EP0762531B1 - Drahtantenne für eine Maschine - Google Patents

Drahtantenne für eine Maschine Download PDF

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Publication number
EP0762531B1
EP0762531B1 EP19960401759 EP96401759A EP0762531B1 EP 0762531 B1 EP0762531 B1 EP 0762531B1 EP 19960401759 EP19960401759 EP 19960401759 EP 96401759 A EP96401759 A EP 96401759A EP 0762531 B1 EP0762531 B1 EP 0762531B1
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EP
European Patent Office
Prior art keywords
wire
antenna
hull
craft
antenna according
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP19960401759
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English (en)
French (fr)
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EP0762531A3 (de
EP0762531A2 (de
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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Publication date
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Publication of EP0762531A2 publication Critical patent/EP0762531A2/de
Publication of EP0762531A3 publication Critical patent/EP0762531A3/de
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Publication of EP0762531B1 publication Critical patent/EP0762531B1/de
Anticipated expiration legal-status Critical
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    • 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 an antenna wired intended in particular to be embedded in a craft such as aircraft.
  • the aircraft may be a reconnaissance aircraft or drone in which antenna is used for interference of waves radioelectric.
  • Such an antenna is generally of the type dipole with a large span of a few meters.
  • the two antenna strands are fixed respectively laterally in front of the fuselage of the aircraft, in front of the wings of the aircraft, and symmetrically by relative to the longitudinal axis of the machine.
  • the strands When taking off or catapulting the craft, the strands are at a first position at which it are arranged along the fuselage of the spacecraft. In cruising regime of the craft, the strands are suddenly deployed to a second position at which they extend perpendicular to the plane horizontal axial of the aircraft. One of the strands extends laterally to the fuselage up, and the other strand extends laterally down the fuselage.
  • This antenna considerably increases the drag of the aircraft up to about 50%, and requires aircraft engine power significantly higher than that required for propulsion of the aircraft without antenna.
  • the arrangement of the antenna strands and their trail disrupt the effectiveness of the control surfaces of the craft, particularly that of the rudder also called yaw control.
  • the present invention aims to remedy the aforementioned drawbacks, and more specifically to provide an antenna whose line increases only by a few percent, that is to say so negligible, the drag of the mobile machine.
  • the wire antenna includes a strand and is characterized in that it includes a hull free rotation mounted around the antenna strand. Thanks to this free rotation assembly, the hull is always positioned at zero incidence. The presence of this free hull in rotation brings a gain considerable on the drag of a vehicle carrying the streamlined antenna, compared to the train of this machine with a non-ttled antenna. The gain can reach around 50 to 80%.
  • the hull includes rigid pads cross and spacers between the platelets.
  • the antenna strand slides across the pads and freely the spacers in order to decrease the friction of the hull on the strand.
  • the pads and spacers are extremely light to reduce the inertia of the hull.
  • the spacers can consist of two symmetrical molded half-spacers having faces glued together in a plane longitudinal to the strand.
  • the hull is translatable with clearance along the antenna strand between a stop attached 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 machine.
  • the aerodynamics of the hull is chosen in such a way so that it has an airplane wing profile transversely to the strand.
  • Profile preferably a cord substantially between a quarter and a fifth of the thickness of the profile.
  • the axis of the strand antenna can 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 machine mobile such as aircraft.
  • the strand has a end fixed in the machine and extends in a plane substantially longitudinal to the machine.
  • the antenna can comprise two symmetrical strands by relative to a longitudinal axis of the machine and developed perpendicular to the plane of lift formed by the wings of the craft.
  • each strand extends substantially in a longitudinal rudder plane of the craft.
  • 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 a strand are identical to means relating to the other strand and arranged symmetrically with respect to the axis longitudinal of the machine.
