Fail-safe dual channel automatic pilot with maneuver limiting

• US 4,035,705 A
• Filed: 03/17/1975
• Issued: 07/12/1977
• Est. Priority Date: 03/17/1975
• Status: Expired due to Term

• Current Assignee: Honeywell Incorporated (Honeywell International Inc.)
• Original Assignee: Sperry Rand Corporation
• Inventors: Miller, Harry
• Primary Examiner(s): Schaefer, Robert K.
• Assistant Examiner(s): Feldhaus, John J.
• Application Number:
  US05/558,582
• Time in Patent Office: 848 Days
• Field of Search: 318/561, 318/563, 318/564, 318/565, 318/566, 318/584, 318/585, 318/8, 235/150.2, 244/194
• US Class Current: 318/564
• CPC Class Codes: G05D 1/0077 using redundant signals or controls

Abstract

Two substantially identical servo channels, coupled through a differential mechanism, position an attitude control surface of an aircraft in response to a common command signal applied to both channels. The common command is coupled to each channel through separate displacement and rate limiting devices to limit the attitude displacement and rate of change of attitude commands about the associated aircraft axis. In the pitch axis a separate normal accelerometer controls each command rate limit so as to prevent excessive pitch maneuvers due to the common command source. Redundant polarity comparators are included for comparing the polarity of the incremental load factor with the polarity of each servo channel output and for applying a brake to clamp the output of a failed servo channel when the polarity of the incremental load factor agrees with the servo motion direction and the incremental load factor exceeds a predetermined level, thus allowing the valid servo to assume control of the aircraft for a limited time until the pilot disconnects the system in response to monitoring circuits which operate alerting devices.

Claims

1. A control system for controlling the movement of the pitch attitude control surface of an aircraft comprising

a common command signal source,

first and second substantially identical servo channels coupled to said common command signal source for providing first and second servo outputs respectively in response to said common command signal,

summing means responsive to said first and second servo outputs and coupled between said first and second servo channels and said pitch attitude control surface for controlling the movement thereof in accordance with the algebraic sum of said first and second servo outputs,

feedback means responsive to said first and second servo outputs for providing feedback signals to said first and second servo channels,

whereby movement of said pitch attitude control surface caused by a failure in one said servo channel tends to be compensated by movement of the output of the other said servo channel to minimize undesired maneuvers of said aircraft,

first and second limiter means coupled between said common command signal source and said first and second servo channels respectively for limiting said common command signal in each said channel to minimize undesired maneuvers of said craft when a failure occurs in said common command signal source,

said first and second limiter means each comprising rate limiter means for limiting the rate of change of said command signal applied to said first and second servo channels respectively, thereby limiting the rate of change of attitude of said craft in response to said command signal, and

first and second normal accelerometer means for providing respective incremental load factor signals representative of the incremental load factor on said aircraft.

2. The control system of claim 1 in which said first and second limiter means each further includes displacement limiter means for limiting the magnitude of said command signal applied to said first and second servo channels respectively thereby limiting the attitude displacement of said craft in response to said command signal.

3. The control system of claim 1 in which said first and second rate limiter means includes first and second adjusting means responsive to said first and second incremental load factor signals respectively for adjusting said rate of change of said command signal in a decreasing relationship with respect to said incremental load factor of said aircraft.

4. The control system of claim 1 in which said first and second servo channels further include

first and second brake means for clamping said first and second servo outputs respectively, and

first and second polarity signal generator means responsive to said first and second servo outputs respectively for providing respective first and second servo polarity signals representative of the directions of motion thereof respectively.

5. The control system of claim 4 further including first and second polarity comparator means responsive to said respective first and second incremental load factor signals and to said respective first and second servo polarity signals for providing respective first and second polarity comparison signals, said first and second brake means being responsive to said respective first and second polarity comparison signals for selectively applying said brake means associated with a failed one of said servo channels in accordance with the polarity comparison between the directions of motion of said failed servo channel and said incremental load factor of said aircraft.

6. The control system of claim 5 further including

first and second incremental load factor level detector means responsive to said first and second incremental load factor signals respectively for providing respective outputs when said incremental load factor of said aircraft exceeds a predetermined level, and

first and second coincidence gate means responsive to said respective outputs of said first and second incremental load factor level detector means and to said respective first and second polarity comparison signals for providing first and second coincidence signals to said first and second brake means respectively for applying said brake means associated with said failed one of said servo channels in accordance with the polarity comparisons between the direction of motion of said failed servo channel and said incremental load factor of said aircraft in coincidence with said incremental load factor of said aircraft exceeding said predetermined level.

7. The control system of claim 3 including first and second servo position sensor means coupled to said summing means for providing respective first and second servo position signals in accordance with said algebraic sum of said first and second servo outputs.

