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 |
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.
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