  • a related means the machine deploys the antenna strand only after takeoff from a first position at which the antenna strand is folded substantially against the machine, towards a second position at which the strand antenna forms an acute angle with an axis longitudinal of the machine.
  • the strand has a free and bendable portion between a attachment point of the strand linked to the machine and a strand holder to which the antenna strand is attached and forming root of the hull.
  • the free portion of the strand is flexed to said first position and substantially linear at said second position.
  • the strand holder turns around a center located in an obtuse sector in front the strand and delimited by the strand in the second position and the longitudinal axis of the machine.
  • the means for deploying may include a guide in the shape 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 sector circular covering substantially half of the guide and is slidably mounted in the guide for turn from a forward position corresponding to the first position of the antenna strand at a position rear corresponding to the second position of the strand antenna.
  • Motor means can be provided to activate the means to deploy in order to move the strand antenna from the first position to the second position after takeoff of the craft.
  • This driving force can also be provided to move the strand antenna from second position to first position before landing of the machine.
  • the antenna includes a strand holder to which the antenna strand is fixed and sliding in a circular slide, and a pull strap having one end attached to a strand holder and another end linked to a means reel, preferably through a return means located substantially along the slide, by example at the rear end of the slide.
  • the antenna includes 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 motor means.
  • the antenna includes 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 a other end driven by a motor means of preferably through a bevel gear located substantially along the slide.
  • the antenna is made up of two fine metal strands cylindrical 1S and 1I protruding from the nose NE of aircraft A in front of wings AI thereof.
  • the strands are always arranged in an axial plane longitudinal of the aircraft, preferably vertical, that is to say in a plane perpendicular to the wings AI aircraft according to the illustrated embodiments, and symmetrically with respect to the longitudinal axis XX of the aircraft.
  • the strands 1S and 1I are at a first position, called folded position PR, and are arranged along the aircraft fuselage FU, as shown in Figures 1 and 2. Free ends 10S and 10I of the strands are arranged towards the rear of the machine. Extremities 11S and 11I of the strands mounted so as to pivot flexible "in the structure of the aircraft are arranged towards the front of the aircraft. One of the 1S strands are arranged above the aircraft and the other strand 1I is located below the aircraft.
  • the strands are deployed at a second position, called the deployed position PD, by 4S and 4I deployment means 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 Figures 3 and 4.
  • the portion of each of the strands of the antenna external to the aircraft includes a very light aerodynamic hull in airplane wing shape to reduce drag antenna strands. Knowing that the strands are identical, we will refer in the following to the strand higher 1S for example.
  • the transverse profile of the hull 2S of the strand 1S includes a substantially ogival leading edge 20, a body 21 narrowing in the form of a bevel from the leading edge 20 toward a trailing edge 22 to the back of the hull.
  • the hull structure is composed of several plastic plates 23 distributed almost regularly along the strand 1S antenna and having the transverse profile described above and shown in Figure 7. Platelets form wing reinforcement ribs and have circular holes 231 traversed by sliding by the antenna strand 1S. Between these plates, foam sections, for example foam reinforced rigid or semi-rigid polyurethane, form light spacers 24 also having the profile transverse external shown in figure 7.
  • each spacer in foam 24 is obtained by means of a mold for molding one of two identical half-spacers which are glued against each other in a plane longitudinal mediator 21P of the hull 2S.
  • the mold includes a punch and a die.
  • Hallmark 241 has a flat internal surface 242 which corresponds in the median plane of the hull 21P.
  • a protuberance semi-cylindrical 243 projects on the surface 242 and is complementary to half of the cylindrical duct longitudinal 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 1S strand In order to minimize the friction of the hull 2S on the strand 1S and therefore all risk of blocking in rotation of the hull which would make the aircraft ungovernable, the 1S strand would cross freely the cylindrical conduits 244 formed at the front of the foam spacers 24, wider than the plate holes 231.
