Abstract: The invention discloses a trailing edge (2) of an aircraft aerodynamic surface, which comprises an upper skin (6) and a lower skin (7), being the upper and lower skins (6, 7) made of composite material. In the trailing edge (2) a lightweight part (1) is assembled at an end section (13) of the upper and lower skins (6, 7). The lightweight part (1) is covered by a metallic sheet (8), and has a “V”-shaped cross section with arms and peak, where the peak of the “V”-shaped cross section has a rounded shape and is located opposite the end section (13) of the upper and lower skins (6, 7).

Abstract: Aircraft flight management devices, systems, computer readable media, and related methods are provided. The present subject matter includes devices, systems, computer readable media, and related methods of providing flight management control during abnormal events and/or situations requiring diversion from the present mission. In some aspects, a system for providing flight management may include a computing platform with a processor, a memory, and a flight management application module (FMAM) configured to receive data from multiple servers. The FMAM may also calculate one or more aircraft ranges and/or diversion routes based upon the received data. In some aspects, systems and devices disclosed herein may be configured to provide diversion assistance by selectively displaying information including the map, one or more of the aircraft ranges, a vertical display, and information regarding one or more airports.

Abstract: A high-lift system on a wing of an aircraft is provided. The wing includes a right-hand and a left-hand wing half with movably held high-lift flaps and the right-hand and left-hand wing half are attached to an aircraft fuselage, thus forming a wing root. Each wing half in a region in close proximity to the wing root, includes a drive unit. In each case this drive unit is joined to a transmission shaft mechanically connected to the respective drive unit, which transmission shaft extends from the drive unit in the direction of the end of the respective wing half and is designed to mechanically move the high-lift flaps arranged in the respective wing half. By means of such an arrangement it is possible to do without deflection gear arrangements from a central drive unit to the individual wing halves.

Abstract: An aircraft thermal control system includes a thermal control unit including an internal circuit, an evaporator and a condenser, the evaporator and the condenser being disposed in the internal circuit. The aircraft thermal control system further includes a cooling circuit which is thermally coupled to the evaporator of the thermal control unit, and a heating circuit which is thermally coupled to the condenser of the thermal control unit.

Abstract: A system for deploying loads out of an aircraft comprises an aerial delivery parachute with an aerial-delivery parachute line and an activation means for placing the aerial delivery parachute in an enveloping flow past the aircraft. Within the aircraft a receiving device can be positioned that receives a tractive force acting on the aerial-delivery parachute line, which tractive force has been determined by a force measuring device and has been transmitted by way of a transmitting device. With the knowledge of the tractive force it is possible both to implement emergency release and to assess whether an aerial delivery parachute has correctly deployed in the flow enveloping the aircraft.

Abstract: A surface element, e.g. a wing, of an aircraft includes a leading edge, a high lift device arrangement positioned along the leading edge and at least one add-on body positioned in a leading edge region, wherein the high lift device arrangement is interrupted in the region of at least one add-on body for preventing collision with the add-on body and wherein the surface element includes an arrangement of openings in a region covering the add-on body, which openings are connected to an air conveying device for conveying air through the openings. Thereby an additional flap for harmonizing the flow above a pylon or other add-on body can be eliminated.

Abstract: Structural component including at least one covering shell and a carrier structure, the covering shell designed in the form of a sandwich and formed by an inner skin section, an outer skin section and a shear-load absorbing core layer disposed between the two sections and connecting the inner and the outer skin sections to one another in a planar manner. The carrier structure is formed by at least one panel-shaped connecting part extending between and transversely to the inner and outer skin sections and connected along a reference longitudinal direction to the covering shell. The connecting part is located outside the carrier structure and fastened to the inner skin section resting thereon in a planar manner, wherein at least one profiled support extending along the reference longitudinal direction is provided in the covering shell in order to form a reinforcing section in the connecting region of the panel-shaped connecting part.

Abstract: A switched-mode power supply device includes a charger (10) to be connected on one side to a direct current electrical network, or rectified alternating current electrical network (RC), a power reserve (11) connected to a second side of the charger (10), and DC-DC output converters (12) delivering regulated output voltages (VS). The output converters (12) are connected by an input to the first side of the charger (10). The charger (10) is a current bidirectional, voltage unidirectional converter which, in a first phase, enables the power reserve (11) to be recharged and maintained charged from the network, where the output converters (12) are powered by the network (RC) and, in a second phase, in the presence of a power brown-out of the network (RC), enables the power reserve (11) to be discharged to power the output converters (12).

Abstract: A heat exchanger for cooling air, with a coolant onward-flow connection for feeding liquid coolant for cooling air and a coolant return-flow connection for discharging liquid coolant. For removing ice by melting accumulated ice in the heat exchanger, a heater is provided that is associated with an electrical heating element. An operational safety device prevents overheating of the heater. The operational safety device comprises a fault-current detection device. Such a heater, with a heating element for heating air for subjecting accumulated ice to heated air, and with such an operational safety device is provided. Also, a galley for a commercial aircraft is provided with a receiving space for trolleys, and a cooling device for cooling the receiving space. The cooling device comprises such a heat exchanger for cooling air.

