Aircraft comprising a device for influencing the directional stability of the aircraft, and a method for influencing the directional stability of the aircraft

A method for influencing directional stability of an aircraft, which method comprises:

• inputting control specifications for controlling a flight path of the aircraft, acquiring rotation rates of the aircraft, from control commands and the rotation rates generating adjusting commands for actuators for moving control flaps of the aircraft for controlling the aircraft, and
• transmitting said adjusting commands for adjusting said control flaps, on the basis of rotation rates about a z-axis of the aircraft acquired by the sensor device, the control function generating commands for actuating of at least one of the tail-mounted flaps such that for lateral control of the aircraft a moment about the z-axis of the aircraft is effected and transmitting the commands to said actuator for actuating the tail-mounted flaps, wherein as a result of a deflection of at least one of the tail-mounted flaps, additional drag is generated which in turn generates the moment about the z-axis of the aircraft.

A method for attenuating the effect of wind gusts that act on an aircraft, the method comprising:

• acquiring at least one of rotation rates and accelerations of the aircraft in a predetermined period of time,
• identifying a wind gust that acts on the aircraft by a comparison function that compares any rise or change or increase in the rotation rate of the aircraft on its vertical axis in a predetermined period of time with a predetermined limit value, and, if this limit value is exceeded, identifies the presence of a wind gust in response to which a countermeasure needs to be ordered, and
• generating adjusting commands to the actuators of tail-mounted flaps to compensate for at least one of the rotation rates and accelerations that occur as a result of the identified wind gust, which at least one of the rotation rates and accelerations act on the aircraft, wherein as a result of a deflection of at least one of the tail-mounted flaps, additional drag is generated which in turn generates a moment about a z-axis of the aircraft.