EP2683028B1 - Antennensystem - Google Patents

Antennensystem Download PDF

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Publication number
EP2683028B1
EP2683028B1 EP20130174798 EP13174798A EP2683028B1 EP 2683028 B1 EP2683028 B1 EP 2683028B1 EP 20130174798 EP20130174798 EP 20130174798 EP 13174798 A EP13174798 A EP 13174798A EP 2683028 B1 EP2683028 B1 EP 2683028B1
Authority
EP
European Patent Office
Prior art keywords
antenna
antenna unit
protecting device
ring
lateral outline
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.)
Not-in-force
Application number
EP20130174798
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English (en)
French (fr)
Other versions
EP2683028A1 (de
Inventor
Jean-Patrick Moreau
Roland Carre
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.)
Dassault Aviation SA
Original Assignee
Dassault Aviation SA
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Filing date
Publication date
Application filed by Dassault Aviation SA filed Critical Dassault Aviation SA
Publication of EP2683028A1 publication Critical patent/EP2683028A1/de
Application granted granted Critical
Publication of EP2683028B1 publication Critical patent/EP2683028B1/de
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • H01Q1/002—Protection against seismic waves, thermal radiation or other disturbances, e.g. nuclear explosion; Arrangements for improving the power handling capability of an antenna
    • 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
    • H01Q1/281—Nose antennas
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/50—Structural association of antennas with earthing switches, lead-in devices or lightning protectors
    • 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
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q21/00—Antenna arrays or systems
    • H01Q21/0006—Particular feeding systems
    • H01Q21/0037—Particular feeding systems linear waveguide fed arrays
    • H01Q21/0043—Slotted waveguides
    • H01Q21/005—Slotted waveguides arrays

Definitions

  • the invention relates to an antenna assembly according to the preamble of claim 1.
  • the invention applies in particular to an airborne radar antenna assembly adapted to the detection and location of weather phenomena.
  • meteorological radars are housed in the forward tip. They generally comprise a slotted antenna, mobile in elevation and azimuth, so as to scan the entire space in front of the aircraft.
  • This antenna is covered by a radome, which forms the outer surface of the front tip of the aircraft and gives it its shape.
  • This radome is electromagnetically transparent to allow the antenna to emit and receive electromagnetic waves.
  • This radome aims to protect the radar antenna including direct effects of lightning.
  • the radome includes conductive lightning arresters regularly arranged on its surface so that in case of lightning on the front tip of the aircraft, the lightning current will flow through these strips to avoid the Lightning attachment on the antenna through the radome.
  • the slot antenna is generally disk-shaped and has a profile in the form of stair steps on its lateral contour. However, these steps have projecting angles forming areas of electric field strength, likely to cause peak effects. Indeed, the electric field around the antenna being maximum near these protruding angles, they are likely to be attachment points of the lightning, so to be responsible for lightning of the antenna.
  • the lightning resistance of the nose of the aircraft is conditioned both by the dielectric characteristics of the material constituting the radome, and by the guaranteed minimum distance between the antenna and the interior wall of the radome, whatever the position of the the antenna, and by the establishment of lightning arrester bands distributed around the periphery of the radome.
  • the guarantee of a minimum distance between the antenna, which is metallic, and the inner wall of the radome makes it possible to limit the electric field developing in the vicinity of the antenna under fogging conditions.
  • the rating of an aircraft in relation to its direct lightning performance is obtained by means of standardized tests.
  • This qualification once acquired, is extended from one aircraft to another, as long as the configuration of the aircraft vis-à-vis the lightning resistance remains unchanged, that is to say as long as the characteristics conditioning the lightning resistance of the aircraft are unchanged. However, as soon as one of these characteristics is modified, the lightning resistance of the front tip of the aircraft is modified. A new qualification is then required, which implies redoing all or part of the qualification tests.
  • the characteristics conditioning the lightning resistance depend on the characteristics of the meteorological radar used, in particular the dimensions of the antenna, its positioning inside the radome and the sweep in the space to be made by the radar. antenna.
