EP0032081B1 - Directable-beam antenna for communication satellite - Google Patents
Directable-beam antenna for communication satellite Download PDFInfo
- Publication number
- EP0032081B1 EP0032081B1 EP80401782A EP80401782A EP0032081B1 EP 0032081 B1 EP0032081 B1 EP 0032081B1 EP 80401782 A EP80401782 A EP 80401782A EP 80401782 A EP80401782 A EP 80401782A EP 0032081 B1 EP0032081 B1 EP 0032081B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- reflector
- axis
- primary source
- antenna
- waves
- 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
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Classifications
-
- 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
- H01Q19/19—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 comprising one main concave reflecting surface associated with an auxiliary reflecting surface
- H01Q19/195—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 comprising one main concave reflecting surface associated with an auxiliary reflecting surface wherein a reflecting surface acts also as a polarisation filter or a polarising device
-
- 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
Definitions
- the present invention relates to orientable beam antennas and more particularly those intended to be used in space vacuum, on board telecommunications satellites.
- These antennas include mechanisms involving rolling and sliding friction, the production of which, with the high degree of reliability required of the equipment on board the satellites, constitutes a difficult and expensive problem to solve.
- the object of the present invention is to obtain a widely orientable antenna from known mechanical components, designed and qualified for operation in a space environment, and used in limited numbers so as to achieve excellent reliability.
- an orientable beam antenna comprising a fixed primary source, a first reflector receiving the radiation emitted by the primary source with which it is mechanically integral, and a second orientable reflector, receiving the waves reflected by the first reflector, the second reflector being mechanically connected to a cardan device comprising two orthogonal axes of rotation, one of which is supported by a frame integral with the source and the first reflector, and the other orthogonal axis of which serves as a pivot axis for this second reflector, is characterized in that, this antenna being intended to be on board a terrestrial satellite to operate in space vacuum, the primary source is a source offset in off-set in a manner known per se with respect to the effective area of the second reflector so as not to intercept the waves reflected by the first reflector, the connection of the second reflector to the gimbal device is carried out in one side in an area located on its edge, and the other axis is near and parallel to a tangent of the second reflector passing through the points
- a primary source 1 of electromagnetic radiation having an axis of symmetry 20 is mechanically secured to a frame 8 also supporting an auxiliary reflector 2, the mechanical holding elements of which are not shown for clarity.
- This reflector is cut from a paraboloid of revolution with apex O (shown in FIG. 2 only) and with focal point F, the latter being contained in the plane of symmetry of the antenna and situated at the mouth of the source. 1.
- the axis 20, which cuts the reflector 2 at a point A, makes, with the straight line FO connecting the focal point F to the top O, an angle a (fig. 2) according to a conventional assembly called "off-set" in Anglo-Saxon literature.
- the frame 8 also supports an axis 7 through two ball bearing bearings 15 and 16.
- This axis 7 pivots (according to arrow 4) a cradle 5 itself supporting an axis 6, orthogonal to the axis 7, through two ball bearings 13 and 14.
- a main plane reflector 3 is movable around the axis 6. It is mechanically fixed, by its periphery, through two fixing lugs of which only one, 17, is visible in the figure, to the movable elements 11 and 9 constituting respectively the rotors of a motor and a resolver which rotate (according to arrow 18) around this axis 6 of which the stators are integral. Conversely, the rotors of a motor and of a resolver are integral with each end of the axis 7, there corresponds respectively the stators 10 and 12 integral with the frame 8.
- the auxiliary reflector 2 consists of parallel conducting wires, the diameter and the pitch of which are chosen so as to act as a polarization filter reflecting for the waves having the polarization of those emitted by the source 1, and transparent for those polarized orthogonally with respect to to the previous ones.
- the planar reflector 3 is made up of equidistant parallel wires of a design similar to those of the reflector 2 but so that the polarization of the reflected waves is then crossed.
- a ray emitted by the source 1 along the axis 20 is reflected at A by the reflector 2 if it has the correct polarization. It propagates along axis 21 to be reflected along axis 22 with a polarization perpendicular to the previous one allowing it to pass through the reflector 2 without significant attenuation.
