EP0043772B1 - Procédé et système d'asservissement d'une plate-forme mobile montée à bord d'un véhicule spatial - Google Patents

Procédé et système d'asservissement d'une plate-forme mobile montée à bord d'un véhicule spatial Download PDF

Info

Publication number
EP0043772B1
EP0043772B1 EP19810401076 EP81401076A EP0043772B1 EP 0043772 B1 EP0043772 B1 EP 0043772B1 EP 19810401076 EP19810401076 EP 19810401076 EP 81401076 A EP81401076 A EP 81401076A EP 0043772 B1 EP0043772 B1 EP 0043772B1
Authority
EP
European Patent Office
Prior art keywords
detector
platform
angular
command
command system
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
Application number
EP19810401076
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0043772A1 (fr
Inventor
Pierre Brunet
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.)
Airbus Group SAS
Original Assignee
Airbus Group SAS
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 Airbus Group SAS filed Critical Airbus Group SAS
Publication of EP0043772A1 publication Critical patent/EP0043772A1/fr
Application granted granted Critical
Publication of EP0043772B1 publication Critical patent/EP0043772B1/fr
Expired legal-status Critical Current

Links

Images

Classifications

    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/27—Adaptation for use in or on movable bodies
    • H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
    • H01Q1/288—Satellite antennas
    • 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
    • H01Q1/18—Means for stabilising antennas on an unstable platform

