DASSAULT AVIATION

An aircraft power supply network and associated aircraft, the power supply network includes a first engine and a second engine, a first and a second set of loads, an auxiliary electrical source and a first electrical machine connected to the first engine. The power supply network also includes a first converter connected to the first electrical machine, a first interconnection bus connected to the first converter by a first primary switch and to the first set of loads and a second electrical machine connected to the second motor. The power supply network further includes a second converter, a second interconnection bus, connected to the second converter by a second primary switch and to the second set of loads, a sharing bus connected to the first interconnection bus by a first inter-bus switch, connected to the second interconnection bus by a second inter-bus switch and connected to the auxiliary electrical source.

A method for securing an aircraft video link using a protocol switch is provided. The method includes receiving, from a first domain, an input video data stream using a first video transmission protocol encapsulating data and complementary data, de-encapsulating the input video data stream to extra the image data, filtering at least part of the complementary data, re-encapsulating the image data using a second video transmission protocol to generate an output video stream, and transmitting the output video stream via the second transmission protocol. An associated system and aircraft are also provided.

A method for securing an aircraft video link from a first domain to a second domain, implemented with controlled spatial and temporal parameterization, associated system and aircraft, the method including receiving, from a first domain, an input video data stream according to an input control plane including spatial and temporal parameterization of the input video data stream, transmitting to the second domain an output video stream obtained from the input video data stream, according to an output control plane including spatial and temporal parameterization, and provision, by the security system, of input control plane parameters imposed on the first domain, the imposed input control plane parameters including spatial and temporal input parameterization defined by the security system.

A support device for an aircraft cabin interior layout assembly comprises a fixed frame extending according to a longitudinal direction; and a table comprising a tray deployable relative to the frame between a retracted configuration and a deployed configuration. The tray extends horizontally in the retracted configuration and in the deployed configuration and is displaceable in rotation about a first axis of rotation, substantially parallel, while remaining horizontal between the retracted configuration and the deployed configuration. The tray is displaceable in translation relative to the frame in the longitudinal direction between a first position of use and a second position of use when the tray is in the deployed configuration, while being fixed in rotation about the first rotation axis.

A system for manufacturing a manufactured object by additive friction stir deposition and associated installation includes a stirring device; and an effector including a feed mechanism of the drawn manufacturing material configurable in a first configuration wherein a first gripping member grips the drawn manufacturing material and moves it in a feed direction while a second gripping member releases the drawn manufacturing material and moves in a direction opposite to the feed direction, and a second configuration wherein the second gripping member grips the drawn manufacturing material and moves it in the feed direction while the first gripping member releases the drawn manufacturing material and moves in the direction opposite to the feed direction. The feed mechanism is configured to alternate between the first configuration and the second configuration.

An aircraft rudder pedal includes a frame, a pair of pedals, an output shaft and a mechanical kinematic chain for transmitting to the output shaft a displacement of at least one of the pedals relative to the frame. The mechanical kinematic chain comprises a central transmission part able to be rotated relative to the frame by a displacement of one of the pedals relative to the frame. The mechanical kinematic chain also includes a transmission mechanism joining the central transmission part to the output shaft. The transmission mechanism includes a homokinetic association of two universal joints between said central transmission part and the output shaft.

A piloting device for piloting an aircraft includes a first and a second control stick movably mounted on a support, a detection system for detecting the positions of the first and second control sticks, an elastic mechanism configured to apply a restoring force to the second control stick, first and second actuation systems configured to apply respective first and second position adjustment forces to the respective first and second control sticks, and a control module configured to control the second adjustment force so that the positions of the first and second control sticks are identical. The control module is configured to control the first adjustment force based on the second adjustment force and the restoring force.

includes a wall, mounted at a first or second coordinate, configured to separate first and second cabin portions and a circuit fluidly connecting a source and the second cabin portion. The circuit fluidly connecting a source, and the second cabin portion further includes a pipe, the pipe further including a first section delivering fluid between the first and second coordinates, a second section delivering fluid to the rear of the second coordinate and a control device. The control device is intendent to be in the open configuration or the closed configuration. In the open configuration, the first and second sections are in fluid communication, when the wall is mounted at the first coordinate or the closed. In the closed configuration, the fluid communication is interrupted, when the wall is mounted at the second coordinate.

An aircraft seat structure with tapered base, and associated aircraft cabin, the seat structure includes a frame and a turret arranged above the frame, the turret being mounted rotatably relative to the frame about a vertical axis between a nominal rest configuration. The seat structure is oriented along a main direction and at least one configuration pivoted about the vertical axis relative to the nominal configuration. The seat structure further includes a main displacement carriage, movable along the main direction with respect to the frame and a seat pan support. The main displacement carriage is supported by the turret, being mounted movably in translation relative to the turret along the main direction in the nominal configuration, the main displacement carriage supporting the seat pan support.

A device for holding objects in an aircraft cabin includes at least one interface, intended for being attached to a wall of the cabin, or for being formed in a wall of the cabin, the interface defining an attachment region for the object, the object being suitable for being placed in contact with the attachment region. The object can be rotated over the attachment region between a position for placing the object on the attachment region, wherein the object can be moved away from the attachment region, and an attachment position of the object on the attachment region, wherein the object is held on the attachment region.