EP3269009B1 - Réflecteur d'antenne, en particulier pour engin spatial - Google Patents

Réflecteur d'antenne, en particulier pour engin spatial Download PDF

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Publication number
EP3269009B1
EP3269009B1 EP16713510.2A EP16713510A EP3269009B1 EP 3269009 B1 EP3269009 B1 EP 3269009B1 EP 16713510 A EP16713510 A EP 16713510A EP 3269009 B1 EP3269009 B1 EP 3269009B1
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EP
European Patent Office
Prior art keywords
shell
rear structure
antenna reflector
reflector according
circular
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.)
Active
Application number
EP16713510.2A
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German (de)
English (en)
French (fr)
Other versions
EP3269009A1 (fr
Inventor
Audrey-Marine LOUIS
Régis RAULT
Frédéric VEILLERAUD
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.)
ArianeGroup SAS
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ArianeGroup SAS
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Publication of EP3269009A1 publication Critical patent/EP3269009A1/fr
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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
    • H01Q19/102—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 of convex toroïdal shape

Definitions

  • the present invention relates to an antenna reflector, in particular for an antenna of a spacecraft and in particular of a satellite.
  • the present invention applies more particularly to a telecommunications satellite antenna reflector, in particular of a large antenna.
  • a satellite antenna reflector for example, is a part of an antenna, which makes it possible to reflect and form the electromagnetic wave exchanged between the satellite and the Earth.
  • the documents EP0741435 , JP2007274563 and WO2010 / 112601 describe the state of the art.
  • an antenna reflector comprises a rigid structure (shell) provided with a reflecting surface, reflecting electromagnetic waves (radiofrequency), and a reinforcement system provided with a so-called rear structure, which maintains the shell and ensures the connection of the hull to the satellite.
  • the shell is secured to the rear structure by a set of flexible fixing elements.
  • the rear structure of a reflector generally comprises an assembly of rectilinear tubes, linked together forming angles.
  • This rear structure has a general shape representing a polygon, for example a rectangle, or an assembly of polygons.
  • the shells generally have a circular contour, or one derived from a circle (such as a truncated circle), in order to optimize the radiofrequency performance of the antenna.
  • the polygonal structure is placed in a plane above the hull, and does not allow it to match the overall parabolic shape of the reflector.
  • the reflector is, geometrically, not very compact.
  • the length of the fasteners between the shell and the rear structure varies depending on their position along the rear structure.
  • the hull edge (or free edge) lengths there is an optimal length for the fasteners.
  • a fastening element that is too long is more sensitive to buckling and reduces the mechanical strength of the fastening element (and of the reflector), and a fastening element that is too short does not allow sufficient flexibility to be left between the structure. rear and hull.
  • a fastening element that is too short induces losses in mechanical performance in the holding of the junction at the foot of the fastening element.
  • the use of a polygonal structure induces variations in the lengths of the fixing elements, and therefore at least part of the fixing elements has a non-optimal length.
  • the preferred positioning for a fastening element is to arrange it radially with respect to the hull.
  • the fasteners are not everywhere arranged radially, or it is necessary to add corner shims between the fasteners and the rear structure to ensure a radial position, which increases the reflector mass.
  • a usual antenna reflector structure comprising a shell and a rear structure (of a reinforcement system) of polygonal type, as mentioned above, is therefore not optimal.
  • the object of the present invention is to remedy at least some of the aforementioned drawbacks.
  • the invention is defined in the appended claims. It relates to an antenna reflector, in particular for a spacecraft and in particular for a satellite, said antenna reflector comprising a shell provided with a first surface which is reflective, and a reinforcement system which is arranged on a second surface of the shell, opposite to said first surface, and which comprises a so-called rear structure.
  • said rear structure comprises at least one part of the structure having a general shape that is at least partially circular.
  • the rear structure is not of the usual completely polygonal type, and comprises at least one part of the structure which is circular.
  • the use of such a part of a circular structure has many advantages making it possible to remedy at least some of the aforementioned drawbacks, as specified below.
  • said at least part of the structure of said rear structure has a generally completely circular shape.
  • said rear structure comprises a plurality of structural parts of general (completely) circular shapes, and of different diameters.
