Abstract: A connecting device for manufacturing a peeling-stress-resistant connection between two components. The connecting device includes a carrier, which has a first surface and a second surface opposing the first surface. The connecting device further includes a plurality of hook and loop elements which extend both from the first and the second surface of the carrier and each have at their free ends facing away from the first or the second surface of the carrier a hook and loop head, which is arranged to enter into a hook and loop connection with a component comprising a fiber-reinforced composite material.

Abstract: A construction kit for a housing structure of a monument for a cabin of a vehicle, in particular of an aircraft includes a plurality of integrally formed sandwich panels which each have two cover panels, which surround a core, and are formed with panel connecting structures which are each formed as a plug region or as a mating plug region. The mating plug region is formed so as to be complementary to the plug region in such a way that a plug region of a sandwich panel can be plugged into the mating plug region of another sandwich panel to connect the sandwich panels.

Abstract: An aerodynamic fairing including at least one sub-assembly, each sub-assembly having a frame which is orientated transversely relative to the longitudinal axis of the fairing and a floor portion which is provided with an inner face, via which the floor portion is fixed to the frame. The fairing further comprises lateral panels which are fixed to the frame and which each extend substantially along the longitudinal axis of the fairing at one side and the other of a plane of symmetry of the fairing. The floor portions of the sub-assemblies are not mechanically connected to each other via rigid connections. The division of the floor into separate portions allows a reduction in the longitudinal thermomechanical stresses applied by the expansion of the floor under the action of the primary hot flow of the turbo reactor.

Abstract: A drive system for rotating a wheel of an aircraft landing gear includes a motor operable to rotate a first drive pinion via a first drive path and a driven gear adapted to be fixed to the wheel. The drive system has a first configuration in which the first drive pinion is capable of meshing with the driven gear to permit the motor to drive the driven gear via the first drive path. One of the first drive pinion and the driven gear comprises a first sprocket and the other of the first drive pinion and the driven gear comprises a series of rollers arranged to form a ring. Each roller being rotatable about a roller axis at a fixed distance from an axis of rotation of the first drive pinion or driven gear, respectively.

Abstract: A device for detecting an impact on a composite material structure. This detection device comprises at least two acoustic modules intended to be secured to the composite material structure and a processing unit able to communicate remotely with each of the acoustic modules. Each acoustic module is electrically autonomous and comprises its own means for recording the sound waves sensed by its acoustic sensor. An aircraft structure is also provided comprising a composite material structural element equipped with the impact detection device. A method is also provided for detecting an impact on a composite material aircraft structural element equipped with an impact detection device.

Abstract: An aircraft fuel tank system is disclosed in which a vent tank is provided with an additional ullage vent for use, in combination with an eternal flame barrier means, when refuelling.

Abstract: A sheet entity, in particular for use as a skin panel for an aircraft fuselage, with a carbon fiber-reinforced plastic laminate and an aluminum-based metal laminate in the edge region, which are connected with one another by means of an adhesive bond, and thereby are electrically insulated from one another, and are stepped back by layers. Also disclosed is a fuselage cell of an aircraft with at least one sheet entity of this type.

Abstract: A method for producing a part is provided, the method including the following: a first step of a computer-aided simulation for a plurality of cross-sections of the part based on a 3D cross-sectional model and obtaining a first result, which represents shrinkage of the part basically caused by thermal and/or chemical reactions; a second step of a further computer-aided simulation for the plurality of cross-sections of the part based on a 2D shell model and obtaining a second result, which represents shrinkage of the part basically caused by thermal and/or chemical reactions; determining a scale factor for the second result in such a way that the second result corresponds to the first result; determining scale factors for any cross-sections which are between two adjacent cross-sections from the plurality of cross-sections, by interpolation; predicting a distortion of the part; and producing the part based on the predicted distortion of the part.

Abstract: A warning light circuitry includes a first logic gate adapted for receiving a first, a second, a third, and a fourth input signal; a second logic gate adapted for receiving a fifth, a sixth, and a seventh input signal; a third logic gate electrically connected to the first and second logic gate; and a warning light electrically connected to the third logic gate. The first logic gate is adapted for providing a first output signal to the third logic gate upon receiving the first, the second, the third, and the fourth input signals. The second logic gate is adapted for providing a second output signal to the third logic gate upon receiving the fifth, the sixth, and the seventh input signals. Therein the third logic gate is adapted for triggering the warning light upon receiving the first or the second output signal.

Abstract: A method of configuring an aircraft management system comprising the following steps, implemented by a configuration module integrated into the avionic system of the aircraft cockpit: obtaining at least one item of computation data for computing at least one configuration parameter of the management system, sending, to a computation module that is independent from the avionic system of the aircraft cockpit, a request for computing said at least one parameter on the basis of said at least one item of computation data, receiving, from said computation module, said at least one computed parameter, and configuring said management system with said at least one received computed parameter.

