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EP2415117B1 - Funkantenne mit verbessertem versteifungsmittel - Google Patents

Funkantenne mit verbessertem versteifungsmittel Download PDF

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Publication number
EP2415117B1
EP2415117B1 EP10712444.8A EP10712444A EP2415117B1 EP 2415117 B1 EP2415117 B1 EP 2415117B1 EP 10712444 A EP10712444 A EP 10712444A EP 2415117 B1 EP2415117 B1 EP 2415117B1
Authority
EP
European Patent Office
Prior art keywords
reflector
membrane
antenna
radio antenna
radio
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.)
Not-in-force
Application number
EP10712444.8A
Other languages
English (en)
French (fr)
Other versions
EP2415117A1 (de
Inventor
Christian Desagulier
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Defence and Space SAS
Original Assignee
Airbus Defence and Space SAS
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Filing date
Publication date
Application filed by Airbus Defence and Space SAS filed Critical Airbus Defence and Space SAS
Publication of EP2415117A1 publication Critical patent/EP2415117A1/de
Application granted granted Critical
Publication of EP2415117B1 publication Critical patent/EP2415117B1/de
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • 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
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/27—Adaptation for use in or on movable bodies
    • H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
    • H01Q1/288—Satellite antennas
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • 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
    • H01Q19/12—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 wherein the surfaces are concave