  • said shell has a paraboloidal structure with or without local shaping, and said at least part of the structure of said rear structure is arranged on the second surface of the shell so as to be held in place. a set of fixing elements (to all the fixing elements of this set), at a substantially constant distance from said second surface, preferably corresponding to an optimum distance.
  • said at least one structural part of said rear structure has a generally mixed shape comprising at least one polygonal part and at least one circular part.
  • said general mixed shape is a truncated circular shape.
  • the present invention also relates to a spacecraft, in particular a satellite, which comprises at least one antenna reflector as mentioned above.
  • the figures 1 and 2 are schematic views, respectively in section and in plan, of an antenna reflector illustrating the invention.
  • the figure 3 is a schematic plan view of a particular embodiment of an antenna reflector provided with a rear structure comprising several concentric structural parts.
  • the figure 4 is a schematic plan view of a particular embodiment of an antenna reflector having a truncated circular shape.
  • the antenna reflector 1 (hereinafter “reflector 1”) illustrating the invention and shown schematically on the figure 1 is a reflector of an antenna, in particular for an antenna of a spacecraft and in particular of a satellite. Although not exclusively, this reflector 1 can be a reflector of an antenna of a telecommunications satellite, in particular of a large antenna, for example with a diameter of the order of two to five meters.
  • Such an antenna reflector must meet very strict specifications and present, in particular, good mechanical resistance to the atmospheres existing when the satellite is launched, surface precision, surface stability during extreme temperature variations such as 'they exist in orbit, good mechanical strength over a wide temperature range, great lightness, and high stiffness.
  • the shell 2 of the reflector 1 comprises a composite sandwich structure comprising a honeycomb core, which is transparent to electromagnetic (radioelectric) waves, and on which are affixed a front skin. and a back skin.
  • Each of the skins includes one or more plies of composite material with, for example, carbon fibers.
  • Each ply can be a one-way ply or a woven ply.
  • the material constituting the front skin (that is to say the reflective front surface 3) of the shell 2 must make it possible to guarantee a reflection of the electromagnetic waves.
  • a stack of composite material plies guarantees good mechanical performance and significant lightness.
  • the shell can have a specific shape for each reflector considered.
  • the rear structure 6 of the reflector 1 comprises at least one part of the structure 7A, 7B, 7C, 7D having a general shape at least partially circular.
  • the rear structure 6 of the reflector 1, comprising at least one part of the structure 7A, 7B, 7C, 7D which is circular, is not of the usual completely polygonal type.
  • the use of such a part of circular structure 7A, 7B, 7C, 7D has many advantages specified below.
  • the rear structure 6 of the reflector 1 comprises a single part of the structure 7A, this part of the structure 7A having a generally completely circular shape.
  • This part of structure 7A is arranged concentrically with respect to the shell 2 which is of the parabolic type and therefore of circular shape in plan view, as shown in FIG. figure 2 .
  • the shell 2 thus has a paraboloidal structure, the center O of which has been shown (located on an axis XX) in particular on the figure 2 .
  • the structural part 7A of said rear structure 6 is arranged on the rear surface 5 of the shell 2 so as to be located, at all points, at a substantially constant distance from said rear surface 5.
  • the reflector 1 also comprises a plurality of fixing elements 8, specified below, which are arranged between the rear surface 5 of the shell 2 and a surface facing said rear structure. 6. These fasteners 8 are intended to secure the reinforcement system 4 and the shell 2.
  • the fixing elements 8 are distributed, preferably uniformly, around the periphery of the rear structure 6.
  • the rear structure 6 is thus placed in a plane above the shell 2, on the side of its rear surface 5, and makes it possible to match the (generally parabolic) shape of the reflector 1.
  • the reflector 1 is geometrically very compact. .
  • the fixing elements 8 can correspond to any mechanical element, in particular an angle iron, for example in the form of a T or an L, making it possible to fix the rear structure 6 at a distance to the rear surface 5 of the shell 2 and having flexibility.
  • the preferred positioning for a fastening element 8 is to arrange it radially with respect to the rear surface 5 (rounded) of the shell 2. This allows maximum flexibility to be created between the shell 2 and the rear structure 6. Thanks to the circular shape of the rear structure 6, the latter can match the shape of the shell 2, and thus over the entire circular part, the fixing elements 8 can be arranged radially without requiring for example corner wedges, which is in particular advantageous for reasons of ease of assembly and reduction in mass.
  • the rear structure 6 comprises a plurality of structural parts 7B and 7C. These parts of structures 7B and 7C have general circular shapes, but with respective diameters d1 and d2 that are different.
  • the rear structure 6 further comprises connecting tubes 9, preferably rectilinear, which connect the structural parts 7B and 7C together, in particular to improve the mechanical strength.