- This axis 22 can take any direction among those possible in a conical portion of the space whose opening angles are respectively proportional to the years deflection plates 23 and 24 defined by the rotation of the corresponding axes 6 and 7.
- Such a structure comprises, for mobile connections, only commercial mechanical components, that is to say ball bearings designed and qualified for operation in a spatial environment, which avoids major studies of specific devices requiring substantial resources and whose performance does not always correspond to what is expected.
- ball bearings designed and qualified for operation in a spatial environment, which avoids major studies of specific devices requiring substantial resources and whose performance does not always correspond to what is expected.
- the structure described is only an example.
- the reflector 2 can be cut from a parabolic cylinder and associated with a linear source, that is to say wide in a parallel direction instead of the foci of this reflector.
- the movable reflector 3 is not necessarily planar but can be, for example, parabolic.
- the network of parallel wires can be replaced by grooves taiJlated in a solid form.
- the fixed reflector 2 Neither is it necessary for the fixed reflector 2 to act as a polarization filter and therefore for the movable reflector to cause a polarization crossing, insofar as the directions of the space where it is desired to radiate the antenna avoids the beam reflected by the movable reflector 3 from meeting the fixed reflector 2.
- the kinematic cardan system for two axes can be replaced by a rotation system of a single axis if the scanning limitation of the resulting space is eligible for operation.
- bearings can be of any other known type, plain bearings for example, insofar as they have the required quality.
Landscapes
- Variable-Direction Aerials And Aerial Arrays (AREA)
- Aerials With Secondary Devices (AREA)
Description
La présente invention concerne les antennes à faisceau orientable et plus particulièrement celles destinées à être utilisées dans le vide spatial, à bord de satellites de télécommunications.The present invention relates to orientable beam antennas and more particularly those intended to be used in space vacuum, on board telecommunications satellites.
Ces antennes comportent des mécanismes impliquant des frottements de roulement et de glissement dont la réalisation, avec le haut degré de fiabilité exigé des matériels embarqués dans les satellites, constitue un problème difficile et onéreux à résoudre.These antennas include mechanisms involving rolling and sliding friction, the production of which, with the high degree of reliability required of the equipment on board the satellites, constitutes a difficult and expensive problem to solve.
Dans le domaine des antennes terrestres, il est connu par exemple du brevet US 2 867 801 de réaliser des antennes à l'aide d'un dispositif fixe comportant une source primaire rayonnant sur un premier réflecteur, et d'un second réflecteur, mobile, recevant le rayonnement issu du premier. Mais, dans ce système le second réflecteur est mobile autour de deux axes orthogonaux passant par son centre, la source primaire étant placée au centre de ce réflecteur. Les réalisations actuelles d'antennes d'un type analogue embarquées, ne permettent pas d'obtenir plus de 10° de débattement total, alors qu'il est souhaitable d'obtenir des variations d'orientation du faisceau rayonné d'au moins ±30°, soit 60° de débattement.In the field of terrestrial antennas, it is known for example from US Pat. No. 2,867,801 to produce antennas using a fixed device comprising a primary source radiating on a first reflector, and a second, mobile reflector, receiving the radiation from the first. However, in this system the second reflector is movable around two orthogonal axes passing through its center, the primary source being placed at the center of this reflector. Current embodiments of antennas of an on-board analogous type do not make it possible to obtain more than 10 ° of total clearance, while it is desirable to obtain variations in orientation of the radiated beam of at least ± 30 °, or 60 ° of travel.
Par ailleurs, il est connu en soi, comme l'illustre à titre d'exemple le brevet US 3 916 416, d'utiliser dans certains types d'antennes une structure dite "off-set" dans laquelle la source est décalée par rapport à l'axe du réflecteur. Classiquement une telle structure est considérée comme inadaptée à l'obtention d'antennes embarquées orientables car la rotation d'un réflecteur décentré entraine des problèmes aérodynamiques et pneumatiques.Furthermore, it is known per se, as illustrated by way of example US Pat. No. 3,916,416, to use in certain types of antennas a structure called "off-set" in which the source is offset with respect to to the axis of the reflector. Conventionally, such a structure is considered unsuitable for obtaining orientable on-board antennas because the rotation of an off-center reflector causes aerodynamic and pneumatic problems.
