| 摘要 |
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.
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