Airbus Operations (s.a.s.)

Airbus Operations Gmbh

Jean-Marc Lacoste

David Rousset

A switching device includes at least one main contactor, a control power supply and an actuator configured to cause the main contactor to change from an open to a closed state against a force generated by the spring. The contactor has a blade and at least one terminal, the blade being configured to assume a position in contact with the terminal and a position not in contact with the terminal. The switching device includes a detection system configured to determine the contact or non-contact blade position of the main contactor, to generate at least one second signal as a function of the determined blade position of the main contactor and to transmit the second signal to the control power supply. The control power supply is configured to generate a control signal configured to keep the main contactor in the closed state upon reception of the second signal.

Electromechanical switching device for an electric power circuit comprising at least one system for detecting the contact or non-contact position of a blade of a contactor

An electrical circuit breaker assembly, and a method for its operation, including a conductive element of an electrical circuit and a cut-off device configured to be activated by a pyrotechnic element and that is configured to sever the conductive element in a cut-off zone delimited by a downstream point. The electrical circuit breaker assembly further includes a contactor element configured to be activated by a pyrotechnic element, the contactor element being configured to connect the downstream point of the cut-off zone to an earth conductor of the electrical circuit prior to a severing of the conductive element or simultaneously with the severing of the conductive element.

Pyrotechnic circuit breaker assembly for an aircraft, and an aircraft comprising such an assembly

A switching device including at least one main breaker, an actuator configured to cause a change of state of the main breaker, from a first to a second state, counter to a spring generated force, the actuator being powered by a control signal equal to a first level to cause the change of state of the main breaker then to a second, lower level, to hold the main breaker in the second state. The switching device comprises a current sensor configured to control the control signal to increase it to a third level higher than the second level if the current flowing in the main breaker is higher than or equal to a given operating threshold, to avoid a spurious change of state of the main breaker. The switching device comprises a re-armable protection system for controlling the time for which the control signal is held at the third level.

Electromechanical switching device of an electric power circuit

An aircraft with electric or hybrid propulsion which includes an electrical installation including at least a first electrical network and at least a second electrical network operating at a voltage higher than that of the first electrical network. This second electrical network includes at least an electrical-energy distribution system, at least a reversible electric motor for aircraft propulsion directly or indirectly connected to the electrical-energy distribution system, at least a reversible electrical system directly or indirectly connected to the electrical-energy distribution system, and a safety unit positioned as close as possible to each electric motor and to each reversible electrical system.

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Toulouse, France

Jean-Marc Lacoste