Abstract: An aircraft structure includes a skin (28) that is reinforced in two directions: by a first family of stiffeners called stringers (30) that are arranged in the longitudinal direction of the aircraft, and by a second family of stiffeners called frames (32) that are arranged in planes that are perpendicular to the longitudinal direction and that ensure the taking up of orbital forces, characterized in that at least one frame (32) has a hollow cross-section that is delimited by a closed profile, produced for a given cross-section in a single piece, of which one portion is in contact with the skin.

Abstract: A scanner comprises a scanning array mounted within a rotatable assembly having a first wheel on a first side, a second wheel on a second side and a membrane forming a drum around the array wherein a load path is provided between the wheels to divert load from the membrane such that it can be made thinner.

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: A method is provided for repairing an aircraft structural component which has a component fault in a portion adjoining a cavity of the aircraft structural component. The method includes removing a region of the aircraft structural component that has the component fault, introducing an expansion body into the cavity of the aircraft structural component through an opening that has been formed by the removal of the region of the aircraft structural component having the component fault, wherein the expansion body while being introduced into the cavity of the aircraft structural component is in a non-expanded state, converting the expansion body that has been introduced into the cavity of the aircraft structural component to an expanded state, and closing the opening by means of a repair material.

Abstract: In a method for manufacturing components from composite fiber materials, at least one placeholder is inserted into a recess in a molding tool, wherein the unfinished component is subsequently produced, the placeholder is removed, at least one lifting pad is inserted into the recess and the unfinished component is removed from the molding tool by inflating the lifting pad. In a system for manufacturing components from composite fiber materials, the component removal process is monitored and controlled by a computer unit in order to prevent predetermined maximum component loads from being exceeded. The gentle component removal process makes it possible to avoid consequential costs for repairing or reworking the components.

Abstract: A method for performing a dimensional inspection of a fabricated composite part (9), comprising steps of: a) Providing a number of points (Iij, Oij) to be inspected in its inner and outer surface; b) Obtaining the positional data of said points (Iij, Oij) from the fabricated composite part (9) hold in a position that allows the access to its outer and inner surfaces as a first set of positional data (WIij, WOij); c) Using said first set of positional data (WIij, WOij) and a second set of positional data (TIij, TOij) of the same points (Iij, Oij) obtained from an analytical model defining its theoretical geometry for calculating the deviations between them taking into account the deformations suffered by the fabricated composite part (9) in said position. The invention also refers to a workstation (11) for performing the method.

Abstract: A method of making a shim comprises the steps of providing a first structural component, such as a rib foot of an aircraft wing. The rib foot is then scanned or mapped to generate the surface profile of the rib foot. The shim is then formed to include a feature on its surface which complements the surface profile of the assembly surface.

Abstract: The invention relates to an odor seal for a vacuum toilet drain system whose cross section in the state of no throughflow tapers off in such a way in the downstream direction that the interior walls on the downstream end of the odor seal rest against each other so that the odor seal in a downstream direction allows throughflow while in the opposite direction it blocks throughflow, wherein the downstream end of the odor seal is closed in the state of throughflow and no throughflow of the odor seal. Furthermore, the invention relates to a drainage device comprising such an odor seal and a sieve which is arranged upstream of the odor seal. Moreover, the invention relates to a vacuum toilet system for an aircraft, comprising such an odor seal or a drainage device.

Abstract: The invention relates to a device for holding an insulating blanket and for fastening systems in an aircraft, comprising a base having two ends from each of which an arm extends. At least one arm has a U-shaped part having two more or less parallel branches, and in that the said device further comprises at least one support for accommodating a system. The invention also relates to an aircraft fuselage section comprising frames, an outer skin, stabilizers and at least one insulating blanket. This section comprises at least one holding device such as described above, mounted so that a frame is situated between the arms of the holding device so that the blanket is between the frame and the holding device.

Abstract: An aircraft fuel cell system includes a fuel cell which has an oxidant inlet for supplying an oxygen-containing medium to the fuel cell. An oxidant supply line has a first end which is connected to the oxidant inlet of the fuel cell. A second end of the oxidant supply line is connectable to a used air outlet of a cabin of the aircraft. A heat exchanger is located in the oxidant supply line and thermally couples the oxygen-containing medium flowing through the oxidant supply line and a second medium flowing through an air conditioning process air line of an air conditioning unit, the heat exchanger being located downstream of a cabin air compressor in the air conditioning process air line.

Abstract: A fuel cell system for an aircraft is stated, which fuel cell system comprises a fuel cell unit and a suction module. The suction module is used to draw oxygen through the fuel cell unit. No vacuum generators are used during cruising flight.

