EP3203580B1 - Système d'antennes comprenant deux antennes - Google Patents

Système d'antennes comprenant deux antennes Download PDF

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Publication number
EP3203580B1
EP3203580B1 EP17158712.4A EP17158712A EP3203580B1 EP 3203580 B1 EP3203580 B1 EP 3203580B1 EP 17158712 A EP17158712 A EP 17158712A EP 3203580 B1 EP3203580 B1 EP 3203580B1
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EP
European Patent Office
Prior art keywords
axis
antenna
pivot bearing
positioning system
aperture
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Active
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EP17158712.4A
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German (de)
English (en)
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EP3203580A1 (fr
Inventor
Jörg Oppenländer
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Lisa Draexlmaier GmbH
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Lisa Draexlmaier GmbH
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Publication of EP3203580A1 publication Critical patent/EP3203580A1/fr
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    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q3/00—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system
    • H01Q3/02—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system using mechanical movement of antenna or antenna system as a whole
    • H01Q3/08—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system using mechanical movement of antenna or antenna system as a whole for varying two co-ordinates of the orientation
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/12—Supports; Mounting means
    • H01Q1/125—Means for positioning
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/27—Adaptation for use in or on movable bodies
    • H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q21/00—Antenna arrays or systems
    • H01Q21/28—Combinations of substantially independent non-interacting antenna units or systems

