EP0709914A1 - Système d'antenne d'une tête chercheuse-HF pour missiles - Google Patents

Système d'antenne d'une tête chercheuse-HF pour missiles Download PDF

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Publication number
EP0709914A1
EP0709914A1 EP95116740A EP95116740A EP0709914A1 EP 0709914 A1 EP0709914 A1 EP 0709914A1 EP 95116740 A EP95116740 A EP 95116740A EP 95116740 A EP95116740 A EP 95116740A EP 0709914 A1 EP0709914 A1 EP 0709914A1
Authority
EP
European Patent Office
Prior art keywords
cross
antenna system
dipole antennas
periodic
log
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
EP95116740A
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German (de)
English (en)
Other versions
EP0709914B1 (fr
Inventor
Helmuth Dipl.-Ing. Thiere
Anton Dipl.-Ing. Brunner
Peter Dipl.-Ing. Fritsche
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.)
Daimler Benz AG
Bodenseewerk Geratetechnik GmbH
Original Assignee
Daimler Benz AG
Bodenseewerk Geratetechnik GmbH
Siemens AG
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Publication date
Application filed by Daimler Benz AG, Bodenseewerk Geratetechnik GmbH, Siemens AG filed Critical Daimler Benz AG
Publication of EP0709914A1 publication Critical patent/EP0709914A1/fr
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Publication of EP0709914B1 publication Critical patent/EP0709914B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/27—Adaptation for use in or on movable bodies
    • H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
    • H01Q1/281—Nose antennas
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q11/00—Electrically-long antennas having dimensions more than twice the shortest operating wavelength and consisting of conductive active radiating elements
    • H01Q11/02—Non-resonant antennas, e.g. travelling-wave antenna
    • H01Q11/10—Logperiodic antennas
    • H01Q11/105—Logperiodic antennas using a dielectric support
    • 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

