WO1998040761A1 - Systeme de poursuite de satellite - Google Patents

Systeme de poursuite de satellite Download PDF

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Publication number
WO1998040761A1
WO1998040761A1 PCT/IL1997/000091 IL9700091W WO9840761A1 WO 1998040761 A1 WO1998040761 A1 WO 1998040761A1 IL 9700091 W IL9700091 W IL 9700091W WO 9840761 A1 WO9840761 A1 WO 9840761A1
Authority
WO
WIPO (PCT)
Prior art keywords
antenna
plate
actuators
satellite
pointing device
Prior art date
Application number
PCT/IL1997/000091
Other languages
English (en)
Inventor
Israel Koffman
Ervin Rozman
Guy Naym
Nathan Levy
Original Assignee
Orbit Communications, Tracking And Telemetry Ltd.
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Orbit Communications, Tracking And Telemetry Ltd. filed Critical Orbit Communications, Tracking And Telemetry Ltd.
Priority to AU22288/97A priority Critical patent/AU2228897A/en
Priority to PCT/IL1997/000091 priority patent/WO1998040761A1/fr
Publication of WO1998040761A1 publication Critical patent/WO1998040761A1/fr

Links

Classifications

    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S3/00—Direction-finders for determining the direction from which infrasonic, sonic, ultrasonic, or electromagnetic waves, or particle emission, not having a directional significance, are being received
    • G01S3/02—Direction-finders for determining the direction from which infrasonic, sonic, ultrasonic, or electromagnetic waves, or particle emission, not having a directional significance, are being received using radio waves
    • G01S3/14—Systems for determining direction or deviation from predetermined direction
    • G01S3/38—Systems for determining direction or deviation from predetermined direction using adjustment of real or effective orientation of directivity characteristic of an antenna or an antenna system to give a desired condition of signal derived from that antenna or antenna system, e.g. to give a maximum or minimum signal
    • G01S3/42—Systems for determining direction or deviation from predetermined direction using adjustment of real or effective orientation of directivity characteristic of an antenna or an antenna system to give a desired condition of signal derived from that antenna or antenna system, e.g. to give a maximum or minimum signal the desired condition being maintained automatically
    • 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
    • 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

