Abstract: A method and device for aiding the piloting of an aircraft during an intermediate approach phase of a descent. The method includes receiving, by a flight management system, values of parameters relative to the aircraft and a flight thereof, and determining, by the flight management system and based on the received values, a vertical profile. The vertical profile includes at least one deceleration segment with an adaptive slope, which defines a descent path that enables the aircraft to hold a constant deceleration rate during the intermediate approach phase. The method also includes guiding, by an aircraft guidance system, the aircraft according to the vertical profile during the intermediate approach phase such that the aircraft holds the constant deceleration rate during the intermediate approach phase.

Abstract: A wing of an aircraft is described, having: a main wing, at least one high lift flap which can be moved between a retracted and an extended position, and a spoiler. The main wing has ejection openings, arranged side-by-side along the main wing spanwise direction, and in the main wing chordwise direction, and which are connected via an air conduit with the outlet device of a flow delivery driver device on the main wing or on the spoiler. The spoiler has inlet openings for the intake of air, which are connected via an air conduit with the inlet device of the flow delivery driver device. The flow delivery driver device has a receiver device for the reception of command signals for purposes of adjustment of the flow delivery driver device. An arrangement of a wing with a device for purposes of flow control with such a wing is also described.

Abstract: The guidance device of the aircraft includes a unit for constructing a flight trajectory of the aircraft, which adapts the height of the flight trajectory to a downstream relief so as to allow the aircraft to clear this downstream relief by implementing a rectilinear climb at maximum rate of climb of the aircraft, along a rectilinear lateral direction corresponding to the direction of the aircraft at the moment of the triggering of the maneuver.

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: A water disinfection system includes a water disinfection device, having a UV light generator for the UV treatment of water, and a water pipe, having a first pipe portion and a second pipe portion and a third pipe portion which branches off between the first and the second pipe portion. The water disinfection device includes a first water connection and a second water connection. The first water connection is connected to the first pipe portion. The second water connection is connectable to a water reservoir which is to be provided. The second pipe portion is connectable to a water source which is to be attached. The third pipe portion is connectable to a tap for water, so as to be able in this way to provide an improvement in the water quality.

Abstract: The invention in particular has as an object methods and devices for automated loading of software, in a piece of equipment such as an aircraft, comprising the updating of the associated documentation. After having received an indication relating to a modification of a software application, a command making it possible to perform the required updating automatically is transmitted to a piece of equipment comprising this software application. In response, an indication relating to the execution of the command is received and a report of execution of the command is transmitted to the manufacturer in order to allow it to update the documentation of the piece of equipment accordingly.

Abstract: A process for the production of a fiber profile (32) that is designed to fill in a space with a nail-head-shaped or half-nail-head-shaped cross-section that originates from the assembly of preforms in a T shape, of which at least one includes a curvature radius at the junction zone of the preforms, includes: supplying powder-coated fibers (28) to a preforming station (30) where the powder is activated and the fibers (28) move into a passage whose shapes are adapted to those of the desired profile, and then making the preformed fibers move into a shaping station (34) where the fiber profile (32) is cooled and shaped by circulating in a cavity whose shapes are adapted to those of the desired profile.

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 security door comprises a frame structure, having a lateral surface in which a plurality of doorways are constructed. A first doorway has a first width along an inner circumference of the frame structure, and lateral surface portions delimiting the first doorway in a first direction and a second direction, opposing the first direction, along the inner circumference of the frame structure have a second width. A lock element is received in the frame structure and comprises a first segment, movable along the frame structure inner circumference relative to the frame structure, and a second segment, movable independently of the first segment along the inner circumference relative to the frame structure. The first segment is dimensioned so that, in a position in which it closes the first doorway, it also closes a second doorway adjacent to the first doorway in the first direction along the frame structure inner circumference.

Abstract: Procedure for the manufacture of a composite part (13) of a closed compartment, said part (13) having an access assembly to said compartment through an opening (11) in said part (13), said access assembly comprising a cover (27) for said opening (11) and a housing panel (25) for said cover (27), comprising steps of: a) providing common laminates (31, 31?, 31?) of a composite material for said cover (27) and said housing panel (25) in an uncured state; b) cutting said common laminates (31, 31?, 31?) by the perimeter foreseen for said cover (27) and separating the cover laminates (33, 33?, 33?) and the housing panel laminates (35, 35?, 35?); c) manufacturing separately, on the one side, the cover (27) using said cover laminates (31, 31?, 31?) and, on the other side, the part (13) together with said housing panel (25) using said housing panel laminates (35, 35?, 35?).

