EP1204158B1 - Structure d'antenne pour appareils volants et aéronefs - Google Patents

Structure d'antenne pour appareils volants et aéronefs Download PDF

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Publication number
EP1204158B1
EP1204158B1 EP20010125860 EP01125860A EP1204158B1 EP 1204158 B1 EP1204158 B1 EP 1204158B1 EP 20010125860 EP20010125860 EP 20010125860 EP 01125860 A EP01125860 A EP 01125860A EP 1204158 B1 EP1204158 B1 EP 1204158B1
Authority
EP
European Patent Office
Prior art keywords
antenna
conductive
folded edge
aircraft
edge
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.)
Expired - Lifetime
Application number
EP20010125860
Other languages
German (de)
English (en)
Other versions
EP1204158A3 (fr
EP1204158A2 (fr
Inventor
Ludwig Mehltretter
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Defence and Space GmbH
Original Assignee
EADS Deutschland GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority claimed from DE10151288A external-priority patent/DE10151288B4/de
Application filed by EADS Deutschland GmbH filed Critical EADS Deutschland GmbH
Publication of EP1204158A2 publication Critical patent/EP1204158A2/fr
Publication of EP1204158A3 publication Critical patent/EP1204158A3/fr
Application granted granted Critical
Publication of EP1204158B1 publication Critical patent/EP1204158B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/27—Adaptation for use in or on movable bodies
    • H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
    • H01Q1/286—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
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/36—Structural form of radiating elements, e.g. cone, spiral, umbrella; Particular materials used therewith
    • 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
    • H01Q9/40—Element having extended radiating surface
    • 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
    • H01Q9/42—Resonant antennas with feed to end of elongated active element, e.g. unipole with folded element, the folded parts being spaced apart a small fraction of the operating wavelength