Definitions

  • the present invention concerns systems for pointing an antenna in a desired spatial direction.
  • the invention relates in particular to such systems in which the desired direction changes as a result of transmitter movement or of the rotation of the antenna platform, and the antenna direction is defined using a plurality of linear actuators of controlled length.
  • antenna positioners are used to direct an antenna in any desired spatial angle. It is required to control the antenna angle in three degrees of freedom, that is two spatial angles to direct the antenna toward the transmitter, and an additional angle for polarity, that is to adjust the polarity of the receiving antenna to that of the transmitted signal.
  • a typical positioner as known in the art includes three gearmotors, to control the azimuth, elevation and roll angle respectively.
  • Such a system has a singularity point at 90 degrees, that is when the antenna points upwards. In this case, the azimuth and roll controls coincide. Moreover, the azimuth suddenly changes by 180 degrees, this increasing the complexity of the angle control.
  • slip rings When using slip rings, there is no problem with cables and unlimited rotation of the antenna is possible, however slip rings are unreliable with the contacts quality suffering at times, and the cost is higher.
  • Still another problem with positioners known in the art relates to the requirement for a plurality of cables between the satellite receiver and the antenna. Since these units are located at separate locations, a multitude of cables has to be installed, with detrimental effects on cost and reliability.
  • Hexapod or Stewart platforms are known in the art, however these devices were not used as part of a satellite tracking system to achieve the benefits detailed in the present invention.
  • ZEISS JENA GMBH CARL, DE 29607680 details an arrangement for reducing danger of crash with universal positioning systems, e.g. hexapod or Stewart platforms - has hinges arranged on object carrier and main carrier so as to allow same degree of angular movement in any direction.
  • PAUSCH K. et al., DE 4241680 discloses a mounting with support ring to which are cardan linked six legs - has base frame, especially for telescope.
  • SMUTNY B., DE 41 17538, details an aligning support for antennae or telescopes especially for satellites - has hexapod frame with telescopic legs adjustable by piezoelectric linear motors.
  • ANONYMOUS, RD 328020 discloses an impedance controlled work surface for automated assembly machine - is on six independently controllable legs and supports force sensor and mechanical gripper.
  • KIRKHAM E. E. et al., US 5028180 discloses a six-axis machine tool for locating operator - has six leg members joined at spaced points to supports with appts. for manipulating leg members.
  • KIRKHAM E. C. et al., US 4988244 details a six-axis machine tool - has spaced platforms joined by six powered and extensible legs joined by universal joints.
  • JOHNSTON E C et al., GB 2201293 and GB 2201293 disclose an aerial sub-reflector mounting structure - has six legs of tripod, bipod and monopod with each leg provided with two threaded bars joined by bottle screws Disclosure of Invention
  • the object is basically accomplished by using a plurality of linear actuators, mounted between a first plate holding the antenna and a second plate which is secured to a fixed base, so that controlling the individual length of each actuator achieves the relative spatial angle between the first and the second plates.
  • a third object of the invention is to provide for a low cost and reliable system. This is accomplished using an outdoor unit close to the antenna and an indoor unit close to the satellite receiver, with a cable carrying multiplexed signals therebetween.
  • Fig. 1 depicts a satellite receiving antenna mounted on a pointing device using linear actuators.
  • Fig. 2 depicts a side view of the antenna and pointing device.
  • Fig. 3 is a perspective view of a pointing device using six linear actuators.
  • Fig. 4 is a front view of the pointing device.
  • Fig. 5 details the structure of the linear actuator.
  • Fig. 6 is a perspective view of a pointing device using four active linear actuators.
  • Fig. 7 depicts a pointing device using two stages of a pointing device with linear actuators.
  • Fig. 8 illustrates a satellite tracking system using the pointing device and a pair of indoor/outdoor controllers.
  • Fig. 1 depicts a satellite receiving antenna 1 mounted on a pointing device 2 using linear actuators 21 , 22, 23, 24.
  • the antenna 1 includes a parabolic reflector 11 with a feeder 12 located at its focus, so as to create a directional antenna pattern.
  • the antenna axis (not shown) is the axis of the parabola defining reflector 11 , and corresponds to the direction of the maximum received energy. It is a purpose of the present invention to keep the antenna axis directed toward a satellite.
  • the electromagnetic waves illuminating aperture 11 are reflected and focused on feeder 12. This is the RF received signal.
  • Antenna reflector 11 is fixedly attached to antenna base plate 14.
  • Feeder support 13 is used to attach feeder 12 to antenna base plate 14, while keeping feeder 12 at its desired location with respect to reflector 11 .
  • Support 13 also includes means (not shown) for transferring the received RF signal to unit 3, and thence to the satellite receiver (not shown), through cable 4.
  • These means for signal transfer may include a (not shown) RF cable or a waveguide.
  • the pointing device 2 includes six actuators, of which the actuators 21 , 22, 23, 24, are illustrated.
