Abstract: A mold including: a central core having a side wall with a plane external surface; an internal mold element having an internal surface facing the external surface of the central core, with surfaces inclined to the vertical in order to form an angle of clearance, and a substantially vertical external surface; an external mold element fitted against the internal mold element and having a substantially vertical internal surface facing the external surface of the internal mold element; at least one of the facing surfaces being designed to receive a substantially vertical lateral preform so that the internal mold element and the external mold element are suitable for clamping said lateral preform.

Abstract: A power breaker strip comprising a strip support and a plurality of interphase spacer elements, and a plurality of interline spacer elements, assembled with the plurality of interphase spacer elements such that each interline spacer element extends at least partly between two consecutive interphase spacer elements. The interphase spacer elements and the interline spacer elements together delimit a plurality of per pitch zones of the strip in which connection terminals of several lines of electrical cables can be inserted.

Abstract: A tank system for the cryogenic storage of hydrogen includes a tank structure with at least one hollow body for accommodating liquid hydrogen and at least one insulating means, which encloses the tank structure, for insulating the at least one hollow body. The tank structure has an exterior shape that is integrateable in a load-bearing primary structure of an aircraft. The tank structure is load bearing and is designed to at least partially absorb a load introduced into the primary structure. This makes it possible to achieve a particularly efficient design of an aircraft in which the fuselage of the aircraft is not divided into two parts by the hydrogen tank integrated therein, can be arranged near the center of gravity, and essentially does not increase the additional weight of the aircraft.

Abstract: A method and device for aiding the monitoring of a turbine engine of an aircraft, which displays on one and the same indicator of a of a display indication elements illustrating as a percentage the engine start progression or the current sub-idle state of the turbine engine, a margin to a limit temperature of the turbine engine, a margin to a maximum temperature of the turbine engine and a margin to a possible failure of the start that is generated by a too low speed increase of the turbine engine.

Abstract: The present disclosure relates to a flight recorder, having a memory, a control device, which is coupled to the memory and which is configured to record flight data during the flight of an aircraft and to store said flight data in the memory, a transceiver device, which is coupled to the control device and which is configured to accept stored flight data signals from the control device and to convert them into acoustic signals, and an acoustic transducer, which is coupled to the transceiver device and which is configured to emit the acoustic signals of the transceiver device into a body of water, the control device being configured to receive control signals via the transceiver device and, depending on the control signals, to retrieve partial data areas of the stored flight data from the memory and to transfer them to the transceiver device.

Abstract: The display device (1) comprises means (3) for correcting an acceleration value used for displaying on a screen (7) a speed trend of the airplane, making it possible to zero a speed trend symbol (11) when the Mach number of the airplane does not vary.

Abstract: A wing tip device for fixing to the outboard end of a wing, the wing defining a wing plane, the wing tip device comprising: an upper wing-like element projecting upwardly with respect to the wing plane and having a trailing edge; and a lower wing-like element fixed with respect to the upper wing-like element and having a root chord and a trailing edge, the lower wing-like element root chord intersecting with the upper wing-like element, and the lower wing-like element projecting downwardly from the intersection, wherein the upper wing-like element is larger than the lower wing-like element and the trailing edge of the lower wing-like element is adjacent the trailing edge of the upper wing-like element at the intersection, and wherein an included angle between the upper and lower wing-like elements at the intersection is less than, or equal to, 160 degrees.

Abstract: An aircraft landing gear assembly comprises a landing gear (10) arranged to be moveable between a stowed position and a deployed position. The assembly includes a removably mounted cover plate (20) that covers a void (12) defined by a part of the landing gear assembly. The plate (20) may have a substantially constant thickness, one or more fixing elements (22) on one side only of the plate, and a sealing element (34) that extends around substantially the entire perimeter (20a) of the plate (20).

Abstract: A lift arrangement for an aircraft includes an aircraft fuselage section with an outside, an aerodynamic lift body attached to the aircraft fuselage section and extending from the aircraft fuselage section outwardly, and a pair of movably held add-on bodies arranged upstream of a leading edge of the aerodynamic lift body. The add-on bodies include an aerodynamically effective surface and are equipped with incoming airflow to generate vortices that impinge on the aerodynamic lift body, thus leading to an increase in lift on the aerodynamic lift body. Thus the lift generation on a lift body is effectively influenced, in particular to compensate for loss of lift as a result of icing. The add-on bodies are moveable, and, can be moved to a neutral position in which they do not project into the flow around the aircraft, and are thus not effective from the point of view of fluid dynamics.

Abstract: An access platform (208) enables containers (222) to be loaded into a cargo hold (218) of an aircraft (202) from a ground vehicle (220). The platform (208) has two opposite and non-parallel ends (210, 214), between which there is defined a support surface, the platform when viewed in plan having a generally trapezoidal shape. In use, an item (222) of cargo is moved between the cargo hold (218) and the ground vehicle (220) via a door opening, the movement of the item (222) through the door opening being in a direction (213) which when viewed in plan is not parallel to the direction (211) in which the door opening faces. During such movement, the item (222) of cargo is supported by from beneath by the support surface of the platform (208).

