EP2270922A1 - Antenne mit Sendeflexibilität, Satellit, der eine solche Antenne umfasst, und Steuerverfahren der Sendeänderung einer solchen Antenne - Google Patents

Antenne mit Sendeflexibilität, Satellit, der eine solche Antenne umfasst, und Steuerverfahren der Sendeänderung einer solchen Antenne Download PDF

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Publication number
EP2270922A1
EP2270922A1 EP10164320A EP10164320A EP2270922A1 EP 2270922 A1 EP2270922 A1 EP 2270922A1 EP 10164320 A EP10164320 A EP 10164320A EP 10164320 A EP10164320 A EP 10164320A EP 2270922 A1 EP2270922 A1 EP 2270922A1
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EP
European Patent Office
Prior art keywords
reflector
source
antenna
sources
focus
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Granted
Application number
EP10164320A
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English (en)
French (fr)
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EP2270922B1 (de
Inventor
Pierre Bosshard
Philippe Lepeltier
Serge Depeyre
Gilles Navarre
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Thales SA
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Thales SA
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Publication of EP2270922B1 publication Critical patent/EP2270922B1/de
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    • 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
    • H01Q3/16—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 relative position of primary active element and a reflecting device
    • H01Q3/20—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 relative position of primary active element and a reflecting device wherein the primary active element is fixed and the reflecting device is movable
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q25/00—Antennas or antenna systems providing at least two radiating patterns
    • H01Q25/007—Antennas or antenna systems providing at least two radiating patterns using two or more primary active elements in the focal region of a focusing 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 antenna with mission flexibility and in particular pointing, polarization and frequency. It also relates to a satellite comprising such an antenna and a method for controlling the change of mission of such an antenna.
  • Satellite dish antennas typically have geometrically formed, single-source illuminated reflectors to cover wide coverage areas pointed at the Earth.
  • An antenna subsystem generally includes a transmitting and receiving antenna, or a transmitting antenna and receiving antenna, per coverage area.
  • the geometric shape of the reflector may optionally be defined to be optimized for several orbital positions of the satellite.
  • the change of the orientation of the linear polarization of a satellite antenna or the change from a linear polarization to a circular polarization can be achieved by using two sources, for example two horns, respectively supplied with linear and circular polarization and placed in front of an oversized reflector.
  • the two sources are positioned closer to the focus of the reflector to reduce the losses due to the defocusing of the sources and the resulting directivity losses of the antenna.
  • Another possibility is to use a single source connected to a complex electrical architecture combining two radiofrequency channels, the first operating in circular polarization, the second in linear polarization. This architecture induces reliability problems, an increase in non-negligible ohmic losses related to the complexity of the RF chain and a significant cost of implementation.
  • the object of the invention is to provide an optimal antenna to meet the need for flexibility in pointing, polarization and frequency and to either eliminate the losses due to defocusing when the covers are fixed, or to limit the aberrations and losses due to defocusing when the antenna must operate on covers that may change, the corresponding spots being called mobile spots.
  • Another object of the invention is to provide a simple antenna to implement, and having a geometry that does not result from a compromise related to flexibility and to reduce the ohmic losses compared to previous solutions.
  • the invention relates to a mission flexibility antenna comprising a single reflector and at least a first source and a second source of radiofrequency signals arranged in front of the reflector, the reflector having a focus and each source having a phase center, characterized in that the sources are independent, fixed, and connected to separate radio-frequency power supply chains defining different and predefined polarization and / or operating frequency characteristics, and in that it further comprises means for moving and orientation of the reflector of a first position in which the focus of the reflector is placed in the center of phase of the first source to a second position in which the focus of the reflector is placed in the center of phase of the second source.
  • the means for moving and orienting the reflector comprise means for actuating the reflector in a translation, without rotation, from the first position to the second position, the reflector being oriented in a fixed pointing direction.
  • the phase centers of the two sources are spaced by a predetermined distance and the translation of the reflector is performed over a distance equal to the distance between the phase centers of the two sources.
  • the means of displacement and orientation of the reflector comprise means for actuating the reflector in a translation combined with one or more rotations, the reflector in the second position being oriented in a pointing direction different from that of the reflector in the first position.
