EP1010214B1 - Antenne für satelliten mit niedriger umlaufbahn - Google Patents

Antenne für satelliten mit niedriger umlaufbahn Download PDF

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Publication number
EP1010214B1
EP1010214B1 EP98917183A EP98917183A EP1010214B1 EP 1010214 B1 EP1010214 B1 EP 1010214B1 EP 98917183 A EP98917183 A EP 98917183A EP 98917183 A EP98917183 A EP 98917183A EP 1010214 B1 EP1010214 B1 EP 1010214B1
Authority
EP
European Patent Office
Prior art keywords
antenna
satellite
elementary
antennas
radiating elements
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP98917183A
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English (en)
French (fr)
Other versions
EP1010214A1 (de
Inventor
Hubert Diez
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.)
Centre National dEtudes Spatiales CNES
Original Assignee
Centre National dEtudes Spatiales CNES
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Publication date
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Publication of EP1010214A1 publication Critical patent/EP1010214A1/de
Application granted granted Critical
Publication of EP1010214B1 publication Critical patent/EP1010214B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q3/00—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system
    • H01Q3/26—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system varying the relative phase or relative amplitude of energisation between two or more active radiating elements; varying the distribution of energy across a radiating aperture
    • H01Q3/30—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system varying the relative phase or relative amplitude of energisation between two or more active radiating elements; varying the distribution of energy across a radiating aperture varying the relative phase between the radiating elements of an array
    • 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
    • H01Q11/08—Helical antennas
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q21/00—Antenna arrays or systems
    • H01Q21/06—Arrays of individually energised antenna units similarly polarised and spaced apart
    • H01Q21/061—Two dimensional planar arrays
    • H01Q21/067—Two dimensional planar arrays using endfire radiating aerial units transverse to the plane of the array

Definitions

  • the present invention relates to antennas for scrolling satellites.
  • the antennas used by scrolling satellites are either type antennas omnidirectional (SPOT, ERS, etc.) or directive pointable (LANDSAT, etc).
  • the beam is Gaussian and scanning is carried out using a pointing, the antenna behaving like a Classic design centered parabolic reflector.
  • Document US 5,587,719 describes an assembly of antennas for satellite to communication comprising several aligned elementary helical antennas along their longitudinal axis.
  • Each elementary antenna includes four strands regularly distributed in a helix around a cylindrical generator.
  • antennas having a winding of their strands in one direction given are inserted between antennas with a winding in direction opposite.
  • An object of the invention is to propose a antenna for traveling satellite which does not require no pointing mechanism, which has a gain superior to omni-directional antennas and that is space-saving and low cost.
  • the invention proposes a system according to claim 1.
  • the beam emission beam is an elliptical beam ("fan beans” according to Anglo-Saxon terminology) which extends in a direction parallel to that of the vector satellite speed.
  • the antenna illustrated in Figure 1 has a plurality of elementary radiating elements referenced by 1.
  • These elementary radiating elements 1 each have a plurality of helical strands regularly distributed around the same generator revolution.
  • the generator is for example conical or cylindrical. These strands are supplied in an equi-amplitude manner.
  • these strands there are four of these strands and define four identical propellers, offset by ⁇ / 2 relative to each other. These four strands are advantageously supplied with phase quadrature.
  • the angular radiation pattern of such elementary radiant element is of the type illustrated in figure 2.
  • This diagram corresponds to the diagram obtained for an axial height of the radiating element of 0.050 m, a basic radius of 0.018 m, as well as a frequency 8000 MHz transmission. It is related to a sphere of measures 10 m in diameter.
  • the elementary radiating elements 1 are distributed in line in a plane perpendicular to the direction of the velocity vector.
  • the pitch between said radiating elements 1 is by example of 19 mm for an emission frequency of 8000 MHz, which eliminates the need for network lobes.
  • the pitch d of the network is such that d ⁇ / (1 + sin ⁇ ) where ⁇ is the wavelength of the radiation, and ⁇ the maximum depointing desired.
  • the radiating elements 1 are supplied via phase shifters 2 of ferrite type and couplers 3, by a power distributor 6 (in this case 1: 5), which is for example of the waveguide type.
  • phase shifters 2 are controlled by a unit 4, which is the satellite on-board computer, to which they are linked by control electronics 5.
  • phase shifts imposed on the different elements 1 radiators are used to make the depointings desired, up to ⁇ 62 °.
  • the choice for radiating elements 1 of propeller structure provides a gain at 50 ° 2 dB higher than the gain presented at 0 ° (excluding the space attenuation difference compensation -62 ° satellite lift from the zenith) and therefore naturally compensate for the loss of depointing.
  • the optimal number of radiating element elementary will vary from five to twelve depending on mission needs.
  • the phase shifters 2 for example have steps of 22.5 ° quantization and are coded on 4 bits.
  • the beams generated by such an antenna are elliptical (major axis of ellipses parallel to the trace satellite).
  • the cover is shown obtained in the case of phase shifts respectively of a radiating element from one end to the other at 90 °, 45 °, 0 °, - 45 ° and -90 °.
  • the diagram is then deviated by + 18 °.
  • the directivity is 11.52 dB.
  • the depointing is then 32 °, the directivity 11.49 dB.
  • the depointing obtained is 48 °, the directivity 11.45 dB maximum.
  • the directivity obtained at 65 ° is greater than 9-dB, or a gain greater than 7.5 dB if we consider losses of 0.5 dB on the distributors, of 0.5 dB for phase shifters, 0.25 dB at the connection and 0.25 dB at the power supply.
  • the depointing antenna which has just been described allows high ground retransmission rates and allows retransmissions of High resolution images.
  • Beam switching takes place preferably before passage, so as to avoid phase jump problems on the generated coverage.
  • the depointing antenna which has just been described has the advantage of being low cost and above all small footprint.
  • the size of the part radiant is 90mm in length, 5mm in width and 50 mm in height.
  • the antenna comprises several online antennas of the type which has just been describes and switching means for switch from one online antenna to another depending movements of the satellite, and in particular of its roll movements.
  • the antenna includes means for motorization which allow to modify the orientation of the line (s) of elementary radiating elements to compensate for potential movements of the satellite, especially its rolling movements.

