Abstract: A method for generating a labeled set of images for use in machine learning based stray light characterization for space-related optical systems. The method includes (a) obtaining a set of images simulated for a space-related optical system, wherein the images of the set of images contain stray light simulated for the space-related optical system, (b) for each image of the set of images, identifying one or more clusters of light contained in the respective image and labeling the respective image by the one or more clusters of light, wherein the one or more clusters of light include at least one cluster of stray light, and (c) creating, based on the labeled images of the set of images, a plurality of new labeled images by applying transformations to the labeled images to generate an augmented set of labeled images.

Abstract: There is provided a method of assigning use of a bandwidth for radio communication. The method includes the following steps: generating an initial frame, the initial frame including a series of allocations; generating a further frame, the further frame including a series of allocations; repeating the step of generating a further frame to generate a matrix of allocations; shuffling at least two columns or at least two rows within the matrix; selecting one or more columns or rows in the matrix, wherein each selected column or row represents a sequence; assigning use of the bandwidth according to the one or more selected sequences; and transmitting one or more data streams on the assigned bandwidth.

Abstract: A tire monitoring device configured to be mounted on a wheel and including: a pressure sensor for sensing an inflation pressure of a tire on the wheel; a wireless communication interface configured to receive data indicative of a command to indicate tire pressure, wherein the wireless communication interface is configured to communicate with at least one other tire monitoring device; a storage storing a predetermined pressure value; an indicator configured to provide a first indication and a second indication, wherein the first indication is different from the second indication; and a processing system configured to operate the indicator to provide the first indication or the second indication responsive to receipt of the command to indicate tire pressure, and based at least in part on the inflation pressure and the predetermined pressure value.

Abstract: An aircraft propulsion assembly having an engine, a nacelle positioned around the engine, an annular duct delimited by the engine and the nacelle for a bypass flow of cold air, at least one bifurcation passing through the annular duct for connecting the engine and the nacelle and having a leading edge and a primary structure of a pylon housed in the bifurcation and configured to connect the engine to an aircraft wing. The propulsion assembly has at least one heat exchange device including a plate heat exchanger, having a hexagonal longitudinal section and positioned in the bifurcation. According to one configuration, the heat exchanger is a countercurrent heat exchanger.

Abstract: An apparatus for monitoring the condition of a pneumatic tyre including a pressure sensor(s) to measure an internal pressure within the tyre. A speed sensor(s) measures a rotational speed of the tyre. A controller is configured to receive data from the pressure sensor and the speed sensor and output indications related to a condition of the tyre. The controller determines the output indications by tracking the internal pressure with respect to time during use of the tyre, identifying at least one change in internal tyre pressure in a time interval. The time interval is between a first reference time and a second reference time, the reference times corresponding to points at which the speed sensor indicates different rotational speeds of the tyre. The controller further monitors the pressure change as a function of rotational speed of the tyre to provide an indicator of tyre condition.

Abstract: A device for accommodating and for releasing a payload on an aerial vehicle having a mounting frame for accommodating the payload, a linear mover for positioning in a cavity of the aerial vehicle, the mover having a base and at least one holding element, and a release device on the mounting frame. The mounting frame has a largely planar opening area surrounded by an opening edge, wherein the mover is coupled with the mounting frame on a side of the mounting frame facing away from the opening area by the at least one holding element. The mover can move the mounting frame linearly and vertically to the opening area at a variable distance from the base, and the release device can hold the payload in the mounting frame and release it selectively from the mounting frame, where necessary, via the opening edge and in a direction away from the base.

Abstract: A luggage compartment, for use in a vehicle, having a housing with an inner volume defining a storage space of the luggage compartment and a flap which is attached to the housing with at least one fastening device. The fastening device has a first portion attached to the flap and a second portion, wherein the second portion of the fastening device is releasably coupled to the first portion of the fastening device and attached to an outer surface of a top wall of the housing. Also a cabin component assembly with the luggage compartment and a ceiling panel arranged adjacent to the top wall of the housing of the luggage compartment and an aircraft with the cabin component assembly.

Abstract: A bulkhead fitting device configured to sealingly link a conduit and a wall traversed by the conduit. This bulkhead fitting device includes a first ring sealingly linked to the conduit, a second ring having a flat, ring-shaped sealing face configured to be pressed against a contact face of the wall or of an intermediate part linked to the wall, an elastically deformable intermediate annular portion sealingly linking the first and second rings, a holding system configured to press the sealing face against the contact face. This bulkhead fitting device guarantees an optimum seal while enabling the absorption of forces and slight relative movements between the conduit and the wall. The device also helps to limit the propagation of vibration.

Abstract: An aircraft including a floor positioned above a central wing box and in a front fuselage portion positioned in front of the central wing box. The floor includes at least one rail which has at least first and second rail portions and at least one articulation connecting the first and second rail portions and configured to allow a pivoting movement, about a transverse and horizontal pivot pin, between the connected first and second rail portions. By virtue of this articulation, it is possible to integrate the rails into the floor and not to position them on the floor.

