CA1297972C - Landing assistance system using navigation satellites - Google Patents
Landing assistance system using navigation satellitesInfo
- Publication number
- CA1297972C CA1297972C CA000559992A CA559992A CA1297972C CA 1297972 C CA1297972 C CA 1297972C CA 000559992 A CA000559992 A CA 000559992A CA 559992 A CA559992 A CA 559992A CA 1297972 C CA1297972 C CA 1297972C
- Authority
- CA
- Canada
- Prior art keywords
- estimate
- data
- receiver
- landing
- satellites
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
Links
Classifications
-
- G—PHYSICS
- G08—SIGNALLING
- G08G—TRAFFIC CONTROL SYSTEMS
- G08G5/00—Traffic control systems for aircraft, e.g. air-traffic control [ATC]
- G08G5/0004—Transmission of traffic-related information to or from an aircraft
- G08G5/0013—Transmission of traffic-related information to or from an aircraft with a ground station
-
- 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
- G01S1/00—Beacons or beacon systems transmitting signals having a characteristic or characteristics capable of being detected by non-directional receivers and defining directions, positions, or position lines fixed relatively to the beacon transmitters; Receivers co-operating therewith
- G01S1/02—Beacons or beacon systems transmitting signals having a characteristic or characteristics capable of being detected by non-directional receivers and defining directions, positions, or position lines fixed relatively to the beacon transmitters; Receivers co-operating therewith using radio waves
- G01S1/08—Systems for determining direction or position line
- G01S1/44—Rotating or oscillating beam beacons defining directions in the plane of rotation or oscillation
- G01S1/54—Narrow-beam systems producing at a receiver a pulse-type envelope signal of the carrier wave of the beam, the timing of which is dependent upon the angle between the direction of the receiver from the beacon and a reference direction from the beacon; Overlapping broad beam systems defining a narrow zone and producing at a receiver a pulse-type envelope signal of the carrier wave of the beam, the timing of which is dependent upon the angle between the direction of the receiver from the beacon and a reference direction from the beacon
- G01S1/56—Timing the pulse-type envelope signals derived by reception of the beam
-
- 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
- G01S19/03—Cooperating elements; Interaction or communication between different cooperating elements or between cooperating elements and receivers
- G01S19/07—Cooperating elements; Interaction or communication between different cooperating elements or between cooperating elements and receivers providing data for correcting measured positioning data, e.g. DGPS [differential GPS] or ionosphere corrections
-
- G—PHYSICS
- G08—SIGNALLING
- G08G—TRAFFIC CONTROL SYSTEMS
- G08G5/00—Traffic control systems for aircraft, e.g. air-traffic control [ATC]
- G08G5/02—Automatic approach or landing aids, i.e. systems in which flight data of incoming planes are processed to provide landing data
- G08G5/025—Navigation or guidance aids
Abstract
LANDING ASSISTANCE SYSTEM USING NAVIGATION SATELLITES
ABSTRACT OF THE DISCLOSURE
The system according to the invention uses GPS/NAVSTAR
navigation satellites. It comprises:
- a fixed station located in the vicinity of the landing zone, containing a receiver for positioning by satellite that gives an estimate of the position of this fixed station and computing means that give correction data representing the deviation between this estimate and a reference position; and a data transmitter transmitting, in particular, these correction data on a radio channel which is conventionally used to transmit data in a microwave landing system called the MLS system;
- an on-board station in each aircraft comprising: an MLS receiver capable of receiving the ancillary data transmitted by the MLS system, a receiver for positioning by satellite and a computing device by which the correction data can be used to correct an estimate of position given by the positioning receiver.
ABSTRACT OF THE DISCLOSURE
The system according to the invention uses GPS/NAVSTAR
navigation satellites. It comprises:
- a fixed station located in the vicinity of the landing zone, containing a receiver for positioning by satellite that gives an estimate of the position of this fixed station and computing means that give correction data representing the deviation between this estimate and a reference position; and a data transmitter transmitting, in particular, these correction data on a radio channel which is conventionally used to transmit data in a microwave landing system called the MLS system;
- an on-board station in each aircraft comprising: an MLS receiver capable of receiving the ancillary data transmitted by the MLS system, a receiver for positioning by satellite and a computing device by which the correction data can be used to correct an estimate of position given by the positioning receiver.
Description
`` ~L2g37~7;~:
LANDING ASSISTANCE SYSTEM USING NAVIGATION SATELLITES
BACKGROUND OF THE INVENTION
l. Field of the Inventlon The invention pertains to a landing assistance system or aircraft.
LANDING ASSISTANCE SYSTEM USING NAVIGATION SATELLITES
BACKGROUND OF THE INVENTION
l. Field of the Inventlon The invention pertains to a landing assistance system or aircraft.
2. Description of the Prlor Art The most recent landing assistance system, which is a standardized one, is a microwave landing sys~em called MLS.
