EP1263080A1 - Slot antenna for airplane - Google Patents

Slot antenna for airplane Download PDF

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Publication number
EP1263080A1
EP1263080A1 EP02291271A EP02291271A EP1263080A1 EP 1263080 A1 EP1263080 A1 EP 1263080A1 EP 02291271 A EP02291271 A EP 02291271A EP 02291271 A EP02291271 A EP 02291271A EP 1263080 A1 EP1263080 A1 EP 1263080A1
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EP
European Patent Office
Prior art keywords
antenna
exciter
cavity
support
airplane
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP02291271A
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German (de)
French (fr)
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EP1263080B8 (en
EP1263080B1 (en
Inventor
René Ceccom
Claude Pichavant
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Airbus Operations SAS
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Airbus Operations SAS
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Publication date
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Publication of EP1263080A1 publication Critical patent/EP1263080A1/en
Application granted granted Critical
Publication of EP1263080B1 publication Critical patent/EP1263080B1/en
Publication of EP1263080B8 publication Critical patent/EP1263080B8/en
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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
    • H01Q1/286—Adaptation for use in or on aircraft, missiles, satellites, or balloons substantially flush mounted with the skin of the craft
    • H01Q1/287—Adaptation for use in or on aircraft, missiles, satellites, or balloons substantially flush mounted with the skin of the craft integrated in a wing or a stabiliser
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q13/00—Waveguide horns or mouths; Slot antennas; Leaky-waveguide antennas; Equivalent structures causing radiation along the transmission path of a guided wave
    • H01Q13/10—Resonant slot antennas

Definitions

  • the present invention relates to an antenna transmission / reception of radiofrequency waves constituted a removable exciter element, integrated in a fixed or mobile structure, for example an airplane, making radiate all or part of the structural element in which it is integrated into, and an airplane using such antenna.
  • the antenna of the invention integrated into the structure of an aircraft. But it could also be integrated into any other vehicle type.
  • a dipole type antenna which is used in particular for radio frequency reception on board an aircraft, requires a ground plan of large area and a length antenna sufficient in view of the radio frequencies considered.
  • the antennas are protected: the radiating part is sheltered by a radome made, among other things, of a material transparent to electromagnetic waves.
  • a such protection must be profiled so that disrupt performance as little as possible aerodynamic.
  • the decoupling values electromagnetic between the different antennas which must comply with the requirements of the standards (ARINC in particular), result in constraints physical distance between the working antennas in the same frequency bands.
  • adding antenna can therefore be very problematic.
  • a US patent, US 6,047,925 describes thus a narrow band UHF antenna integrated in the train hatch of an airplane. By its principle installation, it is necessary after each disassembly of the antenna, to redo the tuning of this last. Such intervention, if it is to be made during a stopover of an airplane operated by a airline, is very penalizing (additional cost, immobilization of the aircraft, very specialized tools, etc.).
  • This antenna is a wide band slot antenna, the dimensions of which are relatively large. So she must be part of a structural element of the plane of dimensions adapted (drift, etc.), without being able to be dissociated from this one. The removal or replacement of such antenna requires disassembly, and possibly the replacement of the structural element considered. In plus the difficulties of installing such antenna, the maintenance costs are high and the aircraft downtime is important.
  • the subject of the present invention is a antenna composed of an excitation element which can be easily integrated into a structural element constituting the radiating part of the antenna, without disrupt the aerodynamic performance of the assembly, said excitation element being able to be removed from this structural element without requiring the replacement of the latter.
  • This structural element can in particular be a part of a construction (for example of a building) or a vehicle (e.g. a plane).
  • the exciter element and the cover are made of fiber glass.
  • the material which fills the excitation element is a resin or a cast thermoplastic material.
  • the stub is made of copper covered with a layer on the surface silver.
  • the cover is fixed on the exciter element to the using non-magnetic screws.
  • the exciting element has a form capable of being fixed in a cut made in an element of the structure of a construction or of a vehicle, for example an airplane.
  • the present invention also relates to a airplane with at least one end element wing has a notch-shaped cavity in which is arranged an excitation element such as previously described.
  • FIG. 1 illustrates the antenna of the invention.
  • Figure 2 illustrates an exploded view of a exemplary embodiment of the antenna of the invention.
  • FIGS 3 and 4 illustrate the location of the structure of the plane where can be advantageously integrated the antenna of the invention.
  • Figure 5 illustrates a response curve of the TOS as a function of the frequency of the antenna the invention.
  • This exciter element 10 can be fixed, as equipment, in a cut made in the structure of a construction or a vehicle, for example example an airplane, the dimensions of this notch determining the bandwidth of the antenna. All composed of the exciter element integrated in the element structure thus forms a band slot antenna narrow. The exciter element is housed in the part "slot" of this slot antenna.
  • the antenna radiation is provided by the structural element 8 which accommodates the element exciter 10.
  • This structural element must be made of a sufficiently conductive material to frequencies used, for example aluminum, and sufficient dimensions (at least a quarter of the wavelength in the polarization direction of electromagnetic wave).
  • the standing wave rate (TOS) is less than 2 on the frequency band in which antenna is used.
  • the dimensions of the antenna depend on the desired frequency band: when the frequency is reduced frequency (for example in HF) the dimensions increase and the frequency limits depend on the possibilities integration into the structure. When we increase the frequency (for example in UHF) the dimensions decrease. You cannot, however, climb too high frequency due to technological constraints of realization of the cavity.
  • the minimum frequencies that can be transmitted are imposed by the structural element 8 in which we wish to integrate said element exciter 10.
  • This structural element must have at least a part whose length, depending on the direction of polarization desired, is greater or equal to a quarter of the wavelength corresponding to this minimum frequency.
  • the minimum dimension, depending on the direction of polarization, is equal to a quarter of the length wave, again c / 4.f, where c is the speed of the light (3.10 ⁇ 8 m / s) and f the frequency in Hertz. If the desired polarization is vertical, this dimension minimum is the height H shown in Figure 1.
  • the maximum frequencies that can be transmitted by such an antenna are estimated to around 5 GHz in the industrial field. it corresponds to a slot of 17 mm in length and 3 mm in height. Such a frequency limitation comes from the difficulty of industrial production of a cavity of dimensions smaller than these. Such a antenna therefore covers the UHF band.
  • the invention can then be applied to HF, VHF, and UHF bands.
  • the exciting element of the invention is integrated in a cavity 20 in one of the elements ends 21 of the wings 22 of an airplane 23 ("wing tip fence “on” winglet “, or end fins of wing).
  • such cavity 20 can be located in the trailing edge of a such element.
  • the coaxial power cable of the stub is connected inside these elements, by through a connector, to a coaxial cable connected to the transmitter / receiver.
  • This coaxial cable runs along the wing of the plane, inside it.
  • the antenna radiation is provided by the corresponding end element.
  • This location of the antenna allows respect radio decoupling with other radio communication and navigation antennas using the same frequency band because said elements are located in the extreme part of the wings, at a sufficient distance from said other antennas. Moreover, such an establishment makes it possible to obtain a diagram of radiation up and down satisfactory because, at the end of the wings, the structure of the plane does not does not interfere with the upward and outward propagation of waves the bottom.
  • the antenna made by integrating the exciter element 10 in the cavity 20 formed in one of the end elements 21 wings 22 of an airplane 23 has a TOS (Rate of Standing Waves) less than or equal to 2 on the civilian VHF band (108-137 MHz) in which it is used with vertical polarization direction of the electromagnetic wave.
  • TOS Rate of Standing Waves
  • the antenna of the invention has been described in the particular case of its integration in an airplane. But she can, everything as well be integrated on any type of vehicle (boat, automobile, etc.) with an element of structure of adequate dimensions compared to wavelengths considered, both to ensure the radiating element function only to be able to make a notch of adequate size in order to insert the exciter, and the material of which is sufficiently conductive at frequencies of antenna operation.
  • Such an antenna has all the more of interest that the vehicle must have performance high aerodynamics.