Definitions

  • the present invention relates to the field of radio antennas with reflectors, and relates in particular to an antenna for a spacecraft, such as a telecommunications satellite.
  • Spacecraft antennas must comply with specifications concerning, in particular, the reflectivity of their reflectors, but also the mechanical strength of the means for connecting reflectors to spacecraft, which are subjected to the acoustic and dynamic vibratory stresses induced by space launchers. These antennas must also comply with specifications concerning their thermoelastic behavior in orbit.
  • FIGs 1 and 1a represent an example of a radio antenna 10 ( figure 1 ) for telecommunications satellites operating at frequencies between about 12 GHz and 18 GHz (Ku-band), of a known type.
  • the reflector 12 of the antenna 10 comprises a shell 14 of the sandwich type formed of a honeycomb structure on which are affixed a front skin - commonly called active skin - and a rear skin, each of these skins consisting of a fold of carbon fibers embedded in an epoxy resin.
  • the reflector 12 of the antenna 10 is supported by a rigid tubular rear structure 16, which is for example of hexagonal shape, centered on an axis of the reflector, and of smaller extent than the extent of the reflector.
  • the rear structure 16 is connected to the rear skin of the reflector 12 by angles 18 ( figure 1a ) capable of ensuring the mechanical strength of the antenna during launching and putting into orbit of the satellite equipped with this antenna, and a thermomechanical decoupling between the reflector 12 and the rear structure 16 when the satellite is in orbit. Furthermore, the rear structure 16 is carried by a support arm 19 intended to provide the connection between the antenna 10 and the satellite.
  • the carbon fibers of the folds of the above-mentioned front and rear skins are arranged in the form of triaxial fabrics which are characterized by quasi-isotropic mechanical properties and by the presence of through openings which are regularly distributed over their surface.
  • the composite materials used in these antennas give them a great lightness, which is an essential advantage in the field of space applications.
  • the reflectivity properties of the reflectors of the type described above are not satisfactory at frequencies between about 20 GHz and 40 GHz (Ka-band), due to the perforation of these reflectors.
  • Solutions have been proposed, which consist, from an antenna of the type described above, to reduce the size of the openings of the active skin, or even to replace the active skin openwork with a full skin, but the antennas and obtained proved to be too sensitive to acoustic demands.
  • the tolerances relating to the reflector profiles are stricter, which leads to more stringent requirements in terms of manufacturing accuracy and stability over time of the reflectors, typically of the order of 30 ⁇ m RMS, compared to 150 ⁇ m RMS for satellites operating at lower frequencies of the Ku band.
  • the sandwich structures of the antenna reflectors of the type described above do not make it possible to easily satisfy the levels of requirement required by operation in the Ka band.
  • the invention aims in particular to provide a simple, economical and effective solution to these problems, to avoid the aforementioned drawbacks.
  • It relates in particular to a radio antenna for spacecraft, able to operate at frequencies of the Ka band, and satisfying the requirements imposed on this type of antenna, in particular with regard to the sensitivity of the antenna to the vibratory stresses induced by the launchers, the accuracy of manufacture of the profile of the antenna reflector and the stability of this profile over time, and in general the thermomechanical behavior of the antenna in orbit.
  • the invention proposes for this purpose a radio antenna, in particular for spacecraft, comprising a reflector and a rear support structure of said reflector, characterized in that the antenna comprises a stiffening membrane attached to the reflector to limit the deflection a peripheral portion of the reflector in a direction parallel to a central axis of the reflector, the stiffening membrane being distinct from the rear support structure.
  • the stiffening membrane makes it possible to reduce the impact of vibrational stresses, in particular acoustic stresses, on the rear support structure of the antenna reflector. This makes it possible in particular to use a full active skin, that is to say not open skin, so as to provide the reflector with optimal reflectivity properties and also to improve the accuracy and stability of the profile of this reflector.
  • the reflector having an active face and a rear face the stiffening membrane preferably comprises a central portion disposed facing the active face of the reflector.
  • the antenna advantageously comprises means for fixing said stiffening membrane on the peripheral portion of the reflector.
  • These fixing means may be configured for fixing the membrane on the active face of the reflector, or for fixing a folded peripheral edge of this membrane on the rear face of the reflector.
  • the membrane thus makes it possible to limit any deformation of the peripheral portion of the reflector directed towards the front of the latter.
  • the stiffening membrane may comprise a peripheral portion folded over a peripheral edge of the reflector and arranged facing the rear face of the reflector so as to be secured to the rear support structure.
  • This configuration allows a contact of the membrane with the active and rear faces of the reflector, at the peripheral edge of the latter, so that the membrane then makes it possible to limit any deformation of the peripheral portion of the reflector directed towards the front or towards the rear of the reflector.
  • the antenna may advantageously comprise rods fixed on the one hand to said rear support structure and on the other hand to the peripheral portion of the reflector, said folded peripheral portion of the stiffening membrane then being fixed on these rods.
  • the stiffening membrane is preferably stretched so as to ensure optimum stiffening of the reflector.
  • the membrane is preferably solid, that is to say without openings. This allows this membrane to dampen any acoustic vibrations in a particularly efficient manner.
  • the antenna is advantageously configured to operate in a predetermined frequency band of the microwave spectrum, this frequency band being able to be in particular included in the Ka band.
  • the stiffening membrane is preferably made of a material transparent to radio waves whose frequency is in said frequency band.
  • said material is a composite material comprising fibers embedded in a cured resin.
  • This type of material has the advantage of great lightness and good mechanical strength.
  • this type of material makes it possible to achieve the rigidification membrane in one piece with the active face of the shell, when the latter itself is made of a similar composite material.
  • the abovementioned fibers are advantageously aramid fibers, of the Kevlar (registered trademark) type, for example, or quartz fibers, the resin in which these fibers are embedded being, for example, an epoxy resin.
  • the stiffening membrane may be made of a material that is not transparent to said radio waves when the arrangement of this membrane is such that the latter does not risk making the reflectivity properties of the antenna insufficient.
  • the stiffening membrane according to the invention has the advantage of being particularly simple to manufacture.
  • the Figures 2 and 3 represent a radio antenna 20 according to a preferred embodiment of the invention.
  • the antenna 20 comprises a reflector 22 and a rear structure 24 for supporting this reflector 22.
  • the reflector 22 comprises a shell 26 of generally paraboloidal shape, of axis 28, formed of a sandwich structure comprising a core honeycomb on which are affixed two skins, respectively front and rear, formed of carbon fibers embedded in a cured epoxy resin and arranged in the form of a unidirectional sheet.
  • the skin and the front face of the reflector are commonly called respectively skin and face active, so that the terms "before” and "active" are equivalent in this text.
  • the rear support structure 24 is similar to the rear structure 16 of the known type of antenna shown in FIG. figure 1 .
  • This structure 24 comprises a hexagonal tubular portion 30 which extends in a plane perpendicular to the axis 28 of the reflector and is centered on this axis 28, and an arm (not visible on the figure 2 ) for connecting the tubular portion 30 to a spacecraft, such as a satellite.
  • the tubular portion 30 of the rear support structure 24 comprises brackets 32 for connecting the shell 26 of the reflector 22 to the rear structure 24.
  • the brackets 32 each comprise a strip 34 which extends substantially parallel to the axis 28 of the reflector 22, and which is fixedly connected, at its front end, to a fastening tab 36 affixed to the rear skin of the shell 26 of the reflector, and at its rear end, to the tubular portion 30 of the rear support structure 24.
  • the lamellae 34 of the brackets 32 allow a thermomechanical decoupling between the reflector 22 and the rear support structure 24.
  • the rear structure 24 has a smaller radial extent than the reflector 22, so that the arrangement of the brackets 36 of the brackets 32 on the shell 26 of this reflector internally delimits a peripheral portion 38 of the reflector 22. This peripheral portion 38 extends to the outer edge 39 of the reflector.
  • the reflector 22 comprises a stiffening membrane 48 having a flat central portion stretched facing the active face of the reflector 22 and a peripheral portion 50 which is folded over the outer edge 39 of the reflector and which extends opposite the face back of the latter.
  • the stiffening membrane 48 is intended to limit the deflection of the peripheral portion 38 of the reflector along its axis 28 when the reflector is subjected to vibratory stresses.
  • peripheral portion 50 of the membrane is intended for fixing the membrane 48 to the rear support structure 24.
  • the antenna 52 comprises connecting rods 54 arranged so that one end of each of these rods 54 is fixed to the tubular portion 30 of the support structure 24 and the other end of each rod 54 is fixed on the rear face of the reflector 22, at the outer edge 39 of the latter.
  • These connecting rods 54 are regularly distributed around the axis 28 of the reflector.
  • the peripheral portion 50 of the stiffening membrane 48 is fixed on the connecting rods 54, for example by gluing, so that the membrane is stretched in its central portion 49.
  • stiffening membrane 48 effectively opposes the deflection of the peripheral portion 38 of the reflector parallel to the axis 28 of the reflector.
  • the stiffening membrane 48 is made of a composite material transparent to radio waves. This material is for example composed of a fabric of aramid fibers embedded in a cured epoxy resin, in such a way that the membrane 48 is solid, that is to say not perforated.
  • the stiffening membrane 48 thus makes it possible to damp at least partially the acoustic vibrations that can propagate towards the active face of the reflector.
  • the membrane 48 may however be formed of a perforated fabric, for example of the bidirectional or triaxial type.
  • stiffening membrane 48 may not be folded towards the rear of the reflector 22 and be fixed on the active face of the reflector at the peripheral portion 38 of the latter.
  • stiffening membrane 48 may be made of another material, such as for example a composite material with quartz fibers or the like embedded in any type of suitable resin.
  • the material of this stiffening membrane 48 is preferably chosen to have a thermoelastic coefficient close to that of the material forming the shell of the reflector, in order to optimize the thermomechanical behavior of the antenna.
  • the shell 26 of the reflector 22 may furthermore, without departing from the scope of the invention, have a shape different from that described above such as for example a globally flat bumpy shape.
  • the stiffening membrane 48 may also be in contact with the active face of the reflector.

