Abstract: An assist device for ensuring the accuracy and integrity of position information of an aircraft on the ground includes means for determining in the airport (AE) a zone (ZP) of insensitivity to multipath GPS signals, the zone (ZP) having a rectangular shape, which is determined relative to the threshold (O) of the runway, and which has a length (L1) equal to the length of the runway and a width (L2) depending on a maximum illumination distance (D). The device further includes means for verifying, while the aircraft is moving in the airport (AE), whether the position relative to position information of the aircraft is inside said runway zone (ZP). A method for ensuring the accuracy and integrity of position information of an aircraft on the ground is also disclosed herein.

Abstract: The present application relates to a mount (10) for mounting a cable harness to a support. The mount (10) comprises a harness receiving portion (42), and a fastener attachment portion (80) from which a fastener for securing the mount (10) to a support is extendable. The mount (10) orientates a fastener extending from the fastener attachment portion (80) to extend about the harness receiving portion (42) to secure a cable harness to the mount (40) when the mount is secured to a support by the fastener. The present application also relates to a mount assembly and a method of mounting a cable harness to a support.

Abstract: A vehicle structure component reinforced by means of an area, a vehicle including such a vehicle structure component, and a corresponding method to reinforce a vehicle structure component are proposed. The area includes a compressive residual stress in a first direction and a compressive or tensile residual stress in a second direction being vertically aligned to the first direction, wherein the ratio of the compressive stress in the first direction and the compressive or tensile residual stress lies between ?0.2 and +1.0. Hence, the propagation direction of cracks in such areas is diverted, faster pressure equalization takes place, and further crack propagation is inhibited.

Abstract: A method for manufacturing a leading edge profile section of an aircraft lifting surface is provided. The method comprises the following steps: a) providing a set of laminated preforms of a composite material configured with a suitable shape for constituting the leading edge profile section; b) arranging said laminated preforms in a curing tooling and subjecting the assembly to an autoclave cycle to co-cure said laminated preforms; c) demoulding the curing tooling in a spanwise direction towards the aircraft symmetry plane. The invention also comprises a leading edge profile section manufactured by said method comprising in addition to the skin of the leading edge profile section, one or more of the following structural elements: an auxiliary spar, a longitudinal stiffener reinforcing an auxiliary spar, a longitudinal stringer reinforcing the skin of the leading edge profile.

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 for manufacturing a structural part including at least two wings extending in intersecting planes made of thermoplastic fiber-reinforced composite material including at least two plies of continuous fibers. The fibers extend from one wing to another. The method includes cutting the at least two plies in a fabric and/or a tape of fibers pre-impregnated with a thermoplastic resin; assembling the plies to create a preform; and compacting the preform to a final shape of the part by subjecting the preform to a defined cycle of temperature and pressure. A toolset can implement the method described above. Such a toolset includes a rigid punch and die such that closing the tool creates a sealed chamber in a shape of the part between the punch and the die.

Abstract: A method for automatically detecting an erroneous height value supplied by a radio altimeter mounted on an aircraft. The method includes measuring, during the aircraft's approach phase with a view to landing, the duration between the times when a first predetermined altitude threshold and a second predetermined altitude threshold are reached. This duration is measured by taking into account current height values supplied by the radio altimeter. The method then includes comparing the measured duration to a predetermined duration reference time, which is lower than a flight duration that would allow the aircraft to descend from the first predetermined altitude threshold to the second predetermined altitude threshold at a maximum vertical speed. An erroneous height value is detected if the measured duration is lower than the predetermined duration reference time.

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: 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: Joining arrangement for the lateral boxes (11, 11?) of a horizontal tail stabilizer with a central tubular box and manufacturing method for said box. The boxes (11, 11?) are joined using an intermediate joining part (31) that comprises a central box (33, 63, 73), upper (35, 35?) and lower (37, 37?) lateral flaps, fitting plates (A) for the trimming device and fitting plates (B) for the pivoting device, the join being made with rivets between the skins (15, 15?; 17, 17?) of the lateral boxes (11, 11?) and said flaps (35; 35?; 37; 37?). The method for manufacturing the intermediate joining part (31) comprises steps to: a) Provide preforms suitable for forming said part (31); b) Form and cure the part (31) made from said preforms using an RTM method.

Abstract: A thrust reverser for a double-flow nacelle that has a cowling, with the thrust reverser having an internal door and an external door designed to be made within the thickness of the cowling. The reverser also has means for simultaneously displacing the doors between a first position called the rest position, in which the doors are integrated into the cowling so as to form an aerodynamic continuity with the external wall and the internal wall of the cowling, and a second active position, in which the doors are open so that the internal and external doors extend toward the inside and toward the outside of the nacelle, respectively, thus at least partially blocking the annular channel of the secondary flow, to deflect the secondary flow and to generate a thrust reversal, with the means being designed to be received in a compartment arranged inside the cowling formed by the doors in the rest position.

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: An air duct for supplying ambient air in an aircraft includes an air inlet, a flow duct portion and a feed device that is devised to feed ambient air through the air inlet and the flow duct portion. A flow control flap closes the air inlet in a first position, releases a first flow cross-section of the air inlet in a second position and releases a larger second flow cross-section of the air inlet in a third position. The flow control flap is designed to not increase drag significantly in the second position while still enabling flow through the flow duct portion, while increasing drag to increase air fow through the flow duct portion in the third position.

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: 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.

Abstract: A window element for a double-shell skin field of an aircraft fuselage cell includes a window frame having a window module disposed in the frame, wherein the frame is disposed in an opening of the double-shell skin field, and wherein the frame is connected to the double-shell skin field by a surrounding embrasure profile positioned against a core structure of the skin field at least in some regions, wherein the core structure includes an inner and an outer covering layer.

Abstract: An apparatus for protecting an electrical network of an aircraft includes a power switch, an activation means coupled with the power switch, and a detection circuit connectable to the electrical network for detecting a voltage. The detection circuit is coupled with the activation means. The activation means is adapted for opening the power switch once the detected voltage is lower than a predetermined voltage. This is particularly advantageous for high voltage direct current networks temporarily, primarily or permanently powered by a fuel cell system.

Abstract: Methods, systems, and computer readable media for automatic connection of software simulation models, for example and without limitation, for engineering simulation use in aircraft development are disclosed. According to one aspect, a method for establishing a communication link between software simulation models includes initiating communication between the software simulation models and a publish subscribe mechanism, classifying a quality of service indicator for each of the software simulation models, comparing the quality of service indicator associated with two software simulation models, and connecting the software simulation models based on the comparison of the quality of service indicators.