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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)
  • Waveguide Aerials (AREA)
  • Aerials With Secondary Devices (AREA)
  • Variable-Direction Aerials And Aerial Arrays (AREA)
  • Input Circuits Of Receivers And Coupling Of Receivers And Audio Equipment (AREA)

Abstract

The aerial includes a dielectric support (11) and a conducting lamella (12) forming the radiating element. A coaxial cable (14) feeds the aerial assembly, passing through the wall of the support (11). The support has a cover attached, forming a part of the outside surface of the aircraft. The aerial assembly includes a support (11) made of dielectric material which is transparent to radiofrequency signals - this may, for example, be glass fibre filled with a further radiofrequency transparent material such as a resin or thermoplastic material. A conducting lamella (12) made of copper and coated with silver in order to improve surface conductivity at the required frequency is accommodated inside the support, enabling the tuning and matching of the aerial for the required frequency. A cover (13) made of radiofrequency transparent material is attached to the support by means of non-magnetic screws. A coaxial cable (14) feeds the aerial assembly, passing through the wall of the support (11). The cable is terminated with a standard coaxial fitting.

Description

Domaine techniqueTechnical area

La présente invention concerne une antenne d'émission/réception d'ondes radiofréquences constituée d'un élément excitateur amovible, intégré dans une structure fixe ou mobile, par exemple un avion, faisant rayonner tout ou partie de l'élément de structure dans lequel il est intégré, et un avion utilisant une telle antenne.The present invention relates to an antenna transmission / reception of radiofrequency waves constituted a removable exciter element, integrated in a fixed or mobile structure, for example an airplane, making radiate all or part of the structural element in which it is integrated into, and an airplane using such antenna.

Etat de la techniqueState of the art

Dans la suite de la description on considérera, à titre d'exemple non limitatif, l'antenne de l'invention intégrée dans la structure d'un avion. Mais elle pourrait aussi être intégrée dans tout autre type de véhicule.In the following description, consider, by way of nonlimiting example, the antenna of the invention integrated into the structure of an aircraft. But it could also be integrated into any other vehicle type.

Pour réaliser une liaison radiofréquence, tant en émission qu'en réception, l'utilisation d'une antenne est nécessaire. Une antenne de type dipole, qui est notamment utilisée pour la réception radiofréquence à bord d'un avion, nécessite un plan de masse de surface importante et une antenne de longueur suffisante eu égard aux fréquences radio considérées.To make a radio frequency link, both in transmission and in reception, the use of a antenna is required. A dipole type antenna, which is used in particular for radio frequency reception on board an aircraft, requires a ground plan of large area and a length antenna sufficient in view of the radio frequencies considered.

Dans un avion, les antennes sont protégées : la partie rayonnante est abritée par un radôme constitué, entre autres, d'un matériau transparent pour les ondes électromagnétiques. Une telle protection doit être profilée de manière à perturber le moins possible les performances aérodynamiques. De plus, les valeurs de découplage électromagnétique entre les différentes antennes, qui doivent se conformer aux exigences des normes (ARINC notamment), se traduisent par des contraintes d'éloignement physique entre les antennes travaillant dans les mêmes bandes de fréquence.In an airplane, the antennas are protected: the radiating part is sheltered by a radome made, among other things, of a material transparent to electromagnetic waves. A such protection must be profiled so that disrupt performance as little as possible aerodynamic. In addition, the decoupling values electromagnetic between the different antennas, which must comply with the requirements of the standards (ARINC in particular), result in constraints physical distance between the working antennas in the same frequency bands.

