Thrust-reversal device for an aircraft including at least two thrust reversers

摘要

A thrust reverser device for an aircraft includes at least two thrust reversers, and each of them includes a movable cowl movably actuated by an actuator driven by an electric motor. The electric motor is powered by a single power-conversion module including at least one autotransformer which is supplied with an alternating electric voltage and connected to at least one rectifier stage converting the alternating electric voltage into a direct voltage. The rectifier stage is connected to a current balancing stage and a current smoothing stage, supplying with the direct voltage the electric motor of the electric actuator of the movable cowl.

主权项

1. A thrust reverser device for an aircraft comprising at least two thrust reversers, each of said thrust reversers comprising at least one cowl movably mounted between a closing position and an opening position, said cowl being actuated by at least one actuator driven by at least one electric motor, said electric motors being electrically supplied by a single power-conversion module electrically supplied by a single power source of said aircraft,
the single power-conversion module comprising at least one autotransformer supplied with an alternating electric voltage by the single power source of said aircraft and connected to at least one rectifier stage adapted for converting said alternating electric voltage into a direct voltage, said rectifier stage being connected to at least one of a current balancing stage and a current smoothing stage, adapted for supplying with the direct voltage said electric motor of said electric actuator of said cowl, wherein the single power-conversion module comprises one of:
two autotransformers being supplied with alternating voltage by said single power source of said aircraft, each of said autotransformers comprising phase-shifted outputs and connected to at least two rectifier circuits, each of said rectifier circuits of a same autotransformer being connected to a single interphase inductor configured to balance currents and deliver a direct voltage supplying at least one electric motor of an actuator of said cowl,two autotransformers supplied with alternating electric voltage by said single power source of said aircraft, and each of said autotransformers comprising phase-shifted outputs and connected to at least one rectifier circuit, each of said rectifier circuits of a same autotransformer being connected to a coupled DC inductor adapted for smoothing a current and delivering a direct voltage supplying at least one electric motor of the actuator of said cowl, anda single autotransformer supplied with alternating electric voltage by said single power source of said aircraft, said autotransformer comprising two phase-shifted outputs connected to at least two rectifier circuits, each of said rectifier circuits being connected to a coupled DC inductor adapted for smoothing current and delivering the direct voltage supplying at least one electric motor of the actuator of said cowl.