  • these characteristics of the radar are not standardized and can be modified to improve performance.
  • the position of the antenna can be advanced in the radome, and / or its increased diameter, the amplitude of the scan is thus increased.
  • the object of the invention is therefore to provide an antenna assembly decreasing the risk of attachment of lightning on the antenna of the weather radar without the need to change the geometry of the nose of the aircraft.
  • the invention relates to an antenna assembly according to claim 1.
  • the antenna assembly comprises one or more of the features of claims 2 to 15.
  • the antenna of the assembly is an antenna of a weather radar, disposed in the front tip of the aircraft.
  • the invention also relates to an aircraft comprising an antenna assembly according to the invention.
  • the assembly 1 is intended to be positioned in the front tip of an aircraft, and to be covered by a radome (not shown) forming the outer surface of this nose.
  • the antenna assembly 1 comprises an antenna 2 and a device 4 for protecting the antenna 2.
  • the antenna 2 is a flat, metallic antenna having a plurality of slots. Such an antenna is generally referred to as “antenna to slots ".
  • the antenna 2 comprises a front surface 2a of radiation, substantially flat, intended to be oriented towards the outside of the aircraft, through the radome.
  • the antenna 2 also comprises a flat rear surface 2b.
  • the front or rear plane of the antenna will be referred to as a plane respectively comprising the front surface 2a or the rear surface 2b of the antenna 2, and the terms "inside” and “outside”, applied to a surface, shall be understood respectively as a peripheral surface oriented towards the axis AA 'which passes through the center of the antenna 2 orthogonal to the antenna, and a peripheral surface oriented away from the axis A-A '.
  • the antenna 2 comprises a network 6 of radiating elements 8.
  • Each radiating element 8 has the shape of a rectangular cross section tube, closed at its ends, forming a waveguide.
  • Each radiating element 8 thus comprises a front wall 8a, forming a portion of the front surface 2a of the antenna, a rear wall 8b, two sides extending between the front walls 8a and 8b, not visible in the figures, and two end walls 8e.
  • Each radiating element 8 is provided on its front wall 8a with radiating sources such as slots, not shown.
  • the radiating elements 8 are of variable lengths. They are juxtaposed by their sides, aligning their respective media in the same longitudinal direction, between two terminal radiating elements 8t, to form the network 6.
  • the antenna 2 thus has a thickness e defined as the thickness of the radiating elements 8 according to a transverse direction.
  • the radiating elements 8 are adapted to form together a coherent electromagnetic field whose propagation direction is perpendicular to the emission surface.
  • the lengths of the radiating elements 8 are such that the antenna 2 has the general shape of a disk.
  • the front 2a and rear 2b surfaces are respectively formed by the front walls 8a and 8b of the radiating elements 8. Moreover, the end walls 8e radiating elements and the sides of the radiating terminal elements 8t directed towards the outside of the antenna 2 form a lateral contour 2c of the antenna 2.
  • the lateral contour 2c of the antenna 2 has at least one angular region.
  • the lateral contour 2c is crenellated, in the form of "steps".
  • the front surface 2a of the antenna 2 comprises a plurality of projecting angles formed by corners 9 of the front walls 8a of at least a portion of the radiating elements 8
  • the lateral contour of the antenna 2 comprises a plurality 10 of the edges protruding rearwardly of the antenna 2 from the corners 9.
  • the corners 9 and the edges 10 form areas of electric field reinforcement likely to cause peak effects.
  • the diameter of the antenna 2 is between 15 and 22 inches, and its thickness e is less than 12 mm.
  • the protective device 4 is able to reduce the electric field at the periphery of the antenna 2, by eliminating the electric field reinforcement zones due to the corners 9 and the edges 10.
  • ring 12 of protection also called Corona ring or curving ring, generally O-ring.
  • the ring has an inner surface 12i, facing the antenna 2, and an outer surface 12e.
  • the ring 12 is arranged around the antenna 2, its inner surface 12i being in electrical contact with the antenna 2.
  • the outer surface 12e is wide and rounded. It is therefore devoid of reinforcement zones likely to cause peak effects.
