EP1204158A2 - 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
EP1204158A2
EP1204158A2 EP01125860A EP01125860A EP1204158A2 EP 1204158 A2 EP1204158 A2 EP 1204158A2 EP 01125860 A EP01125860 A EP 01125860A EP 01125860 A EP01125860 A EP 01125860A EP 1204158 A2 EP1204158 A2 EP 1204158A2
Authority
EP
European Patent Office
Prior art keywords
conductive
folded edge
structural antenna
antenna
structural
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
EP01125860A
Other languages
German (de)
English (en)
Other versions
EP1204158A3 (fr
EP1204158B1 (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 a structural antenna for aircraft or aircraft with approximately omnidirectional radiation pattern, which acts as a conductive element on a non-conductive Layer is arranged, which is the base layer of the surface of an aerodynamic Active area of the aircraft forms, the radiating element around a folded edge the aerodynamic effective area of the aircraft is arranged around.
  • Antennas to be used on aircraft or airplanes are one Subject to a number of requirements.
  • the contour of the aircraft or aircraft should if possible not be influenced so far that the aero-dynamic conditions and thus significantly change the flight characteristics.
  • the arrangement and attachment the antenna must be in accordance with the mechanical structure of the structural parts and the mechanical strength of the structure must not be affected.
  • the radar backscatter cross section should be changed only slightly if possible.
  • antennas in aircraft or aircraft Since the installation location of antennas in aircraft or aircraft is very limited, the antennas in wings, tail units or in the corresponding rudder flaps are increasingly used built-in. The use of antennas in these very narrow buildings Elements is problematic because the radiation properties in the edge direction because of the small aperture are strongly restricted in this direction.
  • US Pat. No. 5,191,351 describes a series of folded broadband antennas with symmetrical Radiation pattern.
  • the proposed log-periodic Antennas are basically suitable for installation on wing edges and their antenna diagrams meet the desired requirements. Feeding the antennas takes place at the folded edge, which results in design-related restrictions.
  • the leading edge of wings and tail surfaces consists of a sharp, continuous metal edge to strengthen the sharp edges to master that for the requirements of low radar detectability are necessary, and on the other hand adequate lightning protection of the antennas to ensure a low-resistance galvanic connection to the structure.
  • the in the Antennas described above can not meet these requirements fulfill.
  • an antenna suitable for aerodynamic active surfaces shows US 3,039,095.
  • the active surface may have sharp edges. Since the Antenna elements are each arranged on the side surfaces of the aerodynamic active surface there are losses in the radiation in the direction of the edges.
  • the object is achieved in that the structure antenna is flat Antenna is executed and integrated in the surface of the aerodynamic effective area is.
  • the aerodynamic effective area in the area of the structural antenna consists of the dielectric material of a non-conductive layer.
  • the conductive surface of the Structural antenna is wholly or at least partially from a non-conductive area Surround layer, which may preferably have the shape of a strip.
  • the structure antenna is fed in the area of the conductive surface facing away from the folded edge, so that the current direction is perpendicular to the folded edge and the wave resistance is on the folded edge is very much lower than in the area of the ends of the structural antenna remote from the edge.
  • the structure antenna according to the invention has one compared to the prior art Number of advantages.
  • the feed is not at the folded edge, but removed from the edge in an area of the wing or tail unit in which due to the increasing Thickness of the structure facilitates the installation and connection of the structure antenna becomes.
  • the possibility of a conductive connection between the structure antenna and the folding edge associated with the structure proves to be a significant advantage because of the Lightning protection and in the manufacture of aircraft, for strength reasons with a metallic sharp edge must be equipped.
  • the sharp edge includes Favorable stealth properties, since the radar backscatter cross section deteriorates only slightly becomes.
  • edges of the structural antenna consisting of metallic conductive surfaces at an angle to the main threat direction, which corresponds to the direction of flight and in that the gaps between the pattern antenna and the conductive
  • the surface layer of the aerodynamic active area may be chosen to be very small.
  • FIGS. 1a and 4a Structural antenna which is arranged on an aerodynamic active surface 3, explained.
  • An aerodynamic active surface 3 in the form of an aerofoil, an empennage or a rudder flap belonging to an unmanned aerial vehicle or aircraft, has a sharp folded edge 4, around which the structure antenna 1 is arranged is.
  • Ia shows a top view of only one half of the structural antenna 1 the other half is symmetrical to the folded edge 4 on the side of the not visible here aerodynamic active surface 3.
  • FIG. 4a shows the section belonging to FIG. 1a through the structural antenna 1.
  • the aerodynamic effective area points at least in the area of the Structural antenna 1 a base layer 6, 12 made of an electrically insulating material such as Plastic or ceramic.
  • the conductive part of the structure antenna 1 consists of a conductive surface 9, 11 as for example by metallizing the surface of the non-conductive layer 6, 12 or in the form of a sheet metal part can be produced.
  • conductive surface 9 is not the same as that along the active surface continuous folding edge 4 electrically connected. But it can, as in Fig. 1 b, 2b and 3b, with the folded edge 4 and thus also with the structure of the aircraft be connected conductively. If, as shown in Fig. Ia, 2a and 3a, of the folded edge 4 is insulated, the conductive surface 9 ends in the immediate vicinity of the folded edge 4.
  • the feeding of the structural antenna 1 is different in FIGS.
  • the structural antenna 1 is at least partially surrounded by a region of the non-conductive layer 6, 12, the conductive surface 9, 11 in the form of a strip in the exemplary embodiment surrounds.
  • the structure antenna is outside the region of the non-conductive layer 6, 12 1 surrounded by a conductive surface 2, which is on the non-conductive layer 6, 12 rests
