Patent ID: 8473121

Claim:
A fly-by-wire control system that reduces phase shift between movement of a mobile control and at least one aerodynamic surface of an aircraft, the system comprising: a mobile control configured to be operable by a pilot to control movement of the aircraft about at least one control axis of maneuver; at least one sensor unit that detects pivoting of the mobile control about the at least one control axis of maneuver and generates electric commands indicative of movement of the mobile control about the at least one control axis of maneuver; at least one controllable damper associated with the at least one sensor unit and the at least one control axis that damps the pivoting of the mobile control about the at least one control axis of maneuver; and a detector that detects pilot induced oscillation conditions from the electric commands generated by the at least one sensor and sends commands modifying damping characteristics of the at least one controllable damper according to amplitude of said detected pilot induced oscillation conditions, wherein: upon the detector detecting a first oscillation condition, the detector sends a first command to the at least one controllable damper setting the damping characteristic according to a predetermined value, and upon the detector detecting a second oscillation condition representative of a pilot induced oscillation condition, the detector sends a second command to the at least one controllable damper increasing magnitude of the damping characteristic based on the amplitude of the second oscillation condition.