  • the friction metal on plastic of strand 35 in the platelets 23 can be further decreased by wrapping the strand in a plastic sheath such as Teflon. Under these conditions, the hull 24 may freely rotate around the carrier strand 1S 2S hull, almost without friction, and so position themselves freely at zero incidence in order to stay in the wind bed as well when deployment of antenna strands only during the regime of aircraft cruise with antenna strands deployed.
  • the hull 2S is also mounted in free translation on a short distance, that is to say with a large clearance, the 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 2S hull is limited by a second stop formed by a movable profiled strand holder 3S constituting a hull root independent of the displacement of the hull in rotation and translation.
  • the 3S strand holder is mounted at perpendicular rotation to strand 1S in the structure of the aircraft.
  • an antenna according to the invention to scramble waves electromagnetic in the metric and decimetric is composed of strands 1S and 1I having each a length between a quarter wave and about half a wave.
  • thickness E of hulls 2S and 2I is between a quarter and a fifth of the chord C of the hulls, i.e. the width of the hulls.
  • the length L of the hull 2S, 2I of each strand is about 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 insert holes 231 and 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 related to the distance between the focus FA aerodynamics of the hull and center of gravity G of the aircraft. So that the antenna does not destabilize the aircraft, and in particular does not intervene predominantly on the effects of control surfaces of the aircraft, in particular of the control surface direction GD of the aircraft, the aerodynamic focus FA hull 2 is provided in front, from the center of aircraft gravity G, as shown in Figure 5.
  • the aerodynamic focus FA is located at the vicinity of the aircraft center of gravity G. It is indeed imperative to have hull root 3S, 3I as far back as possible on the FU fuselage so that the shrouded strands do not disturb not the effects of the control surfaces as well during the deployment of the antenna in cruise mode the aircraft.
  • the strands deployed have an arrow FL which can be chosen between 15 ° and 45 °, preferably around 30 ° depending on the illustrated realization, to move back the AF foci of hulls.
  • the axis of rotation formed by the strand antenna 1S, 1I is located in front of the focal point FA of the hull, i.e. between the focal point FA and the edge hull 20, as shown in the figure 7.
  • the distance, called "static margin" between the axis of the strand 1S, 1I and the aerodynamic focus FA of the hull is around 5% of the cord C of the hull 2S, 2I.
  • Deployment means to deploy simultaneously the shrouded strands 1S and 1I are identical and symmetrical about the axis longitudinal XX of the aircraft. As a result, one of them relative to the upper strand 1S is described in detail with reference to Figures 10 to 12.
  • the means of deployment 4S of the upper strand 1S includes a guide 40 for the respective strand holder 3S.
  • the guide 40 has a circular segment shape and extends perpendicular to the FU fuselage, in a vertical axial plane of the aircraft A. It is fixed to the structure of the aircraft by two 4C consoles.
  • Guide 40 has a transverse slot 41 in segment circular which is approximately 120 ° depending on the illustrated realization.
  • the rope of the slit segment opens out appreciably at the surface of the fuselage and can be protected at the front by a cover aerodynamics attached to the FU fuselage.
  • Singing circular 42 of the guide through which the slot opens 41 inside the aircraft is surrounded by two circular rails 43 with L-profile concentric with segment and attached to the structure of the aircraft.
  • the 3S strand holder forming the root of the hull has a circular edge on which is fixed a rigid U-shaped profile 31 which is slidably mounted between edge 42 of guide 40 and rails 43, which form a circular slide 42-43 for guide the 3S strand holder with slot 41.
  • the strand holder 3S has the sensitive shape of a circular sector relative to an angle PB substantially equal to half of that FE relating to the circular segment defining the slot 41 in the guide 40. Under these conditions, at the folded position PR shown in FIG.
  • the strand holder 3S occupies substantially the half segment relative to the guide slot 41 and located towards the front of the aircraft, and in the deployed position PD shown at Figure 11, the 3S strand holder 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 duct internal practiced 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 crosses freely a front slot 33 of the 3S strand holder, particularly in the folded position PR ( Figure 10), and the slot 41 of the guide 40 up to a connector 14 attached to the structure of the aircraft.
