EP0762531A2 - A wire antenna for a machine - Google Patents

A wire antenna for a machine Download PDF

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Publication number
EP0762531A2
EP0762531A2 EP96401759A EP96401759A EP0762531A2 EP 0762531 A2 EP0762531 A2 EP 0762531A2 EP 96401759 A EP96401759 A EP 96401759A EP 96401759 A EP96401759 A EP 96401759A EP 0762531 A2 EP0762531 A2 EP 0762531A2
Authority
EP
European Patent Office
Prior art keywords
strand
antenna
hull
antenna according
machine
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
EP96401759A
Other languages
German (de)
French (fr)
Other versions
EP0762531A3 (en
EP0762531B1 (en
Inventor
Alain Biolley
Patrick Daugy
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.)
Sagem SA
Original Assignee
Sagem SA
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Filing date
Publication date
Application filed by Sagem SA filed Critical Sagem SA
Publication of EP0762531A2 publication Critical patent/EP0762531A2/en
Publication of EP0762531A3 publication Critical patent/EP0762531A3/en
Application granted granted Critical
Publication of EP0762531B1 publication Critical patent/EP0762531B1/en
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
    • H01Q1/285—Aircraft wire antennas
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/08—Means for collapsing antennas or parts thereof

Definitions

  • the present invention relates to a wire antenna intended in particular to be carried on a vehicle such as an aircraft.
  • the aircraft may be an aircraft or a reconnaissance drone in which the antenna is used for jamming radio waves.
  • Such an antenna is generally of the dipole type having a large span of a few meters.
  • the two antenna strands are respectively fixed laterally in front of the fuselage of the aircraft, in front of the wings of the aircraft, and symmetrically with respect to the longitudinal axis of the craft.
  • the strands are in a first position at which they are arranged along the fuselage of the craft. In cruising mode of the machine, the strands are deployed suddenly to a second position at which they extend perpendicular to the axial horizontal plane of the aircraft. One of the strands extends laterally to the fuselage upwards, and the other strand extends laterally to the fuselage downwards.
  • This antenna considerably increases the drag of the aircraft up to approximately 50%, and requires a significantly higher engine power of the aircraft than that necessary for propelling the aircraft without an antenna.
  • the arrangement of the antenna strands and their drag disturb the effectiveness of the control surfaces of the machine, particularly that of the rudder also known as yaw control.
  • the present invention aims to remedy the aforementioned drawbacks, and more specifically to provide an antenna whose drag increases only by a few percent, that is to say negligibly, the drag of the mobile machine.
  • the wire antenna comprises a strand and is characterized in that it comprises a hull mounted for free rotation around the antenna strand. Thanks to this free rotation assembly, the hull is always positioned at zero incidence. The presence of this free rotating hull brings a considerable gain on the drag of a vehicle carrying the faired antenna, compared to the drag of this vehicle with a non-ttled antenna. The gain can reach around 50 to 80%.
  • the hull includes rigid transverse plates and spacers between the plates.
  • the antenna strand slidly crosses the plates and freely the spacers in order to reduce the friction of the hull on the strand.
  • the inserts and spacers are extremely light to reduce the inertia of the hull.
  • the spacers may consist of two symmetrical molded half-spacers having faces glued against each other in a longitudinal plane to the strand.
  • the hull is translatable with clearance along the antenna strand between a stop fixed to one free end of the antenna strand and another stop to which is fixed the antenna strand which forms the root of the hull relative to the fuselage of a mobile craft.
  • the aerodynamics of the hull is chosen in such a way that it has an airplane wing profile transversely to the strand.
  • the profile preferably has a cord substantially between a quarter and a fifth of the thickness of the profile.
  • the axis of the antenna strand may be located between a leading edge of the hull and an aerodynamic focus of the hull.
  • the invention is particularly directed towards an antenna on board a mobile vehicle such as an aircraft.
  • the strand has one end fixed in the machine and extends in a plane substantially longitudinal to the machine.
  • the antenna may comprise two strands symmetrical with respect to a longitudinal axis of the vehicle and developed perpendicular to the plane of lift formed by the wings of the vehicle.
  • each strand extends substantially in a longitudinal plane of the rudder of the vehicle.
  • each strand forms an arrow, preferably between 15 ° and 45 ° approximately, with a plane perpendicular to the longitudinal axis of the machine.
  • the aerodynamic focus of the hull is preferably located near the center of gravity of the craft.
  • the means set out below relating to one strand are identical to means relating to the other strand and arranged symmetrically with respect to the longitudinal axis of the machine.
  • a means linked to the craft deploys the antenna strand only after takeoff from a first position in which the antenna strand is substantially folded back against the machine, towards a second position at which the strand antenna forms an acute angle with a longitudinal axis of the machine.
  • the strand comprises a free and bendable portion between a point of attachment of the strand linked to the machine and a strand holder to which the antenna strand is fixed and forming the root of the hull.
  • the free portion of the strand is bent at said first position and substantially linear at said second position.
  • the strand holder rotates around a center located in an obtuse sector in front of the strand and delimited by the strand in the second position and the longitudinal axis of the machine.
  • the means for deploying may comprise a guide in the form of an obtuse circular segment, preferably of the order of 120 °, fixed to the body of the machine.
  • the mobile strand holder then substantially forms a circular sector covering substantially half of the guide and is slidably mounted in the guide to rotate from a front position corresponding to the first position of the antenna strand to a rear position corresponding to the second. position of the antenna strand.
  • Motor means may be provided to activate the means for deploying in order to move the antenna strand from the first position to the second position after takeoff of the craft. This motor means can also be provided to move the antenna strand from the second position to the first position before landing the craft.
  • the antenna comprises a strand holder to which the antenna strand is fixed and sliding in a circular slide, and a traction strap having one end fixed to a strand holder and another end linked to a means reel, preferably through a return means located substantially along the slide, for example at the rear end of the slide.
  • the antenna comprises a strand holder to which the antenna strand is fixed and sliding in a circular slide, and a threaded rod having one end cooperating with a toothing along a circular edge of said strand holder and another end driven in rotation by a motor means.
  • the antenna comprises a strand holder to which the antenna strand is fixed and sliding in a circular slide, and a threaded rod having a first end cooperating with a nut linked to said strand holder and another driven end by motor means preferably through an angle transmission means located substantially along the slide.
  • the embodiments described below relate to a wired antenna of the dipole type mounted on a mobile machine, such as an aircraft A of the drone type to board a shuttle plane and to catapult from it.
  • the antenna is composed of two fine cylindrical metallic strands 1S and 1I which project at the level of the nose NE of the aircraft A in front of the wings AI thereof.
  • the strands are always arranged in a longitudinal axial plane of the aircraft, preferably vertical, that is to say in a plane perpendicular to the aircraft wings AI according to the embodiments illustrated, and symmetrically with respect to the longitudinal axis XX of the aircraft.
  • the strands 1S and 1I are in a first position, called the folded position PR, and are arranged along the fuselage FU of the aircraft, as shown in FIGS. 1 and 2.
  • free ends 10S and 10I of the strands are arranged towards the rear of the machine.
  • Ends 11S and 11I of the strands mounted to "flexably pivot" in the structure of the aircraft are disposed towards the front of the aircraft.
  • One strand 1S is disposed above the aircraft and the other strand 1I is disposed below the aircraft.
  • the strands are deployed in a second position, called the deployed position PD, by deployment means 4S and 41 which will be described later.
  • the deployed position PD the strands 1S and 1I are perpendicular to the longitudinal axis XX of the aircraft, or according to the embodiments described below, form an arrow FL of the order of 15 ° to 45 ° with a transverse plane of the aircraft, as shown in FIGS. 3 and 4.
  • each of the strands of the antenna external to the aircraft comprises a very light aerodynamic hull in the shape of an airplane wing so as to reduce the drag of the antenna strands. Knowing that the strands are identical, we will refer in the following to the upper strand 1S for example.
  • the transverse profile of the hull 2S of the strand 1S comprises a substantially ogival leading edge 20, a body 21 tapering in the form of a bevel from the leading edge 20 towards a trailing edge 22 at the back of the hull.
  • the structure of the hull is composed of several plastic plates 23 distributed almost regularly along the antenna strand 1S and having the transverse profile described above and shown in Figure 7.
  • the plates form ribs for reinforcing the wing and have circular holes 231 traversed by sliding by the antenna strand 1S.
  • sections of foam for example of reinforced rigid or semi-rigid polyurethane foam, form light spacers 24 also having the transverse external profile shown in FIG. 7.
  • each foam spacer 24 is obtained by means of a mold for molding one of two identical half-spacers which are glued against one another along a mediator longitudinal plane 21P of the hull 2S.
  • the mold includes a punch and a die.
  • the punch 241 has a planar internal surface 242 which corresponds to the hull mediating plane 21P.
  • a semi-cylindrical protuberance 243 projects on the surface 242 and is complementary to half of the longitudinal cylindrical conduit 244 in a spacer crossed by the strand 1S.
  • the matrix 245 has an internal face 246 which reproduces the transverse external half-profile of the hull.
  • the strand 1S freely crosses the cylindrical conduits 244 formed in front of the spacers foam 24, wider than the plate holes 231.
  • the metal friction on plastic of the strand 35 in the pads 23 can be further reduced by wrapping the strand in a plastic sheath such as Teflon. Under these conditions, the hull 24 can rotate freely around the antenna strand 1S carrying the hull 2S, almost without friction, and thus position itself freely at zero incidence in order to remain in the wind bed as well during the deployment of the strands antenna only during the cruising speed of the aircraft with the antenna strands deployed.
