Abstract: A propulsion unit comprises a turbojet engine and a thermal exchanger, situated above the turbojet engine. The turbojet engine comprises a regulation device to regulate an air flow-rate in a cooling air lead-in conduit conveying a stream of cooling air into a thermal exchanger, The regulation device regulates the air flow-rate upstream with respect to the cooling air lead-in conduit.

Abstract: A device and method for assisting in the management of an engine failure on an aircraft: (1) determine, when an engine failure occurs, flight profiles allowing the closest airports to be reached according to flight strategies and (2) present, on a screen, the airports associated with the determined flight profiles and corresponding predictions.

Abstract: An aircraft device includes a rudder, a control unit that applies a deflection instruction to the rudder, a measuring section that measures a recovery characteristic of aircraft movement in response to the rudder deflection instruction, a recorder that records an applied deflection instruction and a corresponding recovery characteristic, and a servo-control that maintains the recovery characteristic. The control unit receives a recovery instruction for a recovery characteristic, which is identifiable for an aerodynamic effect, and generates the rudder deflection instruction induced by the recovery instruction.

Abstract: The device for flying an aircraft includes a first unit for determining a control value corresponding to an instruction value representing the actuation of a control member by a pilot, a second unit for determining an effective control value corresponding to the instruction value which is actually applied to the aircraft, a third unit for automatically controlling the aircraft, a fourth unit for computing an auxiliary control value, which is closer to the effective controlled value, and a fifth unit for monitoring the control value and for detecting a pilot induced oscillation, where the automatic control is carried out with the aid of the controlled effective value and the auxiliary control value in the case of the detection of the pilot induced oscillation.

Abstract: The invention relates to a method for producing an audible warning when an aircraft autopilot is deactivated. The method includes a) transmitting a first sound in the aircraft cockpit during a time ranging from a first predetermined value and a second predetermined value and b) transmitting a second sound in the aircraft cockpit. The invention also relates to an audible warning device having a monitoring unit for monitoring the deactivation of the aircraft autopilot and an activation unit for emitting an audible warning in the cockpit, where the activation unit is constructed such that it activates the first sound emission whose length ranges from the first predetermined value and a second predetermined value and a second sound when the monitoring unit detects the deactivation of the autopilot.

Abstract: A device for measuring the flow speed of a fluid as well as its direction and its orientation, based on a thermal-sensor measurement principle, that comprises at least three flow measurement probes each having a sensitive member and an obstacle masking a predetermined measurement area of the sensor, characterized in that the flow measurement probes are attached on carrier posts, the carrier posts defining the obstacles that form masking members for an angular sector of the flow measurement probes facing the sensitive member of the probes.

Abstract: A slinging device for a piece includes a sling with a nonextensible part and a section with a spring device, enabling an elastic lengthening or shortening of the sling under load by a limited amplitude in response to a limited change in the load on the piece, the device including a frame and a floating support, the spring device holding the floating support in the absence of application of force to the piece along a vertical axis, in a position of equilibrium centered vertically with respect to the frame under the weight of the piece, and a way for regulating and adapting the position of equilibrium of the floating support depending on the weight of the piece.

Abstract: A system and a method for data transmission between at least one display screen and a remote client system. A first request to send a message via a first communication protocol is caused to be displayed on the display screen, and the message is transmitted to the remote client system via a second communication protocol. A control unit monitors the remote client system. The system induces the generation, and display on the display screen, of a request for confirmation of the first request, by the intermediary of a communication interface, which interface is designed to receive and generate messages in the first communication protocol, as well as to receive and generate messages suitable for being received by the control unit.

Abstract: A method for determining the total temperature of the air stream surrounding an aircraft, including the following operations; measuring a parameter of static temperature, measuring a parameter of total temperature, determining a value of speed of the air stream, determining a total temperature computed from the parameters of measured static temperature and measured total temperature as a function of the speed of the air stream.