Definitions

  • the invention relates to an antenna system with two antennas, each with a positioning system, in particular for use on vehicles, e.g. Aircraft.
  • the low-profile flat-panel antennas required for the communication of aircraft with satellites are subject to particular space-constrained requirements with regard to the positioning of an antenna aperture in the direction of a satellite.
  • Positioning systems for antennas on mobile carriers have the task of optimally aligning the antenna during the spatial movement of the mobile carrier to a target, typically a target antenna, which is located, for example, on a satellite.
  • a target antenna typically a target antenna, which is located, for example, on a satellite.
  • a permanent radio link must be reliably maintained even with rapid movement of the carrier.
  • the wireless communication system uses electromagnetic waves of linear polarization, then the problem arises in 2-axis systems that, as the antenna rotates, the planes of polarization generally rotate so that the polarization plane of the target antenna is no longer aligned with the plane of polarization of the antenna itself on the positioning system matches.
  • a third axis can be introduced which allows rotation of the antenna about the beam axis regardless of the azimuth and elevation axis.
  • Such a 3-axis system then forms a complete orthogonal system and allows optimal polarization tracking.
  • the known 3-axis positioning systems for parabolic antennas can not be used for low-profile antennas, since due to the shape of the antenna aperture and the low installation space no independent rotation about the beam axis is possible, or the angular range in which such a rotation is possible, strong is restricted.
  • the polarization tracking is therefore carried out electronically or electromechanically in the signal processing path, so that no third mechanical axis is needed.
  • Such 2-axis positioning systems with separate polarization tracking 20 are particularly in hull-mounted low-profile antennas on aircraft or Vehicles used.
  • the antenna systems are characterized by the fact that the antenna apertures only have a very small height (typically less than 20 cm) in order to keep the air resistance as small as possible.
  • the antenna apertures are usually rectangular.
  • An example of such a positioning system according to the prior art is in FIG. 1 shown.
  • the additional problem arises that the antenna diagram changes spatially when the antenna rotates about elevation or azimuth axis with respect to the target antenna and its surroundings, since the antenna diagram is non-rotationally symmetrical Antennas is also not rotationally symmetric.
  • the antenna aperture with its azimuth axis always lies in the aircraft plane.
  • the aircraft level is typically a tangential plane to the earth's surface. If the aircraft position and satellite position are not of the same geographical length, then the antenna aperture, when directed at the satellite, will always be twisted by a certain angle, which depends on the geographic length, with respect to the plane of the Clarke orbit.
  • the main ray with respect to the tangent to the geostationary orbit at the location of the target satellite is the maximum width and it may lead to unauthorized irradiation of neighboring satellites.
  • the European patent application EP 0 982 797 A1 discloses two antenna units on a pedestal device with a rotation mechanism for rotating in an azimuth angle direction and an elevation angle direction, respectively.
  • the shows US 2006/0114164 A1 an antenna system having a first planar active subsystem for receiving / transmitting an RF signal of a particular linear polarization direction and for selectively performing electronic scanning.
  • a second subsystem coupled to the active first subsystem and operable for rotational movement of the active subsystem about a first axis perpendicular to a plane defined by the planar active subsystem.
  • a third elevation subsystem coupled to the second subsystem and a fourth azimuth subsystem enables rotational movement of the first planar subsystem about the central axis.
  • the elevation subsystem can be configured such that the first planar active subsystem can be positioned relative to a target in such a way that the linear polarization direction of the planar active subsystem substantially corresponds to the polarization direction of a received / transmitted RF radiation.
  • the positioning system for an antenna aperture, in particular a low-profile antenna, a bracket, on which the antenna aperture along a first axis is rotatably mounted.
  • the bracket is in turn attached to a second axis in a second pivot bearing, which is rotatably mounted on a third axis on a positioning platform.
  • the positioner platform itself is mounted in the vehicle or the third pivot bearing is rigidly connected to the vehicle.
  • the described positioning system is used in an antenna system with a first and a second antenna, at least one of which has a positioning system described above and which use a common positioning platform. This only insignificantly more space is required because both antennas can be mounted under a common radome.
  • maximum flexibility is maintained for both antennas, which opens up numerous fields of application.
  • the three axes A, B, C of the positioning system form one of the antennas, advantageously both antennas, then a complete orthogonal system that allows the antenna aperture 1 to be aimed at a target antenna, even in a space limited in its height align.
  • the rotatable bracket allows movement about the second axis and provides spacing of the antenna aperture from the positioner platform so that its movement about the second axis through the position platform can be unrestrained.
  • the bracket for attaching the antenna aperture may be two-armed or comprise only one arm, which then attaches more to the geometric center or the center of mass of the antenna aperture.
  • the first axis to the second axis, and the second axis to the third axis at an oblique angle, ie are from the right Angular deviating.
  • the oblique arrangement of the axes is the preferred case for general installation space volumes.
  • a right-angled arrangement is more of a special case.
  • most space volumes of aircraft antennas are at least piecewise cylindrical (then preferably right-angled arrangement of the axes).
  • skew-angled arrangements are typically used in sphere volume or sphere section volume. This is usually due to the fact that the system can then be better balanced in terms of weight.
  • the 3-axes of a positioning system according to the invention do not correspond to the generic azimuth, elevation and antenna beam axes ("skew axes").
  • the generic axes can be recovered by a unitary transformation.
  • the angular adjustments with respect to the three axes of the positioning system according to the invention from the generic azimuth, elevation and skew angles clearly result from a corresponding unitary rotation in 3-dimensional space.