Dans un avion de petite taille, l'ajout d'une antenne peut, ainsi, s'avérer très problématique.In a small plane, adding antenna can therefore be very problematic.

Afin de ne pas perturber les caractéristiques aérodynamiques d'un avion, on peut utiliser une antenne intégrée dans la structure de ce dernier.In order not to disturb the aerodynamic characteristics of an airplane, we can use an antenna built into the structure of this latest.

Un brevet américain, US 6 047 925, décrit ainsi une antenne UHF bande étroite intégrée dans la trappe de train d'un avion. De par son principe d'installation, il est nécessaire, après chaque démontage de l'antenne, de refaire l'accord de cette dernière. Une telle intervention, si elle doit être effectuée lors d'une escale d'un avion exploité par une compagnie aérienne, est très pénalisante (surcoût, immobilisation de l'avion, outillage très spécialisé, etc.).A US patent, US 6,047,925, describes thus a narrow band UHF antenna integrated in the train hatch of an airplane. By its principle installation, it is necessary after each disassembly of the antenna, to redo the tuning of this last. Such intervention, if it is to be made during a stopover of an airplane operated by a airline, is very penalizing (additional cost, immobilization of the aircraft, very specialized tools, etc.).

Une demande de brevet français, FR 1 091 358, décrit un autre type d'antenne intégrée dans la structure d'un avion. Cette antenne est une antenne fente large bande, dont les dimensions sont relativement importantes. Elle doit donc faire partie d'un élément de structure de l'avion de dimensions adaptées (dérive, etc.), sans pouvoir être dissociée de celui-ci. La dépose ou le remplacement d'une telle antenne nécessite le démontage, et éventuellement le remplacement, de l'élément de structure considéré. En plus des difficultés d'installation d'une telle antenne, les coûts de maintenance sont élevés et les durées d'immobilisation de l'avion sont importantes.A French patent application, FR 1 091 358, describes another type of integrated antenna in the structure of an airplane. This antenna is a wide band slot antenna, the dimensions of which are relatively large. So she must be part of a structural element of the plane of dimensions adapted (drift, etc.), without being able to be dissociated from this one. The removal or replacement of such antenna requires disassembly, and possibly the replacement of the structural element considered. In plus the difficulties of installing such antenna, the maintenance costs are high and the aircraft downtime is important.

La présente invention a pour objet une antenne composée d'un élément d'excitation pouvant être facilement intégré dans un élément de structure constituant la partie rayonnante de l'antenne, sans perturber les performances aérodynamiques de l'ensemble, ledit élément d'excitation pouvant être retiré de cet élément de structure sans nécessiter le remplacement de ce dernier. Cet élément de structure peut notamment être une partie d'une construction (par exemple d'un bâtiment) ou d'un véhicule (par exemple un avion).The subject of the present invention is a antenna composed of an excitation element which can be easily integrated into a structural element constituting the radiating part of the antenna, without disrupt the aerodynamic performance of the assembly, said excitation element being able to be removed from this structural element without requiring the replacement of the latter. This structural element can in particular be a part of a construction (for example of a building) or a vehicle (e.g. a plane).

Exposé de l'inventionStatement of the invention

La présente invention propose une antenne d'émission/réception d'ondes radiofréquences, comprenant :

  • un élément de structure conducteur dans la bande de fréquences de fonctionnement de l'antenne, de dimension au moins égale au quart de la longueur d'onde selon la direction de polarisation de l'onde électromagnétique pour la fréquence minimale de cette bande de fréquences, et comportant une découpe formant cavité,
  • un élément excitateur amovible disposé dans cette cavité, qui agit en tant qu'excitateur de cette cavité,
  • une liaison électriquement conductrice aux fréquences de fonctionnement de l'antenne, assurant une métallisation entre ledit élément excitateur et ledit élément de structure.
The present invention provides an antenna for transmitting / receiving radiofrequency waves, comprising:
  • a conductive structural element in the operating frequency band of the antenna, of dimension at least equal to a quarter of the wavelength in the direction of polarization of the electromagnetic wave for the minimum frequency of this frequency band, and comprising a cavity cutout,
  • a removable exciter element placed in this cavity, which acts as an exciter in this cavity,
  • an electrically conductive link at the operating frequencies of the antenna, ensuring metallization between said exciter element and said structural element.

Dans un mode de réalisation avantageux, cet élément excitateur comprend :

  • un élément en matériau transparent aux ondes radiofréquences, rempli d'un matériau également transparent aux ondes radiofréquences,
  • une lamelle conductrice formant un stub, permettant de réaliser l'accord et l'adaptation de l'antenne sur la bande de fréquences de fonctionnement,
  • un capot en matériau transparent aux ondes radiofréquences, abritant l'élément excitateur et assurant la continuité du profil de l'élément de structure,
  • une ligne d'alimentation du stub.
In an advantageous embodiment, this excitation element comprises:
  • an element made of material transparent to radiofrequency waves, filled with a material also transparent to radiofrequency waves,
  • a conductive strip forming a stub, making it possible to tune and adapt the antenna to the operating frequency band,
  • a cover made of material transparent to radio frequency waves, housing the excitation element and ensuring the continuity of the profile of the structural element,
  • a stub supply line.

