EP0025739B1 - Primär- und Sekundär-Radarantenne - Google Patents

Primär- und Sekundär-Radarantenne Download PDF

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Publication number
EP0025739B1
EP0025739B1 EP80401242A EP80401242A EP0025739B1 EP 0025739 B1 EP0025739 B1 EP 0025739B1 EP 80401242 A EP80401242 A EP 80401242A EP 80401242 A EP80401242 A EP 80401242A EP 0025739 B1 EP0025739 B1 EP 0025739B1
Authority
EP
European Patent Office
Prior art keywords
primary
radar
interrogation
transceiver
sources
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
Application number
EP80401242A
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English (en)
French (fr)
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EP0025739A1 (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
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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

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    • 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 relates to radar equipment using such air, 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 according to the type of antenna uses.
  • 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 aerial for primary radar and secondary radar conforming to the above is described in document FR-A-2 243 532.
  • This aerial is characterized in that the primary source contains probes emitting and receiving interrogation signals and two sources control signals arranged on either side of the primary source.
  • An air traffic monitoring station comprising a secondary radar, the aerial of which complies with what has been described above, that is to say radiating a diagram of the difference in azimuth type, operates satisfactorily.
  • 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, which width is imposed and on which it is difficult to act.
  • An object of the invention is to remedy this drawback and to define means permitting at the level of the secondary radar of di: to pose a resolution in azimuth greater than that given by the control channel.
  • an aerial for primary radar and secondary radar comprising a reflector illuminated by a primary source coupled to the transceiver of the primary radar which comprises, integrated into it, means for interrogating the detected targets, coupled by a circuit hybrid to the secondary radar transceiver and control means coupled to the secondary radar transceiver through a power divider, is characterized in that, for the secondary radar function, the so-called aerial, in addition to the interrogation channel and the control channel, comprises a monopulse deposit channel, the sum diagram of which is obtained from the interrogation means and the difference diagram from two auxiliary sources arranged on either side of the radiating opening of the primary source in the same plane as the sources of control signals, connected to a deviation meter receiver through a power divider.
  • 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 allowing deviation measurement on the interrogated targets which cannot be separated by the operator on the indicator associated with the control channel and therefore cannot be identified, although interrogated.
  • FIG. 1 represents an exemplary embodiment of a secondary radar antenna comprising the following distance measurement channel - 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, given in document FR-A-2 243 532 but which will be recalled below.
  • This primary source successively comprises a rectangular guide section 1 connected to the transceiver 2 of the primary radar, a transition guide 4, a circular guide section 5 and a horn 6.
  • the link between the primary source and the transmitter -receiver 2 is materialized by two arrows 3.
  • the radar waves pass through the source of the rectangular guide 1 towards the horn 6 from which they are radiated towards the reflector 31.
  • the propagation of the waves s performs in reverse.
  • the reflector 31 is common to the four operating modes of the antenna, primary radar, interrogation and control, monopulse.
  • the antenna comprises means making it possible to perform the function of secondary radar.
  • two probes 8 and 9 placed in the circular guide are available for transmitting and receiving the interrogation signals whose polarization represented by the vector 10 is perpendicular to that of the waves of the primary radar. 5, which are connected to the transceiver 15 of the secondary radar. They are supplied in phase opposition by a hybrid circuit 13 comprising a power divider and a filter.
  • 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 hybrid circuit filter 13a 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 bevelled.
  • 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 31 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 operating mode therefore benefits from the good gain and directivity characteristics of the common reflector, which makes it possible to use, with performance equal to that of known systems, a less efficient transceiver.
  • the control signals are transmitted and received by two sources 16 and 17 placed on either side of the horn 6, symmetrically with respect to its vertical axis V. These sources are connected to the transceiver of the secondary radar 15 by l 'through a power divider circuit 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 same reflector 31 of the radar antenna 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 20 consists of one or more hybrid rings for example.
  • the radiation pattern of the control channel which is of the difference in bearing type and which has an interrogation arc too wide to allow discrimination of the targets, mainly in the approach area is reinforced by another difference type radiation pattern also which allows it to separation of targets in the approach zone, in other words whose azimuthal resolution is finer.
  • the antenna of the secondary radar which already has an interrogation channel and a control channel is reinforced by a monopulse 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 channel to the deviation meter created according to the invention, as has already been said.
  • the sources 23, 24 contributing to the formation of the new difference channel are palcated closer to the radiating opening of the primary source 6 than the sources 16 and 17 of the channel.
  • secondary radar control 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 F of the aerial.
  • auxiliary sources 23-24, the sources of control signals 16-17 and the opening of the horn 6 are substantially in the same vertical plane and that the auxiliary sources and control signals are arranged symmetrically with respect to the vertical axis V of the primary radiating source 6.
  • the signals which they transmit therefore act in a horizontal plane, that is to say in bearing.
  • FIG. 2 represents a variant of the primary radar-secondary radar aerial according to the invention in the case where the primary source operates in circular polarization.
  • the primary source proper comprises a rectangular guide 1, a transition guide 4, a circular guide 5 and the horn 6, 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, as a result of an imperfect adaptation of the horn and which are then dissipated in absorbent charges which are connected to them, are necessary for good functioning in this polarization mode.
  • the probes 8 and 9 are used as in the case of FIG. 1.
  • a diplexer circuit 130 comprising filters and a power divider is 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 hard primary radar signals from the interrogation.
  • the primary radar signals are dissipated in resistive loads 131 and 132.
  • a dielectric strip 22 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 protea calculations, everything happens as if the anoin has an antenna whose gain is approximately 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 radiation diagram correct.
  • the monopulse channel added to the interrogation and control channels of the secondary radar is constituted from probes 8-9 on the one hand which radiate the sum signal and from two auxiliary sources, dipoles 23 and 24 arranged on either side of the primary source 6 which radiate the difference signal.
  • 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 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 transceiver 15 for the interrogation signals.
  • the outputs of the filters 133 and 134 are connected to the adapted charges 131 and 132 which dissipate the energy reflected on the opening of the horn 6.
  • 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 and 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.

