EP2415118A1 - Antenne radioelectrique a cornieres de decouplage ameliorees - Google Patents
Antenne radioelectrique a cornieres de decouplage amelioreesInfo
- Publication number
- EP2415118A1 EP2415118A1 EP10712947A EP10712947A EP2415118A1 EP 2415118 A1 EP2415118 A1 EP 2415118A1 EP 10712947 A EP10712947 A EP 10712947A EP 10712947 A EP10712947 A EP 10712947A EP 2415118 A1 EP2415118 A1 EP 2415118A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- shell
- elastic material
- reflector
- antenna according
- 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
Links
Classifications
-
- 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
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/12—Supports; Mounting means
- H01Q1/20—Resilient mountings
-
- 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 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. The level of the acoustic demands induced by the launchers being very difficult to predict, it is preferable that these antennas are almost insensitive to acoustic forces, to limit the risk of under-sizing or over-dimensioning means connecting reflectors to spacecraft.
- FIGS. 1 and 1 show an example of a radio antenna 10 (FIG. 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 shell 14 of the reflector 12 is supported by a rigid rear structure 16 of this reflector.
- This rear structure 16 is for example formed of tubular elements arranged in a hexagon centered on an axis of the reflector. In the example shown in the figures, these tubular elements have, seen in section, a rectangular shape.
- 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. These openings allow a reduction of the mass of the reflector, and communicate with honeycomb cells of the honeycomb structure so that this type of reflector is insensitive to vibratory stresses, in particular to acoustic stresses during the launch of the satellite equipped with the antenna 10.
- 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 sandwich structures of the type described above which comprise perforated skins formed of a single ply of composite material, do not make it possible to easily satisfy the levels of requirement inherent to a functioning 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 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 support means of this reflector, the reflector comprising a shell adapted to reflect the radio waves, and a rigid rear structure carried by the means support and connected to the shell by decoupling brackets distributed around an axis of the shell and each comprising a first base fixed on the reflector shell, a flexible metal strip or a second base fixed on the rigid rear structure, and a central metal blade connecting the aforementioned first base to the flexible metal strip or to the second aforementioned base and capable of damping a transverse component of vibration of the shell.
- each of said decoupling angles comprises at least one of its ends, a layer of an elastic material capable of damping at least one axial component of vibration of the shell.
- the aforementioned elastic material layer is interposed between said first base and the shell, or between said flexible metal strip or said second base and said rigid rear structure.
- Each decoupling angle can thus comprise either a single layer of elastic material arranged at one end of the angle, or two layers of elastic material respectively arranged at both ends of the angle.
- the layer of elastic material of each angle can significantly reduce the impact of vibrational stresses, including acoustic, on the support means of the reflector of the antenna.
- the shell of the reflector comprises a full front skin, that is to say, not perforated. Due to their elastic material layer, the high damping capacity of the angles makes it possible to use a full front skin, able to provide the reflector with optimal reflectivity properties, while limiting the risks of underwear. sizing of 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%. %.
- said layer of elastic material of each angle 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.
- Each angle may further comprise a sandwich structure comprising two skins of composite material affixed on either side of said layer of elastic material.
- brackets can in particular allow the brackets to be fixed to the reflector by a method similar to a method usually used for fixing the angles of the reflectors of the type Convention described above, which may be of considerable economic interest.
- the elastic material may comprise an adhesive comprising an elastomer or silicone or polyurethane compound.
- 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 front skin and the back 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 antenna is advantageously configured to operate in a predetermined frequency band of the microwave spectrum. waves, this frequency band being in particular included in the Ka band.
- 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 view similar to Figure la, a radio antenna according to the invention.
- Figure 2 shows a portion of the reflector 20 of a radio antenna according to an embodiment of the invention.
- This reflector 20 is generally of the same type as the reflector 12 of the prior art shown in FIGS. 1 and 1a, but the reflector 20 comprises a shell 22 with a full front skin and decoupling brackets 24 of a new type, in accordance with FIG. to the invention.
