EP0881703A1 - Stiff antenna and corresponding fabrication method - Google Patents

Stiff antenna and corresponding fabrication method Download PDF

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Publication number
EP0881703A1
EP0881703A1 EP98401277A EP98401277A EP0881703A1 EP 0881703 A1 EP0881703 A1 EP 0881703A1 EP 98401277 A EP98401277 A EP 98401277A EP 98401277 A EP98401277 A EP 98401277A EP 0881703 A1 EP0881703 A1 EP 0881703A1
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EP
European Patent Office
Prior art keywords
conductive
antenna
aircraft
antenna according
linear
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.)
Withdrawn
Application number
EP98401277A
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German (de)
French (fr)
Inventor
Patrice Raimbault
Jean-Luc Cornelis
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Tramec
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Tramec
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Publication of EP0881703A1 publication Critical patent/EP0881703A1/en
Withdrawn legal-status Critical Current

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    • 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
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q9/00—Electrically-short antennas having dimensions not more than twice the operating wavelength and consisting of conductive active radiating elements
    • H01Q9/04—Resonant antennas
    • H01Q9/30—Resonant antennas with feed to end of elongated active element, e.g. unipole
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q9/00—Electrically-short antennas having dimensions not more than twice the operating wavelength and consisting of conductive active radiating elements
    • H01Q9/04—Resonant antennas
    • H01Q9/30—Resonant antennas with feed to end of elongated active element, e.g. unipole
    • H01Q9/32—Vertical arrangement of element
    • H01Q9/36—Vertical arrangement of element with top loading

