Abstract: The present disclosure is directed towards a method for protecting a multi-phase autotransformer for an aircraft including the steps of receiving values of current input into and output from the first and second phases; determining, as a function of these received values, values of current representative of the operation of the phases; determining, as a function of these determined values, a value representative of a homopolar current flowing in the first phase; comparing, in a first comparison, the value representative of the homopolar current flowing in the first phase with a first predetermined threshold value; and controlling the values of current input into the phases as a function of the first comparison.

Abstract: A device for aiding the localization of an aircraft wreck submerged in a sea is arranged inside the aircraft. The device includes at least one beacon that is able to emit remotely detectable signals. Upon immersion of the aircraft in water, an ejection device automatically ejects the beacon out of the aircraft. The ejection device includes a piston system that generates an opening in the aircraft and expels the beacon accordingly. Also after immersion of the aircraft in water, a trigger device automatically triggers the emission of signals from the beacon.

Abstract: The invention relates to a device for developing an aircraft hold located under the floor of the passenger cabin and the cockpit and including a so-called commercial area in which freight can be transported and a technical area including technical equipment and located at the front of the commercial area an at least partially under the cockpit, wherein said device includes: at least one compartment sealed relative to the hold located at the front of said commercial area and at the back of a portion at least of the technical area; a staircase connecting each compartment to a portion of the intermediate floor between the passenger cabin and the cockpit; and a sealed corridor extending from said staircase to each of said sealed compartments.

Abstract: A method of designing a composite panel, the panel comprising a plurality of zones, each zone comprising a plurality of plies of composite material arranged in a stacking sequence, each ply in each stacking sequence having a respective orientation angle. For each orientation angle a first layout matrix is created which identifies zones in the panel which contain at least one ply with that orientation angle. A second layout matrix is also created which identifies zones in the panel which contain at least two plies with that orientation angle, and so on up to an Nth layout matrix which identifies zones in the panel which contain at least N plies with that orientation angle. The layout matrices are arranged in a plurality of candidate sequences. Selection criteria are then used to choose one or more of the candidate sequences and stacking sequences are assigned to the zones in accordance with the chosen candidate sequence(s).

Abstract: The guiding mode transition aiding device includes a target heading determining device and a mode transition triggering system. The target heading determining device is configured to determine a target heading which represents the heading value reached by the aircraft at the end of a procedure of folding the wings of the aircraft flat from a current operating state. The mode transition triggering system receives the target heading and compares the target heading to a desired heading to be reached by the airplane to assist with triggering a transition between a rolling angle holding mode, in which the aircraft flies with a constant rolling angle, to a heading holding mode, in which the aircraft flies with a constant heading. This device and associated methods may be used during in flight refueling operations.

Abstract: The invention relates to a method for at least partially reworking or replacing a reinforcement element of a fibre composite structure. In a first method step, at least one fibre layer is arranged on a surface section of the reinforcement element and/or at least one replacement section of the reinforcement element of the same material and same layer structure is arranged on a surface reinforcement section of the fibre composite structure. In a second method step, at least a pressure mat adjusted to the contour of the reinforcement element is disposed above the at least one fibre layer and/or the at least one replacement section of the reinforcement element, wherein the at least one pressure mat is supported and fixed in a nominal position by a fixing frame adjusted to the contour of the reinforcement element. In a third method step, the at least one pressure mat is then acted upon by a pressure medium in order to press the same against the reinforcement element and the fixing frame.

Abstract: A wireless high-rate communication device for a vehicle, adapted for data exchange between at least one computer system of the vehicle and at least one computer system of a structure separate from the vehicle. The device includes at least one antenna connected to at least one emitter/receiver in turn connected to the at least one computer system of the vehicle, the device adapted for exchanging data according to a point-to-point ultra-wideband communication mode, with a device of the structure including at least one antenna connected to at least one emitter/receiver in turn connected to at least one computer system of the structure when the at least one antenna of the vehicle is in a vicinity of the at least one antenna of the structure.

Abstract: An attachment device for an aircraft engine including a rigid structure and an attachment mechanism of the engine onto the rigid structure. The attachment mechanism includes two thrust take-up connecting rods mechanically connected to a spreader, a connection fitting fixed to the rigid structure to which the spreader is mechanically connected by a junction fitting by a connection pin, and an additional fitting to which the connecting rods, the spreader, and the connection fitting are mechanically connected. A clearance is provided at the mechanical link between the connecting rods and the additional fitting, the link between the additional fitting and the connection fitting being made using the connection pin being inserted laterally, orthogonal to the median plane of the attachment device.

Abstract: An apparatus for adjusting a surface of an aircraft model includes, but is not limited to a first linear adjustment unit with a first retaining body that is movable along a first axis, a second linear adjustment unit with a second retaining body that is movable along a second axis, and an angle adjustment unit. The second linear adjustment unit is arranged on the first retaining body, and the angle adjustment unit is arranged on the second retaining body and is configured to adjust and lock an angle between an attachment surface and a retaining surface. Consequently, precise positioning of surfaces of a wind-tunnel aircraft model does not require specially manufactured and individually adapted fittings for each setting position to be moved to.

