EP1074064B1 - Appareil de poursuite de satellites a defilement - Google Patents

Appareil de poursuite de satellites a defilement Download PDF

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Publication number
EP1074064B1
EP1074064B1 EP99913414A EP99913414A EP1074064B1 EP 1074064 B1 EP1074064 B1 EP 1074064B1 EP 99913414 A EP99913414 A EP 99913414A EP 99913414 A EP99913414 A EP 99913414A EP 1074064 B1 EP1074064 B1 EP 1074064B1
Authority
EP
European Patent Office
Prior art keywords
layer
radiating elements
satellite
transmission
satellites
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
EP99913414A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1074064A1 (fr
Inventor
Ali Louzir
Henri Fourdeux
Patrice Hirtzlin
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.)
Technicolor SA
Original Assignee
Thomson Multimedia SA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Thomson Multimedia SA filed Critical Thomson Multimedia SA
Publication of EP1074064A1 publication Critical patent/EP1074064A1/fr
Application granted granted Critical
Publication of EP1074064B1 publication Critical patent/EP1074064B1/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
    • H01Q19/00—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic
    • H01Q19/06—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using refracting or diffracting devices, e.g. lens
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q19/00—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic
    • H01Q19/06—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using refracting or diffracting devices, e.g. lens
    • H01Q19/062—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using refracting or diffracting devices, e.g. lens for focusing
    • 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
    • H01Q3/12—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system using mechanical relative movement between primary active elements and secondary devices of antennas or antenna systems
    • H01Q3/14—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system using mechanical relative movement between primary active elements and secondary devices of antennas or antenna systems for varying the relative position of primary active element and a refracting or diffracting device
    • 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 apparatus for transmitting and / or reception of signals in a satellite communication system at scrolling.
  • the geostationary satellite has major disadvantages such as significant attenuations of transmitted signals related to distance separating the antennas used from the geostationary satellite (of the order of 36000 kilometers, the corresponding losses then rising to around 205 dB in the Ku band) and transmission delays (typically of the order of 250 ms to 280 ms) becoming clearly perceptible and annoying especially for real-time applications such as telephony, videoconferencing, etc ...
  • the geostationary orbit located in the plane equatorial, poses a problem of visibility for regions at high latitudes, the elevation angles becoming very low for regions close to the poles.
  • the service can not be provided permanently by a single satellite, the continuity of service imposing the scrolling above the service area of several satellites succeeding each other.
  • the object of the invention is therefore to provide an antenna apparatus for tracking of satellites running according to predefined trajectories, to capture at least two satellites succeeding one another in the area of visibility of the device.
  • active will be attributed to any element exchanging with a satellite also says “active” a major part of the useful data, so that the term “liabilities” will mean any other element trading with a other satellite says “passive” signaling data and little data helpful.
  • the apparatus according to the invention makes it possible to transmit and / or receive at least two focused beams in different places and not suffer a switching delay when switching a first satellite to another.
  • the switching means include switching units comprising first switches at an input connected to the signal processing circuit and N ⁇ M outputs related to N ⁇ M radiating elements and / or second switches at N ⁇ M inputs connected to N ⁇ M elements radiators and at an output connected to the signal processing circuit of reception signals, the sequence of radiating elements presenting as a matrix of elements with N rows and M columns.
  • the integer N is predetermined from so that the aircraft presents, when tracking satellites, a radiation pattern that can tilt from 10 ° to 90 ° in elevation.
  • the integer N is predetermined so as to allow visibility in azimuth around a pre-adjusted azimuth value.
  • the elevation will be understood in this application as the angle between the plan horizontal and the radius R passing through the center of the device and the satellite in the instantaneous plane of the trajectory.