  • the inner and outer surfaces are metallic.
  • the electric field reinforcement zones present on the antenna by its construction are thus "masked" by the protection device 4.
  • the risks for it to hit one of the field-strengthening zones of the antenna 2 are thus rendered virtually zero.
  • the protection device 4 also comprises a deformable flexible seal 14 (visible on the Figure 2 ), interposed between the ring 12 and the antenna 2, and intended to ensure contact between the ring 12 and the antenna 2.
  • the ring 12 has a general shape of revolution about the axis A-A '. It thus has a longitudinal section of generally circular shape.
  • the ring 12 forms a hollow tube 16 wound around the axis A-A '.
  • the ring 12 comprises a longitudinal longitudinal front wall 22, of annular shape, and an annular transverse wall 24, advantageously orthogonal to the longitudinal wall 22 and disposed in line with the lateral contour 2c of the antenna 2.
  • the ring 12 further comprises a rear wall 25 of radial section in curved shape, for example in the form of a circular arc, which extends between an inner rim of the longitudinal wall 22 and a front edge of the transverse wall 24.
  • this circular arc subtends an angle greater than or equal to 270 °.
  • the radial sections of the longitudinal and transverse walls 22 form, for example, radii of this circular arc.
  • the tube 16 is thus defined by the longitudinal wall 22, the transverse wall 24 and the rear wall 25.
  • the longitudinal and transverse walls 24 comprise a longitudinal bearing face 22a and a transverse face 24a, respectively, oriented towards the outside of the tube 16.
  • the rear wall 25 has an external face 25a, that is to say oriented towards the outside the tube 16, which forms the outer surface 12e of the ring 12.
  • the outer surface 12e is generally continuous, convex, curved and devoid of macroscopic asperities. It is therefore substantially free of electric field reinforcement zones.
  • the ring 12 further comprises a rim 28 for holding the antenna 2, generally of revolution about the axis AA ', which projects from the connection zone of the rear wall 25 with the transverse wall 24, orthogonally to the transverse wall 24, towards the center of the antenna 2.
  • the flange 28 has a holding face 28a facing the inside of the tube 16, facing the bearing face 22a.
  • the longitudinal wall 22, the transverse wall 24 and the retaining rim 28 thus define a housing for receiving the antenna 2.
  • the longitudinal wall 22 and the transverse wall 24 form an angle-iron 30 for receiving the antenna 2 while the flange 28 forms a retaining member of the antenna 2 in the bracket 30.
  • the longitudinal bearing surfaces 22a and 24a and the retaining surface 28a form the inner surface 12i of the ring 12.
  • the ring 12 thus comprises a medial portion, surrounding the antenna 2 at its lateral contour 2c, and a rear portion, disposed at the rear of the antenna, facing the rear surface 2b.
  • the ring 12 has an inner radius R 12 , defined as the distance between the axis AA 'and the surface 24a of the transverse wall 24, slightly greater than the radius R 2 of the antenna 2, that is to say the radius R 2 of a circle which would be circumscribed to the antenna 2.
  • the radius R 16 of the tube 16 is greater than the thickness e of the antenna. This radius R 16 is for example between 1.2 and 3 times the thickness e of the antenna, preferably equal to 10mm.
  • the ring 12 is made from a light and rigid material, metal outer surface.
  • the ring 12 is made from a body formed of an insulating material, for example a plastic material covered with a metal layer, for example nickel, chromium, aluminum or tin.
  • the insulating body is for example made by stereolithography, while the metal layer is for example deposited by electrolytic deposition, or by spraying or evaporation under vacuum.
  • the flexible joint 14, of general shape of revolution about a central axis AA ', has a radial section L-shaped.
  • the flexible seal 14 thus comprises a longitudinal branch 32 and a transverse branch 34. Its outer surface is shaped conjugate to the surface of the bracket 30 formed by the bearing surfaces 22a, 24a.
  • the flexible seal 14 is thus disposed in surface abutment against the outer surface of the bracket 30, the outer surfaces of the longitudinal and transverse branches 32 being placed in surface abutment against the external bearing surfaces 22a and 24a respectively.
