EP2415114A1 - Funkantenne - Google Patents

Funkantenne

Info

Publication number
EP2415114A1
EP2415114A1 EP10712443A EP10712443A EP2415114A1 EP 2415114 A1 EP2415114 A1 EP 2415114A1 EP 10712443 A EP10712443 A EP 10712443A EP 10712443 A EP10712443 A EP 10712443A EP 2415114 A1 EP2415114 A1 EP 2415114A1
Authority
EP
European Patent Office
Prior art keywords
skin
reflector
antenna according
elastic material
antenna
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.)
Granted
Application number
EP10712443A
Other languages
English (en)
French (fr)
Other versions
EP2415114B1 (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
Astrium 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
Application filed by Astrium SAS filed Critical Astrium SAS
Publication of EP2415114A1 publication Critical patent/EP2415114A1/de
Application granted granted Critical
Publication of EP2415114B1 publication Critical patent/EP2415114B1/de
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/005—Damping of vibrations; Means for reducing wind-induced forces
    • 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

Definitions

  • the present invention relates to the field of radio-reflector antennas, 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 the reflectors to the spacecraft, which are subjected to acoustic and dynamic vibrational stresses induced. by space launchers. These antennas must also comply with specifications concerning their thermoelastic behavior in orbit.
  • Figures 1 and 1a show an example of a radio antenna 10 (Figure 1) for telecommunications satellite operating at frequencies between 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 shell 14 of the reflector 12 is supported by a rigid tubular rear structure 16 of this reflector.
  • This rear structure 16 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 shell 14 by angles 18
  • Figure la able to ensure the mechanical strength of the antenna when launching and putting into orbit 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 perforated reflectors of the type described above are not satisfactory at frequencies between about 20 GHz and 40 GHz (Ka band).
  • 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 more stringent, which leads to more stringent requirements in terms of manufacturing accuracy and stability over time of the reflectors, typically of the order of 30.
  • RMS compared to 150 ⁇ m RMS for satellites operating at lower frequencies of the Ku 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 a space satellite, able to operate at frequencies of the band Ka, 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 means for supporting this reflector, the reflector comprising a front skin capable of reflecting the radio waves, and a rigid rear structure carried by the support means, the antenna being characterized in that the reflector comprises a layer of elastic material which is interposed between the front skin and the rigid rear structure, and which is capable of damping the vibrations of the front skin.
  • the layer of elastic material makes it possible to considerably reduce the impact of vibratory stresses, in particular acoustic stresses, on the support means of the reflector of the antenna. This limits the level of mechanical strength required for the support means, and thus makes it easier to dimension these support means.
  • the front skin of the reflector is a full skin, that is to say, not perforated.
  • the presence of the layer of elastic material makes it possible to use a full front skin, able to provide the reflector with optimal reflectivity properties, while limiting the risk of under-dimensioning the reflector support means.
  • said elastic material has a Young's modulus of between 0.25 MPa and 1 MPa, a tensile strength of between 0.1 MPa and 0.5 MPa, and an elongation at break of between 20% and 40%. %.
  • the layer of elastic material is thus able to optimally dampen the vibratory stresses to which the antenna is likely to be subjected, in particular when this antenna equips a spacecraft.
  • said elastic material is a foam and comprises at least one compound belonging to the group of polyimides.
  • this elastic material preferably has a density of between 10 kg / m 3 and 20 kg / m 3 .
  • the use of an elastic material of this type allows a weight saving compared to antennas of the prior art whose honeycomb structure generally has a density of between 26 kg / m 3 and 34 kg / m 3 .
  • This weight gain can be used to increase the thickness of the front skin, so as to improve the accuracy and stability over time of the profile of this skin before, without significantly increasing the antenna compared to antennas type known. As will become more apparent in what follows, this weight gain can also help strengthen the rigid rear structure of the reflector.
  • the elastic material may comprise at least one elastomeric adhesive.
  • the elastic material is chosen not to degrade at space operating temperatures in orbit, and more precisely at temperatures between -180 0 C and +200 0 C.
  • the rigid rear structure comprises a rear structural skin fixedly connected to said reflector support means.
  • the damping properties of the layer of elastic material are indeed sufficient to allow such a back skin to fulfill the structuring function of rigid tubular rear structures antennas of the prior art of the type described above.
  • the rear structural skin preferably comprises at least one thickened portion to which are connected said reflector support means. Such a thickened portion reinforces the connection between the reflector and the support means of the latter.
  • the front skin and the rear structural skin are made of a composite material comprising fibers embedded in a cured resin.
  • These fibers are advantageously carbon fibers arranged so as to optimize the isotropy of the mechanical and thermal properties of these skins.
  • these fibers may for example be arranged in the form of two folds of taffeta fabric crossed at angles of plus or minus 45 degrees or in the form of three to six plies of symmetrically draped fiber sheets (0 °, + 60 °, - 60 °).
  • the layer of elastic material is preferably attached to the front skin and the rear structural skin by gluing.