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  • 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)

Claims (4)

1. Strahlerfür Primärradar und Sekundärradar, mit einem Reflektor (31), der von einer Primärquelle (4, 5, 6) angestrahlt wird, die an den Sende/Empfänger (2) des Primärradars angekoppelt ist und Mittel (8-9) zur Abfragung der erfaßten Ziele enthält, welche über einen Hybridkreis (13) an den Sende/Empfänger (15) des Sekundärradras angekoppelt sind, und mit Kontrollmitteln (16-17), welche an den Sende/ Empfänger des Sekundärradars (15) über einen Leistungsteiler (20) angekoppelt sind, dadurch gekennzeichnet, daß für die Funktion des Sekundärradars der Strahler zusätzlich zu dem Abfragekanal und dem Kontrollkanal einen Seitenwinkel-Monopulskanal enthält, dessen Summendiagramm ausgehend von den Abfragemitteln (8-9) und von dem Hybridkreis (13) erhalten wird und dessen Differenzdiagramm ausgehend von zwei Hilfsquellen (23-24) erhalten wird, die auf beiden Seiten der abstrahlenden Öffnung der Primärquelle (6-60) in derselben Ebene wie die Kontrollsignalquellen (16, 17) angeordnet und mit einem Ablage-Meßempfänger (27) über einen Leistungsteiler (26) verbunden sind.
2. Strahler nach Anspruch 1, dadurch gekennzeichnet, daß die das Summensignal des Monopulskanals abstrahlenden Mittel gebildet sind aus zwei Sonden (8-9), die in einer zur Polarisationsebene der Wellen des Primärradars senkrechten Ebene in einem senkrechten Schnitt eines kreisförmigen Wellenleiters (5) angeordnet sind, welcher die Primärquelle (6-60) mit dem Sende/Empfänger (2) des Primärradars über einen Übergang (4) verbindet.
3. Strahler nach Anspruch 1, dadurch gekennzeichnet, daß die Hilfsquellen (23-24), welche das Differenzsignal des Monopulskanals abstrahlen, Dipole sind, welche symmetrisch in bezug auf die senkrechte Achse V der Primärquelle (6-60) und auf beiden Seiten der genannten Quelle näher an der genannten Achse als die Quellen (16-17) der Kontrollmittel angeordnet sind, wobei die Hilfsquellen (23-24), die Quellen (16-17) der Kontrollmittel und die Öffnung der Primärquelle (6-60) im wesentlichen in derselben senkrechten Ebene liegen.
4. Strahler nach Anspruch 1, dadurch gekennzeichnet, daß er einen Ablage-Meßempfänger (27) umfaßt, der einerseits mit dem Sende/Empfänger des Sekundärradars (15), dessen Summensignale er empfängt, und andererseits mit den Hilfsantennen (23-24) über einen Leistungsteiler (26) verbunden ist, wovon er die Differenzsignale empfängt.
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
FR7922450A FR2465328A1 (fr) 1979-09-07 1979-09-07 Aerien pour radar primaire et radar secondaire
FR7922450 1979-09-07

Publications (2)

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

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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)

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS57125864A (en) * 1981-01-29 1982-08-05 Toshiba Corp Antenna device
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
FR2638531B1 (fr) * 1988-10-28 1992-03-20 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
FR2773271B1 (fr) * 1997-12-31 2000-02-25 Thomson Multimedia Sa Emetteur/recepteur d'ondes electromagnetiques
US6730310B2 (en) 1998-10-30 2004-05-04 Colgate-Palmolive Company Wash-off vitamin E compositions
FR2965063B1 (fr) * 2010-09-21 2012-10-12 Thales Sa Procede pour allonger le temps d'eclairement de cibles par un radar secondaire
US10318904B2 (en) 2016-05-06 2019-06-11 General Electric Company Computing system to control the use of physical state attainment of assets to meet temporal performance criteria
WO2018060070A1 (en) 2016-09-29 2018-04-05 Bayer Cropscience Aktiengesellschaft Novel triazole derivatives
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

Family Cites Families (10)

* 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
DE2139216C3 (de) * 1971-08-05 1980-06-12 Siemens Ag, 1000 Berlin Und 8000 Muenchen Richtantennenanordnung, bestehend aus einem Hauptreflektorspiegel und zwei Primärstrahlersystemen und Verfahren zur Herstellung einer dielektrischen Reflektorplatte
FR2243532B1 (de) * 1973-09-07 1977-09-16 Thomson Csf

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
"Radar Handbook" Skolnik McGraw Hill 1970 p. 38-9 à 38-11 *

Also Published As

Publication number Publication date
DE3066094D1 (en) 1984-02-16
NO802636L (no) 1981-03-09
US4376937A (en) 1983-03-15
ATE5836T1 (de) 1984-01-15
JPS5689076A (en) 1981-07-20
FR2465328B1 (de) 1983-12-09
EP0025739A1 (de) 1981-03-25
NO152189C (no) 1985-08-14
FR2465328A1 (fr) 1981-03-20
NO152189B (no) 1985-05-06

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