Patent ID: 8255096

Claim:
A method of minimizing dynamic structural loads of an aircraft, introduced by an external excitation to the aircraft, comprising: generating a signal (x) indicative of the external excitation by a first sensor located in the aircraft, the first sensor measuring the external excitation; deriving signals (y) of pre-controlling for actuating control elements of the aircraft from said excitation indicating signal (x) in accordance with an adjustable pre-controlling rule, so as to reduce the dynamic structural loads introduced to the aircraft; generating an error signal (e, e*) by a second sensor located in the aircraft, said error signal (e, e*) indicative of structural loads of the aircraft structure and representing performance of said pre-controlling; and optimizing said adjustable pre-controlling rule by said error signal (e, e*) and/or by the excitation indicating signal (x) so as to minimize said error signal (e, e*) and thereby the dynamic structural loads.