Safran Electrical & Power

Safran Aircraft Engines

Safran

Benoit Michaud

Philippe Delbosc

Alexis Renotte

Cyrille Gautier

Anthony Gimeno

Laurent Cartailler

Anne Lienhardt

Samir Nehme

Rémi Goncalves

Udo Muller

An electric architecture for a twin-engined, hybrid thermal/electric propulsion aircraft and, for each turboshaft which includes a high-voltage DC propulsive electric distribution network, a non-propulsive electric distribution network which is connected to loads of the aircraft, and an electric distribution network which is connected to loads of an electrified control system of the turboshaft engine, and wherein power supply sources are shared for these different networks.

Electric architecture for a hybrid thermal/electric propulsion aircraft and twin-engined aircraft comprising such an architecture

Overvoltage protection device for a variable-speed and constant-frequency electrical energy generation system includes at least one DC current generator connected, via a DC current bus to the input terminals of at least one inverter and to at least one regulation module for regulating the output voltage of the at least one inverter. The device includes a circuit including at least one switch in series with a resistor, the circuit being connected between the input terminals of the at least one inverter, at least one measurement sensor for measuring the DC voltage across the input terminals of the at least one inverter, a control circuit connected to the at least one measurement sensor and able to receive a voltage measured by the at least one measurement sensor, compare the measured voltage against a threshold and command the closure of the at least one switch if the measured voltage is greater than the threshold, and command opening thereof if not.

Overvoltage protection for a variable-speed and constant-frequency electrical energy generation system

A method for controlling a system for generating electric power for a power distribution network of an aircraft, the system for generating electric power comprising a generator, a rectifier, an inverter which produces a voltage according to several fixed-frequency phases, a DC voltage bus which connects the rectifier to the inverter, the control method comprising: &#x2014;a correction step to determine at least one correction quantity GC, &#x2014;a step of determining a signal SO for controlling the inverter from the determined correction quantity GC, &#x2014;a step of determining a signal SG for controlling the generator from the determined correction quantity GC and &#x2014;a step of transmitting the control signals SO, SG to the inverter and to the generator, respectively.

Method for controlling a system for generating electric power for a power distribution network of an aircraft

A system for dissipating regenerated electric energy produced by an electric actuator of an aircraft, the dissipating system including: a resistor; two switching arms, each switching arm being connected in series with the resistor, the two switching arms being connected together in parallel, each switching arm including two switches connected to one another in series, each switch including two terminals and a control grid, each switch being capable of being controlled by controlling the potential applied to the control grid thereof; and a measurement system capable of measuring the voltage at the terminals of each switch.

System and method for dissipating electric energy regenerated by actuators

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Moissy-Cramayel, France

Benoit Michaud