  • the hull 2S is also mounted in free translation over a short distance, that is to say with a large clearance, along the carrying strand 1S.
  • a plug 12 which forms a first stop limiting the sliding of the hull 25 outwards.
  • the translation of the hull 2S is limited by a second stop formed by a movable profiled strand holder 3S constituting a root of the hull independent of the movements of the hull in rotation and translation.
  • the strand holder 3S is mounted for rotation perpendicular to the strand 1S in the structure of the aircraft.
  • an antenna according to the invention for jamming electromagnetic waves in the metric and decimetric ranges is composed of strands 1S and 1I each having a length of between a quarter wave and a half-wave approximately.
  • the thickness E of the streamers 2S and 21 is between a quarter and a fifth of the cord C of the hulls, that is to say the width of the hulls.
  • the length L of the hull 2S, 21 of each strand is approximately 1.5 m
  • the cord C of the hull is 74 mm
  • the thickness E of the hull is 18 mm
  • the diameter of the strand 1S, 1I and the holes 231 in the plates 23 is 17 mm
  • the axis of the plate holes 231 and the spacer holes 244 is located 14 mm from the front of the leading edge 20.
  • the influence of the antenna on the control surfaces of the aircraft is linked to the distance between the aerodynamic focus FA of the hull and the center of gravity G of the aircraft. So that the antenna does not destabilize the aircraft, and in particular does not intervene in a preponderant manner on the effects of the control surfaces of the aircraft, in particular of the rudder GD of the aircraft, the aerodynamic focus FA of hull 2 is provided in front, from the center of gravity G of the aircraft, as shown in FIG. 5.
  • the aerodynamic focus FA is located in the vicinity of the center of gravity G of the aircraft. It is indeed imperative to have hull roots 3S, 31 as rear as possible on the FU fuselage so that the streamlined strands do not disturb the effects of the control surfaces both during the deployment of the antenna and in cruising speed of the aircraft.
  • the deployed strands have an arrow FL can be chosen between 15 ° and 45 °, preferably about 30 ° depending on the illustrated embodiment, to move the foci FA away from the hulls.
  • the axis of rotation constituted by the antenna strand 1S, 1I is located in front of the focus FA of the hull, it is ie between the focal point FA and the leading edge 20 of the hull, as shown in FIG. 7.
  • the distance, called "static margin" between the axis of the strand 1S, 1I and the aerodynamic focal point FA of the hull is around 5% of the cord C of the hull 2S, 21.
  • the deployment means for simultaneously deploying the streamlined strands 1S and 1I are identical and symmetrical with respect to the longitudinal axis XX of the aircraft. Consequently, one of them relating to the upper strand 1S is described in detail with reference to FIGS. 10 to 12.
  • the deployment means 4S of the upper strand 1S comprises a guide 40 for the respective strand holder 3S.
  • the guide 40 has a circular segment shape and extends perpendicular to the fuselage FU, in a vertical axial plane of the aircraft A. It is fixed to the structure of the aircraft by two consoles 4C.
  • the guide 40 has a transverse slot 41 in a circular segment which is substantially 120 ° according to the illustrated embodiment.
  • the rope of the slit segment opens out substantially at the surface of the fuselage and can be protected at the front by an aerodynamic cover fixed to the FU fuselage.
  • the circular edge 42 of the guide through which the slot 41 opens into the interior of the aircraft is surrounded by two circular rails 43 with an L-profile concentric with the segment and fixed to the structure of the aircraft.
  • the strand holder 3S forming the root of the hull has a circular edge on which is fixed a rigid U-shaped section 31 which is slidably mounted between the edge 42 of the guide 40 and the rails 43, which form a circular slide 42-43 for guide the 3S strand holder with slot 41.
  • the strand holder 3S has the substantial shape of a circular sector relative to an angle PB substantially equal to half that FE relating to the circular segment defining the slot 41 in the guide 40. Under these conditions, in the folded position PR shown in FIG.
  • the strand holder 3S occupies substantially the half-segment relating to the guide slot 41 and situated towards the front of the 'aircraft, and in the deployed position PD shown in Figure 11, the strand holder 3S occupies substantially the other half-segment relating to the guide slot 41 and located towards the rear of the aircraft.
  • the strand 1S is fixed, for example by gluing, in a short internal conduit formed in the top 32 of the strand holder substantially in extension of the leading edge 20 of the 2S hull. Then a portion 13 of the strand 1S freely crosses a front slot 33 of the strand holder 3S, particularly in the folded position PR (FIG. 10), and the slot 41 of the guide 40 up to a connector 14 fixed to the structure of the aircraft .
  • the connector connects the strand 1S to a coaxial power cable 15S coming out of a power amplifier 16S from a jamming source installed in the NE nose of the aircraft.
  • the amplifier 16S is separated by a central cooling plate 17 from another amplifier 16I supplying by coaxial cable 15I the other antenna strand 1I.
  • the point of attachment of the strand 1S materialized by the connector 14 is substantially on the axis of the strand and the strand is substantially rectilinear.
  • the portion 13 of the strand 1S is bent with a curvature whose radius is large enough to avoid any bending or breakage of the strand, particularly at the outlet of the conduit at the top 32 of the strand holder.
  • the fictitious center of rotation CR corresponding to the circular slide composed by the edge of the strand holder 42 and by the rails 43 and to the circular edge 31 of the strand holder sliding in the slide is located in an obtuse angular sector. forward formed between the fuselage body FU of the aircraft, and therefore the longitudinal axis XX, and the strand 1S in the deployed position PD. As shown in FIG. 12, the portion of the strand 1S fixed in the apex 32 of the strand holder 3S does not pass by the center of rotation CR in order to avoid any cracking of the strand.
  • the arrangement of the elements making up the deployment means is symmetrical with respect to the longitudinal axis XX of the aircraft, as are the antenna strands 1S and 1I and the strand carrier guides 3S and 31, and a central motor means for deploying the antenna strands is common to the two deployment means 4S and 41.
  • the activation of the drive means is simultaneous with the unlocking of latching devices ES and EI keeping the free ends 10S and 10I of the hulls against the fuselage FU of the aircraft, as shown in FIG. 2.
  • each deployment means 4Sa, 4Ia comprises a traction strap 5Sa, 5Ia.
  • the front end of the strap is fixed to the rear end of the circular edge 31 of the respective movable strand holder 3S by means of a captive nut 51Sa, 51Ia.
  • the rear end of the strap is connected to a motor means constituted by a compression spring strap reel 6a.
  • the strap is applied against the small co-circular wings of the slide rails 43 from the captive nut 51Sa, 51Ia to a deflection pulley 52Sa, 52Ia mounted idly at the rear end of the respective guide 40.
  • the compression spring In the folded position PR, the compression spring is compressed, i.e. the reel is armed before takeoff or catapult of the aircraft, and the traction straps 5Sa and 5Ia are unwound.
  • a mechanical or electromechanical timer means or such a remote-controlled timer means controls, after takeoff or catapulting of the aircraft, the release of the compressed spring in the reel 6a so as to wind the straps 5Sa and 5Ia which then tow the strand carriers 3S and 31 backwards.
  • the strand carriers slide in the respective guides 40 in opposite directions until they reach the deployed position PD.
  • a deployment means 4Sb, 4Ib comprises a wheel and worm system.
  • the worm is a rigid nylon 5Sb, 5Ib threaded rod extending longitudinally in the aircraft.
  • a front end of the rod meshes with a corresponding toothing provided on the circular edge 31 of the respective strand holder 3S, 31.
  • One end rear of the rod meshes with a bevel gear 52Sb, 52Ib linked to a respective end of the shaft of an electric motor 6b.
  • At least one deployment limit switch 7Db is arranged at the rear end of one of the guide rails 42-43 to be actuated by a stop at the rear end of the strand holder respective 3S in order to cut the power to the motor 6b.
  • Deployment means 4Ss, 4Ic according to the third embodiment shown in FIG. 15 also comprises a wheel and worm system.
  • the worm is a flexible threaded rod 5Sc, 5Ic which is developed substantially parallel to the rear circular half-edge of the respective slide 42-43.
  • the front end of the rod 5Sc, 5Ic meshes with a nut 51Sc, 51Ic fixed to the rear end of the circular edge 31 of the respective strand holder 3S, 31.
  • a bevel gear 52Sc, 52Ic connects the end rear of the respective slide at a respective end of an electric motor 6c.
  • a deployment limit switch 7Dc is also provided at the rear end of one of the guide rails 42-43.
  • the electric motor 6b, 6c can control the rotation of the threaded rods in opposite directions so that the strand holders pass from the deployed antenna position PD to the folded antenna position PR, before the landing of the aircraft, and the free ends 10S and 10I of the hulls fit into the snap-on devices ES and EI.
  • at least one folding limit switch 7Rb, 7Rc is provided at the front end of one of the slides 41-42 guide to be actuated by the stop of the front end of the respective strand holder to cut the power to the motor 6b, 6c.
  • the strands with their deployment means are positioned in a horizontal plane, that is to say are parallel to the wings and elevators of the aircraft.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Remote Sensing (AREA)
  • Physics & Mathematics (AREA)
  • Astronomy & Astrophysics (AREA)
  • General Physics & Mathematics (AREA)
  • Details Of Aerials (AREA)
  • Variable-Direction Aerials And Aerial Arrays (AREA)
  • Aerials With Secondary Devices (AREA)

Abstract

The wire antenna (13) is mounted inside the upper part of a wing like section (2S) with good aerodynamic properties. The section is mounted in a slot (41) with a holder (42). The holder is fitted to the aircraft engine. The section holding the antenna can protrude from the slot at an angle of 60 degrees or it can be retracted by section rotation, with the wire antenna bent and forming a conformal surface with the slot.

Description

La présente invention concerne une antenne filaire destinée notamment à être embarquée dans un engin tel qu'aéronef. En particulier, l'aéronef peut être un avion ou un drone de reconnaissance dans lequel l'antenne sert au brouillage d'ondes radioélectriques.The present invention relates to a wire antenna intended in particular to be carried on a vehicle such as an aircraft. In particular, the aircraft may be an aircraft or a reconnaissance drone in which the antenna is used for jamming radio waves.

