US 11,721,220 B2
Systems and methods for monitoring and identifying failure in dual flight management systems
John Hillier, Phoenix, AZ (US); Daniel E. Lewis, Morris Plains, NJ (US); and Baptiste Duffourd, Beaupuy (FR)
Assigned to Honeywell International Inc., Charlotte, NC (US)
Filed by Honeywell International Inc., Morris Plains, NJ (US)
Filed on Apr. 2, 2020, as Appl. No. 16/838,110.
Claims priority of provisional application 62/828,946, filed on Apr. 3, 2019.
Prior Publication US 2020/0320884 A1, Oct. 8, 2020
Int. Cl. G08G 5/00 (2006.01); B64D 45/00 (2006.01)
CPC G08G 5/003 (2013.01) [B64D 45/00 (2013.01); G08G 5/0004 (2013.01); G08G 5/0047 (2013.01); B64D 2045/0085 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A computer-implemented method for monitoring and identifying failure in flight management systems, the method comprising:
receiving, from a first flight management system (FMS), a first calculated vehicle position;
receiving, from a second FMS, a second calculated vehicle position;
receiving, from a FMS monitor, a third calculated vehicle position;
comparing the first calculated vehicle position with the second calculated vehicle position and the third calculated vehicle position;
based on the comparison of the first calculated vehicle position with the second calculated vehicle position and the third calculated vehicle position, determining whether the vehicle has position integrity;
upon determining that the vehicle has position integrity, receiving a first value of a guidance command for controlling an aircraft for a Required Navigation Authorization Required, RNP AP, procedure from the first FMS;
receiving a second value of the guidance command for controlling the aircraft for the RNP AP procedure from a the second FMS;
receiving a third value from the FMS monitor, wherein the first, second, and third values are at least one of calculated cross track values, track angle errors, and/or calculated timing to transition between legs and segments of a flight plan;
comparing the first value with the second value and the third value to determine whether the first value matches the second value and third value;
upon determining that the first value does not match the second value and third value, determining a FMS that has computed a correct value of the guidance command;
generating a message indicating that the determined FMS is to be used to guide the aircraft; and
automatically reconfiguring the vehicle to use the determined FMS that has computed the correct value of the guidance command.