  • the displacement and orientation means of the reflector comprise at least one motor connected to the reflector via at least one lever arm.
  • the displacement and orientation means of the reflector comprise three motors connected together by lever arms.
  • the lever arms are three parts of an articulated deployment arm of the reflector.
  • the invention also relates to a telecommunication satellite, characterized in that it comprises at least one mission flexibility antenna.
  • the invention also relates to a method for controlling the mission change of a mission flexibility antenna, the antenna comprising a reflector and at least a first source and a second source of radiofrequency signals arranged in front of the reflector, the reflector having a focal point and each source having a phase center, characterized in that it consists in using independent, fixed sources connected to separate radiofrequency power supply chains defining different and predefined polarization and / or operating frequency characteristics, selecting a source according to the desired mission type and then moving and / or orienting the reflector so that the phase center of the selected source is positioned at the focus of the reflector and the reflector illuminates a selected coverage area.
  • the displacement of the reflector is a translation, without rotation, of a first position in which the focus of the reflector is placed in the center of phase of the first source to a second position according to which the focus of the reflector is placed in the center of phase of the second source, the translation being carried out over a distance strictly equal to the distance which separates the phase centers of the two sources.
  • the displacement of the reflector is a translation combined with one or more rotations of a first position according to which the focal point of the reflector is placed in the center of phase of the first source towards a second position according to which the focus of the reflector is placed in the center of phase of the second source,.
  • the flexibility of polarization and / or frequency and / or pointing plane is provided by mechanisms of movement and orientation of the reflector, for example mounted on the deployment arm, which allow the placement of the focus of the reflector at phase center of one of the sources.
  • the movement of the reflector which allows the passage of the phase center of the first source S1 to the phase center of the second source S2 consists in translating the reflector without rotation by a distance which is rigorously equal to that separating the phase centers from the two sources.
  • the relative movement of the reflector consists of a translation associated with one or more rotations.
  • the antenna comprises a reflector 10 mounted on the platform 11 of a satellite via an articulated deployment arm 13, 14, 15 and at least two independent sources S1, S2, ..., Sn radiofrequency signals arranged in front of the reflector.
  • the sources for example cone type, are fixed on a supporting structure 12 arranged on the platform 11 and are arranged in a predetermined fixed configuration, for example next to each other.
  • the sources S1 to Sn may in some cases be placed one above the other or in any other configuration.
  • the antenna further comprises at least one mechanism for moving and orienting the reflector 10 which makes it possible to place the focus of the reflector at the phase center of one of the sources.
  • the movement mechanism and orientation of the reflector mounted for example on the deployment arm 13, 14, 15 of the reflector 10, may for example comprise one or more stepper motors M1, M2, M3 associated with lever arms corresponding or a stepper motor connected to a gimbal.
  • the number of engines and the number of sources depends on the types of missions that the satellite must carry out. For example three engines M1, M2, M3 and three sources S1, S2, Sn are represented on the figure 1 .
  • the motor M1 is secured to the platform 11 and connected to the motor M2 by a first lever arm 13, the M2 and M3 engines are interconnected by a second lever arm 14, the motor M3 is connected to the reflector 10 by a third lever arm 15.
  • the first, second and third lever arm constitute three articulated portions of the deployment arm.
  • the geometric shape of the reflective surface of the reflector 10 is approximately parabolic in shape and differs only slightly. This shape is optimized to illuminate a ground coverage area having predetermined dimensions when only one source is placed in its focus.
  • the motors mounted on the deployment arm allow both to move and orient the reflector 10 according to the mission to be performed by the antenna, but also to fold the reflector in a storage position against the platform 11 in case of prolonged use of the antenna.
  • the sources S1 to Sn can be aligned as shown, for reasons of simplification, in the different figures or placed in two-dimensional configurations, such as for example in a triangle.
  • the polarization and / or frequency flexibility is only possible in one plane and the coverage areas, obtained with the different sources, are aligned.
  • the sources are placed in two-dimensional configurations, it is possible to have polarization flexibility in several planes.
  • the invention consists in using several sources fed via different channels RF1, RF2, ... RFn radiofrequency signal supply.
  • Each radio frequency channel being dedicated to telecommunication functions corresponding to a predetermined polarization, it is optimal which allows a very significant reduction in ohmic losses compared to electrical architectures that use combinations of two radio frequency channels.
