Abstract: A computer-implemented method of modelling a root-mean-square stress in a structure induced by a random load. The method comprises determining a modal correction factor based on data representing the eigensolution for the structure in free vibration. The modal correction factor characterizes the proportion of the random load, which is attributable to the root-mean-square response of the structure. Once the modal correction factor has been calculated, it is applied to data representing a stress in the structure due to a forced vibration to thereby determine the root-mean-square stress induced by the random load.

Abstract: A device for machining a slot on a surface of a cellular structure includes a machining head that includes a chassis, a rotary tool rotating about a tool axis perpendicular to the direction of the slot, two guide wheels arranged on either side of the rotary tool that have a plurality of teeth configured and positioned such that they penetrate the cells of an alignment of the cellular structure. The machining head includes a link between the chassis and at least one guide wheel that enables a degree of freedom in a lateral direction parallel to the tool axis such that the guide wheel is movable in relation to the rotary tool in the lateral direction.

Abstract: A preferred method of the invention is executed by code stored on a non-transient medium to control a portable computing device with a touchscreen. The code generates graphical interfaces includes an application that allows a user to capture necessary data for reporting data to permit quick and efficient diagnoses of repairs by a repair service to a part or sub-assembly of an aircraft. The data acquisition is controlled and guided with reference to actual aircraft specifications that are updated by an aircraft part supplier, such as an aircraft manufacturer.

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 fuselage includes a fuselage section with an inner surface having a non-circular contour and a spherical pressure bulkhead with an outer edge. The outer edge of the spherical pressure bulkhead is attached to the inner surface of the fuselage section and extends along a line, which is non-circular. The line is a three-dimensional curve extending parallel to the inner surface of the fuselage section. An aircraft and a method for manufacturing a fuselage are also described.

Abstract: A structural component, in particular for an aircraft, having a skin and at least one stiffening element for stiffening the skin. Opposite to a run-out of the stiffening element at least one supporting element is positioned. The at least one supporting element defines a supporting area that is opened to the stiffening element run-out in longitudinal direction of the stiffening element run-out and that is closed in transversal direction of the stiffening element run-out.

Abstract: A drive system for driving control surfaces of an aircraft includes at least one drive unit, at least one main shaft connectable to the at least one drive unit and at least two adjusting units for each control surface to be driven. Each adjusting unit includes a differential, two rotary actuators and an adjustment lever. The differential has at least one input means and two output means and is adapted to transfer torque from the at least one input means to the two output means. The input means is connectable to the main shaft, the two rotary actuators each have a rotation input means and a motion output means. The rotation input means is connectable to one of the output means of the differential each and the adjustment lever is connected to the motion output means of both rotary actuators.

Abstract: A transport device for use when mounting interior component modules in an aircraft includes an undercarriage and an interior component module carrier unit. The interior component module carrier unit is supported on the undercarriage and is adapted to be connected to an interior component module, which is preassembled outside of the aircraft, in order to transport the interior component module with the aid of the transport device into a final assembly position in an aircraft fuselage element. At least a part of the interior component module carrier unit is movable relative to the undercarriage such that an interior component module connected to the interior component module carrier unit is movable horizontally and vertically relative to the undercarriage.

Abstract: Redundant storage devices in particular suitable for so-called SSD electronic disks. A data storage system is proposed based on a plurality of redundant physical storage disks in which the read/write commands intended to be sent to the redundant disks are subjected to a transfer function before being sent to at least one of the disks so that the actual commands sent to at least two disks are different. The values returned by the disks that received the commands that had undergone the transfer function are subjected to the inverse transfer function. Thus, a design error in the control module of the disks will be detected, since the control modules of the disks will not be called identically.

Abstract: The present invention relates to an aircraft cockpit with a double flight deck in which a central pane of a windscreen can be removed in order to at least partially clear an opening in order to constitute an emergency exit and ensure natural ventilation of the cockpit. Moreover, a central portion of a glare shield and of a flight station instrument panel are optionally moveable in order to facilitate access to the opening in the event of the need for emergency evacuation.

