Abstract: A modular cabin segment for a vehicle includes a first lateral segment module that accommodates a first toilet arrangement with at least one toilet compartment and a second lateral segment module, wherein in each case an outer lateral face of the first segment module and of the second lateral segment module is designed to adapt in each case to an inner wall of a cabin of the vehicle so as to correspond to the aforesaid. At least one of the modules includes at least one cabin attendant seat that on one side is held on the at least one module so that it can be pivoted on an axis. In this manner very good integration of many different functions in the manner of a construction kit is achieved in order to be able to accommodate a greater number of passenger seats elsewhere within the limited space provided in a cabin.

Abstract: A tray arrangement is provided. The tray arrangement includes a tray element with a first side and a second side. The tray arrangement also includes a bearing arrangement for the tray element. The tray element is supported on the bearing arrangement and the second side comprises a holding arrangement for a mobile device. The bearing arrangement is configured to pivot the tray element about at least an axis which lies in a plane of the tray element or parallel thereto.

Abstract: An auxiliary power system for an airplane includes at least one fuel cell unit each with at least one fuel cell, a voltage output, a fuel intake and an outlet for reaction products, a fuel tank that is couplable with the fuel intake of the fuel cell unit, at least one compressor unit with an air intake and air outlet and an electric motor, which is couplable with a voltage output of the at least one fuel cell unit and, by way of a shaft, with the at least one compressor unit. At least the at least one fuel cell unit, the compressor unit and the electric motor are interconnected to yield a coherent unit, which continuously provides electrical power and pressurized air.

Abstract: An aircraft fuselage including an outer skin that is stiffened by way of a backing structure and that delimits at least one passenger cabin and one cargo hold. In the vertical direction of the fuselage, the cargo hold is arranged below the passenger cabin. The backing structure in the cargo hold above a cargo-hold floor framework comprises at least two lateral quasi-joints, and below the cargo-hold floor framework comprises at least one further quasi-joint. In the cargo hold, in the longitudinal direction of the fuselage, a multitude of energy absorption devices, arranged one behind the other and acting in the transverse direction of the fuselage, are arranged for absorbing tensile loads.

Abstract: An energy supply system, an aircraft and spacecraft using such an energy supply system and a method for providing electrical energy with the energy supply system. The energy supply system comprises an energy source which generates a direct current or a direct voltage. A converter is coupled to the energy source and is designed to convert the generated direct current or the generated direct voltage into an output current specified for the energy supply system or an output voltage specified for the energy supply system. A switching device is designed to couple an output of the energy supply system to the converter or directly to the energy source as a function of the electrical power required by the energy supply system.

Abstract: A flow body having a surface, a leading edge has an active flow control system. The active flow control system includes a plurality of openings, at least one control pressure varying device and at least one fluidic actuator with an interaction chamber having an inlet connectable to an air source, at least two outlets and at least two control pressure ports. The openings are distributed along or parallel to the leading edge in a side-by-side relationship and extend through the surface. The control pressure varying device is connected to the at least two control pressure ports in a fluidic manner, wherein the control pressure varying device is adapted to bring about the flow of the fluid at least majoritarily into a respective one of the outlets. Each of the outlets is connected to one individual opening of the plurality of openings.

Abstract: Structural component including at least one covering shell and a carrier structure, the covering shell designed in the form of a sandwich and formed by an inner skin section, an outer skin section and a shear-load absorbing core layer disposed between the two sections and connecting the inner and the outer skin sections to one another in a planar manner. The carrier structure is formed by at least one panel-shaped connecting part extending between and transversely to the inner and outer skin sections and connected along a reference longitudinal direction to the covering shell. The connecting part is located outside the carrier structure and fastened to the inner skin section resting thereon in a planar manner, wherein at least one profiled support extending along the reference longitudinal direction is provided in the covering shell in order to form a reinforcing section in the connecting region of the panel-shaped connecting part.

Abstract: The present invention relates to a fuselage of an aircraft or spacecraft, with at least one shell element and a structural element. An interspace to which air can be admitted by an air stream is provided between the at least one shell element and the structural element. The fuselage is distinguished by the fact that, to form the air-admitting air stream as an outgoing/incoming air stream of a pressurized interior space of the fuselage, the interspace is connected to a corresponding outgoing/incoming air connection of the interior space. The invention also relates to a corresponding aircraft or spacecraft and to a method of actively insulating such a fuselage.

