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WO1992008105A1 - Procede et dispositif de mesure de position - Google Patents

Procede et dispositif de mesure de position Download PDF

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Publication number
WO1992008105A1
WO1992008105A1 PCT/SE1991/000741 SE9100741W WO9208105A1 WO 1992008105 A1 WO1992008105 A1 WO 1992008105A1 SE 9100741 W SE9100741 W SE 9100741W WO 9208105 A1 WO9208105 A1 WO 9208105A1
Authority
WO
WIPO (PCT)
Prior art keywords
measuring
point
antenna
angle
instrument
Prior art date
Application number
PCT/SE1991/000741
Other languages
English (en)
Inventor
Rudolf Wiklund
Original Assignee
Geotronics Ab
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 Geotronics Ab filed Critical Geotronics Ab
Publication of WO1992008105A1 publication Critical patent/WO1992008105A1/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
    • G01S3/40—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 adjusting orientation of a single directivity characteristic to produce maximum or minimum signal, e.g. rotatable loop antenna or equivalent goniometer system
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
    • G01C1/00—Measuring angles
    • G01C1/02—Theodolites
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
    • G01C15/00—Surveying instruments or accessories not provided for in groups G01C1/00 - G01C13/00
    • 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
    • G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
    • G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
    • G01S19/13—Receivers
    • G01S19/14—Receivers specially adapted for specific applications
    • 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
    • G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
    • G01S19/38—Determining a navigation solution using signals transmitted by a satellite radio beacon positioning system
    • G01S19/39—Determining a navigation solution using signals transmitted by a satellite radio beacon positioning system the satellite radio beacon positioning system transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
    • G01S19/42—Determining position
    • G01S19/51—Relative positioning

