EP2264830B1 - Reflector antenna with variable coverage and operating frequnecies and a satellite with such antenna - Google Patents
Reflector antenna with variable coverage and operating frequnecies and a satellite with such antenna Download PDFInfo
- Publication number
- EP2264830B1 EP2264830B1 EP10164352.6A EP10164352A EP2264830B1 EP 2264830 B1 EP2264830 B1 EP 2264830B1 EP 10164352 A EP10164352 A EP 10164352A EP 2264830 B1 EP2264830 B1 EP 2264830B1
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- Prior art keywords
- reflector
- antenna
- motor
- source
- reflective surface
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Classifications
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/27—Adaptation for use in or on movable bodies
- H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
- H01Q1/288—Satellite antennas
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q15/00—Devices for reflection, refraction, diffraction or polarisation of waves radiated from an antenna, e.g. quasi-optical devices
- H01Q15/14—Reflecting surfaces; Equivalent structures
- H01Q15/16—Reflecting surfaces; Equivalent structures curved in two dimensions, e.g. paraboloidal
- H01Q15/161—Collapsible reflectors
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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
- H01Q19/10—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 reflecting surfaces
- H01Q19/18—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 reflecting surfaces having two or more spaced reflecting surfaces
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q25/00—Antennas or antenna systems providing at least two radiating patterns
- H01Q25/002—Antennas or antenna systems providing at least two radiating patterns providing at least two patterns of different beamwidth; Variable beamwidth antennas
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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
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- 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 a reflector antenna with coverage and frequency flexibility and a satellite having such an antenna. It applies in particular to the field of satellite telecommunication antennas.
- Antennas on board satellites typically have a geometrically shaped, single-source reflector for covering a coverage area pointed at the Earth.
- a satellite typically 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 but generally to cover a single geographical coverage.
- Frequency flexibility over a broadband spectrum for example the Ku, Ku + frequency plan covering frequencies between 10.7GHz and 18.4GHz and a single coverage area, can not be obtained with a single source because no source is currently sufficiently broadband.
- there is a critical point concerning the diplexing between the transmit and receive tapes and it is necessary to maintain a margin of the order of 250 MHz between the high frequency of the transmission band and the low frequency of the transmission band. reception band.
- a first known solution is to use two separate antennas to cover the same geographical area, but this solution causes problems of mass, size and cost.
- a second known solution is to place two sources side by side in front of an oversized reflector so as to minimize the defocusing of the two sources.
- the phase centers of the two sources are placed in the focal plane of the reflector and their axes of radiation are parallel.
- the two sources are positioned as close to the focus of the reflector to reduce the defocusing of the sources and the resulting directivity losses of the antenna.
- this solution is not optimal.
- Another possibility is to use a single source placed at the focus of a reflector, the source being connected to a complex electrical architecture combining two radio frequency chains, the first channel operating in a first frequency plane, the second channel operating in a second plane of frequencies.
- this architecture induces a complexity generating non-negligible ohmic losses and a significant cost of implementation.
- the current solutions require the use of two separate and independent antennas each having a deployable reflector, the reflector to be associated with two different sources to fully cover a chosen frequency band, which imposes thus four sources in total, placed on a lateral face of a satellite and a double system of stacking to deploy or store the two reflectors of the two antennas.
- the patent US 6,859,188 discloses another solution of using a returnable reflector having two reflective surfaces covering two different coverage areas the reflector being associated with a single source. The positioning of one of the reflective surfaces in front of the source makes it possible to select one of the coverage areas, however this solution has no frequency flexibility and does not allow operation in a broadband frequency plan.
- the documents FR 2,648,278 and WO 01/01520 describe two other solutions for obtaining only coverage flexibility.
- the patent US 6,239,763 discloses a coverage flexibility reflector antenna having a reflector having a plurality of distinct reflective surfaces of predetermined shapes and geometrically shaped to respectively cover different geographical areas.
- the object of the invention is to provide an optimal antenna to meet the need for flexibility in coverage and frequency, to eliminate the aberrations and losses due to defocusing, simple to implement, and whose geometry does not result no compromise in performance and reduces the ohmic losses compared to previous solutions.
- the invention relates to an antenna according to claim 1.
- the active source, S1 or S2 is focused because its phase center is positioned in the focus of the reflector.
