EP0881703A1 - Starre Antenne und entsprechendes Herstellungsverfahren - Google Patents
Starre Antenne und entsprechendes Herstellungsverfahren Download PDFInfo
- 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
- Authority
- 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- Withdrawn
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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
-
- 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)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR9706663A FR2764123B1 (fr) | 1997-05-30 | 1997-05-30 | Antenne rigide et procede de fabrication correspondant |
FR9706663 | 1997-05-30 |
Publications (1)
Publication Number | Publication Date |
---|---|
EP0881703A1 true EP0881703A1 (de) | 1998-12-02 |
Family
ID=9507422
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP98401277A Withdrawn EP0881703A1 (de) | 1997-05-30 | 1998-05-28 | Starre Antenne und entsprechendes Herstellungsverfahren |
Country Status (2)
Country | Link |
---|---|
EP (1) | EP0881703A1 (de) |
FR (1) | FR2764123B1 (de) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2000049679A1 (en) * | 1999-02-18 | 2000-08-24 | Totalförsvarets Forskningsinstitut | Antenna carrier for connection to an air vehicle |
Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4080603A (en) * | 1976-07-12 | 1978-03-21 | Howard Belmont Moody | Transmitting and receiving loop antenna with reactive loading |
US4101898A (en) * | 1976-07-26 | 1978-07-18 | David Lee Ingram | Base fed, top-loaded vertical whip antenna |
US4375642A (en) * | 1980-09-25 | 1983-03-01 | Robert Bosch Gmbh | Rod antenna, particularly for mobile FM signal transducing applications |
GB2113922A (en) * | 1982-01-09 | 1983-08-10 | British Aerospace | Antennae |
US4460896A (en) * | 1980-06-16 | 1984-07-17 | Shmitka Clarence F | Antenna with tunable helical resonator |
US4510500A (en) * | 1983-01-28 | 1985-04-09 | The United States Of America As Represented By The Secretary Of The Army | Aircraft shorted loop antenna with impedance matching and amplification at feed point |
EP0505673A1 (de) * | 1991-03-23 | 1992-09-30 | Robert Bosch Gmbh | Stabförmiger Mehrbereichsstrahler |
FR2680282A1 (fr) * | 1991-08-06 | 1993-02-12 | Tramec | Antenne tubulaire et son procede de fabrication. |
-
1997
- 1997-05-30 FR FR9706663A patent/FR2764123B1/fr not_active Expired - Fee Related
-
1998
- 1998-05-28 EP EP98401277A patent/EP0881703A1/de not_active Withdrawn
Patent Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4080603A (en) * | 1976-07-12 | 1978-03-21 | Howard Belmont Moody | Transmitting and receiving loop antenna with reactive loading |
US4101898A (en) * | 1976-07-26 | 1978-07-18 | David Lee Ingram | Base fed, top-loaded vertical whip antenna |
US4460896A (en) * | 1980-06-16 | 1984-07-17 | Shmitka Clarence F | Antenna with tunable helical resonator |
US4375642A (en) * | 1980-09-25 | 1983-03-01 | Robert Bosch Gmbh | Rod antenna, particularly for mobile FM signal transducing applications |
GB2113922A (en) * | 1982-01-09 | 1983-08-10 | British Aerospace | Antennae |
US4510500A (en) * | 1983-01-28 | 1985-04-09 | The United States Of America As Represented By The Secretary Of The Army | Aircraft shorted loop antenna with impedance matching and amplification at feed point |
EP0505673A1 (de) * | 1991-03-23 | 1992-09-30 | Robert Bosch Gmbh | Stabförmiger Mehrbereichsstrahler |
FR2680282A1 (fr) * | 1991-08-06 | 1993-02-12 | Tramec | Antenne tubulaire et son procede de fabrication. |
Non-Patent Citations (1)
Title |
---|
BOAG A ET AL: "DESIGN OF ELECTRICALLY LOADED WIRE ANTENNAS USING GENETIC ALGORITHMS", IEEE TRANSACTIONS ON ANTENNAS AND PROPAGATION (FOR THE WHOLE COLLECTION USE BOCA..LI MAX), vol. 44, no. 5, 1 May 1996 (1996-05-01), pages 687 - 695, XP000584238 * |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
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 |
---|---|
FR2764123B1 (fr) | 1999-07-30 |
FR2764123A1 (fr) | 1998-12-04 |
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Legal Events
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K1C1 | Correction of patent application (title page) published |
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