EP0201727A1 - Antenne à réflecteur - Google Patents

Antenne à réflecteur Download PDF

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Publication number
EP0201727A1
EP0201727A1 EP86104892A EP86104892A EP0201727A1 EP 0201727 A1 EP0201727 A1 EP 0201727A1 EP 86104892 A EP86104892 A EP 86104892A EP 86104892 A EP86104892 A EP 86104892A EP 0201727 A1 EP0201727 A1 EP 0201727A1
Authority
EP
European Patent Office
Prior art keywords
antenna
reflector
hood
stiffening ring
curing
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.)
Ceased
Application number
EP86104892A
Other languages
German (de)
English (en)
Inventor
Marco C. Dr. Bernasconi
Karl Kotacka
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.)
Rheinmetall Air Defence AG
Original Assignee
Oerlikon Contraves AG
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 Oerlikon Contraves AG filed Critical Oerlikon Contraves AG
Publication of EP0201727A1 publication Critical patent/EP0201727A1/fr
Ceased 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 [2D], e.g. paraboloidal
    • H01Q15/161—Collapsible reflectors
    • H01Q15/163—Collapsible reflectors inflatable

Definitions

  • the invention relates to a method for producing a reflector antenna, in particular a reflector antenna made parabolically from a deployable laminate sheet, consisting of an antenna hood that can be inflated into a shell body, a reflector and a stiffening ring.
  • the invention further relates to a reflector antenna manufactured by this method, the reflector of which is combined with an antenna hood to form a hollow body and is stabilized by a tubular stiffening ring.
  • antennas which are intended for spacecraft, for example, there are, in addition to the general requirements to be placed on such antennas, e.g. high dimensional accuracy of the antenna structure, other special requirements that arise due to the transport conditions to orbit, i.e. they should be as light as possible and foldable to the smallest possible storage volume.
  • the known mechanical construction antenna constructions intended for space conditions use rib and / or panel constructions with numerous details, such as hinges, supports, springs, tensioning cables, braking systems for controlled deployment and. Like. So that they are expensive to manufacture and due to their structure made up of many individual parts represent a compromise in terms of shape accuracy and / or the reliability of the reflector.
  • the invention is based on the object, starting from the state of the art of inflatable antennas, to improve the method and the antenna of the type mentioned in such a way that the antenna has, in addition to the basic advantages of its inflatable type, a more stable shape and a substantially longer service life.
  • This object is achieved essentially by the features specified in claims 1 and 4.
  • Curing can only be done under the influence of solar radiation by the antenna during the Curing is oriented towards the sun or with the additional action of a catalyst gas which is part of the gas used to manufacture the antenna shape.
  • the antenna according to the invention can be designed both as a centrally fed antenna and as an offset antenna.
  • Fig.l shows an overall designated 1 and designed as a centrally fed parabolic antenna Reflector antenna, which has an antenna tower 4 surrounded by a reflector 2 and an antenna hood 3 in a circle-symmetrical manner.
  • the antenna tower 4 consists essentially of an interface base part 5, with several rods 7 distributed around the circumference, determining its length and enclosed by a film 6, and from a feed head 8, it being possible for a feed reflector 8 to be provided in place of the feed head 8.
  • the interface base part 5 Through the interface base part 5, the mechanical and electrical connection to a spacecraft, not shown, can be established.
  • the antenna tower 4 In the area of the interface base part 5 and the feed head 8, the antenna tower 4, as shown in more detail in FIG. 4, is enclosed by a fastening ring 9, 10 with an outwardly projecting flange 11, 12 on which the reflector 2 and the antenna hood 3, e.g. fixed by gluing.
  • the reflector 2 and the antenna hood 3 are connected to one another via a tubular stiffening ring 13 which, together with the dimensioning of the surface size of the reflector 2 and the antenna hood 3, determines their shape under the influence of an internal gas pressure.
  • the antenna hood 3 is curved much more parabolically than the reflector 2, so that the fastening ring 10 for the antenna hood 3 has the desired position relative to the feed head 8.
  • the antenna hood 3 can also be symmetrical to the shape of the reflector, i.e. be arched like this, as shown by the embodiment of an offset antenna in FIG. 6.
  • the reflector 2, the antenna hood 3 (RADOM) and the outer jacket of the stiffening ring 13 (TORUS) are made from a fabric that is stiff by curing, which is preferably a laminate pigmented to control absorption.
  • the hardening constituent for example a hardening synthetic resin, is impregnated in a fabric layer of the laminate applied to the inside of the curvature of the reflector 2 and the antenna hood 3.