  • We also define the azimuth as the angle between said radius R and the vertical in the plane transverse to the plane snapshot of the trajectory.
  • the whole M is chosen in order to ensure the continuation of these by an adjustment in Beam azimuth around a pre-adjusted azimuth value.
  • the series of radiating elements, the switching means and transmission signal processing circuits and / or receiving are arranged on the same layer of a substrate.
  • the sequence of radiating elements is engraved on a first layer of a substrate, under which is disposed a second layer comprising said switches and the signal processing circuitry transmission and / or reception.
  • the sequence of radiating elements is engraved on a first layer under which are arranged a second and third layers respectively comprising said switching means and the circuits for processing transmission and / or reception signals.
  • First lines of excitement to excite the elements are engraved on the second layer for the transmission and / or reception of a first beam and second excitation lines are etched on the third layer for transmitting and / or receiving a second beam.
  • slots are etched on the surface bottom of the first layer -forming a ground plane, so as to allow the exchange of energy with the lower layers.
  • the apparatus comprises first and second means of independent support and adjacent to the focusing surface on which are arranged the continuous sequence of radiating elements. So, this last solution is advantageous especially in the case where the satellites can have significant azimuth variations. It allows in particular reduce the value of the integer M to 1, which corresponds to a continuation in elevation, while ensuring your azimuth tracking of mechanical way.
  • said first and second means of support are coupled to actuating means comprising means rotation of the first and second support means for the orientation of the latter so as to allow satellite azimuth tracking.
  • these rotation means comprise an axis rotation through the center of the Luneberg lens, around which said first and second support means are rotatable.
  • the apparatus comprises means for control for the control of the motors of elements and means actuating.
  • the focusing element of the apparatus is a spherical moonberg lens.
  • the apparatus is intended for the pursuit of scrolling satellites.
  • the apparatus further includes means of transmission and / or reception located in the vicinity of a point of the focusing surface of the device and able to communicate constantly with at least one geostationary satellite.
  • this third element is fixed.
  • the tracking apparatus comprises a spherical Luneberg lens 2 full of a dielectric material of characteristics known per se. It has on both ends of a diameter 4 two adjustment buttons 3.
  • the plane transverse to the section of Figure 1.a passing through the diameter 4 delimits said lens 2 in two half-spheres 2 1 and 2 2 , the half-sphere 2 1 facing the space of radiation where the satellites 1 1 and 1 2 are located while the half-sphere 2 2 faces on its focusing surface 5 to a set of radiating elements 6.
  • This set 6 is supported by a cap 61 electrically transparent (made of polystyrene foam) in the shape of the half-sphere 2 2 , thus acting as an interface between the latter and the assembly 6.
  • the assembly 6 and the cap 61 have the shape of a half-arch of rectangular section.
  • the radiating elements 6 consist of pellets 7 ("patch" in English) whose layout will be explained further.
  • the satellite 1 1 is in vis- ibility of the active pellet 6 a whereas the satellite 1 2 is in visibility of the pellet 6 p waiting for active tracking.
  • the pellet 6 has a target satellite 1 1 .
  • the adjustment knobs 3 allow, for their part, the aiming adjustment of the apparatus in azimuth during installation, as illustrated by the double arrow 60.
  • the apparatus is connected to an indoor unit at the dwelling on which the apparatus rests, this unit being a not shown television decoder.
  • Figure 2.a shows a double layer of primary sources 8 and 9 respectively on supports 10 and 11 independent. Since the mechanical adjustment in azimuth of the two supports 10 and 11 is independent, the primary source 8 a active can continue to target the satellite 1 1 while the source 9 p is waiting to continue the satellite 1 2 actively. This does not exclude the fact that the source 9 p continues the satellite 1 2 but the frequency band allocated to it for the exchange of information with the satellite 1 2 is then reduced compared to the frequency band which is allocated to the exchange of information between the satellite 1 1 and the active primary source 8a. This will be explained more clearly below.
