| 摘要 |
The invention relates to a control system (100) for a rotorcraft (1) comprising a rotor (10), at least one variable-pitch propulsive propeller (6L, 6R), and one engine for driving the rotor and the propeller(s), characterised in that it comprises: a member (101, 101 A, 102, 103, 104) for developing a setpoint (?p* + ?d*, ?p* - ?d*) of the propeller pitch based on a thrust variation control instruction TCL); a member (105, 105A) for developing a setpoint (RPM*) of the driving speed (RPM) of the rotor and the propeller(s) based particularly on the rotorcraft movement speed (VTAS); and a member (106) for developing a setpoint (NG*) of the engine speed based particularly on the thrust control instruction (TCL), the driving speed setpoint (RPM*) and a control instruction (?o) of the rotor collective pitch. |