  • the connector connects the 1S strand to a 15S coaxial power cable coming out of a 16S power amplifier from a interference source installed in the NE nose of the aircraft.
  • the 16S amplifier is separated by a central cooling plate 17 from another 16I amplifier powered by a 15I coaxial cable the other antenna strand 1I.
  • the attachment point of the strand 1S materialized by connector 14 is substantially on the axis of the strand and the strand is substantially straight.
  • the portion 13 of strand 1S is bent with a curvature whose radius is large enough to avoid any bending or breaking of the strand, particularly on exit from the duct to the top 32 of the strand holder.
  • the fictitious rotation CR corresponding to the slide circular composed by the edge of strand holder 42 and by the rails 43 and the circular edge 31 of the strand holder sliding in the slide is located in a obtuse front angular sector formed between the body of fuselage FU of the aircraft, and therefore the longitudinal axis XX, and the strand 1S in the deployed position PD.
  • the portion of the strand 1S fixed in the top 32 of the 3S strand holder does not pass by the CR center of rotation in order to avoid any strand crack.
  • the arrangement of the elements component the means of deployment is symmetrical relative to the longitudinal axis XX of the aircraft, as are the antenna strands 1S and 1I and the strand guides 3S and 3I, and a motor means central to deploy the antenna strands is common to the two deployment means 4S and 4I.
  • the activation of the motor means is simultaneous with unlocking devices ES and EI snap fastening ends free 10S and 10I of the hulls against the fuselage FU of the aircraft, as shown in Figure 2.
  • each deployment means 4Sa, 4Ia includes a traction strap 5Sa, 5Ia.
  • the end front of the strap is attached to the rear end of the circular edge 31 of the respective mobile strand holder 3S by means of a captive nut 51Sa, 51Ia.
  • the rear end of the strap is connected to a motor means consisting of a strap winder compression spring 6a.
  • the strap is applied against the small co-circular wings of the rails slide 43 from the captive nut 51Sa, 51Ia up to a deflection pulley 52Sa, 52Ia mounted mad at the rear end of the respective guide 40.
  • the spring of compression is compressed, i.e. the retractor is armed before takeoff or catapult of the aircraft, and the traction straps 5Sa and 5Ia are unwound.
  • a mechanical timer means or electromechanical or such a timer means remote control after takeoff or catapulting of the aircraft, release of the spring compressed in the reel 6a so as to wind the 5Sa and 5Ia straps which then pull the strand holders 3S and 31 backwards.
  • the strands slide in the respective guides 40 in the opposite direction until reaching the deployed position PD.
  • a means of 4Sb, 4Ib deployment according to the second embodiment includes a wheel and worm system.
  • the opinion endless is a threaded rod 5Sb, 5Ib rigid in nylon extending longitudinally in the aircraft.
  • one front end of the rod meshes with a corresponding toothing provided on the circular edge 31 of the strand holder respective 3S, 3I.
  • a rear end of the rod meshes with a bevel gear 52Sb, 52Ib linked to a respective end of the shaft of a electric motor 6b.
  • the electric motor is activated to turn the threaded rods 5Sb in opposite directions and 5Ib so that the strands 3S and 3I turn towards the rear by sliding in the respective guides 40.
  • At least one limit switch 7Db deployment is arranged at the rear end of one of the guide rails 42-43 to be actuated by a stop on the rear end of the strand holder respective 3S in order to cut the power to the motor 6b.
  • a 4Ss, 4Ic deployment means depending on the third embodiment shown in Figure 15 includes also a wheel and worm system.
  • the worm is a threaded rod flexible 5Sc, 5Ic which is developed substantially parallel to the rear circular half-edge of the respective slide 42-43.
  • the front end of the 5Sc, 5Ic rod meshes with a 51Sc, 51Ic nut fixed to the rear end of the circular edge 31 of the strand holder respective 3S, 3I.
  • a bevel gear 52Sc, 52Ic connects the rear end of the slide respective to a respective end of a motor electric 6c.
  • the electric motor 6b, 6c can reverse direction of rod rotation threaded so that the strand holders pass from the antenna position extended PD to position antenna folded PR, before landing the aircraft, and the free ends 10S and 10I of the hulls fit into the devices ES and EI locking mechanism.
  • at least one fold-out limit switch 7Rb, 7Rc is provided at the front end of one of the slides guide 41-42 to be actuated by stopper the front end of the respective strand holder for cutting the power supply to the motor 6b, 6c.
  • strands with their means of deployment are positioned in a horizontal plane, i.e. 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)

