Abstract: A filling method for filling surface imperfections on a surface of a wing comprising a scanning step in which a control unit controls a movement of a scanner past the surface of the wing to scan the surface and transmit the collected data to the control unit, a computation step in which the control unit computes a digitized surface from the data, a determination step in which the control unit determines each surface imperfection by comparing the reference surface and the digitized surface, a generation step in which the control unit generates a digital model of the patch intended to fill the surface imperfection, and a printing step in which the control unit controls the movement of a 3D printer past each surface imperfection and commands the activation of the 3D printer in order to make it print the patch.

Abstract: A system has a frame with first and second spaced apart edges, a first holder couplable to the fuselage structure and embodied for articulated connection to a first region of the frame that is close to the first edge, a second holder couplable to the fuselage structure, and a strut. A first end of the strut is connectable in an articulated manner to the second holder. A second end of the strut is connectable in an articulated manner to a second region of the frame near the second edge and remote from the first edge. The frame and the strut form a triangular structure with the first and second holders. The strut and the frame form two sides of the triangular structure. A length of the first and/or second side is variable to adjust the position of the frame.

Abstract: A passenger door arrangement for an aircraft segment, which arrangement comprises a passenger door, which is configured to assume a raised state and a lowered state, and a “girt bar,” for arming and disarming an escape slide, the girt bar not altering its position relative to the passenger door in the transition from disarming to arming, when the passenger door is in the lowered state. Additionally an aircraft segment, which comprises the passenger door portion and a fuselage portion, an external engagement arrangement being fixed to the fuselage portion.

Abstract: A wing for an aircraft, including a main wing, a slat, and a connection assembly movably connecting the slat to the main wing, such that the slat is movable between a retracted position and at least one extended position. The connection assembly includes a first connection station and a second connection station spaced apart from the first connection station in a wing span direction. The object, to prevent the slat from skewing, is achieved in that the connection assembly includes a sync shaft coupling the first connection station to the second connection station for sync movement of the first and second connection stations.

Abstract: A supervision system for an aircraft for monitoring a safe charging of portable electrical devices of a passenger who may be in an attentive or an inattentive state, comprising a passenger seat, a power supply station assigned to the seat and used to supply electrical power to the portable electrical device, the portable electrical device being connected to the power supply station, a camera, which detects the state of the passenger situated on the seat, and an arrangement to distinguish whether the passenger is in an attentive or inattentive state. A method for safe charging of portable electrical devices is also presented and described, comprising the steps of detecting a passenger with a camera, analyzing whether the passenger is in an attentive state or in an inattentive state, and, if the passenger is in an attentive state, supplying a power supply station with electrical power to be provided to a portable electrical device connected to the power supply station.

Abstract: A brake cooling period prediction system for predicting a brake cooling period following a braking event, comprising a sensor apparatus in communication with a prediction apparatus. The sensor apparatus includes a torque sensor for measuring the torque reacted by a brake during a braking event; a wear sensor for measuring a wear state of the brake; and an environmental sensor for measuring at least one ambient condition of the environment of the brake. The prediction apparatus includes a memory storing information relating to the thermal behaviour of the brake; and a controller configured to receive a torque measurement, a wear measurement and an ambient condition measurement from the sensor apparatus; and predict a cooling period based on the received torque, wear and ambient condition measurements, and the information relating to the thermal behaviour of the brake.

Abstract: An auxetic bi-stable structure that comprises an auxetic curved shell movable between a first and a second stable position, and a rigid element. At least part of the surface of the auxetic curved shell is joined to the rigid element such that the curved shell is movable with respect to the rigid element between the first and second stable positions.

Abstract: A cap is disclosed having a collar portion with three or more contact regions arranged to contact the end of a fastener around which the collar portion is provided, the collar portion having a lobed shape in cross-section such that an outwardly projecting lobe extends between each neighbouring pair of contact regions. An advantage of this lobed arrangement is that the cap can tolerate relatively large manufacturing tolerances at the fastener end. The cap may be for fitting over a nut or fastener head, with the contact regions of the cap being arranged to contact corresponding contact regions on a cylindrical collar base portion of the nut or fastener head. The diameter of this cylindrical collar portion may not be well controlled, so that the manufacturing tolerance is high. The lobed shape of the cap base ensures that the contact regions will always provide a good frictional engagement with the nut, whether the cylindrical collar is undersized, oversized, or at its nominal diameter.

Abstract: A wing assembly with at least two ribs is disclosed. Each rib defines a rib plane and has a peripheral edge. A fluid pipe extends through each rib plane and is disposed external to the peripheral edge of each rib. The fluid pipe is coupled to each rib.

Abstract: A method for repair of a damaged stiffened panel of isogrid type, wherein the repair method comprises a step of removal of material with the aim of removing at least one damaged rib and also steps of fitting at least one structural reinforcement connecting at least two nodes positioned about the damaged zone and of at least one wall reinforcement connecting the wall of the stiffened panel and the structural reinforcement.