8. The control system of claim 7 further including first and second combining means coupled to said first and second adjusting means respectively and responsive to said respective first and second servo position signals and to said respective first and second incremental load factor signals for adjusting said rate of change of said command signal in a decreasing relationship with respect to said incremental load factor of said aircraft and in accordance with a function of said algebraic sum of said first and second servo outputs.

9. The control system of claim 8 in which each said first and second combining means includes wash out circuit means responsive to said respective servo position signal for providing said function of said algebraic sum of said first and second servo outputs.

10. The control system of claim 7 in which said first and second servo position signals are further coupled to said first and second servo channels for providing said feedback signals thereto.

11. The control system of claim 2 in which said first and second servo channels further include first and second rate generator means responsive to said first and second servo outputs respectively for providing respective first and second servo rate signals representative of the rates of motion thereof respectively.

12. The control system of claim 11 further including equalizing integrator means responsive to said first and second servo rate signals for providing respective first and second equalizing signals each representative of the integral of the difference between said first and second servo rate signals, and

first and second equalizer limiter means responsive to said first and second equalizing signals respectively for limiting the magnitudes thereof,

said limited equalizing signals from said first and second equalizer limiter means being applied to said first and second servo channels respectively with opposite polarities with respect to each other in such a manner as to tend to diminish the difference in motion between said first and second servo outputs when said first and second servo outputs are moving in opposite directions relative to each other.

13. The control system of claim 12 further including first and second failure monitors each comprising

equalizer signal level detector means responsive to said respective equalizing and limited equalizing signals for providing a failure signal when the difference therebetween exceeds a predetermined level, and

a pilot alert indicator responsive to said failure signal for providing a failure indication in accordance with said difference exceeding said predetermined level.

14. The control system of claim 13 in which each said failure monitor further includes time delay means within said equalizer level detector means for delaying said failure indication for a predetermined time interval after said difference exceeds said predetermined level.

15. The control system of claim 13 in which each said failure monitor further includes displacement limiter level detector means responsive to said common command signal and to the output signal of a respective one of said displacement limiter means for providing a further failure signal when the difference between said common command signal and said output signal of said displacement limiter means exceeds a predetermined level,

said pilot alert indicator being responsive to said further failure signal for further providing said failure indication when said difference between said common command signal and said output signal of said displacement limiter means exceeds said predetermined level.

16. The control system of claim 1 in which

each said first and second servo channels comprises a reversible servo, and

said summing means comprises differential gear means coupled between said first and second servo channels and said attitude control surface at a reversible point in said control system.

17. The control system of claim 4 further including first and second polarity comparator means responsive to said respective first and second incremental load factor signals and to said respective first and second servo polarity signals for providing respective first and second polarity comparison signals, said first and second brake means being responsive to said respective first and second polarity comparison signals for applying a selected one of said brake means associated with a failed one of said servo channels in accordance with agreement in the polarity comparison between the directions of motion of said failed servo channel and said incremental load factor of said aircraft.

18. The control system of claim 17 further including

first and second incremental load factor level detector means responsive to said first and second incremental load factor signals respectively for providing respective outputs when said incremental load factor of said aircraft exceeds a predetermined level, and

first and second coincidence gate means responsive to said respective outputs of said first and second incremental load factor level detector means and to said respective first and second polarity comparison signals for providing first and second coincidence signals to said first and second brake means respectively for applying said brake means associated with said failed one of said servo channels in accordance with said agreement in said polarity comparison in coincidence with said incremental load factor of said aircraft exceeding said predetermined level.

19. An automatic flight control system for controlling the movement of the pitch attitude control surface of an aircraft comprising

a common command signal source,

first and second substantially identical servo channels coupled to said common command signal source for providing first and second servo outputs respectively in response to said common command signal,

summing means responsive to said first and second servo outputs and coupled between said first and second servo channels and said pitch attitude control surface for controlling the movement thereof in accordance with the algebraic sum of said first and second servo outputs,

feedback means including first and second servo position sensor means coupled to said summing means for providing respective first and second servo position feedback signals to said first and second servo channels respectively in accordance with said algebraic sum of said first and second servo outputs,

whereby movement of said pitch attitude control surface caused by a failure in one said servo channel tends to be compensated by movement of the output of the other said servo channel to minimize undesired maneuvers of said aircraft,

first and second limiter means coupled between said common command signal source and said first and second servo channels respectively for limiting said common command signal in each said channel to minimize excess pitch maneuvers of said craft when a failure occurs in said common command signal source,

said first and second limiter means each comprising rate limiter means for limiting the rate of change of said command signal applied to said first and second servo channels respectively, thereby limiting the rate of change of the pitch attitude of said aircraft in response to said command signal, and

first and second normal accelerometer means for providing respective incremental load factor signals representative of the incremental load factor on said aircraft.

