SYSTEMS AND METHODS FOR PROTECTING FLIGHT CONTROL SYSTEMS
In an embodiment, an aircraft includes a pilot input device, a position sensor coupled to the pilot input device, a flight condition sensor and a flight control computer (FCC). The FCC includes a first microprocessor and a second microprocessor. The first microprocessor is configured to receive input data from the position sensor and the condition sensor and determine therefrom a first output. The second microprocessor is configured to receive input data from the position sensor and the condition sensor and determine therefrom a second output. The FCC is configured to compare the first output and the second output to yield resultant data. Responsive to a determination that the first output and the second output do not match, the FCC is configured to execute first remediation logic if the resultant data satisfies first error criteria and to execute second remediation logic if the resultant data satisfies second error criteria.
1 . An aircraft comprising:
a pilot input device;
a position sensor coupled to the pilot input device;
a flight condition sensor; and
a flight control computer comprising:
a first microprocessor configured to receive input data from the position sensor and the flight condition sensor and determine therefrom a first output; and
a second microprocessor configured to receive input data from the position sensor and the flight condition sensor and determine therefrom a second output;
wherein the flight control computer is configured to:
compare the first output from the first microprocessor and the second output from the second microprocessor, the comparison yielding resultant data; and
responsive to a determination that the first output and the second output do not match:
execute first remediation logic if the resultant data satisfies first error criteria; and
execute second remediation logic if the resultant data satisfies second error criteria.
2 . The aircraft of claim 1 , wherein the first error criteria and the second error criteria are mutually exclusive.
3 . The aircraft of claim 1 , wherein the second error criteria is indicative of greater error severity than the first error criteria.
4 . The aircraft of claim 3 , wherein the execution of the first remediation logic comprises disengagement of a first set of control operations while a second set of control operations remains engaged.
5 . The aircraft of claim 3 , wherein the execution of the first remediation logic comprises disengagement of a first control loop while a second control loop remains engaged.
6 . The aircraft of claim 3 , wherein the execution of the first remediation logic comprises disengagement of an outer control loop that focuses on at least one of guidance and tracking tasks.
7 . The aircraft of claim 3 , wherein the execution of the second remediation logic comprises a switch-over of processing authority to a secondary processing lane in the flight control computer.
8 . The aircraft of claim 3 , wherein the execution of the second remediation logic comprises a switch-over of processing authority to a different flight control computer.
9 . The aircraft of claim 3 , wherein the execution of the second remediation logic comprises a loss of redundancy.
10 . The aircraft of claim 1 , wherein the first error criteria and the second error criteria each comprise an error frequency.
11 . A method comprising, by a flight control computer:
comparing a first output from a first microprocessor and a second output from a second microprocessor, the comparing yielding resultant data; and
responsive to a determination that the first output and the second output do not match:
executing first remediation logic if the resultant data satisfies first error criteria; and
executing second remediation logic if the resultant data satisfies second error criteria.
12 . The method of claim 11 , wherein the first error criteria and the second error criteria are mutually exclusive.
13 . The method of claim 11 , wherein the second error criteria is indicative of greater error severity than the first error criteria.
14 . The method of claim 13 , wherein the executing the first remediation logic comprises disengaging a first set of control operations while a second set of control operations remains engaged.
15 . The method of claim 13 , wherein the executing the first remediation logic comprises disengaging a first control loop while a second control loop remains engaged.
16 . The method of claim 13 , wherein the executing the first remediation logic comprises disengaging an outer control loop that focuses on at least one of guidance and tracking tasks.
17 . The method of claim 13 , wherein the executing the second remediation logic comprises a switch-over of processing authority to a secondary processing lane in the flight control computer.
18 . The method of claim 13 , wherein the executing the second remediation logic comprises a switch-over of processing authority to a different flight control computer.
19 . The method of claim 11 , wherein the first error criteria and the second error criteria each comprise an error frequency.
20 . A flight control computer for an aircraft, the flight control computer comprising:
a first microprocessor configured to receive input data comprising a position and a flight condition and determine therefrom a first output; and
a second microprocessor configured to receive input data comprising a position and a flight condition and determine therefrom a second output; and
wherein the flight control computer is configured to:
compare the first output from the first microprocessor and the second output from the second microprocessor, the comparison yielding resultant data; and
responsive to a determination that the first output and the second output do not match:
execute first remediation logic if the resultant data satisfies first error criteria; and
execute second remediation logic if the resultant data satisfies second error criteria.