Definitions

  • the present invention relates to systems for orienting a mobile platform mounted on board a spacecraft.
  • the reflector generally has a window allowing waves to pass from the earth to the infrared detector, but this distorts the radioelectric beam reflected by the reflector and affects the accuracy of the terrestrial detector.
  • the axis of the beam reflected by the plane mirror has a rotation twice that of said mirror, which is only an approximation in the case of the parabolic reflector.
  • the present invention relates to a method and a device for controlling a mobile platform carrying an antenna or any other system, said method guaranteeing an autonomous control on board the satellite, independent of an external reference.
  • the invention thus proposes a control method for the orientation in space of a mobile platform pivotally mounted around at least one axis on a spacecraft, according to which a torque is exerted on said platform. pivoting as a function of a control command around said axes from said vehicle so as to control in orientation said platform relative to a reference mark by maintaining said platform in a predetermined reference orientation relative to this reference, characterized in that this reference reference is linked to the spacecraft and that this setpoint orientation is adjusted as a function of an external command, determined by reference to an external target, said servo command covering a range wider reference than said external control.
  • the platform orientation system is provided with position detectors.
  • the detectors can be placed along any two axes of rotation of the platform, but it is advantageous to choose the two axes along which the actuators act, as described in the aforementioned patent No. 79.05283.
  • Control of the actuators from the position detectors guarantees a very rapid response to the platform.
  • the platform remains fixed relative to the satellite, in the absence of torque or external force.
  • the method has the advantage of autonomously countering the most brutal disturbances encountered on board satellites, that is to say the effects on the platform of the linear accelerations of the satellite.
  • control loop can be a high gain loop because it does not include detectors specific to the satellite, such as terrestrial detectors for example which generally have the double disadvantage of having a recovery time. relatively long and a fairly low signal-to-noise ratio.
  • detectors specific to the satellite such as terrestrial detectors for example which generally have the double disadvantage of having a recovery time. relatively long and a fairly low signal-to-noise ratio.
  • Detections can be linear or angular. For example, it is possible to use detectors based on the principle of differential transformers which are very fast and very little noise, or detectors based on the use of eddy currents, or detectors with an optical principle, or even capacitive detectors.
  • this broadband device will be called the primary device.
  • the autonomy of the primary device which, as noted, does not use any detector aimed at a target external to the satellite, is advantageous because the satellite can undergo a brief cut in connection with the ground without the servo-control of the platform is cut, that is to say that the platform is never in free oscillations, not damped, around its flexible support, which is an improvement of the device proposed in the aforementioned patents N ° 79.05 283 and No. 79.15 593.
  • this deflection can vary over time, according to the information of any detector, for example due to the angular movements of the satellite relative to the target, for example relative to the geocentric direction.
  • the pointing of the platform is then enslaved to the target by a secondary loop servo-control, said loop having a narrower pass band than the primary device.
  • One possibility is to use the information provided by a detector carried by the satellite, a terrestrial detector or any other detector.
  • the low bandwidth of the secondary loop sufficient to compensate for the slow deflections of the satellite, has the advantage of accommodating the possible delay and / or noise of the detector.
  • the mobile platform supports the whole of the pointing device, for example the whole of an antenna and not only the reflector
  • an advantageous possibility is to use for the secondary loop a detector placed on the platform itself.
  • the detector can be of the radiofrequency, infrared or any other type.
  • a stabilization device simply using the information of the mobile platform, that is to say the signals of the position detectors, and possibly the signals of the speed detectors of the platform. -form and signals from the detector mounted on the platform.
  • the external control comes from a particular detector which is the position detector of another platform.
  • the secondary loop then realizes a slave platform, obeying the commands of the master platform.
  • the two platforms then remain pointed in one or two directions independently of the movements of the satellite. It is also possible to add an offset in the secondary loop of the slave platform to control a depointing with respect to the master platform.
  • the device will have advantageous applications for communication or television satellites with multiple antennas, in particular for transmitting over a determined area, from terrestrial transmitters whose location may vary, or even for transmitting on a mobile receiving target by report to the terrestrial transmitter.
  • the devices are designed redundantly. They therefore always include at least two primary detectors and / or two secondary detectors.
  • the actuators and the control electronics of the primary device are also at least doubled.
  • the output of the network 3 supplies a signal to a power stage 4 which can, for example, be a current amplifier, that is to say a device which transforms a voltage into current with a determined gain, characterized in output amps by input volts.
  • the power stage 4 attacks the coil (s) 5 of a linear actuator composed of one or more coils moving in the air gap of a magnetic circuit 6 carried by the mobile platform around a flexible pivot 7
  • An external control 8 can be added via the secondary circuit 9 composed of a filter adapted to the control used.
  • the assembly is designed redundantly, that is to say that it comprises at least two primary detectors 2 and 2a and two actuators 5 and 5a, 6 and 6a, as well as two chains 3, 4, 9, 8 and 3a, 4a, 9a, 8a.
  • FIG. 2 diagrams the circuit where the external control 9 comes from a detector 10, placed on the satellite 11.
  • the antenna consists of a movable reflector 12 carried by the platform 15 and d 'a radiofrequency source 13 carried by the satellite.
  • the detector 10 can be a terrestrial detector, or a solar detector or even a star detector, the transmitting antenna composed of the reflector 12, and the horn 13 can be adapted to serve, in addition, as a radiofrequency detector whose signal can be used as an external signal for the secondary loop.
  • the antenna 12,13,14 is fully mounted on the mobile platform 15.
  • the antenna 14 can be replaced by any other device which must be finely pointed, for example a radiometer, an image-taking device or even a scientific measurement device.
  • the detector 17 which can be a terrestrial detector or a radiofrequency deviation detector, is placed on the mobile platform 15. This supports the antenna assembly composed of a tower 18, a transmitter or receiver 13 and a reflector 19.
  • the flexible pivot 7 connecting the antenna to the satellite body 11 is in this example placed under one foot of the tower 18, while the actuator 6 and the detector 2 are placed under another foot of the tower.
  • a single axis is shown in Figure 4 to facilitate understanding, but it is understood that the device acts along two axes.
  • the flexible support 7 is under one foot of the tower, two other feet include an actuator-detector assembly 2x, 6x, on the one hand, and 2y, 6y, on the other hand, for controlling the device along two axes xx, yy.
  • the primary device constituted by loop 16 and the secondary loop constituted by detector 17 and filter 9 can also be distinguished, which in this case may simply be an integrator.
  • the signal from the position detector 20 of a master platform 21 is used as control of the secondary circuit of a slave platform 22. It is not prejudged by the control device of the master platform, which can for example be produced according to one of the variants of FIG. 1.
  • a relative deflection command 23, between 21 and 22, can be introduced at 3.