Abstract: An insulation package for thermal and acoustic insulation of a vehicle cabin has a cutout to allow a fastening device to pass through. An insulating element that is disposed in an area of the insulation package surrounding the cutout has an opening corresponding to the cutout for allowing a fastening device to pass through. At least part of the insulating element is aligned perpendicularly to an axis of the passthrough in the cutout and conformed so as to create a gap between a fastening device that has passed through and the insulation package. In this way, condensed water may be prevented from passing through the cutout in the insulation package and into the aircraft cabin.

Abstract: A safety system for reducing the explosion risk of a fuel tank comprises at least one fluid source and at least one fluid container with an inlet and an outlet for a fluid, wherein the fluid container has a structure that is flexible at least in some regions and is designed in such a manner that it can be positioned in a hollow space of the fuel tank, which hollow space is situated above the fuel, with said fluid container when fluid flows into the hollow space essentially occupying the space up to the top of the fuel tank. In this way it is possible to avoid the presence of a free air volume in the fuel tank, which counteracts any formation of a potentially explosive mixture and in this way reduces the explosion risk.

Abstract: An inspection device is provided to monitor hygienic conditions of a space unit for a vehicle. The vehicle includes, but is not limited to, an inspection device, the use of an inspection device, and a method to assure hygienic conditions in a vehicle. In order to optimize assuring hygienic conditions in interior spaces on board a vehicle an inspection device is provided that includes, but is not limited to, an optical detection device. The optical detection device generates electromagnetic radiation to irradiate a surface to be cleaned, and renders visible soiling that, in visible light, is invisible to the human eye. The optical detection device is permanently installable on an interior lining.

Abstract: A method for producing an aircraft structural component includes the steps of introducing a plurality of semi-finished product layers for producing a component from a fibre-reinforced, thermoplastic plastic material into a compression mould, applying pressure to the stacked semi-finished product layers, the stacked semi-finished product layers being fixed, before pressure is applied, at particular points in their position in the compression mould and/or relative to one another in such a way that, while pressure is being applied to the semi-finished product layers stacked in the compression mould, a sliding movement of the semi-finished product layers relative to one another and/or relative to the compression mould, preventing wrinkling in the semi-finished product layers, takes place, and removing the aircraft structural component from the compression mould.

Abstract: A method and device are provided for determining a target altitude for an emergency descent of an aircraft that is to be reached by the end of the emergency descent. The device determines an updated target altitude which takes into account variations of barometric pressure and which is able to replace the target altitude that must be reached at the end of the emergency descent. The method includes determining an initial target altitude representative of the initial position of the aircraft and then repeatedly determining a current target altitude along a reference horizontal distance. The current target altitude is compared to the initial target altitude and is used to update the emergency descent if the current target altitude is lower than the initial target altitude.

Abstract: A fuel cell system module for use in an aircraft includes at least one fuel cell system component. The fuel cell system module is connectable modularly to a fuselage section of the aircraft. A housing element of the fuel cell system module is designed to form a section of an outer skin of the aircraft when the fuel cell system module is in the state connected to the fuselage section of the aircraft.

Abstract: A shower system for use in aircraft while in flight, the shower system having a feed line through which a stream of water can be supplied to the shower system; a showerhead from which a prepared stream of shower water can exit the shower system and a water stream parameter modification device for modifying at least one parameter of the water stream, said water stream parameter modification device incorporated between the feed line and the showerhead, wherein the water stream parameter modification device comprises at least one valve, which opens when not exposed to any pressure upstream to enable an evacuation of the entire shower system.

Abstract: An aircraft structural element situated at an interface between a wing and the fuselage, and including a web and profiled elements flanking the web. At least one the profiled element includes a flat part positioned without overlap in the continuation of a flat part of the web and connected thereto by a welded butt joint using friction stir welding.

Abstract: The data frequency analysis method comprises: a step for inputting signals coming from a first sensor; a step for inputting signals coming from at least a second sensor, each second sensor being positioned close to the first sensor so that the signals coming from each second sensor are strongly correlated with the signals coming from the first sensor; a step of estimating, for each sensor, a transfer function or model established from the combination of the signals from the first sensor and from each second sensor; and a step of extracting the structural properties of the system from each of the estimated models.

Abstract: A monitoring device is disclosed for an actuation system of an aircraft for monitoring a guiding device of a regulating flap with a load sensor. An actuation system with the monitoring device and a method for reconfiguring such an actuation system are disclosed. The monitoring device includes an interface to the load sensor and an interface to a driving device for adjusting the regulating flap. The monitoring device can determine or receive in-flight information actively signaling a predefined flight attitude and/or a predefined operational state of the aircraft. The monitoring device can compare a load value corresponding to a sensor value acquired by the load sensor and a limiting value corresponding to a minimum operational load for the predefined flight attitude and/or the predefined operational state of the aircraft and a monitoring function. The monitoring function can assign a fault mode to the regulating flap.

Abstract: Disclosed is a method and system for avoiding collision between an aircraft A and an intruder aircraft. The method and system involve determining avoidance presets to avoid a collision between the aircraft A and the intruder aircraft, in which the avoidance presets comprise a vertical speed preset. The presets are determined from avoidance information received from an anticollision system, and the determined avoidance presets are transmitted to at least one guidance device that guides the aircraft A based on the avoidance presets.