Definitions

  • the present invention relates to a method for establish ⁇ ing the position of one or more measuring points with the aid of signals received from a GPS-receiving system, and also to an instrument for carrying out the method.
  • the instrument When defining the positions of measuring points and/or when marking out an area with the intention of defining the boundaries of a plot of land, a road or highway, etc., it is normal practice to place a distance meter, or telemeter, in a central position. Subsequent to having adjusted the position of the instrument so that the symmetry line of the instrument stand extends exact ⁇ ly vertical, the instrument is used to make a reference measurement on at least one reference point in the terrain, for example a church steeple, a house, or like landmark, whose position is known beforehand. The instrument measures the distance from and the direction to each reference point and calculates its position with the aid of the reference measuring results. The instru ⁇ ment is then used to define the intended measuring points.
  • One problem with this system is that it is often relatively difficult to find reference points whose positions are known.
  • GPS-system Global System
  • Positioning System and is based on time measurement and on the simultaneous use of signals received from at least four satellites.
  • This system enables an area to be marked out by a single person carrying a GPS- antenna and receiver to the various marking-out points in the terrain.
  • One problem with this type of system is that it is necessary to chose measuring points where the satellite signals will not be obstructed.
  • it is necessary to position the antenna of the GPS-system at a point where the system is free from shading or screening objects. It is necessary to measure or to define those measuring points which are located beneath outwardly jutting roofs or which are shaded by a tree, or are obstructed in some other way, with the aid of other methods.
  • the main object of the present invention is to provide measuring equipment with which the positions of measur- ing points are established or defined in accordance with the GPS-system, although with which the horizontal direction to a selected satellite can also be indicated.
  • Another object of the invention is to provide equipment which also will enable poisition establishment of measuring points which are hidden to the satellites of the GPS-system.
  • a further object of the invention is to provide measur- ing equipment establishing the position of the equipment as well as its alignment in a horizontal plane.
  • Still another object of the invention is to provide measuring equipment for establishing or defining the position of a measuring point and/or for marking out an area, which includes a measuring station having tele- meter equipment of the EDM-type and which is intended to be placed centrally and can be brought into alignment with a plurality of measuring points for marking-out points during a measuring sequence, and which will obviate the necessity of taking reference measurements on known points in the surrounding terrain.
  • Yet another object of the present invention is to pro ⁇ vide a method by means of which solely one measuring point having the possibility of signal reception is re ⁇ quired for the purpose of accurately determining the position of a target. This obviates the need for sever ⁇ al measuring points close to the target point.
  • the main object of the invention is achieved with a measuring instrument of the kind defined in the charac ⁇ terizing clause of the following Claim 1. Further features and further developments of the measuring instrument according to the invention and a method for defining the position of a measuring point are set forth in the remaining Claims.
  • Figure 1 is a schematic illustration of a first embodi ⁇ ment of a measuring instrument according to the invention
  • Figure 2 is a diagram relating to the received signal strength as a function of the angular rotation of the GPS-antenna in Figure 1
  • Figure 3 is a principle diagram illustrating angles measured with the aid of the measuring instrument illustrated in Figure 1;
  • Figure 4 is a diagram relating to the strength of sig ⁇ nals received from a variant of the embodiment illustrated in Figure 1;
  • Figure 5 illustrates schematically a second embodiment of a measuring instrument according to the invention
  • FIG 6 illustrates in principle the processing of signals obtained from the GPS-antenna elements in the measuring instrument according to the Figure 5 embodiment.
  • FIG 7 illustrates signals obtained from the GPS- antenna elements in the measuring instrument according to the Figure 5 embodiment.
  • FIG. 1 A first embodiment of equipment constructed in accor ⁇ dance with the invention is shown in Figure 1.
  • This equipment includes a GPS-antenna 1 with an earth plane 2, and a central antenna element 3 mounted on a rod 4.
  • the GPS-antenna is re- sponsive or sensitive to direction and in the case of this embodiment, the directional sensitivity of the antenna has been achieved by positioning close to the periphery of the antenna an upstanding wing 5 which is made of a material which dampens the carrier wave arriv- ing from the satellites.
  • the wing 5, which is construc ⁇ ted as a signal dampening device, is rotated around the edge of the antenna, either by rotating the actual wing itself or by rotating the rod 4.
  • the wing 5 has a vertical extension sufficient to dampen the carrier wave of a satellite which is located high in the sky. Al ⁇ though not shown, the wing may be mounted,so as to enable it to be raised and lowered.
  • the Figure 1 embodiment also includes a unit 6 which includes a motor mounted on the rod 4.
  • the unit 6 also includes a rota ⁇ tional angle sensor, e.g. a code-disc system or syngon element (not shown).
  • a sighting device 8 such as a telescope, is pivotally mounted on a stand 7, by placing said unit in a housing 9 mounted on said stand.
  • the sighting device can be rotated or pivoted both in a horizontal plane and in a vertical plane, in a known manner, so as to enable said unit to be brought into alignment with a target point C.
  • the rotary angle sensor in the unit 6 functions to measure the angle of rotation between the rotatable rod 4 and the sighting device 8.
  • Rotation in the vertical plane is measured with the aid of a vertical angle indicator 12, which is illustrated purely schematically in the Figure and which is prefer ⁇ ably of the pendulum type.
  • a suitable vertical angle indicator intended for this particular purpose is de ⁇ scribed in U.S.A. Patent Specification No. 4,277,895.
  • verti ⁇ cal position indicator 10 mounted on the stand 7 is also a standard type of verti ⁇ cal position indicator 10 conventionally used with this type of instrument and having two mutually perpendicular level indicators of the spirit-level kind which enable the stand, and therewith also the rod 4, to be brought precisely to a vertical position. This will position the earth plane 2 of the GPS-antenna 1 horizontally.