Landscapes

  • Physics & Mathematics (AREA)
  • Engineering & Computer Science (AREA)
  • Astronomy & Astrophysics (AREA)
  • General Physics & Mathematics (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Variable-Direction Aerials And Aerial Arrays (AREA)
  • Support Of Aerials (AREA)
EP19810401076 1980-07-09 1981-07-03 Procédé et système d'asservissement d'une plate-forme mobile montée à bord d'un véhicule spatial Expired EP0043772B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8015270A FR2486675A1 (fr) 1980-07-09 1980-07-09 Procede et systeme d'asservissement d'une plate-forme mobile montee a bord d'un vehicule spatial
FR8015270 1980-07-09

Publications (2)

Publication Number Publication Date
EP0043772A1 EP0043772A1 (fr) 1982-01-13
EP0043772B1 true EP0043772B1 (fr) 1987-04-15

Family

ID=9244030

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19810401076 Expired EP0043772B1 (fr) 1980-07-09 1981-07-03 Procédé et système d'asservissement d'une plate-forme mobile montée à bord d'un véhicule spatial

Country Status (4)

Country Link
EP (1) EP0043772B1 (enrdf_load_stackoverflow)
JP (1) JPS5741300A (enrdf_load_stackoverflow)
DE (1) DE3176119D1 (enrdf_load_stackoverflow)
FR (1) FR2486675A1 (enrdf_load_stackoverflow)

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4550319A (en) * 1982-09-22 1985-10-29 Rca Corporation Reflector antenna mounted in thermal distortion isolation
DE3308076A1 (de) * 1983-03-08 1984-09-20 Diehl GmbH & Co, 8500 Nürnberg Plattform mit stellmotoren
JPS6213103A (ja) * 1985-07-10 1987-01-21 Aisin Seiki Co Ltd アンテナ装置
IT1224879B (it) * 1988-09-08 1990-10-24 Selenia Spazio Spa Attuatore lineare per il puntamento d'antenna, particolarmente idoneo per applicazioni spaziali
FR2718857B1 (fr) * 1994-04-15 1996-08-14 Giat Ind Sa Procédé et système de stabilisation d'un organe mobile asservi porté par un châssis insuffisamment rigide.
US5587714A (en) * 1995-03-10 1996-12-24 Space Systems/Loral, Inc. Spacecraft antenna pointing error correction
US6025815A (en) * 1995-10-04 2000-02-15 Austrian Aerospace Ges.M.B.H. Drive unit for adjusting satellite components requiring orientation
EP2916386A1 (en) * 2014-03-07 2015-09-09 Alcatel Lucent Antenna and method of operating an antenna
ITUB20159411A1 (it) * 2015-12-28 2017-06-28 Stellar Project S R L Sistema di puntamento stabilizzato compatto
CN110764538B (zh) * 2019-11-12 2023-05-05 南京理工大学 基于三步自适应算法的无人机三轴稳定平台及跟踪方法
CN116960638B (zh) * 2023-09-19 2024-01-12 广东福顺天际通信有限公司 一种反射面可调的反射器

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2907031A (en) * 1953-05-28 1959-09-29 Smiths America Corp Stabilising devices
US3047863A (en) * 1956-09-07 1962-07-31 Collins Radio Co Radiometric navigation system
US3099005A (en) * 1957-10-01 1963-07-23 Rca Corp Stabilized tracking system
US3263944A (en) * 1962-07-02 1966-08-02 Ibm Space craft navigation system
US3529166A (en) * 1963-07-01 1970-09-15 Trw Inc Electromagnetic position-indicating system
DE1272565B (de) * 1965-05-11 1968-07-11 Bundesrep Deutschland Anordnung zur raumfesten Stabilisierung von Geraeten auf Fahrzeugen
US3703999A (en) * 1969-12-12 1972-11-28 Actron Ind Inc Wide band stabilizer
US3731544A (en) * 1971-03-31 1973-05-08 Singer Co Star tracker system
DE2165282A1 (de) * 1971-12-23 1973-06-28 Henning W Dipl Ing Scheel Satellit mit zentraler antenne
JPS516637A (ja) * 1974-07-05 1976-01-20 Anritsu Electric Co Ltd Shikoseikuchusentoritsukeso
US3984072A (en) * 1974-10-02 1976-10-05 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Attitude control system
US4033541A (en) * 1975-05-30 1977-07-05 Mcdonnell Douglas Corporation Torque rejection soft mounted platform
GB1548762A (en) * 1975-07-23 1979-07-18 Scientific Atlanta Satelite tracking systems
JPS54104723A (en) * 1978-02-03 1979-08-17 Mitsubishi Electric Corp Stationary satellite
FR2450444A1 (fr) * 1979-02-28 1980-09-26 Aerospatiale Procede electromagnetique pour regler l'orientation d'une plate-forme