Abstract: The invention relates to a transport cart (10) for loading an aircraft galley, comprising a base element (12) and a plurality of wheels (14) attached to the base element (12). Two frame elements (20, 24) are connected to the base element (12) and disposed at a distance from each other. A first guide device (28, 28?, 28?) is set up for engaging a complementary second guide device formed on a box that is receivable in the aircraft galley to be loaded and for transporting on the transport cart (10). The first guide device (28, 28?, 28?) is further set up for securing the box against displacement on the transport cart (10) in a direction perpendicular to a longitudinal axis (L) of the transport cart (10) when engaged with the complementary second guide device formed on the box. The transport cart (10) finally comprises a locking mechanism (40, 40?) which is set up for securing the box against displacement on the transport cart in a direction parallel to the longitudinal axis (L) of the transport cart (10).

Abstract: The invention relates to a device for receiving baggage in a passenger cabin for aircraft, which device comprises a stowage compartment, also referred to as a “hatrack”, which stowage compartment is arranged above a seat row so as to be swivellable in longitudinal direction of the aircraft. The hatrack includes a single-part housing that forms a baggage receptacle. Starting from an open loading position, the housing is swivellable to a transport position or stowage position on a pivot axis that is arranged near the centre of gravity and that is associated with a bottom of the housing. For affixation of the hatrack the housing is connected to a structure of the aircraft fuselage, which structure is fixed to the aircraft, by means of an exterior frame.

Abstract: An aircraft assembly comprising a plurality of structural components and an electrically conductive bonding network, wherein at least one of the structural components is formed of material of low electrical conductivity, and the bonding network includes either: at least one substantially planar strip of highly electrically conductive material attached to at least the one structural component, and wherein the strip includes a substantially omega-shaped loop extending out of the plane of the strip; or at least one strip of highly electrically conductive material attached to at least the one structural component, wherein the strip comprises first and second planar attachment portions for attaching the strip to the structural component(s) and an intermediate portion extending between the first and second attachment portions, and wherein the intermediate portion includes a loop which extends outwards from the plane of the first attachment portion.

Abstract: The invention relates to a vortex generator (10), in particular for a model (12) in a fluid-dynamic channel. In order to save time during the development of vehicles, in particular aircraft, in particular to save wind tunnel time, it is suggested to configure the vortex generator (10) switchable. Further, the invention relates to various uses of such a switchable vortex generator (10), in particular on models in fluid-dynamic channels and in fluid-dynamic channel tests.

Abstract: An area projection system for reproducing a visual signal on a surface, comprising a light source, a fiber element comprising a plurality of light guide elements, a carrier element and imaging optics, wherein the fiber element comprises a first end and a second end, wherein the first end of the fiber element is arranged on the light source and the second end of the fiber element is arranged on the carrier element, wherein the imaging optics are arranged on the second end of the fiber element, wherein the area projection system is adapted to transmit a visual signal from the light source to the fiber element and subsequently to the imaging optics, and wherein the imaging optics are adapted to reproduce the visual signal on a surface.

Abstract: A simulation or test system for a network architecture of computers and active equipment items, in particular on board an aircraft, and a corresponding method are disclosed. The system comprises a simulation unit comprising models simulating at least one part of the computers. Moreover, each computer or simulation model is able to communicate on a real network through a corresponding active equipment item to which the computer, simulated if need be, is directly connected in the network, and the simulation unit may acquire a message sent out by a computer or a simulation model on the network, and transmit the acquired message to simulation models that are recipients thereof. The simulation unit acquires the message at the corresponding active equipment item to which the sending computer or simulation model is directly connected.

Abstract: An aircraft structure is provided that includes, but is not limited to structural elements, a first multitude of lines that are in a fixed manner connected to structural elements, a second multitude of lines that are in a fixed manner connected to structural elements and whose longitudinal direction intersects the longitudinal direction of the first multitude of lines so that the longitudinal directions of the lines form a network that covers the aircraft structure at least in some sections, and connecting elements in order to, in the state of the structural elements installed in the aircraft structure, connect selected lines of the first multitude to selected lines of the second multitude of selected points of intersection of the network in order to in this way form transmission lines, such as lines for electricity transmission and/or data transmission. Furthermore, a method is provided for manufacturing such an aircraft structure.

Abstract: A wing structure is provided, wherein the wing structure comprises; an upper covering, a lower covering, and a spar, the spar comprising; a spar web, an upper spar cap attached to the upper covering, and a lower spar cap attached to the lower covering, the wing structure also comprising a face spaced apart from the spar web extending between the upper and lower spar caps. The wing structure is arranged to contain fuel in a fuel containment area between the upper and lower coverings on one side of the spar web. The upper and lower spar caps extend from the spar web only on the other side of the spar web to the fuel containment area.

Abstract: A device for the temporary position fixing of adjacently arranged aircraft structures to be interconnected includes a support frame with at least one vacuum suction cup for temporary surface attachment and with clamping means for the position fixing of the aircraft structures to be interconnected. The support frame with the at least one vacuum suction cup in the region of a transverse gap is attached on the side of one aircraft structure. The support frame includes mechanical contact pressure means for the gap-bridging position fixing of the adjacent other aircraft structure. On the support frame there is a counter support to pressure elements of the contact pressure means.