Definitions

  • the invention relates to an aerodynamic active surface with integrated structure antenna for aircraft or aircraft, which has an approximately omnidirectional radiation pattern and which is arranged as a conductive element on the dielectrically active material of a non-conductive layer, which forms the base layer of the surface of the aerodynamic effective surface of the aircraft the radiating element is arranged around a folding edge of the aerodynamic working surface of the aircraft and the conductive surface is partially or completely surrounded by a region of the non-conductive layer and wherein the structural antenna is fed in the region of the conductive surface facing away from the folding edge.
  • Antennas to be used on aircraft or aircraft are subject to a number of requirements. If possible, the contour of the aircraft or aircraft should not be influenced so much that the aerodynamic conditions and thus the flight characteristics change significantly.
  • the arrangement and mounting of the antenna must be in line with the mechanical structure of the structural parts and the mechanical strength of the structure must not be impaired.
  • the Radar Wegstreuquerites should as little as possible be changed.
  • antennas Since the installation of antennas in aircraft or aircraft is very limited, the antennas are increasingly installed in wings, tail units or in the associated rudder flaps.
  • the use of antennas in these very narrow-structure elements is problematic because the radiating properties in the edge direction are severely limited because of the small aperture in this direction.
  • U.S. Patent 5,191,351 describes a series of folded broadband antennas having symmetrical radiation characteristics.
  • the proposed logarithmic periodic Antennas are basically suitable for installation at wing edges and their antenna diagrams meet the desired requirements.
  • the feeding of the antennas takes place at the folded edge, which results in design-related restrictions.
  • the leading edge of the wings and tail units are made of a sharp, continuous metal edge in order to provide a firm grip on the sharp edges required for low radar detection requirements and sufficient lightning protection for the antennas through a low resistance galvanic connection to the structure guarantee.
  • the antennas described in said document can not meet these requirements.
  • EP-A-0 996 191 describes a slot antenna suitable for attachment to aerodynamic surfaces.
  • a conductive surface of the antenna is arranged around the folding edge and lies on non-conductive material. The typical for Nutantennen feed takes place in a remote from the fold edge of the antenna.
  • US-A-2 614 219 discloses a folded monopole antenna positioned along the fold edge of an aerodynamic effective surface, the metallic fold edge being interrupted by a non-conducting insulator.
  • a metal surface which is arranged centrally within the structure of the antenna to the conductive surfaces, is connected to the outer conductor / zero potential of a balanced floating lead.
  • the metal surface extends either almost to the folding edge or it is conductively connected to the folding edge.
  • An advantageous embodiments can be seen in the fact that the conductive surface of the structure antenna at the folding edge is conductively connectable with a surrounding conductive surface of the aerodynamic active surface.
  • the structure antenna according to the invention has a number of advantages over the prior art.
  • the feeding does not take place at the fold edge, but away from the edge in a region of the wing or tail, in which due to the increasing thickness of the structure of the installation and connection of the structure antenna is facilitated.
  • the possibility of a conductive connection between the structural antenna and the folded edge associated with the structure proves to be a significant advantage because of the lightning protection and in the manufacture of aircraft, which must be equipped for reasons of strength with a metallic sharp edge.
  • the sharp edge includes favorable stealth characteristics as the radar flyer cross section is only slightly degraded.
  • an improvement can be achieved in this respect by providing the edges of the structure antenna consisting of metallic conductive surfaces at an angle to the main direction of the threat, which corresponds to the direction of flight, and the spaces between the structure antenna and the conductive surface layer of the aerodynamic effective area may be chosen very small.
  • FIG. Ia Based on the Fig. Ia and Fig. 4a, the basic structure of the structure of the invention antenna, which is arranged on an aerodynamic active surface 3, explained.
  • An aerodynamic active surface 3 in the form of a wing, a tail or a rudder flap belonging to an unmanned aerial vehicle or an aircraft, has a sharp folding edge 4, around which the structural antenna 1 is arranged.
  • 1 a shows a plan view of only one half of the structure antenna 1, the other half lies symmetrically to the folding edge 4 on the side of the aerodynamic active surface 3 which is not visible here.
  • FIG. 4 a shows the section through the structural antenna 1 belonging to FIG.
  • the aerodynamically effective surface has at least in the region of the structural antenna 1 a base layer 6, 12 of an electrically insulating material such as plastic or ceramic.
  • the conductive part of the structural antenna 1 consists of a conductive surface 9, 11 as can be generated for example by metallization of the surface of the non-conductive layer 6, 12 or in the form of a sheet metal part.
  • this conductive surface 9 is not electrically connected to the folding edge 4 passing along the active surface. However, it can, as shown in Fig. 1 b, 2b and 3b, be conductively connected to the folding edge 4 and thus also with the structure of the aircraft or -Zeugs. If, as shown in FIGS.