  • these connecting tubes 9 are arranged radially with respect to the structural parts 7B and 7C.
  • Such an assembly of rectilinear (or straight) connecting tubes 9 and circular tubes (structural parts) can be used when the rear structure consists of several concentric circular structural parts and the straight connecting tubes 9 (preferably radial) are used to tie the circular parts together.
  • the rear structure 6 may therefore in particular comprise one or more completely circular (rear) structure parts, as shown in Figure figure 2 (showing a single circular structure part 7A), or it may have a combination of circular rear structure parts and rectilinear connecting tubes, as shown in FIG. figure 3 .
  • a rear structure 6 with part (s) of circular structure (s) makes it possible to obtain a length D of the shell edge (with respect to the radially outer edge 2A of the shell 2) which is constant throughout the perimeter of the shell 2, or for the single part of structure 7A as in the example of figure 2 , or for the part of structure 7B (of the rear structure 6) radially outermost as in the example of figure 3 . It is thus possible to choose the diameter of this rear structure 7A, 7B to guarantee a length D of the shell edge (or of the free edge) which is optimal, which in particular improves the mechanical performance of the reflector 1 compared to a usual architecture with a polygonal rear structure.
  • the optimum free edge length depends on the material and thickness of the shell 2, as well as the general design of the reflector 1. As an illustration, for a large antenna, the optimum free edge length can be located between 5 cm and 70 cm. Such a free edge makes it possible to dissipate the mechanical energy undergone during launching, but it does not need to be too long so as not to induce large displacements of the shell edge.
  • the use of a circular shape for the rear structure 6 also makes it possible to maintain a symmetry of revolution of the reflector 1, which decreases the areas of stress concentrations (which are areas of potential weakness of the reflector), and improves the all the performances of the reflector 1.
  • the thermal deformation performance of the reflector 1 is increased tenfold (deformations ten times lower) compared to a similar reflector with a polygonal rear structure.
  • the structural part 7D of said rear structure 6 has a generally mixed shape 10 comprising at least one circular part 11, 12 and at least one polygonal (or rectilinear) part 13, 14, such as represented on the figure 4 .
  • this general mixed shape 10 is a truncated circular shape, comprising circular parts (or sections) 11 and 12 and alternating rectilinear parts (or sections) 13 and 14. It also comprises a rectilinear section 15 binding together the two rectilinear parts 13 and 14.
  • the reflector 1 also comprises a plurality of fixing elements (not shown) which are arranged between the rear surface 5 of the shell 2 and the facing surface of the shell. rear structure 6.
  • the fasteners 8 There is an optimum length for the fasteners 8. In fact, a fastener that is too long is more sensitive to buckling and reduces the mechanical strength of this fastener (and of the reflector), and a fastener that is too short does not allow sufficient flexibility to be left between the structure and the hull. In addition, a fastening element that is too short induces losses in mechanical performance in the strength of the junction at the foot of the fastening element.
  • the optimum length for a fixing element 8 is between 3 cm and 40 cm. This optimum length depends on the characteristics of the fastener, such as the material constituting the fastener, its width, its thickness, the type of junction between the fastener and the shell, and the type of junction between the rear element and structure.
  • the rear structure 6 preferably comprises tubes made of carbon-based composite material, which make it possible to ensure the mechanical strength and stiffness, and a great inertia of this rear structure to obtain good performance from the complete reflector.
  • These tubes may have cross sections of different shapes, for example an ellipse or preferably a round, or sections of polygonal shapes, in particular rectangular or square.
  • each part of circular structure can be a complete torus or several parts of a torus.
  • the toroid parts can be assembled together or be separated.
  • the shape of the rear structure 6 may depend, in particular, on the size of the hull 2 and on the position of interfaces with the satellite so as to ensure that the hull 2 is held in place at points distributed over its surface.
  • the method of manufacturing the reflector 1, as described above, is as follows.
  • the rear structure 6 (at least partially circular) is made of a carbon-based composite material. By way of illustration, it can be manufactured by draping pre-impregnated plies, by depositing dry plies, then by low-pressure injection molding of RTM type liquid resin (for “Resin Transfert Molding” in English) or by infusion, then by polymerization of the resin.
  • the manufacture of a toric tubular rear structure 6 is carried out by the use of an toric mold and the layup of composite plies on the mold.
  • the manufacture of the shell 2 of the reflector 1 is, for its part, carried out in the usual way.
  • the assembly of the rear structure 6 is implemented according to methods identical to those used for conventional reflectors, as well as the fixing of the rear structure 6 on the hull 2.