Landscapes

  • Variable-Direction Aerials And Aerial Arrays (AREA)
  • Radio Relay Systems (AREA)
  • Details Of Aerials (AREA)

Claims (8)

  1. System mit einem Umlaufsatelliten und einer Antenne für die Rückübertragung von Bildern zur Erde, die von Sichtaufnahmegeräten des Satelliten gesammelt werden, dadurch gekennzeichnet, daß die Antenne mehrere elementare Strahlungsantennen (1) vom Typ, der mehrere Stränge aufweist, die spiralförmig um die gleiche Dreherzeugende gleichmäßig verteilt sind, sowie Mittel zum Versorgen der verschiedenen Stränge mit gleicher Amplitude umfassen, und daß die Achsen der verschiedenen elementaren Antennen parallel sind und in einer gleichen Ebene ausgerichtet sind, in der sie gleichmäßig beabstandet sind, und daß die Ebene, in der diese verschiedenen elementaren Antennen verteilt sind, so bestimmt ist, daß sie senkrecht zur Richtung des Geschwindigkeitsvektors des Satelliten ist, wenn sich der Satellit im Orbit befindet, und daß die Antenne auch Mittel (2) zur Phasenverschiebung der Versorgung dieser verschiedenen elementaren Antennen umfaßt, die geeignet sind, einen elektronischen Richtversatz des länglichen Strahls zu verwirklichen, der von den elementaren Antennen erzeugt wird.
  2. System nach Anspruch 1, dadurch gekennzeichnet, daß die Anzahl an elementaren Strahlungselementen (1) gleich oder größer als fünf ist.
  3. System nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß die elementaren Strahlungselemente (1) um eine Schrittweite gegeneinander versetzt sind, die derart ausgewählt ist, daß die Gitterkeulen vermieden werden.
  4. System nach Anspruch 3, dadurch gekennzeichnet, daß für eine Sendefrequenz von 8000 MHz die Schrittweite zwischen zwei elementaren Strahlungselementen in der Größenordnung von 19 mm liegt.
  5. System nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß die Phasenverschiebungsmittel auf drei bis acht Bits codiert sind.
  6. System nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß die Phasenverschiebungsmittel (2) vom Ferrit-Typ sind.
  7. System, dadurch gekennzeichnet, daß die Antenne mehrere Antennen in Reihe gemäß einem der vorhergehenden Ansprüche und Umschaltmittel umfaßt, die das Kippen einer Antenne in Reihe zu einer anderen abhängig von Bewegungen des Satelliten ermöglichen, und insbesondere von dessen Wankbewegungen.
  8. System nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet, daß die Antenne Motorisierungsmittel umfaßt, die es ermöglichen, die Orientierung der Reihe(n) an elementaren Strahlungselementen zu ändern, um die möglichen Bewegungen des Satelliten zu kompensieren, insbesondere dessen Wankbewegungen.
EP98917183A 1997-03-17 1998-03-17 Antenne für satelliten mit niedriger umlaufbahn Expired - Lifetime EP1010214B1 (de)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR9703250A FR2760900B1 (fr) 1997-03-17 1997-03-17 Antenne pour satellite a defilement
FR9703250 1997-03-17
PCT/FR1998/000535 WO1998042042A1 (fr) 1997-03-17 1998-03-17 Antenne pour satellite a defilement