Definitions

  • the invention relates to an antenna system housed in a missile according to the preamble of patent claim 1 and patent claim 2.
  • a missile with a long range for locating radar systems or the like requires an HF antenna system to find the target, which enables a monopulse bearing in the azimuth or elevation direction in as many polarizations as possible in a very wide frequency range. Since in such a missile, in addition to the HF radar seeker head, depending on the task, other sensors, e.g. optronic or millimeter-wave sensors for target location and target tracking, the RF antenna system must be compatible with this system in terms of space and undisturbed mode of operation. This means that there should be no blanking or shadowing due to a closed surface or components of the antenna.
  • Missiles with multi-sensors i.e. with HF antennas and optronic sensors are known for the detection of radar systems.
  • a four-arm planar spiral antenna is used as the HF antenna, which can be operated with the aid of a complex passive feed network of hybrid couplers in sum mode and in differential mode over a very wide bandwidth.
  • the spiral antenna is a broadband antenna form, but it works in a very restricted way with regard to polarization. Because of their structure and mode of operation, the direction of rotation of the immanent circular polarization is fixed. It can process either right or left circular polarization and the respective polarization components. Determining the lowest operating frequency is the aperture diameter of the spiral antenna.
  • the differential mode M2 requires a circumference of the radiating active region of at least two wavelengths.
  • the object of the invention is to provide a very broadband effective over several octaves, suitable for monopulse direction finding HF antenna system for a missile, which is compatible with other sensors in terms of space and undisturbed mode of operation and allows any polarization.
  • the logarithmic-periodic dipole antenna is known, for example, from DEIsbell's article: "Log Periodic Dipole Arrays" in "IRE Transactions on Antennas and Propagation", May 1960, pp. 260 to 267. It is one of the almost frequency-independent and therefore very broadband antenna forms. Both orthogonal linear polarizations are available in the cross dipole version. All other polarizations can receive at one of the two outputs with a maximum loss of 3 dB will. With the help of a 90 ° / 3dB hybrid, left and right circular polarization can be formed without polarization loss. Over a very broad frequency band of several octaves, any polarization can be processed without exception. Similar to the planar sine antenna, there is also a frequency-dependent "active area" for the radiation behavior. Several half-wave dipoles are always excited at the respective operating frequency.
  • the longitudinal axes of the four or three logarithmic-periodic cross dipole antennas are inclined so that the phase centers of the active cross dipoles are approximately 0.7 ⁇ ⁇ apart in the entire operating frequency range. This avoids the interferometer properties which have an unfavorable effect on the radiation behavior, such as would occur with an axis-parallel arrangement with increasing frequency and thus increasing electrical antenna spacings.
  • Capacitive loads applied to the ends of the half-wave dipoles in an advantageous manner can considerably reduce the mechanical dimensions in the lower frequency range, so that a greatly reduced base diameter, which then permits the attachment of further sensors, can be achieved.
  • Two unshortened half-wave dipoles next to each other would otherwise require a dimension for the lower frequency that may no longer permit the interference-free accommodation of further sensors.
  • the unfilled space in the cross section of the missile thus offers a favorable integration possibility for further sensors, such as, if necessary, for a millimeter wave antenna system with a monopulse direction finder or other sensors.
  • a group of three according to claim 2 requires approximately logarithmic-periodic cross dipole antennas remain the same size, less installation volume. This means that a larger cross-sectional area in the missile is available for other sensors, for example optronic sensors.
  • the triple antenna system can be designed so that the three log-periodic cross dipole antennas are arranged so that their phase centers form the corner points of an isosceles triangle, the base of which is horizontal.
  • the base can be either below or above, so that a tip of the triangle is exactly above or below. In this case the azimuth symmetry is completely undisturbed.
  • a triangular arrangement with the top up or down can be more economical.
  • the triple antenna system can also be designed so that the three log-periodic cross-dipole antennas are arranged so that their phase centers form the corner points of an isosceles triangle, the base of which is vertical.
  • the base can be either on the left or on the right side, so that a tip of the triangle is on the right outside or left outside. In this case, the symmetry of the elevation is completely undisturbed.
  • the signals of the respective individual lobes of the four log-periodic cross-dipole antennas can be interconnected in a conventionally designed monopulse comparator network so that an amplitude and phase comparison of sum and difference diagrams in elevation and azimuth can be carried out.
  • the broadband monopulse quality must also be taken into account in addition to the free space for other sensors in the horizontal and vertical spacing of the individual logarithmic-periodic cross-dipole antennas.
  • An embodiment described there has a cross shape in cross section and is composed of two orthogonally polarized logarithmic-periodic dipole arrangements.