Claims (19)

  1. Drahtantenne, bestehend aus einem Strahlungselement (1 S), dadurch gekennzeichnet, dass sie eine stromlinienförmige Verkleidung (2S) umfasst, die um das Strahlungselement (1S) frei drehbar ist.
  2. Antenne nach Patentanspruch 1, dadurch gekennzeichnet, dass die stromlinienförmige Verkleidung starre Querplatten (23) aufweist und Versteifungen (24) zwischen den Platten, wobei das Strahlungselement (1S) die Platten (23) gleitfähig durchquert und die Versteifungen (24) frei.
  3. Antenne nach Patentanspruch 2, dadurch gekennzeichnet, dass die Versteifungen (24) aus zwei symmetrischen, in einer Form hergestellten Halbversteifungen bestehen, die Seiten (21F) aufweisen, die in einer zum Strahlungselement längs verlaufenden Ebene aneinander geklebt sind.
  4. Antenne nach irgendeinem der Patentansprüche 1 bis 3, dadurch gekennzeichnet, dass die stromlinienförmige Verkleidung mit Spiel am Strahlungselement entlang zwischen einem Anschlag (12), der an einem freien Ende des Strahlungselementes (1S) angebracht ist, und einem anderen Anschlag (3S) verschiebbar ist, an dem das Strahlungselement angebracht ist und der vorzugsweise den Fuß der stromlinienförmigen Verkleidung bildet.
  5. Antenne nach irgendeinem der Patentansprüche 1 bis 4, dadurch gekennzeichnet, dass die stromlinienförmige Verkleidung (2S) quer zum Strahlungselement (1S) das Profil eines Flugzeugflügels hat, wobei das Profil vorzugsweise eine Flügeltiefe (C) aufweist, die im wesentlichen zwischen einem Viertel und einem Fünftel der Dicke (E) des Profils liegt.
  6. Antenne nach Patentanspruch 5, dadurch gekennzeichnet, dass die Achse des Strahlungselementes zwischen der Vorderkante (20) der stromlinienförmigen Verkleidung und einem aerodynamischen Mittelpunkt (FA) der Verkleidung liegt.
  7. Antenne nach irgendeinem der Patentansprüche 1 bis 6, dadurch gekennzeichnet, dass das genannte Strahlungselement (1S) ein Ende (14) hat, das in einer Maschine (A) befestigt ist, und in einer Ebene verläuft, die im wesentlichen in der Längsrichtung der Maschine verläuft.
  8. Antenne nach Patentanspruch 7, dadurch gekennzeichnet, dass das Strahlungselement (3S) im wesentlichen in einer Längsebene des Seitenruders (GD) der Maschine (A) verläuft.
  9. Antenne nach Patentanspruch 7 oder 8, dadurch gekennzeichnet, dass das Strahlungselement mit einer zur Längsachse (XX) der Maschine (A) senkrechten Ebene einen Pfeil (FL) bildet, der vorzugsweise zwischen ungefähr 15° und 45° liegt.
  10. Antenne nach irgendeinem der Patentansprüche 7 bis 9, dadurch gekennzeichnet, dass ein aerodynamischer Mittelpunkt (FA) der stromlinienförmigen Verkleidung (1S) nahe dem Schwerpunkt (G) der Maschine (A) liegt.
  11. Antenne nach irgendeinem der Patentansprüche 7 bis 10, ein Mittel (4S) umfassend, das mit der Maschine (A) verbunden ist, um das Strahlungselement (1S) aus einer ersten Stellung (PR), in der das Strahlungselement im wesentlichen an die Maschine eingefaltet ist, in eine zweite Stellung (PD) auszufalten, in der das Strahlungselement einen spitzen Winkel mit einer Längsachse (XX) der Maschine einschließt.
  12. Antenne nach Patentanspruch 11, dadurch gekennzeichnet, dass das Strahlungselement (1S) einen freien und biegsamen Abschnitt (13) zwischen einem Befestigungspunkt (14) des Strahlungselementes an der Maschine (A) und einem Strahlungselementträger (3S) aufweist, an dem das Strahlungselement (1S) angebracht ist und der den Fuß der stromlinienförmigen Verkleidung (2S) bildet, wobei der genannte freie Abschnitt des genannten Strahlungselementes in der genannten ersten Stellung (PR) gebogen und in der genannten zweiten Stellung (PD) im wesentlichen gradlinig ist.
  13. Antenne nach Patentanspruch 12, dadurch gekennzeichnet, dass der Strahlungselementträger (3S) sich um einen Mittelpunkt (CR) dreht, der in einem stumpfwinkligen Sektor vor dem Strahlungselement (1S) liegt, der von dem Strahlungselement in der zweiten Stellung (PD) und der Längsachse (XX) der Maschine begrenzt wird.