Abstract: A device for suspension of an engine, configured to be inserted between an aircraft wing and the engine. The device includes a rigid structure and a forward aerodynamic structure mounted fixed on the structure through a suspension mechanism. The forward aerodynamic structure is configured to carry engine fan casings and to be inserted between the rigid structure and the wing. The suspension mechanism includes at least one adjustable length connecting rod of which one end is mounted on the rigid structure, and the other end is mounted on the forward aerodynamic structure.

Abstract: A device for managing an awakening phase, in flight, of a pilot in the cockpit of an airplane, following a rest period, to guarantee his or her return to a state estimated compatible with flying operations, also called state of vigilance, wherein it includes management means for inducing progressive physical stimuli for generating an awareness by the resting pilot that his or her rest period is over, starting a procedure in the form of actions to be carried out by the pilot, means for displaying the procedure drawn up by the management means. The management device includes a warning device in case a state of hypo-vigilance is detected in the pilot, which is activated when the pilot is assumed to be in a state of vigilance.

Abstract: The method of the invention includes forming a difference between left and right braking commands, by converting the difference into an additional control command for rudder and for a steerable nose gear, and applying the additional control command to the rudder and steerable nose gear according to both of the following conditions: the difference is greater than a first threshold and the combined control command transmitted to the rudder and steerable nose gear by a rudder bar is less than a second threshold.

Abstract: The inventive fixing system comprises a front attachment (6), a rear attachment (7) and an intermediate attachment (8) connecting a strut (1) to a wing (2), wherein the lower fitting (17) of the rear attachment (7) is fixedly connected to the transversal rear face (1 G) of said strut on the extension thereof and said lower fitting (17) is substantially in flush with the top face of the strut.

Abstract: An engine mount for an aircraft engine. The engine mount includes a rigid structure forming a box closed at its forward end by a forward closure rib, and a mounting system including a forward engine attachment having an attachment body fixedly mounted on the rigid structure. The attachment body lies against a forward surface, and the engine mount includes at least one shear pin passing at least in part through the attachment body and forward closure rib.

Abstract: A system determines a limit angle of climb corresponding to a climb angle of an aircraft for flying over the ground along an avoidance path and displays a characteristic sign representing the limit angle of climb on a display screen.

Abstract: The invention concerns an electrical cabinet (1) including a housing (2), a door (3) and a hinge (4). The housing and the door support electric wires which are each routed from an electrical component located inside an electrical equipment compartment (11) formed by the housing towards the outside of the compartment to be connected to a corresponding electrical connector (17). Therefor, according to the invention the electric wires are routed through the hinge which is itself connected to the electrical connector. The hinge forms at least one passage orifice (18, 19) guiding, the electric wires from inside the compartment towards the outside of the compartment while directing them towards the electrical connector.

Abstract: A hinge device of a nacelle cowling of an aircraft engine on a supporting structure is disclosed. The hinge device includes two fittings and a link rod connected thereto and mounted on the fitting by an end connection. The link rod is further mounted on the fitting by an intermediate connection including a pivot pin slidably housed in a hole, and the end connection includes a guide pin slidably housed in a guide ramp. The connections are designed so as to create, upon rotation of the link rod about the pin, a relative movement of the axis in the ramp, simultaneously causing a relative movement of the pin in the hole.

Abstract: An engine attachment pylon for an aircraft including an aft engine attachment fitted with an aft attachment body and two lateral brackets each including a longitudinal portion in contact with an inner face of the lateral panel associated with it and mounted fixed on the same inner face, and a transverse portion including an attachment interface for the aft attachment body, the transverse portion configured to pass through a recess formed on the associated lateral panel.

Abstract: A landing assistance device and method for an aircraft according to the invention, based on the landing procedure rules attached to the runway, a lower threshold and an upper threshold of total energy acceptable for the aircraft are determined and the current total energy of the latter is compared with the thresholds.

Abstract: 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.