EP0044241B1 - Réflecteur d'antenne déployable - Google Patents

Réflecteur d'antenne déployable Download PDF

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Publication number
EP0044241B1
EP0044241B1 EP81401041A EP81401041A EP0044241B1 EP 0044241 B1 EP0044241 B1 EP 0044241B1 EP 81401041 A EP81401041 A EP 81401041A EP 81401041 A EP81401041 A EP 81401041A EP 0044241 B1 EP0044241 B1 EP 0044241B1
Authority
EP
European Patent Office
Prior art keywords
reflector
axis
frame elements
arms
dish
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
Application number
EP81401041A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0044241A1 (fr
Inventor
Gilles Labruyere
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.)
Aerospatiale Nationale Industrielle Te Par Ste
Original Assignee
Airbus Group SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
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First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=9244131&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=EP0044241(B1) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by Airbus Group SAS filed Critical Airbus Group SAS
Publication of EP0044241A1 publication Critical patent/EP0044241A1/fr
Application granted granted Critical
Publication of EP0044241B1 publication Critical patent/EP0044241B1/fr
Expired legal-status Critical Current

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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
    • H01Q15/161—Collapsible reflectors
    • 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
    • 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
    • H01Q15/147—Reflecting surfaces; Equivalent structures provided with means for controlling or monitoring the shape of the reflecting surface