  • the thickness of the transverse branch 34 of the seal 14 is substantially equal to the difference between the radius R 2 of the antenna and the radius R 12 of the ring. Moreover, the thickness of the longitudinal branch 32 of the gasket 14 is substantially equal to the difference between the radius R 16 of the tube 16 and the thickness e of the antenna 2.
  • the longitudinal and transverse branches 32 are advantageously equal thickness.
  • the seal 14 is made of a flexible insulating material, for example based on silicone or elastomer.
  • the longitudinal internal surfaces 32a and transverse 34a of the gasket 14 as well as the surface 28a of the retaining rim 28 bear against the antenna 2.
  • the ring 12 is advantageously made in one piece.
  • the retaining rim 28 comprises a plurality of notches 31, intended to allow the engagement of the antenna 2 in the angle 30.
  • each of the notches 31 is adapted to receive one of the corners 9 of the antenna 2 when its engagement in the ring 12 in a direction parallel to the axis A-A '.
  • the ring 12 also comprises means for locking the angular position of the antenna 2 (not visible in the figures), adapted to lock in rotation about the axis AA 'the antenna 2 in the ring 12, once this engaged in the ring 12.
  • These locking means comprise for example a plurality of stops protruding into the bracket 30.
  • the antenna 2 is installed in the device 4 by engaging the antenna 2, parallel to the axis A-A ', in the angle 30, each corner 9 of the antenna 2 being received in a notch 31.
  • the device 4 is then turned around the axis AA 'to an abutment position, in which the antenna 2 is locked in rotation in the ring 12 by the locking means.
  • the protective device 4 formed of the ring 12 and the seal 14 is thus arranged around the antenna 2, coming into contact with each of the projecting ridges 10 of the antenna 2.
  • each of the projecting ridges 10 bears against the transverse internal surface 34a, and the longitudinal inner surface 32a receives, in surface abutment, an annular outer portion of the rear surface 2b of the antenna 2.
  • the antenna 2 is thus maintained in a fixed position in the ring 12 by the longitudinal walls 22 and transverse 24, and the retaining rim 28.
  • the longitudinal wall 22 and the retaining rim 28 form a vice preventing any movement of the antenna 2 with respect to the ring 12 in a transverse direction.
  • the flexible seal 14 secures the ring 12 to the antenna 2, avoiding any movement of one relative to the other, especially in flight.
  • the antenna 2 is locked in rotation about the axis A-A 'by the locking means.
  • the equipotentialisation of the antenna 2 and the ring 12 is provided by the electrical contact existing between the retaining rim 28 and the corners 9 of the antenna 2.
  • the maintenance at the same potential of the antenna 2 and the Ring 12 makes it possible to eliminate current flows between them and to limit the causes of lightning strikes.
  • the antenna assembly 1 is installed in the front tip 37 of an aircraft 38 movably being mounted on a device 40 for scanning.
  • the front plane of the antenna 2 is orthogonal to the roll axis of the aircraft 38.
  • the longitudinal direction of the radiating elements 8 is for example turned by 45 ° by relative to a vertical axis.
  • the device 40 is able to rotate the antenna assembly 1 about two orthogonal axes passing through the center of the antenna 2, and parallel respectively to the yaw axis and to the pitch axis of the aircraft. 38.
  • the antenna assembly 1 is thus mobile in both elevation and azimuth.
  • the antenna assembly 1 can scan an angle of 120 ° in azimuth and 70 ° in elevation around its nominal position.
  • the ring 12 is for example made by assembling two half-rings of longitudinal section of generally semicircular shape around the antenna 2, in a radial plane of the antenna 2.
  • the ring 12 is made from two substantially identical half-rings 44 or 44 ', each half-ring being adapted to surround the antenna 2 on the half of the periphery thereof, c that is to say on an angular sector equal to 180 °.
  • the ring 12 is thus mounted by mechanically assembling the half-rings around the antenna 2 by assembling their respective ends.