  • it covers a frequency range of several octaves, whereby different polarizations are set based on the selection of one of the two dipole radiator rows (ie vertical or horizontal linear polarization) or by combining the two output signals in a broadband 90 ° hybrid (ie left-hand circular polarization or right-hand circular polarization) can, and is enclosed in a foamed radome.
  • FIG. 1 shows a front view and FIG. 2 shows a sectional view II-II of FIG. 1 an antenna group consisting of four logarithmic-periodic cross-dipole antennas 1, 2, 3 and 4, which are arranged as HF Antenna system to be housed in the front in a long-range missile for locating radar systems or the like.
  • the four log-periodic cross-dipole antennas 1, 2, 3 and 4 are mounted on a circular, for example dielectric support plate 5 such that the cross-dipole antennas 1 and 2 and below the cross-dipole antennas 3 and 4 each horizontally next to each other and the cross-dipole antennas 1 and 3 and next to them Cross dipole antennas 2 and 4 are vertically below each other.
  • the four log periodic Cross-dipole antennas 1, 2, 3 and 4 protrude with their longitudinal axes 6, 7, 8 and 9 to the front, wherein there is symmetry with respect to a central axis 10 which is perpendicular to the carrier plate 5.
  • the two crossed rows of dipole radiators of each cross-dipole antenna 1, 2, 3 and 4 ensure that the two orthogonal linear polarizations are separate and at the same time available for the utilization of signals in this regard.
  • the longitudinal axes 6, 7, 8 and 9 are inclined to each other so that the phase centers of the active cross dipole antennas 1, 2, 3 and 4 are approximately 0.7 ⁇ ⁇ apart in the entire operating frequency range.
  • FIG. 3 shows a schematic cross-sectional view of an advantageous integration possibility of a so-called "multi-mode" seeker head, which contains, among other things, an RF antenna system according to the invention.
  • the RF antenna system mounted eccentrically on a circular, for example dielectric, carrier plate 11 consists of four logarithmic-periodic cross-dipole antennas 12, 13, 14 and 15 arranged closely adjacent to one another. Apart from the eccentric position on the carrier plate 11, the four cross-dipole antennas 12, 13 are correct , 14 and 15 composite group of four in principle with that of Figures 1 and 2. However, the eccentric offset of the group of four upwards creates a free space 16 in which a further sensor can be arranged.
  • This free space 16 results for example for an additional millimeter wave antenna system 17, a laser range finder 18 and a further sensor 19 by a special measure on the logarithmic-periodic cross dipole antennas 12, 13, 14 and 15
  • Capacitive loads at the ends of the half-wave dipoles of the four log-periodic cross-dipole antennas 12, 13, 14 and 15 can in fact significantly reduce the mechanical dimensions in the lower frequency range, so that the group of four has a considerably smaller base diameter than the diameter of the Reach support plate 11 leaves.
  • Two unshortened half-wave dipoles next to each other would otherwise, i.e. without the capacitive loads, require a dimension for the lower frequency that is somewhat larger than the diameter of the carrier plate 11.
  • the space in the cross section of the missile within a radome 20, which is not filled, thus offers a favorable integration option for the millimeter wave antenna system at the location of the free space 17 and for further sensors at the locations of the free spaces 16, 18 and 19.
  • FIG. 4 shows the front part of a missile in a schematic side view, in which a very broadband HF search body antenna system according to the invention is accommodated under a radome 20.
  • This antenna system consists of a group 21 of four spatially closely spaced individual antennas which are formed by logarithmic-periodic cross-dipole antennas.
  • the longitudinal axes 22, 23, 24 and 25 (only the axes 23 and 25 of the two front cross-dipole antennas are visible in FIG. 4) of these logarithmic-periodic cross-dipole antennas are inclined so that the phase centers of the active cross-dipoles are approximately in the entire operating frequency range are at most 0.7 ⁇ ⁇ apart.
  • the signals of the individual log-periodic cross dipole antennas of the group of four 21 are interconnected via polarization switches 26, 27, 28 and 29 in a monopulse feed network 30 such that an amplitude and phase comparison of sum and difference diagrams in elevation and azimuth can be carried out.
  • the dipoles of the four log-periodic cross-dipole antennas are half-wave dipoles, the ends of which are capacitively loaded, so that a considerably smaller base diameter of the group of four 21 is achieved.
  • the empty space in the cross section of the missile thus offers a very advantageous integration option for further sensors.
  • FIG. 5 shows in a block diagram a monopulse comparator network, as is provided for example in the arrangement according to FIG. 4 as a monopulse feed network 30.
  • the signals coming from the four log-periodic cross dipole antennas are labeled A, B, C and D. They are first fed to two hybrid circuits 31 and 32, the output signals of which then act on two further hybrid circuits 33 and 34. At the outputs of the two hybrid circuits 33 and 34, a total sum signal ⁇ and a total difference signal ⁇ AZ for the azimuth and a total difference signal ⁇ EL for the elevation are then output for any polarization that is set.
  • This conventionally constructed monopulse comparator network according to FIG.
  • FIG. 6 shows a front view of an antenna group consisting of three logarithmic-periodic cross-dipole antennas 35, 36 and 37 which are arranged in close proximity and which are housed as an RF seeker antenna system in the front in a long-range missile for locating radar systems or the like should.
