EP1291962A1 - Réseau formateur de faisceaux pour véhicule spatial - Google Patents

Réseau formateur de faisceaux pour véhicule spatial Download PDF

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Publication number
EP1291962A1
EP1291962A1 EP02291819A EP02291819A EP1291962A1 EP 1291962 A1 EP1291962 A1 EP 1291962A1 EP 02291819 A EP02291819 A EP 02291819A EP 02291819 A EP02291819 A EP 02291819A EP 1291962 A1 EP1291962 A1 EP 1291962A1
Authority
EP
European Patent Office
Prior art keywords
panels
signals
beam forming
sub
deformation
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.)
Ceased
Application number
EP02291819A
Other languages
German (de)
English (en)
French (fr)
Inventor
Jean-Didier Gayrard
Laurent Martin
Gérard Caille
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.)
Alcatel Lucent SAS
Original Assignee
Alcatel CIT SA
Alcatel 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 Alcatel CIT SA, Alcatel SA filed Critical Alcatel CIT SA
Publication of EP1291962A1 publication Critical patent/EP1291962A1/fr
Ceased 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
    • H01Q3/44—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 electric or magnetic characteristics of reflecting, refracting, or diffracting devices associated with the radiating element
    • H01Q3/46—Active lenses or reflecting arrays
    • 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
    • H01Q1/288—Satellite 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
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S343/00—Communications: radio wave antennas
    • Y10S343/02—Satellite-mounted antenna