  • the synthetic resin comes into contact with a gaseous medium fed into the antenna cavity 15 via a feed line 24 and into the stiffening ring 13 via a feed line 25, in particular a catalyst gas which is a component of a gas used to inflate the antenna.
  • the fabric layer borders on the outside to a laminated plastic film that serves as a gas barrier during curing and also protects the impregnated fabric layer from UV radiation. It can also serve as a carrier layer for a special layer or a coating, for example as an electrically conductive layer for a microwave reflector.
  • the electrically conductive layer is, based on the curvature, on the outside of the plastic film, so that it also takes on a thermal control function and contributes to an increase in temperature and a more uniform temperature distribution during curing.
  • the radiation exchange between the antenna reflector 2 and the antenna cover 3 also contributes to the uniform temperature distribution over the entire surface of the parabolic antenna and thus to increased dimensional stability. It is advantageous here that the inside of the antenna has a high emission.
  • the aforementioned, electrically conductive, ie metallic layer brings about a shielding against thermal radiation which is advantageous for temperature compensation.
  • this is the reflector 2, the antenna hood 3 and the stiffening ring 13, flexible, so that the parts 2, 3 and 13 can be folded into the compact package shape shown in FIGS. 2 and 3 and space-saving in a not shown waste load covering of a launch vehicle or a "space shuttle "to be stowed.
  • the antenna sheath formed from the parts 2, 3 and 13 is folded around the antenna tower 4 and tightly against it, in the form of several longer and shorter folded positions 13, 17, 18.
  • the longer folding layers 17 of the reflector 2 extend over almost the entire length of the tower part located between the interface base part 5 and the feed head 8, while part of the antenna hood 3 in shorter folding positions 18 the upper area and the stiffening ring 13 as the folding position the lower Encloses area of the tower part.
  • a band 19 visible in FIG. 3 is wound helically around the folded layers 13, 17, 18 and thus holds them together as a package 20.
  • the release of the band 19 for unfolding the antenna 1 after reaching the orbit can be done mechanically or by local heating by means not shown, known per se.
  • the shell package 20 is surrounded by a plurality of circumferentially distributed and correspondingly adapted housing shells 21, which are mounted by means of joints 22 on the edge of the interface base 5 and can be unfolded in a bleeding-like manner.
  • the gaseous medium for generating the inflation pressure of the antenna 1 is fed to the antenna cavity 15 and the tubular stiffening ring 13 via hose lines 24, 25, the into the antenna cavity 15 Opening hose line 24, as shown in FIG. 4, opens out through a cylindrical part 27 of the fastening ring 9, while the hose line 25 leading to the fastening ring 13, as shown in FIG. 5, runs along the outside of the reflector 2 and accordingly over one arranged on the outside of the stiffening ring 13, angled coupling part 28 opens into the stiffening ring 13.
  • the pressure required is relatively low due to the lack of pressure in the surrounding space and is of the order of magnitude around 0.4 kp / m2. It is controlled by valves (not shown) in the feed lines.
  • Pressurized gas cylinders with sufficient content for maintaining the pressure during a relatively short curing time of the impregnated synthetic resin are arranged at a suitable point in the associated spacecraft, on the support arm of which the interface base 5 is fastened in a manner not shown.
  • the parabolic antenna is preferably kept facing the sun, so that the antenna surface is heated uniformly to a temperature at which rapid curing, possibly supported by a catalyst gas, takes place.
  • Epoxy resins for example, are suitable as the curing synthetic resin composition.
  • An offset antenna 1 ' is produced according to the same principle according to the invention by inflating the antenna hollow body consisting of a reflector 2', an antenna hood 3 '(RADOM) and a stiffening ring 13'.
  • An antenna arm 31 is attached at a point 30 to the stiffening ring 13 '.
  • the illustration according to FIG. 7 shows the structure of the antenna shell from numerous juxtaposed, cut and glued together material webs 32, the shape of which determines the shape of the antenna.
  • the thickness of the laminate used for the casing body is of the order of 0.1 mm with a correspondingly small thickness of the fabric layer.
  • the overall dimensions of an antenna according to the invention can be chosen within a wide range.
  • the centrally fed antenna is e.g. with a diameter in the order of approx. 22 m and a height of the antenna tower of approx. 6 m and the offset antenna with a diameter of approx. 12 m can be realized. It goes without saying that it can be expedient for antennas with a particularly large diameter to make the antenna tower telescopically in a manner known per se.

