28th Congress of the International Council of the Aeronautical Sciences, 23 - 28 September 2012, Brisbane, Australia
Paper ICAS 2012-5.1.2

FAULT DETECTION AND RECONFIGURATION APPLIED TO A HELICOPTER SWASHPLATE ACTUATOR

T. Rakotomamonjy, D. Tristrant, A. Cabut
ONERA, France

Keywords: helicopter, fault diagnosis, reconfigurable control, swashplate

Using a kinematics model of a helicopter main rotor swashplate, an actuator fault has been numerically simulated and successfully detected using a PCA performed upon flight variables. Then, a method for the reconfiguration of the nominal control law is proposed, based on the minimization of a quadratic criterion.

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