Abstract: A toilet area for an aircraft cabin comprising an access door and housing a toilet bowl. The toilet area also comprises an evacuation exit, the access door occupying a closed position in the toilet area in a toilet configuration and a folded position in the toilet area in an evacuation configuration. Usage in particular in a flying wing aircraft is provided.

Abstract: An aircraft monument includes an elongate cavity having an open end and a lift apparatus mounted to the monument and adapted for lifting goods along the longitudinal axis of the cavity. The monument is adapted to be mounted on a floor structure of an aircraft separating two compartments of the aircraft from each other such that the open end of the cavity faces the floor structure. The lift apparatus includes a guide means including two straight guide members spaced apart, and extending parallel to the longitudinal axis of the cavity, a conveying means including two conveying members each mounted to a different guide member, a moving means for linearly moving the two conveying members, a control means for controlling the moving means to synchronize the linear movement of the conveying members, and a gripping means secured to the conveying means and adapted for selectively gripping and releasing goods.

Abstract: The automatic installation and uninstallation of software modules on equipment on an aircraft. For each reference of an obtained list of references of software modules to be installed or uninstalled, resolution rules linked to an operation associated with the software module in question are identified. The rules comprise at least one reference to an operation of installing or uninstalling at least the software module in question and a list of actions to be performed. For each reference on the obtained list, a list of references of operations to be carried out is determined depending on the obtained list and the identified resolution rules. A list of actions to be performed is determined depending on the list of references of operations to be carried out and the identified resolution rules. At least one referenced action on the list of actions to be performed is executed by calling a specific software agent.

Abstract: An apparatus and method for producing a fiber-reinforced plastics casting (FRP), includes a molding box filled with free flowing molding material, in what a prototype of casting or a textile preform is inserted, forming a mold cavity for infiltration the inserted preform of textile with synthetic resin material in order to form a fiber-reinforced plastics casting (FRP).

Abstract: An apparatus for fabricating a fiber reinforced thermoplastic composite structure is described. The apparatus comprises a localized heat source arranged to heat a portion of a stack of fiber reinforced thermoplastic material layers and an ultrasonic transducer arranged to locally introduce ultrasonic energy waves to the heated portion of the fiber reinforced thermoplastic material layers. The apparatus makes it possible to achieve ultrasonic consolidation of the layers occurs.

Abstract: A sandwich panel for an aircraft includes a lower top layer, an upper top layer and a core layer, wherein the core layer in turn includes pins. The pins extend from a lower top layer in the direction of the upper top layer, and the pins are interconnected by rods. In addition, the rods run inside the core layer, and the pins and rods form a one-piece network.

Abstract: The present invention relates to an automated storage cabinet for trolleys. It includes a device for automatically handling a single trolley with a handling basket including a vertical plate perpendicular to the waiting area, vertically movable between the floor of the waiting area and any one of the levels of the trolley storage cabinet, and two side flanks, connected to the vertical plate and provided with structure for supporting, on either side, two opposite sides of a trolley in the waiting area and for transferring the supported trolley through an opening of the predetermined compartment. The handling device can include structure for inserting the trolley into or extracting the trolley from the predetermined compartment.

Abstract: A method for monitoring the coordinated execution of sequenced tasks by an electronic card including at least one first processor (PP1) and a second processor (PP2) synchronized to the same clock of determined time period, includes: recording in memory means by the first processor (PP1) of a first identifier (ID1) characterizing the time period (T1) in the course of which the first sequenced task has been executed; recording in the memory means by the second processor (PP2) of a second identifier (ID2) characterizing the time period (T1) in the course of which the first accessory task (N1) has been executed; comparing by the first processor (PP1) the first identifier (ID1) and the second identifier (ID2); and signaling by the first processor (PP1) in the case of failure of the comparison so as to signal a defect of coordination of the processors (PP1, PP2).

Abstract: The invention refers to a composite structure for an aircraft comprising a panel and at least one stringer joined to a surface of the skin panel, the stringer having a foot and a web protruding from the foot, and a run-out section at one of its ends. The panel includes a plurality of stacked and co-cured plies of composite material, and at least part of the foot of the stringer at the run-out section, is inserted between two plies of the panel, and it is co-bonded, co-cured or secondary bonded with said two plies. The structure of the invention provides a reinforced join between the foot of the stringer and the skin panel, avoiding peeling or de-bonding problems, without substantially modifying the manufacturing process.

Abstract: The invention relates to an aircraft (10) having a system for measuring a static reference pressure in flight, which system comprises: a pressure sensor (22) connected to the rear portion of the aircraft by a cable (16) and associated with a pressure intake (24) that is located, in flight, in an undisturbed zone downstream from the aircraft, the pressure signal (22) being suitable firstly for measuring a pressure coming from the pressure intake (24) and secondly for transmitting a signal representative of the measured pressure, e.g. an electric signal, to the aircraft; and a system (34) on board the aircraft, which system is suitable for determining a pressure measurement firstly from the transmitted signal and secondly from a position of the pressure sensor (22) relative to the aircraft (10). Pressure is measured dynamically while the aircraft is climbing or descending.