  • the basic principle of the structural antenna used here is that a flat one Resonator with a side length of about 1/2 of the operating wavelength h on one non-conductive base material such as plastic or ceramic or arranged above an air space is.
  • the radiation characteristic is assumed that the reference potential runs at an acute angle to the planar extent of the resonator.
  • In the present Invention reduces the distance to this potential from the distant to Folded edge 4 lying ends of the structural antenna 1 up to the folded edge 4 itself.
  • the wave resistance is large in the area of the ends and in the area of the folded edge 4 very small. This changes in inverse proportion to the wave resistance also the current distribution over the structure antenna.
  • the current flow 5 in the area of Folded edge 4, d. H. the center of the folded structure antenna, is compared to the usual Prior art patch antennas larger. That is why there is also increasing the low radiation per se in the direction of the folded edge 4.
  • an omnidirectional characteristic is achieved in an imaginary Approximately level that is transverse to the aerodynamic effective area in the direction of flight.
  • an increase in the current density can be achieved in the area of the folded edge 4 in that the structure antenna 1 covered area proportional to its width B with increasing distance reduced from edge 4. Examples of this are shown in FIGS. 2a, 2b, 3a and 3b.
  • the structure antenna 1 is one from the known microstrip patch antenna Derived design, shown schematically simplified in Fig. 1 a is. It is folded in its central area so that it is the edge of a wing, of a tail unit or a rudder. 2a, ..., 3b show different Designs of such structure antennas 1 in plan view. As with such structural antennas usual, different structure antenna surface shapes such as square, rectangular, triangular, diamond-shaped, circular, elliptical or similar to Come into play.
  • the edges of the aircraft are often essentially Plastic wings, tail units or rudders with metal rails strengthened. For strength reasons, these metal rails must not be interrupted and also not be replaced by non-conductive plastic elements. So is a senior Connected to the rest of the metallized structure via this edge. Since the structure antenna 1 according to the invention in the area of the folded edge 4 a voltage zero has, is a conductive connection between the pattern antenna 1 and the metallic folding edge 4, as in the arrangements according to Figures 1 b, 2b, 3b, can be realized and also not disadvantageous. These embodiments are preferably used because they meet the requirements for the strength of the folded edge and for lightning protection fulfill. If the structure antenna 1 is grounded in the middle, it is groundless Infeed to avoid asymmetries through the formation of earth loops absolutely necessary.
  • the metallic folded edge 4 is of the conductive type Surface of the wing isolated, as shown in Fig. 1a, 2a and 3a.
  • the structure antenna is a metal surface that extends almost into the folded edge 4 14, which is connected to the jacket of the coaxial supply line 15 and thus that electrical reference potential to the conductive surface 11 forms.
  • the non-conductive layer 12 close to the structure antenna with a conductive coating 16 can be provided, a strip of the non-conductive layer 12 being left free becomes.
  • FIG. 4b shows a preferred design with a symmetrical feed using the known Lindenblad ⁇ / 4 locking pot 17.
  • This type of Infeed is the grounding of the conductive surface of the structure antenna 11 at the folded edge 4 not critical.
  • the feed takes place via the symmetrically arranged Feed points 13a and 13b, which are also in the area of the conductive surface 11 of the Structure antenna 1 are the furthest from the folded edge 4.
  • the metallic Folding edge 4 is forcibly symmetrized via the h / 4 locking pot 17.
  • the conductive Surface 11 of the structure antenna is grounded on the metallic folded edge 4 or compulsorily symmetrical, since the feed through the h / 4 blocking pot 17 is ungrounded.
  • Fig. 4c can be on a metal surface 14, which in the embodiment 4b runs from the folded edge 4 to the locking pot 17, can also be dispensed with.
  • the Power is then supplied directly from the supply line 15 via the locking pot 17 and the connections 13a and 13b, which are also in the area of the conductive surface 11 of the structure antenna 1, which is furthest from the folded edge 4.
  • This makes it a special one Achieved manufacturing advantage because this metal surface 14 is difficult to wedge-shaped Wing structure is to be introduced.
  • Due to the floating supply and grounding the folded edge 4 results in a good symmetry by itself, since in the area of imaginary line of symmetry (dash-dotted lines) within the structure a zero potential formed.
  • the reduction in the wave resistance to the folded edge 4 results themselves in the same way as in the previous examples.
  • 1b, 2b and 3b are variants of the designs already described shown, in which the conductive surface 9 at least with the metallic folded edge 4, which runs along the aerodynamic active surface 3, and also with the conductive surface 2 of the aerodynamic active area itself is connected. Should be the non-conductive Layer 12 around the structure antenna must not be metallized, so is at least the conductive one Given connection between the conductive surface 9 and the folded edge 4, the in turn has the same potential with the structure.

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

Family

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

Country Status (2)

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

Citations (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
DE2212647A1 (de) * 1972-03-16 1973-09-20 Messerschmitt Boelkow Blohm Nutantenne
US5191351A (en) * 1989-12-29 1993-03-02 Texas Instruments Incorporated Folded broadband antenna with a symmetrical pattern
EP0996191A2 (fr) * 1998-10-23 2000-04-26 TRW Inc. Système d'antenne portant conformable pour exciter la structure d aéronef

Patent Citations (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
DE2212647A1 (de) * 1972-03-16 1973-09-20 Messerschmitt Boelkow Blohm Nutantenne
US5191351A (en) * 1989-12-29 1993-03-02 Texas Instruments Incorporated Folded broadband antenna with a symmetrical pattern
EP0996191A2 (fr) * 1998-10-23 2000-04-26 TRW Inc. Système d'antenne portant conformable pour exciter la structure d aéronef

Also Published As

Publication number Publication date
DE50110862D1 (de) 2006-10-12
EP1204158A3 (fr) 2003-12-10
EP1204158B1 (fr) 2006-08-30

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