Abstract: A command system of an aircraft mobile element actuated by a motor is provided. The command system is electrically connected to a power supply, to the motor and to a current consuming device used to effect de-icing. The system establishes a connection between the motor and the current consuming device and inhibits a first connection between the power supply and the motor and a second connection between the power supply and the current consuming device when a braking command is received. The system enables the first connection and the second connection to be established and inhibits the third connection as long as no braking command has been received or when a command to stop braking is received. Thus the mobile element can be easily braked and the overall size of the system is limited.

Abstract: A two-flow jet engine comprising a high-pressure compressor and a drawing system configured to draw air from said jet engine and send it to an air system, and which comprises a pressurized air supply which draws pressurized air from the high-pressure compressor, a pipe which draws outside air, a turbine of which an inlet is connected to the outlet of the pressurized air supply, and a compressor of which an inlet is connected to the pipe, and an outlet is connected to the air system, and where the rotation of the turbine drives the rotation of the compressor. This particular arrangement makes possible an energy gain by virtue of the combined action of the turbine and of the compressor.

Abstract: An aircraft turbine engine includes a fan duct having a wall; an air passage arranged in the wall and including an air inlet opening at the wall, the air passage being designed to receive part of the flow of air from the fan duct across the opening; an air intake housing located above the air inlet opening and fixed to the wall, the housing being arranged to intercept part of the air flow in the fan duct, and successively including, in the air flow direction, an upstream wall then a downstream wall, an upstream opening and a downstream opening arranged on the upstream wall and the downstream wall, respectively, the inside of the housing being in fluidic connection to the air inlet opening, and a movable sealing means between an “open” position; and a “closed” position relative to the downstream opening and the air inlet opening.

Abstract: A turbomachine for an aircraft comprising a fan duct delimited by a wall and through which an air stream flows from upstream to downstream, and an air passage arranged in the wall comprising an air inlet opening flush with the wall, the air passage being designed to draw part of the air flow of the fan duct through the air inlet opening. To control the amount of air entering the air passage, a flap is rotatably mounted on the wall of the fan duct, about an axis of rotation disposed downstream of the air inlet opening, between an open position, in which the flap partially closes the air inlet opening and leaves free the fan duct downstream of the air inlet opening, and a closed position, in which the flap leaves open the air inlet opening and partially closes the fan duct downstream of the air inlet opening.

Abstract: An aircraft turbine engine includes a fan duct having a wall, ; an air passage arranged in the wall and including an air inlet opening at the wall, the air passage being designed to receive part of the flow of air from the fan duct across the opening; an air intake housing located above the air inlet opening and fixed to the wall, the housing being arranged to intercept part of the air flow in the fan duct, and successively including, in the air flow direction, an upstream wall then a downstream wall, an upstream opening and a downstream opening arranged on the upstream wall and the downstream wall, respectively, the inside of the housing being in fluidic connection to the air inlet opening, and a movable sealing means between an “open” position; and a “closed” position relative to the downstream opening and the air inlet opening.