Abstract: A head of a cutting device includes a base configured to be fixed to a machine tool, a cylindrical suction nozzle integral with the base, a connector integral with the base and configured to receive a suction pipe. The suction nozzle is perforated by at least one oblong hole, for example parallel to an axis of the suction nozzle.

Abstract: An aerial device for a vehicle, particularly an aircraft, includes an aerial arrangement and a lens, which includes a first lens area, made of a first material with a first dielectric constant, overlapping the aerial arrangement and a second lens area, made of a second material with a second dielectric constant, overlapping the first lens area, with the second dielectric constant being smaller than the first dielectric constant, and wherein the second lens area extends in a longitudinal direction and in a curve in respect of a vertical direction oriented transverse to the longitudinal direction.

Abstract: A rib foot cleat for sealing around a stringer passing through a rib mouse hole in an aircraft assembly. The rib foot cleat has a body for attaching to a rib at a rib mouse hole and defines a cleat channel configured to be arranged over the stringer. The rib foot cleat also has an injection hole through the cleat body which is in fluid communication with the cleat channel, to allow sealant material to be injected through the injection hole in to the cleat channel for sealing around the stringer.

Abstract: An aircraft barrier system separating, within an aircraft, a secure area from a passenger cabin of the aircraft, comprises a barrier installed inside the passenger cabin and configured to move between an open position and a closed position, a latch mounted to the barrier, and a locking device comprising a latching clamp configured to lock the latch when the barrier is in the closed position. The aircraft barrier system further comprises a release mechanism configured to move the latching clamp from a locking state locking the latch to an unlocking state releasing the latch, wherein the release mechanism is further configured to delay the moving of the latching clamp from the locking state to the unlocking state. Also, an aircraft area and an aircraft having such aircraft barrier system.

Abstract: A rotorcraft provided with a rotary wing and a skid landing gear, the landing gear being provided with a first skid and a second skid and with a first cross-member and a second cross-member. The first cross-member is connected to an airframe of the rotorcraft only by two fastenings. The second cross-member is only carried during flight by two supports fastened to the airframe and traversed by the second cross-member. Each support comprises a hole delimited by a stop surface, the second cross-member always being separated from each stop surface by a clearance. A median supporting member is arranged transversely between the two supports and above the second cross-member.

Abstract: The present disclosure relates to a method for detecting a hard landing comprising: i) determining three ground components of a ground reaction force, and determining, for each connector of a landing gear, three attachment components of a force applied to this connector, ii) determining whether a ground stress point defined by the three ground components lies within or outside a ground dimensioning envelope, and, for each connector, whether an attachment stress point defined by the three corresponding attachment components lies within or outside an attachment dimensioning envelope, iii) determining that a hard landing has been made when at least the ground stress point lies outside the ground dimensioning envelope or at least one attachment stress point lies outside the corresponding attachment dimensioning envelope.

Abstract: A device (40) and a method for manufacturing composite parts such as aircraft bulkheads (23), in which a component of the composite part is placed on a first mold (11) with a robotic device (21), a component of another composite part is placed on a second mold (12) with a robotic device (22), the second mold (12) having a surface identical to the surface the first mold (11), and the first mold and the second mold being mounted on a frame in a central symmetric arrangement around a symmetry central point (15), such that components are placed on the molds (11, 12) symmetrically so as to obtain two identical composite parts at the same time.

Abstract: An aircraft system having a first set of components for performing a function of the aircraft system, and a second, alternative, set of components for performing the function of the aircraft system. The aircraft system has and a controller configured to receive scenario data indicative of a scenario during which the function of the aircraft system is to be performed, and, where each of the first and second sets of components are operational, the controller is configured to select between the first or the second set of components to perform the aircraft system function during the scenario based on the received scenario data. The controller is configured to control the selected set of components to perform the function during the scenario.

Abstract: An aircraft with a fuselage that accommodates a floor panel and a fuel storage system, wherein the fuel storage system comprises a tank system with at least one main tank 5a that is arranged underneath the floor panel; a cross ventilation system with a plurality of ventilation lines for venting the tank system, wherein the plurality of ventilation lines comprises at least one crossing ventilation line 11a that is routed from a first lateral side of the tank system to an opposite second lateral side of the tank system; and wherein the at least one crossing ventilation line is routed underneath or in the floor panel from the first lateral side of the tank system to the second lateral side of the tank system.

Abstract: A rotary wing aircraft that extends along an associated roll axis between a nose region and an aft region and that comprises a fuselage with a front section and a rear section, the rotary wing aircraft comprising: a main rotor that is rotatably mounted at the front section, and a stabilizer arrangement that is arranged at the rear section in the aft region, wherein the rear section extends between the front section and the stabilizer arrangement and comprises an asymmetrical cross-sectional profile in direction of the associated roll axis.

Abstract: An output cone of an aircraft propulsive assembly extending in a general direction called longitudinal direction and including a front part and a rear part. The longitudinal assembly of the front part and rear part forms an acoustic treatment system with at least two degrees of freedom. Such a system allows for the treatment of several frequency ranges or of one wide frequency range by the treatment of several overlapping ranges.