Abstract: According to the invention, fresh air at the turboprop outlet is captured and mixed with the warm airflow created by said turboprop to lower the temperature, via a device having a tubular sleeve able to slide into the tubular duct while hot gases flow therethrough and which can switch from an inner position to a projecting position.

Abstract: This invention relates to an on-board information system, including a central processing unit; a first non-rewritable memory containing a boot program; a volatile memory; and a second non-rewritable memory containing an operating system as well as a set of executable files. The boot program is configured to load the operating system and at least a portion of the executable files into the volatile memory when the on-board information system is initialized.

Abstract: A unit includes a glidepath aerial and a support organ designed to be mounted on the front landing gear of an aircraft, with the landing gear forming an electrically conductive ground plane. The aerial is mounted on the support organ and is electrically insulated from this support organ by insulating elements. The support organ has a longitudinal dimension at least equal to around one quarter of the wavelength ? at which the aerial functions, so that the distance separating this aerial and the ground plane is greater than ?/4, and the aerial also has a transmission line designed to connect the aerial to a receiver in the aircraft. The transmission line is surrounded by an electromagnetic shielding element serving as a faradization screen for the transmission line, and designed to be electrically connected to the ground plane.

Abstract: According to the invention, a plurality of embossments (20) having a rectangular section is provided at the inner periphery of the outlet opening (7) of the fan duct (12), said embossments being separated by longitudinal channels (21) having a convergent (22C) and a divergent (22D) for the cold flow (9).

Abstract: An indirect optical free-space communications system provides broadband transmission of high-speed data in transportation vehicles such as aircraft. The system includes a transmitter with a light source that can be modulated and a receiver with a photo detector, adapted to receive light that is emitted from the transmitter and to convert it into an electric signal. The transmitter and the receiver are directed onto at least one common surface, which reflects the light emitted from the transmitter before it reaches the receiver. The free space communications system is cellular and includes several cells, each of which has a transmitter and at least one corresponding receiver. The cells are configured in such a way that crosstalk with a respective adjoining cell is prevented. The cells are thus independent of one another.

Abstract: According to this invention, artificial force gradient means (9a) of a throttle control lever (4) for a turbo-engine comprise means (17) for adjusting the intensity of the artificial force gradient.

Abstract: An aft part of an aircraft, including at least one engine assembly including a turbine engine and a turbine engine mounting pylon. A rigid structure of the mounting pylon includes a longitudinal central box and a connection box carried by the box and projecting from the box. The aircraft structure includes a fuselage lateral extension projecting from it, and the connection box is pressed into contact with the fuselage extension, below it, an attachment mechanism being arranged between these two entities.

Abstract: A connecting device having two curved ribs of an aircraft or spacecraft, with: a coupling element which can be connected by means of predetermined coupling sections to respective connecting sections of the two ribs; wherein at least the predetermined coupling sections of the coupling element are rectilinearly designed; and wherein at least the respective connecting sections of the two ribs each have rectilinearly running inner belt regions for a respective rectilinear connection of the predetermined coupling sections of the coupling element.

Abstract: The present invention relates to an oscillator, particularly for or in a flat loudspeaker, particularly for use in the aerospace field, comprising an oscillating part carrier, a coupling ring for coupling the oscillator to a sound converter of a loudspeaker, wherein the oscillating part carrier and the coupling ring are connected to each other via a detachable quick-release closure, comprising first closing elements for a locked, secure connection in relation to vibrations and second closing elements that are separate from the first closing elements, for a secure connection between the oscillating part carrier and the coupling ring. The invention further relates to a flat loudspeaker comprising such an oscillator and to a vehicle comprising such a flat loudspeaker.

Abstract: A process for manufacturing a curved structural part includes fabricating a mold of the curved structural part having at least two faces that form a male mold section between a minimum radius of curvature of the curved structural part and another radius of curvature belonging to one of the two faces, preparing a stack of multidirectional fibers of one or more fiber plies oriented ±? or 90° in relation to a longitudinal direction of the curved structural part, cutting a first multidirectional strip in the stack extending longitudinally and having a width at least equal to a maximum width of the curved structural part, applying the first multidirectional strip over the mold to gradually conform the first multidirectional strip to the mold, applying the first multidirectional strip on the face having the minimum radius of curvature, and pressing and tightening the first multidirectional strip over the other faces.

Abstract: Connection devices for a moulding core for producing a fibre composite component are provided. Such a connection device can include a base element for receiving a coupling portion of the moulding core for subjecting the moulding core to a medium, a clamping element for fixing and sealing the coupling portion of the moulding core on the base element, and a locking mechanism for locking the clamping element with respect to the base element and the coupling portion of the moulding core.

