Airbus Operations (s.a.s.)

Airbus France

Airbus Operations Gmbh

David Rousset

Jean-Marc Lacoste

Arnaud Davy

Laurent Peyras

Olivier Raspati

Vincent Rebeyrotte

Stephane Ortet

Guillaume Bonnet

Thomas Jomier

Stéphane Ortet

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

Use of a hydrogen tank of a vehicle such as an aircraft for protecting at least one electrical connection device linked to at least one electrical device. At least one connection device is placed in a tank or in a sealed enclosure supplied with hydrogen by a tank or by any other source of hydrogen supply of the vehicle. The use of a tank that already exists in the vehicle makes it possible to avoid having to use specific chambers incorporated in a complex manner with the connection device.

Vehicle provided with a hydrogen tank, containing at least one electrical connection device

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.

Aircraft with electric or hybrid propulsion comprising a suitable electrical installation

To produce an insulated current sensor for slaving power devices in the field of avionics, use is made of a magnetic core through which there passes an element traversed by a current to be measured. The magnetic core comprises a secondary winding across the terminals of which are connected an oscillator and a measurement device. The cooperation of the oscillator and of the measurement device makes it possible to circumvent all the traditional drifting of current sensors.

Current sensor

A method of managing an electrical power supply outage on board an aircraft, including the following operations: &#x2014;detection of an electrical power supply outage, &#x2014;measurement of a duration of the power supply outage by measuring a discharge time of a capacitor and comparing this measured duration with a threshold duration, &#x2014;saving a long outage indication when the duration of the outage is greater than a threshold duration. The disclosed embodiments also relates to a system implementing this method and including: &#x2014;a circuit for detecting an electrical power supply outage, &#x2014;a circuit for measuring a duration of the power supply outage, and&#x2014;a circuit for managing indications able to manage emissions of signals according to the measured duration of the power supply outage.

Method and system for managing electrical power supply outages on board an aircraft

A device for balancing power generators, including a plurality of converters each including an elementary conversion cell with a switch driven by a comparator that receives a ramp on one input thereof and, on another input, a voltage from a driving amplifier wherein the driving amplifiers receive on their negative input an image of the cell current and have their positive input connected to an adjustment loop including a common path CS_Bus, and wherein the CS_Bus path directly connects the positive inputs of the driving amplifiers to the outputs of transconductance amplifiers associated with the elementary conversion cells.

Device for balancing the power supplied by power generators

An electronic card that includes at least two superimposed conducting layers with an insulation layer between the two conducting layers, the two conducting layers each including a utility conducting portion and a conducting portion at the periphery of the utility conducting portion with an insulating portion between the conducting portions, the insulating portion of a first of the two layers being offset relative to the insulating portion of the second of the layers. An aircraft includes a housing in which at least one such card is provided.

Electronic card and aircraft including same

A safety device for a semiconductor switch controlling a secondary line provided with a fuse on the input side of the switch device that includes component to create a short circuit in the secondary line, so as to cut off the fuse, and means of activating this component following detection of an overcurrent in the secondary line.

Safety device for a semiconductor switch

A device for controlling an electromechanical actuator includes an electric motor and an actuator operated by the electric motor. It also includes a digital signal processor (DSP) providing data of reference voltages (Ud, Uq) on the basis of an decoupled electrical model of the motor. The processor has at least one Park transformation module receiving measurement data for the currents of at least two supply phases of the motor (i_mot, i_mot) and a datum for the estimated angle of the motor (&#x3b8;) and transforming them into data regarding the component of current with stator current axis (id) and the component of current in quadrature with the stator current (iq).

Growing community of inventors

Toulouse, France

David Rousset