- the terms “front”, “back” and “lateral” are used with reference to the direction of transmission of the antenna.
- the shell 22 of the reflector 20 has substantially the shape of a paraboloid of revolution about an axis of the reflector.
- the front skin (not visible in Figure 2) of the shell 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 of the front skin are woven so as 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 fabrics crossed at angles of plus or minus 45 degrees or in the form of three to six plies of plies of fibers draped symmetrically (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 shell 22 further comprises a rear skin 26 which is made of a composite material similar to that described above, of the front skin, and which thus has the same advantages.
- the reflector 20 comprises a rigid rear structure 28 formed of tubular elements 29 of substantially rectangular section, and similar to the rear structure 16 of the reflector 12 of the prior art.
- the rear structure 28 is connected to the shell 22 of the reflector by the brackets 24, which each comprise a central metal blade 30.
- One end of the blade 30 has a first base 32 for attachment to the rear skin 26 of the shell 22, and another end of the blade 30 is fixed to a flexible metal strip 34 fixed on a lateral face 36 of a tubular element 29 of the rear structure 28.
- the flexible strip 34 and, to a lesser extent, the central blade 30, allow by their elasticity to damp the transverse component, that is to say perpendicular to the axis of the shell 22, vibrations of the shell 22.
- each bracket 24 comprises in in addition to a layer of elastic material 38, interposed between the base 32 of the angle and the rear skin 26 of the shell 22, to damp the axial component of any vibration of the shell 22.
- the elastic material 38 is a polyimide foam chosen not to degrade at temperatures between -180 0 C and +200 0 C, and to meet the spatial standards relating to degassing, typically specifying a total loss of mass ( TML) less than about 1%.
- This foam is furthermore chosen to have thermomechanical properties such that this foam affects as little as possible the thermomechanical behavior of the reflector 20.
- Foam is chosen to have a thermoelastic coefficient as low as possible.
- the polyimide foam has a density of between 10 kg / m 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 an elongation at rupture between 20% and 40%.
- the aforementioned physical parameters are chosen according to the level of damping and mechanical decoupling required between the shell 22 and the rear structure 28 of the reflector.
- each bracket 24 may comprise a layer of elastic material of the type described above, interposed between the central plate 30 of the bracket 24 and the rear structure 28 of the reflector.
- each bracket 24 is fixed on a front face 40 of a tubular element 29 of the rear structure 28, for example by a second base similar to the first base 32 mentioned above and connected to the end of the central blade 30 opposite to the first base 32.
- the foam layer can thus be interposed between the second base and the front face 40 of the tubular element 29, to allow good damping of the axial vibration component of the shell 22 .
- the layer of elastic material may be integrated in a sandwich structure, and in particular be inserted between two full skins, for example of a type similar to that of the skins of the shell 22.
- This feature allows in particular, for fixing the brackets 24 to the rear skin 26 of the reflector, to use a fixing method similar to a conventional method of fixing the angles of the reflectors of known type.
- the rear structure 28 is of tubular type, but the invention is also compatible with rear structures of other types, such as planar structures, paraboloidal, or the like, for example composite sandwich type.
