Publication number: 20100204853
Abstract: The flight control system comprises: at least one actuator (13) for a mobile flight surface of the said aircraft; a flight control module (12) in communication with the said actuator (13), the said module comprising a first and a second computer (14-1, 14-2, 14-3, 15-1, 15-2, 15-3), each computer being adapted for calculating a control command established according to at least one predetermined law for control of the said flight surface; the said first computer (14-1, 14-2, 14-3, 15-1, 15-2, 15-3), known as validating computer, comprising logic means adapted for comparing its control command with that of the said second computer (14-1, 14-2, 14-3, 15-1, 15-2, 15-3), known as master computer, and for transmitting the result of the said comparison to the said actuator (13), the said actuator (13) comprising logic means (18, 19) adapted for deciding, on the basis of this result, to execute or not to execute the command of the master computer. The aircraft comprises such a system.
Type:
Application
Filed:
January 20, 2010
Publication date:
August 12, 2010
Applicants:
Airbus Operations (S.A.S), Le Centre National De La Recherche Scientifique
Inventors:
Manel Sghairi, Patrice Brot, Jean-Jacques Aubert, Agnan De Bonneval, Yves Crouzet