Definitions

  • the invention relates to an antenna on board a spacecraft, such as a geostationary satellite, and intended to receive and / or transmit radio frequency signals, such as radiocommunications or radar signals.
  • a geostationary satellite including an antenna transmitting and receiving antenna each of which has a reflector associated with a multiplicity of radiating elements or sources.
  • territory to be covered is divided into zones and these resources are assigned to the various areas in such a way that when to an area a resource is assigned, adjacent areas are assigned different resources.
  • Each zone for example, with a diameter of the order of several hundred kilometers, is of such an extent that it must be covered by several radiating elements in order ensure a high gain and sufficient homogeneity of the radiation from the antenna in the area.
  • a territory 10 ' has been represented covered by an antenna on board a geostationary satellite and n zones 12' 1 , 12 ' 2 , .., 12' n .
  • 4 sub-bands of frequencies f1, f2, f3, f4 are used.
  • Zone 12 ' i is divided into several sub-zones 14' 1 , 14 ' 2 , etc. each of which corresponds to a radiating element of the antenna.
  • FIG. 1 shows that with certain radiating elements, for example that of reference 14 ′ 3 in the center of the zone 12 ′ i , corresponds only one sub-band of frequencies f4, while others, such as those located at the periphery of the zone 12 ′ i are associated with several sub-bands, those which are assigned to the adjacent zones.
  • FIG. 2 represents an antenna for receiving a type known for such a telecommunications system.
  • This antenna comprises a reflector 20 ′ and a plurality of radiating elements 22 1 , ..., 22 N located near the focal plane of the reflector.
  • the signal received by each radiating element for example that of the element 22 N , first passes through a filter 24 N intended in particular for eliminating the emission frequency (powerful) then a low noise amplifier 26 N.
  • the signal is, thanks to a divider 30 N , divided into several parts, possibly with coefficients which may differ from one part to another; the purpose of this division is to allow a radiating element to participate in the formation of several beams. It can thus be seen that an output 32 1 of the divider 30 N is assigned to a zone 34 p , while another output 32 i of the divider 30N is assigned to another zone 34 q .
  • the dividers 30 i , .., 30 N as well as the summers 34 p , .., 34 q intended to reconstitute the zones form part of a device 40 called a beam forming network or brushes ("Beam Forming Network" in English or BFN for short).
  • an assembly comprising a phase shifter 42 and an attenuator 44 is provided for each output of each divider 30 i.
  • the phase shifters 42 and attenuators 44 make it possible to modify the radiation diagram either for correct it, if the satellite has undergone an unwanted movement, that is to give a different distribution to the terrestrial areas.
  • each low noise amplifier 26 N is associated with another low noise amplifier 26 ' N , which is identical to it and whose purpose is to replace the amplifier 26 N in the event of the latter failing.
  • two switches 46 N and 48 N are provided for replacement. It is therefore necessary to provide telemetry means (not shown) to detect the failure and remote control means (also not shown) to ensure replacement.
  • a wide antenna i.e. an antenna having a large signal collection or radiation area electromagnetic, benefits from a significant gain (proportional at the surface) and a corresponding power of separation (proportional to the largest dimension).
  • gain proportional at the surface
  • power of separation proportional to the largest dimension
  • antennas of diameter more than 15 meters poses many technical difficulties and practical, in particular the storage in the cap of the launcher, deployment in orbit from the spacecraft, and, in addition, the various mechanical and electrical constraints inherent in large objects in weightlessness and subjected to vacuum such that structural rigidity, mechanical strength, vibrations mechanical, dilation and contraction.
  • Such an antenna is described in the document US 5430451. It describes a network antenna for spacecraft comprising a plurality of subnets connected by a mechanism of joints of each other. In this way, the antenna can occupy a first stacked position when launching the machine (also called stacked configuration) and a second unfolded and flat position when the machine is launched (called unburdened configuration).
  • the object of the present invention is to resolve the disadvantages mentioned above. Its main purpose is to allow simple implementation of an active antenna with networks wide comprising a plurality of sub-arrays of elements deployable radiators.
  • Consistency is the weighted summation of signals received by subnets.
  • the weighting applied to each signal is calculated according to the angle of incidence searched for signal on the subnetwork, angle of incidence real (or observed) signal on the sub-network and phase shifts due to relative delays in signal propagation due to relative positions and distances between subnets.
  • the summation is carried out in a coherent manner for useful signals through the use of information on the relative geometry of the panels.
  • the plurality of subnets of radiating elements and the associated support panels has the advantage of using a stackable structure that can be accommodated in a volume compatible with that of a cap of a space vehicle launcher.
  • the deployment of this stacked structure does not require a complex opening / closing mechanism.
  • the opening / closing operations can be carried out in the same way as those conventionally operated for solar panels.
  • the support panels do not require mechanical rigidity connecting them with the spacecraft.