  • the structure antenna 1 is at least partially surrounded by a region of the structure non-conductive layer 6, 12 surround, which surrounds the conductive surface 9, 11 in the form of a strip in the embodiment. Outside the region of the non-conductive layer 6, 12, the structure antenna 1 is surrounded by a conductive surface 2, which rests on the non-conductive layer 6,12
  • the basic principle of the structure antenna used here is that a planar resonator with a side length of about 1/2 of the operating wavelength ⁇ on a non-conductive base material such as plastic or ceramic or over an air space is arranged.
  • the reference potential extends at an acute angle to the areal extent of the resonator.
  • the distance to this potential is reduced from the ends of the structure antenna 1 lying away from the folding edge 4 up to the folding edge 4 itself. As a consequence, the characteristic impedance in the region of the ends is large and very small in the region of the folding edge 4.
  • the current distribution across the structure antenna changes inversely proportional to the characteristic impedance.
  • the current flow 5 in the region of the folded edge 4, ie the center of the folded structure antenna, is larger than the conventional patch antennas according to the prior art. Therefore, there is also an increase in the small amount of radiation in the direction of the folding edge 4.
  • an omnidirectional characteristic is approximately achieved in an imaginary plane which lies transversely to the aerodynamically effective area in the direction of flight.
  • an increase in the current density in the region of the folding edge 4 can be achieved in that the area covered by the structure antenna 1 decreases in proportion to its width B as the distance from the edge 4 increases. Examples of these are shown in FIGS. 2a, 2b, 3a and 3b.
  • the structural antenna 1 is, as already described above, a design derived from the known microstrip patch antenna, which is shown schematically simplified in FIG. 1a. It is folded in its central region so that it encloses the edge of a wing, a tail or a rudder.
  • FIGS. 2a,..., 3b show different designs of such structure antennas 1 in plan view.
  • various structural antenna surface shapes such as square, rectangular, triangular, rhombic, circular, elliptical or the like can be used.
  • the edges of the existing essentially plastic wings, empennages or rudders are often reinforced with metal rails in aircraft. For reasons of strength, these metal rails must not be interrupted or replaced by non-conductive plastic elements. Thus, there is a conductive connection with the rest of the metallized structure via this edge. Since the inventive structure antenna 1 has a stress zero point in the region of the folded edge 4, a conductive connection between the structural antenna 1 and the metallic folding edge 4, as in the arrangements according to FIGS. 1 b, 2 b, 3 b, can be realized and is not disadvantageous. These embodiments are preferably used because they well meet the requirements for folding edge strength and lightning protection. With a grounding in the central region of the structure antenna 1, however, a floating input to avoid imbalances by the formation of ground loops is imperative.
  • the feed point lies in the region of the conductive surface 11 of the structure antenna 1 which is farthest from the folded edge 4.
  • the metallic folding edge 4 is insulated in this case from the conductive surface of the support surface, as shown in Fig. 1a, 2a and 3a.
  • a metal surface 14 In the interior of the structure antenna, there is a metal surface 14 extending almost to the folding edge 4, which is connected to the jacket of the coaxial feed line 15 and thus forms the electrical reference potential to the conductive surface 11.
  • the nonconductive layer 12 may be provided with a conductive coating 16 to the vicinity of the structure antenna, leaving a strip of the nonconductive layer 12 exposed.
  • FIG. 4b shows a preferred design with a symmetrical feed using the known Lindenblad ⁇ / 4 -Stopopf 17.
  • the grounding of the conductive surface of the structure antenna 11 at the folding edge 4 is not critical.
  • the feed takes place via the symmetrically arranged feed points 13 a and 13 b, which likewise lie in the region of the conductive surface 11 of the structure antenna 1, which is farthest from the folded edge 4.
  • the metallic folding edge 4 is forcibly symmetrized over the ⁇ / 4 locking pot 17.
  • the conductive surface 11 of the structure antenna is grounded or forcibly balanced at the metallic folding edge 4, since the feed through the ⁇ / 4 locking pot 17 is groundless.
  • Fig. 4c can also be dispensed with a metal surface 14 which extends in the embodiment of Fig. 4b of the folding edge 4 to the locking pot 17.
  • the feeding then takes place directly from the supply line 15 via the blocking pot 17 and the terminals 13a and 13b, which are also in the region of the conductive surface 11 of the structure antenna 1, which is farthest from the folding edge 4.
  • This is a particular advantage for the production achieved because this metal surface 14 is difficult to introduce in the wedge-shaped wing structure. Due to the floating supply and the grounding at the folding edge 4, a good symmetrization results automatically, since a zero potential forms within the structure in the region of the imaginary line of symmetry (represented by dot-dash lines). The reduction of the characteristic impedance towards the folded edge 4 results in the same manner as in the aforementioned examples.
  • FIGS. 1 b, 2 b and 3 b respectively show variants of the previously described designs, in which the conductive surface 9 extends at least with the metallic folding edge 4, which runs along the aerodynamic active surface 3, and also with the conductive surface 2 of the aerodynamically effective surface itself is connected. If the nonconductive layer 12 is not metallized around the structure antenna, then at least the conductive connection between the conductive surface 9 and the folded edge 4 given, which in turn is with the structure at the same potential.