  • the ring 12 is devoid of notches 31.
  • each half-ring 44 comprises two connecting ends 48a and 48b, each end 48a, 48b of a half-ring 44 being adapted to be fixed by screwing to a corresponding end 48b, 48a of the other half-ring 44.
  • Each connecting end 48a, 48b of the two half-rings 44 has a solid cross section, widened towards the inside and towards the rear of the ring 2, and is closed by a planar radial end surface 51.
  • Each end surface 51 then forms a radial shoulder 52, which is pierced with a threaded hole 53.
  • Each end 48a, 48b of a half-ring 44 is screwed to the corresponding end 48b, 48a of the other half-ring 44 by means of a nut through the threaded holes 53.
  • each half-ring 44 'thus comprises two connecting ends 62a, 62b, each end 62a, 62b of a half-ring 44' being adapted to be fastened by clipping to the corresponding end 62b, 62a of the other half.
  • connection ends 62a, 62b fixed to each other of the half-rings 44 ' are represented.
  • These two connector ends are attached to each other by means of a snap-fit assembly, including a locking lug and a corresponding locking aperture.
  • the connecting end 62b thus comprises a locking tab 66 protruding from the end edge of the transverse support wall 24 in a direction substantially parallel to this wall.
  • the tab 66 is elastically deformable. It comprises on its outer surface a stop protrusion 68 forming a radial shoulder 68a oriented towards the transverse support wall 24.
  • the connector end 62a is adapted to be clipped together at the connector end 62b. Its inner surface forms a locking opening 70 adapted to receive the tab 66.
  • the locking opening comprises a radial shoulder 70a adapted to receive bearing the shoulder 68a of the tab 66.
  • connection ends 62a and 62b is made by elastically deforming the tab 66 to introduce it in a longitudinal assembly direction into the locking aperture 70, until the shoulder 68a of the tab 66 or in surface support against the shoulder 70a of the opening 70, preventing any movement of the tab away from the opening 70.
  • the assembly of the ring 12 according to this variant thus requires no tools.
  • the ring 12 also comprises two flexible seals 71, each seal 71 being interposed between two connection ends 62a and 62b, providing the connection between the half-rings 44 and 44 '.
  • the connecting end 62b is also provided with a through opening 72 accessible from its outer surface and opening into the assembly opening 70. This through opening 72 allows the introduction of an unlocking tool, to repel elastically the tab 66 and disassemble the connection ends 62a and 62b.
  • the device 100 comprises an antenna 2, identical to that described with reference to the Figures 1 to 9 , and a protection device 104 comprising a protection ring 112.
  • the ring 112 differs from the ring 12 by its radial section and by its method of assembly.
  • the ring 112 is in fact made by assembling according to an assembly plane defined by the contour of the antenna 2 of two annular elements 114, 115 of substantially circular longitudinal section.
  • a first annular element 114 surrounds the antenna 2 at the level of its lateral contour 2c.
  • the median annular element 114 is generally of revolution about the axis AA '. It has a radial section in the general shape of a quarter disc.
  • the median annular element 114 comprises a rear longitudinal surface 114b, plane and annular. It also comprises a transverse surface 114c annular, orthogonal to the rear surface 114b and disposed at the right side contour 2c of the antenna 2, and a front surface 114a of radial section in the form of a circular arc.
  • the median annular element 114 further comprises a rim 128 for holding the antenna 2, generally of revolution about the axis AA ', which protrudes from the front edge of the transverse surface 114c towards the center of the Antenna 2.
  • the flange 128 comprises a retaining surface 128a directed towards the rear of the antenna 2, able to bear surface against the front surface 2a of the antenna 2, in particular against the corners 9.
  • the distance d between the retaining surface 128a and the rear surface 114b is substantially equal to the thickness e of the antenna.
  • the second annular element 115 is disposed at the rear of the rear plane of the antenna.
  • the rear annular element 115 is generally of revolution about the axis AA '.
  • the rear annular element 115 comprises a longitudinal front wall 115a of annular shape, and a rear wall 115b of semicircular cross-section whose radial section of the front wall 115a forms a diameter.