Definitions

  • the invention relates to a rigid antenna, more particularly intended to be mounted on an aircraft, in particular on a helicopter or on an airplane.
  • the invention also relates to a method of manufacturing an antenna according to the invention.
  • the invention is particularly useful for ensuring high communications frequency in the 2 to 30 MHz band.
  • wired antennas constituted by a cable have already been used in the past. stretched between several points outside the hull of an airplane or helicopter: although the wire antennas are light, their long length complicates their installation, especially in the case of small helicopters. In addition, these wired antennas are dangerous in case of cable breakage by risk winding in the rotor.
  • tubular antennas constituted by a rigid conductive tube of a determined length, carried by also rigid arms fixed to the hull of the aircraft.
  • Document FR 2 680 282 describes a tubular antenna of this type, comprising a tube carried by masts, the tube consisting of an insulating tubular support on which is helically wound a conductive tape externally protected by an insulating coating after winding on the tubular support.
  • This known antenna is generally satisfactory, but has a insufficient radiation in the high frequency range below 6 MHz.
  • the antenna adjustment device constituted by an adapter to capacitive coupling adjustable by ring adjustable in position does not allow a capacitive adaptation usable over the entire frequency band between 2 and 30 MHz.
  • the invention aims to remedy the drawbacks of the technique known in providing a new rigid antenna ensuring communications on all bands useful for aviation in the range between 2 and 30 MHz, presenting reduced length allowing easy installation on all types of aircraft.
  • the subject of the invention is a rigid antenna, intended to be mounted on an aircraft, comprising an outer protective covering made essentially of material substantially transparent to electromagnetic radiation, preferably of electrically insulating material, said outer protective envelope containing an internal conductive assembly comprising a plurality of elements linear conductive interconnected by a plurality of conductive elements wound on insulating supports, said internal conductor mounting being connected to the aircraft from inside support and fixing masts to the hull of the aircraft.
  • the outer protective envelope is made of material fiberglass composite.
  • the outer protective envelope is closed at both ends by end caps.
  • the envelope of external protection is provided with flanges for connection to the hull of an aircraft.
  • each element linear conductor is centered in each insulating support by at least one ring in electrically insulating material.
  • a rigid antenna according to the invention has a structure linear substantially cylindrical.
  • the mounting of the antenna on an aircraft is carried out in a known manner according to the document FR 2 680 282 by locking on a conductive arch of a mast head quick opening.
  • the antenna according to the invention comprises two conductive rings 1, 2.
  • the conductive ring 1 is located on the high frequency side, while the ring conductor 2 is located on the ground side.
  • an envelope 3 of external protection made of material transparent to radiation electromagnetic, preferably in fiberglass composite material.
  • the envelope 3 contains an internal conductive assembly comprising a plurality linear conductive elements 4a, 4b, 4c, 4d interconnected by a plurality of wound conductive elements 5a, 5b, 5c, on insulating supports 6, 7, 8.
  • Each linear conductive element 4a to 4d is made of light metal or an alloy light metal, preferably from a thin tube having a diameter of the order of a centimeter.
  • the sections of metal tube are connected between them by the insulating supports 6, 7, 8 and are centered inside these supports insulators by rings 9a to 9j of electrically insulating material, preferably in fiberglass composite material.
  • each linear conducting element 4a to 4d covers a low thickness of material with good electrical conductivity and thermal.
  • the outer half-perimeter is covered with each linear conducting element by an adhesive film of thickness less than the millimeter of a flexible beryllium copper strip.
  • This coating can also be carried out by shooping or by any other method of coating.
  • each insulating support 6 to 8 is produced by cutting glass fiber composite tube, the ends of which are surrounded by a conductive coating to ensure the electrical connection of all the elements of the conductive assembly.
  • each coiled conductive element 5a or 5b as well produced has two coaxial coils coupled in parallel and wound in direction reverse each other.
  • the large number of contiguous turns of enamelled copper wire is preferably between 80 and 150 turns, while the lower number of non-contiguous turns of externally insulated conductor is preferably included between 5 and 50 turns.
  • the winding diameter is preferably greater than 2 cm and roughly corresponds to the outside diameter of the insulating support 6 or 7.
  • Wedging rings 9a to 9j made of fiberglass composite are fixed to the tube linear conductor 4a to 4d by means of a metal screw embedded in a bore and screwed into a thread made in the linear conductive tube 4a to 4d.
  • the assembly of wedging or centering rings 9a to 9j to the insulating supports 6 to 8 correspondents is made by gluing with an Araldite type glue (trademark registered by the company under Swiss law CIBA).
  • the third coiled conductive element 5c is made by winding on the insulating support 8 of a number of non-contiguous turns of an insulated conductor externally according to a predetermined number between 40 and 120 turns.
  • the outer protective casing 3 preferably made of composite material fiberglass, either by assembling half-shells glued to each other using aforementioned adhesive or by successive assembly of tubular elements on a mandrel and fitting the conductive ring.
  • the second end piece 13 is shaped as clamping nut to be screwed onto a threaded rod 12 trapped at the end of the tube 4d and secured to this end by means of two screws 14, 15. After tightening and gluing of the assembly, the sealing is carried out by gluing the first end piece 16.
  • the two end caps (13 and 16) are advantageously made of light metal or light metal alloy externally insulated, by anodization or by application of a insulating coating.
  • the antenna thus produced has a substantially cylindrical linear structure of a diameter less than 5 cm.
  • a rigid antenna according to the invention has a structure folded contained in a profiled envelope.
  • the antenna is connected to the device by an antenna cable externally insulated passing through a conduit made in the outer casing 3 made of fiberglass composite material.
  • the outer protective envelope is provided with flanges 20 and 21 for connection and mounting on the hull of an aircraft. These connection flanges 20 and 21 can be externally insulated or conductive so as to ensure continuity electric with the hull of the aircraft.
  • Linear conducting elements 4a to 4c made by sections of light metal alloy tube are connected to sections 6, 7, 8a and 8b in composite fiberglass forming an insulating support for the elements wound conductors 5a to 5d similar to the wound conductive elements 5a to 5c described with reference to Figure 1.
  • the assembly of the linear conductive tubes to the insulating support tubes is carried out analogously by means of wedging rings 9 or by other means equivalent mechanical (screwing, gluing, press mounting).
  • the electrical connection can be made by soldering, shooping coating, by means of lugs or equivalent assembly.
  • the coiled conductive element 5c situated on the mass side included a single coil with a predetermined number of non-contiguous turns between 40 and 120 turns, while, in FIG. 2, the last two conductive elements wound 5c and 5d located on the mass side are substantially identical and include each a predetermined number of non-contiguous turns of insulated conductive wire externally between 5 and 60 turns and are interconnected by a length 22 of externally insulated conductive wire or cable less than 1 m.
  • the outer protective casing 3 extends between the conductive rings 1 and 2, while in the second mode of embodiment of the invention, the outer protective casing 3 extends between the two connection flanges 20 and 21 to the hull of the aircraft.
  • the assembly of the outer envelope around the conductive assembly thus produced is carried out by making a waterproof sheath. We can proceed by molding, injection, compression, pultrusion, or by other equivalent techniques.
  • the end caps 13 and 16 or the outer protrusions 23, 24 of the casing 3 can be profiled so aerodynamics, so as not to significantly increase the drag of the aircraft carrying the rigid antenna according to the invention.
  • a preferred embodiment of the invention is produced in the form of an antenna profiled according to an aerodynamic profile comprising an elongated body 30 secured to two masts 31, 32 for fixing to the hull of a aircraft.
  • This antenna has a double vertical and horizontal polarization providing remarkable omni-directional performance.
  • Each mast 31 or 32 has a fixing flange 31a or 32a to the shell of the aircraft, has a section 31b or 32b with an aerodynamic contour and includes an annular support 31c or 32c for engaging and securing the elongated body 30 with two masts 31 and 32
  • the antenna structure is essentially hollow, so as to protect all electrical connections and to connect the reception and transmission devices to through the hull of the aircraft passing through the interior of the masts 31 and 32 and the flanges 31a and 32a.
  • the internal conductive mounting of the antenna is therefore fully protected weathering by the streamlined and sealed external structure of the antenna.
  • the shell is drilled the aircraft at the locations provided for fixing the flanges 31a, 32a; we consolidate the honeycomb wall by resin injection and sealing is carried out, resilient material between the hull of the aircraft and each fixing flange 31a, 32a.
  • the assembly thus produced is particularly resistant and secures the antenna to the hull of the aircraft to become one with it and not to significantly modify the aerodynamic characteristics of the aircraft.
  • the aerodynamic profile of the antenna is also obtained thanks to the ends 33a, 33b tapered, possibly produced in the form of end pieces assembled by screwing or bonding ensuring weathertightness.
  • the envelope being hollow, the internal pressure and temperature of the antenna are pressure and temperature of the interior of the aircraft with which the inside of the antenna is in communication.
  • the internal conductor mounting on the antenna is connected on the high frequency side to the device by an insulated antenna cable C externally and passing inside the flange 32a, and through the shell of the aircraft not shown.
  • the aforementioned cable C is connected to a conductive element linear 34a, advantageously tubular, connected to and surrounded by a conductive element wound 35a from a first small number of turns preferably between 2 and 20 of antenna cable C connected to a second wound conductive element 35b with from the same cable on a second number turns preferably between 5 and 100.
  • the second conductive element 35b is wound on an insulating support 36 simultaneously ensuring the centering and alignment of the conductive element tubular 34a with another conductive element 34b advantageously tubular;
  • this insulating support 36 advantageously made of fiberglass composite material advantageously has a hollow dumbbell shape with a solid part 36a forming a stop for a tubular conductive element such as 34b.
  • the tubular conductive element 34b is advantageously coated at least partially of a small thickness of material having good conductivity electrical and thermal, for example by covering the outer half perimeter of element 34b by a film 40 of beryllium copper with a thickness of less than 2mm.
  • the tubular conductive element 34b is electrically connected to a conductive element wound 35c from an antenna cable on a third number of turns, included preferably between 3 and 50.
  • the wound conductor element 35c contains a coil mounted in parallel and wound in the opposite direction of the turns of said third number; this coil in reverse parallel mounting is carried out by winding on a first large number of turns contiguous, between 50 and 300, of externally insulated wire preferably low diameter less than 1.5mm.
  • the conductive element 35c wound on the insulating support 37 is electrically connected to a tubular conductive element 34c, preferably coated at least partially externally of a small thickness of material 40 having good electrical and thermal conductivity.
  • the insulating support 37 in the form of a hollow dumbbell has a solid part 37a forming a stop for the tubular elements 34b and 34c centered in the support in hollow dumbbell shape 37.
  • the assembly carried out at this stage constitutes an elongated mechanical assembly and conductor which can be inserted into the accessible cavity when the end pieces 33a and / or 33b are not mounted: this assembly is centered at both ends by rings 38, 39 of insulating material, preferably of fiberglass composite.
  • the conductive element wound 35d comprises an antenna cable wound on a fourth number of turns, preferably between 4 and 80, in parallel with a winding in the opposite direction of a second large number of contiguous turns, including between 50 and 300, of an externally insulated wire, preferably of small diameter less than 1.5mm.
  • this parallel mounting is electrically short-circuited at ends by a material of good electrical and thermal conductivity: the support insulator 42 is for example coated for this purpose with a film 40 of small thickness of copper beryllium which is electrically connected to the two ends of the element 35d.
  • the film 40 also provides the electrical connection with a ground braid 43 to be connected to the hull of the aircraft and to one end coaxial 44, for example of the type corresponding to the designation RG 214 UKX 13 with an impedance between 20 and 100 ⁇ .
  • this very light antenna of equal length or less than 2m, is particularly suitable for band operation single lateral (SSB) over the entire frequency band between 2 and 30 MHz.
  • SSB band operation single lateral

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  • Physics & Mathematics (AREA)
  • Engineering & Computer Science (AREA)
  • Astronomy & Astrophysics (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Physics & Mathematics (AREA)
  • Remote Sensing (AREA)
  • Details Of Aerials (AREA)

Abstract

The rigid aerial, mounted on an aircraft, comprises an envelope (3,30) offering external protection, made of a material which is transparent to electromagnetic radiation, and which is preferably also electrically insulating. This outer envelope contains an assembly of internal conductors consisting of a number of linear elements (4a-d). The conductor elements are linked together by a number of conducting coils (5a-c) attached to insulating supports (6-8). The whole assembly is linked to the body of the aircraft by support posts which carry the structure and provide anchorage to the shell of the aircraft. The conductor elements are made of a light metal, or a light metal alloy, coated with a material of good electrical conductivity and good thermal conductivity.

Description

L'invention est relative à une antenne rigide, plus particulièrement destinée à être montée sur un aéronef, en particulier sur un hélicoptère ou sur un avion.The invention relates to a rigid antenna, more particularly intended to be mounted on an aircraft, in particular on a helicopter or on an airplane.

L'invention est également relative à un procédé de fabrication d'une antenne selon l'invention.The invention also relates to a method of manufacturing an antenna according to the invention.

L'invention est particulièrement utile pour assurer les communications en haute fréquence dans la bande des 2 à 30 MHz.The invention is particularly useful for ensuring high communications frequency in the 2 to 30 MHz band.