It has two narrow microwave beams which do a vertical scanning and a horizontal scanning, respectively, in the direction of a landing strip. These two beams are used to determine the position of an aircraft in a vertical plane and a horizontal plane respectively. This MLS system is currently installed or will be installed in all big airports, but has the disadvantage of requiring complicated infrastructure for each landing strip. This infrastructure is, firstly, too expensive for small airports and, secondly, too complicated to be set up quickly, for tactical needs, at a military landing strip.
Furthermore, there are very precise known positioning systems that use navigation satelli-tes, for example the positioning system called NAVSTAR/GPS. A system of this type comprises several satellites. Each satellite emits signals controlled by an atomic clock and comprising, notably, almanac data which make it possible to ascertain ~2~7~
the position of the satellite with respect to a geodesic reference point. A positioning receiver, placed on board an aircraft for example, is used to determine the position of this aircraft by simultaneously receiving the signals emitted by several satellites located in direct line of view at a given moment. A constellation of eighteen satellites is provided for, in order to ena~le reception from four or five satellites at any instant at any point on the earth. Each positioning receiver has a computing device, used to compute the position of the aircraft in three dimensions at high speed, using all the cumulated phase data of the carrier emitted by each sate]lite and using the phase of a code modulating this carrier.
A differential method described, for example, in the French Journal NAVIGATION, No. 137, pages 88 to 91, January 1987, makes it possible to improve the positioning precision achieved through the GPS system. By this differential method, the precision obtained is of about 3 meters on an average and makes it possible to envisage the use of the GPS system as an aircraft landing assistance system. According to this differential method, the system comprises a fixed station which constitutes a reference for aircraft located in the vicinity of the said fixed station, within a radi.us of 100 kilometers for example. The Eixed station has a receiver for positioning by satellite, which ;
~9~
gives an estimate of the position of this fixed station, and computing means that give correction data representing the deviation between this estimate and a reference position, which may be the position of the fixed station identified on a map. After eliminating the essential part of the lag of the clock incorporated in the receiver of the fixed station, the distances observed for each satellite, called pseudo-distances, are compared with the exact differences calculated from the almanac data transmitted by the satellites and from the reference position. The result of these computations give correction data, used to compensate for most of the errors arising out of satellite ephemerides and out of uncertainties in the propagation of radio waves.
The fixed station further comprises radio transmission means to transmit the correctian data to ai.rcraft. The station on board each aircraft comprises, in addi-tion to the receiver for positioning by satellite, radio reception means to receive the correction data and computing means for correcting, by means of the correction data, the position est.imate given by the positioning receiver. This computing device may be incorporated in the positioning receiver, which is then called a differential positioning receiver and directly gives the value of the corrected estimate.
~2~79~
The corrected estimate is precise enouqh to be used to guide a landing operation, but requires additional reception equipment. ~owever, for reasons related to space factor and cost, it is not desirable to increase the quantity of equipment on aircraft so that they can use another landing assistance system that complements the MLS
system.
SUMMARY OF THE INVENTION
The aim of the invention is to propose a landing assistance system which can be used to replace the MLS
system for landing strips that cannot be provided with this system , without considerably increasing the cost of navigation and landing assistance equipment already used on board the aircraft. The object of the invention is a system essentially comprising, on board each aircraft, a conventional receiver designed for MLS type landing assistance and a conventional receiver of the GPS type for positioning by satellite.
According to the invention, a landing assistance system using navigation satellites comprises: several navigation satellites emitting signals controlled by a clock, a fixed station located in the vicinity of the landi.ng strips and a station on board each aircraft, the said fixed station comprising:
~ a receiver or positioning by satellite, the said 2~ 2 ;
receiver giving an estimate of the position of the said fixed station, and computing means giving correction data representing the deviation bet~een this estimate and a reference position;
- radio transmission means to transmit the correction data, transmitting in a radio channel according to the standards of the microwave landing system known as MLS;
and the said on-board station comprising:
- a conventional radio receiver to receive data transmitted by a microwave landing system known as MLS;
- a receiver for positioning by satellite~ and computing means that give an estimate of the position of the aircraft, corrected by means of correction data received by the radio receiver.
BRIEF DESCRIPTION OF T~E DRAWINGS
Figures 1 and 2 represent block diagrams of two embodiments of the system according ko the invention.
DESCRIPTION OF TWO PREFERRED EMBODIMENTS
The embodiment shown in figure 1 comprises several satellites o~ the GPS/NAVSTAR system, 3 to 7, a fixe~
station 1 constituting the reference station and a station 2 on board an aircraEt ~not shown). The fixed station 1 comprises: a receiver 11 ~or non-differential positioning by satellite, a computing device 12 and a data transmitter 13.
~ '79'7~
The receiver 11 is a receiver for non-differential positioning by GPS/NAVSTAR satellite. The sai~ receiver is, for example, a TRIMBLE lOX receiver marketed by the TRIMBLE
firm. It is connected to an antenna 10 that can receive the signals emitted by all satellites in direct line of view.
