Patent ID: 7258307

Claim:
A damping system for damping at least one of at least one rigid body mode of an aircraft and at least one elastic mode of the aircraft for at least one of blast load reduction, increase of stability and increase of comfort in an aircraft, the aircraft having thereon at least one of a controlling surface, a guiding surface and a regulating surface, at least two of the controlling surface, the guiding surface and the regulating surface being formed by at least one of an aileron, a rudder and a spoiler of the aircraft, the damping system comprising: a sensor positioned in the aircraft to detect a lateral force experienced by the aircraft and to generate a sensor signal relating to the lateral force; a controller connected to the sensor to receive the sensor signal and operable responsive to the sensor signal to modify the at least one of the at least one rigid body mode and the at least one elastic mode of the aircraft; and an actuator connected to the controller and operable to receive controller signaling from the controller and responsive to the controller signaling to control and to modify the at least one of the controlling surface, the guiding surface and the regulating surface of the aircraft, wherein the controller comprises a respective resonance filter for each of the at least one rigid body mode and the at least one elastic mode to be modified, and each resonance filter comprises at least two phase correcting units operable to generate the controller signaling comprising at least two feedback signals for moving the at least two of the controlling surface, the guiding surface and the regulating surface for damping at least one of the at least one rigid body mode and the at least one elastic mode of the aircraft.