Abstract: The DC electrical network comprises an electrical load supplied with electricity by an electrical power source to which the electrical load is linked by a first electrical line and a second electrical line. An overcurrent protection system comprising an input pole and an output pole is mounted in series on the first electrical line. The overcurrent protection system comprises an electronic switch mounted in series between the input pole and the output pole, an electrical current sensor, and a controller configured to control the electronic switch. It also comprises an electronic device linked to the input pole and to the second electrical line. The controller is configured to command a conducting state of the electronic device when a current measurement from the electrical current sensor is above a predetermined current threshold, then to command an opening of the electronic switch.

Abstract: A method for producing an armored wall for an aircraft by determining an available thickness of the wall, an allowable areal mass of the wall, and an available space for a wall deformation due to ballistic impact. The method includes retrieving a parameterization of a plurality of armoring materials, which includes a parameter for each of a plurality of material characteristics for each of the plurality of armoring materials. The method also includes comparing the available wall thickness, the allowable areal mass, and the available deformation space with a corresponding parameter of the parameterization, selecting one armoring material for the wall from the plurality of armoring materials based on a result of comparing, and manufacturing a wall by supplementing the selected armoring material to a basic wall structure.

Abstract: A clamping apparatus connecting tube flanges, includes first and second bracing devices. The first bracing device connects first and second mounting devices and has a partially circular shape with a first inner and a first outer wall. The second bracing device connects first and second connecting devices. The first bracing device inner wall has a first recess. The first bracing device outer wall is configured to contact the second bracing device which is configured to contact the first bracing device outer wall to apply substantially radial force on that first outer wall. The first recess shape is configured to substantially convert the radial force applied to the first bracing device outer wall into an axial force inside the first inner wall. The first and second mounting devices each comprise at least two attachment devices connecting the first and second connecting devices of the second bracing device.

Abstract: A deflector provided with a spoiler for a thrust reverser of an aircraft engine nacelle. The deflector, a lateral deflector or an orbital deflector, may be in an exhaust structure of a thrust reverser and comprises a deflector plate configured to act on an aerodynamic flow. The deflector plate has a concave upstream face and a convex downstream face, as well as an intake end and an exhaust end. The deflector is fitted with a spoiler rigidly connected to the exhaust end of the deflector plate and arranged transversely in relation to the deflector plate. The spoiler endowing the deflector with specific properties to act on the aerodynamic flow.

Abstract: A panel for covering a part of a structure in an interior space of an aircraft is disclosed including a main panel section having an interior side and an exterior side, and at least one attachment device coupled with the exterior side. The main panel section is exclusively made from a single thermoplastic material, and the at least one attachment device is adapted for attaching the panel to the respective interior structure.

Abstract: An avionics network including a plurality of avionics components and a configuration monitoring device, which is connected by wire or wirelessly to the plurality of avionics components. The configuration monitoring device has at least one configuration data interface configured to receive a plurality of configuration parameters characterizing the operating status of the avionics components. The configuration monitoring device further includes a parameter filtering device connected to the configuration data interface and configured to filter a subset of the configuration parameters received.

Abstract: A sealing device for covering an aperture in a wing part of an aircraft is disclosed having an interface section for fixedly mounting the sealing device to a surface of the wing part adjacent the aperture, a connecting section, and a cover section for covering at least a part of the aperture. The connecting section is arranged between the interface section and the cover section and connects the interface section and the cover section. The connecting section is adapted to resiliently hold the cover section in a predetermined orientation relative to the interface section to cover at least a part of the aperture. The cover section comprises a contact portion for contacting a surface of an actuation element that protrudes through the aperture.

Abstract: A blind fastener is disclosed having a head, a shaft with a tail, a tail of the blind fastener including the tail of the shaft and a sleeve surrounding the tail of the shaft, and a barrier secured to the tail of the blind fastener. The sleeve is configured to expand away from the tail of the shaft to form an expanded sleeve which is forced against a face of a workpiece to clamp the workpiece between the head and the expanded sleeve. The barrier is configured to be forced against the face of the workpiece to form a sealed cover around the tail of the blind fastener.

Abstract: A method and apparatus for cutting a Non-Crimp Fabric for improving edge stability and reducing stitch retraction is disclosed. The part of the NCF to be cut is treated with a binder and heated to activate the binder and therefore bind the tows and stitches together. By treating only the cutting path the drapability of the wider fabric is maintained. This may be achieved by heating only the part of the NCF to be cut, or applying binder to only the part of the NCF to be cut. The NCF may be compressed and cooled before cutting to improve binding action. A ply cutter may be adapted to carry out the invention by including a heat source and optionally a binder dispenser, compressor and cooler.

Abstract: An aircraft fuselage includes fore and aft sections, a barrier wall separating the sections and an opening therebetween, a rail attached to the barrier wall, a door moveable across the barrier wall between an open position offset from the opening and a closed position covering the opening, a first roller and a second roller rotatably fixed to the door and moveable on the rail along first and second paths to move the door, the rail including a first ramp engaging the first roller as it moves along the first path and to direct the first roller towards the barrier wall, and a second ramp engaging the second roller as it moves along the second path and to direct the second roller towards the barrier wall, the first roller configured to engage the first ramp as the second roller engages the second ramp to move the door towards the barrier wall.

