Abstract: A ventilation system for ventilation of an aircraft area includes a ram-air duct with an air inlet, a first ram-air duct branch and a second ram-air duct branch parallel to the first ram-air duct branch. A supply line connected to the ram-air duct is adapted to supply air flowing through the ram-air duct to the aircraft area to be ventilated. In the first ram-air duct branch a conveying device is arranged. In the second ram-air duct branch a heat exchanger of an aircraft system to be supplied with cooling energy is arranged. The ventilation system provides ventilation to the aircraft area during ground operation without requiring the conveying device to flow air through the heat exchanger.

Abstract: A curable assembly which upon the application of curing conditions will form a completed component or part component comprises two pieces of composite fiber-reinforced, resin matrix material, with filler component of relatively rigid material arranged therebetween. The intermediate component is arranged to be secured between the two pieces. The filler component has a body with first and second opposing surface profiles. The filler component can be used to transmit or react a consolidating load during curing.

Abstract: In the case of a fiber composite component for energy absorption in the event of a crash for an aircraft or spacecraft, the fiber composite component is formed as a laminate construction made of CFRP layers and at least one integrated metal foil portion which is corrosion-resistant with respect to the CFRP layers. A fuselage structure portion of an aircraft or spacecraft is formed using at least one fiber composite component of this type. An aircraft or spacecraft comprises a fuselage structure portion of this type.

Abstract: A method of joining a first component to a second component, the method comprising forming an array of projections extending from a bond surface of the first component, the projections having a plurality of different profiles; and embedding the array of projections in the second component formed of a plurality of laminate plies, wherein each projection profile is adapted to best transfer load into a respective one of the laminate plies. The resultant joint is able to transfer load more progressively between the two components leading to improved tensile strength.

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: A flight control system for an aircraft, intended for controlling a plurality of actuators adapted for actuating control surfaces of the aircraft from information supplied by piloting members and/or sensors of the aircraft. The system includes a primary control system adapted for controlling a first set of control surface actuators and a secondary control system adapted for controlling a second set of control surface actuators, the primary and secondary systems being respectively powered by independent energy sources of different types.

Abstract: The invention relates to a production method for producing seamless, integral aircraft fuselage sections. The method comprises the following steps: a) application of a first vacuum film to a stable winding core and evacuation of the first vacuum film, b) depositing of the fuselage section in layers on the winding core by wrapping the same, c) application of an outer mold that is unstable compared to the stable winding core, to the fuselage section, wherein the winding core stabilizes the outer mold, d) application of a second vacuum film to the outer mold, e) aeration of the first vacuum film and evacuation of the second vacuum film in order to draw the fuselage section closer to the outer mold and detach it from the winding core at least in one region, a) curing of the entire arrangement in an autoclave to produce the finished fuselage section.

Abstract: The system includes deflection transmission means (16) to provide a deflection position of the high-lift device (8) for each setting angle position of an adjustable HTP (2). Preferably, the deflection transmission means (18,20,23) comprise essentially of a mechanical linkage connected between the high-lift device (8) and the aircraft (1).

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 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 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: 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: 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: 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: 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 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 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 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: 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.