Abstract: A method of laying up a segment on a layup surface using a layup head that is mobile with respect to the layup surface, the layup head supporting a spool of a tape of material which includes at least one layer to be laid up from which said segment is cut and at least one interliner, the method including applying the tape of material against the layup surface and removing the interliner using a separator. The tape of material is pressed firmly by a press roller against the layup surface before the interliner is removed as the layup head moves in an advancing movement. A layup head for implementing the method and a layup machine including the layup head are also described.

Abstract: A draining apparatus for draining liquids from a vehicle includes a containment; a drain mast having an outlet opening and an inlet; and an actuator. The containment is adapted for being coupled with a structure of the vehicle, wherein the actuator is coupled with the drain mast and adapted for moving the drain mast into a retracted position and at least one extracted position relative to the containment, and wherein the containment is further adapted for accommodating the drain mast in the retracted position at least partially. The drainage apparatus has clear advantages regarding the parasitic drag compared to known drainage masts as it is only deployed into the flow when it is absolutely necessary.

Abstract: Device intended for a double glazing including at least one outer glazing and one inner glazing separated by an intermediary space filled with a gas, used to isolate an inside environment from an outside environment, a pressure variation being liable to occur between these environments, for example in the case of an aircraft in flight, includes means for conserving the outer glazing and the inner glazing of this double glazing mainly parallel, independently of this pressure variation. The invention also concerns a double glazing including this device, the process for maintaining parallelism and software using the process.

Abstract: The present invention provides a fireproof bulkhead, having a highly porous structure with an intumescent coating, the highly porous structure being formed as a reticulated foam or as a highly porous pimple or nub structure.

Abstract: An aircraft monument for installation in an aircraft cabin including a first functional module, the first functional module including a side wall for delimiting the first functional module from a region of the aircraft cabin adjacent to the first functional module and/or from a region of the aircraft monument adjacent to the first functional module. The side wall is movable between a first and a second operational position and comprises a side-wall region which merely in the second operational position of the side wall serves for delimiting the first functional module from a region of the aircraft cabin adjacent to the first functional module, so that a movement of the side wall out of its first operational position into its second operational position results in an enlargement of a base area of the first functional module.

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 leading edge slat arranged on the aerofoil of an aircraft. The leading edge slat is provided on the front of the main wing. The leading edge slat has a partially extended setting, with its trailing edge flat against the wing, and a further extended setting, with its trailing edge spaced apart from the nose of the wing to open a gap feeding high-energy air from the lower surface of the slat to the upper surface of the wing. The leading edge slat includes a body and a trailing edge facing the main wing, which can be bent around the spanwise direction of the slat relative to the body, and on which the trailing edge of the slat is provided, and which by means of a device generating a contact force is loaded for making contact between the trailing edge of the slat and the profile nose of the wing.

Abstract: A method for joining parts to be joined which are subject to tolerance in the aerospace sector. The method involves determining the geometric data of a first and second part to be joined, determining the joining gap dimensions of the first and second parts from the determined geometric data and arranging a plurality of shape elements which can be connected together in planar manner in a first region of a surface of the first part. The method moreover comprises application of a first adhesive layer onto the plurality of shape elements and in a second region of the surface of the first part. The method finally involves joining the first and second parts, the first adhesive layer being brought into contact with the surface of the second part. A corresponding apparatus is provided for joining parts which are subject to tolerance in the aerospace sector.

Abstract: A method, apparatus and computer program product for modeling the non-linear structural response of a component. The non-linear structural response is modeled using a two-step global-local finite element analysis method, which employs a linear global analysis step, a linear intermediate analysis step and a non-linear local analysis step. The boundary conditions applied in the intermediate step are derived in part from the linear global analysis and the boundary conditions applied in the local analysis are derived in part from the global and intermediate analyses.

Abstract: A method for measuring large components, including providing a large component with markings on at least one outer surface at predefined and spaced-apart locations, providing a camera sensor system having at least one camera and one image analysis device for evaluating a camera image, wherein the position and orientation of the camera in relation to a reference point at a distance from the camera are determined, recording camera images of the individual markings using the camera and transmitting the camera images to the image analysis device, evaluating the camera images using the image analysis device, wherein the position of the individual markings in relation to the position of the camera is determined, and calculating the position of the markings in relation to the reference point from the position of the camera in relation to the reference point and the position of the markings in relation to the camera.