Dans un exemple de réalisation avantageux, l'élément excitateur et le capot sont en fibre de verre. Le matériau qui remplit l'élément excitateur est une résine ou un matériau thermoplastique coulé. Le stub est en cuivre recouvert en surface d'une couche argentée. Le capot est fixé sur l'élément excitateur au moyen de vis amagnétiques. L'élément excitateur a une forme apte à être fixée dans une entaille pratiquée dans un élément de la structure d'une construction ou d'un véhicule, par exemple un avion.In an advantageous exemplary embodiment, the exciter element and the cover are made of fiber glass. The material which fills the excitation element is a resin or a cast thermoplastic material. The stub is made of copper covered with a layer on the surface silver. The cover is fixed on the exciter element to the using non-magnetic screws. The exciting element has a form capable of being fixed in a cut made in an element of the structure of a construction or of a vehicle, for example an airplane.

La présente invention concerne également un avion dont au moins l'un des éléments d'extrémité d'aile comporte une cavité en forme d'entaille dans laquelle est disposé un élément excitateur tel que décrit précédemment.The present invention also relates to a airplane with at least one end element wing has a notch-shaped cavity in which is arranged an excitation element such as previously described.

L'antenne de l'invention présente de nombreux avantages :

  • elle ne modifie pas les propriétés aérodynamiques de l'avion puisqu'elle est intégrée dans un élément de structure de celui-ci,
  • sa mise en place ainsi que sa maintenance (démontage, échange standard, etc.) sont aisées : aucune opération de réglage ou d'accord ne sont nécessaires après le montage de celle-ci,
  • les coûts de maintenance sont donc diminués,
  • elle peut être proposée en tant qu'équipement optionnel dans un avion : en effet, elle peut ne pas faire partie de la structure de celui-ci, mais être fixée sur celle-ci. Un simple capot de protection peut ainsi protéger l'entaille pratiquée dans la structure de l'avion à l'emplacement permettant de recevoir l'élément excitateur,
  • elle peut être intégrée dans un élément de structure suffisamment éloigné des autres antennes utilisant la même bande de fréquences ; ce qui permet de respecter les valeurs de découplage électromagnétique imposées entre antennes.
The antenna of the invention has many advantages:
  • it does not modify the aerodynamic properties of the aircraft since it is integrated into a structural element thereof,
  • its installation as well as its maintenance (dismantling, standard exchange, etc.) are easy: no adjustment or tuning operation is necessary after mounting it,
  • maintenance costs are therefore reduced,
  • it can be offered as optional equipment on an airplane: in fact, it may not be part of the structure thereof, but be fixed to it. A simple protective cover can thus protect the notch formed in the structure of the aircraft at the location making it possible to receive the exciting element,
  • it can be integrated into a structural element sufficiently distant from other antennas using the same frequency band; which makes it possible to comply with the electromagnetic decoupling values imposed between antennas.

Brève description des dessinsBrief description of the drawings

La figure 1 illustre l'antenne de l'invention.Figure 1 illustrates the antenna of the invention.

La figure 2 illustre une vue éclatée d'un exemple de réalisation de l'antenne de l'invention.Figure 2 illustrates an exploded view of a exemplary embodiment of the antenna of the invention.

Les figures 3 et 4 illustrent l'endroit de la structure de l'avion où peut être avantageusement intégrée l'antenne de l'invention.Figures 3 and 4 illustrate the location of the structure of the plane where can be advantageously integrated the antenna of the invention.

La figure 5 illustre une courbe de réponse du TOS en fonction de la fréquence de l'antenne de l'invention.Figure 5 illustrates a response curve of the TOS as a function of the frequency of the antenna the invention.

Exposé détaillé de modes de réalisationDetailed description of embodiments

Comme illustré sur la figure 1, l'antenne d'émission/réception d'ondes radiofréquences de l'inventio comprend :

  • un élément de structure 8 conducteur dans la bande de fréquences de fonctionnement de l'antenne, de dimension au moins égale au quart de la longueur d'onde selon la direction de polarisation de l'onde électromagnétique pour la fréquence minimale de cette bande de fréquences, et comportant une découpe formant cavité 9,
  • un élément excitateur amovible 10 disposé dans cette cavité, qui agit en tant qu'excitateur de cette cavité,
  • une liaison électriquement conductrice aux fréquences de fonctionnement de l'antenne, assurant une métallisation entre ledit élément excitateur 10 et ledit élément de structure 8.
As illustrated in FIG. 1, the antenna for transmitting / receiving radio waves of the inventio comprises:
  • a structural element 8 conducting in the operating frequency band of the antenna, of dimension at least equal to a quarter of the wavelength in the direction of polarization of the electromagnetic wave for the minimum frequency of this frequency band , and comprising a cutout forming a cavity 9,
  • a removable exciter element 10 disposed in this cavity, which acts as an exciter for this cavity,
  • an electrically conductive link at the operating frequencies of the antenna, ensuring metallization between said exciter element 10 and said structural element 8.