20. The control system of claim 19 in which said first and second limiter means each further includes displacement limiter means for limiting the magnitude of said command signal applied to said first and second servo channels respectively thereby limiting the pitch attitude displacement of said aircraft in response to said command signal.

21. The control system of claim 20 in which said first and second rate limiter means includes first and second adjusting means responsive to said first and second incremental load factor signals respectively for adjusting said rate of change of said command signal in a decreasing relationship with respect to said incremental load factor of said aircraft.

22. The control system of claim 21 in which said first and second servo channels further include

first and second brake means for clamping said first and second servo outputs respectively, and

first and second rate generator means responsive to said first and second servo outputs respectively for providing respective first and second servo rate signals representative of the rates and directions of motion thereof respectively.

23. The control system of claim 22 further including first and second polarity comparator means responsive to said respective first and second incremental load factor signals and to said respective first and second servo rate signals for providing respective first and second polarity comparison signals, said first and second brake means being responsive to said respective first and second polarity comparison signals for applying a selected one of said brake means associated with a failed one of said servo channels in accordance with agreement in the polarity comparison between the directions of motion of said failed servo channel and said incremental load factor of said aircraft.

24. The control system of claim 23 further including

first and second incremental load factor level detector means responsive to said first and second incremental load factor signals respectively for providing respective outputs when said incremental load factor of said aircraft exceeds a predetermined level, and

first and second coincidence gate means responsive to said respective outputs of said first and second incremental load factor level detector means and to said respective first and second polarity comparison signals for providing first and second coincidence signals to said first and second brake means respectively for applying said brake means associated with said failed one of said servo channels in accordance with said agreement in said polarity comparison in coincidence with said incremental load factor of said aircraft exceeding said predetermined level.

25. The control system of claim 24 further including first and second combining means coupled to said first and second adjusting means respectively and responsive to said respective first and second servo position signals and to said respective first and second incremental load factor signals for adjusting said rate of change of said command signal in a decreasing relationship with respect to said incremental load factor of said aircraft and in accordance with a function of said algebraic sum of said first and second servo outputs.

26. The control system of claim 25 in which each said first and second combining means includes wash out circuit means responsive to said respective servo position signal for providing said function of said algebraic sum of said first and second servo outputs.

27. The control system of claim 26 further including equalizing integrator means responsive to said first and second servo rate signals for providing respective first and second equalizing signals each representative of the integral of the difference in magnitude between said first and second servo rate signals, and

first and second equalizer limiter means responsive to said first and second equalizing signals respectively for limiting the magnitudes thereof,

said limited equalizing signals from said first and second equalizer limiter means being applied to said first and second servo channels respectively with opposite polarities with respect to each other in such a manner as to tend to diminish the difference in motion between said first and second servo outputs when said first and second servo outputs are moving in opposite directions relative to each other.

28. The control system of claim 27 further including first and second failure monitors each comprising

equalizer signal level detector means responsive to said respective equalizing and limited equalizing signals for providing a failure signal when the difference in magnitude therebetween exceeds a predetermined level, and

a pilot alert indicator responsive to said failure signal for providing a failure indication in accordance with said difference exceeding said predetermined level.

29. The control system of claim 28 in which each said failure monitor further includes time delay means within said equalizer signal level detector means for delaying said failure indication for a predetermined time interval after said difference exceeds said predetermined level.

30. The control system of claim 29 in which each said failure monitor further includes displacement limiter level detector means responsive to said common command signal and to the output signal of a respective one of said displacement limiter means for providing a further failure signal when the difference between said common command signal and said output signal of said displacement limiter means exceeds a predetermined level,

said pilot alert indicator being responsive to said further failure signal for further providing said failure indication when said difference between said common command signal and said output signal of said displacement limiter means exceeds said predetermined level.

31. The control system of claim 30 in which

each said first and second servo channel comprises a reversible servo, and

said summing means comprises differential gear means coupled between said first and second servo channels and said pitch attitude control surface at a reversible point in said control system.

32. The control system of claim 31 in which said first and second servo rate signals are further coupled to said first and second servo channels for providing further feedback signals thereto.

33. The control system of claim 32 in which each said first and second rate limiter means comprises

an integrator,

an algebraic subtracting circuit responsive to said common command signal and coupled to receive the output of said integrator for providing the algebraic difference therebetween, and

limit control means coupling the output of said subtracting circuit to the input of said integrator and coupled to the output of said respective combining means for controlling the gain of said integrator,

said limit control means comprising said adjusting means.