La présente invention a pour but d'obtenir une antenne largement orientable à partir de composants mécaniques connus, conçus et qualifiés pour le fonctionnement en ambiance spatiale, et utilisés en nombre limité de manière à atteindre une excellente fiabilité.The object of the present invention is to obtain a widely orientable antenna from known mechanical components, designed and qualified for operation in a space environment, and used in limited numbers so as to achieve excellent reliability.
Selon l'invention, une antenne à faisceau orientable comportant une source primaire fixe, un premier réflecteur recevant le rayonnement émis par la source primaire dont il est mécaniquement solidaire, et un second réflecteur orientable, recevant les ondes réfléchies par le premier réflecteur, le second réflecteur étant mécaniquement relié à un dispositif à cardan comportant deux axes de rotation orthogonaux dont l'un est supporté par un bâti solidaire de la source et du premier réflecteur, et dont l'autre axe, orthogonal, sert d'axe de pivot à ce second réflecteur, est caractérisée en ce que, cette antenne étant destinée à être embarquée à bord d'un satellite terrestre pour fonctionner dans le vide spatial, la source primaire est une source décalée en off-set de manière connue en soi par rapport à la surface effective du second réflecteur pour ne pas intercepter les ondes réfléchies par le premier réflecteur, la liaison du second réflecteur au dispositif à cardan est réalisée d'un seul côté en une zone située sur son bord, et l'autre axe est près de et parallèle à une tangente du second réflecteur passant par les points de fixation du bord dudit réflecteur au dispositif à cardan.According to the invention, an orientable beam antenna comprising a fixed primary source, a first reflector receiving the radiation emitted by the primary source with which it is mechanically integral, and a second orientable reflector, receiving the waves reflected by the first reflector, the second reflector being mechanically connected to a cardan device comprising two orthogonal axes of rotation, one of which is supported by a frame integral with the source and the first reflector, and the other orthogonal axis of which serves as a pivot axis for this second reflector, is characterized in that, this antenna being intended to be on board a terrestrial satellite to operate in space vacuum, the primary source is a source offset in off-set in a manner known per se with respect to the effective area of the second reflector so as not to intercept the waves reflected by the first reflector, the connection of the second reflector to the gimbal device is carried out in one side in an area located on its edge, and the other axis is near and parallel to a tangent of the second reflector passing through the points of attachment of the edge of said reflector to the gimbal device.
L'invention sera mieux comprise et d'autres caractéristiques apparaîtront à l'aide de la description ci-après et des dessins s'y rapportant sur lesquels:
- - la fig. 1 est un exemple de réalisation d'antenne à faisceau orientable selon l'invention;
- - la fig. 2 est une coupe partielle de la fig. 1, menée dans le plan de symétrie de l'antenne.
- - fig. 1 is an exemplary embodiment of a steerable beam antenna according to the invention;
- - fig. 2 is a partial section of FIG. 1, carried out in the plane of symmetry of the antenna.
Sur la fig. 1, une source primaire 1 de rayonnement électromagnétique ayant un axe de symétrie 20 est mécaniquement solidaire d'un bâti 8 supportant également un réflecteur auxiliaire 2, dont les éléments mécaniques de maintien ne sont pas représentés pour plus de clarté. Ce réflecteur est découpé dans un paraboloïde de révolution de sommet O (représenté sur la seule fig. 2) et de foyer F, ce dernier étant contenu dans le plan de symétrie de l'antenne et situé au niveau de l'embouchure de la source 1. L'axe 20, qui coupe le réflecteur 2 en un point A, fait, avec la droite FO reliant le foyer F au sommet O, un angle a (fig. 2) selon un montage classique dit en "off-set" dans la littérature anglo-saxonne.In fig. 1, a primary source 1 of electromagnetic radiation having an axis of
Le bâti 8 supporte également un axe 7 à travers deux paliers à roulement à billes 15 et 16. Autour de cet axe 7 pivote (selon la flèche 4) un berceau 5 supportant lui-même un axe 6, orthogonal à l'axe 7, à travers deux paliers à roulement à billes 13 et 14.The
Un réflecteur principal plan 3 est mobile autour de l'axe 6. Il est fixé mécaniquement, par sa périphérie, à travers deux pattes de fixation dont une seule, 17, est visible sur la figure, aux éléments mobiles 11 et 9 constituant respectivement les rotors d'un moteur et d'un résolver qui tournent (selon la flèche 18) autour de cet axe 6 dont les stators sont solidaires. Inversement, les rotors d'un moteur et d'un résolver sont solidaires de chaque extrémité de l'axe 7, il y correspond respectivement les stators 10 et 12 solidaires du bâti 8.A
Le réflecteur auxiliaire 2 est constitué de fils conducteurs parallèles dont le diamètre et le pas sont choisis de manière à agir comme un filtre de polarisation réfléchissant pour les ondes ayant la polarisation de celles émises par la source 1, et transparent pour celles polarisées orthogonalement par rapport aux précédentes.The auxiliary reflector 2 consists of parallel conducting wires, the diameter and the pitch of which are chosen so as to act as a polarization filter reflecting for the waves having the polarization of those emitted by the source 1, and transparent for those polarized orthogonally with respect to to the previous ones.
