Patent ID: 7504996

Claim:
A satellite-based positioning receiver, comprising several digital signal processing channels each intended to be associated with a respective satellite and each providing a first digital datum representing a pseudo-distance between the receiver and the satellite calculated on the basis of an instantaneous phase of a pseudo-random code present in the signal transmitted by the satellite and a second digital datum representing this pseudo-distance calculated on the basis of an instantaneous phase of the carrier of the signal transmitted by the satellite, comprising an: extended Kalman filter including: means for calculating a position of the receiver in a terrestrial reference frame on the basis of a previously calculated position and of an error in this position; means for calculating propagation of an estimated state vector comprising the error in the calculated position of the receiver, on the basis of a matrix propagation equation involving a propagation matrix, means for calculating registration of the state vector on the basis of observations relating to each satellite and of a matrix of observations relating the state vector and the observations, means for calculating observations, receiving the first and the second digital datum to calculate an estimated pseudo-distance between the receiver and each satellite, so as to establish observations to be applied to the input of the registration calculation means, means for calculating an estimated pseudo-distance for each satellite, by calculating the distance between the calculated position of the receiver in the terrestrial reference frame and each satellite; wherein the means for calculating observations comprise means for subtracting the estimated pseudo-distance from the first and from the second digital datum and applying the result of the subtraction to the input of the registration calculation means; wherein the matrix propagation equation brings into the state vector a component representing the ambiguity of the measurement of the carrier pseudo-distance, per satellite; and wherein calculating registration of the state vector on the basis of observations is based on a code pseudo-distance observation and a carrier pseudo-distance observation.