Minimizing dynamic structural loads of an aircraft

Details Minimizing dynamic structural loads of an aircraft Minimizing dynamic structural loads of an aircraft

G - Physics

05

D

G05D 1/00 (2006.01)

Patent

CA 2637990

Minimizing dynamic structural loads of an aircraft (2), introduced by an external excitation (1 ), which, comprises generating a signal (x) indicative of the external excitation (1 ); deriving signals (y) of pre-controlling for actuating control elements of the aircraft (2) from said excitation indicating signal (x) in accordance with a pre-controlling rule, so as to reduce the dynamic structural loads introduced to the aircraft (2); generating an error signal (e, e*) representing performance of said pre-controlling; optimizing the pre-controlling rule by said error signal (e, e*) and/or said excitation indicating signal (x) so as to minimize the dynamic structural loads.

La présente invention se rapporte à un procédé permettant de réduire au minimum les charges structurelles dynamiques exercées sur un aéronef (2) par une excitation externe (1). Le procédé selon l'invention consiste : à générer un signal (x) donnant une indication sur l'excitation externe (1) ; à dériver, dudit signal d'indication d'excitation (x), des signaux (y) de commande préalable permettant d'actionner des éléments de commande de l'aéronef (2), conformément à une règle de commande préalable, de manière à réduire les charges structurelles dynamiques exercées sur l'aéronef (2) ; à générer un signal d'erreur (e, e*) représentant l'efficacité de ladite commande préalable ; et à optimiser la règle de commande préalable à l'aide dudit signal d'erreur (e, e*) et/ou dudit signal d'indication d'excitation (x), afin de réduire les charges structurelles dynamiques au minimum.

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