Une telle antenne est généralement du type dipôle ayant une grande envergure de quelques mètres. Les deux brins de l'antenne sont respectivement fixés latéralement à l'avant du fuselage de l'aéronef, devant les ailes de l'aéronef, et symétriquement par rapport à l'axe longitudinal de l'engin.Such an antenna is generally of the dipole type having a large span of a few meters. The two antenna strands are respectively fixed laterally in front of the fuselage of the aircraft, in front of the wings of the aircraft, and symmetrically with respect to the longitudinal axis of the craft.

Lors du décollage ou du catapultage de l'engin, les brins sont à une première position à laquelle il sont disposés le long du fuselage de l'engin. En régime de croisière de l'engin, les brins sont déployés brusquement à une seconde position à laquelle ils s'étendent perpendiculairement au plan horizontal axial de l'aéronef. L'un des brins s'étend latéralement au fuselage vers le haut, et l'autre brin s'étend latéralement au fuselage vers le bas.During takeoff or catapulting of the craft, the strands are in a first position at which they are arranged along the fuselage of the craft. In cruising mode of the machine, the strands are deployed suddenly to a second position at which they extend perpendicular to the axial horizontal plane of the aircraft. One of the strands extends laterally to the fuselage upwards, and the other strand extends laterally to the fuselage downwards.

Cette antenne augmente considérablement la traînée de l'aéronef jusqu'à 50 % environ, et nécessite une puissance motrice de l'aéronef nettement plus élevée que celle nécessaire à la propulsion de l'aéronef sans antenne. Corollairement, la disposition des brins d'antenne et leur traînée perturbent l'efficacité des gouvernes de l'engin, particulièrement celle de la gouverne de direction dite également gouverne de lacet.This antenna considerably increases the drag of the aircraft up to approximately 50%, and requires a significantly higher engine power of the aircraft than that necessary for propelling the aircraft without an antenna. As a corollary, the arrangement of the antenna strands and their drag disturb the effectiveness of the control surfaces of the machine, particularly that of the rudder also known as yaw control.

La présente invention vise à remédier aux inconvénients précités, et plus précisément à fournir une antenne dont la traînée n'augmente que de quelques pour-cent, c'est-à-dire de manière négligeable, la traînée de l'engin mobile.The present invention aims to remedy the aforementioned drawbacks, and more specifically to provide an antenna whose drag increases only by a few percent, that is to say negligibly, the drag of the mobile machine.

A cette fin, l'antenne filaire comprend un brin et est caractérisé en ce qu'elle comprend une carène montée à rotation libre autour du brin d'antenne. Grâce à ce montage à rotation libre, la carène est toujours positionnée à incidence nulle. La présence de cette carène libre en rotation apporte un gain considérable sur la traînée d'un engin portant l'antenne carénée, comparativement à la traînée de cet engin avec une antenne non carénée. Le gain peut atteindre 50 à 80 % environ.To this end, the wire antenna comprises a strand and is characterized in that it comprises a hull mounted for free rotation around the antenna strand. Thanks to this free rotation assembly, the hull is always positioned at zero incidence. The presence of this free rotating hull brings a considerable gain on the drag of a vehicle carrying the faired antenna, compared to the drag of this vehicle with a non-faired antenna. The gain can reach around 50 to 80%.

La carène comprend des plaquettes rigides transversales et des entretoises entre les plaquettes. Le brin d'antenne traverse à glissement les plaquettes et librement les entretoises afin de diminuer le frottement de la carène sur le brin. Les plaquettes et les entretoises sont extrêmement légères pour diminuer l'inertie de la carène.The hull includes rigid transverse plates and spacers between the plates. The antenna strand slidly crosses the plates and freely the spacers in order to reduce the friction of the hull on the strand. The inserts and spacers are extremely light to reduce the inertia of the hull.

Les entretoises peuvent être constituées de deux demi-entretoises moulées symétriques ayant des faces collées l'une contre l'autre dans un plan longitudinal au brin.The spacers may consist of two symmetrical molded half-spacers having faces glued against each other in a longitudinal plane to the strand.

De préférence, la carène est translatable avec jeu le long du brin d'antenne entre une butée fixée à une extrémité libre du brin d'antenne et une autre butée à laquelle est fixé le brin d'antenne qui forme l'emplanture de la carène relativement au fuselage d'un engin mobile.Preferably, the hull is translatable with clearance along the antenna strand between a stop fixed to one free end of the antenna strand and another stop to which is fixed the antenna strand which forms the root of the hull relative to the fuselage of a mobile craft.

L'aérodynamisme de la carène est choisi de telle manière qu'elle présente un profil d'aile d'avion transversalement au brin. Le profil a de préférence une corde sensiblement comprise entre un quart et un cinquième de l'épaisseur du profil. L'axe du brin d'antenne peut être situé entre un bord d'attaque de la carène et un foyer aérodynamique de la carène.The aerodynamics of the hull is chosen in such a way that it has an airplane wing profile transversely to the strand. The profile preferably has a cord substantially between a quarter and a fifth of the thickness of the profile. The axis of the antenna strand may be located between a leading edge of the hull and an aerodynamic focus of the hull.

Comme déjà dit, l'invention est particulièrement dirigée vers une antenne embarquée dans un engin mobile tel qu'aéronef. Dans ce cas, le brin a une extrémité fixée dans l'engin et s'étend dans un plan sensiblement longitudinal à l'engin. En particulier, l'antenne peut comprendre deux brins symétriques par rapport à un axe longitudinal de l'engin et développés perpendiculairement au plan de sustentation formée par les ailes de l'engin. En d'autres termes, chaque brin s'étend sensiblement dans un plan longitudinal de gouverne de direction de l'engin.As already said, the invention is particularly directed towards an antenna on board a mobile vehicle such as an aircraft. In this case, the strand has one end fixed in the machine and extends in a plane substantially longitudinal to the machine. In particular, the antenna may comprise two strands symmetrical with respect to a longitudinal axis of the vehicle and developed perpendicular to the plane of lift formed by the wings of the vehicle. In other words, each strand extends substantially in a longitudinal plane of the rudder of the vehicle.

Afin de diminuer l'effet de l'antenne sur les gouvernes de l'engin, particulièrement lorsque l'emplanture des brins est située à l'avant de l'aéronef, chaque brin forme une flèche, de préférence comprise entre 15° et 45° environ, avec un plan perpendiculaire à l'axe longitudinal de l'engin. Le foyer aérodynamique de la carène est de préférence situé à proximité du centre de gravité de l'engin.In order to reduce the effect of the antenna on the control surfaces of the craft, particularly when the root of the strands is located at the front of the aircraft, each strand forms an arrow, preferably between 15 ° and 45 ° approximately, with a plane perpendicular to the longitudinal axis of the machine. The aerodynamic focus of the hull is preferably located near the center of gravity of the craft.

Les moyens énoncés ci-dessous relatifs à un brin sont identiques à des moyens relatifs à l'autre brin et disposés symétriquement par rapport à l'axe longitudinal de l'engin.The means set out below relating to one strand are identical to means relating to the other strand and arranged symmetrically with respect to the longitudinal axis of the machine.

De manière à ne pas augmenter la poussée lors du décollage ou du catapultage de l'engin, un moyen lié à l'engin déploie le brin d'antenne seulement après le décollage depuis une première position à laquelle le brin d'antenne est replié sensiblement contre l'engin, vers une seconde position à laquelle le brin d'antenne forme un angle aigu avec un axe longitudinal de l'engin.In order not to increase the thrust during takeoff or catapulting of the craft, a means linked to the craft deploys the antenna strand only after takeoff from a first position in which the antenna strand is substantially folded back against the machine, towards a second position at which the strand antenna forms an acute angle with a longitudinal axis of the machine.

Selon une réalisation particulière, le brin comporte une portion libre et fléchissable entre un point de fixation du brin lié à l'engin et un porte-brin auquel le brin d'antenne est fixé et formant emplanture de la carène. La portion libre du brin est fléchie à ladite première position et sensiblement linéaire à ladite seconde position. De manière à éviter toute cassure du brin, le porte-brin tourne autour d'un centre situé dans un secteur obtus devant le brin et délimité par le brin à la seconde position et l'axe longitudinal de l'engin.According to a particular embodiment, the strand comprises a free and bendable portion between a point of attachment of the strand linked to the machine and a strand holder to which the antenna strand is fixed and forming the root of the hull. The free portion of the strand is bent at said first position and substantially linear at said second position. In order to avoid any breakage of the strand, the strand holder rotates around a center located in an obtuse sector in front of the strand and delimited by the strand in the second position and the longitudinal axis of the machine.

Le moyen pour déployer peut comprendre un guide en forme de segment circulaire obtus, de préférence de l'ordre de 120°, fixé au corps de l'engin. Le porte-brin mobile forme alors sensiblement un secteur circulaire couvrant sensiblement la moitié du guide et est monté à coulissement dans le guide pour tourner d'une position avant correspondant à la première position du brin d'antenne à une position arrière correspondant à la seconde position du brin d'antenne.The means for deploying may comprise a guide in the form of an obtuse circular segment, preferably of the order of 120 °, fixed to the body of the machine. The mobile strand holder then substantially forms a circular sector covering substantially half of the guide and is slidably mounted in the guide to rotate from a front position corresponding to the first position of the antenna strand to a rear position corresponding to the second. position of the antenna strand.

Un moyen moteur peut être prévu pour activer le moyen pour déployer afin de déplacer le brin d'antenne depuis la première position vers la seconde position après décollage de l'engin. Ce moyen moteur peut être également prévu pour déplacer le brin d'antenne depuis la seconde position vers la première position avant atterrissage de l'engin.Motor means may be provided to activate the means for deploying in order to move the antenna strand from the first position to the second position after takeoff of the craft. This motor means can also be provided to move the antenna strand from the second position to the first position before landing the craft.