  • the absence of a locking system and the freedom of movement (possible oscillations) between the adjacent panels makes it possible to reduce the mechanical stresses on the spacecraft.
  • the beam forming network according to the invention comprises digital signal processing means.
  • the digital means of signal processing include software calculation means.
  • each radiating element of the panels is connected to respective means phase shift capable of modifying the phase of the wave to be transmitted, and what the beam forming network includes means for respectively controlling said phase shift means so as to what the respective modification of the phase of the elements radiating distorted position panels compensates for this deformation.
  • said plurality of panels is composed of a first and a second series of signs for receiving and transmitting signals radio frequency, in that said system includes a device multi-source transmission intended to transmit the signals to be transmitted towards the second series of panels with radiating elements corresponding to each source, each element corresponding beam being intended to receive its own signal intended to be phase-shifted by said phase-shifting means in function of the deformation information received by the network, and in that the signal thus possibly out of phase is transmitted to the respective radiating element of the first series of panels for radio frequency transmission.
  • the processing means analog radio frequency signals received and to be transmitted are arranged on the panels.
  • said means of analog processing are connected to the training network of beams by at least one optical fiber.
  • the invention also relates to a spacecraft, characterized in that it includes a system for receiving radio frequency signals according to the invention.
  • said information representative of deformation includes the angle formed between said two adjacent panels, this angle being used for the summons.
  • said method comprises a step of transmitting a beacon signal by a transmitter remote beacon signal, the location of this transmitter being known so as to allow the estimation of said information representative of a deformation with respect to said predetermined configuration expected.
  • FIG. 3 represents a satellite 1 of telecommunications antenna 2 network in its deployed position according to a first embodiment.
  • Two panels 4 are attached to the body 3 of the satellite of solar generator for energy transformation solar energy. These panels 4 are in mode deployed in FIG. 3.
  • the receiving antenna 2 On either side of the body 3 of the satellite are also arranged the receiving antenna 2 and a 5 transmitting antenna.
  • the transmitting antenna is of conventional design and does not works the invention.
  • Power amplifiers and others elements necessary for the emission part can be, in all or part, hosted on the body of the satellite, this thanks to the economy of congestion on the body of the satellite which confers the invention from the receiving side.
  • the antenna 2 network is composed of a plurality of 8-plane panels arranged near the body of the satellite. These panels are used to support sub-networks 6 of elements 7 radiant with polarizer, schematically represented on the Figure 3 for one of the subnets. The panels are not necessarily linked together by a mechanism of fixed joints. The connection between the panels as well as that connecting certain panels 8 to the body of the satellite can be realized by cables 9. Each subnet 6 can be compared to an active network called direct radiation network or DRA (from the English "Direct Radiating Array ").
  • DRA direct radiation network
  • FIG. 4 shows, in section, the elements constituting a sub-network 6 of a panel 8 according to a mode of realization of the invention.
  • Signals arriving on the subnet 6 of a panel are received by the radiating elements 7 of the subnet.
  • the signal received on each radiating element channel is first filtered by a block 10 of filtering and amplification low noise called LNA ("Low Noise Amplifier" in English) intended to filter and only amplify the part of the signal received centered on the desired frequency and particularly to eliminate the transmission frequency.
  • LNA Low Noise Amplifier
  • the signal thus filtered on each channel is then supplied at the output of the filtering and amplification block to a sampler-blocker 11 intended to take a sample modulation of the received microwave signal.
  • this sampler is designed optical and delivers the samples on an optical fiber 12. Des electric cables, not shown, allow the supply of electrical power of amplifiers 10 and samplers 11.
  • Each optical fiber 12 of each panel is connected to inputs 130 for receiving a processing unit 13 digital also called beam forming network or BFN (for "Beam Forming Network” in English).
  • This network 13 is intended that the total area of the subnets is used to capture optimal radio energy emitted by terminals terrestrial, as explained below. This is especially achieved by bringing together and summing up all wanted signals received from all corresponding optical fibers to the different reception channels.
  • network 13 is a microcontroller and the implementation consistency is achieved by known means of consistency which can be a software part 131.
  • the principle of the invention is based on the fact that which the direction of arrival of the wave front corresponding to a wave emitted by a terrestrial terminal and arriving on the panels 8 is not the same for each of the panels if these have relative positions fluctuating over time.
  • the network 13 beam former sum the signals from different radiant elements taking into account, for each sample, the relative position of each panel.