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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)
EP16713510.2A 2015-03-10 2016-03-08 Réflecteur d'antenne, en particulier pour engin spatial Active EP3269009B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1500456A FR3033670B1 (fr) 2015-03-10 2015-03-10 Reflecteur d'antenne, en particulier pour engin spatial
PCT/FR2016/000039 WO2016142591A1 (fr) 2015-03-10 2016-03-08 Réflecteur d'antenne, en particulier pour engin spatial

Publications (2)

Publication Number Publication Date
EP3269009A1 EP3269009A1 (fr) 2018-01-17
EP3269009B1 true EP3269009B1 (fr) 2021-08-11

Family

ID=53673988

Family Applications (1)

Application Number Title Priority Date Filing Date
EP16713510.2A Active EP3269009B1 (fr) 2015-03-10 2016-03-08 Réflecteur d'antenne, en particulier pour engin spatial

Country Status (6)

Country Link
US (1) US20180048072A1 (es)
EP (1) EP3269009B1 (es)
CA (1) CA2977890C (es)
ES (1) ES2895500T3 (es)
FR (1) FR3033670B1 (es)
WO (1) WO2016142591A1 (es)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113036443B (zh) * 2021-03-04 2022-01-28 西安电子科技大学 一种用于宽带和宽角rcs减缩的光学透明电磁超表面

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5686930A (en) * 1994-01-31 1997-11-11 Brydon; Louis B. Ultra lightweight thin membrane antenna reflector
EP1835565A1 (en) * 2006-03-16 2007-09-19 Saab AB Reflector
JP4702747B2 (ja) * 2006-03-31 2011-06-15 日本無線株式会社 反射鏡アンテナ支持構造体
FR2944155B1 (fr) * 2009-04-02 2016-05-13 Astrium Sas Antenne radioelectronique a cornieres de decouplage ameliorees
US9337544B2 (en) * 2013-01-07 2016-05-10 Lockheed Martin Corporation Configurable backing structure for a reflector antenna and corrective synthesis for mechanical adjustment thereof
CN104981941B (zh) * 2014-04-01 2018-02-02 优倍快网络公司 天线组件

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
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Also Published As

Publication number Publication date
FR3033670B1 (fr) 2018-10-12
WO2016142591A1 (fr) 2016-09-15
CA2977890C (fr) 2023-02-21
EP3269009A1 (fr) 2018-01-17
FR3033670A1 (fr) 2016-09-16
ES2895500T3 (es) 2022-02-21
US20180048072A1 (en) 2018-02-15
CA2977890A1 (fr) 2016-09-15

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