Selon une première réalisation, l'antenne comprend un porte-brin auquel le brin d'antenne est fixé et coulissant dans une glissière circulaire, et une sangle de traction ayant une extrémité fixée à un porte-brin et une autre extrémité liée à un moyen enrouleur, de préférence à travers un moyen de renvoi situé sensiblement le long de la glissière, par exemple à l'extrémité arrière de la glissière.According to a first embodiment, the antenna comprises a strand holder to which the antenna strand is fixed and sliding in a circular slide, and a traction strap having one end fixed to a strand holder and another end linked to a means reel, preferably through a return means located substantially along the slide, for example at the rear end of the slide.

Selon une seconde réalisation, l'antenne comprend un porte-brin auquel le brin d'antenne est fixé et coulissant dans une glissière circulaire, et une tige filetée ayant une extrémité coopérant avec une denture le long d'un chant circulaire dudit porte-brin et une autre extrémité entraînée en rotation par un moyen moteur.According to a second embodiment, the antenna comprises a strand holder to which the antenna strand is fixed and sliding in a circular slide, and a threaded rod having one end cooperating with a toothing along a circular edge of said strand holder and another end driven in rotation by a motor means.

Selon une troisième réalisation, l'antenne comprend un porte-brin auquel le brin d'antenne est fixé et coulissant dans une glissière circulaire, et une tige filetée ayant une première extrémité coopérant avec un écrou lié audit porte-brin et une autre extrémité entraînée par un moyen moteur de préférence à travers un moyen de renvoi d'angle situé sensiblement le long de la glissière.According to a third embodiment, the antenna comprises a strand holder to which the antenna strand is fixed and sliding in a circular slide, and a threaded rod having a first end cooperating with a nut linked to said strand holder and another driven end by motor means preferably through an angle transmission means located substantially along the slide.

D'autres caractéristiques et avantages de la présente invention apparaîtront plus clairement à la lecture de la description suivante de plusieurs réalisations préférées de l'invention en référence aux dessins annexés correspondants dans lesquels :

  • les figures 1 et 2 sont des vues schématiques de face et de côté vertical d'un aéronef supportant deux brins d'antenne selon l'invention en position repliée ;
  • les figures 3 et 4 sont des vues schématiques de face et de côté vertical d'un aéronef supportant deux brins d'antenne selon l'invention en position déployée ;
  • la figure 5 est une vue schématique de dessus de l'aéronef ;
  • la figure 6 est une vue de dessus d'une carène d'un brin de l'antenne ;
  • la figure 7 est une vue de côté d'une plaquette de renfort de la carène ;
  • la figure 8 est une vue en coupe de la carène le long de l'axe longitudinal du brin ;
  • la figure 9 est une vue schématique transversale explosée d'un moule pour entretoise de la carène ;
  • la figure 10 est une vue en perspective d'un guide du porte-brin d'un brin de l'antenne en position repliée ;
  • la figure 11 est une vue en perspective du guide du porte-brin de la figure 10 en position déployée ;
  • la figure 12 est un diagramme en coupe transversale schématique à travers la fente du guide montrant le passage d'une position rectiligne à une position fléchie d'une portion de brin d'antenne située entre le porte-brin et un connecteur de câble dans la structure de l'aéronef ;
  • la figure 13 est une vue schématique longitudinale verticale, partiellement en coupe en partie supérieure, des moyens de déploiement en position d'antenne repliée selon une première réalisation ;
  • la figure 14 est une vue schématique longitudinale verticale, partiellement en coupe en partie supérieure, des moyens de déploiement en position d'antenne repliée selon une seconde réalisation ; et
  • la figure 14 est une vue schématique longitudinale verticale, partiellement en coupe en partie supérieure, des moyens de déploiement en position d'antenne repliée selon une troisième réalisation.
Other characteristics and advantages of the present invention will appear more clearly on reading the following description of several preferred embodiments of the invention with reference to the corresponding appended drawings in which:
  • Figures 1 and 2 are schematic front and vertical side views of an aircraft supporting two antenna strands according to the invention in the folded position;
  • Figures 3 and 4 are schematic front and vertical side views of an aircraft supporting two antenna strands according to the invention in the deployed position;
  • Figure 5 is a schematic top view of the aircraft;
  • Figure 6 is a top view of a hull of a strand of the antenna;
  • Figure 7 is a side view of a hull reinforcement plate;
  • Figure 8 is a sectional view of the hull along the longitudinal axis of the strand;
  • Figure 9 is an exploded cross-sectional view of a mold for the hull spacer;
  • Figure 10 is a perspective view of a guide of the strand holder of a strand of the antenna in the folded position;
  • Figure 11 is a perspective view of the guide of the strand holder of Figure 10 in the deployed position;
  • FIG. 12 is a diagrammatic cross-sectional diagram through the slot of the guide showing the passage from a straight position to a bent position of a portion of antenna strand located between the strand holder and a cable connector in the aircraft structure;
  • FIG. 13 is a vertical longitudinal schematic view, partially in section in the upper part, of the deployment means in the folded antenna position according to a first embodiment;
  • Figure 14 is a vertical longitudinal schematic view, partially in section at the top, of the deployment means in the folded antenna position according to a second embodiment; and
  • FIG. 14 is a vertical longitudinal schematic view, partially in section at the top, of the deployment means in folded antenna position according to a third embodiment.

Les réalisations décrites ci-après sont relatives à une antenne filaire de type dipôle montée sur un engin mobile, tel qu'un aéronef A du type drone à embarquer sur un avion-navette et à catapulter depuis celui-ci.The embodiments described below relate to a wired antenna of the dipole type mounted on a mobile machine, such as an aircraft A of the drone type to board a shuttle plane and to catapult from it.

Comme montré schématiquement aux figures 1 à 5, l'antenne est composée de deux brins métalliques fins cylindriques 1S et 1I qui saillent au niveau du nez NE de l'aéronef A devant les ailes AI de celui-ci. Les brins sont toujours disposés dans un plan axial longitudinal de l'aéronef, de préférence vertical, c'est-à-dire dans un plan perpendiculaire aux ailes d'aéronef AI selon les réalisations illustrées, et symétriquement par rapport à l'axe longitudinal XX de l'aéronef.As shown diagrammatically in FIGS. 1 to 5, the antenna is composed of two fine cylindrical metallic strands 1S and 1I which project at the level of the nose NE of the aircraft A in front of the wings AI thereof. The strands are always arranged in a longitudinal axial plane of the aircraft, preferably vertical, that is to say in a plane perpendicular to the aircraft wings AI according to the embodiments illustrated, and symmetrically with respect to the longitudinal axis XX of the aircraft.

Au repos, et lors du catapultage de l'aéronef, les brins 1S et 1I sont à une première position, dite position repliée PR, et sont disposés le long du fuselage FU de l'aéronef, comme montré aux figures 1 et 2. Des extrémités libres 10S et 10I des brins sont disposées vers l'arrière de l'engin. Des extrémités 11S et 11I des brins montées à "pivotement de manière flexible" dans la structure de l'aéronef sont disposées vers l'avant de l'aéronef. L'un 1S des brins est disposé dessus l'aéronef et l'autre brin 1I est disposé dessous l'aéronef.At rest, and during the catapulting of the aircraft, the strands 1S and 1I are in a first position, called the folded position PR, and are arranged along the fuselage FU of the aircraft, as shown in FIGS. 1 and 2. free ends 10S and 10I of the strands are arranged towards the rear of the machine. Ends 11S and 11I of the strands mounted to "flexably pivot" in the structure of the aircraft are disposed towards the front of the aircraft. One strand 1S is disposed above the aircraft and the other strand 1I is disposed below the aircraft.

Après catapultage, les brins sont déployés à une seconde position, dite position déployée PD, par des moyens de déploiement 4S et 41 qui seront décrits ultérieurement. A cette position déployée, les brins 1S et 1I sont perpendiculaires à l'axe longitudinal XX de l'aéronef, ou selon les réalisations décrites ci-après, forment une flèche FL de l'ordre de 15° à 45° avec un plan transversal de l'aéronef, comme montré aux figures 3 et 4.After catapulting, the strands are deployed in a second position, called the deployed position PD, by deployment means 4S and 41 which will be described later. In this deployed position, the strands 1S and 1I are perpendicular to the longitudinal axis XX of the aircraft, or according to the embodiments described below, form an arrow FL of the order of 15 ° to 45 ° with a transverse plane of the aircraft, as shown in FIGS. 3 and 4.

En référence aux figures 6 à 8, la portion de chacun des brins de l'antenne externe à l'aéronef comprend une carène aérodynamique très légère en forme d'aile d'avion de manière à diminuer la traînée des brins d'antenne. Sachant que les brins sont identiques, on se réfèrera dans la suite au brin supérieur 1S par exemple.With reference to FIGS. 6 to 8, the portion of each of the strands of the antenna external to the aircraft comprises a very light aerodynamic hull in the shape of an airplane wing so as to reduce the drag of the antenna strands. Knowing that the strands are identical, we will refer in the following to the upper strand 1S for example.

Comme montré particulièrement à la figure 7, le profil transversal de la carène 2S du brin 1S comprend un bord d'attaque sensiblement ogival 20, un corps 21 se rétrécissant en forme de biseau depuis le bord d'attaque 20 vers un bord de fuite 22 à l'arrière de la carène.As shown particularly in FIG. 7, the transverse profile of the hull 2S of the strand 1S comprises a substantially ogival leading edge 20, a body 21 tapering in the form of a bevel from the leading edge 20 towards a trailing edge 22 at the back of the hull.