  • the equipment also includes a calculating or computing unit 11 which comprises a receiver unit for receiving signals from the GPS-antenna 1.
  • the computing unit also receives signals from the rotary angle indicator 6 and the vertical angle indicator 12 (not shown) .
  • the signal damping device 5 can be rotated around the central antenna element 3 of the antenna 1, the device is able to dampen the ability to receive signals within a defined and variable angular range.
  • Figure 2 is a curve which illustrates how the strength of the signal received varies in relation to a reference signal with the angle of rotation.
  • This reference signal may be obtained, for instance, by measuring the strength of signals received from a selected satellite while rotating the wing 5 through one or more revolu ⁇ tions and recording the instantaneous variants in signal strength. It should be noted that further variations in signal strength may occur, due to signal reflection from objects in the surroundings.
  • the satellite moves in a well known manner, which is programmed in the receiving unit 11, whereas the reflected signals move along other paths, particularly in another directions, since they are reflected and have a phase which is different to the phase of the direct signal. Consequently, those varia- tions in the received antenna signal which are due to such reflections can be eliminated by computer process ⁇ ing the signal, e.g. by autocorrelation.
  • a reduction in the strength of signals received between the rotary angle positions V and V are caused by s 6 passage of the signal damping device 5 through these angular positions between the antenna and the trans ⁇ mitter.
  • Figure 3 is a principle diagram which illustrates a measuring system according to one method according to the invention.
  • the equipment includes only one telescope 8, as illustrated in Figure 1, such that only the direction to a measuring point is defined and not the distance from the equipment to said measuring point. Consequently, it is necessary to effect measurements on the measuring point C from two positions A and B, so as to enable the position of measuring point C to be determined by triangulation (the distance between the first mentioned two positions and the directions towards the point C become known) .
  • respective angles o and ⁇ are measured at the point of intersection of the normal of a signal-transmitting satellite in a horizontal plane through the measuring point and the direction towards the point C in the same horizontal plane, i.e. the horizontal sighting direction of the telescope 8, in the two positions A and B respec ⁇ tively.
  • This is the direction which is indicated by the direction indicator 6 in the embodiment illustrated in Figure 1.
  • the positions of the satellites are well known at each moment in time, and data relating to these positions is stored in the receiver, in the computing unit 11.
  • the measurements made on the point C from the measuring points A and B make known the position of the measuring point A and the angle in the horizontal plane, A, S ,
  • ⁇ __ A also make known the position of the measuring point B and the angle ⁇ in the horizontal plane B, S , C , and
  • the position of the measuring point C can be calculated from this data with the aid of geometrical methods well known to the person skilled in this art.
  • the method comprises the steps of:
  • the aforesaid recorded values depend on the position of the selected satellite and also on signal strength and on the damping ability of the signal damping device.
  • step S7 Repeating steps S2 to S6 for one or more of the remaining satellites. This step may optionally be omitted. Alternatively, the step may be coupled to a condition that it- need only be carried out when the spread between the angular positions calculated when measuring onto the first selected satellite is greater than a determined spread value. It will be understood that the repeated measurements are carried out uniformly and that the path travelled by the satellite between consecutive measurements can be determined.
  • S10 Calculating the position of the point C with the aid of geometrical formulae and with the aid of satellite data stored in the computing unit 11.
  • the position of C is calculated a number of times with the aid of the data repeatedly determined and stored, and a mean value is formed from the calcu- lated positions.
  • the angular position ⁇ or ⁇ between V and V can be
  • the distance meter may be provided conventionally with a simple sight or with a telescopic sight (not shown in the particular Figure since the difference from the Figure 1 embodiment is only marginal).
  • the measurement effected on the point C can be carried out from solely one measuring point A.
  • the measuring process can be carried out either on a prism, e.g. a cubic prism, placed at the target point C or may be carried out directly on the target point, by calcu- lating on the measuring beam effected directly by the target point (direct reflex).
  • the latter alternative provides a slightly less accurate measuring result than the former process.
  • a rotary angle detector 9' will facilitate the measuring procedure, since the detector 9' can be used, for instance, when defining a measuring point and/or when marking-out in a manner such that reference measuring to establish posi ⁇ tions and reference angle positions is carried out with the aid of GPS and the actual measuring sequence for the area concerned is then effected with the use of the rotary angle detector 9' to provide the horizontal angle in question. This enables an area to be surveyed much more quickly and with fewer calculations than when hori ⁇ zontal angles are defined against one or more satellites when measuring on each measuring point in the area.
  • surveying instruments provided with rotary angle detectors 9' are well known and, according to the invention, such a detector need only be complemented with a GPS-receiver with, a modified antenna in order to provide a reference, whereafter surveying of the area concerned is effected in a conventional manner without modifying calculations during a surveying sequence, as distinct from conventional procedures.
  • the computing unit 11 can then function in accordance with the following method steps of:
  • SI Placing the equipment in a measuring position A.
  • S2 Bringing the sighting device 8 into alignment with a point C.
  • Rotating the damping wing 5 Setting the reference level according to Figure 2. Measuring the vertical angle defined by the sighting device 8 with the unit 12. And measuring the distance from the measuring equipment to the measuring point C.
