Abstract: A rotor system for an aircraft including a rotor (1) with a drive part (2) mounted rotatable about a rotation axis (8) and supporting the proximal end (9) of at least one rotor blade (3). The rotor system comprises a jet turbine (4) for providing pressurized exhaust gas to a rotary structure (7) having at least one jet nozzle outlet (6) and at least one jet stream duct (5) for transporting the pressurized exhaust gas from the turbine (4) to the jet nozzle outlet (6) to cause rotation of the rotary structure (7) by expelling the pressurized exhaust gas through the nozzle outlet (6). In addition, only the rotary structure (7) and not the rotor blade (3) comprise a jet stream duct (5) and a nozzle outlet (6).

Abstract: In order to suppress induction of precession when the rotor (24, 26) of a helicopter is tilted relative to a fuselage (31), the tilt trajectory is supplemented by transverse components. The helicopter is of the type with a bendable, actuated joint (34) between the rotor and a fuselage. A controller (2) receives an input signal (4) from a steering device (1) and transforms this input signal in an output signal (7) for an actuating system (3) for movement in the joint. The controller calculates on the basis of the input signal an estimation for further input signals, and adds a transverse component to the input trajectory before sending the output trajectory (11).

Abstract: In order to suppress induction of precession when the rotor (24, 26) of a helicopter is tilted relative to a fuselage (31), the tilt trajectory is supplemented by transverse components. The helicopter is of the type with a bendable, actuated joint (34) between the rotor and a fuselage. A controller (2) receives an input signal (4) from a steering device (1) and transforms this input signal in an output signal (7) for an actuating system (3) for movement in the joint. The controller calculates on the basis of the input signal an estimation for further input signals, and adds a transverse component to the input trajectory before sending the output trajectory (11).

Abstract: A rotor system for an aircraft including a rotor (1) with a drive part (2) mounted rotatable about a rotation axis (8) and supporting the proximal end (9) of at least one rotor blade (3). The rotor system comprises a jet turbine (4) for providing pressurised exhaust gas to a rotary structure (7) having at least one jet nozzle outlet (6) and at least one jet stream duct (5) for transporting the pressurised exhaust gas from the turbine (4) to the jet nozzle outlet (6) to cause rotation of the rotary structure (7) by expelling the pressurised exhaust gas through the nozzle outlet (6). In addition, only the rotary structure (7) and not the rotor blade (3) comprise a jet stream duct (5) and a nozzle outlet (6).