It has a first output, connected to an input of the computing device 12, to give it an estimate X, Y, Z of the geodesic coordinates of the position of the fixed station 1, calculated conventionally from -the signals received from four satellites 3 to 6 from among all the satellites 3 to 7, which are in a direct line view at the instant considered. This computation consists essentially in determining the pseudo-distances between the fixed station 1 and these four satellites 3 to 6, and then in deducing therefrom the geodesic coordinates of the fixed station using the almanac data which are transmitted by these satellites and which make it possible to ascertain, at any instant, the position of the said satellites with reference to the earth. The receiver 11 has a second output connected to an input of the data transmitter 13 to yive it the numbers of the satellites, the si~nals of which are used to estimate the coordinates X, Y, Z.
The computing device 12 further has an input that reaeives three refererlce coordinates which are constant.
It calculates the deviation between these reference ~9~
coordinates and the coordinates X, Y, Z and deduces therefrom correction data marked ~X, ~ . It has an output connected to an inpu~ of the transmitter 13 to give it these correction data. The reference coordinates may be either the exact geodesic position of the fixed station 1, if it is known, or the position which has been determined by the receiver 11 at a prior instant and has been memorized once and for all.
The computing device 12 consists of a conventional microprocessor base computing device. It also has the function o~ giving a so-called integrity datum, indicating that the signals of the satellites, used to determine the coordinates X, Y, Z, are of adequate quality. The device 12 has an output connected to an input of the transmitter 13 to give it this integrity datum.
The data transmitter 13 has an input receiving a sequence of data which is proper to the landing zone: for example, the angle of the direction of a landing strip with respect to the magnetic north, the coordinates of the approach end of the strip and the identity of the strip.
The coordinates of the approach end of the strip, transmitted by the transmitter 13, should relate to the same reference point as the reference coordinates given to the computing device 12 of the fixed station 1. The coordinates transmitted are the geodesic coordinates of the 7917~
approach end of the strip in cases where the reference coordinates are the geodesic coordinates of the fixed station 1. The coordinates transmitted are coordinates measured by using the system according to the invention, in cases where the reference coordinates are coordinates that have been measured by means o~ the receiver 11 of the station 1 at a prior instant, and been memorized once and for all. For this, an aircraft is placed at the approach end of the strip and a series of position measurements is done with an on-board station. The transmitter 13 has an output connected to an omnidirectional antenna 1~ in the horizontal plane. It transmits on a radio channel which is usually dedicated to the transmission of ancillary data for the MLS type landing assistance system. The transmitter 13 transmits, according to the standardized format for the MLS
system, the data consisting of the correction data ~X, ~Y, ~Z, the integrity datum, the satellite numhers and data proper to the landing æone. The MLS channel frequency used by the transmitter 13 is proper to the landing zone.
The on-board station 2 comprises: a data receiver 17, a receiver 18 for non-differential positioning by satellite and a computing device 19. The data receiver 17 is a conventional receiver used in all aircraft ~itted with an MLS type landing assistance system. The said receiver 17 is connected to an antenna 1~ which is omnidirectional in q the horizontal plane. It is matched by the aircraft pilot to the MI.S channel frequency proper to the landing zone.
The receiver 17 has a first output connected to an input of the receiver 18 to give it the numbers of the satellites used by the fixed station 1 to estimate the coordinates X, Y, Z. The receiver 17 also has a second output, connected to an input of the computing device 19 to give it the correction data ~ , and third output and a fourth output, respectively connected to two inputs of an on-board computer 8, placed in the aircraft considered, to give it (namely the data receiver 17) the integrity datum and the data proper to the landing zone.
The receiver 18 is connected to an antenna 20 enabling it to receive all the satellites 3 to 7 which are in direct line of view at the instant considered. The receiver 18 is a conventional receiver for non-differential positioning by GPS/NAVSTAR satellite. It has an output that gives an estimate X', Y', Z' of the geodesic coordinates of the aircraft at an input of the computing device 19. The receiver la may consist of a TRI~BLE lOX receiver which is lightly modifiecl because the numbers of the satellites whose signals are used by the receiver 18 are not input manually by an operator, but are given by the receiver 17.
This modification is not described because it is within the scope of persons skilled in the art. An output of the computing device 19 gives a corrected estimate of the geodesic coordinates of the on-board station 2, computed according to a conventional algorithm, using correction data AX, ~y and ~ and estimate data X', Y', Z' given by the receiver 18.
The on-board computer 8 hence receives highly precise coordinates of the position of the aircraft and the integrity datum which guarantees the validity of the signals of the satellites used and that of the correction data. It further receives the angle of the direction of the strip with respect to the magnetic north, the coordinates of the approach end of the strip and, if necessary, any other data proper to the landing zone. The computer 8 is a conventional on-board computer which determines the landing guidance data. These data are given to the human pilot by a landing indicator, or else they are given to the automatic pilot.
The receivers for positioning by satellite conventionally comprise a microprocessor-based computing device. An alternative embodiment oE the system according to the invention may lie in the use of the computing device incorporated in the receiver 11 of the fixed station 1 to constitute the computing device 12 through A modification o~ the programming of the microprocessor which computes positions in the receiver 11.
~2917972 Similarly, the computations done by the computing device l9 of the on-board station 2 may be done by the microprocessor, which computes positions in the receiver 18, through a modification of the programme of this microprocessor. This same microprocessor may be used also to perform some of guidance computations instead of the on-board computer ~.