  • the delay or phase shift to compensate in the digital processing of a corresponding signal to a given radiating element must then be based on the conjugation of the parameters of the angle of incidence of this signal, the distance of this element from others and the angle it forms with the other radiating elements of reception.
  • the panels supporting each element radiating their being parallel it comes down to the same result as to refer to the angles that the different panels between them.
  • Figure 5 illustrates schematically, in one case simplified two-dimensional for clarity of presentation, two panels 81, 82 respectively supporting radiating elements 71, 72, the panels being interconnected by a cable 9.
  • the panels and their radiating elements are coplanar and the wavefront 14 attacks the radiating elements at an angle ⁇ relative to the perpendicular to the panels, this being true for both panels.
  • the phase law is adapted to the level of the network 13 trainer of beams to concentrate the radiated energy in the direction ⁇ .
  • the plane of panel 82 has undergone a deviation ⁇ from the plane of the panel 81.
  • the law of phase of the radiating elements 72 of the panel 81 is then adapted to maximize the energy radiation in the ⁇ direction making an angle of ⁇ + ⁇ with the perpendicular to the plane of the panel 81.
  • the determination of this angle ⁇ can be carried out by the regular transmission of a predetermined beacon signal.
  • the beacon signal is advantageously transmitted from a station earthly.
  • This beacon signal has a power such that each radiating element can receive this signal with a ratio sufficient noise signal. In this way, this signal received by each radiating element can be conveyed to the network 13.
  • the latter knowing the position of the transmitting ground station of the beacon signal and knowing the position and attitude of the spacecraft, knows the angle of incidence of the incoming signal, and can deduce by a simple geometric calculation prerecorded, the value of the angle ⁇ .
  • This method presents the advantage of being self-adaptive to follow the evolution of relative geometry of the panels.
  • the beacon signal is transmitted by a ground station (not shown) so periodic so as to obtain a value for this angle set to updated regularly.
  • the beacon signal can come from another place, such that a transmitter on the satellite, or on another satellite or still use any other reference signal conveyed in the aerial media, the principle being to be able to benefit from a signal detectable by network 13 as being a reference signal for measuring the angle ⁇ .
  • Figures 7 and 8 show variants of the telecommunications satellite 1 of FIG. 3, in which the principle of the invention of taking information into account deformation of the panels is used not only for the reception but also for the broadcast.
  • the main advantage of the structure as described for Figures 7 and 8 is the benefit of the network's self-correcting characteristics 13 beam former regardless of distortions that the positions of the panels between them.
  • FIGS. 7 and 8 the sampler-blocker of Figure 4 optical design has been replaced by a analog-to-digital converter 15 electrically connected by a link 16 to the network 13.
  • each radiating element has been connected a delay line 19 and a controllable phase shifter 20 for signal processing on transmission.
  • FIG. 7 illustrates a mast 17 connected to the body 3 of the satellite and carrying the device 18 multisource of emission. This type of arrangement is known as reflector array name or "reflect-array" in English.
  • the phase shifter 20 which is connected to a radiating element receives a control signal from a network output port 132 to control the phase shift value of the element on transmission.
  • the phase shifter is controlled so as to modify the phase of the wave to be emitted, this modification being of the order of deflection undergone by the panel supporting said radiating element (angle ⁇ in the example in Figure 6).
  • the delay line 19 in series compensates for the propagation delay between the multi-source device 19 and the radiating element 7.
  • FIG. 8 illustrates a variant of the embodiment of the previous figure, in which two sets of panels in deployed mode, the first series oriented towards signal to be received from the land terminal and the second series in look at the first series and whose radiating elements are on the face opposite to that opposite the first series.
  • These 8tx radiating elements face the 18 multisource device and are intended to receive the signals transmitted by the sources 183 of this device 18.
  • This arrangement is known as "bootlace" type lens term.
  • the phase shifter 20 which is connected to a radiating element receives a control signal from a network output port 132 13 to control the value of phase shift of the element on transmission.
  • the phase shifter is controlled so as to modify the phase of the wave to be emitted, this modification being of the order of the deviation undergone by the panel supporting said radiating element (angle ⁇ in example Figure 6).
  • Figures 7 and 8 show the particular advantage of centralizing amplifications to emission, which allows the use of wave tubes progressive instead of SSPA, and therefore better power output performance.
  • the series of panels supporting 8tx panels does not have blocks power boost for transmission, which is favorable to the thermal control of these panels, and therefore what can qualify them as so-called "cold" signs.
  • a mode of implementation (not shown) implementing power amplifiers for emission on panels has other advantages.
  • optical fibers used 12 for the connection of the analog signal processing part to the network 13 beam former can be replaced by any other means of electrical connection.
  • Optical fiber has the advantage of reducing the size of the connections.
  • the deployment used for opening / closing support panels can be of any type.

