Abstract: Thermal test apparatus comprising a specimen supported by a fixture, a thermal shroud comprising a flexible insulating fabric forming an enclosure around at least a portion of the specimen, and a temperature controlled air supply connected to an opening formed in the enclosure for delivering a supply of temperature controlled air into the enclosure. Also, a method of conducting a thermal test.

Abstract: Disclosed is a display system for an aircraft cockpit. The display system includes a plurality of display devices, each of which comprises at least one viewing screen configured to display a display format, and a cursor management unit linked to each display device and configured for moving a cursor over sensitive objects on the viewing screens of the display devices.

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 retaining nut comprises a nut body and a plurality of axially extending integrally formed deflectable locking fingers. The locking fingers have a frusto-conical surface opposite a threaded surface. The frusto-conical surface of the locking fingers are adapted to co-operate with a conical washer. Tightening the threaded nut on a threaded shaft against the washer causes the locking fingers to deflect radially towards the shaft. This provides a secure radial clamping of the nut on the shaft.

Abstract: A process for producing a panel for acoustic treatment including a resistive porous layer, an alveolar structure, a reflective layer with openings, and a drainage plate having a furrow for delimiting at least one evacuation pipe when the drainage plate is flattened against the free surface of the reflective layer, includes: shaping the reflective layer according to its final geometry, affixing a demolding film on at least one portion of the free surface of the reflective layer, positioning on the demolding film a core whose cross-section is adapted to that of the evacuation pipe so that the core covers the openings of the reflective layer, molding the drainage plate on the demolding film and the core, demolding the drainage plate and removing the core and the demolding film, and making the drainage plate integral with the free surface of the reflective layer.

Abstract: A heating system according to the invention comprises a heating layer that is integrated into a prepreg layer of a high-resistance prepreg material. The heating layer may comprise a bonded heating fabric, a metal oxide coating or electrically conductive threads. According to the invention, the heating system is integrated into a component to be heated. This component may consist, for example, of a floor panel for an aircraft.

Abstract: A process for manufacturing a piece made of composite material with a hollow form and including a fiber preform (50) that is embedded in a matrix, includes placing the preform (50) in a first chamber (64) delimited by a mold (52) that is in contact with the surface of the piece to be produced outside of the hollow form and a counter-mold (54) that is in contact with the surface of the piece to be produced inside of the hollow form, and using a mold (52) that is made in at least two parts (52.1, 52.2) and elements (78) for controlling the spacing of the at least two parts (52.1, 52.2) that are contiguous using the expansion phenomenon during the polymerization phase.

Abstract: The present invention provides an arrangement for passing a line in a load-free manner through a pressure frame of a fuselage of an aircraft or spacecraft, including an opening penetrating the pressure frame, through which opening the line is passed, the line being mechanically decoupled from the pressure frame; and a flexible sealing device arranged outside the opening at least in portions, which sealing device is simultaneously operatively connected to the line and the pressure frame for the pressure-tight separation of a first side from a second side of the pressure frame. The present invention also provides a fuselage for an aircraft or spacecraft having an arrangement of this type and an aircraft or spacecraft having an arrangement of this type or having a fuselage of this type.

Abstract: A joint comprising first and second rib components, the first rib having an abutment surface and a plurality of lugs disposed adjacent to the abutment surface; and the second rib having an abutment surface and a plurality of lugs disposed adjacent to the abutment surface, wherein the abutment surfaces of the respective ribs are abutting and joined with a tension joint, and wherein the lugs are pinned to form a pinned lug joint by aligning respective holes in the plurality of lugs such that the lugs of the first and second ribs are interleaved and have one or more pins passing through the aligned lug holes. The joint may be used for attaching a wing tip device to the outboard end of an aircraft wing.

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 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 three-phase induction machine with a starting winding and a running winding and a winding change-over switch which switches over a flow of current between the starting winding and the running winding, wherein a phase of the phases of the starting winding and a corresponding phase of the phases of the running winding of the three-phase induction machine are supplied with electrical energy by a common electrical supply line, and wherein one phase of the phases of the starting winding and the corresponding phase of the phases of the running winding are electrically interconnected by an electrically conductive connection in the three-phase induction machine. Also provided is a method for operating a three-phase induction machine as well as an aircraft or spacecraft which has a corresponding three-phase induction machine.

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: 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 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: 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: 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: 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: 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: 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.