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: 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: 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: 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 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.

Abstract: The invention pertains to a method and apparatus for verifying the consistency of the values given by an angle of attack probe of an aircraft. The method and apparatus verifies the proper operation of the angle of attack probe by using the aircraft's vertical load factor measurement provided by an accelerometer to estimate the angle of attack and then comparing the estimated angle of attach with the measure angle of attack.

Abstract: A method for determining the thrust of at least one engine, which is held on a supporting structure of a vehicle, includes the steps of acquiring the elongation of at least one structural element onto which the thrust of the at least one engine acts, by means of at least one strain gage; calculating the force causing the elongation in the at least one structural element, taking into account the materials characteristics of the structural element; and determining the thrust of the at least one engine as an effective force component in the direction of thrust of the vehicle. It is thus not necessary to carry out an estimate of the thrust on the basis of other physical variables such as shaft speeds, pressure or exhaust gas temperature of engines.

Abstract: An aircraft structural assembly includes an area element which has a core and an outer layer. A first surface of the area element is convexly curved, at least in certain sections, relative to an imaginary central area of the area element extending through the core of the area element. By contrast, a second surface of the area element located opposite the first surface is oriented, at least in certain sections, parallel to the imaginary central area of the area element extending through the core of the area element. The area element is configured in the form of a floor panel of a floor system. The first or the second surface of the area element is designed to form a walkable floor surface of the floor system in the state of the aircraft structural assembly when mounted in an aircraft.

Abstract: A keel beam connected to a central wing box of an aircraft and ensuring the connection between a front structure and a rear structure of an aircraft is characterized in that it includes, on the one hand, a U-shaped body with a horizontal base and two solid lateral walls, and on the other hand, a cover which has a U shape oriented in the same manner as the body, with a base in the lower portion and curved edges, the ends of which are oriented upward so that each curved edge includes an outer surface flattened against and fixed to the inner surface of the lateral walls in order to define, with the body, a closed section, the cover including openings for accessing the inside of the keel beam.

Abstract: An aircraft having an aircraft fuselage that has an outer skin includes an air sucking fuselage component with an outer surface that is perforated at least in some regions, and a suction profile body. The suction profile body is arranged on the outer skin, forms a local bulge in the outer skin, and further includes a suction opening that is arranged at a location at which there is the lowest pressure, for example at a position furthest away from the outer skin. The suction opening is connected to a suction connection of the air sucking fuselage component. In this way laminarization of the flow at the air sucking fuselage component may take place without the use of active air conveying devices.

Abstract: A sensor device for a fuel system, the sensor device comprising sensing means configured to sense a property of fuel within the fuel system, and transmitting means configured to wirelessly transmit a signal representative of the sensed fuel property to a remote receiver. Also a sensor device comprising a photo-diode which is operable to function as an antenna or part of an antenna for the device. Also a method for communicating with a plurality of sensor devices.

Abstract: An integral composite wing spar (12) and composite stiffener (32) formed by simultaneous curing of the matrix components in a specialised tool. A method of manufacture and tool is also provided.

Abstract: The invention provides a filter for a pipe, the filter comprising an attachment portion for attaching to the pipe, and a filter surface for presentation to and filtering of an oncoming flow of the pipe, wherein the filter surface has at least one pointed apex for protruding into the oncoming flow. The invention also provides a pipe for transporting an oncoming flow, wherein the pipe is provided with a filter surface across the cross-sectional area of the pipe and wherein the filter surface has at least one pointed apex protruding along the longitudinal axis of the pipe. The invention also provides an aircraft with such a filter or pipe and a method of filtering an oncoming flow of a pipe.

Abstract: The invention concerns a reinforcement device for the purpose of reinforcing a main load-bearing covering panel, also a corresponding main load-bearing covering panel, a structural component of a flow body, and also a corresponding flow body. Here the reinforcement device serves the purpose of accommodating and transferring forces and/or stresses in the interior of the covering panel. In accordance with the present invention, in addition to forces and/or stress in the normal direction, forces and/or stresses in a crosswise direction, that is to say, for example, transverse stresses and/or shear stresses, can also be accommodated and transferred.

Abstract: An aircraft nacelle comprising a lip extended by an inner conduit forming an air intake, a front frame delimiting with said lip an annular channel wherein hot air circulates, as well as a panel for acoustic treatment comprising, from outside inwardly, an acoustic resistive layer, at least one honeycomb structure, and a reflective layer, as well as ducts for channeling hot air with each one inlet communicating with the annular channel and one outlet communicating with the inner conduit, wherein the panel for acoustic treatment comprises, upstream from the ducts, an annular channel which extends over at least a portion of the nacelle circumference, at least one conduit providing communication between said annular channel and the upstream annular channel, and a plurality of ducts that open into said downstream annular channel, the panel for acoustic treatment being connected to the front frame in regard to the annular channel.

Abstract: A device for manually painting a large surface using a spray gun connected to a paint feed line for the supply of an enamel paint and to a pressure line for the provision of compressed air. After the manual actuation of an operating switch arranged on a handle piece, the spray gun sprays the enamel paint by compressed air via a spray head to apply the enamel paint onto the surface. The spray gun includes means such that it can be moved manually along the surface. The means include an extension rod, at one end of which the spray gun is attached by the handle piece and which is configured such that, when held by an operator on an arm holder configured at the opposite end, it extends from the elbow along the forearm of the operator and beyond the distal end of the forearm.

Abstract: Interactive dialog devices and methods can be installed on an aircraft for communication between an operator of the aircraft and a guidance system of the aircraft. A dialog device can include a global screen configured for displaying guidance information related to each of a navigation display, a vertical display, and a primary flight display. The global screen can include at least one graphic object which is produced in the form of an interaction element which represents a control feature that can be grasped and moved by an operator to modify a value of at least one guidance target of the guidance system associated with one or more of the navigation display, the vertical display, or the primary flight display.