  • this transformation is easier to do, but angles different from one another in a perpendicular arrangement of the axes can also be taken into account in order to achieve a better mass balance.
  • the attachment of the antenna aperture with the bracket takes place on two opposite sides of the antenna aperture.
  • the hanger has two arms. This allows the antenna aperture between the arms of the arms to spin without continuing to apply in height. This is particularly the case when the attachment of the antenna aperture to the Narrow sides takes place via a respective first pivot bearing and is driven for example via a direct drive.
  • a holder secures the second rotary bearing to a third rotary bearing and the third rotary bearing is arranged on the positioning platform. This gives the antenna aperture a sufficient height above the positioner platform to make slight pivotal movements about the second axis. It is helpful if the antenna aperture has an oval or stepped oval shape, preferably with a height to width ratio of 1: ⁇ 4.
  • the overall height can be reduced further if a third drive is arranged perpendicular to the positioning platform and drives the third pivot bearing via a toothed ring arranged below the positioning platform.
  • the antenna is then covered by a radome, which has a bowl shape and builds up in operation only low aerodynamic resistances.
  • a rotational movement about the first axis and / or a rotational movement of the bracket on the second axis can be performed by means of a linear actuator.
  • a substantially centrally arranged high-frequency rotary feedthrough is integrated, which conducts high-frequency signals from and to the antenna aperture, preferably for two high-frequency channels. This supports the full 360 ° rotation of this pivot bearing.
  • the high-frequency rotary feedthrough integrated into the third rotary bearing can thus also more easily encapsulated and well protected against moisture ingress.
  • two or more separate slip ring pairs for the power supply of the drives of the other moving parts and for control purposes are preferably integrated into the third pivot bearing.
  • Flexible coaxial conductors are suitable for the other high-frequency connections to the antenna aperture, since typically the second rotary bearing and the first rotary bearing execute only very limited rotations and the flexible coaxial conductors can easily follow these movements.
  • the two antennas can advantageously develop the following application scenarios.
  • Either the first antenna in the Ka band and the second antenna in the Ku band can be operated.
  • the preferred one can be selected.
  • the other antenna then has no function in operation and only rotates with.
  • both antennas are operated parallel to each other in the same frequency band, so for example in Ka-band or Ku-band or X-band.
  • Ka-band or Ku-band or X-band In most positions of the aircraft from equator to northern latitudes of 48 ° the elevation angle of the antenna to a geostationary satellite near the equator is only up to 30 °.
  • both antennas can simultaneously on the Align satellites and operate in parallel. This improves the signal-to-noise ratio and the transmitted data rate can be increased.
  • Another advantageous use of the antenna system relates to a synchronization of both antennas.
  • a symmetrical arrangement of both antennas about the third axis of rotation brings a synchronous movement of both antennas also around the first and second rotation axis (so-called butterfly operation) additionally the advantage that no additional angular momentum act on the antenna system and forces on the engine and transmission are minimized.
  • FIG. 3 shows the front view of the antenna aperture 1 at an elevation angle 0 ° and a typical movement volume limitation by a radome 18th
  • FIG. 4 shows how by a mechanical restriction, such as a stop 21, the angular range of rotation about the second axis can be limited, so that the antenna aperture 1 does not leave the movement volume.
  • Figures 5 to 8 show different alignment scenarios, which show that the movement of the positioning system can be realized in a very small volume of movement.
  • the orientation of the aperture in FIG. 5 represents, for example, a situation in which the antenna is located below the equator, but the longitude of the position of the antenna and that of the target satellite is different.
  • the antenna aperture can not be parallel to its long axis Equator will be aligned, but only with its narrow axis.
  • the main antenna beam is then very wide and there are typically several satellites in the beam.
  • the antenna When received, the antenna then receives the signals from several satellites simultaneously resulting in undesirable interference and significant degradation of the signal from the target satellite.
  • the transmission power typically the transmission power must be greatly reduced, because otherwise neighboring satellites of the target satellite would be irradiated, which is not allowed by regulation.
  • the antenna aperture optimally, namely aligned with its long axis parallel to the equator.
  • the elevation angle of the satellite then corresponds here to the angle about the second axis B (about 20 °) and no longer the angle about the first axis A, which is then 90 ° here.
  • the azimuth angle of the target satellite in this special case corresponds to the angle about the third axis C.
  • FIGS. 6 to 8 For example, further alignment possibilities are shown, which can all be realized within the same installation space.
  • ⁇ ', ⁇ ' and ⁇ can be chosen so that the angle forming the long main axis of the antenna aperture and the tangent to the geostationary orbit at the location of the target satellite is minimized. This always ensures that the antenna aperture is optimally aligned with respect to its antenna pattern under the boundary condition of the limited movement volume on the target satellites.
  • Such arrangements can the available volume of movement z. For example, if it is not a simple cylinder volume (that is, for example, a truncated cone volume, an ellipsoidal volume of revolution, or a volume with constrictions), it will make even better use. Also, to minimize the moment of inertia, i. To minimize the dynamic load of the axles during operation, be more favorable if the movement planes are not perpendicular to each other. The coordinate system that can be assigned to the axes is then skew-angled. The arrangement works as long as the vectors forming the coordinate system are linearly independent of each other in three-dimensional space.
  • Such a positioning system is then characterized by having three axes which are arranged such that an antenna aperture is mounted on a first axis which lies in a plane which is perpendicular to the main beam direction and can be rotated about this axis, the first axis is attached to a second axis, the second axis is attached to a third axis, and the axes are interconnected such that the plane passing through the second axis when rotating about the first axis and the plane passing through the first axis Axis, when rotated about the second axis, passes through an angle that is non-zero, and the plane that passes through the second axis when rotating about the third axis, and the plane that passes through the third axis when rotated about the second axis forms an angle, which is not null.