Figure 2 is a block diagram of a second embodiment of the system according to the invention. This second embodiment differs from the first embodiment in the type of correction data transmitted from the fixed station 1 to the on-board station 2. In the fixed station l, the receiver ll is replaced by a receiver ll' which is a receiver for positioning by satellite. The said receiver gives, in addition to the estimate of the three coordinates X, ~, Z, an estimate o~ the pseudo-distances measured between the fixed station 1 and all the satellites 3 to 7 respectively, which are in direct line of view of the fixed station l at the instant considered.
In this example, the receiver 11' gives five pseudo-distance values, dl,...d5, which respectively correspond to the satellites 3 to 7. These values are applied to an input o a computing device 12', similar to the computing device 12 but working according to a slightly dif~erent programme to determine the correction data ~IL29t7~7~
~dl,...~5, representing the deviation between the estimate of the pseudo-distances dl,...d5 and the fixed reference values which are computed by the computing device 12'. In this second embodiment, the reference values consis-t of true values of the pseudo-distances between the fixed stakion 1 and the satellites 3 to 7, these true values being computed, at a given instant, from the position of each satellite and the position of the fixed station 1. ~s in the first embodiment, the computing device 12' has an input that receives three fixed reference coordinates. These three coordinates are either the geodesic coordinates of the station 1 or the coordinates were measured by the receiver 11' at a prior instant and were memorized once and for all.
The computing device 12' determines, like the computing device 12, an integrity datum indicating good reception of the signals emitted by the satellites and used to determine the estimate of the pseudo-distances dl,...d5.
As in the first embodiment, the data transmitter 13 transmits on a channel according to the standards of the MLS landing assistance system and according to a format that complies with these standards. It transmtts the correction data ~or all the satellites that are in direct line o view, the integrity datum, the numbers of the 2S satellites corresponding to the correction data and data ~97~72 proper to the landing zone.
The on-board station 2 differs from that of the first embodiment in the fact that the receiver 18 and the computing means 19 consist of a receiver 18' for differential positioning by satellite. A receiver of this type has an input for correction data transmitted by a fixed reference station. The receiver 18' receives transmissions from all the satellites, 3 to 7, which are in direct line of view, and selects four of them to make an estimate of its position. It does not necessarily select the same satelltes as those selected by the receiver 11' to determine its position.
A conventional receiver for differential positioning by GPS/NAVSTAR satellite, capable of correcting an estimate of its position by means of correction data transmitted by a fixed reference station, can be used practically without modification. For example, the recei.ver 18' may comprise a TR-5S type receiver marketed by the SERCEL (trademark) firm.
This second embodiment requires a differential positioning receiver i.n each on-board station 2, but has the advantage of giving better positioniny precision Eor a receiver since the correction is done directly on the pseudo-distances o~ the satellites, before filtering and estimatin~ the position, unlike the first embodiment where ~2~7~72 the correction is done after filtering and estimating the position. Another advantage lies in the absence of constraints in the choice of the four satellites used by the receiver 18' to determine its position.
It is also possible to transmit additional correction data in addition to corrections on pseudo-distances. This additional correction data would consist of corrections on the pseudo-speeds of the satellites with respect to the fixed station 1, the true pseudo-speeds being computed by the computing device 12 or 12' using almanac data from the satellites. Known algorithms make it possible to use these additional correction data to compute a corrected estimate of the aircraft position with greater precision.
The invention is not restricted to the two embodiments described above. Many types of receivers for differential as well as non-differential positioning by satellite can be used to make the system of the invention. In all cases, an advantage of the on-board station is that it can be made using an MLS receiver and a receiver for differential positioning by satellite which are in standard use, or are going to come into standard use on aircraft. The fixed station does not require any complicated installation with directional antenna. Thiæ means that it can be speedily installed anywhere. It is therefore far less costly to install than an MLS fixed station. Furthermore, one and the ~L297~72 same fixed station can be used for several neighbouring strips, by transmitting distinct data packets for each strip on the same MLS channel, unlike the case of the MLS
system where a separate fixed station is needed for each strip.
It has two narrow microwave beams which do a vertical scanning and a horizontal scanning, respectively, in the direction of a landing strip. These two beams are used to determine the position of an aircraft in a vertical plane and a horizontal plane respectively. This MLS system is currently installed or will be installed in all big airports, but has the disadvantage of requiring complicated infrastructure for each landing strip. This infrastructure is, firstly, too expensive for small airports and, secondly, too complicated to be set up quickly, for tactical needs, at a military landing strip.
Furthermore, there are very precise known positioning systems that use navigation satelli-tes, for example the positioning system called NAVSTAR/GPS. A system of this type comprises several satellites. Each satellite emits signals controlled by an atomic clock and comprising, notably, almanac data which make it possible to ascertain ~2~7~
the position of the satellite with respect to a geodesic reference point. A positioning receiver, placed on board an aircraft for example, is used to determine the position of this aircraft by simultaneously receiving the signals emitted by several satellites located in direct line of view at a given moment. A constellation of eighteen satellites is provided for, in order to ena~le reception from four or five satellites at any instant at any point on the earth. Each positioning receiver has a computing device, used to compute the position of the aircraft in three dimensions at high speed, using all the cumulated phase data of the carrier emitted by each sate]lite and using the phase of a code modulating this carrier.