A cet effet, on a déjà utilisé par le passé des antennes filaires constituées par un câble tendu entre plusieurs points à l'extérieur de la coque d'un avion ou d'un hélicoptère : bien que les antennes filaires soient légères, leur longueur importante complique leur installation, notamment dans le cas d'hélicoptères de dimensions réduites. En outre, ces antennes filaires s'avèrent dangereuses en cas de rupture de câble par risque d'enroulement dans le rotor.For this purpose, wired antennas constituted by a cable have already been used in the past. stretched between several points outside the hull of an airplane or helicopter: although the wire antennas are light, their long length complicates their installation, especially in the case of small helicopters. In addition, these wired antennas are dangerous in case of cable breakage by risk winding in the rotor.

Pour remplacer l'antenne filaire, on a proposé d'utiliser des antennes tubulaires constituées par un tube conducteur rigide d'une longueur déterminée, porté par des bras également rigides fixés à la coque de l'aéronef. Le document FR 2 680 282 décrit une antenne tubulaire de ce type, comportant un tube porté par des mâts, le tube étant constitué d'un support tubulaire isolant sur lequel est enroulé en hélice un ruban conducteur protégé extérieurement par un revêtement isolant après enroulement sur le support tubulaire.To replace the wire antenna, it has been proposed to use tubular antennas constituted by a rigid conductive tube of a determined length, carried by also rigid arms fixed to the hull of the aircraft. Document FR 2 680 282 describes a tubular antenna of this type, comprising a tube carried by masts, the tube consisting of an insulating tubular support on which is helically wound a conductive tape externally protected by an insulating coating after winding on the tubular support.

Cette antenne connue donne généralement satisfaction, mais présente un rayonnement insuffisant dans le domaine de haute fréquence situé en-dessous de 6 MHz. En outre, le dispositif de réglage de l'antenne constitué par un adaptateur à couplage capacitif ajustable par bague réglable en position ne permet pas de réaliser une adaptation capacitive utilisable sur toute la bande de fréquence comprise entre 2 et 30 MHz.This known antenna is generally satisfactory, but has a insufficient radiation in the high frequency range below 6 MHz. In addition, the antenna adjustment device constituted by an adapter to capacitive coupling adjustable by ring adjustable in position does not allow a capacitive adaptation usable over the entire frequency band between 2 and 30 MHz.

L'invention a pour but de remédier aux inconvénients de la technique connue en fournissant une nouvelle antenne rigide assurant les communications sur toutes les bandes utiles pour l'aviation dans la plage comprise entre 2 et 30 MHz, présentant une longueur réduite permettant une installation facile sur tous types d'aéronefs. The invention aims to remedy the drawbacks of the technique known in providing a new rigid antenna ensuring communications on all bands useful for aviation in the range between 2 and 30 MHz, presenting reduced length allowing easy installation on all types of aircraft.

L'invention a pour objet une antenne rigide, destinée à être montée sur un aéronef, comportant une enveloppe de protection extérieure réalisée essentiellement en matériau sensiblement transparent au rayonnement électromagnétique, de préférence en matériau électriquement isolant, ladite enveloppe de protection extérieure contenant un montage conducteur interne comprenant une pluralité d'éléments linéaires conducteurs reliés entre eux par une pluralité d'éléments conducteurs bobinés sur des supports isolants, ledit montage conducteur interne étant relié à l'aéronef par l'intérieur de mâts de support et de fixation à la coque de l'aéronef.The subject of the invention is a rigid antenna, intended to be mounted on an aircraft, comprising an outer protective covering made essentially of material substantially transparent to electromagnetic radiation, preferably of electrically insulating material, said outer protective envelope containing an internal conductive assembly comprising a plurality of elements linear conductive interconnected by a plurality of conductive elements wound on insulating supports, said internal conductor mounting being connected to the aircraft from inside support and fixing masts to the hull of the aircraft.

Selon d'autres caractéristiques de l'invention :

  • au moins un élément conducteur linéaire est réalisé en métal léger ou en alliage métallique léger, revêtu au moins partiellement d'une épaisseur faible de matériau présentant une bonne conductivité électrique et thermique;
  • au moins un élément conducteur bobiné comporte deux bobines, dont la première comporte un premier grand nombre de spires jointives et dont la deuxième, bobinée en sens inverse de la première, comporte un second nombre inférieur de spires non jointives, de fil ou câble conducteur isolé extérieurement ;
  • au moins un élément conducteur bobiné comporte un nombre prédéterminé de spires non jointives, de fil ou câble conducteur isolé extérieurement.
  • selon une première variante de réalisation de l'invention, l'antenne présente une structure linéaire sensiblement cylindrique.
  • selon une deuxième variante de réalisation de l'invention, l'antenne présente une structure repliée contenue dans une enveloppe profilée.
According to other characteristics of the invention:
  • at least one linear conductive element is made of light metal or a light metal alloy, at least partially coated with a small thickness of material having good electrical and thermal conductivity;
  • at least one coiled conductive element comprises two coils, the first of which comprises a first large number of contiguous turns and the second of which, wound in opposite direction to the first, comprises a second lower number of non-contiguous turns, of insulated conductive wire or cable externally;
  • at least one coiled conductive element has a predetermined number of non-contiguous turns, externally insulated conductive wire or cable.
  • according to a first alternative embodiment of the invention, the antenna has a substantially cylindrical linear structure.
  • according to a second alternative embodiment of the invention, the antenna has a folded structure contained in a profiled envelope.

De préférence, l'enveloppe de protection extérieure est réalisée en matériau composite fibre de verre.Preferably, the outer protective envelope is made of material fiberglass composite.

Dans la première variante de réalisation, l'enveloppe de protection extérieure est obturée aux deux extrémités par des embouts.In the first alternative embodiment, the outer protective envelope is closed at both ends by end caps.

Dans les deuxième et troisième variantes de réalisation de l'invention, l'enveloppe de protection extérieure est munie de brides de raccordement à la coque d'un aéronef. In the second and third alternative embodiments of the invention, the envelope of external protection is provided with flanges for connection to the hull of an aircraft.

Avantageusement, dans les variantes de réalisation décrites, chaque élément conducteur linéaire est centré dans chaque support isolant par au moins une bague en matériau électriquement isolant.Advantageously, in the embodiments described, each element linear conductor is centered in each insulating support by at least one ring in electrically insulating material.

L'invention est également relative à un procédé de fabrication d'une antenne rigide comportant les étapes suivantes :

  • a) prévoir au moins une bague ou moyen de calage pour des éléments conducteurs linéaires;
  • b) associer chaque bague ou moyen de calage à un support isolant ;
  • c) bobiner au moins un élément conducteur sur au moins un support isolant, pour réaliser au moins un élément conducteur bobiné ;
  • d) assurer le raccordement électrique des éléments conducteurs linéaires et bobinés selon un montage conducteur ;
  • e) revêtir ledit montage conducteur d'une enveloppe de protection extérieure réalisée essentiellement en matériau sensiblement transparent au rayonnement électromagnétique.
    • The invention also relates to a method for manufacturing a rigid antenna comprising the following steps:
  • a) provide at least one ring or wedging means for linear conductive elements;
  • b) associate each ring or wedging means with an insulating support;
  • c) winding at least one conductive element on at least one insulating support, in order to produce at least one wound conductive element;
  • d) ensuring the electrical connection of the linear and wound conductive elements according to a conductive assembly;
  • e) coating said conductive assembly with an external protective envelope made essentially of material substantially transparent to electromagnetic radiation.