La figure 2 représente un mode de réalisation avantageux de l'élément excitateur amovible 10 de l'antenne d'émission/réception d'ondes radiofréquences de l'invention qui comprend :

  • un élément 11 en un matériau diélectrique transparent aux ondes radiofréquences, par exemple en fibre de verre, rempli d'un matériau également transparent aux ondes radiofréquences, par exemple en résine ou en un matériau thermoplastique coulé,
  • une lamelle conductrice formant un stub 12, par exemple en cuivre recouvert en surface d'une couche argentée afin d'améliorer la conduction (dans le domaine de fréquences considérées, la conduction se fait presque exclusivement en surface : "effet de peau") disposée dans cet élément 11, permettant de réaliser l'accord et l'adaptation de l'antenne sur la bande de fréquences utilisée,
  • un capot 13 en un matériau transparent aux radiofréquences, par exemple en fibre de verre, fixé, par exemple vissé au moyen de vis amagnétiques, sur le pourtour de la cavité, ces vis assurant aussi la métallisation entre l'élément excitateur et l'élément de structure, par exemple en permettant le contact électrique entre cet élément de structure 8 conducteur et un clinquant de cuivre raccordé à la tresse de masse du câble coaxial 14 alimentant le stub 12
  • une ligne 14 d'alimentation du stub, par exemple un câble coaxial, muni d'un connecteur standard de raccordement, permettant de relier l'antenne à un câble coaxial connecté à un émetteur/récepteur.
FIG. 2 represents an advantageous embodiment of the removable exciter element 10 of the antenna for transmitting / receiving radiofrequency waves of the invention which comprises:
  • an element 11 made of a dielectric material transparent to radiofrequency waves, for example fiberglass, filled with a material also transparent to radiofrequency waves, for example of resin or of a cast thermoplastic material,
  • a conductive strip forming a stub 12, for example made of copper covered on the surface with a silver layer in order to improve the conduction (in the frequency range considered, the conduction takes place almost exclusively at the surface: "skin effect") arranged in this element 11, making it possible to tune and adapt the antenna to the frequency band used,
  • a cover 13 made of a material transparent to radio frequencies, for example fiberglass, fixed, for example screwed by means of non-magnetic screws, around the periphery of the cavity, these screws also ensuring metallization between the exciter element and the element structure, for example by allowing electrical contact between this conductive structural element 8 and a copper foil connected to the ground braid of the coaxial cable 14 supplying the stub 12
  • a line 14 for supplying the stub, for example a coaxial cable, provided with a standard connector for connection, making it possible to connect the antenna to a coaxial cable connected to a transmitter / receiver.

Cet élément excitateur 10 peut être fixé, en tant qu'équipement, dans une entaille pratiquée dans la structure d'une construction ou d'un véhicule, par exemple un avion, les dimensions de cette entaille déterminant la bande passante de l'antenne. L'ensemble composé de l'élément excitateur intégré dans l'élément de structure forme ainsi une antenne fente bande étroite. L'élément excitateur est logé dans la partie "fente" de cette antenne fente.This exciter element 10 can be fixed, as equipment, in a cut made in the structure of a construction or a vehicle, for example example an airplane, the dimensions of this notch determining the bandwidth of the antenna. All composed of the exciter element integrated in the element structure thus forms a band slot antenna narrow. The exciter element is housed in the part "slot" of this slot antenna.

Le rayonnement de l'antenne est assuré par l'élément de structure 8 qui accueille l'élément excitateur 10. Cet élément de structure doit être constitué d'un matériau suffisamment conducteur aux fréquences utilisées, par exemple en aluminium, et de dimensions suffisantes (au minimum le quart de la longueur d'ondes selon la direction de polarisation de l'onde électromagnétique).The antenna radiation is provided by the structural element 8 which accommodates the element exciter 10. This structural element must be made of a sufficiently conductive material to frequencies used, for example aluminum, and sufficient dimensions (at least a quarter of the wavelength in the polarization direction of electromagnetic wave).

En pratique, le taux d'ondes stationnaires (TOS) est inférieur à 2 sur la bande de fréquences dans laquelle est utilisée l'antenne.In practice, the standing wave rate (TOS) is less than 2 on the frequency band in which antenna is used.

Les dimensions de l'antenne dépendent de la bande de fréquences souhaitée : lorsqu'on diminue la fréquence (par exemple en HF) les dimensions augmentent et les limites de fréquences dépendent des possibilités d'intégration dans la structure. Lorsqu'on augmente la fréquence (par exemple en UHF) les dimensions diminuent. On ne peut toutefois pas monter trop haut en fréquence en raison des contraintes technologiques de réalisation de la cavité.The dimensions of the antenna depend on the desired frequency band: when the frequency is reduced frequency (for example in HF) the dimensions increase and the frequency limits depend on the possibilities integration into the structure. When we increase the frequency (for example in UHF) the dimensions decrease. You cannot, however, climb too high frequency due to technological constraints of realization of the cavity.

Les fréquences minimales pouvant être transmises sont imposées par l'élément de structure 8 dans lequel on souhaite intégrer ledit élément excitateur 10. Cet élément de structure doit présenter au moins une partie dont la longueur, selon la direction de polarisation souhaitée, est supérieure ou égale au quart de la longueur d'onde correspondant à cette fréquence minimale.The minimum frequencies that can be transmitted are imposed by the structural element 8 in which we wish to integrate said element exciter 10. This structural element must have at least a part whose length, depending on the direction of polarization desired, is greater or equal to a quarter of the wavelength corresponding to this minimum frequency.

La dimension minimale, selon la direction de polarisation, est égale au quart de la longueur d'onde, soit encore c/4.f, où c est la vitesse de la lumière (3.10^8 m/s) et f la fréquence en Hertz. Si la polarisation souhaitée est verticale, cette dimension minimale est la hauteur H représentée sur la figure 1.The minimum dimension, depending on the direction of polarization, is equal to a quarter of the length wave, again c / 4.f, where c is the speed of the light (3.10 ^ 8 m / s) and f the frequency in Hertz. If the desired polarization is vertical, this dimension minimum is the height H shown in Figure 1.