  14. Antenne nach Patentanspruch 12 oder 13, dadurch gekennzeichnet, dass das Mittel zum Ausfalten eine Führung (40) in Form eines stumpfwinkligen Kreissektors, vorzugsweise in der Größenordnung von 120°, umfasst, die am Körper der Maschine befestigt ist, wobei der genannte bewegliche Strahlungselementträger im wesentlichen einen Kreissektor bildet, der im wesentlichen die Hälfte der Führung (40) abdeckt und in der Führung gleitend angebracht ist, um sich von einer vorderen Stellung, die der genannten ersten Stellung (PR) des Strahlungselements entspricht, in eine hintere Stellung zu drehen, die der genannten zweiten Stellung (PD) des Strahlungselements entspricht.
  15. Antenne nach irgendeinem der Patentansprüche 11 bis 14, ein Motormittel (6a, 6b, 6c) umfassend, um das Mittel zum Ausfalten (4Sa, 4Sb, 4Sc) zu betätigen, um das Strahlungselement nach dem Start der Maschine aus der genannten ersten Stellung (PR) in die genannte zweite Stellung (PD) zu bringen und vorzugsweise vor dem Landen der Maschine aus der genannten zweiten Stellung (PD) in die genannte erste Stellung (PR).
  16. Antenne nach irgendeinem der Patentansprüche 7 bis 15, einen Strahlungselementträger (3S) umfassend, an dem das Strahlungselement (1S) befestigt ist, und der in einer kreisförmigen Gleitbahn (42-43) gleitet, und einen Zuggurt (5Sa) mit einem Ende (51Sa), das an einem Strahlungselementträger (3S) befestigt ist, und einem anderen Ende, das mit einem Aufrollmittel (6a) verbunden ist, vorzugsweise über ein Umlenkmittel (52Sa), das im wesentlichen an der genannten Gleitbahn (42-43) entlang angeordnet ist.
  17. Antenne nach irgendeinem der Patentansprüche 7 bis 15, einen Strahlungselementträger (3S) umfassend, an dem das Strahlungselement (1S) befestigt ist, und der in einer kreisförmigen Gleitbahn (42-43) gleitet, und eine Zahnstange (5Sb) mit einem Ende, das mit einer Zahnung am kreisförmigen Rand (31) des genannten Strahlungselementträgers (3S) entlang zusammenarbeitet, und einem anderen Ende (52Sb), das durch ein Motormittel (6b) in Drehung versetzt wird.
  18. Antenne nach irgendeinem der Patentansprüche 7 bis 15, einen Strahlungselementträger (3S) umfassend, an dem das Strahlungselement (1S) befestigt ist, und der in einer kreisförmigen Gleitbahn (42-43) gleitet, und eine Zahnstange (5Sc) mit einem ersten Ende, das mit einer Mutter (51Sc) zusammenarbeitet, die mit dem genannten Strahlungselementträger (3S) verbunden ist, und einem anderen Ende, das durch ein Motormittel (6c) vorzugsweise über ein Winkelumlenkmittel (52Sc) angetrieben wird, das im wesentlichen an der genannten Gleitbahn (42-43) entlang angeordnet ist.
  19. Antenne nach irgendeinem der Patentansprüche 1 bis 18, ein anderes Strahlungselement (1I) umfassend, um das eine andere stromlinienförmige Verkleidung (2I) frei drehbar angebracht ist, wobei die Strahlungselemente (1S, 1I) symmetrisch zu einer Längsachse (XX) einer Maschine (A) angeordnet sind, die die Antenne trägt.
EP19960401759 1995-09-08 1996-08-08 Drahtantenne für eine Maschine Expired - Lifetime EP0762531B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9510643A FR2738674B1 (fr) 1995-09-08 1995-09-08 Antenne filaire pour engin
FR9510643 1995-09-08

Publications (3)

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

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Application Number Title Priority Date Filing Date
EP19960401759 Expired - Lifetime EP0762531B1 (de) 1995-09-08 1996-08-08 Drahtantenne für eine Maschine

Country Status (3)

Country Link
EP (1) EP0762531B1 (de)
DE (1) DE69612343T2 (de)
FR (1) FR2738674B1 (de)

Family Cites Families (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
FR2738674A1 (fr) 1997-03-14
EP0762531A3 (de) 1997-03-19
EP0762531A2 (de) 1997-03-12
FR2738674B1 (fr) 1997-12-05
DE69612343D1 (de) 2001-05-10
DE69612343T2 (de) 2001-09-06

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