  • the antenna aperture 1 is on two opposite narrow sides, each with a first pivot bearing 2 on a U-shaped, substantially centered (for apertures with an inhomogeneous mass distribution, the bracket may be slightly different from the geometric center, but in terms of mass due to the weighting mounted centrally) mounted bracket 3 with two arms attached.
  • the stator of the pivot bearing 2 is located in each case on the bracket 3 and the rotor on the respective side of the antenna aperture 1 (not shown separately), so that the antenna aperture 1 about the first axis, which passes through the two first pivot bearing 2 in the bracket. 3 can be turned. Since at the in FIG. 9 shown flat antenna aperture, the main beam direction is perpendicular to the aperture surface (aperture plane), the first axis lies in a plane which is perpendicular to the main beam direction.
  • the bracket 3 is attached to the side which does not intersect the first axis, with a second pivot bearing 4 to a holder 5, wherein the rotor of the second pivot bearing 4 on the bracket 3 and the stator is on the holder 5 (not shown separately ).
  • the holder 5 is fixed by means of a Positionierer disorder 6 on the rotor of a third pivot bearing 7.
  • the stator of the third pivot bearing 7 is typically rigidly connected to the structure of the mobile carrier of the antenna system.
  • the third pivot bearing 7 is designed so that it has an opening in the middle, in which high-frequency rotary unions and slip ring rotary unions can be accommodated.
  • FIG. 10 exemplifies a structure of such a third, encapsulated pivot bearing 7 in cross section.
  • the third pivot bearing 7 consists of a stator 12 and a rotor 10, which are connected by a bearing 11.
  • the bearing 11 may e.g. be designed as a polymer bearing, ball bearings, or needle roller bearings.
  • a high frequency rotary leadthrough 8 is mounted in the rotation axis of the rotary bearing 7.
  • the stator of the high-frequency rotary leadthrough 8 with its terminals 8b (here, for example, with two channels) is connected to the stator 12 of the rotary bearing 7.
  • the rotor of the high-frequency rotary feedthrough 8 with its connections 8a is connected to the rotor 10 of the rotary bearing 7.
  • slip rings 9a, 9b with their connections for the power supply and control of the drives are provided in the center of the rotary bearing 7, the connections 9a to the rotor 10 and the connections 9b to the stator 12 of the rotary feedthrough 7.
  • Abrasive bodies 13 thereby ensure a galvanic contact between the terminals of the rotor 10 and those of the stator 12.
  • each channel is split into 2 subchannels. Thus, only half of the current flows through the (critical) grinding bodies. Often a decomposition in> 2 sub-channels is made.
  • the signal is also routed via the slip rings.
  • typical slip ring configurations have approx. 8 - 32 channels. Of these, about 4 - 6 are for the power supply, often one for the ground connection extra, and the rest for control purposes.
  • the three axes of the positioning system are each equipped with a motor drive, so that the angle of inclination about the axes are set separately for each axis can.
  • the motors are preferably electric motors, in particular brushless electric motors.
  • the drive for rotation about the third axis is preferably mounted on the Positionierwhere 6, as this makes the most efficient use of space, and equipped with a gear that allows a very precise alignment.
  • the drive 15 for rotation about the third axis is advantageously mounted vertically on the positioning platform 6 and its gear meshes with a ring gear 19 (see FIG FIG. 3 ) located on the underside of the positioning platform 6.
  • This arrangement has the advantage that by appropriate design of the ring gear 19 very high angular resolutions can be achieved.
  • a drive motor can be coupled directly with a resolver (angular resolution sensor) in a compact design.
  • the drive 16 for rotation about the second axis can be designed as a direct drive "direct drive”. That no gear is required here because the axle can be driven directly.
  • a drive motor 17 for rotation about the first axis may be mounted in or on the bracket.
  • a belt transmission or a rod transmission for driving the first axis.
  • a direct drive can be used.
  • linear actuators 14 can also be used for rotation about the second and first axes. This is schematically in FIG. 12 shown.
  • the lifting body of the linear actuator 14 is attached to the bracket 3, the base on the Positioniermann 6.
  • the angular position of the bracket 3 about the second axis B can be easily adjusted. Since in typical arrangements, the angular range about the second axis B is only up to ⁇ 20 °, no motor with gear is required. This represents a great simplification of the arrangement.
  • the angular position about the first axis can be accomplished with a linear actuator. Again, the required angular range in typical arrangements is only 0 ° to 90 °. Also, arrangements with multiple actuators for each axis are conceivable.
  • FIG. 13 shows an inventive antenna system with a first antenna 31 and a second antenna 32, which use a common positioning platform 6.
  • the positioning systems of both antennas 31, 32 are preferably according to the variants of the FIGS. 2 to 12 designed. However, both antennas 31, 32 need not be identical. So it is also possible to use other positioning mechanisms, eg as in FIG. 1 , However, care should be taken that the weight and arrangement of the antennas are chosen so that there is no imbalance when the positioning platform 6 moves about the third axis.
  • the antennas can be designed with respect to their aperture for the same frequency band, in particular X-band, Ka-band or Ku-band.
  • the dimensioning of the aperture is for example in WO2010 / 124867A1 and WO2014 / 005699A1 described.
  • both antennas 31, 32 can be aligned and operated in parallel with the satellite.
  • the signal currents via both antennas 31, 32 are then combined in a transceiver, not shown, in the case of reception and divided in the transmission case.
  • the first antenna in the Ka band and the second antenna in the Ku band can be operated.
  • the antennas which are different in terms of the aperture are preferably matched to one another in terms of weight and weight distribution.
  • both antennas 31, 32 In the desired symmetrical arrangement with respect to weight and center of gravity of both antennas 31, 32 about the third axis of rotation brings a synchronous movement of both antennas 31, 32 also around the first and second axis of rotation (so-called butterfly operation) additional advantages. Regardless of whether both antennas 31, 32 are in operation, hangers and pivot bearings for the first and second axes of rotation of both antennas 31, 32 substantially synchronously. This minimizes the load on the engine and transmission.