  • step S7 Repeating steps S2 to S6 for one or more of the remaining satellites. This step may optionally be omitted. Alternatively, the step may be coupled to a condition that the step need only be carried out when the spread between the angular positions cal ⁇ culated when measuring against the first selected satellite are greater than a determined spread value. It will be realized that the repeated mea- surements are taken uniformly and that the distance moved by the satellite between consecutive measure ⁇ ments can be determined.
  • Sllr Optionally establishing a reference angular posi- tion in the horizontal plane and marking this posi ⁇ tion on the horizontal angle indicator 9', and carrying out a series of measurements against dif ⁇ ferent measuring points in the terrain with the aid of the angle measuring device 9'.
  • the Figure 1 embodiment has been described as having solely one single damping wing.
  • the wing 5 can be constructed so that the side of the wing which faces towards the antenna element 3 will reflect sig ⁇ nals.
  • Figure 4 illustrates the signal received thereby from the antenna element 3 of the antenna 1.
  • the angu ⁇ lar positions for passage through an upper reference level can therewith also be indicated and the angular position therebetween is calculated as a complement to the angular positions calculated for passage through a lower signal level.
  • the signals obtained from a wing that has been provided with a reflector are dependent on the distance from the wing to the antenna element 3. This distance corres ⁇ ponds to the wavelength of the carrier wave of the satellite signal.
  • a reflector e.g. a mirror, which may also be curved
  • This distance corres ⁇ ponds to the wavelength of the carrier wave of the satellite signal.
  • the full-line curve shown to the right in the Figure is obtained, with amplifica ⁇ tion of the received signal through the reflector.
  • said distance lies in the proximity of half a wavelength or some odd multiples of said wave ⁇ length, the signal is extinguished to some extent, as illustrated by the broken-line curve.
  • two signal damping wings may be placed diametrically opposite one another, where one wing solely has a signal-damping function and the other wing has both a signal-reflecting and a signal-damping function.
  • This arrangement will result in a more exten ⁇ sive decrease in signal level than that shown to the right in Figure 4 at the angular position of the wing arrangement at which reflection has effect, because the signal level is both dampened by the damping wing and reduced due to extinguishing of the signal by diffrac ⁇ tion of the reflecting wing.
  • a certain positional error may be caused by double indication, partly because of the different positions of the wing in relation to the antenna element 3 and partly because of movement of the satellite with time, although this positional error can be compensated for when processing the signals received.
  • signal strength such as to indicate at least one of the level through-passes during one revolution.
  • steps S3-S5 above will be slightly modified, because level through-pass is indicated twice with each revolution instead of only once.
  • the equipment includes an antenna 14, an earth plane 2 and three antenna elements 15a, 15b, 15c.
  • the three antenna elements are arranged at a given distance from the centre of the antenna, for instance at an angular spacing of 120 degrees.
  • the equipment illustrated in Figure 5 also includes an EDM-instrument 13 which is mounted on a stand 16 and which can be rotated in a vertical direction by means of a knob or wheel 17, and further includes a sighting device 18 by means of which the instrument 13 is brought into alignment with the target point C.
  • the EDM-instru- ment is provided, in a known manner, with an arrangement for fine adjustment of the alignment with the target point when said target point is provided with a prism and with a vertical angle indicator 10, for instance a pendulum-type indicator.
  • the EDM-instrument can be rotated in a horizontal plane relative to the instrument stand, by means of a horizontal rotational device 19, which is provided with a horizontal angle indicator (not shown) .
  • the antenna 14 of the Figure 5 embodiment is not rotat- able relative to the unit 16 around a vertical shaft.
  • the direction to the satellite whose signal shall be received is established by comparison between the mutual phase positions of the signals received. This can be achieved by processing the signals in seve ⁇ ral different ways.
  • a principle for signal processing in three stages is illustrated in Figure 6.
  • the antenna elements 15a, 15b, 15c may be placed so close together that the difference in the propagation path between the satellite signals which impinge on the elements lies well within 1/2 wavelength of the satellite carrier frequency. It is also conceivable, however, to place the antenna elements much further apart. In order to be able to establish the propagation path differences and the direction towards the selected satellite obtained from these differences on the basis of analyzing the phases of said signals, it is essential that the mutual positions of the antenna elements 15a, 15b, 15c are accurately determined.
  • the signals received from the three antenna elements 15a, 15b and 15c are shown in Figure 7 and the signals are phase-analyzed in a first stage SB1, such that the phase differences ⁇ and ⁇ (see Figure 7) in respect of the antenna.element which lies first in phase and which is thus the antenna element of said three antenna elements which lies nearest the satellite can be indicated.
  • Phase analysis can be carried out in several different ways, all of which are well known to the skilled person and are therefore not described here.
  • the difference in the paths travelled by the three signals before being received by respective antenna elements is calculated in the second step SB2 of the signal processing stage.
  • the horizontal direction of the antenna in relation to the satellite is calculated geometrically with the aid of information relating to the calculated propagation paths and the mutual positioning of the antenna elements 15a, 15b, 15c.
  • This calculation is well known to one skilled in this art and will not therefore be described in detail. It can be mentioned, however, by way of example, that an extremely simple calculation can be made when two of the antenna elements 15a, 15b, 15c re ⁇ ceive signals which have mutually the same phase. The direction will then lie midway between these elements and through the centre and outwards, when the signal of the third antenna element lags in phase and in the other direction when said signal precedes in phase.
  • the antenna 14 is fixedly connected to the holder of the EDM-instrument 16 and the indicated direc- tion to the satellite is therefore placed in relation to the horizontal direction of the instrument 16, i.e. it is the horizontal angle between the instrument and the selected satellite that is measured.

