System and method for compensating structural vibrations of an aircraft caused by outside disturbances

Abstract

A method for compensating lateral - anti-symmetric and longitudinal - symmetric structural vibrations of an aircraft caused by turbulence, gust, wind blasts, wake penetration and buffeting in flight is presented. The method includes the steps of detecting the structural vibrations by a novel measurement technology using pitch, roll and yaw rates determined by an inertial sensing system. The noval measurement supplying the determined disturbing values to a flight control system, producing phase- and amplitude-correct control flap movements by generating appropriate control signals in respective control drives to counteract the phases and amplitudes of the excited vibrations. The design requirements especially the elastic mode stability criteria are described. For the symmetric mode alleviation additional means for improvement using high frequency trailing edge split-flap flight control system control laws are outlined. Also lateral vibration alleviation using rudder and trailing edge flaps is described.