Abstract: A system and method for the acoustic analysis of a body, in particular a fuselage structure of an aircraft, is provided including: inputting data for geometry, material, boundary conditions and acoustic parameters of the body, generating a body idealized in terms of its structural mechanics, and a cavity simulating the interior of the body, on the basis of the data inputted as a numerical body model, inputting the geometry of the body with a pattern of nodes and the generation of finite elements, stimulating an acoustic loading case by subjecting the body model to at least one sound pressure wave at a defined frequency, analyzing the effect of the sound pressure wave on the body model, and outputting a sound reduction index (R) for the body with reference to that frequency.

Abstract: The invention relates to a compressor/turbine arrangement for use in an air conditioning unit of an aircraft air conditioning system comprising a process air supply line which is designed to supply process air generated by a process air source to a compressor. A detection device is designed to detect a characteristic signal for the temperature of the process air flowing through the process air supply line. A turbine is designed to drive the compressor. A cooling device is disposed in a process air line connecting the compressor to the turbine and is designed to cool the process air coming out of the compressor and flowing through the process air line in the direction of the turbine. Downstream of the cooling device a connecting line branches off from the process air line and opens into the process air supply line. A control device is designed to control a process air flow through the connecting line in dependence on the signal detected by the detection device.

Abstract: A method and system for displaying information on an electrical display unit in an aircraft cabin including a generating unit for generating at least one signal which clearly identifies the information, a first acquiring unit for wirelessly acquiring the at least one signal and a control unit for controlling the display unit on the basis of the at least one signal. The system may also have a second acquiring unit for acquiring departure and/or arrival location information relating to a flight and a third acquiring unit for acquiring passenger information.

Abstract: A drilling template for use in the field of producing aircraft or spacecraft or parts thereof has a first template part and a second template part. The first template part and the second template part are in each case provided here with means for fixing positions of bores to be produced. The drilling template has coupling means, by which the first template part and the second template part can be coupled to one another in such a way that the coupled template parts are movable relative to one another.

Abstract: A method and a device for the execution of the method for the reproduction of an impact event of a projectile, with any ratio of energy and impulse, wherein a feed rate of an impress element is controlled by taking account of an alteration in velocity that is proportional to the quotient of a resistance force and a freely selected projective mass.

Abstract: A system for rigging a control surface of an aircraft, wherein the control surface is movable relative to a reference structure of the aircraft by means of at least one actuator, comprises a mobile control unit having being connectable to at least one actuator, an input means for commanding a deflection of the control surface, and an optical rigging apparatus having a first rigging component and a second rigging component. The first rigging component is adapted for being mounted on a reference structure to which the control surface is swivably attached and the second rigging component is adapted for being mounted on the control surface itself. Thereby an accurate rigging may be conducted with a clearly reduced number of personnel and a clearly reduced time for completion.

Abstract: A device and a method for determining the position of a movable transportation unit are described. The device and the method are suitable for accurately detecting the position, automatically fixing loads in position and/or loading and unloading transportation units in aircraft in a relatively quick manner. The device includes a movable transportation unit and a detection means. The transportation unit has a recess for receiving a locking unit in order to lock the transportation unit. The detection means detects when the recess in the movable transportation unit is in a position for engagement with the locking unit. The method for determining the position of a movable transportation unit includes moving the transportation unit from an initial position into a target position, providing the locking unit at the target position of the transportation unit, and locking the locking unit by the engagement thereof in the recess in the transportation unit.

Abstract: An insulation arrangement with two or more insulation packages that overlap such that at least one overlapping region is formed and are arrangeable on a fuselage wall is provided. The insulation packages comprise an insulating material and welded cover films. The cover films are realized in an airtight and waterproof fashion and comprise ventilation openings on a side that is directed toward the fuselage wall in an overlapping region. In this way, pressure variations in the insulation packages can be compensated with relatively dry air that originates from a gap between the insulation packages and the fuselage wall in order to thusly reduce the accumulation of condensation water in the insulation packages.

Abstract: The invention relates to an assembly for storing objects in the cabin of a vehicle, comprising at least one frame with attachment means, and at least one holding device for mounting the objects, wherein the frame has a contour that, at least in some regions, essentially corresponds to the interior contour of a storage container so that the frame can be arranged in the storage container and can be attached in the storage container with the use of the attachment means, and wherein the holding device can be removably stored in the frame. The assembly according to the invention can be placed in a preassembled state in the vehicle, thus reducing the time required for installation and maintenance, while at the same time making better use of the available space.

Abstract: An equipment module for a vehicle comprises a floor element, at least one first inductive coupling element and at least one electronics unit. The floor element comprises at least one attachment means, which can be reached from the top, for attaching items of equipment, and on the underside at least one retaining means for attaching the floor element at a positioning space in a vehicle. The first inductive coupling element is arranged on the floor element and is connected to at least one electronics unit. The electronics unit is adapted for providing an identification signal by way of the first inductive coupling element, which identification signal makes it possible to identify the equipment module. The invention makes it possible to quickly reconfigure a cabin of a vehicle, and makes it possible for the vehicle to quickly identify all the reconfigurable installations for adapting items of equipment on the vehicle side.

Abstract: A tie bar for connecting an equipment fitting of an equipment module to a structure fitting of a fuselage cell structure. At each end the tie bar has a fork head each with a fork head hole for a bolt. The spacing between the fork heads can be continuously adjusted. A captive bushing is utilized for sound and vibration decoupling. The bushings which are a press fit in the fork head holes can no longer fall out during the handling of the tie bars 10. The dimensions of the bushings made of plastic are adapted to the respective application scenario by a tolerance calculation and guarantee an effective sound and vibration decoupling between the structure fitting and the equipment fitting.

