Method for navigating a carrier device using a Kalman filter estimating a navigation state of the carrier device
A method for navigating a carrier using a Kalman filter estimating a navigation state of a carrier, comprising: obtaining, from a signal transmitted by the satellite and subsequently received by the carrier, a delta range measured between the carrier and a satellite and another measured kinematic datum which is associated with the satellite, generating, from position data for the carrier and the satellite in the navigation state, an estimated delta range between the carrier and the satellite, calculating, using the delta ranges, a delta range innovation associated with the satellite, carrying out a test on the delta range innovation, the test result indicating whether or not the signal was a multi-path signal, using, by means of the filter, the kinematic datum as an observation to update the navigation state provided that the test result indicates that the signal was not a multi-path signal.
1. A method comprising:
obtaining a measured delta range between a carrier device and a satellite and another measured kinematic data associated with the satellite, from a positioning signal emitted by the satellite then received by the carrier device,
generating an estimated delta range between the carrier device and the satellite, from position data of the carrier device and the satellite contained in a navigation state of the carrier device estimated by a Kalman filter,
calculating a delta range innovation associated with the satellite, from the estimated delta range and the measured delta range,
carrying out a test on the delta range innovation; producing a test result indicating whether or not the positioning signal has followed a multi-path,
using the measured kinematic data associated with the satellite as an observation by the Kalman filter to update the navigation state of the carrier device on condition that the test result indicates that the positioning signal has not followed a multi-path.
2. The method according to claim 1 , wherein the measured kinematic data associated with the satellite is a pseudo-distance between the carrier device and the satellite.
3. The method according to claim 1 , wherein the measured delta range is not used by the Kalman filter to update the navigation state of the carrier device.
4. The method according to claim 1 , further comprising:
calculating a second innovation associated with the satellite, the second innovation relating to the measured kinematic data,
carrying out a test on the second innovation associated with the satellite, producing a second test result indicating a level of likelihood of the measured kinematic data, wherein using the measured kinematic data associated with the satellite as an observation by the Kalman filter to update the navigation state of the carrier device is conditioned to the second test result.
5. The method according to claim 4 , wherein the test on the second innovation associated with the satellite is implemented only on condition that the test result indicates that the positioning signal has not followed a multi-path.
6. The method according to claim 1 , wherein carrying out the delta range innovation test comprises:
calculating a term depending on a deviation between the delta range innovation associated with the satellite and a covariance of the delta range innovation associated with the satellite, and
making a comparison between the calculated term and a predefined threshold, wherein the test result depends on the comparison.
7. The method according to claim 1 , wherein generating the estimated delta range comprises:
calculating a distance between the carrier device and the satellite at a time t, from position data of the carrier device and the satellite, contained in a navigation state of the carrier device associated with the time t,
making an inverse prediction by the Kalman filter from the navigation state of the carrier device at the time t, so as to obtain a navigation state of the carrier device associated with a time t−ΔT,
calculating a distance between the carrier device and the satellite at the time t−ΔT, from position data of the carrier device and the satellite, contained in the navigation state of the carrier device associated with the time t−ΔT,
calculating a deviation between the distance between the carrier device and the satellite at the time t, and the distance between the carrier device and the satellite at the time t−ΔT.
8. The method according to claim 1 , wherein the Kalman filter implements a tight inertial/satellite coupling.
9. A non-transitory computer-readable medium comprising code instructions for causing a computer to perform the method as claimed in claim 1 .
10. A navigation system comprising:
The non-transitory medium of claim 9 ,
a processing unit configured to execute the code instructions,
a receiver configured to receive the positioning signal.