US 11,860,260 B2
Systems and methods for high-integrity satellite positioning
Sebastien Carcanague, San Francisco, CA (US); and Fergus MacPherson Noble, San Francisco, CA (US)
Assigned to Swift Navigation, Inc., San Francisco, CA (US)
Filed by Swift Navigation, Inc., San Francisco, CA (US)
Filed on May 31, 2022, as Appl. No. 17/829,019.
Application 17/829,019 is a continuation of application No. 17/752,712, filed on May 24, 2022, granted, now 11,543,541.
Application 17/752,712 is a continuation of application No. 17/022,924, filed on Sep. 16, 2020, granted, now 11,372,114.
Application 17/022,924 is a continuation of application No. 16/865,077, filed on May 1, 2020, granted, now 10,809,388, issued on Oct. 20, 2020.
Claims priority of provisional application 62/841,380, filed on May 1, 2019.
Prior Publication US 2023/0030332 A1, Feb. 2, 2023
Int. Cl. G01S 19/44 (2010.01); G01S 19/07 (2010.01); G01S 19/52 (2010.01); G01S 19/25 (2010.01); G01S 19/49 (2010.01); G01S 19/20 (2010.01)
CPC G01S 19/44 (2013.01) [G01S 19/07 (2013.01); G01S 19/20 (2013.01); G01S 19/252 (2013.01); G01S 19/49 (2013.01); G01S 19/52 (2013.01)] 21 Claims
OG exemplary drawing
 
1. A system for determining a position of a global navigation satellite system (GNSS) receiver, the system comprising:
a cloud computing server configured to:
receive a set of satellite observations observed at a set of GNSS rovers, satellite orbit information, satellite clock information, and bias information;
determine corrections data from the set of satellite observations, the satellite orbit information, the satellite clock information, and the bias information;
generate corrections information comprising the corrections data, an integrity flag comprising a satellite flag when an integrity issue associated with a satellite effect is detected and an atmospheric flag when an integrity issue associated with an atmospheric effect is detected, and a probability of a satellite failure; wherein the integrity flag is generated based on a comparison of residuals remaining after applying the corrections data to a second set of satellite observations observed by a second set of GNSS rovers to a threshold; and
broadcast the corrections information;
wherein the broadcasted corrections information are receivable by a positioning engine configured to apply the corrections information to a set of satellite signals measured by the GNSS receiver to determine the GNSS receiver position when the integrity flag indicates that an integrity issue is not detected, wherein an integrity of the position depends on the probability of the satellite failure.