Abstract: The invention relates to an air supply system of an aircraft, in particular of a passenger aircraft, which comprises a fresh air system, through which fresh air can be supplied to an aircraft cabin, a circulating air system, which is coupled to the fresh air system and through which used cabin air can be supplied to the fresh air system, a cooling air system for cooling an air conditioning system of the aircraft disposed in the fresh air system, and a ventilation system coupled to the cooling air system for ventilating an installation space of the air conditioning system. The air supply system includes a device for fluidically coupling the cooling air system and the ventilation system. The device is disposed and configured inside the fuselage of the aircraft such that the air in one system can be driven through the air flow in the other system. The invention also relates to a method for mixing two air streams in an air supply system of this kind of an aircraft.

Abstract: An apparatus for aligning segments with one another include a positioning device and a projection device, installed on the construction site, projecting projection lines onto the segments from different directions so that distances between the projection lines and reference points applied to the segments can be determined. The position of the individual reference points on the segments can be determined with reference to a coordinate system by an evaluation device. Based on the spatial arrangement of the reference points, theoretical best-fit planes and best-fit lines are then generated for each segment. The segments are levelled by moving the positioning device or adjusting the shortest possible distance between the theoretical best-fit planes and best-fit lines to the projection lines and are aligned by again moving the positioning device so that the distances between the theoretical best-fit planes and best-fit lines of the first segment and of the second segment are minimised.

Abstract: A line bracket for mounting on a support structure of an airplane, includes a mounting section for attachment to the support structure and a U-shaped bracket section for receiving at least one line. The support structure can be closed by a cover part (by a clip-on connection, wherein the mounting section is configured to be plate-like for resting against the support structure, a floor region of the U-shaped bracket section extends essentially at a right angle away from the mounting section, and a first leg region of the bracket section is formed by part of the mounting section and corresponds to an opposite second leg region for forming an insertion opening for the line, which insertion opening) is closeable by way of the cover part that is hinged at the end of one of the leg regions, to install the line from the side in the bracket section.

Abstract: A locking mechanism, in particular suitable for use in a decompression arrangement, includes a pressure chamber surrounded by a delimiting wall, wherein at least a section of the pressure chamber delimiting wall is formed by an actuating element which is in a rest position when the pressure in the interior of the pressure chamber corresponds to the ambient pressure and moves into a differential pressure position when the pressure in the interior of the pressure chamber exceeds the ambient pressure by a predetermined differential value. The locking mechanism further includes a locking bar which is kept in a locked position when the actuating element is in its rest position and is movable into an unlocked position when the actuating element is in its differential pressure position.

Abstract: An aircraft door arrangement having a pivotable door for closing an aperture in the fuselage of an aircraft and selectively movable between closed and open positions by a linear actuating mechanism having a casing and a rod selectively extendable and retractable. An actuator mounting mounts the casing between two elements of the primary structure of the aircraft. The rod is pivotally coupled to the door. The actuator mounting includes a rigid mounting component including three legs extending in a common plane together with the casing and the rotation axis and each having a first and a second longitudinal end. The first and second legs symmetrically extend from the casing at an angle at opposite sides thereof. Each of the second ends of the first and second legs is rotatably coupled on the rotation axis to another one of the spaced elements of the primary structure of the aircraft.

Abstract: An arrangement for reinforcing a fiber composite component for the aviation and aerospace industry, in which a reinforcing element having a receiving region and a pressure element adapted to the receiving region geometry are provided. The pressure element is inserted into the reinforcing element receiving region. The reinforcing element and the inserted pressure element are fastened relative to one another in a reproducible manner by a reversible fastening device. The fastening device includes a first fastening portion mounted on the pressure element and a second fastening portion which can be mounted on the reinforcing element. The reinforcing element, together with the pressure element fastened thereto, is then applied in a reproducible manner to the fiber composite component cured to connect the reinforcing element to the fiber composite component. The reversible fastening device and the pressure element are then removed from the reinforced fiber composite component.

Abstract: A locating device for locating at least one apparatus which is arrangeable on board a transport unit, for example an aircraft, a locating system having such a locating device and at least one apparatus to be located, an aircraft having a locating system of this type, an associated method for locating at least one apparatus which is to be located and is arrangeable on board a transport unit, for example on board an aircraft, and a computer program for carrying out the method. The locating device includes a detecting unit for detecting a wireless audio signal transmitted by the apparatus to be located; and a computing unit for determining the distance of the apparatus to be located from the detecting unit based on the wireless audio signal and on a first information signal assigned to the audio signal and transmitted via a first deterministic data connection.

Abstract: A waste compaction system for a vehicle includes a moveable trolley for storing waste, and a docking station integratable into a cabin monument for inserting the trolley. The trolley includes a housing having an opening for inserting waste, a vacuum waste compacting mechanism inside the housing and a first suction port accessible from outside the housing, the first suction port being couplable with the vacuum waste compacting mechanism. The docking station and the trolley are adapted to each other such that the trolley is engageable with the docking station, and wherein the docking station includes a second suction port couplable with a suction line in the vehicle and the first suction port. Resultantly, a lightweight and efficient waste compaction system is provided, which allows moving the trolley for collecting waste inside a cabin of the vehicle.

Abstract: An aircraft door includes an outer shell with an exterior and an interior, a stiffening structure arranged on the interior of the outer shell, and at least one door seal arranged on the interior of the outer shell. The door seal is circumferential in an edge region. In the edge region between the outer shell and the door seal at least one circumferential stiffening component is arranged that is connected to the stiffening structure. Thus, in a particularly simple manner and without modifications to a stiffening structure, an aircraft door may be provided with very substantial stiffness in an edge region.