Le réflecteur plan 3 est constitué de fils parallèles équidistants de conception analogue à ceux du réflecteur 2 mais de telle sorte que la polarisation des ondes réfléchies soit alors croisée. Ainsi un rayon émis par la source 1 selon l'axe 20 est réfléchi en A par le réflecteur 2 s'il présente la polarisation correcte. Il se propage selon l'axe 21 pour être réfléchi selon l'axe 22 avec une polarisation perpendiculaire à la précédente lui permettant de traverser sans atténuation notable le réflecteur 2. Cet axe 22 peut prendre une direction quelconque parmi celles possibles dans une portion conique de l'espace dont les angles d'ouverture sont respectivement proportionnels aux angles de débattement 23 et 24 définis par la rotation des axes correspondants 6 et 7.The
Une telle structure ne comporte, pour les liaisons mobiles, que des composants mécaniques du commerce, c'est-à-dire des roulements à billes conçus et qualifiés pour le fonctionnement en ambiance spatiale, ce qui évite les études importantes de dispositifs spécifiques nécessitant des moyens conséquents et dont les performances ne correspondent pas toujours à ce qu'on en attend. Bien entendu la structure décrite n'est qu'un exemple.Such a structure comprises, for mobile connections, only commercial mechanical components, that is to say ball bearings designed and qualified for operation in a spatial environment, which avoids major studies of specific devices requiring substantial resources and whose performance does not always correspond to what is expected. Of course the structure described is only an example.
Une autre forme peut être donnée au réflecteur 2, en particulier, il peut être découpé dans un cylindre parabolique et associé à une source linéaire, c'est-à-dire large dans une direction parallèle au lieu des foyers de ce réflecteur. Le réflecteur mobile 3 n'est pas nécessairement plan mais peut être, par exemple, parabolique. De même le réseau de fils parallèles peut être remplacé par des sillons taiJlés dans une forme pleine.Another shape can be given to the reflector 2, in particular, it can be cut from a parabolic cylinder and associated with a linear source, that is to say wide in a parallel direction instead of the foci of this reflector. The
Il n'est pas non plus nécessaire que le réflecteur fixe 2 joue le rôle de filtre de polarisation et donc que le réflecteur mobile provoque un croisement de polarisation, dans la mesure où les directions de l'espace où il est désiré de faire rayonner l'antenne permettent d'éviter au faisceau réfléchi par le réflecteur mobile 3 de rencontrer le réflecteur fixe 2. De même le système cinématique à cardan pour deux axes peut être remplacé par un système de rotation d'un simple axe si la limitation de balayage de l'espace qui en résulte est admissible pour l'exploitation.Neither is it necessary for the fixed reflector 2 to act as a polarization filter and therefore for the movable reflector to cause a polarization crossing, insofar as the directions of the space where it is desired to radiate the antenna avoids the beam reflected by the
Enfin les paliers peuvent être de tout autre type connu, des paliers lisses par exemple, dans la mesure où ils présentent la qualité requise.Finally, the bearings can be of any other known type, plain bearings for example, insofar as they have the required quality.
