Abstract: The invention relates to an assembly for a turbomachine, comprising: —a nacelle comprising an inlet lip which defines an air inlet, and—a device for modifying the geometry of the air inlet, comprising: —a first spout, and—a second spout, the first spout and the second spout being translatably movable in relation the nacelle between: —a first configuration, in which the first spout forms the inlet lip and the second spout extends inside the nacelle, and—a second configuration, in which the first spout extends away from the inlet lip, and the second spout forms the inlet lip so as to define an air flow channel between a downstream surface of the first spout and an upstream surface of the second spout.

Abstract: An aircraft includes a fuselage carrying a nacelle of the aircraft offset relative to a wing of the aircraft. The nacelle forms an air inlet fairing of a propulsion assembly. The nacelle includes a lower wall and an upper wall delimiting together a height of the nacelle. The lower wall includes an air inlet edge being contiguous with a trailing edge of the wing.

Abstract: Vibration absorbing device comprising a housing (12), a membrane (14) enclosed in the housing (12) and thus forming two chambers (18a, 18b) in the housing (12), said chambers (18a, 18b) being filled with a fluid, at least one weight (16), arranged on the membrane (14) in order that a movement of the weight (16) causes a movement of the membrane (14), and at least one duct (24) arranged to permit the fluid to flow between the two chambers (18a, 18b) if the membrane (14) and the weight (16) move.

Abstract: The invention relates to an assembly for a turbomachine, comprising: —a nacelle comprising an inlet lip which defines an air inlet, and—a device for modifying the geometry of the air inlet, comprising: —a first spout, and—a second spout, the first spout and the second spout being translatably movable in relation the nacelle between: —a first configuration, in which the first spout forms the inlet lip and the second spout extends inside the nacelle, and—a second configuration, in which the first spout extends away from the inlet lip, and the second spout forms the inlet lip so as to define an air flow channel between a downstream surface of the first spout and an upstream surface of the second spout.

Abstract: An aircraft includes a fuselage carrying a nacelle of the aircraft offset relative to a wing of the aircraft. The nacelle forms an air inlet fairing of a propulsion assembly. The nacelle includes a lower wall and an upper wall delimiting together a height of the nacelle. The lower wall includes an air inlet edge being contiguous with a trailing edge of the wing.

Abstract: A method for transmitting data packets through a random-access (RA) transmission channel shared by a plurality of user terminals uses and exploits a function F for assigning and distributing transmission resources F(u) to the user terminals, knowledge of the graph of which is shared by the sending user terminals and the receiving station in a preliminary step. During the decoding of the received packets, the graph {(u, F(u)} of the assigning and distributing function is exploited by the receiving station to minimize, or even to decrease to zero, the number of replica-location correlations required in case of failure of the conventional CRD-SA protocol decoding process.

Abstract: The disclosure provides methods for managing an automated system having a display and adapted to be controlled by a human operator and by at least one automatic controller. The methods include triggering a condition associated with a parameter of the automated system, displaying the parameter on the display in a first display zone, automatically changing the automatic controller between a first state and a second state subsequent to the triggering the condition, displaying the second state on the display in a second display zone, detecting, by a gaze tracking device of the human operator and after displaying the parameter and displaying the second state, a plurality of viewed zones of the display that are viewed by the human operator within a predetermined time interval, and verifying whether the plurality of viewed zones comprises at least the second display zone and the first display zone.

Abstract: Satellite navigation device having an architecture which uses, in parallel, an estimator based on scalar tracking and an estimator using vector tracking. As such, it is possible to compare the results given by the two estimators. In the case of a divergence between the two estimators, a study of the divergences makes it possible to determine contamination of the navigator or certain scalar channels and to modify the parameters of the navigator so as to keep a reliable measurement of the position.

Abstract: An aerial micro-drone having a fixed wing supporting a propulsion device. The micro-drone has wheels for traveling on the ground, which are attached to the side ends of a section of the wing. The rotational axis Y1 of the wheels is located in front of the center of gravity of the micro-drone. The center of gravity of the micro-drone is located in front of the aerodynamic center of the micro-drone. The rotational axis Y1 of the wheels being aligned with the thrust axis of the propulsion device and the wheels are sized such that the radius D/2 thereof is greater than the distance between the rotational axis Y1 of the wheels and the trailing edge of the wing.

Abstract: A microscale radio-controlled aerial micro-drone vehicle, having a fixed wing (as opposed to a rotary wing) having a propulsion device the vehicle including wheels for traveling on the ground, which are attached to the side ends of a section of the wing. The rotational axis Y1 of the wheels being located in front of the center of gravity of the micro-drone, the center of gravity of the micro-drone being located in front of the aerodynamic center of the micro-drone. The rotational axis Y1 of the wheels being aligned with the thrust axis of the propulsion device and the wheels are sized such that the radius D/2 thereof is greater than the distance between the rotational axis Y1 of the wheels and the trailing edge of the wing.