  • the actuators are located between fixed plate 28 and antenna base plate 14. By controlling the length of each actuator, as detailed below, it is possible to control the spatial angle of plate 14 with respect to plate 28, thus to control the angle of the antenna 1 .
  • pointing device 2 uses the Stewart platform for antenna 1 pointing in the desired direction.
  • the Steward platform previously used for moving a platform in six degrees of freedom, is used, according to the present invention, to point a receiving antenna in a desired direction, together with electronic tracking means to be detailed below.
  • the outdoor control unit 3 includes the electronics to control the movement of the actuators 21 , 22, 23, 24, and to couple the received RF energy to outdoor coax cable 4.
  • Unit 3 is connected to each of the linear actuators 21 , 22, 23, 24 with (not shown) electrical wires, and to antenna feeder 12 with (not shown) RF cable or waveguide.
  • a low noise amplifier (not shown) may be located in unit 3 or close to the feeder 12.
  • unit 3 is mounted on plate 14. This has the advantage that only one cable (cable 4) has to be connected to the moving antenna 1.
  • unit 3 is mounted on fixed plate 28. This has the advantage that a lower load is placed upon the actuators 21 , 22, 23, 24, since the weight of unit 3 is excluded. The disadvantage is that RF and electrical power cables have to be connected to the antenna 1 .
  • the whole pointing device 2 is enclosed in a flexible or soft cover (not shown) , to keep the actuators 21 , 22, 23, 24 which are located inside clean and dry, while the antenna 1 is located outdoors, possibly in adverse weather.
  • antenna 1 includes parabolic reflector 11 and feeder 12.
  • the feeder support 13 is used to attach feeder 12 to antenna base plate 14.
  • LNA Low Noise Amplifier
  • SNR Signal to Noise Ratio
  • RF cable 16 (or a flexible waveguide) transfers the RF received signal to unit 3 located on fixed plate 28.
  • Antenna reflector 11 is attached to plate 14 using antenna support means 142.
  • the pointing device 2 includes six linear actuators, of which actuators 21 , 22, 23 are shown.
  • the rotary joints 212, 222, 232 couple actuators 21 , 22, 23 respectively to fixed plate 28.
  • the rotary joints 213, 223, 233 couple actuators 21 , 22, 23 respectively to antenna base plate 14.
  • the rotary joints 212, 222, 232, 213, 223, 233 allow the angular movement of plate
  • the outdoor control unit 3 is mounted on plate 28, and is connected to the satellite receiver indoors (not shown) through outdoor coax cable 4.
  • Unit 3 couples the RF signal from feeder 12 to cable 4, and applies control signals (not shown) to actuators 21 , 22, 23.
  • Fig. 3 illustrates a pointing device using six linear actuators 21 , 22, 23, 24, 25 and 26.
  • the receiving antenna (not shown) is mounted on antenna base plate 14.
  • the antenna axis 17 is normal to plate 14, or has a fixed spatial angle with respect to plate 14. Thus, controlling the orientation of plate 14 determines the orientation of the antenna.
  • joint 213, 223, 233 couple each a pair of actuators to antenna base plate 14, a total of six actuators. These joints should allow free rotation of each actuator with respect to platform 14.
  • joint 213 couples actuators 21 and 24, joint 223 couples actuators 22 and 25, and joint 233 couples actuators 23 and 26.
  • each of the rotary joints 213, 223, 233 include a first and second joint means (not shown) .
  • the ends of two actuators are coupled together using a first rotary joint, then the common joint is coupled to plate 14 using a second rotary joint.
  • one end of actuators 21 , 22, 23, 24, 25 and 26 is each coupled to plate 14 using a separate rotary joint.
  • rotary joints 212, 222, 232, 242, 252, 262 connect the other end of actuators 21 , 22, 23, 24, 25, 26 respectively to fixed plate 28.
  • the antenna axis 17 By changing the length of each of the six actuators in a coordinated manner, a flexible control of the antenna axis 17 is achieved. That is, the antenna axis (not shown) can be made to point in any desired angle.
  • the present invention provides for pointing an antenna to a satellite (not shown) while the satellite is moving on its orbit around the earth, and/or the antenna is rotating because it is mounted on a moving platform.
  • Fig. 4 illustrates a front view of the pointing device, wherein a receiving antenna (not shown) is mounted on antenna base plate 14.
  • the rotary joints 213, 223, 233, 243, 253, 263 each couple one of the actuators 21 , 22, 23, 24, 25, 26, respectively, to antenna base plate 14.
  • the embodiment illustrated is different embodiment than that previously illustrated with reference to Fig. 3, in that separate rotary joints are used for each actuator to couple to plate 14.
  • rotary joints 212, 222, 232, 242, 252, 262 connect actuators 21 , 22, 23, 24, 25, 26 respectively to fixed plate 28.
  • the orientation of plate 14 with respect to plate 28 is achieved by changing the length of each of the actuators.
  • Fig. 5 details the structure of each of the linear actuators 21 , 22, 23, 24, 25, 26 detailed in Fig. 4 above.
  • the actuator includes two elongated, generally coaxial parts 5 and 6 which move with respect to each other to change the overall length of the actuator, thus to achieve the desired antenna pointing effect.
  • Part 6 includes an elongated hollow part comprising a first part 601 which is outside of part 5, and a second part 602 which is inside part 5.
  • the hollow part is preferably cylindrical, and is shaped so as to extend through opening 53.
  • Opening 53 thus allows the movement of part 6 relative to part 5.
  • the opening 53 optionally includes a sealant layer 533 around its circumference.
  • Sealant layer 533 may include for example rubber or plastic or other elastic material to prevent moisture, dust or gases from entering the device.