Selon la réalisation illustrée aux figures 6 à 8, la structure de la carène est composée de plusieurs plaquettes 23 en matière plastique réparties quasi-régulièrement le long du brin d'antenne 1S et ayant le profil transversal décrit ci-dessus et montré à la figure 7. Les plaquettes forment des nervures de renfort d'aile et présentent des trous circulaires 231 traversés à glissement par le brin d'antenne 1S. Entre ces plaquettes, des tronçons en mousse, par exemple en mousse de polyuréthane rigide ou semi-rigide renforcée, forment des entretoises légères 24 ayant également le profil externe transversal montré à la figure 7.According to the embodiment illustrated in Figures 6 to 8, the structure of the hull is composed of several plastic plates 23 distributed almost regularly along the antenna strand 1S and having the transverse profile described above and shown in Figure 7. The plates form ribs for reinforcing the wing and have circular holes 231 traversed by sliding by the antenna strand 1S. Between these plates, sections of foam, for example of reinforced rigid or semi-rigid polyurethane foam, form light spacers 24 also having the transverse external profile shown in FIG. 7.

Comme montré à la figure 9, chaque entretoise en mousse 24 est obtenue au moyen d'un moule pour mouler l'une de deux demi-entretoises identiques qui sont collées l'une contre l'autre suivant un plan longitudinal médiateur 21P de la carène 2S. Le moule comprend un poinçon et une matrice. Le poinçon 241 présente une surface interne plane 242 qui correspond au plan médiateur de carène 21P. Une protubérance semi-cylindrique 243 saille sur la surface 242 et est complémentaire de la moitié du conduit cylindrique longitudinal 244 dans une entretoise traversé par le brin 1S. La matrice 245 a une face interne 246 qui reproduit le demi-profil externe transversal de la carène.As shown in FIG. 9, each foam spacer 24 is obtained by means of a mold for molding one of two identical half-spacers which are glued against one another along a mediator longitudinal plane 21P of the hull 2S. The mold includes a punch and a die. The punch 241 has a planar internal surface 242 which corresponds to the hull mediating plane 21P. A semi-cylindrical protuberance 243 projects on the surface 242 and is complementary to half of the longitudinal cylindrical conduit 244 in a spacer crossed by the strand 1S. The matrix 245 has an internal face 246 which reproduces the transverse external half-profile of the hull.

Afin de limiter au maximum les frottements de la carène 2S sur le brin 1S et par conséquent tout risque de blocage en rotation de la carène qui rendrait ingouvernable l'aéronef, le brin 1S traverse librement les conduits cylindriques 244 ménagés à l'avant des entretoises en mousse 24, plus larges que les trous de plaquette 231. En outre, le frottement métal sur matière plastique du brin 35 dans les plaquettes 23 peut être encore diminué en enveloppant le brin dans une gaine en matière plastique telle que Téflon. Dans ces conditions, la carène 24 peut tourner librement autour du brin d'antenne 1S porteur de la carène 2S, quasiment sans frottement, et ainsi se positionner librement à incidence nulle afin de rester dans le lit du vent aussi bien lors du déploiement des brins d'antenne que pendant le régime de croisière de l'aéronef avec les brins d'antenne déployés.In order to limit as much as possible the friction of the hull 2S on the strand 1S and consequently any risk of blocking in rotation of the hull which would make the aircraft ungovernable, the strand 1S freely crosses the cylindrical conduits 244 formed in front of the spacers foam 24, wider than the plate holes 231. In addition, the metal friction on plastic of the strand 35 in the pads 23 can be further reduced by wrapping the strand in a plastic sheath such as Teflon. Under these conditions, the hull 24 can rotate freely around the antenna strand 1S carrying the hull 2S, almost without friction, and thus position itself freely at zero incidence in order to remain in the wind bed as well during the deployment of the strands antenna only during the cruising speed of the aircraft with the antenna strands deployed.

Comme montré en détail à la figure 8, la carène 2S est également montée à translation libre sur une faible distance, c'est-à-dire avec un grand jeu, le long du brin porteur 1S. A l'extrémité libre 10S du brin 1S est vissé un bouchon 12 qui forme une première butée limitant le glissement de la carène 25 vers l'extérieur. Du côté de l'autre extrémité 11S du brin 1S pénétrant dans le fuselage FU de l'aéronef, la translation de la carène 2S est limitée par une seconde butée formée par un porte-brin profilé mobile 3S constituant une emplanture de la carène indépendante des déplacements de la carène en rotation et translation. Comme on le verra ci-après, le porte-brin 3S est monté à rotation perpendiculaire au brin 1S dans la structure de l'aéronef.As shown in detail in FIG. 8, the hull 2S is also mounted in free translation over a short distance, that is to say with a large clearance, along the carrying strand 1S. At the free end 10S of the strand 1S is screwed a plug 12 which forms a first stop limiting the sliding of the hull 25 outwards. On the side of the other end 11S of the strand 1S entering the fuselage FU of the aircraft, the translation of the hull 2S is limited by a second stop formed by a movable profiled strand holder 3S constituting a root of the hull independent of the movements of the hull in rotation and translation. As will be seen below, the strand holder 3S is mounted for rotation perpendicular to the strand 1S in the structure of the aircraft.

Afin de fixer les idées, une antenne selon l'invention pour brouiller des ondes électromagnétiques dans les gammes métrique et décimétrique est composée de brins 1S et 1I ayant chacun une longueur comprise entre un quart d'onde et une demi-onde environ. Pour obtenir une traînée de l'antenne carénée de l'ordre de 5 % de la traînée de l'aéronef sans antenne et donc une portance faible des brins carénés, l'épaisseur E des carènes 2S et 21 est comprise entre un quart et un cinquième de la corde C des carènes, c'est-à-dire la largeur des carènes. Par exemple, la longueur L de la carène 2S, 21 de chaque brin est de 1,5 m environ, la corde C de la carène est de 74 mm, l'épaisseur E de la carène est de 18 mm, le diamètre du brin 1S, 1I et des trous 231 dans les plaquettes 23 est de 17 mm, et l'axe des trous de plaquette 231 et des trous d'entretoise 244 est situé à 14 mm de l'avant du bord d'attaque 20.In order to fix ideas, an antenna according to the invention for jamming electromagnetic waves in the metric and decimetric ranges is composed of strands 1S and 1I each having a length of between a quarter wave and a half-wave approximately. To obtain a stream of the streamlined antenna of the order of 5% of the trail of the aircraft without the antenna and therefore a low lift of the streamlined strands, the thickness E of the streamers 2S and 21 is between a quarter and a fifth of the cord C of the hulls, that is to say the width of the hulls. For example, the length L of the hull 2S, 21 of each strand is approximately 1.5 m, the cord C of the hull is 74 mm, the thickness E of the hull is 18 mm, the diameter of the strand 1S, 1I and the holes 231 in the plates 23 is 17 mm, and the axis of the plate holes 231 and the spacer holes 244 is located 14 mm from the front of the leading edge 20.

Grâce à des mesures en soufflerie, il a été montré que l'influence de l'antenne sur les gouvernes de l'aéronef est liée à la distance entre le foyer aérodynamique FA de la carène et le centre de gravité G de l'aéronef. Pour que l'antenne ne déstabilise pas l'aéronef, et particulièrement n'intervienne pas d'une manière prépondérante sur les effets des gouvernes de l'aéronef, notamment de la gouverne de direction GD de l'aéronef, le foyer aérodynamique FA de la carène 2 est prévu en avant, du centre de gravité G de l'aéronef, comme montré à la figure 5. De préférence, le foyer aérodynamique FA est situé au voisinage du centre de gravité G de l'aéronef. Il est en effet impératif d'avoir des emplantures de carène 3S, 31 le plus en arrière possible sur le fuselage FU de manière à ce que les brins carénés ne perturbent pas les effets des gouvernes aussi bien pendant le déploiement de l'antenne qu'en régime de croisière de l'aéronef.Thanks to wind tunnel measurements, it has been shown that the influence of the antenna on the control surfaces of the aircraft is linked to the distance between the aerodynamic focus FA of the hull and the center of gravity G of the aircraft. So that the antenna does not destabilize the aircraft, and in particular does not intervene in a preponderant manner on the effects of the control surfaces of the aircraft, in particular of the rudder GD of the aircraft, the aerodynamic focus FA of hull 2 is provided in front, from the center of gravity G of the aircraft, as shown in FIG. 5. Preferably, the aerodynamic focus FA is located in the vicinity of the center of gravity G of the aircraft. It is indeed imperative to have hull roots 3S, 31 as rear as possible on the FU fuselage so that the streamlined strands do not disturb the effects of the control surfaces both during the deployment of the antenna and in cruising speed of the aircraft.

Lorsque les emplantures 3S et 31 des brins carénés 1S et 1I sont relativement en avant du centre de gravité de l'aéronef à cause d'implantation d'autres éléments notamment de sustentation sur l'arrière du fuselage FU, les brins déployés présentent une flèche FL pouvant être choisie entre 15° et 45°, de préférence 30° environ selon la réalisation illustrée, pour reculer les foyers FA des carènes.When the bases 3S and 31 of the faired strands 1S and 1I are relatively in front of the center of gravity of the aircraft due to the implantation of other elements, in particular of lift on the rear of the fuselage FU, the deployed strands have an arrow FL can be chosen between 15 ° and 45 °, preferably about 30 ° depending on the illustrated embodiment, to move the foci FA away from the hulls.