A differential method described, for example, in the French Journal NAVIGATION, No. 137, pages 88 to 91, January 1987, makes it possible to improve the positioning precision achieved through the GPS system. By this differential method, the precision obtained is of about 3 meters on an average and makes it possible to envisage the use of the GPS system as an aircraft landing assistance system. According to this differential method, the system comprises a fixed station which constitutes a reference for aircraft located in the vicinity of the said fixed station, within a radi.us of 100 kilometers for example. The Eixed station has a receiver for positioning by satellite, which ;
~9~
gives an estimate of the position of this fixed station, and computing means that give correction data representing the deviation between this estimate and a reference position, which may be the position of the fixed station identified on a map. After eliminating the essential part of the lag of the clock incorporated in the receiver of the fixed station, the distances observed for each satellite, called pseudo-distances, are compared with the exact differences calculated from the almanac data transmitted by the satellites and from the reference position. The result of these computations give correction data, used to compensate for most of the errors arising out of satellite ephemerides and out of uncertainties in the propagation of radio waves.
The fixed station further comprises radio transmission means to transmit the correctian data to ai.rcraft. The station on board each aircraft comprises, in addi-tion to the receiver for positioning by satellite, radio reception means to receive the correction data and computing means for correcting, by means of the correction data, the position est.imate given by the positioning receiver. This computing device may be incorporated in the positioning receiver, which is then called a differential positioning receiver and directly gives the value of the corrected estimate.
~2~79~
The corrected estimate is precise enouqh to be used to guide a landing operation, but requires additional reception equipment. ~owever, for reasons related to space factor and cost, it is not desirable to increase the quantity of equipment on aircraft so that they can use another landing assistance system that complements the MLS
system.
SUMMARY OF THE INVENTION
The aim of the invention is to propose a landing assistance system which can be used to replace the MLS
system for landing strips that cannot be provided with this system , without considerably increasing the cost of navigation and landing assistance equipment already used on board the aircraft. The object of the invention is a system essentially comprising, on board each aircraft, a conventional receiver designed for MLS type landing assistance and a conventional receiver of the GPS type for positioning by satellite.
According to the invention, a landing assistance system using navigation satellites comprises: several navigation satellites emitting signals controlled by a clock, a fixed station located in the vicinity of the landi.ng strips and a station on board each aircraft, the said fixed station comprising:
~ a receiver or positioning by satellite, the said 2~ 2 ;
receiver giving an estimate of the position of the said fixed station, and computing means giving correction data representing the deviation bet~een this estimate and a reference position;
- radio transmission means to transmit the correction data, transmitting in a radio channel according to the standards of the microwave landing system known as MLS;
and the said on-board station comprising:
- a conventional radio receiver to receive data transmitted by a microwave landing system known as MLS;
- a receiver for positioning by satellite~ and computing means that give an estimate of the position of the aircraft, corrected by means of correction data received by the radio receiver.
BRIEF DESCRIPTION OF T~E DRAWINGS
Figures 1 and 2 represent block diagrams of two embodiments of the system according ko the invention.
DESCRIPTION OF TWO PREFERRED EMBODIMENTS
The embodiment shown in figure 1 comprises several satellites o~ the GPS/NAVSTAR system, 3 to 7, a fixe~
station 1 constituting the reference station and a station 2 on board an aircraEt ~not shown). The fixed station 1 comprises: a receiver 11 ~or non-differential positioning by satellite, a computing device 12 and a data transmitter 13.
~ '79'7~
The receiver 11 is a receiver for non-differential positioning by GPS/NAVSTAR satellite. The sai~ receiver is, for example, a TRIMBLE lOX receiver marketed by the TRIMBLE
firm. It is connected to an antenna 10 that can receive the signals emitted by all satellites in direct line of view.
It has a first output, connected to an input of the computing device 12, to give it an estimate X, Y, Z of the geodesic coordinates of the position of the fixed station 1, calculated conventionally from -the signals received from four satellites 3 to 6 from among all the satellites 3 to 7, which are in a direct line view at the instant considered. This computation consists essentially in determining the pseudo-distances between the fixed station 1 and these four satellites 3 to 6, and then in deducing therefrom the geodesic coordinates of the fixed station using the almanac data which are transmitted by these satellites and which make it possible to ascertain, at any instant, the position of the said satellites with reference to the earth. The receiver 11 has a second output connected to an input of the data transmitter 13 to yive it the numbers of the satellites, the si~nals of which are used to estimate the coordinates X, Y, Z.
The computing device 12 further has an input that reaeives three refererlce coordinates which are constant.