- the antenna comprises reflector deployment means comprising at least a first motor and reflector reversing means comprising at least a second motor, the two motors having axes of rotation perpendicular to each other, the second motor actuating the reversal of the reflector from the first position to the second position by a rotation of a predetermined angle of the common support.
- the reflector comprises a third deployment position in which the focus of the first reflecting surface is placed at the phase center of the second source and a fourth deployment position in which the focus of the second reflecting surface is placed in the center of phase. from the first source.
- the antenna further comprises translational means of the reflector comprising a third motor connected to the first motor and the second motor by lever arms, the third motor having an axis of rotation parallel to the axis of rotation of the first motor the first and third motors actuating the translational reflector to change the focus position of the first reflective surface, respectively the second reflective surface, from the first source to the second source.
- translational means of the reflector comprising a third motor connected to the first motor and the second motor by lever arms, the third motor having an axis of rotation parallel to the axis of rotation of the first motor the first and third motors actuating the translational reflector to change the focus position of the first reflective surface, respectively the second reflective surface, from the first source to the second source.
- the antenna comprises a single reflector, this reflector being the returnable reflector.
- This reflector being the returnable reflector.
- a large number of different covers can thus be produced (although, ultimately, only two covers are accessible on the reflector), for example highly distorted geographical covers, very elongated.
- the antenna comprises a main reflector associated with an auxiliary reflector (for example an antenna with a Cassegrain type mounting).
- an auxiliary reflector for example an antenna with a Cassegrain type mounting.
- the main reflector which has two returnable reflective surfaces, so as to benefit from a maximum of degrees of freedom in the production of covers.
- the sources can be attached side by side or one above the other.
- the invention also relates to a telecommunications satellite comprising such an antenna.
- the passive simple offset antenna comprises a reflector 10 in the stored position on the platform 11 of a satellite, for example on a lateral face parallel to a plane YZ, and two independent sources S1, S2 of radio frequency signals.
- the reflector 10 comprises two distinct and differently shaped reflective surfaces R1, R2 fixed back-to-back on a common support 15, as represented for example on the figure 1b . Each reflective surface is geometrically shaped and optimized for a given mission so as to illuminate a ground coverage area having predetermined dimensions when only one source is placed in the home.
- the sources S1, S2 for example of the horn type, are fixed on an inclined plane 16 arranged on the platform 11 and are arranged in a predetermined fixed configuration for example one next to the other.
- the sources S1 and S2 may in some cases be placed one above the other or in any other configuration.
- one of the reflecting surfaces R1, R2 is positioned facing the two sources S1, S2 and is oriented in a predetermined pointing direction 17.
- the reflector 10 is returnable relative to the plane of the support 15 by a rotation of the assembly consisting of the support 15 and the two reflecting surfaces R1, R2, which allows to change reflective surface and therefore desired coverage area.
- the invention therefore consists in positioning the two reflecting surfaces R1, R2 on the common support 15 so that in a first position of the reflector 10 corresponding to a first mission of the satellite, the phase center of the source S1 is placed at the focus of the first reflecting surface R1 and so that in a second position of the reflector obtained by a rotation of the reflector and corresponding to a second mission of the satellite, the phase center of the second source S2 is placed at the focus of the second reflecting surface R2.
- the rotation allowing the reversal of the reflector from the first position to the second position is performed around an axis 22 parallel to the plane of the support 15 and at a predetermined angle depending on the relative positioning of the reflecting surfaces R1, R2 on the support 15.
- the angle of rotation for the reversal of the reflector is adjustable within a predetermined range of values, for example between 175 ° and 195 °.
- the reflector deployment mechanism comprises for example a motor M1 having an axis of rotation parallel to the plane YZ and a deployment arm 13 which can be actuated in rotation by the motor M1 between a position in which the reflector 10 is stored against the wall of the platform 11 parallel to the YZ plane of the satellite and a deployment position.
- the reversal mechanism of the reflector 10 comprises, for example, a second motor M2 axis perpendicular to the axis of the motor M1 and connected to the deployment arm 13 and the reflector 10.
- the second motor M2 actuates the reversal of the reflector 10 from the first position to the second position by a rotation of a predetermined angle of the common support 15.
- the two sources S1, S2 are fed respectively via two different channels 2, 3 for supplying radiofrequency RF signals preferably integrated in a box 14.
- Each RF channel 2, 3 being dedicated to telecommunication functions, the two sources S1, S2 may be fed in different frequency planes F1 and F2, each frequency plan may include one or more frequency subbands on transmission and / or reception.