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  • Physics & Mathematics (AREA)
  • Engineering & Computer Science (AREA)
  • Astronomy & Astrophysics (AREA)
  • General Physics & Mathematics (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Details Of Aerials (AREA)
  • Variable-Direction Aerials And Aerial Arrays (AREA)
EP02291819A 2001-09-06 2002-07-18 Réseau formateur de faisceaux pour véhicule spatial Ceased EP1291962A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0111532A FR2829297B1 (fr) 2001-09-06 2001-09-06 Reseau formateur de faisceaux, vehicule spatial, systeme associe et methode de formation de faisceaux
FR0111532 2001-09-06

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EP1291962A1 true EP1291962A1 (fr) 2003-03-12

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EP02291819A Ceased EP1291962A1 (fr) 2001-09-06 2002-07-18 Réseau formateur de faisceaux pour véhicule spatial

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US (1) US6703970B2 (ja)
EP (1) EP1291962A1 (ja)
JP (1) JP4146194B2 (ja)
FR (1) FR2829297B1 (ja)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ITRM20080674A1 (it) * 2008-12-18 2010-06-19 Space Engineering Spa Antenna a lente discreta attiva aperiodica per coperture satellitari multifascio

Families Citing this family (10)

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Publication number Priority date Publication date Assignee Title
US6762716B2 (en) * 2002-12-13 2004-07-13 The Boeing Company Digital beacon asymmetry and quantization compensation
US6954173B2 (en) * 2003-07-02 2005-10-11 Raytheon Company Techniques for measurement of deformation of electronically scanned antenna array structures
US6914554B1 (en) * 2003-10-17 2005-07-05 The United States Of America As Represented By The Secretary Of The Army Radar beam steering with remote reflectors/refractors
EP2119047B1 (en) * 2007-03-03 2010-09-22 Astrium Limited Satellite beam-pointing error correction in digital beam-forming architecture
JP2012222725A (ja) * 2011-04-13 2012-11-12 Toshiba Corp アクティブアレイアンテナ装置
US9293820B2 (en) * 2013-03-13 2016-03-22 The Boeing Company Compensating for a non-ideal surface of a reflector in a satellite communication system
US10439851B2 (en) * 2016-09-20 2019-10-08 Ohio State Innovation Foundation Frequency-independent receiver and beamforming technique
CN111357214B (zh) * 2017-11-16 2022-11-15 联想(北京)有限公司 用于mimo发射的方法及设备
KR102393301B1 (ko) * 2021-11-23 2022-05-02 한화시스템(주) 저궤도 통신위성 안테나 시스템 및 이의 점진적 성능 열화 감소 방법
DE102022123305B3 (de) 2022-09-13 2023-12-28 Deutsches Zentrum für Luft- und Raumfahrt e.V. Richtantenne mit Vermessungssystem zur automatischen Phasenlageneinstellung

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US5175556A (en) * 1991-06-07 1992-12-29 General Electric Company Spacecraft antenna pattern control system
US5430451A (en) * 1992-09-08 1995-07-04 National Space Development Agency Of Japan Array antenna mounted on spacecrafts
US6104343A (en) * 1998-01-14 2000-08-15 Raytheon Company Array antenna having multiple independently steered beams
WO2000072462A2 (en) * 1999-05-10 2000-11-30 Raytheon Company Method and apparatus for a digital phased array antenna

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FR2746365B1 (fr) * 1996-03-20 1998-06-12 Centre Nat Etd Spatiales Perfectionnements aux satellites d'observation ou de telecommunication
US6333712B1 (en) * 1999-11-04 2001-12-25 The Boeing Company Structural deformation compensation system for large phased-array antennas

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US5175556A (en) * 1991-06-07 1992-12-29 General Electric Company Spacecraft antenna pattern control system
US5430451A (en) * 1992-09-08 1995-07-04 National Space Development Agency Of Japan Array antenna mounted on spacecrafts
US6104343A (en) * 1998-01-14 2000-08-15 Raytheon Company Array antenna having multiple independently steered beams
WO2000072462A2 (en) * 1999-05-10 2000-11-30 Raytheon Company Method and apparatus for a digital phased array antenna

Non-Patent Citations (1)

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Title
YONEZAWA R ET AL: "BEAM-SHAPE CORRECTION IN DEPLOYABLE PHASED ARRAYS", IEEE TRANSACTIONS ON ANTENNAS AND PROPAGATION, IEEE INC. NEW YORK, US, vol. 47, no. 3, March 1999 (1999-03-01), pages 482 - 486, XP000830208, ISSN: 0018-926X *

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ITRM20080674A1 (it) * 2008-12-18 2010-06-19 Space Engineering Spa Antenna a lente discreta attiva aperiodica per coperture satellitari multifascio
EP2221919A1 (en) * 2008-12-18 2010-08-25 Agence Spatiale Européenne Multibeam active discrete lens antenna
US8358249B2 (en) 2008-12-18 2013-01-22 Agence Spatiale Europeenne Multibeam active discrete lens antenna

Also Published As

Publication number Publication date
FR2829297A1 (fr) 2003-03-07
JP4146194B2 (ja) 2008-09-03
JP2003087041A (ja) 2003-03-20
FR2829297B1 (fr) 2007-01-05
US20030043068A1 (en) 2003-03-06
US6703970B2 (en) 2004-03-09

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