It calculates the deviation between these reference ~9~
coordinates and the coordinates X, Y, Z and deduces therefrom correction data marked ~X, ~ . It has an output connected to an inpu~ of the transmitter 13 to give it these correction data. The reference coordinates may be either the exact geodesic position of the fixed station 1, if it is known, or the position which has been determined by the receiver 11 at a prior instant and has been memorized once and for all.
The computing device 12 consists of a conventional microprocessor base computing device. It also has the function o~ giving a so-called integrity datum, indicating that the signals of the satellites, used to determine the coordinates X, Y, Z, are of adequate quality. The device 12 has an output connected to an input of the transmitter 13 to give it this integrity datum.
The data transmitter 13 has an input receiving a sequence of data which is proper to the landing zone: for example, the angle of the direction of a landing strip with respect to the magnetic north, the coordinates of the approach end of the strip and the identity of the strip.
The coordinates of the approach end of the strip, transmitted by the transmitter 13, should relate to the same reference point as the reference coordinates given to the computing device 12 of the fixed station 1. The coordinates transmitted are the geodesic coordinates of the 7917~
approach end of the strip in cases where the reference coordinates are the geodesic coordinates of the fixed station 1. The coordinates transmitted are coordinates measured by using the system according to the invention, in cases where the reference coordinates are coordinates that have been measured by means o~ the receiver 11 of the station 1 at a prior instant, and been memorized once and for all. For this, an aircraft is placed at the approach end of the strip and a series of position measurements is done with an on-board station. The transmitter 13 has an output connected to an omnidirectional antenna 1~ in the horizontal plane. It transmits on a radio channel which is usually dedicated to the transmission of ancillary data for the MLS type landing assistance system. The transmitter 13 transmits, according to the standardized format for the MLS
system, the data consisting of the correction data ~X, ~Y, ~Z, the integrity datum, the satellite numhers and data proper to the landing æone. The MLS channel frequency used by the transmitter 13 is proper to the landing zone.
The on-board station 2 comprises: a data receiver 17, a receiver 18 for non-differential positioning by satellite and a computing device 19. The data receiver 17 is a conventional receiver used in all aircraft ~itted with an MLS type landing assistance system. The said receiver 17 is connected to an antenna 1~ which is omnidirectional in q the horizontal plane. It is matched by the aircraft pilot to the MI.S channel frequency proper to the landing zone.
The receiver 17 has a first output connected to an input of the receiver 18 to give it the numbers of the satellites used by the fixed station 1 to estimate the coordinates X, Y, Z. The receiver 17 also has a second output, connected to an input of the computing device 19 to give it the correction data ~ , and third output and a fourth output, respectively connected to two inputs of an on-board computer 8, placed in the aircraft considered, to give it (namely the data receiver 17) the integrity datum and the data proper to the landing zone.
The receiver 18 is connected to an antenna 20 enabling it to receive all the satellites 3 to 7 which are in direct line of view at the instant considered. The receiver 18 is a conventional receiver for non-differential positioning by GPS/NAVSTAR satellite. It has an output that gives an estimate X', Y', Z' of the geodesic coordinates of the aircraft at an input of the computing device 19. The receiver la may consist of a TRI~BLE lOX receiver which is lightly modifiecl because the numbers of the satellites whose signals are used by the receiver 18 are not input manually by an operator, but are given by the receiver 17.
This modification is not described because it is within the scope of persons skilled in the art. An output of the computing device 19 gives a corrected estimate of the geodesic coordinates of the on-board station 2, computed according to a conventional algorithm, using correction data AX, ~y and ~ and estimate data X', Y', Z' given by the receiver 18.
The on-board computer 8 hence receives highly precise coordinates of the position of the aircraft and the integrity datum which guarantees the validity of the signals of the satellites used and that of the correction data. It further receives the angle of the direction of the strip with respect to the magnetic north, the coordinates of the approach end of the strip and, if necessary, any other data proper to the landing zone. The computer 8 is a conventional on-board computer which determines the landing guidance data. These data are given to the human pilot by a landing indicator, or else they are given to the automatic pilot.
The receivers for positioning by satellite conventionally comprise a microprocessor-based computing device. An alternative embodiment oE the system according to the invention may lie in the use of the computing device incorporated in the receiver 11 of the fixed station 1 to constitute the computing device 12 through A modification o~ the programming of the microprocessor which computes positions in the receiver 11.
~2917972 Similarly, the computations done by the computing device l9 of the on-board station 2 may be done by the microprocessor, which computes positions in the receiver 18, through a modification of the programme of this microprocessor. This same microprocessor may be used also to perform some of guidance computations instead of the on-board computer ~.
Figure 2 is a block diagram of a second embodiment of the system according to the invention. This second embodiment differs from the first embodiment in the type of correction data transmitted from the fixed station 1 to the on-board station 2. In the fixed station l, the receiver ll is replaced by a receiver ll' which is a receiver for positioning by satellite. The said receiver gives, in addition to the estimate of the three coordinates X, ~, Z, an estimate o~ the pseudo-distances measured between the fixed station 1 and all the satellites 3 to 7 respectively, which are in direct line of view of the fixed station l at the instant considered.