Definitions

  • the present invention relates to an antenna reflector, in particular of large dimensions, for example intended to equip a telecommunication or direct television satellite.
  • an antenna reflector comprising an electrically conductive flexible cap made of a wire mesh.
  • Most of the embodiments described therein comprise a rigid structure supporting said cap and tensioning members, for example cables, between the cap and the structure.
  • tensioning members for example cables
  • US-A-3,605,107 describes a deployable reflector, the structure of which comprises a plurality of articulated arms. This structure does not, however, allow precision shaping of the reflector, in the deployed position, satisfying the required tolerances.
  • US-A-2,763,002 describes a deployable reflector, the structure of which comprises a plurality of movable arms. This structure, however, only allows the deployment position of a flat reflector.
  • the present invention relates to an antenna reflector satisfying the constraints mentioned above and overcoming the drawbacks of known embodiments.
  • the antenna reflector comprising a flexible conductive cap and a rigid structure supporting said cap, is remarkable in that said structure consists, on the one hand, of a plurality of members converging towards the axis of the reflector and distributed around said axis, the ends of said members close to this axis being articulated about axes tangent to a circle orthogonal to said axis of the reflector, so as to be able to assume a folded position along said axis of the reflector and a deployed position transverse to the latter axis in the manner of the branches of an umbrella, and, on the other hand, of a plurality of arms, each of which is articulated at the end of a member remote from the axis of the reflector, so that, when said members are in the deployed position, said arms are angularly projecting from them so that said structure forms a sort of cradle, in the concavity of which is disposed said deployed flexible cap, and that, when said members are in the folded
  • a foldable and deployable antenna which does not require rotation drive means and avoids any floating of the deployed cap, but requires an actuation mechanism with a limited operating time.
  • tensioning members allowing the shape of the reflector to be adjusted. Indeed, the connection between the flexible cap and the structure can be achieved, on the one hand between the periphery of the cap and the free ends of said articulated arms and, on the other hand, by tensioning members arranged between the convex surface of the cap and said members.
  • the antenna reflector according to the invention has the advantage of having a rigid structure to which flexible caps of different diameters and curvatures can be adapted.
  • the same rigid structure can be used to obtain reflectors with different focal lengths, or else off-center and / or excited reflectors in offset.
  • Each frame can be in one piece or on the contrary be made up of several foldable and deployable sections.
  • the members are in one piece, they advantageously have a trapezoidal section so that, the diameter of the circle to which their articulation axes are tangent being chosen accordingly, they can, in the folded position, come into contact with each other another, so that said bundle has a closed outer surface, at least substantially cylindrical. It is then advantageous that said arms also have a trapezoidal section so that, in the folded position, they form an at least substantially cylindrical block, determining the internal diameter of said beam.
  • the members and the arms form a closed enclosure for the folded cap, which is thus protected.
  • a satellite fitted with at least one reflector according to the invention in the folded state, can be mounted inside the cover of its launcher. After putting said satellite into orbit, it is then necessary to deploy said reflector.
  • any known drive means can be provided (spring, electric screw jack, pneumatic jack, etc.) controlling the opening of the structure by means, for example, of a system of links. Whatever the drive means chosen, it can actuate a movable member sliding along the axis of said reflector and to which all of said links are connected. Thus, the opening of the members is simultaneous.
  • the reflector according to the invention to connect the reflector according to the invention to the satellite or to an articulated arm on the satellite, it is advantageous to provide a hollow base, coaxial with the axis of the reflector, on which said members are articulated, and with the inside of which is located at least partially housed the opening mechanism of the reflector.
  • opening conjugation means are provided, such as cables and rollers connecting each frame and its associated arm, so that, when the actuation mechanism causes said frames to pass from their folded position to their deployed position, said arms pass automatically and gradually from their folded position along the inner side of the members to their angularly projecting position.
  • stop systems are provided between these elements.
  • FIGs 1 and 2 there is shown an artificial satellite 1 equipped with a small reflector 2 of fixed size and a deployable reflector 3 according to the invention, of large dimensions.
  • the satellite 1 is placed inside the cover 4 of a launcher and the reflectors 2 and 3 are then folded against the body of the satellite.
  • the folded position of the reflector 2 is not indicated, while that of the reflector 3, shown in dotted lines, bears the reference 3 '.
  • the reflectors 2 and 3 When the satellite is in its orbit (configuration illustrated in Figures 1 and 2), the reflectors 2 and 3 are unfolded and occupy the positions indicated in solid lines. It will be noted that for this purpose the reflector 2 is simply rotated about a hinge axis 5 connecting it to the body of the satellite, while the reflector 3, in addition to a rotation of its support arm 6 around an axis 7 allowing its separation from the satellite body 1, undergoes a deployment and a rotation about an axis 8 connecting it to said support arm 6.
  • the deployable reflector according to the invention has a structure preferably of revolution around its axis XX and comprises a massive base 9, fixed to the end of the arm 6 and on which are articulated , around axes 10, a plurality of radial members 11. At the end of members 11 opposite axes 10 are articulated, around axes 12 orthogonal to members 11, arms 13 capable of pivoting between a position for which they are folded between said grooves and a position for which they are transverse thereto (see FIG. 5) this latter position being determined for the cooperation of a stop 14 integral with said arms with the end of said members.
  • a flexible reflecting cap 15 is made integral, (directly or via tension links), by its periphery, with the free ends of the arms 13, while tension wires 16 are provided between the convex face of the cap 15 and the members 11.
  • a reversible actuation mechanism 17 makes it possible to control the deployment of the members 11 and of the arms 13.
  • the reflective caic " * ' must be a good conductor of electricity, flexible, dimensionally stable, light, resistant and have a low coefficient of expansion. It can be produced for example in the form of a fabric or a knitted fabric whose weaving or knitting characteristics give flexibility and whose constituent materials determine the stability, thermal expansion and conductivity.
  • the materials used for the production of this fabric or knitted fabric can be either metallic (molybdenum, chro - mel R, ...) is synthetic and coated in a known manner with a metallization (such as for example a polyester wire metallized with gold).
  • the weaving or knitting yarn advantageously consists of a plurality of strands (up to 300) and it can be twisted to reduce its bending stiffness, its diameter is preferably very small (of the order of 50 ⁇ ) and the mesh diameter is compatible with the wavelength used.
  • a golden molybdenum wire having a diameter of 50 g and consisting of 3 twisted strands, is used to make the cap 15. This yarn is knitted in garter stitch, the stitches having a diameter of 0.7 mm.
  • Said cap can also be made of a flexible, homogeneous and isotropic material metallized on the surface or internally by inclusion of conductive pulverulent charges.
  • said cap may include in its central part a rigid dome of small diameter ensuring the continuity of the reflective profile and made integral with the base 9.
  • the members 11 are rectilinear beams with closed section. They can be made of carbon fibers and have a trapezoidal section to present a minimum bulk in the folded position (see FIGS. 5 and 6), and maximum inertias of bending and torsion. Thus, in this position, the beams 11 can form a faceted tube 18, the interior cavity 25 of which, determined by the cylinder 26 formed by the arms 13 folded, encloses the cap 15 (not shown in FIG. 5).
  • the arms 13 are produced in a similar manner to the members 11. Preferably, the deployments of the arms 13 are combined with those of the members. Such a combination of movements can be obtained by means of a cable system 27 and pulleys 28, said cable being anchored on the base 9.
  • Means for returning the arms 13 to the members 11 can be constituted by leaf springs, not shown in FIG. 3. Another means for returning the arms 13 to the members 11 can be obtained by doubling the cables 27 with cables of substantially equal length but along an opposite path relative to the joints 10 and 12 ( Figure 5).
  • the reflective surface of the cap 15 is shaped in accordance with the theoretical profile of the reflector by adjusting the length of the tensioning wires 16.
  • the wires 16 are stretched between points distributed judiciously, and for example uniformly, on the cap 15 and points distributed on the members 11, the structure 11, 13 being considered to be very rigid in front of the fabric of the cap 15.
  • each member 11 occupies a position substantially parallel to the axis X-X and the corresponding arm 13 is folded against the face of said member facing this axis (see FIGS. 5 and 6).
  • all of the members 11 form a quasi-cylindrical and tubular bundle 18, the internal diameter of which is determined by the arms 13 which are in contact with each other.
  • the flexible cap 15 is then enclosed in the interior space 25 of the bundle 18, delimited by the members 11 and the arms 13.
  • the actuation mechanism 17 acts by moving a movable member such as 23 along the axis XX , the members 11 open in the manner of the branches of an umbrella under the action of the connecting rods 20 or 23 (see the right-hand part of FIG. 5), while the arms 13 gradually unfold by turning around the joints 10, under the action of the motion conjugation cables 27.
  • the members In the maximum open position, the members form a substantially planar star, the arms 13 are in the erection position and the cap 15 is stretched.
  • the members 11 and the arms 13 are in one piece, it goes without saying that they could consist of a plurality of deployable sections, which would further increase the surface of the reflector according to the invention, for less bulk in the folded state.
  • a light and deployable structure 11, 13 is produced, which can be considered to be practically non-deformable under limited variations in stresses (creep) and in temperature.
  • Such a structure allows the maintenance of a cap 15, the shape of which is independent of said structure and can be best adapted to the mission to be fulfilled, for example of parabolic shape of centered revolution, or off-center in the case of an antenna. with offset illumination.
  • the invention therefore makes it possible to produce identical structures, for caps of different shapes.

