bearing, allowing the separation in bearing of the close targets questioned. .
  • the improvement in the azimuth resolution of a secondary radar is obtained by the creation, at the level of the secondary radar, of a monopulse channel making it possible to make the variometry on the targets questioned which are not separable by the operator on the indicator associated with the control channel and therefore are not identifiable, although questioned.
  • FIG. 1 represents an exemplary embodiment of a secondary radar antenna comprising the deviation measurement channel according to the invention.
  • This antenna is a so-called integrated antenna in the primary radar, solution which seems to prevail at present.
  • this antenna comprises a certain number of elements, the combination of which falls under the known art, but which will be recalled below.
  • the focusing element that is to say the reflector which is common to the four operating modes of the antenna, primary radar, interrogation and control, monopulse, does not appear in the drawing, which represents in these conditions the primary source of the primary radar, which is modified so as to also transmit the signals relating to the secondary radar function.
  • This primary source successively comprises a rectangular guide section connected to the transceiver 2 of the primary radar, a transition guide 4, a circular guide section 5 and a horn 6.
  • the connection between the primary source and the transmitter- receiver 2 is indicated by two arrows 3.
  • Radar waves the polarization vector of which is represented by arrow 7 on transmission, pass through the source of the rectan guide gular 1 towards the horn 6 from which they are radiated towards the reflector. Upon reception, the waves propagate in the opposite direction.
  • the antenna comprises means making it possible to perform the function of secondary radar.
  • the circuit 13 is connected to the transceiver 15 by a coaxial line 14 and the probes 8 and 9 are connected to the circuit 13 by the coaxial lines 12 and 11 respectively.
  • the purpose of the filter of the hybrid circuit 13 is to transmit only the interrogation signals and to inhibit the signals at the frequency of the primary radar. Indeed, the horn 6 and the circular guide 5 being common to the waves of the primary and secondary radars, a fraction of the energy of the signals of the primary radar can be transmitted to the transceiver of the secondary radar by the probes. These signals are eliminated in circuit 13.
  • the dimensions of the guide 5 are determined for correct operation of the source at the frequency of the primary radar.
  • the operating frequency of the secondary radar being generally lower than that of the primary radar, the guide 5 is cut off for the waves of the secondary radar.
  • a dielectric strip 22 is then placed inside this guide.
  • the shapes of this blade were determined so as not to modify the performance of the primary source at the frequency of the primary radar.
  • the large faces of this plate are perpendicular to the polarization vector of the radar waves so that the thickness they pass through is minimum.
  • the thickness of the blade for the interrogation signals is maximum.
  • the cut of the blade is elliptical and on the side of the guide 4, it is beveled.
  • the blade is made of polypropylene, a material with a low loss tangent.
  • the signals from the primary radar and the interrogation signals are thus radiated by the same horn 6 which illuminates the reflector not shown in the figure, but which is of the double curvature type for example. It presents a great directivity in deposit, and a diagram in neighboring site of a square cosecant.
  • the interrogation mode of operation therefore benefits from the good characteristics of gain and directivity of the common reflector, which makes it possible to use, at performances equal to that of known systems, a less efficient transceiver.
  • the control signals are transmitted and received by two auxiliary sources 16 and 17 placed on either side of the horn 6. These sources are connected to the transceiver of the secondary radar 15 by means of a divider circuit of power 20 and coaxial connecting lines 18 and 19 between the sources and the divider on the one hand, and 21 between the divider and the transceiver 15 on the other hand.
  • the sources 16 and 17 are supplied in phase opposition.
  • the axes of these two sources are included in the same horizontal plane.
  • the same radar antenna reflector is still lit by the control sources.
  • the control radiation diagram is therefore of the difference in deposit type and of the square cosecant type in elevation thanks to the properties of the reflector.
  • Each source 16 or 17 consists for example of a group of dipoles arranged in a sealed housing.
  • the metal bottom of the housing acts as a reflective plane.
  • the cover of the housing, permeable to waves, is made of glass-polyester for example.
  • the power divider consists of one or more hybrid rings for example.
  • the radiation pattern of the control channel which is of the difference in deposit type and which has a too wide interrogation arc to allow always possible discrimination of the targets, mainly in the approach area is reinforced by another radiation pattern in bearing of the difference type also which allows a separation of the targets in the approach area , in other words whose azimuth resolution is finer.
  • the antenna of the secondary radar which already has an interrogation channel and a control channel is reinforced by a monopule channel, that is to say that in addition to the radiation patterns which have already been described, it has a new difference diagram. More precisely, at the level of the monopulse function, a sum channel and a difference channel are formed at the response frequency of the transponders, which in the example considered is 1090 MHz. The sum signal is obtained at the output of the hybrid circuit 13 where it has been separated from the signal from the primary radar. This signal is none other than the response signal of the transponders.