  • This bonding can be achieved simply by a homogeneous contact and under adequate docking pressure, the front and rear faces of the layer of foam respectively with the skin before and with the structural back skin.
  • the rear structural skin is flat and extends perpendicularly to an axis of the reflector.
  • the layer of elastic material is then advantageously profiled so that its front and rear faces have substantially the same shape respectively as the front skin and the rear skin.
  • the rear structural skin may have a shape substantially identical to that of the front skin.
  • the layer of elastic material is profiled to maximize the contact area between its upper face and the skin before one hand, and between its lower face and the rear skin on the other. Due to its elasticity, the layer of elastic material also makes it possible to compensate for the differences between the theoretical and real profiles of the front and rear skins, and also to compensate for the presence of any parts in excess thickness of the rear structural skin.
  • the bonding surface between the front and rear skins respectively and the layer of elastic material can thus be maximum, so as to allow in particular a reduction of the requirements relating to the mechanical strength in shear of the reflector support means.
  • the rear structural skin has a hollow central portion.
  • the rear structural skin comprises, in one piece, fastening elements to the support means.
  • These support means which are for example formed of an arm, can in fact be connected to the rear structural skin by flooding a fixing portion of these support means in the resin which composes the rear structural skin.
  • the antenna is advantageously configured to operate in a predetermined frequency band of the microwave spectrum, this frequency band being in particular included in the Ka band.
  • This use of an active non-open face, made possible by the invention, is indeed particularly advantageous in the Ka band, as explained above.
  • FIG. 1, already described is a schematic perspective view of a radio antenna of a known type
  • FIG. 1a is a view on a larger scale of the detail Ia of FIG. 1;
  • FIG. 2 is a schematic perspective view of the reflector of a radio antenna according to the invention.
  • FIG. 2 represents a reflector 20 of a radio antenna for a spacecraft according to one embodiment of the invention.
  • the reflector 20 comprises a front skin 22, sometimes also called active skin, and a structural rear skin 24 carried by a support arm (not shown in Figure 2) intended to provide the connection between the antenna and a spacecraft.
  • the front skin 22 of the reflector has substantially the shape of a paraboloid of revolution about an axis 26.
  • This front skin 22 is made of a conventional composite material, of the type comprising a fabric of structural fibers, for example carbon, embedded in an epoxy resin or the like.
  • the structural fibers are woven according to a draping adapted to ensure optimal isotropy of the mechanical behavior of the skin before 22, and so that the front skin 22 is full.
  • these structural fibers are for example arranged in the form of two folds of taffeta fabric crossed at angles plus or minus 45 degrees or in the form of three to six plies of symmetrically draped fiber sheets (0 °, +60 °, -60 °). This type of structure makes it possible in particular to optimize the accuracy and stability over time of the profile of the front skin.
  • the rear skin 24 is made of a composite material similar to that of the front skin 22, but has a more rigid structure than that of the front skin so as to ensure the mechanical connection between the front skin of the reflector and the support arm of the antenna.
  • the rear skin 24 thus constitutes a rigid rear structure.
  • the support arm has an end fixed by gluing on the rear face of the rear skin 24.
  • the end of the support arm may be integrated with the rear skin 24, for example by embedding this end in the resin constituting the rear skin 24.
  • the structural rear skin 24 has one or more reinforced portions in excess thickness located at level of attachment of the support arm of the antenna.
  • the front skin 22 and the structural back skin 24 are respectively adhered to the front and rear faces of a layer of polyimide foam 28, intended to dampen the vibrations to which the front skin 22 is likely to be subjected, especially during the launch. and putting into orbit a spacecraft equipped with the antenna.
  • the polyimide foam is chosen so as not to degrade at temperatures between -180 ° C. and + 200 ° C., and to satisfy the spatial standards relating to degassing, typically specifying a total mass loss (TML) of less than about 1%. .
  • This foam is further selected to have thermomechanical properties such that this foam affects as little as possible the thermomechanical behavior of the reflector 20.
  • the foam is chosen to have a thermoelastic coefficient as low as possible.
  • the polyimide foam has a density of between 10 kg / m 3 and 20 kg / m 3 , a tensile strength of between 0.1 MPa and 0.5 MPa, a Young's modulus of between 0.25 MPa and 1 MPa, and a breaking elongation of between 20% and 40%.
  • the aforementioned physical parameters are chosen according to the level of damping and mechanical decoupling required between the front skin 22 and the structural rear skin 24.
  • the structural rear skin 24 is in the form of a flat disc and the foam layer 28 is profiled so as to maximize the contact surface on the one hand between the front face of the foam layer 28 and the front skin 22, and secondly between the rear face of the foam layer 28 and the rear skin 24.
  • the rear skin 24 may be of a shape similar to that of the front skin 22.
  • the foam layer 28 makes it possible to compensate for the differences between the profiles. Theoretical and real skins before 22 and rear 24, and also to compensate the part or parts of the extra thickness of the rear skin 24.
  • the structural rear skin 24 may comprise a central portion recessed so as to form a ring centered on the axis 26 of the reflector.
  • the front skin of the reflector may of course have a shape different from that described above by way of example without departing from the scope of the invention.