  • the rear annular element 115 thus forms a hollow tube 116, having a radial section in the general shape of a semicircle.
  • the median annulus 114 and rear 115 have substantially the same outer diameter.
  • the inner radius R 114 of the median annular element 114, defined as the distance between the axis AA 'and the transverse surface 114c is slightly greater than the radius R 2 of the antenna 2.
  • the radius of the tube 116 is for example between 1.2 and 3 times the thickness e of the antenna.
  • the front wall 115a of the rear annular element 115 is able to bear surface against the rear surface 114b of the median annular element 114, and against a substantially annular outer portion of the rear surface 2b of the antenna 2 .
  • the ring 112 is assembled by positioning the median annular element 114 around the antenna 2, its transverse surface 114c disposed in line with the lateral contour 2c of the antenna 2, and its holding surface 128a being in surface abutment against the front surface 2a of the antenna 2, and positioning the rear annular element 115 behind the antenna 2, its front surface 115a being at the right of the rear surface 114b of the median annular element 114, and against an outer portion substantially annular of the rear surface 2b of the antenna 2.
  • An annular seal 129 is interposed between the front surfaces 115a and the rear surface 114b. This seal 129 is intended to ensure contact between the annular elements 114, 115. It is made of an electrically conductive elastomeric material.
  • the annular elements 114 and 115 are for example fixed to each other by screwing or clipping.
  • the ring 112 is thus arranged around the antenna 2, coming into contact with each of the projecting ridges 10.
  • the corners 9 are in surface abutment against the surface 128a of the support rim 128, and covered by this rim 128.
  • the retaining surface 128a, the transverse surface 114c of the medial annular element 114 and a portion of the front surface 115a of the rear annular element 115 form an inner surface 112i of the ring 12, in electrical contact with the lateral contour 2c.
  • the transverse surface 114c and a portion of the front surface 115a delimit an angle of reception 130 of the antenna 2.
  • the antenna 2 is held there in a fixed position by being clamped between the front wall 115a and the rim 128 of maintenance.
  • the front surface 114a and the outer surface of the rear wall 115b form an outer surface 112e of the ring 112. This outer surface is wide and rounded. It is therefore devoid of reinforcement zones likely to cause peak effects.
  • a flexible seal similar to the flexible seal 14 is interposed between the ring 112 and the antenna 12.
  • the outer surface of the ring 112 is metallic. The equipotentialisation of the antenna 2 and the ring 112 is thus ensured by the electrical contact between the retaining rim 128 and the corners 9 of the antenna 2.
  • the ring 112 is made from a light and rigid material.
  • the outer surface of each annular element 114, 115 is metallic.
  • each half-ring 114, 115 of the ring 112 is produced as previously described for the half-rings of the ring 12.
  • the antenna assembly according to the invention makes it possible to avoid the risks of attachment of the lightning thus to improve the lightning resistance of an aircraft integrating this device with respect to the antenna 2 alone.
  • This improvement in lightning resistance is furthermore achieved without having to modify the arrangement of the front tip of the aircraft, that is to say without having to modify the position of the antenna in this forward tip. to enlarge the radome.
  • the antenna assembly according to the invention does not include any point or projecting edge, which would form a strengthening zone of the electric field.
  • the outer surface of the ring and wide and rounded which reduces the static field periphery of the antenna.
  • the ring comprises a medial portion, surrounding the antenna 2 at its lateral contour 2c, and a rear portion disposed at the rear of the antenna 2. Only the retaining flanges extend forward of the front plane of the antenna 2.
  • Such a structure of the ring makes it possible to develop an external surface of the large ring while minimizing the disturbances of the radiation pattern of the antenna. 'antenna. Indeed, this external surface develops mainly behind the antenna 2.
  • the realization of the ring of light material makes it possible to minimize the increase in the inertia of the antenna due to the ring. This lightness is particularly accentuated by the hollow tube form of the ring. In addition, the rigidity of this material makes it possible to limit the deformations of the ring.
  • the ring 12 or 112 is entirely metallic.