  • 6 to active sources, 8a is a beam 12 called active then passive sources than 6 percent, 9 percent is a bundle called passive 12 percent.
  • the control of the supports 10, 11 is carried out respectively by motors 100, 110 whose actuation is itself controlled by control means 36, 46 detailed below.
  • Figure 3.a is a detailed view of area D illustrated on the Figure 1.a and represents a vertical section of a first layer 13 of pastilles 16 next to the radiation space, a second layer 14 of supply circuits of said pellets 16 able to transmit / receive a first beam, and a third layer 15 of power circuits said pellets 16 adapted to transmit / receive a second beam.
  • the FIG. 3b represents the circuit for feeding pellets 16, arranged on the second layer of Figure 3.a and able to excite the first beam then that Figure 3.c illustrates characteristics identical to Figure 3.b for the excitation of the second beam.
  • the term "beam" is used in the present request to designate any exchange both in reception between a chip 16 and a satellite.
  • the surface bottom of the layer 13 has a metallized surface 18 forming a common ground plane to the three layers of circuits. of the slots 19 detailed in Figure 5 are etched in the ground plane 18, allowing the radiation of the waves between the pellets 16 and the second and third layers 14, 15.
  • the lower surface of the second layer 14 presents the supply circuit 17 of the chip 16 (active or passive ) able to emit / pick up the first beam (active or passive) while the third layer 15 comprises the feed circuit 20 of the pellet 16 ( respectively passive or active) capable of transmitting / sensing the second beam (respectively passive or active).
  • feed lines excite pellets 16 on orthogonal sides.
  • First lines 17 carry the signals received by the pellets 16 and attack ports 21 of a switch 21, an output 21 2 of which drives a frequency conversion circuit 22 to transmit the signals thus transposed into the intermediate satellite band (or BIS). ) to an indoor unit of a dwelling not shown.
  • BIS intermediate satellite band
  • this BIS band is standardized in the context of a direct-to-home satellite communication device. In the present framework, one is not obliged to take this same band for transposition into intermediate frequency.
  • Second lines 17 2 come from a second switch 23 and carry the signals to be transmitted to the satellite.
  • the second switch 23 selects the pad 16 for the aim of the satellite.
  • the input of the switch 23 is connected to a frequency conversion circuit 24 whose input is connected to the indoor unit of the dwelling.
  • Each frequency conversion circuit 22, 24 as well as those mentioned in the following include, in a manner known per se, a mixer 25 and a local oscillator 26 for frequency transposition.
  • the frequency conversion circuits further include a low noise amplifier 27 while in a uplink, the frequency conversion circuits include a power amplifier 28.
  • feed lines excite pellets 16 on orthogonal sides.
  • Third lines 29 carry the signals received by the pellets 16 and attack ports 30 of a third switch 30, an output of which 2 drives a frequency conversion circuit 31 for transmitting the signals thus transposed into the satellite intermediate band.
  • Fourth lines 29 2 come from a fourth switch 32 and carry the signals to be transmitted to the satellite.
  • the fourth switch 32 selects the pad 16 for the aim of the satellite.
  • the input of the switch 32 is connected to a frequency conversion circuit 33 whose input is connected to the indoor unit.
  • the switches 21, 23 are controlled by first means of controlling 34 allowing select the pellet 16 adapted to target the first satellite while the switches 30, 32 are controlled by second means of control 35 to select the pellet 16 adapted to target the second satellite.
  • the first and second control means are included in the microcontroller 36 having stored in a memory 37 information such as the trajectory history of the satellites, ... and also a gain value playing the role of threshold for the detection of a satellite below which the microcontroller 36 must switch either to the adjacent chip 16 to continue the satellite either to the pellet 16 aiming with the second beam the second satellite.
  • the switches 21, 23, 30 and 32 are for example electronic chips with k control pins connected to the microcontroller 36 and N ⁇ M legs connected to the various pellets 16 and a pattte entry or exit.
  • Figure 4.a is a detailed view of a variant of zone D of FIG. 1.a, and represents the first layer 13 of pellets 16 oriented to the radiation space, a second layer 37 for processing the signals to be transmitted and a third layer 38 of signal processing received.
  • Figure 4.b shows the second layer 37 of treatment of signals to be emitted from Figure 4.a, while Figure 4.c represents the third layer 38 for processing the signals received from FIG.