Publications (2)

Publication Number Publication Date
EP1010214A1 EP1010214A1 (de) 2000-06-21
EP1010214B1 true EP1010214B1 (de) 2003-08-20

Family

ID=9504893

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98917183A Expired - Lifetime EP1010214B1 (de) 1997-03-17 1998-03-17 Antenne für satelliten mit niedriger umlaufbahn

Country Status (8)

Country Link
US (1) US6252562B1 (de)
EP (1) EP1010214B1 (de)
JP (1) JP2001516536A (de)
AT (1) ATE247871T1 (de)
CA (1) CA2284872A1 (de)
DE (1) DE69817373T2 (de)
FR (1) FR2760900B1 (de)
WO (1) WO1998042042A1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7015871B2 (en) 2003-12-18 2006-03-21 Kathrein-Werke Kg Mobile radio antenna arrangement for a base station

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SE516105C2 (sv) * 1999-06-11 2001-11-19 Allgon Ab En metod för att styra strålningsmönstret hos en antenn, ett antennsystem och en radiokommunikationsanordning
FR2810456B1 (fr) * 2000-06-20 2005-02-11 Mitsubishi Electric Inf Tech Dispositif d'antenne reconfigurable pour station de telecommunication
DE10104564C1 (de) 2001-02-01 2002-09-19 Kathrein Werke Kg Steuerungsvorrichtung zum Einstellen eines unterschiedlichen Absenkwinkels insbesondere von zu einer Basisstation gehörenden Mobilfunkantennen sowie eine zugehörige Antenne und Verfahren zur Veränderung eines Absenkwinkels
FR2839207B1 (fr) * 2002-04-29 2004-07-16 Chelton Antennas Antenne accordable passive a large bande
US6806845B2 (en) * 2003-01-14 2004-10-19 Honeywell Federal Manufacturing & Technologies, Llc Time-delayed directional beam phased array antenna
US6784458B1 (en) * 2003-04-14 2004-08-31 Harvatek Corp. Random partitionable dot matrix LED display
FR2976749B1 (fr) * 2011-06-16 2013-06-28 Astrium Sas Dispositif et procede d'optimisation de la couverture au sol d'un systeme spatial hybride.
US10199711B2 (en) 2015-05-13 2019-02-05 The Arizona Board Of Regents On Behalf Of The University Of Arizona Deployable reflector antenna
EP3322999A4 (de) * 2015-07-16 2019-03-20 Arizona Board of Regents on behalf of the University of Arizona Phasengesteuerte leitungsspeisung für reflektorantenne

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5587719A (en) * 1994-02-04 1996-12-24 Orbital Sciences Corporation Axially arrayed helical antenna

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4989011A (en) * 1987-10-23 1991-01-29 Hughes Aircraft Company Dual mode phased array antenna system
US5041842A (en) * 1990-04-18 1991-08-20 Blaese Herbert R Helical base station antenna with support
US5258771A (en) * 1990-05-14 1993-11-02 General Electric Co. Interleaved helix arrays
US5345248A (en) * 1992-07-22 1994-09-06 Space Systems/Loral, Inc. Staggered helical array antenna
US5986619A (en) * 1996-05-07 1999-11-16 Leo One Ip, L.L.C. Multi-band concentric helical antenna

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5587719A (en) * 1994-02-04 1996-12-24 Orbital Sciences Corporation Axially arrayed helical antenna

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7015871B2 (en) 2003-12-18 2006-03-21 Kathrein-Werke Kg Mobile radio antenna arrangement for a base station

Also Published As

Publication number Publication date
DE69817373D1 (de) 2003-09-25
DE69817373T2 (de) 2004-06-09
CA2284872A1 (fr) 1998-09-24
ATE247871T1 (de) 2003-09-15
FR2760900B1 (fr) 1999-05-28
EP1010214A1 (de) 2000-06-21
FR2760900A1 (fr) 1998-09-18
US6252562B1 (en) 2001-06-26
JP2001516536A (ja) 2001-09-25
WO1998042042A1 (fr) 1998-09-24

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