Claims (4)
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR7931803A FR2472853A1 (en) | 1979-12-27 | 1979-12-27 | ANTENNA WITH AN ADJUSTABLE BEAM AND SATELLITE COMPRISING SUCH ANTENNA |
| FR7931803 | 1979-12-27 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP0032081A1 EP0032081A1 (en) | 1981-07-15 |
| EP0032081B1 true EP0032081B1 (en) | 1986-10-08 |
Family
ID=9233208
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP80401782A Expired EP0032081B1 (en) | 1979-12-27 | 1980-12-12 | Directable-beam antenna for communication satellite |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US4408209A (en) |
| EP (1) | EP0032081B1 (en) |
| CA (1) | CA1169547A (en) |
| DE (1) | DE3071796D1 (en) |
| FR (1) | FR2472853A1 (en) |
Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2268834B (en) * | 1980-12-04 | 1994-06-22 | Racal Mesl Ltd | Radar arrangements and methods of detecting different types of targets |
| DE4112837A1 (en) * | 1991-04-19 | 1992-10-22 | Teldix Gmbh | Aerial reflector swivel mechanism - has reflector fitted at free end of jib arm, rotatably mounted by its opposite end between two spaced, lever arms |
| DE19544500C2 (en) * | 1994-12-15 | 1999-07-08 | Daimler Benz Aerospace Ag | Reflector antenna, in particular for a communication satellite |
| EP2137789B1 (en) * | 2007-03-16 | 2013-05-08 | Mobile SAT Ltd. | A vehicle mounted antenna and methods for transmitting and/or receiving signals |
| FR2989523B1 (en) * | 2012-04-13 | 2014-05-02 | Thales Sa | MULTI-REFLECTING ANTENNA FOR TELECOMMUNICATIONS SATELLITE |
| US10024954B1 (en) * | 2012-11-05 | 2018-07-17 | The United States Of America As Represented By The Secretary Of The Navy | Integrated axial choke rotary offset parabolic reflector |
| US9590299B2 (en) * | 2015-06-15 | 2017-03-07 | Northrop Grumman Systems Corporation | Integrated antenna and RF payload for low-cost inter-satellite links using super-elliptical antenna aperture with single axis gimbal |
| FR3054732B1 (en) * | 2016-07-26 | 2020-01-03 | Thales | POINTABLE MULTI-BEAM ANTENNA, TELECOMMUNICATION SATELLITE AND ASSTELLATION OF ASSOCIATED SATELLITES |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2867801A (en) * | 1953-09-14 | 1959-01-06 | Elliott Brothers London Ltd | High frequency radio aerials |
| GB905440A (en) * | 1957-12-18 | 1962-09-05 | Gen Electric Co Ltd | Improvements in or relating to position control arrangements and aerial systems including such arrangements |
| US3407404A (en) * | 1964-10-05 | 1968-10-22 | Bell Telephone Labor Inc | Directive microwave antenna capable of rotating about two intersecting axes |
| US3914768A (en) * | 1974-01-31 | 1975-10-21 | Bell Telephone Labor Inc | Multiple-beam Cassegrainian antenna |
| US3916416A (en) * | 1974-09-24 | 1975-10-28 | Us Navy | 360{20 {0 Azimuth scanning antenna without rotating RF joints |
| US4070678A (en) * | 1976-04-02 | 1978-01-24 | Raytheon Company | Wide angle scanning antenna assembly |
-
1979
- 1979-12-27 FR FR7931803A patent/FR2472853A1/en active Granted
-
1980
- 1980-12-12 EP EP80401782A patent/EP0032081B1/en not_active Expired
- 1980-12-12 DE DE8080401782T patent/DE3071796D1/en not_active Expired
- 1980-12-22 CA CA000367293A patent/CA1169547A/en not_active Expired
- 1980-12-23 US US06/220,156 patent/US4408209A/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| US4408209A (en) | 1983-10-04 |
| DE3071796D1 (en) | 1986-11-13 |
| FR2472853A1 (en) | 1981-07-03 |
| FR2472853B1 (en) | 1983-09-16 |
| CA1169547A (en) | 1984-06-19 |
| EP0032081A1 (en) | 1981-07-15 |
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