- 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)
- 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)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0952151A FR2944155B1 (fr) | 2009-04-02 | 2009-04-02 | Antenne radioelectronique a cornieres de decouplage ameliorees |
PCT/EP2010/054457 WO2010112601A1 (fr) | 2009-04-02 | 2010-04-02 | Antenne radioelectrique a cornieres de decouplage ameliorees |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2415118A1 true EP2415118A1 (fr) | 2012-02-08 |
EP2415118B1 EP2415118B1 (fr) | 2014-11-12 |
Family
ID=41210426
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP10712947.0A Not-in-force EP2415118B1 (fr) | 2009-04-02 | 2010-04-02 | Antenne radioelectrique a cornieres de decouplage ameliorees |
Country Status (5)
Country | Link |
---|---|
US (1) | US20120026056A1 (fr) |
EP (1) | EP2415118B1 (fr) |
ES (1) | ES2530571T3 (fr) |
FR (1) | FR2944155B1 (fr) |
WO (1) | WO2010112601A1 (fr) |
Families Citing this family (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8274446B2 (en) * | 2010-06-03 | 2012-09-25 | Raytheon Company | Lightweight antenna attachment structure |
FR2981686B1 (fr) | 2011-10-21 | 2016-05-20 | Snecma | Turbomachine comprenant un recepteur a helices contrarotatives supporte par une enveloppe structurale fixee au carter intermediaire |
US9680229B2 (en) * | 2013-06-28 | 2017-06-13 | The Boeing Company | Modular reflector assembly for a reflector antenna |
FR3033670B1 (fr) * | 2015-03-10 | 2018-10-12 | Arianegroup Sas | Reflecteur d'antenne, en particulier pour engin spatial |
FR3068522B1 (fr) * | 2017-06-30 | 2019-08-16 | Airbus Safran Launchers Sas | Systeme d'interface modulaire pour un reflecteur d'antenne, en particulier d'une antenne d'un engin spatial tel qu'un satellite notamment. |
US11398682B2 (en) * | 2020-04-03 | 2022-07-26 | Lockheed Martin Corporation | Hosted, compact, large-aperture, multi-reflector antenna system deployable with high-dissipation feed |
Family Cites Families (11)
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 |
US5178709A (en) * | 1985-04-15 | 1993-01-12 | Mitsubishi Denki Kabushiki Kaisha | Method of manufacturing a reflector of fiber reinforced plastic material |
CA2135703A1 (fr) * | 1994-01-31 | 1995-08-01 | Louis B. Brydon | Reflecteur d'antenne en membrane mince ultra-legere |
US5900442A (en) * | 1995-05-12 | 1999-05-04 | Imperial Chemical Industries Plc | Flexible polyurethane foams |
US6082719A (en) * | 1998-05-12 | 2000-07-04 | Trw Inc. | Spacecraft antenna vibration control damper |
DE29914904U1 (de) * | 1999-08-25 | 1999-12-30 | Michel, Oliver, 41564 Kaarst | Satellitenempfänger und Vorrichtung zum Abdecken eines Satellitenempfängers |
US6515636B2 (en) * | 2001-04-12 | 2003-02-04 | Lockheed Martin Corporation | Active array antenna with flexible membrane elements and tensioning arrangement |
DE10361481B4 (de) * | 2003-07-22 | 2006-08-17 | Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V. | Modulare Schnittstelle zum Dämpfen mechanischer Schwingungen |
US7104515B2 (en) * | 2004-11-12 | 2006-09-12 | Harris Corporation | Flexure elastomer antenna isolation system |
US7173575B2 (en) * | 2005-01-26 | 2007-02-06 | Andrew Corporation | Reflector antenna support structure |
-
2009
- 2009-04-02 FR FR0952151A patent/FR2944155B1/fr not_active Expired - Fee Related
-
2010
- 2010-04-02 EP EP10712947.0A patent/EP2415118B1/fr not_active Not-in-force
- 2010-04-02 ES ES10712947T patent/ES2530571T3/es active Active
- 2010-04-02 US US13/260,833 patent/US20120026056A1/en not_active Abandoned
- 2010-04-02 WO PCT/EP2010/054457 patent/WO2010112601A1/fr active Application Filing
Non-Patent Citations (1)
Title |
---|
See references of WO2010112601A1 * |
Also Published As
Publication number | Publication date |
---|---|
EP2415118B1 (fr) | 2014-11-12 |
ES2530571T3 (es) | 2015-03-03 |
US20120026056A1 (en) | 2012-02-02 |
FR2944155A1 (fr) | 2010-10-08 |
WO2010112601A1 (fr) | 2010-10-07 |
FR2944155B1 (fr) | 2016-05-13 |
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