Pour obtenir la stabilité de chacune des carènes 2S et 21 lorsque l'aéronef est en régime de croisière, l'axe de rotation constitué par le brin d'antenne 1S, 1I est situé en avant du foyer FA de la carène, c'est-à-dire entre le foyer FA et le bord d'attaque 20 de la carène, comme montré à la figure 7. Typiquement, la distance, dite "marge statique", entre l'axe du brin 1S, 1I et le foyer aérodynamique FA de la carène est de l'ordre de 5 % de la corde C de la carène 2S, 21.To obtain the stability of each of the hulls 2S and 21 when the aircraft is at cruising speed, the axis of rotation constituted by the antenna strand 1S, 1I is located in front of the focus FA of the hull, it is ie between the focal point FA and the leading edge 20 of the hull, as shown in FIG. 7. Typically, the distance, called "static margin", between the axis of the strand 1S, 1I and the aerodynamic focal point FA of the hull is around 5% of the cord C of the hull 2S, 21.

Les moyens de déploiement pour déployer simultanément les brins carénés 1S et 1I sont identiques et symétriques par rapport à l'axe longitudinal XX de l'aéronef. En conséquence, l'un d'eux relatif au brin supérieur 1S est décrit en détail en référence aux figures 10 à 12.The deployment means for simultaneously deploying the streamlined strands 1S and 1I are identical and symmetrical with respect to the longitudinal axis XX of the aircraft. Consequently, one of them relating to the upper strand 1S is described in detail with reference to FIGS. 10 to 12.

Le moyen de déploiement 4S du brin supérieur 1S comprend un guide 40 pour le porte-brin respectif 3S. Le guide 40 a une forme en segment circulaire et s'étend perpendiculairement au fuselage FU, dans un plan axial vertical de l'aéronef A. Il est fixé à la structure de l'aéronef par deux consoles 4C. Le guide 40 présente une fente traversière 41 en segment circulaire qui est sensiblement de 120° selon la réalisation illustrée. La corde du segment de fente débouche sensiblement à la surface du fuselage et peut être protégée à l'avant par un cache aérodynamique fixé au fuselage FU. Le chant circulaire 42 du guide par lequel débouche la fente 41 à l'intérieur de l'aéronef est entouré de deux rails circulaires 43 à profil en L concentriques au segment et fixés à la structure de l'aéronef.The deployment means 4S of the upper strand 1S comprises a guide 40 for the respective strand holder 3S. The guide 40 has a circular segment shape and extends perpendicular to the fuselage FU, in a vertical axial plane of the aircraft A. It is fixed to the structure of the aircraft by two consoles 4C. The guide 40 has a transverse slot 41 in a circular segment which is substantially 120 ° according to the illustrated embodiment. The rope of the slit segment opens out substantially at the surface of the fuselage and can be protected at the front by an aerodynamic cover fixed to the FU fuselage. The circular edge 42 of the guide through which the slot 41 opens into the interior of the aircraft is surrounded by two circular rails 43 with an L-profile concentric with the segment and fixed to the structure of the aircraft.

Le porte-brin 3S formant emplanture de la carène présente un chant circulaire sur lequel est fixé un profilé rigide en U 31 qui est monté à glissement entre le chant 42 du guide 40 et les rails 43, lesquels forment une glissière circulaire 42-43 pour guider avec la fente 41 le porte-brin 3S. Comme cela apparaît en comparant les figures 10 et 11 et comme indiqué schématiquement à la figure 12, le porte-brin 3S a la forme sensible d'un secteur circulaire relatif à un angle PB sensiblement égal à la moitié de celui FE relatif au segment circulaire définissant la fente 41 dans le guide 40. Dans ces conditions, à la position repliée PR montrée à la figure 10, le porte-brin 3S occupe sensiblement le demi-segment relatif à la fente de guide 41 et situé vers l'avant de l'aéronef, et à la position déployée PD montrée à la figure 11, le porte-brin 3S occupe sensiblement l'autre demi-segment relatif à la fente de guide 41 et situé vers l'arrière de l'aéronef.The strand holder 3S forming the root of the hull has a circular edge on which is fixed a rigid U-shaped section 31 which is slidably mounted between the edge 42 of the guide 40 and the rails 43, which form a circular slide 42-43 for guide the 3S strand holder with slot 41. As shown by comparing Figures 10 and 11 and as shown schematically in Figure 12, the strand holder 3S has the substantial shape of a circular sector relative to an angle PB substantially equal to half that FE relating to the circular segment defining the slot 41 in the guide 40. Under these conditions, in the folded position PR shown in FIG. 10, the strand holder 3S occupies substantially the half-segment relating to the guide slot 41 and situated towards the front of the 'aircraft, and in the deployed position PD shown in Figure 11, the strand holder 3S occupies substantially the other half-segment relating to the guide slot 41 and located towards the rear of the aircraft.

Comme montré schématiquement à la figure 12, après avoir traversé la carène 2S, le brin 1S est fixé, par exemple par collage, dans un court conduit interne pratiqué dans le sommet 32 du porte-brin sensiblement en prolongement du bord d'attaque 20 de la carène 2S. Puis une portion 13 du brin 1S traverse librement une fente avant 33 du porte-brin 3S, particulièrement en position repliée PR (figure 10), et la fente 41 du guide 40 jusqu'à un connecteur 14 fixé à la structure de l'aéronef. Le connecteur relie le brin 1S à un câble coaxial d'alimentation 15S sortant d'un amplificateur de puissance 16S d'une source de brouillage installée dans le nez NE de l'aéronef. L'amplificateur 16S est séparé par une plaque de refroidissement centrale 17 d'un autre amplificateur 16I alimentant par un câble coaxial 15I l'autre brin d'antenne 1I.As shown diagrammatically in FIG. 12, after having crossed the hull 2S, the strand 1S is fixed, for example by gluing, in a short internal conduit formed in the top 32 of the strand holder substantially in extension of the leading edge 20 of the 2S hull. Then a portion 13 of the strand 1S freely crosses a front slot 33 of the strand holder 3S, particularly in the folded position PR (FIG. 10), and the slot 41 of the guide 40 up to a connector 14 fixed to the structure of the aircraft . The connector connects the strand 1S to a coaxial power cable 15S coming out of a power amplifier 16S from a jamming source installed in the NE nose of the aircraft. The amplifier 16S is separated by a central cooling plate 17 from another amplifier 16I supplying by coaxial cable 15I the other antenna strand 1I.

En position déployée PD, le point de fixation du brin 1S matérialisé par le connecteur 14 est sensiblement sur l'axe du brin et le brin est sensiblement rectiligne. En position repliée PR, la portion 13 du brin 1S est fléchie avec une courbure dont le rayon est assez grand pour éviter toute pliure ou cassure du brin, particulièrement en sortie du conduit au sommet 32 du porte-brin.In the deployed position PD, the point of attachment of the strand 1S materialized by the connector 14 is substantially on the axis of the strand and the strand is substantially rectilinear. In the folded position PR, the portion 13 of the strand 1S is bent with a curvature whose radius is large enough to avoid any bending or breakage of the strand, particularly at the outlet of the conduit at the top 32 of the strand holder.

Pour satisfaire cette condition, le centre de rotation fictif CR correspondant à la glissière circulaire composée par le chant de porte-brin 42 et par les rails 43 et au chant circulaire 31 du porte-brin coulissant dans la glissière est situé dans un secteur angulaire obtus avant formé entre le corps de fuselage FU de l'aéronef, et donc l'axe longitudinal XX, et le brin 1S à la position déployée PD. Comme cela apparaît à la figure 12, la portion du brin 1S fixée dans le sommet 32 du porte-brin 3S ne passe pas par le centre de rotation CR afin d'éviter toute fêlure du brin.To satisfy this condition, the fictitious center of rotation CR corresponding to the circular slide composed by the edge of the strand holder 42 and by the rails 43 and to the circular edge 31 of the strand holder sliding in the slide is located in an obtuse angular sector. forward formed between the fuselage body FU of the aircraft, and therefore the longitudinal axis XX, and the strand 1S in the deployed position PD. As shown in FIG. 12, the portion of the strand 1S fixed in the apex 32 of the strand holder 3S does not pass by the center of rotation CR in order to avoid any cracking of the strand.

Dans les trois réalisations de la partie motrice des moyens de déploiement des brins d'antenne décrites ci-après, la disposition des éléments composant les moyens de déploiement est symétrique par rapport à l'axe longitudinal XX de l'aéronef, comme le sont les brins d'antenne 1S et 1I et les guides de porte-brin 3S et 31, et un moyen moteur central pour déployer les brins de l'antenne est commun aux deux moyens de déploiement 4S et 41. Dans ces trois réalisations, lorsque les brins 1S, 1I doivent être déployés, l'activation du moyen moteur est simultanée au déverrouillage de dispositifs d'encliquetage ES et EI maintenant les extrémités libres 10S et 10I des carènes contre le fuselage FU de l'aéronef, comme montré à la figure 2.In the three embodiments of the drive part of the means for deploying the antenna strands described below, the arrangement of the elements making up the deployment means is symmetrical with respect to the longitudinal axis XX of the aircraft, as are the antenna strands 1S and 1I and the strand carrier guides 3S and 31, and a central motor means for deploying the antenna strands is common to the two deployment means 4S and 41. In these three embodiments, when the strands 1S, 1I must be deployed, the activation of the drive means is simultaneous with the unlocking of latching devices ES and EI keeping the free ends 10S and 10I of the hulls against the fuselage FU of the aircraft, as shown in FIG. 2.