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  • Engineering & Computer Science (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Computer Networks & Wireless Communication (AREA)
  • Position Fixing By Use Of Radio Waves (AREA)

Abstract

L'invention concerne un instrument de mesure utilisé pour déterminer la position d'au moins un point de mesure (C) à proximité de l'instrument de mesure, ainsi qu'un procédé de détermination de la position d'au moins un point de mesure. Ledit instrument de mesure comprend un équipement de réception (1, 2, 3) permettant d'indiquer des positions de signaux, par exemple selon le GPS, ainsi qu'un dispositif de visée de point de mesure (8; 16) relié à l'équipement de réception, et pouvant être mis en alignement avec ledit point de mesure. En plus d'un agencement de détermination de position classique, l'équipement de réception peut être également doté d'un dispositif de détection de direction (5, 6; 15a, 15b, 15c) dont la fonction est d'indiquer la direction horizontale à partir de l'instrument de mesure jusqu'à au moins une unité d'émission sélectionnée. L'instrument comprend également un agencement (6, 11) fournissant une direction de référence utilisée dans la mesure d'angles horizontaux du dispositif de visée de point de mesure sur la base de la direction indiquée à l'unité d'émission sélectionnée.
PCT/SE1991/000741 1990-11-02 1991-11-01 Procede et dispositif de mesure de position WO1992008105A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
SE9003500A SE9003500D0 (sv) 1990-11-02 1990-11-02 Hoeghastighetsmaetning
SE9003500-7 1990-11-02

Publications (1)

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WO1992008105A1 true WO1992008105A1 (fr) 1992-05-14

