Method and device for controlling a rotary wing aircraft

Method for controlling a rotary wing aircraft with at least one main rotor, comprising a rotor head and rotor blades (12), arranged such that each rotor blade (12) is supported to be able to pivot or twist around the lengthwise axis of its blade on the rotor head and has at least one control flap (14) that can be deflected, the rotary wing aircraft being controlled only by changing the respective blade pitch angle (X) by means of changing the flap angle (Y) of the assigned control flaps (14) by the resulting blade pitch angle (X3) being set by applying the resulting flap angle (Y4) to the control flap (14) and the resulting flap angle (Y4) being computed using an algorithm, the input quantities comprising the flap control angle (Y1) depending on the pilot primary control and the flap correction angle (Y2) depending on the secondary control, characterized in that periodic actuating signals are generated to check the rotor integrity, wherein the secondary control comprises a secondary regulator (24) that suppresses blade flutter and/or reduces dynamic loads and blade vortex interferences.

Method for controlling a rotary wing aircraft with at least one main rotor, comprising a rotor head and rotor blades (12), arranged such that each rotor blade (12) is supported to be able to pivot or twist around the lengthwise axis of its blade on the rotor head and has at least one control flap (14) that can be deflected, the rotary wing aircraft being controlled only by changing the respective blade pitch angle (X) by means of changing the flap angle (Y) of the assigned control flaps (14) by the resulting blade pitch angle (X3) being set by applying the resulting flap angle (Y4) to the control flap (14) and the resulting flap angle (Y4) being computed using an algorithm, the input quantities comprising the flap control angle (Y1) depending on the pilot primary control and the flap correction angle (Y2) depending on the secondary control, characterized in that periodic actuating signals are generated to check the rotor integrity, wherein the secondary control comprises a secondary regulator (24) and the rotary wing aircraft further includes an automatic flight control systems AFCS (26), wherein the secondary regulator (24) and/or the AFCS (26) work according to regulation processes of the H∞ or “least-mean-square method” or according to disturbance rejection by means of notch filters.