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  • Physics & Mathematics (AREA)
  • Engineering & Computer Science (AREA)
  • Astronomy & Astrophysics (AREA)
  • General Physics & Mathematics (AREA)
  • Remote Sensing (AREA)
  • Electromagnetism (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Aerials With Secondary Devices (AREA)
  • Details Of Aerials (AREA)
EP81401041A 1980-07-11 1981-06-29 Réflecteur d'antenne déployable Expired EP0044241B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8015527A FR2486722A1 (fr) 1980-07-11 1980-07-11 Reflecteur d'antenne deployable
FR8015527 1980-07-11

Publications (2)

Publication Number Publication Date
EP0044241A1 EP0044241A1 (fr) 1982-01-20
EP0044241B1 true EP0044241B1 (fr) 1984-11-14

Family

ID=9244131

Family Applications (1)

Application Number Title Priority Date Filing Date
EP81401041A Expired EP0044241B1 (fr) 1980-07-11 1981-06-29 Réflecteur d'antenne déployable

Country Status (6)

Country Link
US (1) US4352113A (OSRAM)
EP (1) EP0044241B1 (OSRAM)
JP (1) JPS5750103A (OSRAM)
CA (1) CA1167564A (OSRAM)
DE (1) DE3167179D1 (OSRAM)
FR (1) FR2486722A1 (OSRAM)