  • First part 5 includes a gearmotor 51 (that is, an electrical motor and gear to reduce the angular speed while increasing the angular moment) , and a threaded rod 52 rotated by gearmotor 51 .
  • gearmotor 51 that is, an electrical motor and gear to reduce the angular speed while increasing the angular moment
  • a partially broken away view of part 5 is illustrated, to detail the internal structure of the device.
  • a threaded nut 62 is attached to part 602.
  • the thread on nut 62 corresponds to the thread on threaded rod 52, such that, while nut 62 is rotated relative to rod 52, a linear displacement of nut 62 along rod 52 is achieved.
  • a square sheet 61 is attached to nut 62, with sheet 61 being restrained by the corresponding square cross section of part 5, such that nut 62 and sheet 61 can move along part 5, but cannot rotate therein. This ensures the relative rotation between rod 52 and nut 62, while rod 52 is being rotated.
  • Other means for preventing the rotation of nut 62 may be used, for example a second bar (not shown) running in parallel to bar 62, with a corresponding hole in nut 62, so as to prevent the sliding of nut 62 along that bar, while preventing its rotation.
  • Nut 62 is part of second part 6, thus movement of nut 62 results in the movement of part 6 relative to part 5, while gearmotor 51 rotates rod 52.
  • the direction of rotation of gearmotor 51 defines the change in the actuator, either to increase or to decrease its overall length.
  • a potentiometer 55 is included in part 5, to measure the relative displacement between parts 5 and 6.
  • the potentiometer may include (not shown) an elongated resistance strip attached to part 5, with a moving contact attached to part 6, so that displacement of part 6 results in a varying resistance between one end of the strip and the moving contact, the resistance being indicative of displacement.
  • displacement measurement means may include (not shown) noncontact means, for example electro-optical, inductive or capacitive means. These means may provide improved reliability, which is important for outdoors use.
  • a hook or other coupling means 56 on the free end of part 5, and a similar hook or other coupling means 66 on the free end of part 6, allow to connect the ends of the actuator to the rotary joints as detailed above, to the fixed and/or moving plates in the device.
  • Fig. 6 details another embodiment of a pointing device, using only four active linear actuators.
  • a modified structure is used, which does not have the full six degrees of freedom. These are not required, however, for pointing an antenna in a desired direction.
  • the linear displacement degrees of freedom, which are necessary in robotics or in flight simulators, are not required for the application detailed in the present invention.
  • the antenna (not shown) is mounted on antenna base plate 14, while antenna axis 17 is normal to plate 14, or has a fixed spatial angle with respect to plate 14. Only two pairs of actuators are used, that is actuators 21 and 24, and actuators 23 and 26. The third actuator pair is replaced with a passive, fixed length pole 29. One end of pole 29 is coupled with rotary joint 293 to plate 14, and the other end is fixedly attached to fixed plate 28. Alternately, a rotary joint 292 is used to couple pole 29 to plate 28.
  • antenna axis 17 can be directed in any desired direction within the angular range of the device.
  • the control computations are simplified, since less variables are to be computed. This results in lower cost, lower power consumption faster response. Moreover, less of a mechanical load is placed upon the active actuators, since part of the load is placed on the fixed support 29. It is possible to place support 29 close to the center of gravity of the antenna, so that support 29 bears a considerable portion of the total load.
  • the reliability is also increased, both as a result of the reduction in the number of actuators, and the reduced force acting on each actuator.
  • Fig. 7 depicts an extended range embodiment of the pointing device, according to the present invention. It uses two stages of a pointing device, each using a plurality of linear actuators.
  • Antenna 1 is mounted on antenna base plate 14.
  • Actuators 21 and 24 are one pair of the two pairs of actuators being used.
  • the third actuator pair is replaced with a passive, fixed length pole 29.
  • Actuators 21 and 24 and pole 29 are coupled to an intermediary plate 19.
  • plate 19 is attached to the fixed plate 28 through additional actuators 215 and 245, and pole 295.
  • This structure achieves an extended range of scanning angles, that is double the range of one device.
  • the extended range can be achieved with relatively simple control signals, by using the same control signal for two corresponding actuators, that is actuator 21 and 215, actuator 24 and 245 etc.
  • the poles 29 and 295 are located closer to the center of gravity of antenna 1 , so as to achieve lower loading on the actuators.
  • lower cost actuators can be used, which can generate lower forces.
  • the two stage, stacked pointing device can also be implemented with the six actuator device detailed above with reference to Fig. 3. In that case, however, there are a total of 12 actuators to control, which appears more complicated and higher in cost than the device detailed with reference to Fig. 7
  • Fig. 8 illustrates a satellite tracking system using the pointing device and a pair of indoor/outdoor controllers.
  • Antenna 1 is directional, for maximum received power while the antenna axis points toward a satellite.
  • the pointing device 2 includes actuators (not shown) with mechanical coupling means 202 to antenna 1 , to bring the antenna 1 in the desired direction.
  • Antenna 1 is connected to Low Noise Amplifier (LNA) 15.
  • LNA Low Noise Amplifier