- the phase center 5 of the source S1 is positioned at the focus of the first reflecting surface R1 which points in a first pointing direction 17 located on a first land cover area corresponding to a first predetermined mission.
- the phase center 6 of the source S2 is positioned at the focus of the second reflecting surface R2 which points in a second pointing direction 18 located on a second land cover area different from the first coverage area and corresponding to a second mission predetermined.
- the transition from the first mission to the second mission is performed by rotating a predetermined angle of the returnable reflector 10, for example 180 °, relative to the plane of the support 15.
- the rotational drive of the reflector 10 is performed at second motor M2.
- the desired change of pointing direction between mission 1 and mission 2 determines the relative position of the two reflecting surfaces R1, R2 relative to each other on support 15.
- the invention consists in selecting one of the sources S1 or S2 as a function of the desired frequency and then moving and orienting the reflector 10 so that the selected source is positioned in the focus of the reflector and that the reflector illuminates the selected coverage area.
- the phase center of the source S1 is positioned at the focus of the first reflective surface R1 of the reflector 10 which points in a pointing direction 17 located for example on the Earth's equator.
- the invention consists in switching the power supply from the source S1 to the source S2 and moving the reflector in translation from the source S1 to the source S2 to position the focus of the first reflective surface R1 at the center of phase 6 of the source S2, as shown in FIG.
- the displacement and orientation of the reflector 10 in front of the source S2 without changing the pointing direction 17 of the antenna can be achieved for example by means of two motors M1, M3, the motor M3 being connected to the motor M1 and the motor M2 by means of corresponding lever arms 20, 21.
- the two motors M1, M3 have axes of rotation parallel, or almost parallel, between them and almost parallel to the plane YZ of the lateral face of the platform 11 of the satellite which supports the reflector 10.
- the actuation of the motor M1 in rotation in the opposite direction of the clockwise and at a rotation angle depending on the spacing between the sources S1 and S2, causes the first lever arm 20 to rotate in the same direction which has the effect of moving and to bring the motor M3 and the reflector 10 closer to the platform 11 of the satellite, as shown in FIG. figure 3b and thus move the reflector of the source S1 to the source S2.
- Actuating the motor M3 in rotation in the clockwise direction at the same angle of rotation as the motor M1 then makes it possible, by means of the lever arm 21, to tilt the reflector 10 in rotation in the direction of rotation.
- the same operations may be reproduced with one or more additional sources, for example to perform one or more other missions in other frequency plans if each additional source is connected to an RF channel dedicated and optimized for another frequency plan than that of sources S1 and S2.
- the first mission is carried out by placing the focus of the reflecting surface R1 on the center of phase 5 of the first source S1, for the second mission, the reflector is translated and the center of phase 6 of the second source S2 is at the focus of the reflective surface R1, for the third mission, the reflector is rotated by a predetermined adjustable angle, for example between 175 ° and 195 ° in the exemplary embodiments, and the first source S1 is at the focus of the reflecting surface R2 and for the fourth mission, the second source S2 is at the focus of the reflecting surface R2.
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Description
La présente invention concerne une antenne à réflecteur à flexibilité de couverture et de fréquence et un satellite comportant une telle antenne. Elle s'applique notamment au domaine des antennes de télécommunication par satellite.The present invention relates to a reflector antenna with coverage and frequency flexibility and a satellite having such an antenna. It applies in particular to the field of satellite telecommunication antennas.
La durée de vie croissante des satellites de télécommunications et l'évolution des exigences associées aux différentes missions qui peuvent leur être confiées, impose que les charges utiles, et en particulier les antennes, des futures générations de satellites soient flexibles. Cette flexibilité peut être réalisée au niveau de la zone de couverture géographique de l'antenne et/ou au niveau de la polarisation et/ou au niveau de la bande de fréquences de fonctionnement. Cette flexibilité n'a pas pour objectif de couvrir toutes les zones de couverture géographiques simultanément mais d'avoir le choix entre plusieurs couvertures géographiques pouvant être générées par la même antenne et de pouvoir modifier, en orbite, la mission du satellite.The increasing lifespan of telecommunications satellites and the evolution of the requirements associated with the various missions that may be entrusted to them, requires that the payloads, and in particular the antennas, of future generations of satellites be flexible. This flexibility can be achieved at the geographical coverage area of the antenna and / or at the level of the polarization and / or at the level of the frequency band of operation. This flexibility is not intended to cover all geographical coverage areas at the same time but to have the choice of several geographic coverage that can be generated by the same antenna and to be able to modify, in orbit, the mission of the satellite.