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

Claims (15)

  1. Système d'antennes comprenant une première et une deuxième antenne (31, 32) qui comportent chacune un système de positionnement, le système de positionnement étant conçu pour une ouverture d'antenne respective (1) telle sorte que
    • l'ouverture d'antenne (1) est fixée sur un étrier (3) de manière à pouvoir tourner le long d'un premier axe (A),
    • l'étrier (3) est fixé à un deuxième axe (B) au niveau d'un deuxième palier de rotation (4), et le deuxième palier de rotation (4) du système de positionnement étant pourvu d'au moins une butée (21) qui limite à moins de +/- 90° la plage angulaire du mouvement de rotation de l'étrier (3) sur le deuxième axe (B) à la manière d'une borne mécanique,
    • le deuxième palier de rotation (4) est monté sur une plate-forme de positionnement (6) de manière à pouvoir tourner sur un troisième axe (C),
    les deux systèmes de positionnement utilisant une plateforme de positionnement commune (6), et
    le premier axe (A) du système de positionnement formant par rapport au deuxième axe (B), et le deuxième axe (B) formant par rapport au troisième axe (C), un angle oblique s'écartant de la verticale.
  2. Système d'antennes selon la revendication 1, dans lequel le premier axe (A) du système de positionnement est situé dans un plan qui est perpendiculaire à une direction de faisceau principale.
  3. Système d'antennes selon la revendication 1 ou 2, dans lequel le plan du système de positionnement, qui passe par le premier axe (A) lors de la rotation autour du deuxième axe (B), est perpendiculaire au deuxième axe (B), et le deuxième axe (B) est monté sur un troisième axe (C) de telle sorte que le plan, qui passe par le deuxième axe (B) lors d'une rotation autour du troisième axe (C), est perpendiculaire au troisième axe (C) .
  4. Système d'antennes selon l'une des revendications précédentes, dans lequel la fixation de l'ouverture d'antenne (1) du système de positionnement à l'étrier (3) est effectuée sur deux côtés opposés de l'ouverture d'antennes (1).
  5. Système d'antennes selon la revendication 4, dans lequel la fixation de l'ouverture d'antenne (1) du système de positionnement est effectuée sur ses petits côtés à chaque fois par le biais d'un premier palier de rotation (2).
  6. Système d'antennes selon l'une quelconque des revendications précédentes, dans lequel un support (5) du système de positionnement fixe le deuxième palier de rotation (4) à un troisième palier de rotation (7) et le troisième palier de rotation est disposé sur la plate-forme de positionnement (6).
  7. Système d'antennes selon la revendication 6, dans lequel un troisième entraînement (15) du système de positionnement est disposé perpendiculairement à la plate-forme de positionnement (6) et entraîne le troisième palier de rotation (7) par le biais d'une couronne dentée (19) disposée au-dessous de la plate-forme de positionnement (6).
  8. Système d'antennes selon l'une des revendications précédentes, dans lequel l'ouverture d'antenne (1) du système de positionnement a une forme ovale ou une forme ovalisée de manière étagée.
  9. Système d'antennes selon l'une des revendications précédentes, dans lequel le mouvement de rotation de l'étrier (3) sur le deuxième axe (B) est limité à moins de +/- 45°, de préférence moins de +/- 20°.
  10. Système d'antennes selon l'une des revendications précédentes, dans lequel un mouvement de rotation de l'ouverture d'antenne (1) du système de positionnement autour du premier axe (A) et/ou un mouvement de rotation de l'étrier (3) sur le deuxième axe (B) est réalisé au moyen d'un actionneur linéaire (14).
  11. Système d'antennes selon l'une des revendications précédentes, dans lequel la rotation de l'ouverture d'antenne (1) du système de positionnement dans le premier palier de rotation (2) et/ou dans le deuxième palier de rotation (4) est entraînée par un entraînement direct (17, 16).
  12. Système d'antennes selon l'une des revendications précédentes, dans lequel au moins le troisième palier de rotation (7) du système de positionnement est pourvu sensiblement au centre d'un passage tournant à haute fréquence (8) qui transmet des signaux à hautes fréquences vers et depuis l'ouverture d'antenne (1), lesquels alimentent de préférence deux canaux à hautes fréquences.
  13. Système d'antennes selon la revendication 12, dans lequel le troisième palier de rotation (7) du système de positionnement comprend au moins deux paires de bagues collectrices séparées (9a, 9b) et assure l'alimentation en courant et/ou la commande d'entraînements des premier et deuxième paliers de rotation (2, 4) .
  14. Système d'antennes selon l'une des revendications précédentes, dans lequel une transmission de signaux à hautes fréquences de l'ouverture d'antenne (1) du système de positionnement à un passage tournant à hautes fréquences (8) est effectuée dans le troisième palier de rotation (7) par des conducteurs coaxiaux flexibles.
  15. Système d'antennes selon la revendication 1, dans lequel la première antenne (31) est utilisée dans la bande Ka et la deuxième antenne (32) est utilisée dans la bande Ku ou les deux antennes (31, 32) sont utilisées dans la bande Ka ou la bande Ku.
EP17158712.4A 2015-02-06 2016-01-21 Système d'antennes comprenant deux antennes Active EP3203580B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102015101721.0A DE102015101721A1 (de) 2015-02-06 2015-02-06 Positionierungssystem für Antennen
EP16152165.3A EP3054529B1 (fr) 2015-02-06 2016-01-21 Systeme de positionnement pour antennes et systeme d'antennes