Abstract: The present invention provides a method and an apparatus for detecting a communication channel in whose frequency band radio signals are transmitted by different radio signal sources inside a cabin. In this case a wide band antenna receives the radio signals transmitted inside the cabin. Different demodulators are provided, each of which demodulate the radio signals received by the wide band antenna within an associated frequency range of the demodulator. A configuration logic establishes whether, in a frequency band within a demodulated frequency range, radio signals are being transmitted simultaneously by different radio signal sources. In the case of impermissible signal transmissions of a radio signal source, e.g.

Abstract: An arrangement for monitoring the functionality of a structural adhesive layer to be fabricated between a first surface of a stiffening element and another component. A sensor block is bonded to a second surface of the stiffening component opposite to the first surface. The area of the structural adhesive layer incorporates a plurality of air openings and vacuum openings that vertically extend through the stiffening component and structural adhesive layer and the sensor block. The air openings are interconnected among each other by at least one air channel, and the vacuum openings by at least one vacuum channel. At least one of the channels is connected to an evaluator unit to detect a failure of the structural adhesive layer.

Abstract: A device for cutting to size and handling a substantially planar blank from a planar CFRP semi-finished product positioned on a cutting table by a cutting means, it being possible for the separated blank to be drawn up by suction and at least raised by a vacuum effector, characterized in that at least one blank electrode can be brought into contact with the blank and at least one peripheral electrode can be brought into contact with a peripheral portion separated from the CFRP semi-finished product and the at least two electrodes are connected to a voltage source and to a measuring means, the measuring means being able to detect a complete separation of the blank from the CFRP semi-finished product.

Abstract: A noise reduction unit for inserting in a vacuum suction drain is adapted to be flown through by a material to be conveyed through the vacuum suction drain and comprises an inlet section with a first diameter, a middle section with a second diameter and an outlet section with a third diameter. The middle section is adapted to affect a flow velocity reduction of the material to be conveyed such that the noise level arising during the conveying process is being reduced.

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.

Abstract: A gutter profile for draining liquids on an aircraft, comprising a connecting section for connecting the gutter profile to an outer skin of the aircraft and comprising a drain section for forming a drain cross-section of the gutter profile. The drain section is pre-tensioned into a ground position which opens the drain cross-section and has a flow guiding device for transferring the drain section into a flight position which closes the drain cross-section. An aircraft having such a gutter profile is also disclosed.

Abstract: A method for the manufacture of a fiber composite component with at least one opening, which is edged by an integral collar, a device for the execution of a method of this type with a mold core, which has at least one convexity for the formation of a component section in the form of a bulge, also a fiber composite component with a multiplicity of openings, each of which is edged by an integral collar.

Abstract: A door for a storage compartment of an aircraft includes a door leaf and a profiled strip connected to an edge of the door leaf. The profiled strip includes openings that provide a path for gas exchange such that smoke from the storage compartment is detectable outside of the storage compartment by passing the profiled strip.

Abstract: Disclosed is a method for the manufacture of an aircraft fuselage with at least two fuselage barrels wherein connecting segments are firstly prepared for the formation of a transverse joint region for a later transverse joint, and the fuselage barrels are then constructed around the connecting segments; also disclosed is an aircraft fuselage with ring-type connecting segments for the formation of such a transverse joint.

Abstract: A movable joining device for connecting structural components of an aircraft, with joining means moveably arranged on a guiding device situated on the outside of the structural components so as to fixedly connect joining edges of the structural components positioned adjacent to each other, wherein the joining means includes a welding unit that can move on the rail-like guiding device, and is equipped with a special so-called bobbin tool as a tool for friction stir welding.

Abstract: A data communications network for an aircraft includes a first branch for establishing a wireless data connection to a first group of end devices, a primary control unit connected to the first branch, and a backup control unit connected to the first branch. The primary control unit is configured for data transmission to and from the first group of end devices via the first branch. The backup control unit is configured for detecting an operating state of the primary control unit and for taking over data transmission to and from the first group of end devices via the first branch from the primary control unit in case of a failure of the primary control unit.

Abstract: A control device for activating an oxygen system of a transport mechanism, in particular an aircraft, a control system having such a control device, an associated method for activating an oxygen system of a transport mechanism, in particular an aircraft, and a computer program for carrying out the method. Furthermore, a network is provided for a transport mechanism, in particular for an aircraft. The control device for activating the oxygen system comprises a first activation unit which is configured to activate at least a part of the oxygen system by wireless transmission of a first activation signal.