An actuation system for resolving the effects of force-fight between multiple stages within an actuator coupled to an aircraft flight control member includes a yoke configured for connection to the flight control member. A first control member is operatively coupled to a first actuator and configured to cause the first actuator to output a first force to the yoke, and a second control member is operatively coupled to a second actuator and a third actuator symmetrically arranged on opposite sides of the first actuator. The second control member is configured to operate independent of the first control member and to cause the second actuator and the third actuator to output a second force to the yoke and a third force to the yoke respectively, wherein the combined force is substantially the same as the first force to effect motion of the flight control member.
Symmetrically loaded dual hydraulic fly-by-wire actuator
2020-02-25
Patent
Elektronische Ressource
Englisch
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