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Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1995006883A1 (fr) * 1993-09-01 1995-03-09 Trimble Navigation Reperage par systeme de positionnement par satellite (satps) integrant un calculateur d'angle de relevement
WO1995019576A1 (fr) * 1994-01-14 1995-07-20 Bicc Public Limited Company Procede et appareil de positionnement de machines de construction
EP0706665A4 (fr) * 1993-07-01 1996-05-08 Trimble Navigation Ltd
EP0744626A1 (fr) * 1995-05-23 1996-11-27 DASSAULT SERCEL Navigation-Positionnement Procédé et dispositif pour l'implantation précise de points à la surface de la terre par localisation radio-satellitaire
WO1997050129A1 (fr) * 1996-06-24 1997-12-31 Emilio Moreno Garcia Dispositif d'alimentation photovoltaique perfectionne applicable aux theodolites et similaires
WO2007000067A1 (fr) * 2005-06-27 2007-01-04 Eidgenössische Technische Hochschule Zürich Procede et systeme d'acquisition d'informations d'azimut a l'aide de signaux envoyes par satellite
CN104215971A (zh) * 2014-08-15 2014-12-17 广州市中海达测绘仪器有限公司 Gnss手持终端及其对中整平方法和数据采集方法
WO2018109440A1 (fr) * 2016-12-13 2018-06-21 Bae Systems Plc Agencement d'antenne

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WO1990000718A1 (fr) * 1988-07-06 1990-01-25 Wild Leitz Ag Appareil geodesique avec recepteur pour systemes de mesure de la position de satellites et son procede d'exploitation
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WO1990000719A1 (fr) * 1988-07-06 1990-01-25 Wild Leitz Ag Systeme geodesique avec une station electrooptique totale et une station mobile de reception pour systemes de positionnement de satellites
WO1990000718A1 (fr) * 1988-07-06 1990-01-25 Wild Leitz Ag Appareil geodesique avec recepteur pour systemes de mesure de la position de satellites et son procede d'exploitation
US4990922A (en) * 1990-03-14 1991-02-05 The United States Of America As Represented By The Administrator, National Aeronautics And Space Administration System and method for measuring ocean surface currents at locations remote from land masses using synthetic aperture radar

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PATENT ABSTRACTS OF JAPAN, Vol. 12, No. 238, P726; & JP,A,63 029 279, publ 1988-02-06, FURUNO ELECTRIC CO LTD. *

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0706665A4 (fr) * 1993-07-01 1996-05-08 Trimble Navigation Ltd
WO1995006883A1 (fr) * 1993-09-01 1995-03-09 Trimble Navigation Reperage par systeme de positionnement par satellite (satps) integrant un calculateur d'angle de relevement
WO1995019576A1 (fr) * 1994-01-14 1995-07-20 Bicc Public Limited Company Procede et appareil de positionnement de machines de construction
EP0744626A1 (fr) * 1995-05-23 1996-11-27 DASSAULT SERCEL Navigation-Positionnement Procédé et dispositif pour l'implantation précise de points à la surface de la terre par localisation radio-satellitaire
FR2734643A1 (fr) * 1995-05-23 1996-11-29 Soc Et Rech Et Const Electroni Procede et dispositif pour l'implantation precise de points a la surface de la terre par localisation radio-satellitaire
US5745074A (en) * 1995-05-23 1998-04-28 Dassault Sercel Navigation-Positionnement Staking out method and device using a satellite positioning system
WO1997050129A1 (fr) * 1996-06-24 1997-12-31 Emilio Moreno Garcia Dispositif d'alimentation photovoltaique perfectionne applicable aux theodolites et similaires
WO2007000067A1 (fr) * 2005-06-27 2007-01-04 Eidgenössische Technische Hochschule Zürich Procede et systeme d'acquisition d'informations d'azimut a l'aide de signaux envoyes par satellite
CN104215971A (zh) * 2014-08-15 2014-12-17 广州市中海达测绘仪器有限公司 Gnss手持终端及其对中整平方法和数据采集方法
WO2018109440A1 (fr) * 2016-12-13 2018-06-21 Bae Systems Plc Agencement d'antenne

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