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  • Physics & Mathematics (AREA)
  • Engineering & Computer Science (AREA)
  • Astronomy & Astrophysics (AREA)
  • General Physics & Mathematics (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Electromagnetism (AREA)
  • Aerials With Secondary Devices (AREA)
  • Details Of Aerials (AREA)

Claims (9)

  1. Funkantenne (20, 52), insbesondere für ein Raumfahrzeug, umfassend einen Reflektor (22) und eine hintere Haltestruktur (24) des Reflektors, dadurch gekennzeichnet, dass die Antenne (20, 52) eine Versteifungsmembran (48) aufweist, die an dem Reflektor (22) so angebracht ist, dass der Federungsweg eines Randbereichs (38) des Reflektors in einer Richtung, die parallel zu einer zentralen Achse (28) dieses Reflektors (22) verläuft, beschränkt wird, wobei diese Versteifungsmembran (48) sich von der hinteren Haltestruktur (24) unterscheidet.
  2. Funkantenne (20, 52) nach Anspruch 1, dadurch gekennzeichnet, dass der Reflektor (22) eine aktive Seite und eine Rückseite aufweist und die Versteifungsmembran (48) einen mittleren Teil umfasst, der gegenüber der aktiven Seite des Reflektors (22) angeordnet ist.
  3. Funkantenne (52) nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass die Antenne Mittel zur Befestigung der Membran (48) am Randbereich (38) des Reflektors (22) aufweist.
  4. Funkantenne (52) nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass die Membran (48) einen Umfangsbereich (50) aufweist, der um eine periphere Kante des Reflektors (22) zurückgebogen ist und der gegenüber der Rückseite dieses Reflektors angeordnet ist, so dass er mit der hinteren Haltestruktur (24) fest verbunden ist.
  5. Funkantenne (52) nach Anspruch 4, dadurch gekennzeichnet, dass die Antenne Stäbe (54) aufweist, die einerseits an der hinteren Haltestruktur (24) und andererseits an dem Randbereich (38) des Reflektors befestigt sind und an denen der Umfangsbereich (50) der Membran (48) befestigt ist.
  6. Funkantenne nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass die Antenne (20, 52) konfiguriert ist, um in einem vorgegebenen Frequenzband des Spektrums der Mikrowellen zu funktionieren.
  7. Funkantenne nach Anspruch 6, dadurch gekennzeichnet, dass das Frequenzband in dem Ka-Band enthalten ist.
  8. Funkantenne nach Anspruch 6 oder 7, dadurch gekennzeichnet, dass die Versteifungsmembran aus einem transparenten Material mit Funkwellen ausgeführt ist, deren Frequenz in dem Frequenzband enthalten ist.
  9. Funkantenne nach Anspruch 8, dadurch gekennzeichnet, dass das Material ein Verbundmaterial ist, das Fasern aufweist, die in einem gehärteten Harz gebettet sind.
EP10712444.8A 2009-04-02 2010-04-02 Funkantenne mit verbessertem versteifungsmittel Not-in-force EP2415117B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0952150A FR2944154B1 (fr) 2009-04-02 2009-04-02 Antenne radioelectrique comportant des moyens de rigidification ameliores
PCT/EP2010/054456 WO2010112600A1 (fr) 2009-04-02 2010-04-02 Antenne radioelectrique comportant des moyens de rigidification améliorés