  • the three log-periodic cross-dipole antennas 35, 36 and 37 are mounted on a circular, for example dielectric, carrier plate 38 in such a way that the two cross-dipole antennas 35 and 36 each lie horizontally next to one another and the cross-dipole antenna 37 is arranged centrally above it.
  • the three log-periodic cross dipole antennas 35, 36 and 37 are arranged so that their phase centers 39, 40 and 41 are the corner points of one form isosceles triangle, the base of which is horizontal.
  • the base of this triangle is in the embodiment shown in Fig. 6 below, so that a tip of the triangle is exactly on top. In this case the azimuth symmetry is completely undisturbed.
  • the elevation symmetry is disturbed because there is only one logarithmic-periodic cross-dipole antenna in the upper half of the antenna system, namely the antenna 37, and in the lower half there are two logarithmic-periodic cross-dipole antennas, namely the antennas 35 and 36.
  • the three log-periodic cross dipole antennas 35, 36 and 37 project forward with their longitudinal axes 42, 43 and 44.
  • the two crossed rows of dipole radiators of each cross dipole antenna 35, 36 and 37 ensure that the two orthogonal linear polarizations are separate and at the same time available for the utilization of signals in this regard.
  • the longitudinal axes 42, 43 and 44 are inclined relative to one another in such a way that the phase centers 39, 40 and 41 of the respectively active cross-dipole antennas 35, 36 and 37 are approximately a maximum of 0.7 ⁇ ⁇ apart in the entire operating frequency range.
  • the unfilled space 45 in the cross section of the missile below the antenna system consisting of the three log-periodic cross dipole antennas 35, 36 and 37 offers an additional sensor, for example an optronic sensor, a favorable possibility for integration.
  • FIG. 7 also shows a front view of an antenna group consisting of three logarithmic-periodic cross-dipole antennas 46, 47 and 48 which are arranged in close proximity and which are housed as an RF seeker antenna system in the front in a long-range missile for locating radar systems or the like shall be.
  • the three log-periodic cross dipole antennas 46, 47 and 48 are mounted on a circular, for example dielectric support plate 49 in such a way that the two cross dipole antennas 46 and 47 are each horizontally next to one another and the cross dipole antenna 48 is arranged centrally below it.
  • the three log periodic Cross dipole antennas 46, 47 and 48 are arranged so that their phase centers 50, 51 and 52 form the corner points of an isosceles triangle, the base of which is horizontal.
  • the base of this triangle is in the embodiment shown in Fig. 7 above, so that a tip of the triangle is exactly below.
  • the azimuth symmetry is completely undisturbed, whereas the elevation symmetry is disturbed because two antennas are provided in the upper half of the antenna system and only one antenna is present in the lower half.
  • the three log-periodic cross dipole antennas 46, 47 and 48 protrude forward with their longitudinal axes 53, 54 and 55.
  • the two crossed rows of dipole radiators of each cross dipole antenna 46, 47 and 48 ensure that the two orthogonal linear polarizations are separate and at the same time available for the utilization of signals in this regard.
  • the longitudinal axes 53, 54 and 55 are inclined relative to one another in such a way that the phase centers 50, 51 and 52 of the respectively active cross-dipole antennas 46, 47 and 48 are at a maximum of 0.7 ⁇ ⁇ apart in the entire operating frequency range.
  • the unfilled space 56 in the cross section of the missile below the antenna system consisting of the three log-periodic cross dipole antennas 46, 47 and 48 offers an additional sensor, for example an optronic sensor, a favorable possibility for integration.
  • FIG. 8 shows in a block diagram a monopulse feed network as can be provided, for example, in an advantageous manner for the antenna system in the arrangement according to FIG. 7.
  • the signals coming from the three log-periodic cross dipole antennas are labeled A, B and C.
  • three 3dB dividers 57, 58 and 59 are provided, the inputs of which are each connected to one of the three log-periodic cross-dipole antennas.
  • Signal A thus arrives at the input of the 3dB divider 57, signal B at the input of the 3dB divider 58 and signal C at the input of the 3dB divider 59
  • Two 3dB dividers 57 and 58 which are therefore connected on the input side to the logarithmic-periodic cross-dipole antennas lying with their phase centers in the two corner points of the isosceles triangle, are connected to a terminating resistor 60 and 61, respectively.
  • the other output of the two 3dB dividers 57 and 58 is connected to an input of one of two 3dB / 180 ° hybrid circuits 62 and 63, the second input of which is connected to an output of the third 3dB distributor 59, that is to say its input is connected to the logarithmic-periodic cross-dipole antenna which is not in a base vertex of the isosceles triangle.
  • the difference output of the two 3dB / 180 ° hybrid circuits 62 and 63 is with an input of a first further 3dB / 180 ° hybrid circuit 64 and the sum output of the two 3dB / 180 ° hybrid circuits 62 and 63 with one input a second further 3dB / 180 ° hybrid circuit 65 connected.
  • the total difference signal ⁇ El are at the two outputs of the first further 3dB / 180 ° hybrid circuit 64 in the elevation and the total differential signal ⁇ Az in azimuth and the sum output of the second further 3dB / 180 ° hybrid circuit 65, to whose differential Output a terminating resistor 66 is present, the total signal ⁇ .
  • the disturbed elevation symmetry is corrected by the combination in the monopulse feed network shown in FIG. 8.
  • This disturbance arises because there are two log-periodic cross-dipole antennas in the upper half of the antenna system and only one such cross-dipole antenna in the lower half.