Abstract: A profile plate portion is disclosed for use as an outer wall of a flow body including a first profile plate panel that is fluid permeable, a second profile plate panel extending along the first profile plate panel, and a reinforcing device for supporting the first profile plate panel and the second profile plate panel on one another. Fluid can flow through the reinforcing device, and/or fluid of the flow present at the first profile plate panel, which flows through the first profile plate panel, can flow through the reinforcing device in the local profile plate thickness direction from the first profile plate panel to the second profile plate panel and in some regions can flow through to an inside that is situated opposite the flow side. A method is disclosed for manufacturing a profile plate portion and a flow body component with a suction-extraction device for fluid.

Abstract: A method for obtaining the inertial properties of a movable rotating around a hinge line in an aircraft control surface. The method includes the steps of removing the mechanical connections of the actuators from the movable, leaving the movable free to rotate around its hinge line, further balancing the movable and calculating in a first approach its coarse static momentum. The method includes refining the coarse static momentum and obtaining simultaneously a frictional momentum of the movable; incorporating an elastic element on the control surface and configuring a second order mechanical system; inducing forced oscillations on the movable at a certain frequency, this frequency being increased until it is sensibly close to the resonance frequency of the movable to produce a wave response; calculating, from the wave response, the momentum of inertia of the movable.

Abstract: A measurement device for measurement of forces in structural components, having a measurement sensor, which is embodied such that it is connected with the structural component in a force-fit and/or form-fit manner, and generates measurement signals as a function of force transfers in the structural component, the measurement device having a measurement casing upon the measurement sensor. Processing of received measurement signals can occur, and the measurement casing has connecting means, for placing in position and releasable attachment of the measurement casing on the structural component, and the contacting means of the measurement casing can establish contact with the measurement sensor for the reception of the measurement signals.

Abstract: The present invention provides a structural element for an aircraft and spacecraft, having a core which includes core regions which are uncoupled from one another by means of an expansion joint arranged between the core regions. The present invention further provides a method for producing a structural element for an aircraft or spacecraft, including the following method steps: providing a core of the structural element, which core includes core regions; and arranging an expansion joint between the core regions. The present invention relates still further to an aircraft and/or spacecraft having such a structural element.

Abstract: A device for exciting a landing gear of an aircraft while it is on the ground. The device includes an oblong bracing foot, a movable support on which the oblong foot is mounted and an arrangement for setting the gear into vibration.

Abstract: A movable joining device for connecting structural components of an aircraft, with joining means moveably arranged on a guiding device situated on the outside of the structural components so as to fixedly connect joining edges of the structural components positioned adjacent to each other, wherein the joining means includes a welding unit that can move on the rail-like guiding device, and is equipped with a special so-called bobbin tool as a tool for friction stir welding.

Abstract: Method for optimising the design of sealing rings of internal manhole covers which close the manhole openings over the inner surface of the skin of an aircraft structure, the surface that is in contact with the inner surface of the skin being the optimized surface of said sealing rings, the method including dividing the outer contour and the inner contour of the optimised surface into n points; grouping into families Fi the sealing rings of each manhole opening; generating the curves that are best adapted to the set of points taken for the outer contour and for the inner contour of each sealing ring for each one of the families Fi; generating a ruled surface among the curves generated for each one of the families Fi.

Abstract: A wing assembly for an aircraft comprising a spar, a wing cover and a rib; wherein the spar has a web portion and a flange portion joined by a radius corner; wherein a gap is formed at an interface between the spar, the wing cover and the rib; wherein the assembly further comprises a seal member which substantially covers the gap, and sealant provided between the seal member and the rib and/or the wing cover and/or the spar so as to seal the gap. Also a method for sealing a gap in an aircraft wing assembly.

Abstract: A wing for an aircraft includes a leading edge and a wing tip extension extending from an end of a main wing region to a wing tip. The wing tip extension includes an arrangement of openings at least from the end of a main wing region to the wing tip along the leading edge, which openings are connected to an air conveying device for conveying air through the openings. Thereby in flight states with a low flight velocity the flow around a wing tip extension can be harmonized such that the drag is decreased and the lift of the wing is increased.

Abstract: An aft aerodynamic fairing for a pylon for attaching an aircraft propelling assembly, including a caisson structure, a heat-shield floor, as well as a support structure for this floor comprising linking parts arranged to link two side edges of this floor to the caisson structure. The linking parts of each side edge of the floor are configured so as to allow travelling motion of the side edge relative to the caisson structure in a corresponding direction included in a plane orthogonal to a longitudinal direction of the fairing. The linking parts form a sliding link between the floor and the caisson structure, reducing the stresses induced by the deformations of these elements in use.

Abstract: A device for forming a microstructured coating on a substrate. The device includes a microstructured band that can be moved by rolling without slipping on the substrate and going around main pressure application elements assembled on a chassis, and secondary pressure application elements assembled on the chassis so as to be in contact with an inner face of the band in a zone of a strand of the band delimited by said main pressure application elements, this zone being exposed to the action of a curing apparatus that accelerates curing of a curable material designed to form said coating. A method for forming a microstructured coating using the above-mentioned device.