A differential flatness approach for rotorcraft fault detection

The purpose of this communication is to investigate the usefulness of the differential flatness theory of a non linear system such as a four rotor aircraft to design an efficient fault detection scheme. The flight dynamics equations of a four rotor aircraft as well as the dynamics of the engines controlling the rotors are introduced. Then the differential flatness of the rotorcraft flight dynamics is displayed and finally a fault detection scheme, based on the differential flatness property, is proposed.