Selon la première réalisation montrée à la figure 13, chaque moyen de déploiement 4Sa, 4Ia comprend une sangle de traction 5Sa, 5Ia. L'extrémité avant de la sangle est fixée à l'extrémité arrière du chant circulaire 31 du porte-brin respectif mobile 3S par l'intermédiaire d'un écrou prisonnier 51Sa, 51Ia. L'extrémité arrière de la sangle est reliée à un moyen moteur constitué par un enrouleur de sangle à ressort de compression 6a. La sangle est appliquée contre les petites ailes co-circulaires des rails de glissière 43 depuis l'écrou prisonnier 51Sa, 51Ia jusqu'à une poulie de renvoi 52Sa, 52Ia montée folle à l'extrémité arrière du guide respectif 40.According to the first embodiment shown in Figure 13, each deployment means 4Sa, 4Ia comprises a traction strap 5Sa, 5Ia. The front end of the strap is fixed to the rear end of the circular edge 31 of the respective movable strand holder 3S by means of a captive nut 51Sa, 51Ia. The rear end of the strap is connected to a motor means constituted by a compression spring strap reel 6a. The strap is applied against the small co-circular wings of the slide rails 43 from the captive nut 51Sa, 51Ia to a deflection pulley 52Sa, 52Ia mounted idly at the rear end of the respective guide 40.

En position repliée PR, le ressort de compression est comprimé, c'est-à-dire l'enrouleur est armé avant décollage ou catapultage de l'aéronef, et les sangles de traction 5Sa et 5Ia sont déroulées.In the folded position PR, the compression spring is compressed, i.e. the reel is armed before takeoff or catapult of the aircraft, and the traction straps 5Sa and 5Ia are unwound.

Un moyen temporisateur mécanique ou électromécanique ou un tel moyen temporisateur télécommandé commande, après le décollage ou catapultage de l'aéronef, la libération du ressort comprimé dans l'enrouleur 6a de manière à enrouler les sangles 5Sa et 5Ia qui tractent alors les porte-brin 3S et 31 vers l'arrière. Les porte-brin glissent dans les guides respectifs 40 en sens contraire jusqu'à atteindre en butée la position déployée PD.A mechanical or electromechanical timer means or such a remote-controlled timer means controls, after takeoff or catapulting of the aircraft, the release of the compressed spring in the reel 6a so as to wind the straps 5Sa and 5Ia which then tow the strand carriers 3S and 31 backwards. The strand carriers slide in the respective guides 40 in opposite directions until they reach the deployed position PD.

En référence à la figure 14, un moyen de déploiement 4Sb, 4Ib selon la seconde réalisation comprend un système de roue et vis sans fin. La vis sans fin est une tige filetée 5Sb, 5Ib rigide en nylon s'étendant longitudinalement dans l'aéronef. Au niveau d'un palier de vis 51Sb, 51Ib sous le milieu de la glissière respective 42-43, une extrémité avant de la tige engrène avec une denture correspondante prévue sur le chant circulaire 31 du porte-brin respectif 3S, 31. Une extrémité arrière de la tige engrène avec un engrenage de renvoi d'angle 52Sb, 52Ib lié à une extrémité respective de l'arbre d'un moteur électrique 6b.Referring to Figure 14, a deployment means 4Sb, 4Ib according to the second embodiment comprises a wheel and worm system. The worm is a rigid nylon 5Sb, 5Ib threaded rod extending longitudinally in the aircraft. At a screw bearing 51Sb, 51Ib under the middle of the respective slide 42-43, a front end of the rod meshes with a corresponding toothing provided on the circular edge 31 of the respective strand holder 3S, 31. One end rear of the rod meshes with a bevel gear 52Sb, 52Ib linked to a respective end of the shaft of an electric motor 6b.

Sous la commande d'un temporisateur armé préalablement avant décollage ou catapultage, ou télécommandé, le moteur électrique est activé pour tourner en sens contraire les tiges filetées 5Sb et 5Ib afin que les porte-brin 3S et 31 tournent vers l'arrière en glissant dans les guides respectifs 40. Au moins un interrupteur de fin de course de déploiement 7Db est disposé à l'extrémité arrière de l'une des glissières de guidage 42-43 pour être actionné par butée de l'extrémité arrière du porte-brin respectif 3S afin de couper l'alimentation du moteur 6b.Under the control of a timer armed prior to takeoff or catapult, or remote-controlled, the electric motor is activated to turn the threaded rods 5Sb and 5Ib in opposite directions so that the strand carriers 3S and 31 turn backwards by sliding in the respective guides 40. At least one deployment limit switch 7Db is arranged at the rear end of one of the guide rails 42-43 to be actuated by a stop at the rear end of the strand holder respective 3S in order to cut the power to the motor 6b.

Un moyen de déploiement 4Ss, 4Ic selon la troisième réalisation montrée à la figure 15 comprend également un système de roue et vis sans fin. Cependant, la vis sans fin est une tige filetée flexible 5Sc, 5Ic qui est développée sensiblement parallèlement au demi-chant circulaire arrière de la glissière respective 42-43. L'extrémité avant de la tige 5Sc, 5Ic engrène avec un écrou 51Sc, 51Ic fixé à l'extrémité arrière du chant circulaire 31 du porte-brin respectif 3S, 31. Un engrenage de renvoi d'angle 52Sc, 52Ic relie l'extrémité arrière de la glissière respective à une extrémité respective d'un moteur électrique 6c.Deployment means 4Ss, 4Ic according to the third embodiment shown in FIG. 15 also comprises a wheel and worm system. However, the worm is a flexible threaded rod 5Sc, 5Ic which is developed substantially parallel to the rear circular half-edge of the respective slide 42-43. The front end of the rod 5Sc, 5Ic meshes with a nut 51Sc, 51Ic fixed to the rear end of the circular edge 31 of the respective strand holder 3S, 31. A bevel gear 52Sc, 52Ic connects the end rear of the respective slide at a respective end of an electric motor 6c.

Lorsque le moteur 6c est actionné, la rotation de la tige 5Sc, 5Ic est vissée dans l'écrou 51Sc, 51Ic, qui passe entre les rails respectifs 43 en direction de l'engrenage de renvoi d'angle respectif 52Sc, 52Ic. Un interrupteur de fin de course de déploiement 7Dc est également prévu à l'extrémité arrière de l'une des glissières de guidage 42-43.When the motor 6c is activated, the rotation of the rod 5Sc, 5Ic is screwed into the nut 51Sc, 51Ic, which passes between the respective rails 43 in the direction of the respective angular gear 52Sc, 52Ic. A deployment limit switch 7Dc is also provided at the rear end of one of the guide rails 42-43.

De préférence, dans les deuxième et troisième réalisations, le moteur électrique 6b, 6c peut commander en sens inverse la rotation des tiges filetées afin que les porte-brin passent de la position d'antenne déployée PD à la position d'antenne repliée PR, avant l'atterrissage de l'aéronef, et les extrémités libres 10S et 10I des carènes s'emboîtent dans les dispositifs d'encliquetage ES et EI. Dans ce cas, au moins un interrupteur de fin de course de repliement 7Rb, 7Rc est prévu à l'extrémité avant de l'une des glissières de guidage 41-42 pour être actionné par butée de l'extrémité avant du porte-brin respectif pour couper l'alimentation du moteur 6b, 6c.Preferably, in the second and third embodiments, the electric motor 6b, 6c can control the rotation of the threaded rods in opposite directions so that the strand holders pass from the deployed antenna position PD to the folded antenna position PR, before the landing of the aircraft, and the free ends 10S and 10I of the hulls fit into the snap-on devices ES and EI. In this case, at least one folding limit switch 7Rb, 7Rc is provided at the front end of one of the slides 41-42 guide to be actuated by the stop of the front end of the respective strand holder to cut the power to the motor 6b, 6c.

Selon d'autres réalisations, et en fonction du type d'aéronef et particulièrement de ses ailes, les brins avec leurs moyens de déploiement sont positionnés dans un plan horizontal, c'est-à-dire sont parallèles aux ailes et gouvernes de profondeur de l'aéronef.According to other embodiments, and depending on the type of aircraft and particularly its wings, the strands with their deployment means are positioned in a horizontal plane, that is to say are parallel to the wings and elevators of the aircraft.

Claims (19)