Abstract: A method for optimizing a climb phase of an aircraft, implemented repeatedly during the climb phase, includes an acquiring step for acquiring current values of input parameters, a determining step for determining a current optimized DTflex value from the current values of the input parameters and from optimized DTflex values recorded in a database and a transmitting step for transmitting the determined current optimized DTflex value to a user system with a view to controlling the thrust of the aircraft, the method making it possible to continuously adapt, during the climb phase, the optimized DTflex value so it corresponds to current conditions of the aircraft to maximize its performance particular for fuel consumption.

Abstract: A method for managing taxiing paths of an aircraft includes at least one computer system, the method being implemented by the computer system. The method includes the following steps: editing an initial path; displaying a route of the initial path on a screen using a first route symbolism; obtaining a validation of the initial path; displaying a route of the validated initial path on the screen using a second route symbolism; implementing the validated initial path in a taxiing setpoint of the aircraft. The method further includes an editing process and an independent display process.

Abstract: A support for coaxial flanges of a double-coaxial coupling includes a circular support structure providing a primary mounting zone for attaching a primary flange for connecting a primary outer tube, and a secondary mounting zone for attaching a secondary flange for connecting a coaxial secondary inner tube. The primary and the secondary mounting zones are spaced apart from each other in a radial direction for centering the primary and the secondary flanges in a radially spaced coaxial manner. The primary mounting zone provides an outer circumferential connection region with at least three mounting points for attaching the primary flange. The secondary mounting zone provides an inner circumferential connection region with at least three mounting points for attaching the secondary flange. A thermal path within the circular support structure between the mounting points of the primary and secondary mounting zones is longer than the distance between the two points.

Abstract: An aircraft brake control system for controlling antiskid braking of an aircraft wheel is disclosed including a control assembly having a mode controller which sets the mode of operation of an antiskid brake calculator, configured to set a first mode, when an input of the indication of a brake energy supply configuration indicates a first brake energy supply being used, in which the antiskid brake calculator applies a first restriction level on a rise rate of the antiskid brake command, and a second mode, when the input 305 indicates a second brake energy supply being used, in which the antiskid brake calculator applies a second, lower, restriction level on a rise rate of the antiskid brake command.

Abstract: An aircraft fuselage assembly includes a primary structure with first and second rows of support elements extending parallel to a longitudinal axis and into an interior space of the fuselage where they have a free end. The free ends of the first and second rows are spaced from one another to from a free space below a common plane of the free ends and extending to the primary structure. A cargo floor assembly with at least one first cargo floor element is fixedly connected to the free ends of the first row in the common plane and at least one second cargo floor element fixedly connected to the free ends of the second row in the common plane. At least one central cargo floor element is arranged between the first and second lines and is releasably connected to the support elements of the first and second rows.

Abstract: An aircraft assembly is disclosed including an aircraft panel, a channel attached to the aircraft panel, a fuel line for carrying cryogenic fuel, the fuel line disposed in the channel, and a sealed containment space around the fuel line for containing cryogenic fuel leaked from the fuel line, the containment space defined between the channel, the fuel pipe, and the aircraft panel.

Abstract: An actuator is disclosed including an actuator body mounted for movement over a range of motion, the range of motion including a first part and a second part, the first part being the range of motion extending between an end position and the second part. The actuator includes a motor coupled to the actuator body to move the actuator body in the first direction and a controller configured to control the supply of current to drive the motor. The mechanical resistance to movement of the actuator body in the first direction is higher in the first part of the range of motion than in the second part of the range of motion. The controller is configured such that any additional current supplied to the motor when the actuator body is in the first part of the range of motion is limited thereby causing the speed of the actuator body to reduce as the actuator body approaches the end position.

Abstract: An inflatable separating region for a vehicle interior, in particular for a passenger cabin of an aircraft, includes a supporting structure with interconnected inflatable tubes made of a flexible material and arranged, in an inflated state, to form a self-supporting frame structure for the separating region; and a covering with flexible wall membranes which connect the inflatable tubes to one another in a planar manner to separate off the separating region in the inflated state from the vehicle interior.

Abstract: A module an aircraft fuselage includes a support device including a lower end for connection to a fuselage structure in a lower deck of the fuselage, an upper end for connection to an intermediate floor in the fuselage, and an energy absorption element between the upper end and the lower end. A wall panel is connected to the support device and extends along a longitudinal axis and a circumferential direction. In case of a defined crash of an underside of the aircraft fuselage, the energy absorption element is configured to undergo a defined plastic deformation and absorb a defined amount of kinetic energy of that a part of the fuselage structure connected to the lower end of the support device. The plastic deformation and amount of absorbed energy are of a magnitude that in case of defined crash, the module is configured where the fuselage structure will, at the underside of the aircraft fuselage, deform no more than a minimum height.

Abstract: A connecting system for connecting components in a vehicle includes a first elongate element with a first connecting face at a first end, and a second elongate element with a second connecting face at a second end. The first and second elements each comprise holding devices distributed along an annular connecting line. The connecting faces are congruent. The connecting faces and holding devices are configured to be brought into a flush superficial contact when the orientations of the elongate elements coincide, and the mutually opposing holding devices then connect with one another. One of the elements has a length adjustment component configured to change a position of the respective connecting face in a longitudinal direction of the respective element. The connecting faces comprise at least one pair of connectable interfaces which correlate with one another in pairs for transfer of a fluid, electrical or optical signals or electrical current.