    • L'invention sera mieux comprise grâce à la description qui va suivre, donnée à titre d'exemple non limitatif en référence aux dessins annexés dans lesquels :

    • la figure 1 représente une vue en coupe avec arrachements partiels d'une première variante de réalisation de l'invention.
    • la figure 2 représente une vue en coupe avec arrachements partiels d'une deuxième variante de réalisation de l'invention.
    • la figure 3 représente schématiquement une vue en perspective d'une troisième variante de réalisation de l'invention.
    • les figures 4a, 4b et 4c représentent schématiquement un ensemble de vues partielles en coupe longitudinale de l'antenne de la figure 3.
    The invention will be better understood from the description which follows, given by way of nonlimiting example with reference to the appended drawings in which:
    • Figure 1 shows a sectional view with partial cutaway of a first alternative embodiment of the invention.
    • Figure 2 shows a sectional view with partial cutaway of a second embodiment of the invention.
    • FIG. 3 schematically represents a perspective view of a third alternative embodiment of the invention.
    • FIGS. 4a, 4b and 4c schematically represent a set of partial views in longitudinal section of the antenna of FIG. 3.

    En référence à la figure 1, une antenne rigide selon l'invention présente une structure linéaire sensiblement cylindrique. Referring to Figure 1, a rigid antenna according to the invention has a structure linear substantially cylindrical.

    Le montage de l'antenne sur un aéronef est effectué de manière connue selon le document FR 2 680 282 par verrouillage sur un arceau conducteur d'une tête de mât à ouverture rapide.The mounting of the antenna on an aircraft is carried out in a known manner according to the document FR 2 680 282 by locking on a conductive arch of a mast head quick opening.

    A cet effet, l'antenne selon l'invention comporte deux bagues conductrices 1, 2. La bague conductrice 1 est située du côté haute fréquence, tandis que la bague conductrice 2 est située du côté masse.To this end, the antenna according to the invention comprises two conductive rings 1, 2. The conductive ring 1 is located on the high frequency side, while the ring conductor 2 is located on the ground side.

    Dans l'espace compris entre les bagues conductrices 1, 2, s'étend une enveloppe 3 de protection extérieure réalisée en matériau transparent au rayonnement électromagnétique, de préférence en matériau composite fibre de verre.In the space between the conductive rings 1, 2, extends an envelope 3 of external protection made of material transparent to radiation electromagnetic, preferably in fiberglass composite material.

    L'enveloppe 3 contient un montage conducteur interne comprenant une pluralité d'éléments conducteurs linéaires 4a, 4b, 4c, 4d reliés entre eux par une pluralité d'éléments conducteurs bobinés 5a, 5b, 5c, sur des supports isolants 6, 7, 8.The envelope 3 contains an internal conductive assembly comprising a plurality linear conductive elements 4a, 4b, 4c, 4d interconnected by a plurality of wound conductive elements 5a, 5b, 5c, on insulating supports 6, 7, 8.

    Chaque élément conducteur linéaire 4a à 4d, est réalisé en métal léger ou en alliage métallique léger, de préférence à partir d'un tube de faible épaisseur présentant un diamètre de l'ordre du centimètre. Les tronçons de tube métallique sont raccordés entre eux par les supports isolants 6, 7, 8 et sont centrés à l'intérieur de ces supports isolants par des bagues 9a à 9j en matériau électriquement isolant, de préférence en matériau composite fibre de verre.Each linear conductive element 4a to 4d is made of light metal or an alloy light metal, preferably from a thin tube having a diameter of the order of a centimeter. The sections of metal tube are connected between them by the insulating supports 6, 7, 8 and are centered inside these supports insulators by rings 9a to 9j of electrically insulating material, preferably in fiberglass composite material.

    Pour assurer une bonne continuité électrique et une bonne répartition thermique, on revêt au moins partiellement chaque élément conducteur linéaire 4a à 4d d'une épaisseur faible de matériau présentant une bonne conductivité électrique et thermique. Avantageusement, à cet effet, on recouvre le demi-périmètre extérieur de chaque élément conducteur linéaire par un film 10 adhésif d'épaisseur inférieure au millimètre d'une bande souple de cuivre au béryllium.To ensure good electrical continuity and good thermal distribution, we at least partially covers each linear conducting element 4a to 4d with a low thickness of material with good electrical conductivity and thermal. Advantageously, for this purpose, the outer half-perimeter is covered with each linear conducting element by an adhesive film of thickness less than the millimeter of a flexible beryllium copper strip.

    On peut également effectuer ce revêtement par shoopage ou par tout autre mode de revêtement.This coating can also be carried out by shooping or by any other method of coating.

    Sur le premier support isolant 6, on bobine un premier grand nombre de spires jointives de fil fin de cuivre émaillé extérieurement de manière à réaliser une première bobine ; puis on bobine en sens inverse un second nombre inférieur de spires non jointives de câble conducteur isolé extérieurement De préférence, le diamètre du fil fm de cuivre émaillé est inférieur à 1 mm, tandis que la section du câble conducteur est supérieure à 2 mm2. Après réalisation des deux bobines sur le premier support isolant 6, on effectue le raccordement électrique entre les bobines montées en parallèle et l'élément conducteur linéaire par revêtement d'une épaisseur faible de matériau conducteur : à cet effet, on utilise avantageusement la bande adhésive de cuivre au béryllium précitée pour réaliser la continuité électrique en 11a et 11b en entourant complètement le support isolant 6. De préférence, chaque support isolant 6 à 8 est réalisé par tronçonnage de tube en composite fibre de verre dont les extrémités sont entourées d'un revêtement conducteur pour assurer le raccordement électrique de l'ensemble des éléments du montage conducteur.On the first insulating support 6, a first large number of contiguous turns of externally enamelled copper wire are wound in order to produce a first coil; then a second lower number of non-contiguous turns of externally insulated conductor cable is wound in the opposite direction. Preferably, the diameter of the fm enamelled copper wire is less than 1 mm, while the section of the conductor cable is greater than 2 mm 2 . After the two coils have been produced on the first insulating support 6, the electrical connection is made between the coils mounted in parallel and the linear conductive element by coating a small thickness of conductive material: for this purpose, the adhesive tape is advantageously used. of beryllium copper mentioned above to achieve electrical continuity in 11a and 11b by completely surrounding the insulating support 6. Preferably, each insulating support 6 to 8 is produced by cutting glass fiber composite tube, the ends of which are surrounded by a conductive coating to ensure the electrical connection of all the elements of the conductive assembly.

    Sur le deuxième tronçon 7 de tube composite fibre de verre, on réalise un élément conducteur bobiné sensiblement identique à celui réalisé sur le tronçon 6, par un premier enroulement de spires jointives de fil conducteur émaillé suivi d'un deuxième enroulement de spires non jointives de câbles conducteurs isolés extérieurement Dans chaque cas, chaque élément conducteur bobiné 5a ou 5b ainsi réalisé comporte deux bobines coaxiales couplées en parallèle et bobinées en sens inverse l'une de l'autre. Le grand nombre de spires jointives de fil de cuivre émaillé est de préférence compris entre 80 et 150 spires, tandis que le nombre inférieur de spires non jointives de conducteur isolé extérieurement est de préférence compris entre 5 et 50 spires. Le diamètre de bobinage est de préférence supérieur à 2 cm et correspond sensiblement au diamètre extérieur du support isolant 6 ou 7.On the second section 7 of fiberglass composite tube, an element is produced coiled conductor substantially identical to that produced on section 6, by a first winding of contiguous turns of enamelled conductive wire followed by a second winding of non-contiguous turns of insulated conductive cables externally In each case, each coiled conductive element 5a or 5b as well produced has two coaxial coils coupled in parallel and wound in direction reverse each other. The large number of contiguous turns of enamelled copper wire is preferably between 80 and 150 turns, while the lower number of non-contiguous turns of externally insulated conductor is preferably included between 5 and 50 turns. The winding diameter is preferably greater than 2 cm and roughly corresponds to the outside diameter of the insulating support 6 or 7.