In this example, the receiver 11' gives five pseudo-distance values, dl,...d5, which respectively correspond to the satellites 3 to 7. These values are applied to an input o a computing device 12', similar to the computing device 12 but working according to a slightly dif~erent programme to determine the correction data ~IL29t7~7~
~dl,...~5, representing the deviation between the estimate of the pseudo-distances dl,...d5 and the fixed reference values which are computed by the computing device 12'. In this second embodiment, the reference values consis-t of true values of the pseudo-distances between the fixed stakion 1 and the satellites 3 to 7, these true values being computed, at a given instant, from the position of each satellite and the position of the fixed station 1. ~s in the first embodiment, the computing device 12' has an input that receives three fixed reference coordinates. These three coordinates are either the geodesic coordinates of the station 1 or the coordinates were measured by the receiver 11' at a prior instant and were memorized once and for all.
The computing device 12' determines, like the computing device 12, an integrity datum indicating good reception of the signals emitted by the satellites and used to determine the estimate of the pseudo-distances dl,...d5.
As in the first embodiment, the data transmitter 13 transmits on a channel according to the standards of the MLS landing assistance system and according to a format that complies with these standards. It transmtts the correction data ~or all the satellites that are in direct line o view, the integrity datum, the numbers of the 2S satellites corresponding to the correction data and data ~97~72 proper to the landing zone.
The on-board station 2 differs from that of the first embodiment in the fact that the receiver 18 and the computing means 19 consist of a receiver 18' for differential positioning by satellite. A receiver of this type has an input for correction data transmitted by a fixed reference station. The receiver 18' receives transmissions from all the satellites, 3 to 7, which are in direct line of view, and selects four of them to make an estimate of its position. It does not necessarily select the same satelltes as those selected by the receiver 11' to determine its position.
A conventional receiver for differential positioning by GPS/NAVSTAR satellite, capable of correcting an estimate of its position by means of correction data transmitted by a fixed reference station, can be used practically without modification. For example, the recei.ver 18' may comprise a TR-5S type receiver marketed by the SERCEL (trademark) firm.
This second embodiment requires a differential positioning receiver i.n each on-board station 2, but has the advantage of giving better positioniny precision Eor a receiver since the correction is done directly on the pseudo-distances o~ the satellites, before filtering and estimatin~ the position, unlike the first embodiment where ~2~7~72 the correction is done after filtering and estimating the position. Another advantage lies in the absence of constraints in the choice of the four satellites used by the receiver 18' to determine its position.
It is also possible to transmit additional correction data in addition to corrections on pseudo-distances. This additional correction data would consist of corrections on the pseudo-speeds of the satellites with respect to the fixed station 1, the true pseudo-speeds being computed by the computing device 12 or 12' using almanac data from the satellites. Known algorithms make it possible to use these additional correction data to compute a corrected estimate of the aircraft position with greater precision.
The invention is not restricted to the two embodiments described above. Many types of receivers for differential as well as non-differential positioning by satellite can be used to make the system of the invention. In all cases, an advantage of the on-board station is that it can be made using an MLS receiver and a receiver for differential positioning by satellite which are in standard use, or are going to come into standard use on aircraft. The fixed station does not require any complicated installation with directional antenna. Thiæ means that it can be speedily installed anywhere. It is therefore far less costly to install than an MLS fixed station. Furthermore, one and the ~L297~72 same fixed station can be used for several neighbouring strips, by transmitting distinct data packets for each strip on the same MLS channel, unlike the case of the MLS
system where a separate fixed station is needed for each strip.
Claims (5)
1. A landing assistance system for assisting aircrafts as they approach a landing strip, said landing system comprising a fixed station located in the vicinity of the landing strip, a station on board each aircraft, and several navigation satellites occupying different positions with respect to the fixed station and emitting clock-controlled signals, said fixed station comprising:
a first receiver for receiving clock-controlled signals from the satellites and for calculating from the so received signals estimate data representative of the position of the fixed station;
means for computing correction data representing a deviation between predetermined reference position data and the said estimate data;
and radio transmission means for transmitting the correction data through a radio channel according to the standards of a microwave landing system known as MLS;
said on-board station comprising:
a radio receiver capable of receiving data transmitted by a microwave landing system known as MLS, in order to receive the correction data transmitted from the said radio transmission means;
a second receiver for receiving clock-controlled signals from the satellites, and for calculating from the so received signals estimate data representative of the position of the aircraft; and means for correcting the estimate data representative of the position of the aircraft by means of the correction data received by the said radio receiver in order to produce corrected data indicative of the position of the aircraft.
a first receiver for receiving clock-controlled signals from the satellites and for calculating from the so received signals estimate data representative of the position of the fixed station;
means for computing correction data representing a deviation between predetermined reference position data and the said estimate data;
and radio transmission means for transmitting the correction data through a radio channel according to the standards of a microwave landing system known as MLS;
said on-board station comprising:
a radio receiver capable of receiving data transmitted by a microwave landing system known as MLS, in order to receive the correction data transmitted from the said radio transmission means;
a second receiver for receiving clock-controlled signals from the satellites, and for calculating from the so received signals estimate data representative of the position of the aircraft; and means for correcting the estimate data representative of the position of the aircraft by means of the correction data received by the said radio receiver in order to produce corrected data indicative of the position of the aircraft.
