Abstract: An aircraft nacelle with a connecting device between a first conduit of an air intake and a second conduit of a motor, both conduits being arranged end-to-end, the connecting device including an annular flange connected to the air intake, an annular flange connected to the motor pressed against annular flange of the air intake, the flanges extending in a plane perpendicular to the longitudinal axis of the nacelle; bolt holes formed in annular flanges and disposed plumb to one another; and connecting elements located in bolt holes, for connecting the annular flanges, wherein at least one flange includes at least one opening interposed between a bolt hole and junction zone of the flange and/or between a bolt hole and outer edge of the flange.

Abstract: An aircraft panel, notably a fuselage panel of the aircraft, includes at least one opening equipped with a surround intended to accept a closing-off device that closes off the opening. The panel includes at least one exterior surface. The surround surrounding the opening is fixed to the panel, forming an interface for fitting the closing-off device, and includes at least one lip extending towards the center of the opening. The lip supports the closing-off device. The surround has an external face interposed between the exterior surface of the panel and the closing-off device. The surround includes fixing apparatus which works by gripping the edge of the opening of the panel.

Abstract: Method and system for displaying meteorological phenomena encountered by an aircraft flying along a flight plan. The display system includes a display device configured to present on a screen a meteorological indicator, the meteorological indicator comprising a time line representing a time scale relating to the duration of the flight of the aircraft along the flight plan and, on this time line, a set of first symbols illustrating meteorological phenomena and a second symbol indicating the current instant.

Abstract: A stiffened panel includes a panel at least one of whose surfaces is equipped with stiffeners each of which includes a base that is pressed against the surface of panel, as well as a core that is oriented orthogonally relative to the base and whose first longitudinal edge is integral to the latter. At least one of the stiffeners includes a multitude of notches that cross over a second longitudinal edge of the core opposite the first edge, so that they extend towards the outside of the stiffener.

Abstract: The invention relates to a seat back for an aircraft comprising a structural column bearing a plurality of devices for supporting an occupant of the seat, these devices being distributed along the structural column and oriented transversely relatively to the structural column so as to each protrude on either side of this column. This solution can reduce the mass and dimensions, while providing satisfactory comfort for the occupant.

Abstract: The present invention relates to an aircraft window, of the type including a holding frame for securing the window to the fuselage of an aircraft and at least one pane mounted in the holding frame by a sealing system, the at least one pane having an inner surface and an outer surface, characterized in that: the pane includes, in a first state called the rest state, at least one concavity in its outer surface when there is no pressure difference between the outer surface and the inner surface of the pane, and the at least one concavity of the pane is at least partially eradicated in a second state in which there is a pressure difference between the outer surface and the inner surface of the pane.

Abstract: The object of the invention is an electrical harness having a plurality of electrically conductive elements held one against another in a braided sheath obtained by braiding strands around the electrical conductor elements, the strands being joined and forming a web around the electrical conductor elements when held against each other, wherein it includes a device to space comprising at least one portion with a peripheral surface at the level of which channels are provided wherein an electrical conductor fits, said portion having a section such that it allows to obtain spaced strands at the level of said device to space when the sheath is being braided around the electrical conductor elements.

Abstract: A propulsive system for aircraft that has a jet engine and a nacelle surrounding the aforementioned jet engine. The nacelle has a front section fixed relative to the jet engine, and a rear extremity behind the front section, and has a rear section with two petals hinged relative to the front section. Each of the two petals in a position called zero-setting forms an extension of the front section of the nacelle in which the inside and outside surfaces of the petals and, respectively, determine the aerodynamic forms of the rear section, which are in geometric continuity with the inside and outside surfaces and, respectively, that determine the aerodynamic forms of the front section. The petals can be set individually at a positive or negative setting angle to put into play the reverser, APU, air brake, vectorial, and taxiing modes of the propulsive system.

Abstract: A heating system including an energy supply device, wherein the heating system includes a base heating device having an insulation layer, with an electrothermal base heating layer arranged thereon and with an electrical connecting device by way of which the energy supply device is connected to the base heating layer. The heating system includes an additional heating device having an insulation layer, with an electrothermal additional heating layer arranged thereon and with an electrical connecting device by way of which the energy supply device is connected to the additional heating layer. The energy supply device is connected to the heating layers by way of the connecting devices and in the activation phase, current is supplied during at least a partial period of time to the additional heating layer so that the base heating layer generates heat permanently, while the additional heating layer generates heat in the partial period of time.