Landscapes

  • Physics & Mathematics (AREA)
  • Electromagnetism (AREA)
  • Aerials With Secondary Devices (AREA)
  • Details Of Aerials (AREA)
EP10712443.0A 2009-04-02 2010-04-02 Funkantenne Not-in-force EP2415114B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0952149A FR2944156B1 (fr) 2009-04-02 2009-04-02 Antenne radioelectrique
PCT/EP2010/054455 WO2010112599A1 (fr) 2009-04-02 2010-04-02 Antenne radioelectrique

Publications (2)

Publication Number Publication Date
EP2415114A1 true EP2415114A1 (de) 2012-02-08
EP2415114B1 EP2415114B1 (de) 2013-08-28

Family

ID=41060004

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10712443.0A Not-in-force EP2415114B1 (de) 2009-04-02 2010-04-02 Funkantenne

Country Status (5)

Country Link
US (1) US8872718B2 (de)
EP (1) EP2415114B1 (de)
ES (1) ES2437075T3 (de)
FR (1) FR2944156B1 (de)
WO (1) WO2010112599A1 (de)

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1144475B (de) * 1961-05-06 1963-02-28 Bayer Ag Verfahren zur Herstellung von Urethangruppen enthaltenden Schaumstoffen
US3620987A (en) * 1969-11-21 1971-11-16 Upjohn Co Preparation of polymer foam
US3897294A (en) * 1974-05-06 1975-07-29 Gen Dynamics Corp Method of forming a parabolic antenna
US4636801A (en) * 1983-04-18 1987-01-13 Hughes Aircraft Company Multiple reflector system with dielectric support webs and foam body
US5178709A (en) * 1985-04-15 1993-01-12 Mitsubishi Denki Kabushiki Kaisha Method of manufacturing a reflector of fiber reinforced plastic material
US5184141A (en) * 1990-04-05 1993-02-02 Vought Aircraft Company Structurally-embedded electronics assembly
US5900442A (en) * 1995-05-12 1999-05-04 Imperial Chemical Industries Plc Flexible polyurethane foams
US20040113863A1 (en) * 2002-12-16 2004-06-17 Stonier Roger A. Microwave frequency antenna reflector
EP1589612B1 (de) * 2004-04-22 2007-10-31 Saab AB Reflektor

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2010112599A1 *

Also Published As

Publication number Publication date
FR2944156B1 (fr) 2011-05-13
FR2944156A1 (fr) 2010-10-08
ES2437075T3 (es) 2014-01-08
WO2010112599A1 (fr) 2010-10-07
US20120026055A1 (en) 2012-02-02
US8872718B2 (en) 2014-10-28
EP2415114B1 (de) 2013-08-28

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