  • a new auxiliary source being in the form of two dipoles 23, 24 located on either side of the radiating opening of the primary source. 6 of the radar and in the same plane as the sources 16 and 17 used to form the control channel of the secondary radar associated with the primary radar.
  • the sum and difference signals obtained in this new monopulse channel are processed in a difference meter receiver 27.
  • These sources 23 and 24 are connected for the transmission of difference signals to the difference meter receiver by cables 25 and 30 to a divider circuit. of power 26, itself connected by the link 28 to the receiver 27.
  • This receiver is connected by the cable 29 to the transceiver 15 of the already existing secondary radar, which transmits the sum signal of the new pathway created according to the invention, as has already been said.
  • the sources 23, 24 contributing to the formation of the new difference path are placed closer to the radiating aperture of the primary source 6 than sources 16 and 17 of the secondary radar control channel.
  • This arrangement is dictated by the need to have a high deviation slope which is a function of the distance existing between the sources on either side of the focal axis of the aerial.
  • FIG. 2 represents a variant of the aerial primary radar-secondary radar according to the invention in the case where the primary source operates in circular polarization.
  • the primary source proper comprises a rectangular guide 3, a transition guide 4, a circular guide 5 and the horn, containing a polarizing element 60.
  • the probes 8 and 9 have their axes inclined by 45 ° relative to a vertical axis. These probes which make it possible to recover the waves reflected on the front face of the horn in emission, and which are then dissipated in absorbent charges which are connected to them are necessary for a good functioning in this mode of polarization.
  • the probes 8 and 9 are used as in the case of FIG. 1.
  • a diplexer circuit 130 comprising filters and a power divider are arranged between the transceiver 15 and the probes .
  • Coaxial lines 110, 120 and 140 provide the microwave link between the probes and the diplexer on the one hand and between the diplexer and the transceiver 15 on the other hand.
  • the diplexer separates the signals from the primary radar and the interrogation.
  • the primary radar signals are dissipated in resistive loads 131 and 132.
  • a dielectric strip 16 is also placed in the circular guide 5. Its median plane contains the axis of the probes. The plane of polarization of the primary radar wave is perpendicular to the dielectric plate.
  • the circular guide 5 is symmetrically excited by the recovery probes 8 and 9. After passing through the polarizer 60 and the horn 6, the interrogation signals are radiated with an elliptical polarization.
  • the transponders installed on board aircraft are designed to transmit and receive waves in vertical linear polarization.
  • the fact that the polarization of the wave radiated by the secondary radar is elliptical does not present any drawback. In range calculations, everything happens as if you had an antenna whose gain is about 3 dB lower than its nominal gain. Given the additional gain brought by the use of the reflector of the primary radar antenna, this loss is immaterial.
  • Control operation is obtained, as in FIG. 1, by two sources 16 and 17 connected to the transceiver 15 by the connection lines 18 and 19, the power divider 20 and the connection line 21.
  • Each of the auxiliary sources comprises, as in the case of FIG. 1, a group of dipoles arranged on a metallic background serving as a reflector.
  • the dipoles are of the half-wave type.
  • the different parameters of the dipoles are determined to obtain a good adaptation and a correct radiation diagram.
  • the monopulse channel added to the interrogation and control channels of the secondary radar is made up of probes on the one hand which provide the sum signal and two auxiliary sources, dipoles 23 and 24 arranged on the one hand and on the other side of the primary source 6.
  • a so-called deviation meter receiver 27 is connected on the one hand to the transceiver 15 of the secondary radar and to the power divider 26 itself connected by the cables 25 and 30 to the dipoles 23 and 24.
  • Figure 3 is a diagram of a diplexer used in the device according to the invention. It makes it possible to connect the recovery probes 8 and 9 on the one hand to suitable loads 131 and 132 for the signals from the primary radar and on the other hand to the transmitter- receiver 15 for interrogation signals.
  • the outputs of the filters 133 and 134 are connected to the adapted loads 131 and 132 which dissipate the energy reflected on the opening of the horn.
  • the outputs of the other filters 135 and 136 are connected to two terminals of a power divider 137, the third terminal of which is connected to the transceiver 15 via the connection line 140.
  • the arrangement of the diametrically opposed probes in the circular guide 5 results in the need to have a phase shift of 180 ° between the two paths which supply them. This phase shift is obtained by the divider itself.
  • the divider is a classic hybrid ring.
  • the entire hybrid circuit 130 can be produced in a photoengraved three-ply circuit then coated by molding to ensure its sealing.
  • FIG. 4 shows for the aerial object of the present invention, the radiation patterns in bearing of the interrogation channel, the control channel and the monopulse channel added to the previous ones.
  • solid line designated by A
  • the difference diagram of the control channel has been represented.
  • B the sum diagram of the interrogation channel is designated, which will also be that of the added monopulse channel.
  • the intersection of diagrams A and B makes it possible to define the interrogation arc on CD.
  • E is designated, in line, the difference diagram of the monopulse channel associated with the secondary radar, whose cross-checking with the sum diagram B, makes it possible to define the arc of deviation GH.
  • a combined aerial for primary and secondary radar has thus been described, allowing in particular a substantial improvement in the secondary radar function.

