| 摘要 |
A flight control system for a rotary wing aircraft, the aircraft following a track Tsol relative to the ground with a ground course angle TKsol, a forward speed Va, a pitch angle P, and a heading Ψ, the aircraft having one or more rotary wings provided with blades of collective pitch and of cyclic pitch that are variable about respective pitch axes and that are capable of performing movements in rotation and in translation. The flight control system has two control members each provided respectively with at least one movement axis A, B, C, D, and an autopilot for generating control signals. An action on one of the control members relative to one of the movement axes A, B, C, D gives rise independently to a modification to the forward speed Va, to the ground course angle TKsol, or indeed to the pitch angle P by means of the autopilot. |