  • Unit 3 includes means (not shown) for coupling the RF signal to cable 4, so as to transfer the RF signal to the indoor control unit 7.
  • the means for RF signal coupling are required since cable 4 concurrently transfers a plurality of electrical signals: the received RF signal is transferred from unit 3 to unit 7, while electrical power voltage and angle setting commands for the antenna 1 are transferred from unit 7 to unit 3.
  • the present invention it is advantageous to transfer all these signals through a common wideband cable 4, since this achieves a lower cost and more reliable system.
  • the cost of components and installation is lower while using just one cable between the outdoor antenna 1 and the indoor unit 7. More so if there is a long distance between these units, for example in high buildings. Fewer cables also increase the reliability, since there are fewer components outside which can malfunction.
  • a plurality of signals are multiplexed to share a common cable 4.
  • Control signals 35 for the actuators are transferred from unit 3 to power drivers unit 33.
  • Unit 3 or unit 33 include optional (not shown) low pass filter means and/or RFI filters to guard the received RF signal in unit 3 from power spikes which may interfere with the signal.
  • Power drivers unit 33 generate the power driving signals 34 having the required power to drive the actuators in unit 2.
  • actuators which extend to the desired length, according to the applied voltage or current.
  • each actuator receives an electrical signal to activate it, and returns a signal (not shown) indicative of the actual length of the actuator. This signal is to be transferred back to unit 3, to allow closing the control loop there.
  • Unit 3 also includes means (not shown) for extracting electrical power from cable 4, and for providing the electrical power line 37 for power drivers unit 33 and the electrical power line 36 for the LNA 15.
  • indoor control unit 7 performs functions complementary to those of the abovedetailed unit 3.
  • unit 7 includes means (not shown) for separating the received RF signal from the antenna 1 and available on cable 4. The RF signal is then transferred to output 71 , to a satellite receiver (not shown) .
  • Unit 7 also includes control means (not shown) for computing the required length of each actuator, for pointing the antenna 1 in the desired direction, means for generating control signals for the actuators accordingly, and for coupling these control signals to cable 4.
  • control means (not shown) for computing the required length of each actuator, for pointing the antenna 1 in the desired direction, means for generating control signals for the actuators accordingly, and for coupling these control signals to cable 4.
  • the controller (not shown) in unit 7 initiates small angular movements of antenna 1 about its normal direction. For each angle, the signal intensity input 72 from the satellite receiver (not shown) is monitored. The antenna 1 is then moved in the direction of the greater received intensity. This performs a form of antenna scanning, to track the satellite.
  • the controller (not shown) in unit 7 defines a different satellite to be tracked, in a new direction.
  • the decision may be based on user commands through input 75, or on a preprogrammed routine, or because of problems in reception with the presently tracked satellite.
  • unit 7 includes means (not shown) for coupling electrical power into cable 4, for the outdoor unit 3. Electrical power is received from a power source through input 77.
  • the electrical power is coupled, using for example low pass filters (not shown), to the cable 4.
  • this is a DC (Direct Current) voltage
  • a low frequency voltage can be used, for example at 50 Hz or 60 Hz or 400 Hz.
  • Analog implementation may use subcarriers, that is a signal at a different frequency for each signal.
  • Digital implementation may use pulses, and may use a common carrier signal at a medium frequency, in the hundreds of kHz to several MHz range. That carrier is modulated with the digital code corresponding to the antenna azimuth, elevation and roll (polarization), or directly indicating the required length for each actuator.
  • the various signals on cable 4 are separated according to their corresponding frequency range: the satellite received signal has a very high frequency, in the GigaHz range, while the control signals are in the MegaHz range, and the power voltage is DC or has a frequency of less than one kiloHz.
  • electrical filters and couplers can be used to add or extract these signals as desired, as known in the art.
  • a low pass filter can be used for the electrical power, a bandpass filter in the MegaHz range for the control signals and a bandpass filter in the GigaHz range for the satellite signal.
  • the status display 74 is used to display information pertaining to the satellite tracking to the user.
  • Optional input (not shown) indicative of undesired platform rotation can be used to correct the angle of antenna 1 with respect to the "fixed" platform for the undesired rotation.
  • Controller 3 performs functions complementary to those of controller 7:
  • a) RF signal from antenna 1 is coupled into cable 4.
  • control signals for the actuators are extracted from cable 4 and are applied to drivers unit 33, to drive the actuators (not shown) accordingly.
  • unit 7 can be a separate unit, or it can be incorporated in the satellite receiver.
  • the computation of the length of each actuator can be computed either in unit 3 or in unit 7.
  • coax cable 4 for example one cable for the received RF, and a second cable for the electrical power and for signals relating to the antenna orientation or received signal strength or the length of each actuator, according to implementation.