Publications (2)

Publication Number Publication Date
EP2415117A1 EP2415117A1 (de) 2012-02-08
EP2415117B1 true EP2415117B1 (de) 2014-11-12

Family

ID=41181089

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10712444.8A Not-in-force EP2415117B1 (de) 2009-04-02 2010-04-02 Funkantenne mit verbessertem versteifungsmittel

Country Status (5)

Country Link
US (1) US20120019430A1 (de)
EP (1) EP2415117B1 (de)
ES (1) ES2530570T3 (de)
FR (1) FR2944154B1 (de)
WO (1) WO2010112600A1 (de)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2993414B1 (fr) * 2012-07-13 2014-08-22 Thales Sa Reflecteur d'antenne de telecommunication pour application a hautes frequences dans un environnement spatial geostationnaire
US11658385B2 (en) 2018-12-20 2023-05-23 Tendeg Llc Antenna system with deployable and adjustable reflector
CA3124214A1 (en) 2018-12-20 2020-06-25 Tendeg Llc Antenna system
US11239567B2 (en) * 2019-05-08 2022-02-01 Tendeg Llc Antenna

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB412966A (en) * 1932-02-08 1934-07-06 Lorenz C Ag Improvements in or relating to reflector structures for use in radio signalling systems
FR1029235A (fr) * 1950-12-07 1953-06-01 Radio Electr Soc Fr Perfectionnements à la suspension des réflecteurs de rayonnement ultra-cou orientables
US3351947A (en) * 1965-02-17 1967-11-07 Mark Products Company Shrouded parabolic antenna structure
US3397399A (en) * 1966-02-07 1968-08-13 Goodyear Aerospace Corp Collapsible dish reflector
US3707720A (en) * 1970-10-02 1972-12-26 Westinghouse Electric Corp Erectable space antenna
US4171876A (en) * 1977-10-17 1979-10-23 Wood Douglas E Apparatus for supporting large-dimension curved reflectors
US4281900A (en) * 1979-10-31 1981-08-04 Ford Aerospace & Communications Corp. Frontal reflector bracing
US4585317A (en) * 1981-11-05 1986-04-29 Marvin Hodges Reflector with attenuating connecting plates
US4918459A (en) * 1989-02-27 1990-04-17 Teso John S De Apparatus for protecting antennas
US5451972A (en) * 1994-05-12 1995-09-19 Paul Dean Franklin Satellite antenna dish cover
DE29914904U1 (de) * 1999-08-25 1999-12-30 Michel, Oliver, 41564 Kaarst Satellitenempfänger und Vorrichtung zum Abdecken eines Satellitenempfängers
GB2435547B (en) * 2006-02-23 2009-09-23 Wen-Chao Shen Satellite dish antenna assembly

Also Published As

Publication number Publication date
EP2415117A1 (de) 2012-02-08
FR2944154A1 (fr) 2010-10-08
ES2530570T3 (es) 2015-03-03
US20120019430A1 (en) 2012-01-26
FR2944154B1 (fr) 2016-05-06
WO2010112600A1 (fr) 2010-10-07

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