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  • Physics & Mathematics (AREA)
  • Engineering & Computer Science (AREA)
  • Astronomy & Astrophysics (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Physics & Mathematics (AREA)
  • Remote Sensing (AREA)
  • Radar Systems Or Details Thereof (AREA)
  • Variable-Direction Aerials And Aerial Arrays (AREA)
EP95116740A 1994-10-25 1995-10-24 Système d'antenne d'une tête chercheuse-HF pour missiles Expired - Lifetime EP0709914B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4438089 1994-10-25
DE4438089 1994-10-25

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EP0709914A1 true EP0709914A1 (fr) 1996-05-01
EP0709914B1 EP0709914B1 (fr) 2000-01-12

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2079128A1 (fr) 2008-01-11 2009-07-15 Michael Salewski Système d'antenne de brouilleur
CN105633584A (zh) * 2015-12-30 2016-06-01 中国电子科技集团公司第三十九研究所 基于星载多波束天线空间立体结构布局的对数周期馈源阵

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US5999138A (en) * 1998-03-30 1999-12-07 Ponce De Leon; Lorenzo A. Low power switched diversity antenna system
GB0016409D0 (en) * 2000-07-05 2001-08-01 Royal Ordnance Plc Proximity sensing device
US8773300B2 (en) * 2011-03-31 2014-07-08 Raytheon Company Antenna/optics system and method
US8791853B2 (en) * 2011-04-20 2014-07-29 Rockwell Collins, Inc. Air-to-ground antenna
IL232381B (en) * 2014-04-30 2020-02-27 Israel Aerospace Ind Ltd Cover
CN106252900A (zh) * 2016-07-27 2016-12-21 江西洪都航空工业集团有限责任公司 一种共口径宽带干涉仪天线阵
US11682842B1 (en) 2020-10-08 2023-06-20 Rockwell Collins, Inc. Log periodic array application of minature active differential/quadrature radiating elements

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FR2407486A1 (fr) * 1977-10-25 1979-05-25 Saab Scania Ab Dispositif de determination d'une direction repondant a une radiation electromagnetique
US4360816A (en) * 1971-07-21 1982-11-23 The United States Of America As Represented By The Secretary Of The Navy Phased array of six log-periodic dipoles
US4490725A (en) * 1981-10-09 1984-12-25 Gte Products Corporation Log-periodic antenna
US4977408A (en) * 1989-06-28 1990-12-11 General Electric Company Deployable antenna bay
US5274390A (en) * 1991-12-06 1993-12-28 The Pennsylvania Research Corporation Frequency-Independent phased-array antenna

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US2270130A (en) * 1940-08-30 1942-01-13 Rca Corp Directive antenna system
US2414103A (en) * 1941-07-08 1947-01-14 Sperry Gyroscope Co Inc Apparatus for controlling missiles in flight
US3273158A (en) * 1961-07-19 1966-09-13 Ling Temco Vought Inc Multi-polarized tracking antenna
US3147479A (en) * 1962-03-01 1964-09-01 Radiation Inc Plural juxtaposed parabolic reflectors with frequency independent feeds
US4348677A (en) * 1979-06-25 1982-09-07 General Dynamics, Pomona Division Common aperture dual mode seeker antenna
US4658262A (en) * 1985-02-19 1987-04-14 Duhamel Raymond H Dual polarized sinuous antennas
US5451969A (en) * 1993-03-22 1995-09-19 Raytheon Company Dual polarized dual band antenna

Patent Citations (5)

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Publication number Priority date Publication date Assignee Title
US4360816A (en) * 1971-07-21 1982-11-23 The United States Of America As Represented By The Secretary Of The Navy Phased array of six log-periodic dipoles
FR2407486A1 (fr) * 1977-10-25 1979-05-25 Saab Scania Ab Dispositif de determination d'une direction repondant a une radiation electromagnetique
US4490725A (en) * 1981-10-09 1984-12-25 Gte Products Corporation Log-periodic antenna
US4977408A (en) * 1989-06-28 1990-12-11 General Electric Company Deployable antenna bay
US5274390A (en) * 1991-12-06 1993-12-28 The Pennsylvania Research Corporation Frequency-Independent phased-array antenna

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2079128A1 (fr) 2008-01-11 2009-07-15 Michael Salewski Système d'antenne de brouilleur
WO2009087088A1 (fr) * 2008-01-11 2009-07-16 Michael Salewski Système d'antenne de brouillage intentionnel
CN105633584A (zh) * 2015-12-30 2016-06-01 中国电子科技集团公司第三十九研究所 基于星载多波束天线空间立体结构布局的对数周期馈源阵
CN105633584B (zh) * 2015-12-30 2018-07-13 中国电子科技集团公司第三十九研究所 基于星载多波束天线空间立体结构布局的对数周期馈源阵

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US5686929A (en) 1997-11-11
EP0709914B1 (fr) 2000-01-12
DE59507604D1 (de) 2000-02-17

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