Les antennes placées à bord des satellites comportent typiquement un réflecteur, géométriquement formé, éclairé par une source unique pour couvrir une zone de couverture pointée sur la Terre. Un satellite comporte généralement une antenne d'émission et de réception, ou une antenne d'émission et une antenne de réception, par zone de couverture. La forme géométrique du réflecteur peut éventuellement être définie de façon à être optimisée pour plusieurs positions orbitales du satellite mais généralement pour couvrir une unique couverture géographique.Antennas on board satellites typically have a geometrically shaped, single-source reflector for covering a coverage area pointed at the Earth. A satellite typically 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 but generally to cover a single geographical coverage.
La flexibilité de fréquence sur un spectre à large bande, par exemple le plan de fréquences Ku, Ku+ couvrant les fréquences comprises entre 10,7GHz et 18,4GHz et une seule zone de couverture, ne peut pas être obtenue avec une seule source car aucune source n'est actuellement suffisamment à large bande. En outre, il existe un point critique concernant le diplexage entre les bandes d'émission et de réception et il est nécessaire de conserver une marge de l'ordre de 250MHz entre la fréquence haute de la bande d'émission et la fréquence basse de la bande de réception.Frequency flexibility over a broadband spectrum, for example the Ku, Ku + frequency plan covering frequencies between 10.7GHz and 18.4GHz and a single coverage area, can not be obtained with a single source because no source is currently sufficiently broadband. In addition, there is a critical point concerning the diplexing between the transmit and receive tapes and it is necessary to maintain a margin of the order of 250 MHz between the high frequency of the transmission band and the low frequency of the transmission band. reception band.
Une première solution connue est d'utiliser deux antennes distinctes pour couvrir la même zone géographique, mais cette solution engendre des problèmes de masse, d'encombrement et de coût.A first known solution is to use two separate antennas to cover the same geographical area, but this solution causes problems of mass, size and cost.
Une deuxième solution connue consiste à placer deux sources côte à côte devant un réflecteur surdimensionné de manière à minimiser la défocalisation des deux sources. Les centres de phase des deux sources sont placés dans le plan focal du réflecteur et leurs axes de rayonnement sont parallèles. Les deux sources sont positionnées au plus près du foyer du réflecteur pour réduire la défocalisation des sources et les pertes en directivité de l'antenne qui en résultent. Cependant cette solution n'est pas optimale.A second known solution is to place two sources side by side in front of an oversized reflector so as to minimize the defocusing of the two sources. The phase centers of the two sources are placed in the focal plane of the reflector and their axes of radiation are parallel. The two sources are positioned as close to the focus of the reflector to reduce the defocusing of the sources and the resulting directivity losses of the antenna. However, this solution is not optimal.
Une autre possibilité consiste à utiliser une seule source placée au foyer d'un réflecteur, la source étant reliée à une architecture électrique complexe combinant deux chaînes radiofréquences, la première chaîne fonctionnant dans un premier plan de fréquences, la seconde chaîne fonctionnant dans un second plan de fréquences. Cependant cette architecture induit une complexité engendrant des pertes ohmiques non négligeables et un coût de réalisation important.Another possibility is to use a single source placed at the focus of a reflector, the source being connected to a complex electrical architecture combining two radio frequency chains, the first channel operating in a first frequency plane, the second channel operating in a second plane of frequencies. However, this architecture induces a complexity generating non-negligible ohmic losses and a significant cost of implementation.
Par ailleurs, pour réaliser deux zones de couverture distinctes, les solutions actuelles nécessitent d'utiliser deux antennes distinctes et indépendantes comportant chacune un réflecteur déployable, le réflecteur devant être associé à deux sources différentes pour couvrir entièrement une bande de fréquence choisie, ce qui impose donc quatre sources au total, placées sur une face latérale d'un satellite et un double système de gerbage pour déployer ou stocker les deux réflecteurs des deux antennes.Moreover, to achieve two distinct coverage areas, the current solutions require the use of two separate and independent antennas each having a deployable reflector, the reflector to be associated with two different sources to fully cover a chosen frequency band, which imposes thus four sources in total, placed on a lateral face of a satellite and a double system of stacking to deploy or store the two reflectors of the two antennas.
