The capability of compensating automatically for a failure in an actuator and the associated drive circuit is enhanced by providing a dual channel actuator, each channel having a drive coil and a position sensor tracking the position of the actuator output shaft. A separate circuit is provided for each actuator channel to detect drive loop failures and hydraulic failures. When the drive loop of one channel fails, it is disengaged, and the gain in the remaining drive loop is doubled to maintain authority. In an embodiment, the remaining drive loop cannot disengage when certain criteria, relating to the failure of associated actuators, are met. The invention is particularly useful for aerospace applications.
Redundant control system for X-wing valve actuators
10.06.1986
Sonstige
Keine Angabe
Englisch
REDUNDANT HYDRAULIC CONTROL SYSTEM FOR ACTUATORS
NTIS | 1971
|Redundant, thin-wing, high-pressure, direct-drive valve actuation system
Tema Archiv | 1990
|Redundant, Thin-Wing, High-Pressure, Direct-Drive Valve Actuation System
SAE Technical Papers | 1990
|Autonomous Control System Reconfiguration for Spacecraft with Non-Redundant Actuators
British Library Conference Proceedings | 1995
|