Families Citing this family (28)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3124907A1 (de) * 1981-06-25 1983-01-13 Messerschmitt-Bölkow-Blohm GmbH, 8000 München "entfaltbarer antennen-netzreflektor"
US4550319A (en) * 1982-09-22 1985-10-29 Rca Corporation Reflector antenna mounted in thermal distortion isolation
DE3423526A1 (de) * 1984-06-26 1986-01-02 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn Entfaltbarer und wiedereinfaltbarer antennenreflektor
US4771293A (en) * 1984-11-07 1988-09-13 The General Electric Company P.L.C. Dual reflector folding antenna
US4750002A (en) * 1986-09-12 1988-06-07 Harris Corporation Antenna panel having adjustable supports to improve surface accuracy
US4862190A (en) * 1987-05-15 1989-08-29 Trw Inc. Deployable offset dish structure
US4796033A (en) * 1987-06-18 1989-01-03 Hughes Aircraft Company Hub and rim reflector
JPS6458810A (en) * 1987-08-29 1989-03-06 Ii Matsukoneru Baanaado Ball joint coupling device
US4811033A (en) * 1987-11-10 1989-03-07 National Aeronautics And Space Administration Antenna surface contour control system
US4841305A (en) * 1988-02-01 1989-06-20 Dalsat, Inc. Method of sectioning an antennae reflector
US5061945A (en) * 1990-02-12 1991-10-29 Hull Harold L Portable satellite antenna system
KR920022699A (ko) * 1991-05-16 1992-12-19 김광호 지연 보상 회로
US5864324A (en) * 1996-05-15 1999-01-26 Trw Inc. Telescoping deployable antenna reflector and method of deployment
US6219009B1 (en) 1997-06-30 2001-04-17 Harris Corporation Tensioned cord/tie attachment of antenna reflector to inflatable radial truss support structure
US5963182A (en) * 1997-07-07 1999-10-05 Bassily; Samir F. Edge-supported umbrella reflector with low stowage profile
GB2330006A (en) * 1997-10-03 1999-04-07 Matra Marconi Space Uk Ltd Antenna reflector
US6876181B1 (en) * 1998-02-27 2005-04-05 Power Integrations, Inc. Off-line converter with digital control
US6618025B2 (en) 1999-06-11 2003-09-09 Harris Corporation Lightweight, compactly deployable support structure with telescoping members
US6313811B1 (en) 1999-06-11 2001-11-06 Harris Corporation Lightweight, compactly deployable support structure
US6531992B1 (en) * 2001-03-20 2003-03-11 Netune Communications, Inc. Back frame assembly
EP2738865B1 (en) 2010-12-15 2018-03-28 Planet Labs Inc. Integrated antenna system for imaging microsatellites
CN102765491B (zh) * 2012-08-03 2014-08-06 西安电子科技大学 空间绳系可展开面装置
US9214722B2 (en) 2013-05-15 2015-12-15 Georgia Tech Research Corporation Origami folded antennas
CN107248620B (zh) * 2017-04-22 2020-05-08 西安电子科技大学 一种自回弹多维可重构高参数星载可展开天线
US10811759B2 (en) 2018-11-13 2020-10-20 Eagle Technology, Llc Mesh antenna reflector with deployable perimeter
US11139549B2 (en) 2019-01-16 2021-10-05 Eagle Technology, Llc Compact storable extendible member reflector
JP7425432B2 (ja) * 2019-01-28 2024-01-31 国立研究開発法人宇宙航空研究開発機構 メッシュ構造体およびその製造方法、アンテナ反射鏡、電磁シールド材、導波管
US10797400B1 (en) 2019-03-14 2020-10-06 Eagle Technology, Llc High compaction ratio reflector antenna with offset optics

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3224007A (en) * 1961-01-31 1965-12-14 Clark A Mathis Wire mesh collapsible disk reflector
US3496687A (en) * 1967-03-22 1970-02-24 North American Rockwell Extensible structure
US3508270A (en) * 1967-01-04 1970-04-21 Bell Telephone Labor Inc Inflatable communications antenna satellite
US3521290A (en) * 1967-06-16 1970-07-21 Nasa Self-erecting reflector

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2763002A (en) * 1951-06-30 1956-09-11 Bendix Aviat Corp Collapsible antenna
US2945234A (en) * 1958-05-05 1960-07-12 Avco Mfg Corp Collapsible reflecting structure for electric waves
US3530469A (en) * 1968-06-26 1970-09-22 North American Rockwell Energy impingement device
US3717879A (en) * 1968-12-03 1973-02-20 Neotec Corp Collapsible reflector
US3605107A (en) * 1969-07-17 1971-09-14 Hughes Aircraft Co Lightweight reflecting structures utilizing magnetic deployment forces
US3631505A (en) * 1970-03-23 1971-12-28 Goodyear Aerospace Corp Expandable antenna

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3224007A (en) * 1961-01-31 1965-12-14 Clark A Mathis Wire mesh collapsible disk reflector
US3508270A (en) * 1967-01-04 1970-04-21 Bell Telephone Labor Inc Inflatable communications antenna satellite
US3496687A (en) * 1967-03-22 1970-02-24 North American Rockwell Extensible structure
US3521290A (en) * 1967-06-16 1970-07-21 Nasa Self-erecting reflector

Also Published As

Publication number Publication date
FR2486722B1 (OSRAM) 1984-07-20
DE3167179D1 (en) 1984-12-20
JPS5750103A (en) 1982-03-24
JPS6255723B2 (OSRAM) 1987-11-20
EP0044241A1 (fr) 1982-01-20
CA1167564A (fr) 1984-05-15
US4352113A (en) 1982-09-28
FR2486722A1 (fr) 1982-01-15

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