MECHATRONIC SYSTEM FOR CONTROLLING AN AIRCRAFT ENGINE FAILURE

Abstract

A mechatronic system (1) tolerant to a single electrical failure of a hybrid-electric or electric aircraft machine, said mechatronic system (1) comprising an electric machine (2) and at least two electronic circuits (3a, 3b) each comprising at least one energy accumulator (5a, 5b) and at least one converter (7a, 7b) positioned downstream of the energy accumulator (5a, 5b), the electric machine (2) being connected to the aircraft engine and to the electronic circuits (3a, 3b). The electronic circuits (3a, 3b) each include at least one electrical fault symmetrization element (8a, 8b) comprising at least one phase signal (a, b, c, a', b', c') fault symmetrization branch at the output of the converter (7a,7b) connected to an associated phase (A, B, C, A', B', C') of the electrical machine (2), the electrical machine (2) comprising at least two magnetically independent three-phase stars (4a, 4b).Figure for the abbreviation: Fig 2.