    Les bagues de calage 9a à 9j en composite fibre de verre sont fixées sur le tube conducteur linéaire 4a à 4d au moyen d'une vis métallique noyée dans un alésage et vissée dans un taraudage pratiqué dans le tube conducteur linéaire 4a à 4d. L'assemblage des bagues de calage ou de centrage 9a à 9j aux supports isolants 6 à 8 correspondants est effectué par collage au moyen d'une colle du genre Araldite (marque déposée par la société de droit suisse CIBA).Wedging rings 9a to 9j made of fiberglass composite are fixed to the tube linear conductor 4a to 4d by means of a metal screw embedded in a bore and screwed into a thread made in the linear conductive tube 4a to 4d. The assembly of wedging or centering rings 9a to 9j to the insulating supports 6 to 8 correspondents is made by gluing with an Araldite type glue (trademark registered by the company under Swiss law CIBA).

    Le troisième élément conducteur bobiné 5c est effectué par enroulement sur le support isolant 8 d'un nombre de spires non jointives d'un conducteur isolé extérieurement selon un nombre prédéterminé compris entre 40 et 120 spires.The third coiled conductive element 5c is made by winding on the insulating support 8 of a number of non-contiguous turns of an insulated conductor externally according to a predetermined number between 40 and 120 turns.

    Après assemblage de proche en proche, et établissement du raccordement électrique de tous les éléments 1, 4a, 5a, 4b, 5b, 4c, 5c, 4d et 2 dans cet ordre pour former un montage conducteur reliant les bagues conductrices 1 et 2, on met en place l'enveloppe 3 de protection extérieure réalisée de préférence en matériau composite fibre de verre, soit par assemblage de demi-coquilles collées l'une à l'autre au moyen d'une colle précitée ou par assemblage successif d'éléments tubulaires sur un mandrin et mise en place de la bague conductrice. Le deuxième embout 13 est conformé en écrou de serrage à visser sur une tige filetée 12 prisonnière de l'extrémité du tube 4d et solidarisée à cette extrémité au moyen de deux vis 14, 15. Après serrage et collage de l'ensemble, l'étanchéité est réalisée par collage du premier embout 16. Les deux embouts d'extrémité (13 et 16) sont avantageusement réalisés en métal léger ou en alliage métallique léger isolé extérieurement, par anodisation ou par application d'un revêtement isolant.After assembly step by step, and establishment of the electrical connection of all elements 1, 4a, 5a, 4b, 5b, 4c, 5c, 4d and 2 in this order to form a conductor mounting connecting the conductive rings 1 and 2, we put in place the outer protective casing 3 preferably made of composite material fiberglass, either by assembling half-shells glued to each other using aforementioned adhesive or by successive assembly of tubular elements on a mandrel and fitting the conductive ring. The second end piece 13 is shaped as clamping nut to be screwed onto a threaded rod 12 trapped at the end of the tube 4d and secured to this end by means of two screws 14, 15. After tightening and gluing of the assembly, the sealing is carried out by gluing the first end piece 16. The two end caps (13 and 16) are advantageously made of light metal or light metal alloy externally insulated, by anodization or by application of a insulating coating.

    L'antenne ainsi réalisée présente une structure linéaire sensiblement cylindrique d'un diamètre inférieur à 5 cm.The antenna thus produced has a substantially cylindrical linear structure of a diameter less than 5 cm.

    En référence à la figure 2, une antenne rigide selon l'invention présente une structure repliée contenue dans une enveloppe profilée.Referring to Figure 2, a rigid antenna according to the invention has a structure folded contained in a profiled envelope.

    Les chiffres de référence identiques aux chiffres de la figure 1 désignent des éléments identiques ou fonctionnellement équivalents aux éléments de la figure 1.The reference numbers identical to the figures in FIG. 1 designate elements identical or functionally equivalent to the elements in FIG. 1.

    Du côté haute fréquence, l'antenne est raccordée à l'appareil par un câble d'antenne isolé extérieurement passant à travers un conduit réalisé dans l'enveloppe extérieure 3 en matériau composite fibre de verre.On the high frequency side, the antenna is connected to the device by an antenna cable externally insulated passing through a conduit made in the outer casing 3 made of fiberglass composite material.

    L'enveloppe de protection extérieure est munie de brides 20 et 21 de raccordement et de montage sur la coque d'un aéronef. Ces brides de raccordement 20 et 21 peuvent être isolées extérieurement ou conductrices de manière à assurer une continuité électrique avec la coque de l'aéronef. Les éléments conducteurs linéaires 4a à 4c réalisés par tronçons de tube en alliage métallique léger sont raccordés à des tronçons 6, 7, 8a et 8b en fibre de verre composite formant support isolant pour les éléments conducteurs bobinés 5a à 5d analogues aux éléments conducteurs bobinés 5a à 5c décrits en référence à la figure 1.The outer protective envelope is provided with flanges 20 and 21 for connection and mounting on the hull of an aircraft. These connection flanges 20 and 21 can be externally insulated or conductive so as to ensure continuity electric with the hull of the aircraft. Linear conducting elements 4a to 4c made by sections of light metal alloy tube are connected to sections 6, 7, 8a and 8b in composite fiberglass forming an insulating support for the elements wound conductors 5a to 5d similar to the wound conductive elements 5a to 5c described with reference to Figure 1.

    L'assemblage des tubes conducteurs linéaires aux tubes supports isolants s'effectue de manière analogue au moyen de bagues de calage 9 ou par d'autres moyens mécaniques équivalents (vissage, collage, montage à la presse). The assembly of the linear conductive tubes to the insulating support tubes is carried out analogously by means of wedging rings 9 or by other means equivalent mechanical (screwing, gluing, press mounting).

    Le raccordement électrique peut se faire par brasage, revêtement du genre shoopage, au moyen de cosses ou d'assemblage équivalent.The electrical connection can be made by soldering, shooping coating, by means of lugs or equivalent assembly.

    Sur la figure 1, l'élément conducteur bobiné 5c situé du côté masse comportait une bobine unique avec un nombre prédéterminé de spires non jointives compris entre 40 et 120 spires, tandis que, sur la figure 2, les deux derniers éléments conducteurs bobinés 5c et 5d situés du côté masse sont sensiblement identiques et comportent chacun un nombre prédéterminé de spires non jointives de fil conducteur isolé extérieurement compris entre 5 et 60 spires et sont reliés entre eux par une longueur 22 de fil ou câble conducteur isolé extérieurement inférieure à 1 m.In FIG. 1, the coiled conductive element 5c situated on the mass side included a single coil with a predetermined number of non-contiguous turns between 40 and 120 turns, while, in FIG. 2, the last two conductive elements wound 5c and 5d located on the mass side are substantially identical and include each a predetermined number of non-contiguous turns of insulated conductive wire externally between 5 and 60 turns and are interconnected by a length 22 of externally insulated conductive wire or cable less than 1 m.