  • the different sources S1 to Sn can be fed in different polarizations and / or in different frequency planes.
  • the invention then consists in selecting a source as a function of the desired type of polarization and frequency and then moving and orienting the reflector so that the center of the phase of the selected source is positioned at the focus of the reflector and that the reflector illuminates the selected coverage area.
  • the invention consists in translating, without rotation, the reflector of a first position 10a according to which the focal point of the reflector is placed at the center of phase 5 of the first source S1 towards a second position 10b according to which the focus of the reflector is placed at the center of phase 6 of the second source S2.
  • the displacement distance of the reflector in translation is strictly equal to the distance D1 which separates the phase centers 5, 6 of the two sources S1, S2.
  • the movement of the reflector is a translation combined with one or more rotations.
  • S1 can be fed in a linear polarization and operate in the Ku frequency band
  • S2 can be fed in a circular polarization and operate in the Ku frequency band
  • S3 can be fed in a linear polarization shifted by 7.5 ° and operate in the Ku + frequency band.
  • the center of phase 5 of the source S1 is positioned at the focus of the reflector 10 which points in a pointing direction 16 located for example on the Earth's equator.
  • the source S1 is for example supplied by a linearly polarized signal via a first radiofrequency channel RF1 and the source S2 is for example connected to a second radiofrequency ring RF2 allowing a circular polarization, to go from the linear polarization to the circular polarization without changing the pointing of the antenna
  • the invention consists in switching the power supply from the source S1 to the source S2 and moving the reflector in translation, over a distance D1, from the source S1 to the source S2 to position the focus of the reflector 10 at the center of phase 6 of the source S2, as shown in FIG.
  • the invention consists in actuating the motors M1, M2, M3 in rotation.
  • the three motors may for example have axes of rotation substantially parallel to each other and perpendicular to the plane of movement of the reflector. Actuating the motor M1 in rotation in the counterclockwise direction causes the first arm 13 to rotate in the same direction, which has the effect of moving the motor M2, the motor M3 and the reflector 10 away from the machine. platform 11 of the satellite and thus move the reflector 10 of the source S1 to the source S2.
  • the rotation of the motors M2 and / or M3 in a clockwise direction then makes it possible to tilt the reflector 10 in rotation until it is in a position parallel to its initial position and that the center phase 6 of the source S2 is thus positioned at the focus of the reflector 10 and illuminates the same coverage area on the Earth.
  • Successive rotations of the various motors M1, M2 and / or M3 thus make a translation to the reflector 10 such that its focus passes from the source S1 to the source S2.
  • the same operations can be reproduced with another source such as the source S3, for example to change operating frequency plan if the source S3 is connected to a third radio frequency channel RF3 optimized for another frequency plane than that of the sources S1 and S2.
  • the three engines also make it possible to obtain a pointing flexibility and to be able to change coverage areas by changing sources, as represented on the figures 3a , 3b, 3c and the figure 4b .
  • the center of phase 5 of the source S1 is placed at the focus of the reflector 10 which points in a first direction 20 on a first zone 23 for example located on the equator.
  • the reflector has been translated and rotated relative to its initial position of the figure 3a and is therefore not parallel to this initial position.
  • the same operations on the motors M1, M2, M3 can be performed to move the reflector 10 to the third source S3 so that that the phase center 7 of the source S3 is placed at the focus of the reflector and orienting it in a third pointing direction 22 corresponding to a third coverage area 25 on the equator.
  • the figure 4b shows the three different positions 10a, 10b, 10c of the reflector 10 when the different sources S1, S2, S3 are placed at home and for three different pointing directions 20, 21, 22 on the equator.
  • the coverage areas 23, 24, 25 represented in the example of the figure 4b correspond to successive pointing differences spaced by an angle of 3 ° and to a configuration in which the three sources S1, S2, S3 are aligned.
  • the spacing D between the phase centers of the first source S1 and the last source S3 directly depends on the focal length of the reflector 10 and the angular separation between the covers.
  • FIG. 5 shows an example of areas of contiguous covers on the equator obtained with three sources S1, S2, S3.
  • the two zones 26, 27 located between the zones 23 and 24 can be obtained with the same source S1 placed at the focus of the reflector 10, and only changing the orientation of the reflector 10 to change the pointing direction. In this case, only the motors M2 and / or M3 are actuated in rotation, the motor M1 does not move.
  • the three M1, M2, M3 engines provide pointing flexibility in the East-West direction.
  • a fourth motor not shown, with an axis perpendicular to the axes of the motors M1, M2, M3, it becomes possible to modify the orientation angle of the reflector 10 in the North-South direction.