2. A landing assistance system according to claim 1, in which:
the estimate data calculated by the said first receiver comprise an estimate of three geodesic coordinates of the position of said fixed station;
the correction data computed by the computing means of the fixed station comprise (a) deviations between said predetermined reference position data and the said estimate of three geodesic coordinates, and (b) numbers identifying the satellites of which the emitted signals have been used to calculate the said estimate of coordinates;
the estimate data calculated by the said second receiver comprise an estimate of three geodesic coordinates of the position of the aircraft calculated from the clock-controlled signals received from the satellites identified by the said numbers; and the corrected data from the correcting means comprise the estimate of the three geodesic coordinates of the position of the aircraft corrected by means of the correction data received by the said radio receiver.
the estimate data calculated by the said first receiver comprise an estimate of three geodesic coordinates of the position of said fixed station;
the correction data computed by the computing means of the fixed station comprise (a) deviations between said predetermined reference position data and the said estimate of three geodesic coordinates, and (b) numbers identifying the satellites of which the emitted signals have been used to calculate the said estimate of coordinates;
the estimate data calculated by the said second receiver comprise an estimate of three geodesic coordinates of the position of the aircraft calculated from the clock-controlled signals received from the satellites identified by the said numbers; and the corrected data from the correcting means comprise the estimate of the three geodesic coordinates of the position of the aircraft corrected by means of the correction data received by the said radio receiver.
3. A landing assistance system according to claim 1, in which:
the estimate data calculated by the said first receiver comprise an estimate of pseudo-distances between the fixed station and each of said satellites of which the emitted signals can be received by the first receiver;
the correction data computed by the computing means of the fixed station comprise deviations between the said estimate of the pseudo-distances and reference pseudo-distance values computed by the computing means from the predetermined reference position data;
the estimate data calculated by the said second receiver comprise pseudo-distances between the on-board station and each of said satellites of which the emitted signals can be received by the on-board station; and the corrected data from the correcting means comprise the estimate of the said pseudo-distances between the on-board station and the satellites by means of the correction data received by the said radio receiver.
the estimate data calculated by the said first receiver comprise an estimate of pseudo-distances between the fixed station and each of said satellites of which the emitted signals can be received by the first receiver;
the correction data computed by the computing means of the fixed station comprise deviations between the said estimate of the pseudo-distances and reference pseudo-distance values computed by the computing means from the predetermined reference position data;
the estimate data calculated by the said second receiver comprise pseudo-distances between the on-board station and each of said satellites of which the emitted signals can be received by the on-board station; and the corrected data from the correcting means comprise the estimate of the said pseudo-distances between the on-board station and the satellites by means of the correction data received by the said radio receiver.
4. A landing assistance system according to claim 1, wherein the landing strip is included into a landing zone and comprises an approach end, and wherein the said radio transmission means comprises means for further transmitting data proper to the landing zone, such as the coordinates of the approach end of the landing strip, these coordinates having been measured, in a reference point of the fixed station, by means of a station placed on board an aircraft positioned on this approach end.
5. A landing assistance system according to claim 1, wherein the said fixed station is common to several landing strips, and the said radio transmission means comprises means for transmitting, in addition to correction data, other data proper to each of these landing strips, respectively.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR8702648 | 1987-02-27 | ||
| FR878702648A FR2611399B1 (en) | 1987-02-27 | 1987-02-27 | LANDING ASSISTANCE SYSTEM USING NAVIGATION SATELLITES |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA1297972C true CA1297972C (en) | 1992-03-24 |
Family
ID=9348412
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA000559992A Expired - Lifetime CA1297972C (en) | 1987-02-27 | 1988-02-26 | Landing assistance system using navigation satellites |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US4894655A (en) |
| EP (1) | EP0283353B1 (en) |
| CA (1) | CA1297972C (en) |
| DE (1) | DE3881557T2 (en) |
| FR (1) | FR2611399B1 (en) |
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-
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- 1987-02-27 FR FR878702648A patent/FR2611399B1/en not_active Expired - Fee Related
-
1988
- 1988-02-23 EP EP88400409A patent/EP0283353B1/en not_active Expired - Lifetime
- 1988-02-23 DE DE8888400409T patent/DE3881557T2/en not_active Expired - Fee Related
- 1988-02-26 US US07/161,099 patent/US4894655A/en not_active Expired - Fee Related
- 1988-02-26 CA CA000559992A patent/CA1297972C/en not_active Expired - Lifetime
Also Published As
| Publication number | Publication date |
|---|---|
| EP0283353A1 (en) | 1988-09-21 |
| US4894655A (en) | 1990-01-16 |
| DE3881557D1 (en) | 1993-07-15 |
| EP0283353B1 (en) | 1993-06-09 |
| FR2611399B1 (en) | 1994-06-17 |
| FR2611399A1 (en) | 1988-09-02 |
| DE3881557T2 (en) | 1993-09-16 |
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