    Dans les deux cas, l'antenne rigide selon l'invention est de préférence fabriquée à l'aide d'un procédé comportant les étapes suivantes :

  • a) monter au moins une bague de calage sur un tube conducteur linéaire ;
  • b) assembler chaque bague de calage à un support isolant ;
  • c) bobiner au moins un élément conducteur sur au moins un support isolant pour réaliser au moins un élément conducteur bobiné ;
  • d) assurer le raccordement électrique des éléments conducteurs linéaires et bobinés selon un montage conducteur ;
  • e) revêtir ledit montage conducteur d'une enveloppe de protection extérieure réalisée essentiellement en matériau composite fibre de verre.
    • In both cases, the rigid antenna according to the invention is preferably manufactured using a method comprising the following steps:
  • a) mounting at least one timing ring on a linear conductive tube;
  • b) assemble each setting ring to an insulating support;
  • c) winding at least one conductive element on at least one insulating support to produce at least one coiled conductive element;
  • d) ensuring the electrical connection of the linear and wound conductive elements according to a conductive assembly;
  • e) coating said conductive assembly with an outer protective envelope made essentially of fiberglass composite material.

    • Dans la première variante de réalisation, l'enveloppe 3 de protection extérieure s'étend entre les bagues conductrices 1 et 2, tandis que dans le deuxième mode de réalisation de l'invention, l'enveloppe 3 de protection extérieure s'étend entre les deux brides de raccordement 20 et 21 à la coque de l'aéronef.In the first variant, the outer protective casing 3 extends between the conductive rings 1 and 2, while in the second mode of embodiment of the invention, the outer protective casing 3 extends between the two connection flanges 20 and 21 to the hull of the aircraft.

    L'assemblage de l'enveloppe extérieure autour du montage conducteur ainsi réalisé s'effectue par réalisation d'un fourreau étanche. On peut procéder par moulage, injection, compression, pultrusion, ou par d'autres techniques équivalentes.The assembly of the outer envelope around the conductive assembly thus produced is carried out by making a waterproof sheath. We can proceed by molding, injection, compression, pultrusion, or by other equivalent techniques.

    Comme on le voit, dans les deux cas, les embouts d'extrémité 13 et 16 ou les protubérances extérieures 23, 24 de l'enveloppe 3 peuvent être profilés de manière aérodynamique, de manière à ne pas augmenter notablement la traínée de l'aéronef portant l'antenne rigide selon l'invention. As can be seen, in both cases, the end caps 13 and 16 or the outer protrusions 23, 24 of the casing 3 can be profiled so aerodynamics, so as not to significantly increase the drag of the aircraft carrying the rigid antenna according to the invention.

    L'invention décrite en référence à deux modes de réalisation particuliers, n'y est nullement limitée, mais couvre au contraire toute modification de structure et toute variante de réalisation dans le cadre et l'esprit de l'invention.The invention described with reference to two particular embodiments, is not in no way limited, but on the contrary covers any structural modification and any variant embodiment within the scope and spirit of the invention.

    Ainsi, en référence à la figure 3, un mode préféré de réalisation de l'invention est réalisé sous forme d'une antenne profilée selon un profil aérodynamique comportant un corps allongé 30 solidarisé à deux mâts 31, 32 de fixation sur la coque d'un aéronef.Thus, with reference to FIG. 3, a preferred embodiment of the invention is produced in the form of an antenna profiled according to an aerodynamic profile comprising an elongated body 30 secured to two masts 31, 32 for fixing to the hull of a aircraft.

    Cette antenne présente une double polarisation verticale et horizontale fournissant des performances remarquables d'omnidirectionalité.This antenna has a double vertical and horizontal polarization providing remarkable omni-directional performance.

    Chaque mât 31 ou 32 comporte une bride de fixation 31a ou 32a à la coque de l'aéronef, présente une section 31b ou 32b avec un contour aérodynamique et comporte un support annulaire 31c ou 32c d'engagement et de solidarisation du corps allongé 30 aux deux mâts 31 et 32Each mast 31 or 32 has a fixing flange 31a or 32a to the shell of the aircraft, has a section 31b or 32b with an aerodynamic contour and includes an annular support 31c or 32c for engaging and securing the elongated body 30 with two masts 31 and 32

    La structure de l'antenne est essentiellement creuse, de manière à protéger toutes les connexions électriques et à raccorder les appareils de réception et de transmission à travers la coque de l'aéronef en passant par l'intérieur des mâts 31 et 32 et des brides 31a et 32a.The antenna structure is essentially hollow, so as to protect all electrical connections and to connect the reception and transmission devices to through the hull of the aircraft passing through the interior of the masts 31 and 32 and the flanges 31a and 32a.

    Le montage conducteur interne de l'antenne est par conséquent entièrement protégé des intempéries par la structure extérieure carénée et étanche de l'antenne.The internal conductive mounting of the antenna is therefore fully protected weathering by the streamlined and sealed external structure of the antenna.

    Pour assurer une étanchéité totale par rapport à l'extérieur, on perce la coque de l'aéronef aux endroits prévus pour la fixation des brides 31a, 32a; on consolide la paroi en nids d'abeille par injection de résine et on réalise une étanchéité, en matériau résilient entre la coque de l'aéronef et chaque bride de fixation 31a, 32a.To ensure total tightness from the outside, the shell is drilled the aircraft at the locations provided for fixing the flanges 31a, 32a; we consolidate the honeycomb wall by resin injection and sealing is carried out, resilient material between the hull of the aircraft and each fixing flange 31a, 32a.

    Le montage ainsi réalisé est particulièrement résistant et solidarise l'antenne à la coque de l'aéronef pour faire corps avec celle-ci et ne pas modifier notablement les caractéristiques aérodynamiques de l'aéronef.The assembly thus produced is particularly resistant and secures the antenna to the hull of the aircraft to become one with it and not to significantly modify the aerodynamic characteristics of the aircraft.

    Le profil aérodynamique de l'antenne est également obtenu grâce à des extrémités 33a, 33b fuselées, éventuellement réalisées sous formes d'embouts assemblés par vissage ou collage assurant une étanchéité aux intempéries. The aerodynamic profile of the antenna is also obtained thanks to the ends 33a, 33b tapered, possibly produced in the form of end pieces assembled by screwing or bonding ensuring weathertightness.

    L'enveloppe étant creuse, la pression et la température intérieures de l'antenne sont voisines de la pression et de la température de l'intérieur de l'aéronef avec lequel l'intérieur de l'antenne est en communication.The envelope being hollow, the internal pressure and temperature of the antenna are pressure and temperature of the interior of the aircraft with which the inside of the antenna is in communication.

    En référence aux figures 4a à 4c, le montage conducteur interne à l'antenne est raccordée du côté haute fréquence à l'appareil par un câble C d'antenne isolé extérieurement et passant à l'intérieur de la bride 32a, et à travers la coque de l'aéronef non représentée. Le câble C précité est relié à un élément conducteur linéaire 34a, avantageusement tubulaire, relié à et entouré par un élément conducteur bobiné 35a à partir d'un premier faible nombre de spires compris de préférence entre 2 et 20 de câble C d'antenne relié à un deuxième élément conducteur bobiné 35b à partir du même câble sur un deuxième nombre se spires compris de préférence entre 5 et 100.With reference to FIGS. 4a to 4c, the internal conductor mounting on the antenna is connected on the high frequency side to the device by an insulated antenna cable C externally and passing inside the flange 32a, and through the shell of the aircraft not shown. The aforementioned cable C is connected to a conductive element linear 34a, advantageously tubular, connected to and surrounded by a conductive element wound 35a from a first small number of turns preferably between 2 and 20 of antenna cable C connected to a second wound conductive element 35b with from the same cable on a second number turns preferably between 5 and 100.