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  • Physics & Mathematics (AREA)
  • Electromagnetism (AREA)
  • Aerials With Secondary Devices (AREA)
  • Variable-Direction Aerials And Aerial Arrays (AREA)
EP10164320.3A 2009-06-19 2010-05-28 Antenne mit Sendeflexibilität, Satellit, der eine solche Antenne umfasst, und Steuerverfahren der Sendeänderung einer solchen Antenne Active EP2270922B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0902996A FR2947103B1 (fr) 2009-06-19 2009-06-19 Antenne a flexibilite de mission, satellite comportant une telle antenne et procede de commande du changement de mission d'une telle antenne

Publications (2)

Publication Number Publication Date
EP2270922A1 true EP2270922A1 (de) 2011-01-05
EP2270922B1 EP2270922B1 (de) 2017-01-18

Family

ID=41582185

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10164320.3A Active EP2270922B1 (de) 2009-06-19 2010-05-28 Antenne mit Sendeflexibilität, Satellit, der eine solche Antenne umfasst, und Steuerverfahren der Sendeänderung einer solchen Antenne

Country Status (5)

Country Link
US (1) US8659493B2 (de)
EP (1) EP2270922B1 (de)
CA (1) CA2706764C (de)
ES (1) ES2622128T3 (de)
FR (1) FR2947103B1 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103094685A (zh) * 2013-01-25 2013-05-08 西安电子科技大学 基于轴向偏焦的大型天线罩电性能补偿方法
WO2014022312A1 (en) 2012-07-30 2014-02-06 Lockheed Martin Corporation Low cost, high-performance, switched multi-feed steerable antenna system

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10012361B2 (en) * 2010-11-15 2018-07-03 Adl, Inc. Multi-spectral variable focus illuminator
US20120274507A1 (en) * 2011-04-28 2012-11-01 Jaafar Cherkaoui Architecture and method for optimal tracking of multiple broadband satellite terminals in support of in theatre and rapid deployment applications
FR3024128B1 (fr) * 2014-07-25 2016-07-22 Thales Sa Procede de mise a poste d'un satellite et de test en orbite de sa charge utile
US10122085B2 (en) * 2014-12-15 2018-11-06 The Boeing Company Feed re-pointing technique for multiple shaped beams reflector antennas
CN105826689B (zh) * 2016-05-24 2018-04-27 西安恒达微波技术开发有限公司 一种超宽带复合天线及其应用的天线系统
US10516216B2 (en) 2018-01-12 2019-12-24 Eagle Technology, Llc Deployable reflector antenna system
GB201811459D0 (en) 2018-07-12 2018-08-29 Airbus Defence & Space Ltd Reconfigurable active array-fed reflector antenna
US10707552B2 (en) 2018-08-21 2020-07-07 Eagle Technology, Llc Folded rib truss structure for reflector antenna with zero over stretch
FR3086927B1 (fr) * 2018-10-04 2020-09-18 Thales Sa Dispositif de deploiement

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US3534375A (en) * 1968-07-09 1970-10-13 T O Paine Multi-feed cone cassegrain antenna
FR2648278A1 (fr) * 1989-06-13 1990-12-14 Europ Agence Spatiale Antenne a faisceaux commutables
EP0845833A2 (de) * 1996-11-27 1998-06-03 HE HOLDINGS, INC. dba HUGHES ELECTRONICS Rekonfigurierbarer profilierter Reflektor im Orbit mit Speise/Reflektor-Defokussierung und kardanaufgehängtem Reflektor
US6441794B1 (en) * 2001-08-13 2002-08-27 Space Systems/Loral, Inc. Dual function subreflector for communication satellite antenna

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US4638322A (en) * 1984-02-14 1987-01-20 The Boeing Company Multiple feed antenna
US6239763B1 (en) * 1999-06-29 2001-05-29 Lockheed Martin Corporation Apparatus and method for reconfiguring antenna contoured beams by switching between shaped-surface subreflectors
WO2005097595A1 (en) * 2004-04-08 2005-10-20 Eads Astrium Limited Deployable boom

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Publication number Priority date Publication date Assignee Title
US3534375A (en) * 1968-07-09 1970-10-13 T O Paine Multi-feed cone cassegrain antenna
FR2648278A1 (fr) * 1989-06-13 1990-12-14 Europ Agence Spatiale Antenne a faisceaux commutables
EP0845833A2 (de) * 1996-11-27 1998-06-03 HE HOLDINGS, INC. dba HUGHES ELECTRONICS Rekonfigurierbarer profilierter Reflektor im Orbit mit Speise/Reflektor-Defokussierung und kardanaufgehängtem Reflektor
US6441794B1 (en) * 2001-08-13 2002-08-27 Space Systems/Loral, Inc. Dual function subreflector for communication satellite antenna

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2014022312A1 (en) 2012-07-30 2014-02-06 Lockheed Martin Corporation Low cost, high-performance, switched multi-feed steerable antenna system
EP2880713A4 (de) * 2012-07-30 2015-12-16 Lockheed Corp Kostengünstiges, hochleistungsfähiges, geschaltetes und aus mehreren quellen steuerbares antennensystem
US9337535B2 (en) 2012-07-30 2016-05-10 Lockheed Martin Corporation Low cost, high-performance, switched multi-feed steerable antenna system
CN103094685A (zh) * 2013-01-25 2013-05-08 西安电子科技大学 基于轴向偏焦的大型天线罩电性能补偿方法
CN103094685B (zh) * 2013-01-25 2014-12-03 西安电子科技大学 基于轴向偏焦的大型天线罩电性能补偿方法

Also Published As

Publication number Publication date
FR2947103B1 (fr) 2012-05-18
ES2622128T3 (es) 2017-07-05
FR2947103A1 (fr) 2010-12-24
US20100321263A1 (en) 2010-12-23
CA2706764C (fr) 2016-08-16
EP2270922B1 (de) 2017-01-18
US8659493B2 (en) 2014-02-25
CA2706764A1 (fr) 2010-12-19

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