Le brevet
Les documents
The documents
Le brevet
Le but de l'invention est de réaliser une antenne optimale permettant de répondre aux besoins de flexibilité en couverture et en fréquence, permettant de supprimer les aberrations et les pertes dues à la défocalisation, simple à mettre en oeuvre, et dont la géométrie ne résulte pas d'un compromis en performances et permet de réduire les pertes ohmiques par rapport aux solutions antérieures.The object of the invention is to provide an optimal antenna to meet the need for flexibility in coverage and frequency, to eliminate the aberrations and losses due to defocusing, simple to implement, and whose geometry does not result no compromise in performance and reduces the ohmic losses compared to previous solutions.
Pour cela, l'invention concerne une antenne selon la revendication 1. Ainsi, quelle que soit la configuration dans laquelle l'antenne selon l'invention est utilisée, la source active, S1 ou S2, est focalisée car son centre de phase est positionné au foyer du réflecteur.For this, the invention relates to an antenna according to
Avantageusement, l'antenne comporte des moyens de déploiement du réflecteur comportant au moins un premier moteur et des moyens de retournement du réflecteur comportant au moins un deuxième moteur, les deux moteurs ayant des axes de rotation perpendiculaires entre eux, le deuxième moteur actionnant le retournement du réflecteur de la première position à la deuxième position par une rotation d'un angle prédéterminé du support commun.Advantageously, the antenna comprises reflector deployment means comprising at least a first motor and reflector reversing means comprising at least a second motor, the two motors having axes of rotation perpendicular to each other, the second motor actuating the reversal of the reflector from the first position to the second position by a rotation of a predetermined angle of the common support.
Avantageusement, le réflecteur comporte une troisième position de déploiement selon laquelle le foyer de la première surface réfléchissante est placé au centre de phase de la deuxième source et une quatrième position de déploiement selon laquelle le foyer de la deuxième surface réfléchissante est placé au centre de phase de la première source.Advantageously, the reflector comprises a third deployment position in which the focus of the first reflecting surface is placed at the phase center of the second source and a fourth deployment position in which the focus of the second reflecting surface is placed in the center of phase. from the first source.
Avantageusement, l'antenne comporte en outre des moyens de translation du réflecteur comportant un troisième moteur relié au premier moteur et au deuxième moteur par des bras de levier, le troisième moteur ayant un axe de rotation parallèle à l'axe de rotation du premier moteur, le premier et le troisième moteur actionnant le réflecteur en translation permettant un changement de la position du foyer de la première surface réfléchissante, respectivement de la deuxième surface réfléchissante, de la première source à la deuxième source. L'antenne selon l'invention bénéficie ainsi d'une cinématique spécifique, grâce notamment aux trois moteurs placés judicieusement, et permet d'atteindre des performances RF optimales sur deux couvertures distinctes et sur deux plans de fréquences différents.Advantageously, the antenna further comprises translational means of the reflector comprising a third motor connected to the first motor and the second motor by lever arms, the third motor having an axis of rotation parallel to the axis of rotation of the first motor the first and third motors actuating the translational reflector to change the focus position of the first reflective surface, respectively the second reflective surface, from the first source to the second source. The antenna according to the invention thus benefits from a specific kinematics, thanks in particular to the three judiciously placed motors, and makes it possible to achieve optimal RF performance on two distinct covers and on two different frequency planes.
Selon un mode de réalisation, l'antenne comporte un unique réflecteur, ce réflecteur étant le réflecteur retournable. Un grand nombre de couvertures différentes peuvent ainsi être produites (bien que, in fine, uniquement deux couvertures soient accessibles sur le réflecteur), par exemple des couvertures géographiques très déformées, très allongées.According to one embodiment, the antenna comprises a single reflector, this reflector being the returnable reflector. A large number of different covers can thus be produced (although, ultimately, only two covers are accessible on the reflector), for example highly distorted geographical covers, very elongated.
Selon un autre mode de réalisation, l'antenne comporte un réflecteur principal associé à un réflecteur auxiliaire (par exemple une antenne avec un montage de type Cassegrain). Dans ce cas, c'est de préférence le réflecteur principal qui comporte deux surfaces réfléchissantes retournables, de manière à bénéficier d'un maximum de degrés de libertés dans la production des couvertures.According to another embodiment, the antenna comprises a main reflector associated with an auxiliary reflector (for example an antenna with a Cassegrain type mounting). In this case, it is preferably the main reflector which has two returnable reflective surfaces, so as to benefit from a maximum of degrees of freedom in the production of covers.