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  • Physics & Mathematics (AREA)
  • Engineering & Computer Science (AREA)
  • General Physics & Mathematics (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Variable-Direction Aerials And Aerial Arrays (AREA)

Abstract

Un système de poursuite de satellite destiné à pointer une antenne réceptrice (11) vers un satellite comprend un dispositif de pointage (2), un moyen de commande (3) et un moyen de poursuite (7) de satellite. Le dispositif de pointage (2) comprend une première plaque (40) ainsi qu'une seconde plaque (28) entre lesquelles se trouve une pluralité d'actionneurs linéaires (21, 22, 23, 24) permettant de commander l'angle spatial entre les première et seconde plaques par variation de la longueur de chaque actionneur. La première plaque est fixée sur un point ou sur une base fixe et la seconde plaque est utilisée pour y fixer une antenne directionnelle. Les moyens de commande comprennent un dispositif de calcul de la longueur requise pour chaque actionneur, selon l'orientation voulue de l'antenne. Les moyens de poursuite de satellite comprennent un dispositif déclenchant des mouvements de balayage de l'antenne afin de détecter des écarts angulaires de son axe de réception par rapport à la direction du satellite, et destiné à corriger ces écarts.
PCT/IL1997/000091 1997-03-11 1997-03-11 Systeme de poursuite de satellite WO1998040761A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
AU22288/97A AU2228897A (en) 1997-03-11 1997-03-11 Satellite tracking system
PCT/IL1997/000091 WO1998040761A1 (fr) 1997-03-11 1997-03-11 Systeme de poursuite de satellite

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/IL1997/000091 WO1998040761A1 (fr) 1997-03-11 1997-03-11 Systeme de poursuite de satellite

Publications (1)

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WO1998040761A1 true WO1998040761A1 (fr) 1998-09-17

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Cited By (8)

