초록 ▼

A fly-by-wire control system for an aircraft including detection of pilot induced oscillations and a mobile control unit for such a system. According to the invention, provision is made for the pivotings of the mobile control unit to be damped by a controllable damper controlled by a detector that d

A fly-by-wire control system for an aircraft including detection of pilot induced oscillations and a mobile control unit for such a system. According to the invention, provision is made for the pivotings of the mobile control unit to be damped by a controllable damper controlled by a detector that detects oscillations corresponding to pilot induced oscillations.

대표청구항 ▼

1. 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 maneu

1. 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; anda 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, andupon 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. 2. The system of claim 1, wherein the controllable damper is a mechanical or hydraulic damper. 3. The system of claim 1, wherein the controllable damper is a magnetic machine. 4. The system of claim 3, wherein the magnetic machine is a synchronous machine with a permanent-magnet rotor. 5. The system of claim 1, wherein the mobile control is moveable about a roil-control axis and a pitch-control axis. 6. The system of claim 5, further comprising a sensor that detects pivoting of the mobile control about the roll-control axis and a sensor that detects pivoting of the mobile control about the pitch-control axis. 7. The system of claim 6, further comprising a controllable damper that damps movement of the mobile control about the roll-control axis and a controllable damper that damps movement of the mobile control about the pitch-control axis. 8. The system of claim 1, wherein the detector is incorporated into a computer that sends orders to an actuator of the at least one aerodynamic surface based on the damping characteristic commands sent by the detector.