Abstract: An aerodynamic profile including a skin defining the outer surface of the aerodynamic profile, a leading edge, a trailing edge and a central portion representing at least 50% of the chord of the profile. The profile includes a hollow core of composite material reinforced with a textile having unidirectional fibers. The hollow core has, in cross section, an oblong shape that is rounded, in particular at each of its ends. The skin bears against the hollow core over the length of the central portion of the aerodynamic profile, both on the pressure side and on the suction side of the profile. The reinforcement with a textile having unidirectional fibers permits an ideal orientation of reinforcing fibers in order to optimize mechanical properties in certain directions. The shape of the hollow core, elongate along the chord of the profile and rounded, lends it great resistance to deformation.

Abstract: A 3D printing device includes a printing substrate, a movable printing head configured for additively producing from a modelling material a component on the printing substrate, and a flexible printing space cover which, proceeding from the printing head, spans the printing substrate such that a closed printing space is formed between the printing head and the printing substrate, wherein a printing nozzle of the printing head for applying the modelling material protrudes into the printing space. A support structure of the device includes flexible support rods which run from the printing head to the printing substrate and which hold the printing space cover above the printing substrate.

Abstract: A cap for forming a sealed cavity around an end of a fastener is disclosed. The cap has a cap body with an annular base terminating at a base rim which surrounds an opening into a central cavity. The cap also has an annular skirt providing an annular pocket between the skirt and the base. An inlet hole is provided in the skirt which is in fluid communication with the annular pocket. A protuberance protrudes in the annular pocket and faces the inlet hole to promote a flow of sealant injected through the inlet hole to flow annularly around the annular pocket.

Abstract: A panel assembly with a panel and a stringer is disclosed. The stringer has a stringer foot and an upstanding stringer web. The stringer foot has a flange which extends in a widthwise direction between the stringer web and a lateral edge and in a lengthwise direction alongside the stringer web, and a foot run-out which extends between the flange and a tip of the stringer foot. The foot run-out is bonded to the panel at a foot run-out interface. Reinforcement elements, such as tufts, pass through the foot run-out interface into the panel. The reinforcement elements are distributed across the foot run-out interface in a series of rows including an end row nearest to the tip of the stringer foot and further rows spaced progressively further from the tip of the stringer foot. At least the end row has three or more of the reinforcement elements which are distributed along a polygonal curve.

Abstract: A reference block for ultrasonic shear waves calibration, comprising slots, wherein the reference block has at least two different thicknesses, each thickness comprising two cavities with at least one slot being provided at each cavity. Preferably, the reference block comprises a plurality of steps, each step defining a different thickness.

Abstract: The disclosure refers to an airplane's own mobility system. For supporting a passenger with reduced mobility on board an airplane and for simplifying as much as possible the use of a toilette, a mobility system for passengers with reduced mobility is provided. The mobility system includes an onboard toilette spatial unit having an entrance zone, an entrance door, and a toilette using zone with a toilette. Moreover, a movement device with a passenger carrying equipment is provided, which is moveable at least from the entrance zone to the toilette using zone and supported in the ceiling area. The passenger carrying equipment includes a seat device enabling a passenger a seat like position. For using the toilette, a passenger is movable back and forth with the movement device from the entrance zone to the toilette using zone.

Abstract: A linkage mechanism for a flaperon includes a support structure linkage, a droop panel linkage, and a flaperon linkage. The support structure linkage is pivotally attached to a support structure of a wing of an aircraft. The droop panel linkage is pivotally attached a droop panel. The flaperon linkage is pivotally attached to a flaperon. A second end of the droop panel linkage and a second end of the flaperon linkage are pivotally attached to a connecting section of the support structure linkage. The connecting section is spaced apart from the pivot end of the support structure linkage such that the linkage mechanism transfers a pivoting motion from the flaperon into a pivoting motion of the droop panel.

Abstract: A cargo hold component system for a cargo hold of an aircraft, the cargo hold component system including floor elements and fixing elements. The floor elements can at least partially be fixed releasably by the fixing elements to fixing sites provided on or in the hold floor, such that in a state fixed to the fixing sites, the floor elements support a loading of the hold with cargo containers, and that in a state in which a first group of the floor elements has been removed from the fixing sites by release of the fixing elements and a second group of the floor elements has been partially removed from the fixing sites by release of the fixing elements, the hold is sealed gas-tightly.

Abstract: An electrically heatable layer stack is disclosed. The electrically heatable layer stack includes at least two substrate layers, and at least one carbon nanotubes-, CNT-, layer, which is arranged between the substrate layers and which is configured to conduct an electric current. The substrate layers and the at least one CNT-layer are configured to produce heating of at least one of the substrate layers when an electric current is applied to the at least one CNT-layer. A vehicle assembly group, an aircraft, a method and a system for manufacturing an electrically heatable layer stack are also disclosed.

Abstract: A cap for forming a sealed cavity around an end of a fastener protruding from a surface of a structure is disclosed. The disclosure relates to a spark prevention cap. The cap has an annular base with an annular base terminating at a base rim. The base rim surrounds an opening into a central cavity for receiving the end of the fastener. The base rim lies in a base rim plane around at least a majority of a circumference of the annular base. An annular skirt provides an annular pocket in which a sealant material is received. A biasing configuration is configured to positively bias the base rim against the surface of the structure.