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WO2001047062A1 (fr) * 1999-12-21 2001-06-28 Robert Bosch Gmbh Dispositif pour regler un systeme a faisceaux
WO2002097920A1 (fr) * 2001-05-31 2002-12-05 In-Snec Procede d'orientation d'une tourelle hexapode
WO2006037953A1 (fr) * 2004-10-02 2006-04-13 Qinetiq Limited Systeme d'antennes compensant une variation des caracteristiques de rayonnement
ES2363393A1 (es) * 2009-06-19 2011-08-02 Electrotecnica Industrial Y Naval, S.L. Seguidor solar.
EP2916386A1 (fr) * 2014-03-07 2015-09-09 Alcatel Lucent Antenne et procédé de fonctionnement d'une antenne
FR3028099A1 (fr) * 2014-10-29 2016-05-06 Thales Sa Dispositif d'orientation d'un element mobile du type plateau d'antenne
CN110970735A (zh) * 2015-09-28 2020-04-07 上海创投机电工程有限公司 一种基于3/6-spu型并联机构天线结构系统
SE2200060A1 (en) * 2022-06-03 2023-12-04 Saab Ab An antenna platform arrangement

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US3293643A (en) * 1963-07-02 1966-12-20 Bofors Ab Fire control system for use on board a ship
US4837576A (en) * 1984-11-16 1989-06-06 Electrospace Systems, Inc. Antenna tracking system
US5089824A (en) * 1988-04-12 1992-02-18 Nippon Steel Corporation Antenna apparatus and attitude control method
US5422648A (en) * 1991-12-10 1995-06-06 Nippon Steel Corporation Receiving antenna apparatus for broadcast by satellite

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Publication number Priority date Publication date Assignee Title
US3134102A (en) * 1958-02-28 1964-05-19 Gen Precision Inc Aircraft doppler measuring system
US3293643A (en) * 1963-07-02 1966-12-20 Bofors Ab Fire control system for use on board a ship
US4837576A (en) * 1984-11-16 1989-06-06 Electrospace Systems, Inc. Antenna tracking system
US5089824A (en) * 1988-04-12 1992-02-18 Nippon Steel Corporation Antenna apparatus and attitude control method
US5422648A (en) * 1991-12-10 1995-06-06 Nippon Steel Corporation Receiving antenna apparatus for broadcast by satellite

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2001047062A1 (fr) * 1999-12-21 2001-06-28 Robert Bosch Gmbh Dispositif pour regler un systeme a faisceaux
US6573860B1 (en) 1999-12-21 2003-06-03 Robert Bosch Gmbh Device for adjusting a beam system
JP2003518609A (ja) * 1999-12-21 2003-06-10 ローベルト ボッシュ ゲゼルシャフト ミット ベシュレンクテル ハフツング 指向性ビームシステムの調節装置
WO2002097920A1 (fr) * 2001-05-31 2002-12-05 In-Snec Procede d'orientation d'une tourelle hexapode
FR2825445A1 (fr) * 2001-05-31 2002-12-06 Innovation Technologie Conseil Procede d'orientation d'une tourelle hexapode
KR100880290B1 (ko) * 2001-05-31 2009-01-23 인-스넥 헥사포드 터렛의 이동판을 변위시키는 방법 및 장치
WO2006037953A1 (fr) * 2004-10-02 2006-04-13 Qinetiq Limited Systeme d'antennes compensant une variation des caracteristiques de rayonnement
US7683845B2 (en) 2004-10-02 2010-03-23 Qinetiq Limited Antenna system compensating a change in radiation characteristics
ES2363393A1 (es) * 2009-06-19 2011-08-02 Electrotecnica Industrial Y Naval, S.L. Seguidor solar.
EP2916386A1 (fr) * 2014-03-07 2015-09-09 Alcatel Lucent Antenne et procédé de fonctionnement d'une antenne
FR3028099A1 (fr) * 2014-10-29 2016-05-06 Thales Sa Dispositif d'orientation d'un element mobile du type plateau d'antenne
WO2016066395A1 (fr) * 2014-10-29 2016-05-06 Thales Dispositif d'orientation d'un élément mobile du type plateau d'antenne
CN110970735A (zh) * 2015-09-28 2020-04-07 上海创投机电工程有限公司 一种基于3/6-spu型并联机构天线结构系统
SE2200060A1 (en) * 2022-06-03 2023-12-04 Saab Ab An antenna platform arrangement
WO2023234842A1 (fr) * 2022-06-03 2023-12-07 Saab Ab Agencement de plateforme d'antenne
SE545795C2 (en) * 2022-06-03 2024-02-06 Saab Ab An antenna platform arrangement

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