    De préférence, le deuxième élément conducteur 35b est bobiné sur un support isolant 36 assurant simultanément le centrage et l'alignement de l'élément conducteur tubulaire 34a avec un autre élément conducteur 34b avantageusement tubulaire ; ce support isolant 36 avantageusement réalisé en matériau composite fibre de verre présente avantageusement une forme en haltère creuse avec une partie pleine 36a formant butée pour un élément conducteur tubulaire tel que 34b.Preferably, the second conductive element 35b is wound on an insulating support 36 simultaneously ensuring the centering and alignment of the conductive element tubular 34a with another conductive element 34b advantageously tubular; this insulating support 36 advantageously made of fiberglass composite material advantageously has a hollow dumbbell shape with a solid part 36a forming a stop for a tubular conductive element such as 34b.

    L'élément conducteur tubulaire 34b est avantageusement revêtu au moins partiellement d'une épaisseur faible de matériau présentant une bonne conductivité électrique et thermique, par exemple en recouvrant le demi périmètre extérieur de l'élément 34b par un film 40 de cuivre au béryllium d'épaisseur inférieure à 2mm.The tubular conductive element 34b is advantageously coated at least partially of a small thickness of material having good conductivity electrical and thermal, for example by covering the outer half perimeter of element 34b by a film 40 of beryllium copper with a thickness of less than 2mm.

    L'élément conducteur tubulaire 34b est relié électriquement à un élément conducteur bobiné 35c à partir d'un câble d'antenne sur un troisième nombre de spires, compris de préférence entre 3 et 50.The tubular conductive element 34b is electrically connected to a conductive element wound 35c from an antenna cable on a third number of turns, included preferably between 3 and 50.

    L'élément conducteur bobiné 35c contient une bobine montée en parallèle et bobinée en sens inverse des spires dudit troisième nombre; cette bobine en sens inverse montée en parallèle est réalisée par bobinage sur un premier grand nombre de spires jointives, compris entre 50 et 300, de fil isolé extérieurement de préférence de faible diamètre inférieur à 1,5mm. The wound conductor element 35c contains a coil mounted in parallel and wound in the opposite direction of the turns of said third number; this coil in reverse parallel mounting is carried out by winding on a first large number of turns contiguous, between 50 and 300, of externally insulated wire preferably low diameter less than 1.5mm.

    L'élément conducteur 35c bobiné sur le support isolant 37 est relié électriquement à un élément conducteur tubulaire 34c, de préférence revêtu au moins partiellement extérieurement d'une épaisseur faible de matériau 40 présentant une bonne conductivité électrique et thermique.The conductive element 35c wound on the insulating support 37 is electrically connected to a tubular conductive element 34c, preferably coated at least partially externally of a small thickness of material 40 having good electrical and thermal conductivity.

    Le support isolant 37 en forme d'haltère creuse présente une partie pleine 37a formant butée pour les éléments tubulaires 34b et 34c centrés dans le support en forme d'haltère creuse 37.The insulating support 37 in the form of a hollow dumbbell has a solid part 37a forming a stop for the tubular elements 34b and 34c centered in the support in hollow dumbbell shape 37.

    L'assemblage réalisé à ce stade constitue un ensemble mécanique allongé et conducteur pouvant être enfilé dans la cavité accessible lorsque les embouts 33a et/ou 33b ne sont pas montés : cet assemblage est centré aux deux extrémités par des bagues 38, 39 en matériau isolant, de préférence en composite fibre de verre.The assembly carried out at this stage constitutes an elongated mechanical assembly and conductor which can be inserted into the accessible cavity when the end pieces 33a and / or 33b are not mounted: this assembly is centered at both ends by rings 38, 39 of insulating material, preferably of fiberglass composite.

    Après avoir monté ledit ensemble allongé dans la structure creuse allongée, on raccorde électriquement grâce à la vis de contact 41 le montage allongé conducteur précité à un câble C d'antenne et à un élément conducteur bobiné 35d situé à l'intérieur du mât 31.After mounting said elongated assembly in the elongated hollow structure, we electrically connects with the contact screw 41 the elongated conductive mounting above to an antenna cable C and to a wound conductive element 35d located at inside the mast 31.

    L'élément conducteur bobiné 35d comprend un câble d'antenne bobiné sur un quatrième nombre de spires, compris de préférence entre 4 et 80, en parallèle avec un bobinage en sens inverse d'un deuxième grand nombre de spires jointives, compris entre 50 et 300, d'un fil isolé extérieurement de préférence de faible diamètre inférieur à 1,5mm.The conductive element wound 35d comprises an antenna cable wound on a fourth number of turns, preferably between 4 and 80, in parallel with a winding in the opposite direction of a second large number of contiguous turns, including between 50 and 300, of an externally insulated wire, preferably of small diameter less than 1.5mm.

    Avantageusement, ce montage en parallèle est court-circuité électriquement aux extrémités par un matériau de bonne conductivité électrique et thermique : le support isolant 42 est par exemple revêtu à cet effet d'un film 40 d'épaisseur faible de cuivre au beryllium qui est relié électriquement aux deux extrémités de l'élément 35d.Advantageously, this parallel mounting is electrically short-circuited at ends by a material of good electrical and thermal conductivity: the support insulator 42 is for example coated for this purpose with a film 40 of small thickness of copper beryllium which is electrically connected to the two ends of the element 35d.

    Avantageusement, le film 40 assure également la connexion électrique avec une tresse de masse 43 devant être reliée à la coque de l'aéronef et à une extrémité coaxiale 44, par exemple du type correspondant à la désignation RG 214 UKX 13 d'une impédance comprise entre 20 et 100 Ω.Advantageously, the film 40 also provides the electrical connection with a ground braid 43 to be connected to the hull of the aircraft and to one end coaxial 44, for example of the type corresponding to the designation RG 214 UKX 13 with an impedance between 20 and 100 Ω.

    Les essais ont permis de constater que cette antenne très légère, d'une longueur égale ou inférieure à 2m, est particulièrement adaptée à un fonctionnement en bande latérale unique (BLU) sur toute la bande de fréquence comprise entre 2 et 30 MHz. Tests have shown that this very light antenna, of equal length or less than 2m, is particularly suitable for band operation single lateral (SSB) over the entire frequency band between 2 and 30 MHz.

    L'invention décrite en référence à trois modes de réalisation particuliers n'y est nullement limitée, mais couvre au contraire toute modification de forme et toute variante de réalisation dans le cadre et l'esprit de l'invention.The invention described with reference to three particular embodiments is not there in no way limited, but on the contrary covers any modification of form and any variant embodiment within the scope and spirit of the invention.