Abstract: Methods for transferring a payload such as passengers and/or luggage and/or freight between an airport and a cabin of an aircraft are provided. Air terminals, aircraft and removable cabin modules suitable for implementing these methods are also provided. An aircraft is provided which includes a removable cabin module. A docking module is also provided for transferring a removable cabin module between an aircraft and an airport. A method for modifying the internal configuration of the cabin of such an aircraft by replacing a removable cabin module of the aircraft is also provided.

Abstract: An air-sucking vehicle tail section component or wing section component includes an outer delimitation part having microperforation including boreholes, and inner delimitation part having a plurality of suction boreholes including fluid connections to the microperforation boreholes, and connecting elements. The inner delimitation part is connected via the connecting elements to the outer delimitation part. The outer delimitation part includes a continuously curved shape. The inner delimitation part includes two or more planar inner delimitation part components, which are each connected to one another at one edge to form a connection edge, and the connection edge is configured to be attached to the outer delimitation part. A type of framework structure is thus provided, which causes increased stability and can split impacting objects in particular if two inner delimitation part components are used on the vehicle tail section component or wing section component.

Abstract: A method of preparing a component (60) to be joined to another component (55). The method comprises growing an array of projections (56, 57) on a bond region of the component (55) in a series of layers, each layer being grown by directing energy and/or material from a head to selected parts of the bond region. The joint may be used to join a pair of structural components, for instance in an aerospace application. For instance the joint may be used to join a reinforcing plate, floating rib foot, or stringer to a panel such as a wing or fuselage cover. Alternatively the joint may be used to join adjacent layers in a laminate structure.

Abstract: The invention relates in particular to a method and a system for monitoring a graphical interface in a computer system of an aircraft cockpit. The method comprises, in addition to the display of a graphical interface of a client application based on a tree structure of graphical interaction objects composing said graphical interface, the following steps: obtaining a plurality of graphical interaction objects having a tree-structure organization; creating and adding, to said obtained tree structure, at least one new graphical interaction object defining a critical graphical display zone; modifying the tree-structure dependency of at least one critical graphical interaction object, of the obtained tree structure to make it dependent from the new graphical interaction object defining the critical zone; and performing critical monitoring only of the critical graphical objects attached to the critical zone.

Abstract: A contact sealing ring includes an electrically conductive annular disc which has a central through-opening, a first electrically conductive contact formation which protrudes from a first side of the annular disc, and a second electrically conductive contact formation which protrudes from a second side, opposite the first side, of the annular disc.

Abstract: An elongated supporting pillar for a high-strength structural component is designed to absorb bending forces that act transversely to a longitudinal direction of extension of the supporting pillar. The supporting pillar comprises a wall which at least partially encloses an elongated cavity of the supporting pillar. A reinforcement structure is arranged within the cavity and transversely to the direction of longitudinal extension in such a manner that the reinforcement structure can absorb at least some of the bending forces. The reinforcement structure is designed integrally with the wall, wherein both the wall and the reinforcement structure comprise a meltable material. The supporting pillar has a conical shape, and wherein a first end of the supporting pillar is wider than a second end of the supporting pillar.

Abstract: A method and a device for management of maintenance information items in an aircraft comprising a centralized maintenance system is disclosed. After a maintenance message has been received, the value of an impact attribute associated with the message received is determined according to predetermined configuration data. In response to the message received and to the value of the impact attribute associated with the at least one message received, the message received is processed. A determination of configuration data for the management of maintenance information items in an aircraft is also explained.

Abstract: The invention relates to a method of connecting two fuselage sections (1, 2, 21, 22) formed by a fiber-reinforced plastics material, in particular wound fuselage sections (1, 2, 21, 22) for aircraft fuselage cells, having a multiplicity of stringers (10, 11, 35, 36) arranged with a uniform distribution at a distance from and parallel to one another on the inner side of an outer skin (3, 4, 25, 26), with the formation of a transverse joint (5, 30).

Abstract: The invention pertains to a method for verifying the consistency of the values (?1,?2,?3) given by the sideslip probes (1,2,3) of an aircraft and to a device implementing this method. This method is noteworthy in that it consists in consolidating the values of two sideslip probes by using the value of the incidence ?.

Abstract: Method for manufacturing a dry textile preform, including: pulling a textile fabric sheet; grabbing a first side portion of the sheet between rollers, the rollers forming a first flange of the first side portion of the sheet inclined at a predeterminable angle to the plane of extension of the sheet; grabbing a second side portion of the sheet opposite to the first side portion between other rollers, the other rollers forming a second flange of the second side portion of the sheet inclined at a predeterminable angle to the plane of extension of the sheet; adjusting a difference between the rolling speed of the pair of first rollers and the rolling speed of the pair of second rollers to form a curvature radius of the sheet; and adjusting distance between the rollers perpendicular to the movement direction of the sheet to form a web portion between the first flange.