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: Optimizing data updates in an operationally approved software application of aircraft, comprising a first software component using a second software component. Following the receipt of a software component comprising an update of said second software component, said received software component is analyzed and a class of the update of said second software component is determined. Depending on said class, the update of said second software component is transmitted to said first software component and/or to a central download system. If the update of said second software component is transmitted to said first software component, said second software component is updated and a configuration report showing said update is created.

Abstract: An electrical consumer of an aircraft comprises an electric motor and an inverter for producing an alternating voltage for the electric motor. A method for controlling the electrical consumer comprises determining a rotational frequency for the electric motor. The method also includes establishing whether the rotational frequency leads to oscillations in the input current of the inverter which are below a predefined threshold, the oscillations being produced by the inverter when producing a supply voltage for the electric motor, and changing the rotational frequency if it has been established that the rotational frequency leads to oscillations below the predefined threshold.

Abstract: A method and apparatus for manufacturing a composite material part from a preform of fibers pre-impregnated with resin. The method includes laying the preform on a laying surface of a tool with a peripheral shoulder, covering the preform with a conforming plate delimited by a peripheral edge which extends beyond the peripheral flank of the preform over the entire periphery of the preform, using shims calibrated to position the conforming plate, the shims being arranged between the support surface of the peripheral shoulder and the peripheral edge of the conforming plate, removing the calibrated shims, arranging a seal connecting the conforming plate and the tool all around the preform, and polymerizing the preform.

Abstract: A method for the repair of a sandwich plate having a core structure, a top surface layer and a bottom surface layer and a plurality of honeycomb-shaped cells includes providing at least one penetrating drill hole in at least one of the top surface layer and the bottom surface layer above one of the plurality of honeycomb-shaped cells in a damaged region of the sandwich plate, injecting a stabilising material into the honeycomb-shaped cell, and filling the damaged region with a filler material.

Abstract: The invention pertains to an aircraft with at least one passenger cabin that comprises at least one door entry area for the passengers and for the flight attendants that is visually separated from the passenger cabin and referred to as a space unit. Variable or mobile elements assigned to at least one partition wall/one monument of the space element can be arranged in the space unit that can be used as a disposition zone during the flight phase in order to realize working areas or service and/or comfort facilities for passengers or for the flight attendants.

Abstract: An aircraft raceway mounting apparatus comprising an attachment formation for attachment of the apparatus to an aircraft structure, a raceway receiving formation for receiving a raceway, the raceway receiving formation comprising a snap fit formation for retention of a raceway. An aircraft raceway clamping apparatus comprising a concave raceway receiving formation having a raceway support region and a mouth, a bridge member configured to at least partially span the mouth, a clamping member movably mounted to the bridge member to advance into the mouth.

Abstract: An aircraft includes an insulation system for thermal and acoustic insulation. The insulation system includes a cabin, an outer skin, a sound insulating unit, and a heat insulating unit. The sound insulating unit is designed to acoustically insulate the aircraft. The heat insulating unit is designed to thermally insulate the aircraft. The sound insulating unit and the heat insulating unit are arranged between the cabin and the outer skin.

Abstract: An air guiding element for an aircraft air-conditioning system includes a distributing pipe having an air inlet opening arranged in the region of an end face of the distributing pipe and an air discharge opening arranged in the region of a generated surface of the distributing pipe. The air guiding element further comprises a flow diverting element having a first section connected to the air discharge opening of the distributing pipe and a second section arranged downstream of the first section relative to the direction of the air flow through the air guiding element. The second section is configured to deflect the air as it flows through the second section at an angle of approximately 45 to 135° relative to the direction of the air flow through the first section, and a diffuser which is arranged downstream of the second section.

Abstract: A door frame is provided at an opening made in a fuselage of an aircraft that is delimited by a skin. The frame includes an upper longitudinal stiffener and a lower longitudinal stiffener and two vertical substructures, each arranged on one side of the opening, connected by the upper and lower longitudinal stiffeners. The frame also comprises at least one stop provided at the level of the opening that uptakes radial forces exerted by the door. Each vertical substructure comprises at least three walls made of composite material that are connected to one another to form a box substructure having a closed and hollow cross-section in a sectional plane perpendicular to an axis of the length of the vertical substructure.