Antenne filaire comprenant un brin (1S), caractérisé en ce qu'elle comprend une carène (2S) montée à rotation libre autour du brin d'antenne (1S).Wired antenna comprising a strand (1S), characterized in that it comprises a hull (2S) mounted with free rotation around the antenna strand (1S). Antenne conforme à la revendication 1, caractérisée en ce que la carène comprend des plaquettes rigides transversales (23) et des entretoises (24) entre les plaquettes, le brin d'antenne (1S) traversant à glissement les plaquettes (23) et librement les entretoises (24).Antenna according to claim 1, characterized in that the hull comprises transverse rigid plates (23) and spacers (24) between the plates, the antenna strand (1S) passing slidingly through the plates (23) and freely spacers (24). Antenne conforme à la revendication 2, caractérisée en ce que les entretoises (24) sont constituées de deux demi-entretoises moulées symétriques ayant des faces (21F) collées l'une contre l'autre dans un plan longitudinal au brin.Antenna according to claim 2, characterized in that the spacers (24) consist of two symmetrical molded half-spacers having faces (21F) glued against each other in a longitudinal plane to the strand. Antenne conforme à l'une quelconque des revendications 1 à 3, caractérisée en ce que la carène est translatable avec jeu le long du brin d'antenne entre une butée (12) fixée à une extrémité libre du brin d'antenne (1S) et une autre butée (3S) à laquelle est fixé le brin d'antenne, de préférence formant emplanture de la carène.Antenna according to any one of claims 1 to 3, characterized in that the hull is translatable with clearance along the antenna strand between a stop (12) fixed to a free end of the antenna strand (1S) and another stop (3S) to which the antenna strand is fixed, preferably forming the base of the hull. Antenne conforme à l'une quelconque des revendications 1 à 4, caractérisée en ce que la carène (2S) a un profil d'aile d'avion transversalement au brin (1S), le profil ayant de préférence une corde (C) sensiblement comprise entre un quart et un cinquième de l'épaisseur (E) du profil.Antenna according to any one of claims 1 to 4, characterized in that the hull (2S) has an aircraft wing profile transversely to the strand (1S), the profile preferably having a cord (C) substantially included between a quarter and a fifth of the thickness (E) of the profile. Antenne conforme à la revendication 5, caractérisée en ce que l'axe du brin d'antenne est situé entre un bord d'attaque (20) de la carène et un foyer aérodynamique (FA) de la carène.Antenna according to claim 5, characterized in that the axis of the antenna strand is located between a leading edge (20) of the hull and an aerodynamic focus (FA) of the hull. Antenne conforme à l'une quelconque des revendications 1 à 6, caractérisée en ce que ledit brin (1S) a une extrémité (14) fixée dans un engin (A) et s'étend dans un plan sensiblement longitudinal à l'engin.Antenna according to any one of claims 1 to 6, characterized in that said strand (1S) has one end (14) fixed in a machine (A) and extends in a plane substantially longitudinal to the machine. Antenne conforme à la revendication 7, caractérisée en ce que le brin (3S) s'étend sensiblement dans un plan longitudinal de gouverne de direction (GD) de l'engin (A).Antenna according to claim 7, characterized in that the strand (3S) extends substantially in a longitudinal plane of the rudder (GD) of the vehicle (A). Antenne conforme à la revendication 7 ou 8, caractérisée en ce que le brin forme une flèche (FL), de préférence comprise entre 15° et 45° environ, avec un plan perpendiculaire à l'axe longitudinal (XX) de l'engin (A).Antenna according to claim 7 or 8, characterized in that the strand forms an arrow (FL), preferably between approximately 15 ° and 45 °, with a plane perpendicular to the longitudinal axis (XX) of the machine ( AT). Antenne conforme à l'une quelconque des revendications 7 à 9, caractérisée en ce qu'un foyer aérodynamique (FA) de la carène (1S) est situé à proximité du centre de gravité (G) de l'engin (A).Antenna according to any one of claims 7 to 9, characterized in that an aerodynamic focus (FA) of the hull (1S) is located near the center of gravity (G) of the vehicle (A). Antenne conforme à l'une quelconque des revendications 7 à 10, comprenant un moyen (4S) lié à l'engin (A) pour déployer le brin d'antenne (1S) depuis une première position (PR) à laquelle le brin d'antenne est replié sensiblement contre l'engin, vers une seconde position (PD) à laquelle le brin d'antenne forme un angle aigu avec un axe longitudinal (XX) de l'engin.An antenna according to any one of claims 7 to 10, comprising means (4S) linked to the machine (A) for deploying the antenna strand (1S) from a first position (PR) at which the strand antenna is folded substantially against the machine, towards a second position (PD) at which the strand antenna forms an acute angle with a longitudinal axis (XX) of the machine. Antenne conforme à la revendication 11, caractérisée en ce que le brin (1S) comporte une portion libre et fléchissable (13) entre un point de fixation (14) du brin lié à l'engin (A) et un porte-brin (3S) auquel le brin d'antenne (1S) est fixé et formant emplanture de la carène (2S), ladite portion libre dudit brin étant fléchie à ladite première position (PR) et sensiblement linéaire à ladite seconde position (PD).Antenna according to claim 11, characterized in that the strand (1S) has a free and bendable portion (13) between a fixing point (14) of the strand linked to the machine (A) and a strand holder (3S ) to which the antenna strand (1S) is fixed and forming the root of the hull (2S), said free portion of said strand being bent at said first position (PR) and substantially linear at said second position (PD). Antenne conforme à la revendication 12, caractérisée en ce que le porte-brin (3S) tourne autour d'un centre (CR) situé dans un secteur obtus devant le brin (1S) et délimité par le brin à la seconde position (PD) et l'axe longitudinal (XX) de l'engin.Antenna according to claim 12, characterized in that the strand holder (3S) rotates around a center (CR) located in an obtuse sector in front of the strand (1S) and delimited by the strand in the second position (PD) and the longitudinal axis (XX) of the machine. Antenne conforme à la revendication 12 ou 13, caractérisée en ce que le moyen pour déployer comprend un guide (40) en forme de segment circulaire obtus, de préférence de l'ordre de 120°, fixé au corps de l'engin, ledit porte-brin mobile formant sensiblement un secteur circulaire couvrant sensiblement la moitié du guide (40) et étant monté à coulissement dans le guide pour tourner d'une position avant correspondant à ladite première position (PR) du brin d'antenne à une position arrière correspondant à ladite seconde position (PD) du brin d'antenne.Antenna according to claim 12 or 13, characterized in that the means for deploying comprises a guide (40) in the form of an obtuse circular segment, preferably of the order of 120 °, fixed to the body of the machine, said door -mobile strand substantially forming a circular sector covering substantially half of the guide (40) and being slidably mounted in the guide to rotate from a front position corresponding to said first position (PR) of the antenna strand to a corresponding rear position at said second position (PD) of the antenna strand. Antenne conforme à l'une quelconque des revendications 11 à 14, comprenant un moyen moteur (6a, 6b, 6c) pour activer le moyen pour déployer (4Sa, 4Sb, 4Sc) afin de déplacer le brin d'antenne depuis ladite première position (PR) vers ladite seconde position (PD) après décollage de l'engin, et de préférence depuis ladite seconde position (PD) vers ladite première position (PR) avant atterrissage de l'engin.An antenna according to any one of claims 11 to 14, comprising a motor means (6a, 6b, 6c) to activate the means for deploying (4Sa, 4Sb, 4Sc) in order to move the antenna strand from said first position (PR) to said second position (PD) after takeoff of the craft, and preferably from said second position (PD) to said first position (PR) before landing of the craft. Antenne conforme à l'une quelconque des revendications 7 à 15, comprenant un porte-brin (3S) auquel le brin d'antenne (1S) est fixé et coulissant dans une glissière circulaire (42-43), et une sangle de traction (5Sa) ayant une extrémité (51Sa) fixée à un porte-brin (3S) et une autre extrémité liée à un moyen enrouleur (6a), de préférence à travers un moyen de renvoi (52Sa) situé sensiblement le long de ladite glissière (42-43).Antenna according to any one of Claims 7 to 15, comprising a strand holder (3S) to which the antenna strand (1S) is fixed and sliding in a circular slide (42-43), and a traction strap ( 5Sa) having one end (51Sa) fixed to a strand holder (3S) and another end linked to a winding means (6a), preferably through a deflection means (52Sa) located substantially along said slide (42 -43). Antenne conforme à l'une quelconque des revendications 7 à 15, comprenant un porte-brin (3S) auquel le brin d'antenne (1S) est fixé et coulissant dans une glissière circulaire (42-43), et une tige filetée (5Sb) ayant une extrémité coopérant avec une denture le long d'un chant circulaire (31) dudit porte-brin (3S) et une autre extrémité (52Sb) entraînée en rotation par un moyen moteur (6b).Antenna according to any one of claims 7 to 15, comprising a strand holder (3S) to which the antenna strand (1S) is fixed and sliding in a circular slide (42-43), and a threaded rod (5Sb ) having one end cooperating with a toothing along a circular edge (31) of said strand holder (3S) and another end (52Sb) driven in rotation by a motor means (6b). Antenne conforme à l'une quelconque des revendications 7 à 15, comprenant un porte-brin (3S) auquel le brin d'antenne (1S) est fixé et coulissant dans une glissière circulaire (42-43), et une tige filetée (5Sc) ayant une première extrémité coopérant avec un écrou (51Sc) lié audit porte-brin (3S) et une autre extrémité entraînée par un moyen moteur (6c) de préférence à travers un moyen de renvoi d'angle (52Sc) situé sensiblement le long de la glissière (42-43).Antenna according to any one of claims 7 to 15, comprising a strand holder (3S) to which the antenna strand (1S) is fixed and sliding in a circular slide (42-43), and a threaded rod (5Sc ) having a first end cooperating with a nut (51Sc) linked to said strand holder (3S) and another end driven by a motor means (6c) preferably through an angle gear (52Sc) located substantially along the slide (42-43). Antenne conforme à l'une quelconque des revendications 1 à 18, comprenant un autre brin (1I) autour duquel une autre carène (21) est montée à rotation libre, les brins (1S, 1I) étant disposés symétriquement par rapport à un axe longitudinal (XX) d'un engin (A) supportant l'antenne.An antenna according to any one of claims 1 to 18, comprising another strand (1I) around which another hull (21) is mounted to rotate freely, the strands (1S, 1I) being arranged symmetrically with respect to a longitudinal axis (XX) of a machine (A) supporting the antenna.
EP19960401759 1995-09-08 1996-08-08 A wire antenna for a machine Expired - Lifetime EP0762531B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9510643 1995-09-08
FR9510643A FR2738674B1 (en) 1995-09-08 1995-09-08 WIRED ANTENNA FOR MACHINE

Publications (3)

Publication Number Publication Date
EP0762531A2 true EP0762531A2 (en) 1997-03-12
EP0762531A3 EP0762531A3 (en) 1997-03-19
EP0762531B1 EP0762531B1 (en) 2001-04-04

Family

ID=9482448

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19960401759 Expired - Lifetime EP0762531B1 (en) 1995-09-08 1996-08-08 A wire antenna for a machine

Country Status (3)

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EP (1) EP0762531B1 (en)
DE (1) DE69612343T2 (en)
FR (1) FR2738674B1 (en)

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1489869A (en) * 1974-10-22 1977-10-26 Hawker Siddeley Aviation Ltd Radio aerials for aircraft

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1489869A (en) * 1974-10-22 1977-10-26 Hawker Siddeley Aviation Ltd Radio aerials for aircraft

Also Published As

Publication number Publication date
DE69612343D1 (en) 2001-05-10
EP0762531A3 (en) 1997-03-19
FR2738674A1 (en) 1997-03-14
EP0762531B1 (en) 2001-04-04
FR2738674B1 (en) 1997-12-05
DE69612343T2 (en) 2001-09-06

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