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  • Physics & Mathematics (AREA)
  • Electromagnetism (AREA)
  • Aerials With Secondary Devices (AREA)
  • Details Of Aerials (AREA)
EP86104892A 1985-05-15 1986-04-10 Antenne à réflecteur Ceased EP0201727A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH2077/85 1985-05-15
CH207785 1985-05-15

Publications (1)

Publication Number Publication Date
EP0201727A1 true EP0201727A1 (fr) 1986-11-20

Family

ID=4225361

Family Applications (1)

Application Number Title Priority Date Filing Date
EP86104892A Ceased EP0201727A1 (fr) 1985-05-15 1986-04-10 Antenne à réflecteur

Country Status (3)

Country Link
US (1) US4755819A (fr)
EP (1) EP0201727A1 (fr)
JP (1) JPS61264901A (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3014417A1 (fr) * 2013-12-10 2015-06-12 Eads Europ Aeronautic Defence Nouvelle architecture de vehicule spatial

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2591153B2 (ja) * 1989-04-28 1997-03-19 日本電気株式会社 インフレータブルアンテナ
US5920294A (en) * 1997-06-30 1999-07-06 Harris Corporation Tensioned cord attachment of antenna reflector to inflated support structure
US6219009B1 (en) 1997-06-30 2001-04-17 Harris Corporation Tensioned cord/tie attachment of antenna reflector to inflatable radial truss support structure
US5990851A (en) * 1998-01-16 1999-11-23 Harris Corporation Space deployable antenna structure tensioned by hinged spreader-standoff elements distributed around inflatable hoop
US6115003A (en) * 1998-03-11 2000-09-05 Dennis J. Kozakoff Inflatable plane wave antenna
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
AU7384800A (en) * 1999-09-21 2001-04-24 Johns Hokpins University, The Hybrid inflatable antenna
WO2001054228A1 (fr) * 2000-01-18 2001-07-26 Medzmariashvili Elgudja V Antenne parabolique deployable
US6512496B2 (en) 2001-01-17 2003-01-28 Asi Technology Corporation Expandible antenna
US7382332B2 (en) * 2001-05-30 2008-06-03 Essig Jr John Raymond Modular inflatable multifunction field-deployable apparatus and methods of manufacture
WO2002097917A1 (fr) * 2001-05-30 2002-12-05 Essig John R Jr Dispositif reflecteur parabolique gonflable multifonction et procede de fabrication
FR2841047A1 (fr) * 2002-10-09 2003-12-19 Agence Spatiale Europeenne Reflecteur d'antenne pliable et depliable, notamment pour une antenne de grande envergure destinee a des applications de telecommunications spatiales
US7138958B2 (en) * 2004-02-27 2006-11-21 Andrew Corporation Reflector antenna radome with backlobe suppressor ring and method of manufacturing
FR2887523B1 (fr) * 2005-06-22 2008-11-07 Eads Astrium Sas Soc Par Actio Structure legere deployable et rigidifiable apres deploiement, son procede de realisation, et son application a l'equipement d'un vehicule spatial
US20100313880A1 (en) * 2007-11-13 2010-12-16 Feng Shi Solar Concentrator
ES2441070T3 (es) * 2008-08-07 2014-01-31 Thales Alenia Space Italia S.P.A. Dispositivo de blindaje para aparatos ópticos y/o electrónicos, y vehículo espacial que comprende dicho dispositivo
US8794229B2 (en) 2011-06-15 2014-08-05 Feng Shi Solar concentrator
US9899743B2 (en) 2014-07-17 2018-02-20 Cubic Corporation Foldable radio wave antenna deployment apparatus for a satellite
US9960498B2 (en) 2014-07-17 2018-05-01 Cubic Corporation Foldable radio wave antenna
US9912070B2 (en) 2015-03-11 2018-03-06 Cubic Corporation Ground-based satellite communication system for a foldable radio wave antenna
US10916859B2 (en) * 2019-03-15 2021-02-09 Massachusetts Institute Of Technology Inflatable reflector antenna and related methods
RU201366U1 (ru) * 2020-02-04 2020-12-11 Александр Витальевич Лопатин Параболический трансформируемый торовый рефлектор
RU203899U1 (ru) * 2020-09-21 2021-04-26 Александр Витальевич Лопатин Надувное устройство раскрытия трансформируемого рефлектора зонтичного типа
US20240098515A1 (en) * 2022-09-15 2024-03-21 At&T Intellectual Property I, L.P. Automated Orienting of Customer Premises Equipment