Landscapes

  • Physics & Mathematics (AREA)
  • Electromagnetism (AREA)
  • Radar Systems Or Details Thereof (AREA)
  • Traffic Control Systems (AREA)
  • Variable-Direction Aerials And Aerial Arrays (AREA)
  • Burglar Alarm Systems (AREA)
  • Waveguide Aerials (AREA)
EP80401242A 1979-09-07 1980-08-29 Primär- und Sekundär-Radarantenne Expired EP0025739B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AT80401242T ATE5836T1 (de) 1979-09-07 1980-08-29 Primaer- und sekundaer-radarantenne.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR7922450 1979-09-07
FR7922450A FR2465328A1 (fr) 1979-09-07 1979-09-07 Aerien pour radar primaire et radar secondaire

Publications (2)

Publication Number Publication Date
EP0025739A1 true EP0025739A1 (de) 1981-03-25
EP0025739B1 EP0025739B1 (de) 1984-01-11

Family

ID=9229468

Family Applications (1)

Application Number Title Priority Date Filing Date
EP80401242A Expired EP0025739B1 (de) 1979-09-07 1980-08-29 Primär- und Sekundär-Radarantenne

Country Status (7)

Country Link
US (1) US4376937A (de)
EP (1) EP0025739B1 (de)
JP (1) JPS5689076A (de)
AT (1) ATE5836T1 (de)
DE (1) DE3066094D1 (de)
FR (1) FR2465328A1 (de)
NO (1) NO152189C (de)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0057538A2 (de) * 1981-01-29 1982-08-11 Kabushiki Kaisha Toshiba Antennenanordnung
FR2638531A1 (fr) * 1988-10-28 1990-05-04 Thomson Csf Systeme d'integration des voies somme et difference i.f.f. dans une antenne de surveillance radar
US5483663A (en) * 1994-04-05 1996-01-09 Diversified Communication Engineering, Inc. System for providing local originating signals with direct broadcast satellite television signals
US5761605A (en) * 1996-10-11 1998-06-02 Northpoint Technology, Ltd. Apparatus and method for reusing satellite broadcast spectrum for terrestrially broadcast signals
FR2773271A1 (fr) * 1997-12-31 1999-07-02 Thomson Multimedia Sa Emetteur/recepteur d'ondes electromagnetiques
US6730310B2 (en) 1998-10-30 2004-05-04 Colgate-Palmolive Company Wash-off vitamin E compositions
WO2018060070A1 (en) 2016-09-29 2018-04-05 Bayer Cropscience Aktiengesellschaft Novel triazole derivatives

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5940707A (ja) * 1982-08-31 1984-03-06 Nec Corp レ−ダ空中線
US4870426A (en) * 1988-08-22 1989-09-26 The Boeing Company Dual band antenna element
FR2965063B1 (fr) * 2010-09-21 2012-10-12 Thales Sa Procede pour allonger le temps d'eclairement de cibles par un radar secondaire
US20170323239A1 (en) 2016-05-06 2017-11-09 General Electric Company Constrained time computing control system to simulate and optimize aircraft operations with dynamic thermodynamic state and asset utilization attainment
DE102018100845A1 (de) * 2018-01-16 2019-07-18 Krohne Messtechnik Gmbh Füllstandmessgerät
FR3081230B1 (fr) * 2018-05-17 2020-07-03 Thales Procede pour mesurer en fonctionnement operationnel certaines caracteristiques du transpondeur de bord en utilisant le radar secondaire

