Communications: directive radio wave systems and devices (e.g. – Directive – Including a satellite
Reexamination Certificate
1999-01-15
2001-01-09
Issing, Gregory C. (Department: 3662)
Communications: directive radio wave systems and devices (e.g.,
Directive
Including a satellite
Reexamination Certificate
active
06172638
ABSTRACT:
BACKGROUND OF THE INVENTION
1. Field of the Invention
The invention relates to satellite positioning receivers such as GPS (Global Positioning System) receivers.
2. Discussion of the Background
The GPS system uses a constellation of satellites which move around the earth on very precisely determined orbits, that is to say it is possible to know the position of an arbitrary satellite at any time. The satellites transmit radiofrequency signals, containing navigation data and codes which make it possible to identify each satellite. These codes phase modulate a carrier frequency. A GPS receiver, on the ground or on a land, air or sea vehicle, can receive the signals from several satellites simultaneously, precisely calculate its distance from each of the satellites, and deduce therefrom its precise position in latitude, longitude and altitude in a terrestrial frame. It can also deduce therefrom the precise date and time of the reception in the time frame of the GPS system. It can lastly deduce therefrom, by Doppler measurements, its own velocity vector in the terrestrial frame (the case of a receiver mounted on a moving vehicle).
In the GPS system, each satellite is identified by a pseudo-random code which is individual to it and repetitively (for example every millisecond) modulates a carrier frequency which the satellite transmits. There are systems similar to GPS, in particular the GLONASS system, in which this pseudo-random code also exists even though it is not used to identify individual satellites. The invention which will be described is directly applicable to the GLONASS system, but for the sake of simplicity reference will be made below only to the GPS system, and more precisely the “civil” part of the GPS system which also has a military part to which the invention is equally applicable.
The pseudo-random code is a long code (1023 bits at 1.023 MHz, i.e. 1 millisecond), and one of its main functions is to make it possible to extract the satellite's signal from a noise level much higher (for example 30 dB) than the level of the signal. This technique is now widely known as spread spectrum transmission. The signal is extracted from the noise using an operation, in the receiver, of correlation between the received signal and a periodic pseudo-random code which is identical to the one expected to be found in the signal. If the codes do not coincide temporally, there is no correlation between the received signals and the local code generated by a local code generator; if they almost coincide, there is some degree of correlation, the correlation energy becoming stronger as the coincidence becomes more exact. It is therefore possible to establish a correlation signal making it possible to slave a local code generator until exact coincidence is obtained between the local code and the code modulating the signal which the satellite transmits. A code slaving loop then makes it possible to maintain this coincidence.
The pseudo-random code is transmitted by the satellite at extremely precise times which are known at the receiver. Use is made of the correlation operation to determine the arrival time of this code in the receiver: the characteristic time or epoch of transmission of the local code is determined, and since this local code coincides with the received code when the maximum correlation is established, this time represents the arrival time of the received code. The difference between a time at which the code is transmitted via the satellite and a time at which the code is received by the receiver makes it possible to determine a propagation time of the signals between the satellite and the receiver. Knowing that the propagation velocity of the signals is the velocity of light, the distance between the receiver and a given satellite can be calculated. The same operation performed on two other satellites makes it possible, by triangulation, to determine the exact position of the receiver relative to the three satellites.
By using a fourth satellite, the clock errors of the receiver are eliminated, the clock of the receiver not being as precise as that of the satellites. Further to the position of the receiver, it is then possible to calculate a precise time for the position measurement, in the time frame of the GPS satellites.
The position of each of the satellites is known at any time: it is calculated on the basis of tables which are stored in the receiver and are updated by the navigation message broadcast by the satellites. The velocity of the satellites at any time can also be calculated on the basis of these tables.
It is possible to determine, on the basis of the signals sent by four satellites, the time and the position of the receiver relative to the four satellites. Furthermore, by changing co-ordinates, the position of the receiver in a fixed terrestrial frame is obtained.
Similarly, the velocity of the receiver is calculated on the basis of a Doppler-effect measurement on the carrier frequency of the radiofrequency signal sent by the satellites. It is therefore possible to calculate the relative velocity of the receiver with respect to each of the satellites, along the director axis which joins this satellite to the receiver. Four satellites are needed to eliminate the time ambiguity. Four different relative velocity vectors are obtained, along the director axes joining the receiver to the four satellites. Simple calculations make it possible to determine the velocity of the receiver along three axes in the terrestrial frame on the basis of these four velocity vectors and the following information:
the directions of the receiver-satellite director axes with respect to a fixed terrestrial frame (longitude, latitude, altitude); these directions are themselves obtained by knowledge of the position of the receiver at a given time and the position of each satellite at the same time;
the individual velocities of the satellites in the terrestrial frame at this time.
If more than four satellites are used, redundant information is obtained. This is the case for professional-quality receivers used, in particular, in aeronautics. This redundant information makes it possible to eliminate satellites which would give defective information. The information is considered as defective on the grounds that it is not coherent with the measurements taken as a whole.
There are a variety of causes which may lie behind a lack of coherency, for example the presence of multiple radiofrequency wave paths between the satellite and the receiver. These multiple paths exist, in particular, when buildings or other fixed obstacles generate reflections in the vicinity of the receiver.
SUMMARY OF INVENTION
One object of the invention is to eliminate the influence of multiple paths on the position measurements as far as possible.
If the receiver receives, on the one hand, a wave transmitted in direct line of sight by a satellite, the distance measurement obtained on the basis of this direct path will give a certain value of the distance between the receiver and the satellite. If it receives a wave along a reflected path, the measurement obtained will be one corresponding to the path extended by the reflection. If the obstacle is nearby, the receiver will receive a combined signal, one part of which corresponds to the direct path and one part of which corresponds to the reflected path, and the distance measurement (using the correlation principle indicated above) will lead to a distance which is neither quite the direct path nor quite the reflected path.
For precise measurement applications, this defect is unacceptable. This is the case, in particular, for fixed reception stations which are used in differential measurement systems. In these systems, the fixed ground station takes position measurements, compares the measurements with its known fixed position, and transmits information about corrections to be made to the measurements corresponding to each satellite. The neighbouring receivers, on board vehicles, receive signals from satellites and the corrections transmitted by the fixed station.
Issing Gregory C.
Oblon & Spivak, McClelland, Maier & Neustadt P.C.
Sextant Avionique
LandOfFree
Satellite signal receiver with detector of incoherence... does not yet have a rating. At this time, there are no reviews or comments for this patent.
If you have personal experience with Satellite signal receiver with detector of incoherence..., we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Satellite signal receiver with detector of incoherence... will most certainly appreciate the feedback.
Profile ID: LFUS-PAI-O-2497148