Also Published As

Publication number Publication date
FR2486675A1 (fr) 1982-01-15
DE3176119D1 (en) 1987-05-21
FR2486675B1 (enrdf_load_stackoverflow) 1984-11-23
JPS5741300A (en) 1982-03-08
JPH0457123B2 (enrdf_load_stackoverflow) 1992-09-10
EP0043772A1 (fr) 1982-01-13

Similar Documents

Publication Publication Date Title
US11716140B2 (en) Two-mirror tracking system for free-space optical communication
EP1116959B1 (en) Satellite communication optical beam acquisition techniques using a plurality of scan patterns
EP1130809B1 (en) Satellite optical communication acquisition techniques
EP0043772B1 (fr) Procédé et système d'asservissement d'une plate-forme mobile montée à bord d'un véhicule spatial
US10003402B2 (en) Ground terminal design for high rate direct to earth optical communications
CA1232164A (fr) Systeme de reconnaissance comportant un vehicule aerien tournant autour de son axe longitudinal
US6347001B1 (en) Free-space laser communication system having six axes of movement
US7171126B2 (en) Airborne free-space-optical system utilizing three-tier, ultrafine steering
EP3488540B1 (fr) Systeme combine d'imagerie et de communication par signaux laser
US5229871A (en) Optical data link for communicating data between a stationary member and a rotating member and an X-ray computer tomography apparatus incorporating the same
US11018766B2 (en) Optical satellite communication
FR2485275A1 (fr) Procede de pilotage d'orientation d'antenne sur un satellite et configuration de detecteurs mettant en oeuvre ce procede
FR2551855A1 (fr) Miroir de pointage avec dispositif de stabilisation
FR2737184A1 (fr) Systeme d'observation de satellites geostationnaires, utilisation d'un tel systeme et procedes d'observation correspondants
EP4386419A1 (fr) Procédé de commande du pointage d'une antenne
FR2530009A1 (fr) Appareil de visee panoramique stabilisee comprenant un detecteur thermique
EP0321342B1 (fr) Dispositif inertiel de stabilisation en inclinaison d'un élément orientable et miroir de télescope embarqué muni d'un tel dispositif
FR2690532A1 (fr) Dispositif de pointage pour appareil optique.
EP1635485B1 (fr) Procédé de transmission optique entre un terminal embarqué sur un engin spatial et un terminal distant, et engin spatial adapté pour un tel procédé
FR2687794A1 (fr) Ensemble radar de poursuite pour missile.
Schuster et al. Optomechanical design of STRV-2 lasercom transceiver using novel azimuth/slant gimbal
US20240230849A9 (en) Optical Tracking Control System
FR2751792A1 (fr) Dispositif de commande d'un appareil autour de trois axes et systeme de poursuite de satellite comportant un tel dispositif
FR2955182A1 (fr) Systeme de poursuite et de guidage a distance d'un vehicule dans un systeme de reference
EP1174677A1 (fr) Système de stabilisation d'un drone et système de pilotage d'un drone utilisant un tel système de stabilisation

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Designated state(s): DE GB NL

17P Request for examination filed

Effective date: 19820215

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE GB NL

REF Corresponds to:

Ref document number: 3176119

Country of ref document: DE

Date of ref document: 19870521

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed
PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 19940622

Year of fee payment: 14

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: NL

Payment date: 19940731

Year of fee payment: 14

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 19940826

Year of fee payment: 14

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Effective date: 19950703

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Effective date: 19960201

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 19950703

NLV4 Nl: lapsed or anulled due to non-payment of the annual fee

Effective date: 19960201

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Effective date: 19960402