Avantageusement, les sources peuvent être fixées côte à côte ou l'une au-dessus de l'autre.Advantageously, the sources can be attached side by side or one above the other.
L'invention concerne également un satellite de télécommunications comportant une telle antenne.The invention also relates to a telecommunications satellite comprising such an antenna.
D'autres particularités et avantages de l'invention apparaîtront clairement dans la suite de la description donnée à titre d'exemple purement illustratif et non limitatif, en référence aux dessins schématiques annexés qui représentent :
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figure 1a : un schéma en perspective d'un exemple d'antenne à réflecteur à flexibilité de couverture, montée sur la plate-forme d'un satellite, le réflecteur étant dans une position stockée, selon l'invention; -
figure 1b : un schéma en perspective du réflecteur en position déployée montrant les deux surfaces réfléchissantes du réflecteur montées sur un support commun, selon l'invention ; -
figures 2a ,2b : deux schémas de la même antenne pour deux directions de pointage différentes, selon l'invention ; -
figures 3a ,3b : deux schémas de la même antenne dans une deuxième et une troisième positions selon lesquelles la source S1, respectivement la source S2, est au foyer du réflecteur pointé dans une même direction, selon l'invention ;
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figure 1a : a perspective diagram of an example of reflector antenna with flexibility of coverage, mounted on the platform of a satellite, the reflector being in a stored position, according to the invention; -
figure 1b : a perspective diagram of the reflector in the deployed position showing the two reflecting surfaces of the reflector mounted on a common support, according to the invention; -
Figures 2a ,2b : two diagrams of the same antenna for two different pointing directions, according to the invention; -
figures 3a ,3b : two diagrams of the same antenna in a second and a third positions according to which the source S1, respectively the source S2, is at the focus of the reflector pointed in the same direction, according to the invention;
Sur l'exemple représenté sur la
En position déployée, l'une des surfaces réfléchissantes R1, R2 est positionnée en regard des deux sources S1, S2 et est orientée selon une direction de pointage prédéterminée 17. Le réflecteur 10 est retournable par rapport au plan du support 15 par une rotation de l'ensemble constitué par le support 15 et les deux surfaces réfléchissantes R1, R2, ce qui permet de pouvoir changer de surface réfléchissante et donc de zone de couverture souhaitée. L'invention consiste donc à positionner les deux surfaces réfléchissantes R1, R2 sur le support commun 15 de façon que dans une première position du réflecteur 10 correspondant à une première mission du satellite, le centre de phase de la source S1 soit placé au foyer de la première surface réfléchissante R1 et de façon que dans une deuxième position du réflecteur obtenue par une rotation du réflecteur et correspondant à une deuxième mission du satellite, le centre de phase de la deuxième source S2 soit placée au foyer de la deuxième surface réfléchissante R2. La rotation permettant le retournement du réflecteur de la première position à la deuxième position est réalisée autour d'un axe 22 parallèle au plan du support 15 et sur un angle prédéterminé dépendant du positionnement relatif des surfaces réfléchissantes R1, R2 sur le support 15. A titre d'exemple non limitatif, l'angle de rotation pour le retournement du réflecteur est réglable dans une fourchette de valeurs prédéterminée, par exemple entre 175° et 195°.In the deployed position, one of the reflecting surfaces R1, R2 is positioned facing the two sources S1, S2 and is oriented in a
Le mécanisme de déploiement du réflecteur comporte par exemple un moteur M1 ayant un axe de rotation parallèle au plan YZ et un bras de déploiement 13 pouvant être actionné en rotation par le moteur M1 entre une position dans laquelle le réflecteur 10 est stocké contre la paroi de la plate-forme 11 parallèle au plan YZ du satellite et une position de déploiement. Le mécanisme de retournement du réflecteur 10 comporte par exemple un deuxième moteur M2 d'axe perpendiculaire à l'axe du moteur M1 et relié au bras de déploiement 13 et au réflecteur 10. Le deuxième moteur M2 actionne le retournement du réflecteur 10 de la première position à la deuxième position par une rotation d'un angle prédéterminé du support commun 15.The reflector deployment mechanism comprises for example a motor M1 having an axis of rotation parallel to the plane YZ and a