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2139216A1 (de) * 1971-08-05 1973-02-15 Siemens Ag Richtantennenanordnung
FR2243532A1 (de) * 1973-09-07 1975-04-04 Thomson Csf
DE2411158B1 (de) * 1974-03-08 1975-08-07 Siemens Ag, 1000 Berlin Und 8000 Muenchen Monopuls-Richtantennenanordnung mit einem aus Dipolen bestehenden Primärstrahlersystem

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3312970A (en) * 1941-06-27 1967-04-04 Rca Corp Pulse echo recognition systems
US3296615A (en) * 1942-01-19 1967-01-03 Robert M Page Identification and recognition system
US3311912A (en) * 1942-12-11 1967-03-28 Verne R Philpott Radar recognition system
US3032759A (en) * 1956-08-31 1962-05-01 North American Aviation Inc Conical scanning system
US3893116A (en) * 1958-12-30 1975-07-01 Hughes Aircraft Co Radar lobing system
US3122737A (en) * 1960-05-17 1964-02-25 Setrin Morton Apparatus for suppressing side-lobe interrogations in transponder beacon systems
US3618091A (en) * 1961-11-10 1971-11-02 Sanders Associates Inc Conical antenna system
US3688313A (en) * 1966-12-19 1972-08-29 Motorola Inc Combined cw and pulse tracking systems

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2139216A1 (de) * 1971-08-05 1973-02-15 Siemens Ag Richtantennenanordnung
FR2243532A1 (de) * 1973-09-07 1975-04-04 Thomson Csf
DE2411158B1 (de) * 1974-03-08 1975-08-07 Siemens Ag, 1000 Berlin Und 8000 Muenchen Monopuls-Richtantennenanordnung mit einem aus Dipolen bestehenden Primärstrahlersystem

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0057538A2 (de) * 1981-01-29 1982-08-11 Kabushiki Kaisha Toshiba Antennenanordnung
EP0057538A3 (en) * 1981-01-29 1982-12-01 Tokyo Shibaura Denki Kabushiki Kaisha Antenna device
US4468670A (en) * 1981-01-29 1984-08-28 Tokyo Shibaura Denki Kabushiki Kaisha Antenna device for air traffic radar
FR2638531A1 (fr) * 1988-10-28 1990-05-04 Thomson Csf Systeme d'integration des voies somme et difference i.f.f. dans une antenne de surveillance radar
EP0367656A1 (de) * 1988-10-28 1990-05-09 Thomson-Csf System zur Integration von FF-Summen- und -Differenzkanälen in einer Antenne eines Überwachungsradars
US5036336A (en) * 1988-10-28 1991-07-30 Thomson-Csf System for the integration of I.F.F. sum and difference channels in a radar surveillance antenna
US5483663A (en) * 1994-04-05 1996-01-09 Diversified Communication Engineering, Inc. System for providing local originating signals with direct broadcast satellite television signals
US5761605A (en) * 1996-10-11 1998-06-02 Northpoint Technology, Ltd. Apparatus and method for reusing satellite broadcast spectrum for terrestrially broadcast signals
US6208834B1 (en) 1996-10-11 2001-03-27 Northpoint Technology, Ltd. Apparatus and method for facilitating terrestrial transmissions at frequencies also used for satellite transmissions to a common geographic area
US7853197B2 (en) 1996-10-11 2010-12-14 Carmen Tawil Apparatus and method for reusing satellite broadcast spectrum for terrestrially broadcast signals
FR2773271A1 (fr) * 1997-12-31 1999-07-02 Thomson Multimedia Sa Emetteur/recepteur d'ondes electromagnetiques
US6730310B2 (en) 1998-10-30 2004-05-04 Colgate-Palmolive Company Wash-off vitamin E compositions
WO2018060070A1 (en) 2016-09-29 2018-04-05 Bayer Cropscience Aktiengesellschaft Novel triazole derivatives

Also Published As

Publication number Publication date
ATE5836T1 (de) 1984-01-15
EP0025739B1 (de) 1984-01-11
FR2465328A1 (fr) 1981-03-20
NO152189C (no) 1985-08-14
NO802636L (no) 1981-03-09
NO152189B (no) 1985-05-06
DE3066094D1 (en) 1984-02-16
FR2465328B1 (de) 1983-12-09
US4376937A (en) 1983-03-15
JPS5689076A (en) 1981-07-20