  • the lower surface of the second layer 37 has a supply circuit 38 of the pellet 16 capable of emitting the first and second bundle while the third layer 38 includes the circuit supply 39 of the pellet 16 adapted to receive the first and second beams.
  • the pellet 16 is excited by two opposite sides for transmit separately the first beam and the second beam on layer 37, and to separately capture the first beam and the second beam on the layer 38.
  • feed lines 38 energize pellets 16 on opposite sides.
  • First lines 38 convey the signals to be transmitted on a first beam in a polarization and second lines 38 2 convey signals to be transmitted on a second beam according to the same polarization.
  • These lines 38 1 , 38 2 are respectively connected to first and second switches 40, 41.
  • An input of each of the switches 40, 41 is connected to a frequency converter circuit of the type of that explained above.
  • feed lines 39 exciting the pellets 16 on opposite sides First lines 39 1 convey signals received on a first beam in a polarization and second lines 39 2 convey signals received on a second beam of the same polarization. These lines 39 1 , 39 2 are respectively connected to first and second switches 42, 43. An output of each of the switches 42, 43 is connected to a frequency converter circuit of the type of that explained above.
  • the switch 40 is controlled by third means of control 44 included in a microcontroller 46 for selecting the patch 16 capable of obtaining the optimum beam for the emission towards the first satellite while the switch 41 is controlled by fourth control means 45 able to obtain the optimum beam for the transmission to the second satellite.
  • the switch 42 is controlled by the third control means 44 making it possible to select the patch 16 able to obtain the optimal beam for the receiving signals from the first satellite while the switch 43 is controlled by the fourth control means 45 capable of obtaining the optimal beam for receiving signals from the second satellite.
  • FIG. 5 shows the slots 19 on the face opposite to the face comprising the pellets 16 of the first layer 13.
  • PolII and Pol lines 21 exciting the chip 16 by orthogonal sides correspond to the excitation lines supplying the slots 19 3 in FIG. the case of the embodiment of Figures 3.a to 3.c.
  • a same chip 16 conveys the data transmitted and received by a beam.
  • the excitation by the two orthogonal sides allows the separation of the reception channel and the emission channel on two orthogonal polarizations.
  • the notation Polij corresponds to the line of the beam j conveyed according to a polarization i.
  • the lines Pol11 and Pol12 correspond to the variant of the figures 4.a to 4.c.
  • Pol11 and pol 12 lines excite the chip 16 by sides opposites and convey the data of the reception path of the first beam on one line and the second beam on a second line (or data from the channel of emission of the first beam on a line and the second beam on a second line).
  • the apparatus operates as follows: In the field of visibility of the device is first the first satellite.
  • the active beam associated with the active pellet follows the latter on its path. Before the first satellite disappears from the visibility of the device, a second satellite appears.
  • the device continues to communicate in transmission / reception of the useful data of the first satellite while pursuing the second satellite and communicating only the signaling data thereof to the control means.
  • the lens of Luneberg for example has a diameter of 35 cm, and the device operates at frequencies in the order of 12 GHz.
  • the passage from one pellet to another occurs when the transmit / receive gain variations exceed ⁇ 0.5 dB, or 1 dB relative to the radiation equivalent to the maximum level.
  • the integer N will be determined according to the necessary azimuth coverage, taking into account the rule, as an example, of an incrementation of N one unit for an additional azimuth coverage of 3 °, for the example above.
  • the choices of M and N obviously depend on other beam width, gain fluctuations as the device can tolerate and 16 pellets dimensions that limit the gaps minimum between them.
  • the control means measure the level of the signal received / transmitted to the satellite (active or passive). Since this one is below a predetermined threshold, these actuate the appropriate switches in order to to switch to another pellet and determine the pellet that allows the best satellite tracking.
  • the invention is not limited to the modes of realization as described. So, the Luneberg lens can be cylindrical.
  • the management of the switching from the satellite 1 1 to the satellite 1 2 can be made in any other way than that imagined to explain the operation of the present invention. It can comprise any known methods of multiple access to said at least two satellites 1 1 , 1 2 .