Si l'on considère une dimension minimale de quelques mètres (afin d'être techniquement réalisable) on obtient une antenne permettant de couvrir la bande HF (2-30 MHz).If we consider a minimum dimension of a few meters (in order to be technically feasible) we get an antenna to cover the band HF (2-30 MHz).

Les fréquences maximales pouvant être transmises par une telle antenne sont estimées à environ 5 GHz dans le domaine industriel. Cela correspond à une fente de 17 mm de longueur et 3 mm de hauteur. Une telle limitation en fréquence provient de la difficulté de réalisation industrielle d'une cavité de dimensions inférieures à celles-ci. Une telle antenne permet donc de couvrir la bande UHF.The maximum frequencies that can be transmitted by such an antenna are estimated to around 5 GHz in the industrial field. it corresponds to a slot of 17 mm in length and 3 mm in height. Such a frequency limitation comes from the difficulty of industrial production of a cavity of dimensions smaller than these. Such a antenna therefore covers the UHF band.

L'invention peut alors s'appliquer aux bandes HF, VHF, et UHF. The invention can then be applied to HF, VHF, and UHF bands.

Dans un exemple de réalisation illustré sur les figures 3 et 4, l'élément excitateur de l'invention est intégré dans une cavité 20 dans un des éléments d'extrémités 21 des ailes 22 d'un avion 23 ("wing tip fence" on "winglet", ou ailettes d'extrémité de voilure).In an exemplary embodiment illustrated on Figures 3 and 4, the exciting element of the invention is integrated in a cavity 20 in one of the elements ends 21 of the wings 22 of an airplane 23 ("wing tip fence "on" winglet ", or end fins of wing).

Comme illustré sur la figure 4, une telle cavité 20 peut être située dans le bord de fuite d'un tel élément.As illustrated in Figure 4, such cavity 20 can be located in the trailing edge of a such element.

Un tel emplacement permet de modifier le moins possible les renforts permettant auxdits éléments d'extrémité des ailes de résister aux efforts aérodynamiques lors du vol de l'avion. Mais d'autres emplacements sont également possibles.Such a location allows you to modify the the reinforcements allowing said elements are less possible wing tips to resist efforts aerodynamics during the flight of the aircraft. But others locations are also possible.

Le câble coaxial d'alimentation du stub est raccordé à l'intérieur de ces éléments, par l'intermédiaire d'un connecteur, à un câble coaxial relié à l'émetteur/récepteur. Ce câble coaxial chemine le long de l'aile de l'avion, à l'intérieur de celle-ci. Le rayonnement de l'antenne est assuré par l'élément d'extrémité correspondant.The coaxial power cable of the stub is connected inside these elements, by through a connector, to a coaxial cable connected to the transmitter / receiver. This coaxial cable runs along the wing of the plane, inside it. The antenna radiation is provided by the corresponding end element.

Cette implantation de l'antenne permet de respecter les découplages radioélectriques avec les autres antennes de radio-communication et de navigation utilisant la même bande de fréquences car lesdits éléments sont situés en partie extrême des ailes, à une distance suffisante desdites autres antennes. De plus, une telle implantation permet d'obtenir un diagramme de rayonnement vers le haut et vers le bas satisfaisant car, en extrémité des ailes, la structure de l'avion ne gêne pas la propagation des ondes vers le haut et vers le bas.This location of the antenna allows respect radio decoupling with other radio communication and navigation antennas using the same frequency band because said elements are located in the extreme part of the wings, at a sufficient distance from said other antennas. Moreover, such an establishment makes it possible to obtain a diagram of radiation up and down satisfactory because, at the end of the wings, the structure of the plane does not does not interfere with the upward and outward propagation of waves the bottom.

Dans un cas concret de réalisation on considère un élément excitateur, tel que représenté sur la figure 2, réalisé à l'échelle 1. Les dimensions de celui-ci sont alors les suivantes :

  • longueur L = 170 mm,
  • hauteur H = 83 mm.
In a specific embodiment, an excitation element, as shown in FIG. 2, is considered, made on scale 1. The dimensions of the latter are then as follows:
  • length L = 170 mm,
  • height H = 83 mm.

Comme illustré sur la figure 5, l'antenne réalisée en intégrant l'élément excitateur 10 dans la cavité 20 pratiquée dans un des éléments d'extrémité 21 des ailes 22 d'un avion 23 présente un TOS (Taux d'Ondes Stationnaires) inférieur ou égal à 2 sur la bande VHF civile (108-137 MHz) dans laquelle elle est utilisée avec une direction de polarisation verticale de l'onde électromagnétique.As illustrated in Figure 5, the antenna made by integrating the exciter element 10 in the cavity 20 formed in one of the end elements 21 wings 22 of an airplane 23 has a TOS (Rate of Standing Waves) less than or equal to 2 on the civilian VHF band (108-137 MHz) in which it is used with vertical polarization direction of the electromagnetic wave.

Dans la description qui précède l'antenne de l'invention a été décrite dans le cas particulier de son intégration dans un avion. Mais elle peut, tout aussi bien être intégrée sur tout type de véhicule (bateau, automobile, etc.) présentant un élément de structure de dimensions adéquates par rapport aux longueurs d'ondes considérées, tant pour assurer la fonction d'élément rayonnant que pour pouvoir y pratiquer une entaille de taille adéquate afin d'y insérer l'élément excitateur, et dont le matériau est suffisamment conducteur aux fréquences de fonctionnement de l'antenne. In the description above the antenna of the invention has been described in the particular case of its integration in an airplane. But she can, everything as well be integrated on any type of vehicle (boat, automobile, etc.) with an element of structure of adequate dimensions compared to wavelengths considered, both to ensure the radiating element function only to be able to make a notch of adequate size in order to insert the exciter, and the material of which is sufficiently conductive at frequencies of antenna operation.