  • the ring is integrated into the antenna during its manufacture, which avoids the assembly of the ring around the antenna.
  • the ring can be made in one piece with the antenna.

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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 (15)

  1. Antenneneinrichtung (1), aufweisend eine Antenne (2), die aufweist: eine vordere Strahlungsfläche (2a), eine rückwärtige Fläche (2b) und einen seitlichen Umriss (2c), der mindestens einen elektrisches-Feld-Verstärkungsbereich (9, 10) aufweist,
    wobei die Antenneneinrichtung (1) dadurch gekennzeichnet ist, dass sie ferner eine Vorrichtung zum Schützen (4) der Antenne (2) vor Blitzeinschlag aufweist, aufweisend eine Innenfläche (12i, 112i), die zumindest teilweise den seitlichen Umriss (2c) der Antenne (2) abdeckt, wobei sie mit dem seitlichen Umriss (2c) in elektrischem Kontakt ist, wobei die Innenfläche (12i, 112i) den oder jeden elektrisches-Feld-Verstärkungsbereich (9, 10) bedeckt, wobei die Schutzvorrichtung (4) eine gekrümmte Außenfläche (12e, 112e) entgegengesetzt zu der Innenfläche (12i, 112i) aufweist.
  2. Antenneneinrichtung (1) gemäß Anspruch 1, dadurch gekennzeichnet, dass die Antenne (2) eine scheibenförmige Planarantenne ist, wobei die Schutzvorrichtung (4) vorteilhafterweise ringförmig ist.
  3. Antenneneinrichtung (1) gemäß irgendeinem der Ansprüche 1 bis 2, dadurch gekennzeichnet, dass der elektrisches-Feld-Verstärkungsbereich (9, 10) ein winkelförmiger Abschnitt des seitlichen Umrisses (2c) ist.
  4. Antenneneinrichtung (1) gemäß irgendeinem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass die Schutzvorrichtung (4) einen medianen Umfangsabschnitt, der gegenüber dem seitlichen Umriss (2c) angeordnet ist, und einen rückwärtigen Abschnitt aufweist, der hinten an der rückwärtigen Fläche (2b) angeordnet ist, wobei der mediane und der rückwärtige Abschnitt eine Aufnahme (30, 130) zum Unterbringen der Antenne (2) ausbilden.
  5. Antenneneinrichtung (1) gemäß Anspruch 4, dadurch gekennzeichnet, dass die Schutzvorrichtung (4) ferner einen Halterand (28, 128) aufweist, der vor der vorderen Fläche (2a) der Antenne (2) angeordnet ist, wobei der rückwärtige Abschnitt und der Halterand (28, 128) die Antenne (2) in der Schutzvorrichtung (4) einklemmen.
  6. Antenneneinrichtung (1) gemäß Anspruch 5, dadurch gekennzeichnet, dass der rückwärtige Abschnitt eine Längsfläche zum Abstützen (22a, 115a) an der rückwärtigen Fläche (2b) der Antenne (2) aufweist, wobei der mediane Abschnitt eine transversale Fläche zum Abstützen (24a, 114c) an dem seitlichen Umriss (2c) aufweist, und wobei der Halterand (28, 128) eine Haltefläche (28a, 128a) aufweist, die flächig an der vorderen Fläche (2a) der Antenne (2) abgestützt ist, wobei die Innenfläche durch die Längsstützfläche (22a, 115a), die transversale Stützfläche (24a, 114c) und die Haltefläche (28a, 128a) ausgebildet ist.
  7. Antenneneinrichtung (1) gemäß irgendeinem der Ansprüche 5 oder 6, dadurch gekennzeichnet, dass der Halterand (28, 128) mit mindestens einem Teil der Feldverstärkungsbereiche (9, 10) der Antenne (2) in elektrischem Kontakt ist.
  8. Antenneneinrichtung (1) gemäß irgendeinem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Schutzvorrichtung (4) einen steifen Körper (12, 112) und eine verformbare Befestigungsdichtung (14) aufweist, die teilweise zwischen dem Körper (12, 112) und der Antenne (2) angeordnet ist.