Abstract: A method and an arrangement for reinforcing a fibre composite component for the aviation and aerospace industry, in which a reinforcing element having a receiving region and a pressure element adapted to the receiving region geometry. The pressure element is inserted into the reinforcing element receiving region. The reinforcing element and the inserted pressure element are fastened relative to one another in a reproducible manner by a reversible fastening device. The fastening device includes a first fastening portion mounted on the pressure element and a second fastening portion which can be mounted on the reinforcing element. The reinforcing element, with the pressure element, is then applied in a reproducible manner to the fibre composite component to be reinforced, to form a moulding portion. The formed moulding portion is cured to connect the reinforcing element to the fibre composite component. The fastening device and the pressure element are then removed from the fibre composite component.

Abstract: A trailing edge flap arrangement for an aircraft wing, comprising an array of flap elements moveable collectively between a retracted and an extended position, wherein at least the leading flap element is rotatable about its axis independently of the collective array movement. Also, a method of operating the trailing edge flap arrangement, comprising collectively moving the array of flap elements between a retracted and an extended position, and rotating at least the leading flap element about its axis independently of the collective array movement. The flap arrangement can be deployed as a single slotted flap which can be vented to further improve lift performance. The flap arrangement can also be operated to provide variable camber across the performance envelope.

Abstract: The present invention relates to a device for holding systems, for example an electric or fluid-guiding line, on a structure, in particular an aircraft or spacecraft, comprising: a first holding part, which has a first encompassing portion to encompass the system in portions and a first foot portion; a second holding part, which has a second encompassing portion for encompassing the system in portions and a second foot portion; a fastening mechanism, by means of which the first and second foot portion of the first and second holding part can be detachably fastened to one another, so the first and second encompassing portion of the first and second holding part encompass a region, in which the system is located with its entire periphery.

Abstract: An aircraft fuselage structure is described with frames running in the circumferential direction, stringers running in the longitudinal direction and a skin which is arranged thereon and outwardly seals the aircraft fuselage in a compression-proof manner. According to the invention, it is provided that the aircraft fuselage structure contains prefabricated integral units (10) which each run in the circumferential direction of a fuselage segment and in which the frame (11) of a fuselage segment and connecting elements (17, 18) for connection to skin elements (20) comprising stringers (22) and skin (21) are formed.

Abstract: The invention relates to a residence and sleeping module in an aircraft, for accommodating at least one member of an aircraft crew, wherein the module comprises a first partial module for docking a second partial module to it. In this arrangement, the first partial module or the second partial module comprises a connecting element, and the first partial module is designed to be arranged at a vertical height of an aircraft, which vertical height differs from that of the second partial module. In this arrangement, the connecting element is designed such that the second partial module can be docked to the first partial module by means of the connecting element.

Abstract: A system for manufacturing a vehicle cabin includes, but is not limited to at least one first installation component, at least one first surface element, and at least one guide element. The first surface element is slidably arranged on the first installation component with the guide element to form a cabin module, and the guide element is lockable in at least one assembly position and at least one operating position. The resultant cabin module in the assembly position includes, but is not limited to outer dimensions enabling incorporation into a fuselage section of a vehicle, so that the cabin module in the operating position can make up at least a section of the cabin in the fuselage section of the vehicle.

Abstract: This aircraft control cabin comprises an avionics display device with multiple fixed screens (10a-10d) and at least one screen (15, 16) as an accessory, designed to be a replacement screen or extra screen for the avionics display system. The screen (15, 16) is a touch screen housed in a retractable tablet which slides underneath an instrument panel in the control cabin, the touch screen (15, 16) being designed to occupy a stowed position underneath the instrument panel, a first position of use in the retractable tablet in which the touch screen (15, 16) acts as a means of interaction for controlling various items in the control cabin and a second position of use in which the touch screen (15, 16) is put in a position in which it replaces or supplements a screen (10a-10d) belonging to the avionics display system. Use in an aircraft.

Abstract: The invention relates to a method for adjustment of a harmonization compensation applied to alleviate a discrepancy of conformity between a video image transmitted by a video transducer (1) and projected by a head-up display device (5, 6), of an aircraft, and an external scene ahead of the aircraft. At least one equipment item of the aircraft—preferably the said HUD device—equipped with at least one control element accessible in the cockpit, is programmed to be able to function according to a nominal mode and according to a maintenance mode, in which at least one of its control elements, known as a redirected control element, is used to define the applied harmonization compensation. An operator activates the maintenance mode and starts an adjustment operation, in which he modifies in real time the applied harmonization compensation, by manipulating at least one redirected control element, until the video image is matched with the external scene.

Abstract: An aircraft cabin plate absorber includes a supporting panel, a cover panel and an intermediate layer which is arranged between the supporting panel and the cover panel. The cover panel includes a cover layer which is visible from the cabin space, and is arranged on the supporting panel on the side facing the sound inside the cabin space. The cover panel is fastened to the supporting panel by the intermediate layer, and comprises at least one connecting region, in which it is connected to the supporting panel, and at least one absorption region, in which it is arranged so as to oscillate with respect to the supporting panel. The panel is optimized in term of space requirement and weight for use in aircraft and has improved sound absorption properties.