Messier-bugatti-dowty

Centre National De La Recherche Scientifique

Messier-bugatti Inc.

Universite Dé Lorraine

Safran Landing Systems

François-Noël Leynaert

Florent Nierlich

Eric Evenor

Daniel Bucheton

Pierre-Yves Liegeois

Farid Meibody-Tabar

Etienne Annee

Guillaume Durand

Serge Lionel Pierfederici

Babak Nahid Mobarakeh

Marc Quenerchdu

Raphaël Pierrat

Marc QUENERCH`DU

The invention relates to a method of limiting a current isupplied by a DC power supply, the method comprising: is calculated in which i is a current that is an image of the power supply current i, the averaged quantity being reset to zero at the beginning of each period, with the switch being caused to be closed so long as said averaged quantity remains below a predetermined current threshold i, and with the switch being caused to be open, otherwise.

Method of limiting a current supplied by a DC power supply

The invention relates to an actuator including an electrical machine. The electrical actuator () comprising: a polyphase machine (); at least one connection member () for powering the actuator from at least one network () delivering alternating current; and first and second buses () connected in parallel between each connection member () and the machine () for applying frequency control thereto. Each inverter () comprises a plurality of arms each having two controlled switches, each phase of the machine () being connected both to the two switches of an arm of the first inverter () and also to the two switches of an arm of the second inverter (). The actuator further comprises controlled connection and disconnection means interposed between each bus () and each connection member. The invention is applicable to actuators used in aviation.

Electric actuator including two current-controlled voltage inverters powering an electrical machine, and reconfigurable in the presence of a defect

The invention relates to an aircraft undercarriage including a steerable bottom portion and a steering member suitable for turning the steerable bottom portion in response to a steering order. According to the invention, the steering member comprises a plurality of electromechanical steering actuators each having at least one main electric motor, and the actuators are disposed on the undercarriage so as to enable all of them to co-operate simultaneously with the steerable bottom portion in order to steer it, each of the electro-mechanical steering actuators including controllable coupling means for selectively placing the actuator either in a coupled state in which it is coupled with the steerable bottom portion , in which the main electric motor of the actuator is suitable for causing the steerable bottom portion to turn; or else in an uncoupled state in which it is uncoupled from the steerable bottom portion and in which the main electric motor of the actuator is isolated from the steerable bottom portion.

Aircraft undercarriage including a plurality of electromechanical actuators, and a method of testing it

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Montmorency, France

François-Noël Leynaert