  9. Antenneneinrichtung (1) gemäß irgendeinem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Schutzvorrichtung (4) aufweist: einen steifen Körper (12), der aus einem Stück ausgebildet ist, der eine Innenfläche (12i, 112i) aufweist, die zumindest teilweise den seitlichen Umriss (2c) der Antenne (2) abdeckt, wobei sie mit dem seitlichen Umriss (2c) in elektrischem Kontakt ist, wobei die Innenfläche (12i, 112i) den oder jeden elektrisches-Feld-Verstärkungsbereich (9, 10) bedeckt, wobei der steife Körper (12) eine gekrümmte Außenfläche (12e, 112e) entgegengesetzt zu der Innenfläche (12i, 112i) aufweist, und dass der steife Körper (12) Mittel zum Eingreifen der Antenne (2) in den steifen Körper (12) aufweist.
  10. Antenneneinrichtung (1) gemäß Anspruch 9, dadurch gekennzeichnet, dass der steife Körper (12) Mittel zum Verriegeln der Position der Antenne (2) bezüglich der Schutzvorrichtung (4) aufweist.
  11. Antenneneinrichtung (1) gemäß irgendeinem der Ansprüche 1 bis 8, dadurch gekennzeichnet, dass die Schutzvorrichtung (4) mehrere Elemente (44, 44') aufweist, die entlang einer radialen Ebene der Antenne (2) montiert sind.
  12. Antenneneinrichtung (1) gemäß irgendeinem der Ansprüche 1 bis 8, dadurch gekennzeichnet, dass die Schutzvorrichtung (4) mindestens zwei Elemente (114, 115) aufweist, die auf beiden Seiten des seitlichen Umrisses (2c) der Antenne montiert sind.
  13. Antenneneinrichtung (1) gemäß irgendeinem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die innere (12i, 112i) und die äußere (12e, 112e) ringförmige Fläche elektrisch leitend, vorteilhafterweise metallisiert sind.
  14. Antenneneinrichtung (1) gemäß irgendeinem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Schutzvorrichtung (4) aus einem elektrisch isolierenden Material hergestellt ist, das zumindest teilweise durch eine Metallablagerung bedeckt ist.
  15. Antenneneinrichtung (1) gemäß irgendeinem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Antenne (2) eine Mehrzahl von Schlitzen aufweist.
EP20130174798 2012-07-05 2013-07-02 Antennensystem Not-in-force EP2683028B1 (de)

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FR1201909A FR2993103B1 (fr) 2012-07-05 2012-07-05 Ensemble d'antenne

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Publication number Priority date Publication date Assignee Title
US10165698B2 (en) 2015-11-12 2018-12-25 Kimtron, Inc. Anode terminal for reducing field enhancement
US10158169B1 (en) 2017-08-01 2018-12-18 Winegard Company Mobile antenna system

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Publication number Priority date Publication date Assignee Title
FR2675767B1 (fr) * 1991-04-23 1993-07-23 Birault Jean Radome parafoudre pour avion.
GB2295594B (en) * 1994-12-01 1999-03-10 Chelton Electrostatics Ltd A lightning diverter
GB9828768D0 (en) * 1998-12-29 1999-02-17 Symmetricom Inc An antenna
US6362787B1 (en) * 1999-04-26 2002-03-26 Andrew Corporation Lightning protection for an active antenna using patch/microstrip elements
US6198445B1 (en) * 1999-12-29 2001-03-06 Northrop Grumman Corporation Conformal load bearing antenna structure
JP3634244B2 (ja) * 2000-06-30 2005-03-30 三菱電機株式会社 誘雷装置及びその誘雷導体部の配置方法
US8514136B2 (en) * 2009-10-26 2013-08-20 The Boeing Company Conformal high frequency antenna

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US9350066B2 (en) 2016-05-24
FR2993103B1 (fr) 2014-08-15
EP2683028A1 (de) 2014-01-08
US20140009353A1 (en) 2014-01-09

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