Abstract: The wiper blade for a surface of the type with a dual curvature, the wiper blade including a flexible blade element and a means of applying a pressing force to at least one point of the blade element in a direction Z mostly normal to the surface, also including means of varying the pressing force over time, at least some of the points, between pre-chosen positive and negative limit values, and means of commanding the pressing force. These means for bringing about local pressure or lift are electromagnetic.

Abstract: An aircraft nacelle includes a cowling, an engine housed in an internal volume of the cowling, and at least one thrust reverser, an air passage duct being formed between an internal wall of the cowling and an external wall of the engine. The cowling includes a fixed cowling part and a moving cowling part that is translationally movable between a plurality of positions, at least one of the positions varying an air flow through the duct. The moving cowling part includes the at least one thrust reverser so that translational movement of the moving cowling part also allows the moving cowling part to switch from a position in which the at least one thrust reverser is retracted into a reverse-thrust position in which a bypass flow is deflected to generate a reverse thrust.

Abstract: The invention relates to a secure access airlock enabling the communication between several rooms of an aircraft, the secure airlock being installed in an area of the aircraft between a first room and at least one second room, characterized in that it includes two mobile partitions provided in the form of portions of concentric cylinders, each of the partitions being capable of being moved, separately from one another, about a common axis, so as to provide a single opening therebetween which makes it possible to access either of the rooms, the two partitions being capable of moving over two concentric cylinders having different diameters.

Abstract: The aerodyne, e.g. an airplane, includes: an auxiliary power unit suitable for producing electricity; a first electricity distributor connected to the unit; at least one flight propulsion engine including an electricity generator; at least one undercarriage motor, the motor enabling the aerodyne to taxi; and a second electricity distributor connected to the generator and to the undercarriage motor in order to transmit electricity from the generator to the motor independently of the first distributor.

Abstract: Method and device for automatically determining an optimized approach profile for an aircraft. The device provides for a flexible configuration change speed which is not limited to the standard single predetermined configuration change speed in order to prevent segments which are not authorized, in particular segments which are too steep, the following configuration (Ci+1) being able to be maintained during a configuration change in an upstream direction until the corresponding speed profile reaches a maximum speed.

Abstract: A cutting plate includes a planar interface able to accept electrical connectors, two ramps for supporting harnesses and two lateral walls, the dimensions of the interface and of the two ramps in a longitudinal direction being adapted to suit the number of connectors of the cutting plate and the dimensions in the directions other than the longitudinal direction and the dimensions of the lateral walls conforming to standard dimensions.

Abstract: The automatic piloting system includes an element for automatically supplying a computation unit, when the aircraft is guided according to a descending corrected speed and a new corrected speed which is greater than the corrected speed used for guidance of the aircraft is input by the pilot, with a predetermined maximum Mach number which replaces the current Mach number and which is intended to form, together with the new input corrected speed, a pair of speeds which is taken into account by the computation unit for determining the guidance instructions for the aircraft.

Abstract: An aircraft exterior door installation with a door attached to an airframe. A damper is arranged to damp motion of the door as it is opened by rotating it away from the airframe. A coupling mechanism couples the damper with the door over an opening damping range and decouples the damper from the door at the end of the opening damping range. The damper does not damp the motion of the door as it opens beyond the opening damping range. Instead of damping the door over its full range of motion, it is only damped over a limited inner range of its motion. A further advantage of decoupling the door and the damper is that the damper does not need to extend into the airflow to the same extent as the door, thus minimizing aerodynamic drag.

Abstract: Interactive dialog device between an operator of an aircraft and a guidance system of the aircraft. The dialog device includes an interaction on a screen which represents, on the one hand, a playback element indicating the value of a guidance setpoint of the guidance system of the aircraft, and on the other hand, a control element which can be grasped and moved along a curve by an operator to modify the value of the guidance setpoint.

Abstract: A method of testing an electrical junction between a first metallic element and a second metallic element in an aircraft current return network, said network comprising a plurality of metallic elements, each of which is connected to at least two other elements, said aircraft comprising at least one element made of a composite material connected to said network. The method is remarkable in that its use does not damage the composite structure of the aircraft.

Abstract: The invention relates to method for obtaining a part made of a composite of fibers embedded in a resin matrix which comprises a body and an edge. The method comprises a first step of stacking plies of fibers and further comprises a step of curing the plies. The method further comprises prior to the curing step, the step of covering the edge with at least one additional ply, in order to compensate for the migration of the resin during curing.