Landscapes

  • Physics & Mathematics (AREA)
  • Electromagnetism (AREA)
  • Variable-Direction Aerials And Aerial Arrays (AREA)
  • Radio Relay Systems (AREA)
  • Aerials With Secondary Devices (AREA)
EP99913414A 1998-04-23 1999-04-15 Appareil de poursuite de satellites a defilement Expired - Lifetime EP1074064B1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR9805112 1998-04-23
FR9805112A FR2778043A1 (fr) 1998-04-23 1998-04-23 Appareil de poursuite a satellites a defilement
PCT/FR1999/000881 WO1999056347A1 (fr) 1998-04-23 1999-04-15 Appareil de poursuite de satellites a defilement

Publications (2)

Publication Number Publication Date
EP1074064A1 EP1074064A1 (fr) 2001-02-07
EP1074064B1 true EP1074064B1 (fr) 2005-06-15

Family

ID=9525604

Family Applications (1)

Application Number Title Priority Date Filing Date
EP99913414A Expired - Lifetime EP1074064B1 (fr) 1998-04-23 1999-04-15 Appareil de poursuite de satellites a defilement

Country Status (13)

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US (1) US20030020652A1 (es)
EP (1) EP1074064B1 (es)
JP (1) JP4219556B2 (es)
KR (1) KR100584892B1 (es)
CN (1) CN1122330C (es)
AU (1) AU3154499A (es)
BR (1) BR9910135A (es)
DE (1) DE69925827T2 (es)
ES (1) ES2244185T3 (es)
FR (1) FR2778043A1 (es)
HU (1) HUP0101576A3 (es)
ID (1) ID27828A (es)
WO (1) WO1999056347A1 (es)

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE29925006U1 (de) 1999-09-20 2008-04-03 Fractus, S.A. Mehrebenenantenne
EP1819014A1 (en) 2001-09-28 2007-08-15 Sumitomo Electric Industries, Ltd. Radio wave lens antenna device
AU2002340506A1 (en) 2002-11-07 2004-06-07 Fractus, S.A. Integrated circuit package including miniature antenna
DE60322116D1 (de) 2003-01-30 2008-08-21 Toshiba Carrier Corp Linsenantennensystem
US20050111379A1 (en) * 2003-10-15 2005-05-26 Samsung Electronics Co., Ltd. Method for controlling packet rate in a mobile communication system
JP4119352B2 (ja) 2003-11-28 2008-07-16 株式会社東芝 レンズアンテナ装置
WO2008015757A1 (fr) * 2006-08-04 2008-02-07 Sei Hybrid Products, Inc. Radar mesurant la vitesse du vent
US9673888B2 (en) * 2015-09-23 2017-06-06 Qualcomm Incorporated Acquiring LEO satellites without compass
ES2805344T3 (es) 2016-05-06 2021-02-11 Amphenol Antenna Solutions Inc Antena multihaz, de alta ganancia, para comunicaciones inalámbricas 5G
CN111009728A (zh) * 2018-10-08 2020-04-14 合肥若森智能科技有限公司 龙伯透镜及基于龙伯透镜阵列的低剖面阵列天线、卫星天线
CN112566204A (zh) * 2020-12-02 2021-03-26 上海擎昆信息科技有限公司 一种基于龙伯透镜的波束切换方法和装置
CN113206390A (zh) * 2021-05-13 2021-08-03 广州通则康威智能科技有限公司 5g-cpe高增益双龙勃透镜天线装置及其工作方法

Family Cites Families (6)

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Publication number Priority date Publication date Assignee Title
US4531129A (en) * 1983-03-01 1985-07-23 Cubic Corporation Multiple-feed luneberg lens scanning antenna system
US5453753A (en) * 1993-09-08 1995-09-26 Dorne & Margolin, Inc. Mechanically steerable modular planar patch array antenna
US5703603A (en) * 1994-04-28 1997-12-30 Tovarischestvo S Ogranichennoi Otvetstvennostju "Konkur" Multi-beam lens antenna
FR2719948B1 (fr) * 1994-05-10 1996-07-19 Dassault Electronique Antenne multi-faisceaux pour la réception de micro-ondes émanant de plusieurs satellites.
FR2762936B1 (fr) * 1997-04-30 1999-06-11 Alsthom Cge Alcatel Dispositif terminal-antenne pour constellation de satellites defilants
FR2770343B1 (fr) * 1997-10-29 1999-12-31 Dassault Electronique Suivi multi-satellites en continu

Also Published As

Publication number Publication date
WO1999056347A1 (fr) 1999-11-04
US20030020652A1 (en) 2003-01-30
AU3154499A (en) 1999-11-16
EP1074064A1 (fr) 2001-02-07
JP4219556B2 (ja) 2009-02-04
HUP0101576A2 (hu) 2001-09-28
DE69925827T2 (de) 2006-05-04
ID27828A (id) 2001-04-26
CN1122330C (zh) 2003-09-24
DE69925827D1 (de) 2005-07-21
BR9910135A (pt) 2001-01-30
HUP0101576A3 (en) 2003-05-28
KR100584892B1 (ko) 2006-05-30
KR20010042874A (ko) 2001-05-25
ES2244185T3 (es) 2005-12-01
FR2778043A1 (fr) 1999-10-29
CN1297594A (zh) 2001-05-30
JP2002513230A (ja) 2002-05-08

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