Related Parent Applications (2)

Application Number Title Priority Date Filing Date
EP16152165.3A Division EP3054529B1 (fr) 2015-02-06 2016-01-21 Systeme de positionnement pour antennes et systeme d'antennes
EP16152165.3A Division-Into EP3054529B1 (fr) 2015-02-06 2016-01-21 Systeme de positionnement pour antennes et systeme d'antennes

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EP3203580A1 EP3203580A1 (fr) 2017-08-09
EP3203580B1 true EP3203580B1 (fr) 2018-09-26

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EP16152165.3A Active EP3054529B1 (fr) 2015-02-06 2016-01-21 Systeme de positionnement pour antennes et systeme d'antennes
EP17158712.4A Active EP3203580B1 (fr) 2015-02-06 2016-01-21 Système d'antennes comprenant deux antennes

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US (1) US10290937B2 (fr)
EP (2) EP3054529B1 (fr)
CN (1) CN105870571B (fr)
DE (1) DE102015101721A1 (fr)
ES (1) ES2729653T3 (fr)

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JP6760825B2 (ja) * 2016-11-11 2020-09-23 三菱重工業株式会社 レーダ装置及び航空機
DE102017112552A1 (de) 2017-06-07 2018-12-13 Lisa Dräxlmaier GmbH Antenne mit mehreren einzelstrahlern
CN107425256B (zh) * 2017-07-04 2020-01-14 上海宇航系统工程研究所 一种星载抛物面天线高定位精度展开锁位机构
CN107819196B (zh) * 2017-09-25 2020-05-29 上海卫星工程研究所 带性能约束的三维指向对地数传天线布局系统
FR3079281B1 (fr) * 2018-03-22 2020-03-20 Thales Dispositif de positionnement
CN112298056B (zh) * 2020-10-12 2024-03-15 长春通视光电技术股份有限公司 一种车载雷达俯仰角度摆动机构
FR3130124B1 (fr) * 2021-12-09 2023-12-08 Univ Franche Comte Dispositif d’orientation

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CN105870571B (zh) 2020-09-25
CN105870571A (zh) 2016-08-17
ES2729653T3 (es) 2019-11-05
EP3203580A1 (fr) 2017-08-09
US10290937B2 (en) 2019-05-14
EP3054529A1 (fr) 2016-08-10
US20160233579A1 (en) 2016-08-11
EP3054529B1 (fr) 2019-04-17
DE102015101721A1 (de) 2016-08-11

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