    Claims (11)

    Antenne rigide, destinée à être montée sur un aéronef, comportant une enveloppe (3, 30) de protection extérieure réalisée essentiellement en matériau sensiblement transparent au rayonnement électromagnétique, de préférence en matériau électriquement isolant, ladite enveloppe (3, 30) de protection extérieure contenant un montage conducteur interne comprenant une pluralité d'éléments linéaires (4a-4d, 34a-34c) conducteurs reliés entre eux par une pluralité d'éléments conducteurs bobinés (5a-5c, 35a-35d) sur des supports isolants (6-8, 36, 37, 42), ledit montage conducteur interne étant relié à l'aéronef par l'intérieur de mâts (31, 32) de support et de fixation à la coque de l'aéronef.Rigid antenna, intended to be mounted on an aircraft, comprising an envelope (3, 30) of external protection made essentially of material substantially transparent to electromagnetic radiation, preferably made of material electrically insulating, said outer protective casing (3, 30) containing a internal conductor assembly comprising a plurality of linear elements (4a-4d, 34a-34c) conductors interconnected by a plurality of conductive elements wound (5a-5c, 35a-35d) on insulating supports (6-8, 36, 37, 42), said mounting internal conductor being connected to the aircraft by the interior of support masts (31, 32) and fixing to the hull of the aircraft. Antenne selon la revendication 1, caractérisée en ce qu'au moins un élément conducteur linéaire (4a - 4d, 34a-34c) est réalisé en métal léger ou en alliage métallique léger, revêtu au moins partiellement d'une épaisseur faible de matériau (10,40) présentant une bonne conductivité électrique et thermique.Antenna according to claim 1, characterized in that at least one element linear conductor (4a - 4d, 34a-34c) is made of light metal or an alloy light metal, at least partially coated with a small thickness of material (10.40) having good electrical and thermal conductivity. Antenne selon la revendication 1 ou la revendication 2, caractérisée en ce qu'au moins un élément conducteur bobiné (5a, 5b, 35c-35d) comporte deux bobines, dont la première comporte un premier grand nombre de spires jointives et dont la deuxième, bobinée en sens inverse de la première, comporte un second nombre inférieur de spires non jointives de fil ou câble conducteur isolé extérieurement.Antenna according to claim 1 or claim 2, characterized in that at at least one coiled conductive element (5a, 5b, 35c-35d) has two coils, of which the first comprises a first large number of contiguous turns and the second, wound in opposite direction to the first, has a second number lower of non-contiguous turns of wire or conducting cable insulated externally. Antenne selon la revendication 1 ou la revendication 2, caractérisée en ce qu'au moins un élément conducteur bobiné (5c, 5d, 35a, 35b) comporte un nombre prédéterminé de spires non jointives de fil ou câble C conducteur isolé extérieurement.Antenna according to claim 1 or claim 2, characterized in that at at least one coiled conductive element (5c, 5d, 35a, 35b) has a number predetermined non-contiguous turns of insulated conductive wire or cable C outwardly. Antenne selon l'une quelconque des revendications 1 à 4, caractérisée en ce que l'antenne présente une structure linéaire sensiblement cylindrique (figure 1).Antenna according to any one of claims 1 to 4, characterized in that the antenna has a substantially cylindrical linear structure (Figure 1). Antenne selon l'une quelconque des revendications 1 à 4, caractérisée en ce que l'antenne présente une structure repliée contenue dans une enveloppe profilée (figure 2, figures 4a-4c).Antenna according to any one of claims 1 to 4, characterized in that the antenna has a folded structure contained in a profiled envelope (figure 2, Figures 4a-4c). Antenne selon l'une quelconque des revendications précédentes, caractérisée en ce que l'enveloppe (3, 30) de protection extérieure est réalisée en matériau composite fibre de verre. Antenna according to any one of the preceding claims, characterized in that the outer protective casing (3, 30) is made of composite material fiberglass. Antenne selon l'une quelconque des revendications précédentes, caractérisée en ce que l'enveloppe (3, 30) de protection extérieure est obturée à deux extrémités par des embouts (13, 16, 33a, 33b).Antenna according to any one of the preceding claims, characterized in that the outer protective casing (3, 30) is closed at two ends by end caps (13, 16, 33a, 33b). Antenne selon l'une quelconque des revendications 1 à 7, caractérisée en ce que l'enveloppe (3, 30) de protection extérieure est munie de brides (20, 21, 31a, 32a) de raccordement à la coque d'un aéronef.Antenna according to any one of claims 1 to 7, characterized in that the outer protective casing (3, 30) is provided with flanges (20, 21, 31a, 32a) of connection to the hull of an aircraft. Antenne selon l'une quelconque des revendications 1 à 9, caractérisée en ce que chaque élément conducteur linéaire (4a - 4d, 34a-34c) est centré dans chaque support isolant par au moins une bague (9, 9a - 9j, 38, 39) en matériau électriquement isolant.Antenna according to any one of claims 1 to 9, characterized in that each linear conductive element (4a - 4d, 34a-34c) is centered in each support insulating by at least one ring (9, 9a - 9j, 38, 39) of electrically insulating material. Procédé de fabrication d'une antenne rigide comportant les étapes suivantes : a) prévoir au moins une bague ou moyen (9, 38, 36, 37, 42) de calage pour des éléments (4a - 4d, 34a, 34c) conducteurs linéaires ; b) associer chaque moyen de calage (9, 38, 36, 37, 42) à un support isolant (6 - 8, 8a, 8b, 36, 37, 42); c) bobiner au moins un élément conducteur sur au moins un support isolant (6 - 8, 8a, 8b), pour réaliser au moins un élément conducteur bobiné (5a - 5c, 35a-35d) ; d) assurer le raccordement électrique des éléments conducteurs linéaires (4a - 4d, 34a-34c) et bobinés (5a-5c, 35a-35d) selon un montage conducteur ; e) revêtir ledit montage conducteur d'une enveloppe (3, 30) de protection extérieure essentiellement en matériau sensiblement transparent au rayonnement électromagnétique. Method for manufacturing a rigid antenna comprising the following steps: a) providing at least one ring or means (9, 38, 36, 37, 42) of wedging for elements (4a - 4d, 34a, 34c) linear conductors; b) associate each wedging means (9, 38, 36, 37, 42) with an insulating support (6 - 8, 8a, 8b, 36, 37, 42); c) winding at least one conductive element on at least one insulating support (6 - 8, 8a, 8b), to produce at least one wound conductive element (5a - 5c, 35a-35d); d) ensuring the electrical connection of the linear (4a - 4d, 34a-34c) and wound (5a-5c, 35a-35d) conductive elements according to a conductive arrangement; e) coating said conductive assembly with an envelope (3, 30) of external protection essentially of material substantially transparent to electromagnetic radiation.
    EP98401277A 1997-05-30 1998-05-28 Stiff antenna and corresponding fabrication method Withdrawn EP0881703A1 (en)

    Applications Claiming Priority (2)

    Application Number Priority Date Filing Date Title
    FR9706663A FR2764123B1 (en) 1997-05-30 1997-05-30 RIGID ANTENNA AND CORRESPONDING MANUFACTURING METHOD
    FR9706663 1997-05-30

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    FR (1) FR2764123B1 (en)

    Cited By (1)

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    WO2000049679A1 (en) * 1999-02-18 2000-08-24 Totalförsvarets Forskningsinstitut Antenna carrier for connection to an air vehicle

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    WO2000049679A1 (en) * 1999-02-18 2000-08-24 Totalförsvarets Forskningsinstitut Antenna carrier for connection to an air vehicle
    US6476770B1 (en) 1999-02-18 2002-11-05 Totalforsvarets Forskningsinstitut Antenna carrier for connection to an air vehicle

    Also Published As

    Publication number Publication date
    FR2764123A1 (en) 1998-12-04
    FR2764123B1 (en) 1999-07-30

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