Une telle antenne présente d'autant plus d'intérêt que le véhicule doit avoir des performances aérodynamiques élevées.Such an antenna has all the more of interest that the vehicle must have performance high aerodynamics.

Elle peut aussi être utilisée pour des installations fixes (bâtiments, etc.) soumises à des contraintes environnementales sévères (vents violents, etc.)¸.It can also be used for fixed installations (buildings, etc.) subject to severe environmental constraints (strong winds, etc.) ¸.

Claims (9)

Antenne d'émission/réception d'ondes radiofréquences caractérisée en ce qu'elle comprend : un élément de structure (8) conducteur dans la bande de fréquences de fonctionnement de l'antenne, de dimension au moins égale au quart de la longueur d'onde selon la direction de polarisation de l'onde électromagnétique pour la fréquence minimale de cette bande de fréquences, et comportant une découpe formant cavité (9), un élément excitateur amovible (10) disposé dans cette cavité, qui agit en tant qu'excitateur de cette cavité (9), une métallisation électriquement conductrice aux fréquences de fonctionnement de l'antenne assurant une métallisation entre ledit élément excitateur (10) et ledit élément de structure (8),
et en ce que l'élément excitateur (10) comprend : un élément (11) en matériau transparent aux ondes radiofréquences, rempli d'un matériau également transparent aux ondes radiofréquences, une lamelle conductrice (12) formant un stub permettant de réaliser l'accord et l'adaptation de l'antenne sur la bande de fréquences de fonctionnement, un capot (13) en matériau transparent aux radiofréquences abritant l'élément excitateur (10) et assurant la continuité du profil de l'élément de structure (8), une ligne (14) d'alimentation du stub. Radiofrequency wave transmission / reception antenna characterized in that it comprises: a structural element (8) conductive in the operating frequency band of the antenna, of dimension at least equal to a quarter of the wavelength in the direction of polarization of the electromagnetic wave for the minimum frequency of this band frequencies, and comprising a cavity cutout (9), a removable exciter element (10) disposed in this cavity, which acts as an exciter for this cavity (9), an electrically conductive metallization at the operating frequencies of the antenna ensuring metallization between said exciter element (10) and said structural element (8),
and in that the exciter element (10) comprises: an element (11) of material transparent to radio waves, filled with a material also transparent to radio waves, a conductive strip (12) forming a stub making it possible to achieve tuning and adaptation of the antenna on the operating frequency band, a cover (13) made of a material transparent to radio frequencies housing the exciter element (10) and ensuring the continuity of the profile of the structural element (8), a line (14) for supplying the stub. Antenne selon la revendication 1, dans laquelle l'élément excitateur (10) et le capot (13) sont en fibre de verre.Antenna according to claim 1, in which the exciter element (10) and the cover (13) are made of fiberglass. Antenne selon la revendication 1, dans laquelle le matériau qui remplit l'élément excitateur (10) est une résine ou un matériau thermoplastique coulé.Antenna according to claim 1, in which the material that fills the exciting element (10) is a resin or a thermoplastic material sank. Antenne selon la revendication 1, dans laquelle le stub est en cuivre recouvert en surface d'une couche argentée.Antenna according to claim 1, in which the stub is made of copper covered on the surface a silver layer. Antenne selon la revendication 1, dans laquelle le capot (13) est fixé sur l'élément excitateur (10) au moyen de vis amagnétiques.Antenna according to claim 1, in which the cover (13) is fixed on the element exciter (10) by means of non-magnetic screws. Antenne selon l'une quelconque des revendications précédentes dans laquelle l'élément excitateur (10), a une forme apte à être fixée dans une entaille pratiquée dans un élément de la structure d'une construction ou d'un véhicule.Antenna according to any one of previous claims wherein the element exciter (10), has a shape capable of being fixed in a cut in an element of the structure construction or vehicle. Antenne selon la revendication 6, dans lequel ledit véhicule est un avion.Antenna according to claim 6, in which said vehicle is an airplane. Avion caractérisé en ce qu'au moins l'un de ses éléments de structure est muni d'une cavité dans laquelle est disposé un élément excitateur (10) selon l'une quelconque des revendications 1 à 6. Airplane characterized in that at least one of its structural elements is provided with a cavity in which is arranged an exciter element (10) according to any one of claims 1 to 6. Avion caractérisé en ce qu'au moins l'un de ses éléments (21) d'extrémité d'aile est muni d'une cavité dans laquelle est disposé un élément excitateur (10) selon l'une quelconque des revendications 1 à 6.Airplane characterized in that at least one of its wing end elements (21) is provided with a cavity in which is arranged an exciter element (10) according to any one of claims 1 to 6.
EP02291271A 2001-05-25 2002-05-23 Slot antenna for airplane Expired - Lifetime EP1263080B8 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0106903A FR2825191B1 (en) 2001-05-25 2001-05-25 RADIO FREQUENCY TRANSMISSION / RECEPTION ANTENNA AND AIRCRAFT USING SUCH ANTENNA
FR0106903 2001-05-25

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EP1263080A1 true EP1263080A1 (en) 2002-12-04
EP1263080B1 EP1263080B1 (en) 2009-09-02
EP1263080B8 EP1263080B8 (en) 2009-11-04

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US (1) US6653980B2 (en)
EP (1) EP1263080B8 (en)
AT (1) ATE441949T1 (en)
BR (1) BR0201918A (en)
CA (1) CA2387206C (en)
DE (1) DE60233544D1 (en)
FR (1) FR2825191B1 (en)