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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)

Claims (4)

  1. Aire de captation aérodynamique avec structure d'antenne intégrée (1) pour des appareils volants ou des aéronefs, qui comporte une caractéristique de rayonnement presque circulaire et est disposée en tant que surface conductrice (9, 11) sur le matériau diélectriquement efficace d'une couche non conductrice qui forme la couche de base de la surface de l'aire de captation aérodynamique (3) de l'appareil volant, la surface conductrice (9, 11) étant disposée autour d'une arête de pliage (4) de l'aire de captation aérodynamique de l'appareil volant et entourée en partie ou entièrement d'une zone de la couche non conductrice (6, 12) et la structure d'antenne (1) étant alimentée dans la zone de la surface conductrice (9, 11) détournée de l'arête de pliage (4), caractérisée en ce qu'une surface métallique (14) qui est disposée à l'intérieur de la structure d'antenne (1) au milieu de la surface conductrice (9, 11) est reliée au conducteur extérieur d'un câble d'alimentation symétrique isolé de la terre (15), si bien que le sens du courant (5) est perpendiculaire à l'arête de pliage (4) et que l'impédance caractéristique au niveau de l'arête de pliage est très inférieure à celle de la zone des extrémités de la structure d'antenne (1) éloignées de l'arête.
  2. Aire de captation aérodynamique avec structure d'antenne intégrée selon la revendication 1, caractérisée en ce que la surface métallique (14) est reliée de manière conductrice à l'arête de pliage (4).
  3. Aire de captation aérodynamique avec structure d'antenne intégrée (1) pour des appareils volants ou des aéronefs, qui comporte une caractéristique de rayonnement presque circulaire et est disposée en tant que surface conductrice (9, 11) sur le matériau diélectriquement efficace d'une couche non conductrice qui forme la couche de base de la surface de l'aire de captation aérodynamique (3) de l'appareil volant, la surface conductrice (9, 11) étant disposée autour d'une arête de pliage (4) de l'aire de captation aérodynamique de l'appareil volant et entourée en partie ou entièrement d'une zone de la couche non conductrice (6, 12) et la structure d'antenne (1) étant alimentée dans la zone de la surface conductrice (9, 11) détournée de l'arête de pliage (4), caractérisée en ce que la surface conductrice (9, 11) de la structure d'antenne est alimentée symétriquement via les raccords sous potentiel (13a) et (13b) du câble d'alimentation symétrique isolé de la terre (15), si bien que le sens du courant (5) est perpendiculaire à l'arête de pliage (4) et que l'impédance caractéristique au niveau de l'arête de pliage est très inférieure à celle de la zone des extrémités de la structure d'antenne (1) éloignées de l'arête.
  4. Aire de captation aérodynamique avec structure d'antenne intégrée selon la revendication 1 ou 3, caractérisée en ce que la surface conductrice (9, 11) sur l'arête de pliage (4) est reliée de manière conductrice (8) à une surface apte à assurer une conduction (2) qui l'entoure.
EP20010125860 2000-11-02 2001-10-30 Structure d'antenne pour appareils volants et aéronefs Expired - Lifetime EP1204158B1 (fr)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
DE10054332 2000-11-02
DE10054332 2000-11-02
DE10151288A DE10151288B4 (de) 2000-11-02 2001-10-22 Struktur-antenne für Fluggeräte oder Flugzeuge
DE10151288 2001-10-22

Publications (3)

Publication Number Publication Date
EP1204158A2 EP1204158A2 (fr) 2002-05-08
EP1204158A3 EP1204158A3 (fr) 2003-12-10
EP1204158B1 true EP1204158B1 (fr) 2006-08-30

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ID=26007550

Family Applications (1)

Application Number Title Priority Date Filing Date
EP20010125860 Expired - Lifetime EP1204158B1 (fr) 2000-11-02 2001-10-30 Structure d'antenne pour appareils volants et aéronefs

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EP (1) EP1204158B1 (fr)
DE (1) DE50110862D1 (fr)

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2614219A (en) * 1947-09-30 1952-10-14 Cary Rex Henry John Aerial system
DE2212647B2 (de) * 1972-03-16 1977-06-23 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Antenne fuer den frequenzbereich zwischen 2 und 30 mhz mit einer in eine metallische struktur eingeschnittenen nut
US5191351A (en) * 1989-12-29 1993-03-02 Texas Instruments Incorporated Folded broadband antenna with a symmetrical pattern
US6097343A (en) * 1998-10-23 2000-08-01 Trw Inc. Conformal load-bearing antenna system that excites aircraft structure

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Publication number Publication date
EP1204158A3 (fr) 2003-12-10
DE50110862D1 (de) 2006-10-12
EP1204158A2 (fr) 2002-05-08

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