Les deux sources S1, S2 sont alimentées respectivement par l'intermédiaire de deux chaînes 2, 3 différentes d'alimentation en signaux radiofréquence RF de préférence intégrées dans un boîtier 14. Chaque chaîne RF 2, 3 étant dédiée à des fonctions de télécommunication, les deux sources S1, S2 peuvent être alimentées dans des plans de fréquence différents F1 et F2, chaque plan de fréquence pouvant comporter une ou plusieurs sous-bandes de fréquence à l'émission et/ou à la réception.The two sources S1, S2 are fed respectively via two
Sur la
Outre la flexibilité de couverture obtenue par le retournement du réflecteur 10, il est possible d'obtenir une flexibilité de fréquence sur une même zone de couverture et donc pour une même position et une même direction de pointage du réflecteur, sans pertes ni aberrations dues à une défocalisation. Pour cela, l'invention consiste à sélectionner l'une des sources S1 ou S2 en fonction de la fréquence souhaitée puis à déplacer et orienter le réflecteur 10 de façon que la source sélectionnée soit positionnée au foyer du réflecteur et que le réflecteur illumine la zone de couverture sélectionnée.In addition to the flexibility of coverage obtained by the reversal of the
Dans la configuration initiale représentée sur la
Avec une seule antenne comportant deux surfaces réfléchissantes interchangeables, trois moteurs et deux sources S1, S2, il est ainsi possible de déployer l'antenne en orbite, de la positionner de manière à remplir au choix une mission parmi quatre missions possibles. Les deux surfaces réfléchissantes étant interchangeables et mécaniquement solidarisées entre elles, les quatre missions différentes sont remplies en utilisant une seule structure mécanique de support et de déploiement. La première mission est réalisée en plaçant le foyer de la surface réfléchissante R1 sur le centre de phase 5 de la première source S1, pour la deuxième mission, le réflecteur est translaté et le centre de phase 6 de la deuxième source S2 est au foyer de la surface réfléchissante R1, pour la troisième mission, le réflecteur est tourné d'un angle réglable prédéterminé, par exemple compris entre 175° et 195° sur les exemples de réalisation, et la première source S1 est au foyer de la surface réfléchissante R2 et pour la quatrième mission, la deuxième source S2 est au foyer de la surface réfléchissante R2.With a single antenna comprising two interchangeable reflective surfaces, three motors and two sources S1, S2, it is thus possible to deploy the antenna in orbit, to position it so as to fulfill one of four possible missions. The two reflective surfaces being interchangeable and mechanically joined together, the four different missions are fulfilled using a single mechanical structure of support and deployment. The first mission is carried out by placing the focus of the reflecting surface R1 on the center of
Grâce aux trois moteurs, il est ainsi possible de focaliser les sources S1 ou S2 au foyer de l'une des surfaces réfléchissantes R1, R2 du réflecteur 10 ce qui permet d'obtenir des performances optimales sur tout le plan de fréquence. En ajoutant des sources supplémentaires, des missions additionnelles dans des plans de fréquence différents deviennent également possibles.Thanks to the three motors, it is thus possible to focus the sources S1 or S2 at the focus of one of the reflective surfaces R1, R2 of the
Claims (6)
- An antenna having a reflector with coverage and frequency flexibility, comprising a reversible reflector (10) that can be deployed along a deployment axis, which reflector has two distinct reflective surfaces (R1, R2) geometrically shaped so as to respectively cover a first and a second geographical zone, which zones are different and have predetermined shapes, the two reflective surfaces (R1, R2) being attached back-to-back on a common support (15) and the antenna further comprising at least two independent sources (S1, S2) disposed in a fixed configuration and connected to distinct radiofrequency supply chains (2, 3) defining different and predefined operating frequency planes (F1, F2), the reflector (10) comprising a first deployment position, in which the focal point of the first reflective surface (R1) is placed at the phase centre (5) of the first source (S1), and a second deployment position, in which the focal point of the second reflective surface (R2) is placed at the phase centre (6) of the second source (S2), the reflector transitioning from one position to the other by rotating about an axis (22) parallel to the support plane (15) and perpendicular to the deployment axis of the reflector.