Families Citing this family (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7182297B2 (en) * 2003-01-17 2007-02-27 The Insitu Group, Inc. Method and apparatus for supporting aircraft components, including actuators
US6954182B2 (en) * 2003-01-17 2005-10-11 The Insitu Group, Inc. Conductive structures including aircraft antennae and associated methods of formation
DE10335216B4 (en) * 2003-08-01 2005-07-14 Eads Deutschland Gmbh In the area of an outer surface of an aircraft arranged phased array antenna
US7339537B2 (en) * 2004-10-28 2008-03-04 Alliant Techsystems Inc. Capacitive drive antenna and an air vehicle so equipped
US7624951B1 (en) 2006-08-04 2009-12-01 Hawker Beechcraft Corporation Aircraft with antennas mounted on the tops and bottoms of aerodynamic-surface extensions
US7737898B2 (en) * 2007-03-01 2010-06-15 L-3 Communications Integrated Systems, L.P. Very high frequency line of sight winglet antenna
FR2915643B1 (en) * 2007-04-26 2009-07-10 Bouygues Telecom Sa TRANSPARENT ANTENNA REPEATER SYSTEM INTEGRATED IN A GLASS
US8395557B2 (en) 2007-04-27 2013-03-12 Northrop Grumman Systems Corporation Broadband antenna having electrically isolated first and second antennas
US7861969B2 (en) * 2007-05-24 2011-01-04 The Boeing Company Shaped composite stringers and methods of making
US7605757B1 (en) * 2007-05-31 2009-10-20 Rockwell Collins, Inc. Multiple signal receiver
US7879276B2 (en) * 2007-11-08 2011-02-01 The Boeing Company Foam stiffened hollow composite stringer
US8026857B2 (en) * 2008-01-17 2011-09-27 The Boeing Company Wireless data communication and power transmission using aircraft structures having properties of an electromagnetic cavity
US7889142B1 (en) 2008-08-27 2011-02-15 Lockheed Martin Corporation Aerodynamic wingtip device with integral ground plane
US8540921B2 (en) * 2008-11-25 2013-09-24 The Boeing Company Method of forming a reinforced foam-filled composite stringer
US8235327B2 (en) 2009-03-18 2012-08-07 Insitu, Inc. Adjustable servomechanism assemblies and associated systems and methods
US8500066B2 (en) * 2009-06-12 2013-08-06 The Boeing Company Method and apparatus for wireless aircraft communications and power system using fuselage stringers
US8570152B2 (en) 2009-07-23 2013-10-29 The Boeing Company Method and apparatus for wireless sensing with power harvesting of a wireless signal
US8617687B2 (en) * 2009-08-03 2013-12-31 The Boeing Company Multi-functional aircraft structures
US8354968B1 (en) * 2010-04-08 2013-01-15 Paulsen Lee M Boxed feed for improved high frequency (HF) shunt antenna performance
US9705185B2 (en) * 2013-04-11 2017-07-11 Raytheon Company Integrated antenna and antenna component
US9994298B2 (en) 2015-06-30 2018-06-12 Lockheed Martin Corporation System for embedded removable aperture
FI126944B (en) * 2016-01-27 2017-08-15 Stealthcase Oy Apparatus and method for receiving and further emitting electromagnetic signals

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB643557A (en) * 1948-06-30 1950-09-20 Mini Of Supply Improvements in or relating to aerial systems
GB803723A (en) * 1956-11-09 1958-10-29 Standard Telephones Cables Ltd Improvements in or relating to aircraft antenna
US3534370A (en) * 1968-08-09 1970-10-13 Lockheed Aircraft Corp Ferrite-loaded notch antenna

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2505751A (en) * 1946-09-27 1950-05-02 John T Bolljahn Broad band antenna
US3943520A (en) * 1975-03-07 1976-03-09 The United States Of America As Represented By The Secretary Of The Army Nose cone capacitively tuned wedge antenna
US5187489A (en) * 1991-08-26 1993-02-16 Hughes Aircraft Company Asymmetrically flared notch radiator
US6047925A (en) * 1993-07-01 2000-04-11 The Boeing Company Nose gear door integral composite glide slope antenna
US5461392A (en) * 1994-04-25 1995-10-24 Hughes Aircraft Company Transverse probe antenna element embedded in a flared notch array
US5748152A (en) * 1994-12-27 1998-05-05 Mcdonnell Douglas Corporation Broad band parallel plate antenna
US5825332A (en) * 1996-09-12 1998-10-20 Trw Inc. Multifunction structurally integrated VHF-UHF aircraft antenna system
US6094171A (en) * 1998-10-23 2000-07-25 Trw Inc. External pod with an integrated antenna system that excites aircraft structure, and a related method for its use

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB643557A (en) * 1948-06-30 1950-09-20 Mini Of Supply Improvements in or relating to aerial systems
GB803723A (en) * 1956-11-09 1958-10-29 Standard Telephones Cables Ltd Improvements in or relating to aircraft antenna
US3534370A (en) * 1968-08-09 1970-10-13 Lockheed Aircraft Corp Ferrite-loaded notch antenna

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FR2825191A1 (en) 2002-11-29
CA2387206A1 (en) 2002-11-25
ATE441949T1 (en) 2009-09-15
US20020186170A1 (en) 2002-12-12
BR0201918A (en) 2003-04-22
CA2387206C (en) 2012-02-28
FR2825191B1 (en) 2004-04-16
EP1263080B8 (en) 2009-11-04
EP1263080B1 (en) 2009-09-02
DE60233544D1 (en) 2009-10-15
US6653980B2 (en) 2003-11-25

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