Similar Documents

Publication Publication Date Title
EP0025739B1 (de) Primär- und Sekundär-Radarantenne
EP0012055A1 (de) In Streifenleitertechnik ausgeführter Monopulsprimärstrahler und Antenne mit einem solchen Strahler
EP0899814B1 (de) Strahlende Struktur
FR2501868A1 (fr) Appareil pour determiner la presence de conditions de trajets de reflexion multiples lors de la poursuite d'une cible a l'aide d'un radar
FR2648626A1 (fr) Element rayonnant diplexant
EP3223032B1 (de) Sekundärradar für die erfassung von zielen in grosser höhe
EP0018878B1 (de) IFF-Bordsystem mit Radar- und Abfrageantenne
FR2993715A1 (fr) Source radiofrequence compacte, antenne et systeme d'antennes multifaisceaux comportant de telles sources compactes et systeme de telecommunication par satellite comportant au moins une telle antenne
EP1798809B1 (de) Vorrichtung zum Ausstrahlen und/oder Empfangen von elektromagnetischen Wellen für aerodynamisch gesteuerte Luftfahrzeuge
CA2800952C (fr) Antenne compacte large bande a tres faible epaisseur et a double polarisations lineaires orthogonales operant dans les bandes v/uhf
EP1181744B1 (de) Antenne mit vertikaler polarisation
FR2984612A1 (fr) Joint tournant hyperfrequence
EP2006954B1 (de) Kommunikationsgerät für Schienenfahrzeuge
FR3101486A1 (fr) Antenne multi-bande
EP0021866B1 (de) Vorrichtung zur Unterdrückung von Störsignalen mit einer drehenden linearen Polarisation und deren Verwendung in einem Radargerät
EP3155689B1 (de) Flachantenne zur satellitenkommunikation
FR3003703A1 (fr) Dispositif de reduction de signature radar d'antenne, systeme antennaire et procede associe
EP3365943B1 (de) Antennenvorrichtung für erfassungshilfe und entsprechendes antennensystem zur überwachung eines sich bewegenden ziels
EP3155690B1 (de) Flachantenne zur satellitenkommunikation
EP0337841A1 (de) Unsymmetrisch gespeiste breitbandige Sendeantennenschleife und Antennenfeld aus einer Vielzahl dieser Schleifen
FR2755796A1 (fr) Alimentation pour une antenne de radar dans la bande des gigahertz
FR2661562A1 (fr) Antenne cassegrain.
FR2943466A1 (fr) Element rayonnant a bipolarisation
EP0429349A1 (de) Verfahren und Einrichtung zur Übertragung breitbandiger Signale mit Hilfe einer mobilen Ausrüstung
FR3131105A1 (fr) Antenne élémentaire de type micro-ruban et antenne réseau améliorées

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

Designated state(s): AT BE CH DE GB IT LI SE

17P Request for examination filed

Effective date: 19810403

ITF It: translation for a ep patent filed

Owner name: JACOBACCI & PERANI S.P.A.

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Designated state(s): AT BE CH DE GB IT LI SE

REF Corresponds to:

Ref document number: 5836

Country of ref document: AT

Date of ref document: 19840115

Kind code of ref document: T

REF Corresponds to:

Ref document number: 3066094

Country of ref document: DE

Date of ref document: 19840216

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

Ref country code: CH

Payment date: 19840720

Year of fee payment: 5

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

Ref country code: DE

Payment date: 19840723

Year of fee payment: 5

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

Ref country code: SE

Payment date: 19840930

Year of fee payment: 5

Ref country code: BE

Payment date: 19840930

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

Ref country code: AT

Payment date: 19860829

Year of fee payment: 7

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

Ref country code: GB

Effective date: 19890829

Ref country code: AT

Effective date: 19890829

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

Ref country code: SE

Effective date: 19890830

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

Ref country code: LI

Effective date: 19890831

Ref country code: CH

Effective date: 19890831

Ref country code: BE

Effective date: 19890831

BERE Be: lapsed

Owner name: THOMSON-CSF

Effective date: 19890831

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

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

Ref country code: DE

Effective date: 19900501

GBPC Gb: european patent ceased through non-payment of renewal fee
EUG Se: european patent has lapsed

Ref document number: 80401242.5

Effective date: 19900418