Abnormal aircraft response monitor

1. A flight control system for an aircraft, comprising:

at least two flight control computers at least one of which is utilized at any one time to control flight of the aircraft, each of the at least two flight control computers having at least two processors, each of the at least two processors being responsive to an aircraft input signal indicative of at least one of a plurality of aircraft flight parameters, each of the at least two processors computing in parallel and providing a control output command signal indicative of a desired control of a flight control surface of the aircraft based on control laws;

wherein:

at least one of the at least two processors for each of the at least two flight control computers comprises an abnormal response monitor configured to detect a residual error in software that embodies the control laws by being responsive to the aircraft input signal indicative of at least one of a plurality of aircraft flight parameters and determining whether the control output command signal is within an acceptable value for the control output command; and

when the abnormal response monitor detects the residual error in the software by determining that the control output signal command is not within the acceptable value, then the one of the at least two flight control computers in which it is determined that the control output command signal is not within the acceptable value is disabled from being allowed to control flight of the aircraft.

2. The flight control system of claim 1 , wherein the aircraft input signal is indicative of a pitch of the aircraft.

3. The flight control system of claim 2 , wherein the aircraft input signal includes at least one from the group comprising a pitch angle, an amount of deflection of an elevator on the aircraft, and a normal acceleration of the aircraft.

4. The flight control system of claim 1 , wherein the aircraft input signal is indicative of a roll of the aircraft.

5. The flight control system of claim 4 , wherein the aircraft input signal includes at least one from the group comprising a roll angle, an amount of deflection of an aileron on the aircraft, and a normal acceleration of the aircraft.

6. The flight control system of claim 1 , wherein the flight control system comprises a fly-by-wire aircraft flight control system.

7. A method for determining the existence of a residual error in software that embodies control laws used to generate a control output command signal indicative of a desired control of a flight control surface of an aircraft, the method comprising:

providing at least two flight control computers at least one of which is utilized at any one time to control flight of the aircraft, each of the at least two flight control computers having at least two processors, each of the at least two processors being responsive to an aircraft input signal indicative of at least one of a plurality of aircraft flight parameters, each of the at least two processors computing in parallel and providing a control output command signal indicative of a desired control of a flight control surface of the aircraft based on the control laws, wherein at least one of the at least two processors for each of the at least two flight control computers comprises an abnormal response monitor configured to detect the residual error in the software;

sensing, using said abnormal response monitor, the aircraft input signal indicative of at least one of a plurality of aircraft flight parameters;

determining, from the sensed aircraft input signal, whether the control output command signal is within an acceptable value for the control output command; and

when the residual error in the software is detected by determining that the control output command signal is not within an acceptable value, then the one of at least two flight control computers for the aircraft in which it is determined that the control output command signal is not within an acceptable value is disabled from being allowed to control flight of the aircraft.

8. The method of claim 7 , wherein the sensed aircraft input signal is indicative of a pitch of the aircraft.

9. The method of claim 8 , wherein the sensed aircraft input signal includes at least one from the group comprising a pitch angle, an amount of deflection of an elevator on the aircraft, and a normal acceleration of the aircraft.

10. The method of claim 7 , wherein the sensed aircraft input signal is indicative of a roll of the aircraft.

11. The method of claim 10 , wherein the sensed aircraft input signal includes at least one from the group comprising a roll angle, an amount of deflection of an aileron on the aircraft, and a normal acceleration of the aircraft.

12. The method of claim 7 , wherein the flight control system comprises a fly-by-wire aircraft flight control system.

13. A computer program product for a flight control system for an aircraft, the flight control system comprising at least two flight control computers at least one of which is utilized at any one time to control flight of the aircraft, each of the at least two flight control computers having at least two processors, each of the at least two processors being responsive to an aircraft input signal indicative of at least one of a plurality of aircraft flight parameters, each of the at least two processors computing in parallel and providing a control output command signal indicative of a desired control of a flight control surface of the aircraft based on control laws, wherein at least one of the at least two processors for each of the at least two flight control computers comprises an abnormal response monitor for determining the existence of a residual error in software that embodies the control laws used to generate the control output command signal indicative of a desired control of a flight control surface of the aircraft, the computer program product comprising a non-transitory computer readable storage medium having program code embodied therewith, the program code readable/executable by a computer, processor or logic circuit to perform a method comprising:

sensing, using the abnormal response monitor, the aircraft input signal indicative of at least one of a plurality of aircraft flight parameters;

determining, from the sensed aircraft input signal, whether the control output command signal is within an acceptable value for the control output command; and

when the residual error in the software is detected by determining that the control output command signal is not within an acceptable value, then the one of at least two flight control computers for the aircraft in which it is determined that the control output command signal is not within an acceptable value is disabled from being allowed to control flight of the aircraft.

14. The computer program product of claim 13 , wherein the sensed aircraft input signal is indicative of a pitch of the aircraft.

15. The computer program product of claim 14 , wherein the sensed aircraft input signal includes at least one from the group comprising a pitch angle, an amount of deflection of an elevator on the aircraft, and a normal acceleration of the aircraft.

16. The computer program product of claim 13 , wherein the sensed aircraft input signal is indicative of a roll of the aircraft.

17. The computer program product of claim 16 , wherein the sensed aircraft input signal includes at least one from the group comprising a roll angle, an amount of deflection of an aileron on the aircraft, and a normal acceleration of the aircraft.

18. The computer program product of claim 13 , wherein the flight control system comprises a fly-by-wire aircraft flight control system.