- The antenna as claimed in claim 1, characterised in that it comprises means for deploying the reflector (10), comprising at least one first motor (M1), and means for reversing the reflector (10), comprising at least one second motor (M2), the two motors (M1, M2) having axes of rotation that are perpendicular to one another, the second motor (M2) actuating the reversal of the reflector (10) from the first position to the second position by rotating the common support (15) by a predetermined angle.
- The antenna as claimed in claim 1 or 2, characterised in that the reflector (10) comprises a third deployment position, in which the focal point of the first reflective surface (R1) is placed at the phase centre (5) of the second source (S2), and a fourth deployment position, in which the focal point of the second reflective surface (R2) is placed at the phase centre (5) of the first source (S1).
- The antenna as claimed in claim 3, characterised in that it further comprises means for translationally moving the reflector (10), comprising a third motor (M3) connected to the first motor (M1) and to the second motor (M2) by means of lever arms (20, 21), the third motor (M3) having an axis of rotation parallel to the axis of rotation of the first motor (M1), with the first and the third motor (M1, M3) translationally actuating the reflector (10), allowing the position of the focal point of the first reflective surface (R1) and of the second reflective surface (R2), respectively, to be changed from the first source (S1) to the second source (S2).
- The antenna as claimed in any one of the preceding claims, characterised in that the sources (S1, S2) are attached side-by-side or one above the other.
- A telecommunication satellite, characterised in that it comprises at least one antenna as claimed in any one of the preceding claims.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0902995A FR2947104B1 (en) | 2009-06-19 | 2009-06-19 | REFLECTING ANTENNA WITH COVER AND FREQUENCY FLEXIBILITY AND SATELLITE COMPRISING SUCH ANTENNA |
Publications (2)
Publication Number | Publication Date |
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EP2264830A1 EP2264830A1 (en) | 2010-12-22 |
EP2264830B1 true EP2264830B1 (en) | 2018-08-29 |
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Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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EP10164352.6A Active EP2264830B1 (en) | 2009-06-19 | 2010-05-28 | Reflector antenna with variable coverage and operating frequnecies and a satellite with such antenna |
Country Status (5)
Country | Link |
---|---|
US (1) | US8384610B2 (en) |
EP (1) | EP2264830B1 (en) |
CA (1) | CA2706761C (en) |
ES (1) | ES2699484T3 (en) |
FR (1) | FR2947104B1 (en) |
Families Citing this family (2)
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FR3067535B1 (en) * | 2017-06-09 | 2023-03-03 | Airbus Defence & Space Sas | TELECOMMUNICATIONS SATELLITE, METHOD FOR BEAM FORMING AND METHOD FOR MAKING A SATELLITE PAYLOAD |
FR3073347B1 (en) * | 2017-11-08 | 2021-03-19 | Airbus Defence & Space Sas | SATELLITE PAYLOAD INCLUDING A DOUBLE REFLECTIVE SURFACE REFLECTOR |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
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 |
US6795034B2 (en) * | 2002-07-10 | 2004-09-21 | The Boeing Company | Gregorian antenna system for shaped beam and multiple frequency use |
Family Cites Families (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2648278A1 (en) * | 1989-06-13 | 1990-12-14 | Europ Agence Spatiale | Antenna with switchable beams |
US6859188B1 (en) * | 2003-03-27 | 2005-02-22 | Lockheed Martin Corporation | Rotationally configurable offset reflector antenna |
-
2009
- 2009-06-19 FR FR0902995A patent/FR2947104B1/en active Active
-
2010
- 2010-05-28 EP EP10164352.6A patent/EP2264830B1/en active Active
- 2010-05-28 ES ES10164352T patent/ES2699484T3/en active Active
- 2010-06-14 CA CA2706761A patent/CA2706761C/en active Active
- 2010-06-21 US US12/820,013 patent/US8384610B2/en active Active
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
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 |
US6795034B2 (en) * | 2002-07-10 | 2004-09-21 | The Boeing Company | Gregorian antenna system for shaped beam and multiple frequency use |
Also Published As
Publication number | Publication date |
---|---|
FR2947104B1 (en) | 2011-07-29 |
FR2947104A1 (en) | 2010-12-24 |
CA2706761A1 (en) | 2010-12-19 |
ES2699484T3 (en) | 2019-02-11 |
CA2706761C (en) | 2016-08-02 |
US20100321266A1 (en) | 2010-12-23 |
EP2264830A1 (en) | 2010-12-22 |
US8384610B2 (en) | 2013-02-26 |
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