Citations (5)

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Publication number Priority date Publication date Assignee Title
US2996212A (en) * 1959-08-20 1961-08-15 Jr William John O'sullivan Self supporting space vehicle
US3282533A (en) * 1962-08-07 1966-11-01 Raymond G Spain Rigidizable expandable structures and system
US3324000A (en) * 1964-06-18 1967-06-06 Colgate Palmolive Co 1, 4-benzodioxyl carbamates in skeletal muscle relaxation
US3354458A (en) * 1966-05-20 1967-11-21 Goodyear Aerospace Corp Wire-film space satellite
US3391882A (en) * 1964-03-11 1968-07-09 Keltec Ind Inc Erectable structure for a space environment

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US3224000A (en) * 1963-03-18 1965-12-14 Goodyear Aerospace Corp Communication satellite and method for making same
US3916418A (en) * 1972-06-22 1975-10-28 Itt Fiber-reinforced molded reflector with metallic reflecting layer
US4191604A (en) * 1976-01-07 1980-03-04 General Dynamics Corporation Pomona Division Method of constructing three-dimensionally curved, knit wire reflector
US4364053A (en) * 1980-09-18 1982-12-14 William Hotine Inflatable stressed skin microwave antenna
US4475109A (en) * 1982-01-25 1984-10-02 Rockwell International Corporation Inflatable antenna
US4550319A (en) * 1982-09-22 1985-10-29 Rca Corporation Reflector antenna mounted in thermal distortion isolation
JPS5997205A (ja) * 1982-11-26 1984-06-05 General Res Obu Erekutoronitsukusu:Kk サテライト・アンテナ

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2996212A (en) * 1959-08-20 1961-08-15 Jr William John O'sullivan Self supporting space vehicle
US3282533A (en) * 1962-08-07 1966-11-01 Raymond G Spain Rigidizable expandable structures and system
US3391882A (en) * 1964-03-11 1968-07-09 Keltec Ind Inc Erectable structure for a space environment
US3324000A (en) * 1964-06-18 1967-06-06 Colgate Palmolive Co 1, 4-benzodioxyl carbamates in skeletal muscle relaxation
US3354458A (en) * 1966-05-20 1967-11-21 Goodyear Aerospace Corp Wire-film space satellite

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
NASA CONTRACTOR REPORT, CR-1688, Band III, Februar 1971, Seiten 262,263,263a, Washington, US; "Antennas for space communication - deployable paraboloids" *

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3014417A1 (fr) * 2013-12-10 2015-06-12 Eads Europ Aeronautic Defence Nouvelle architecture de vehicule spatial
WO2015086970A1 (fr) * 2013-12-10 2015-06-18 Airbus Group Sas Nouvelle architecture de véhicule spatial
US10450092B2 (en) 2013-12-10 2019-10-22 Airbus Group Sas Spacecraft architecture having torus-shaped solar concentrator

Also Published As

Publication number Publication date
JPS61264901A (ja) 1986-11-22
US4755819A (en) 1988-07-05

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Inventor name: KOTACKA, KARL