Abstract: A surveillance device and method provide access to a surveillance system for keeping a cabin of an aircraft under surveillance. A computer program may be used to execute the method for accessing the surveillance system. The surveillance device includes an authentication unit for examining an access-authorisation request for access to the surveillance system, and a control unit for selecting, on the basis of the access-authorisation request, a display unit from a plurality of display units provided in the aircraft, and for relaying a video-image signal corresponding to a captured video image of a subarea of the cabin of the aircraft to the selected display unit for the purpose of displaying the video image.

Abstract: An electrical system for an aircraft is provided. The system comprises an inverter for transforming a first alternating current from an on-board network having a variable frequency into a second alternating current, and at least a first electrical load and at least a second electrical load, which are configured to be operated simultaneously by the second alternating current.

Abstract: A cargo loading system for a cargo compartment of a means of transport, for example a cargo aircraft or a passenger aircraft, is provided. The system includes at least one power drive unit for transporting cargo of the means of transport. The power drive unit and a control module are coupled to a BUS system. The control module generates control signals for the power drive unit and maintenance data of the power drive unit for the control and maintenance of the power drive unit. The BUS system transmits the control signals and maintenance data of the power drive unit between the control module and the power drive unit. In this manner an existing hardware platform of the means of transport can be used, and weight and cabling as well as the number of control boxes of the means of transport can be reduced.

Abstract: A freight evaluation system for providing freight information with respect to an item of freight of an aircraft includes a freight evaluation unit for collecting and analyzing data of a freight loading system and a recognition system and for determining the current position of the item of freight therefrom.

Abstract: An aircraft interior lining component includes a composite material, wherein the composite material includes a matrix, first reinforcing fibres embedded in the matrix and second reinforcing fibres embedded in the matrix. The strength of an interface between a surface of the first reinforcing fibres and the matrix surrounding the surface of the first reinforcing fibres is greater than the strength of an interface between a surface of the second reinforcing fibres and the matrix surrounding the surface of the second reinforcing fibres.

Abstract: A device for acquiring mechanical loads on mechanically loaded bodies is provided. The device exhibits a resonance-capable micro-bridge structure, an alternating voltage source with a variable frequency, an impedance measuring device for acquiring the impedance of the micro-bridge structure and an electronic unit for receiving determined impedance values and changing the frequency of the alternating voltage source. By exciting the micro-bridge structure and measuring its impedance, a conclusion can be drawn as to the expansion-dependent resonance frequency, which in return makes it possible to determine the expansion, and hence the mechanical load. Such a device is sufficiently accurate, and largely independent of outside influences.

Abstract: A support structure for an air supply arrangement for air conditioning aircraft passenger cabins. The air supply arrangement comprises at least one centrally controlled cabin ventilation system and an individually adjustable cabin ventilation system. The support structure includes: a first section for receiving and/or integrating cabin ventilation system components, a second section for receiving and/or integrating passenger emergency oxygen supply components and a third section comprising a plurality of receiving devices. Each receiving device receives and releasably secures an active module for individually adjustable cabin ventilation. The third section has at least the number of receiving devices required for at least one receiving device to be associated with each seating row for a maximum number of seating rows arrangeable in the cabin A supply system includes at least one such support structure and at least one of the active modules. A method is provided for configuring a corresponding supply system.

Abstract: A fiber composite component assembly includes at least two plate-shaped composite structures which in each case are made from synthetic-resin embedded fibers and are integrally interconnected by way of an adhesive layer arranged in between, and additional mechanical reinforcement means, wherein the fiber composite components include several partial regions that do not contain synthetic resin, which partial regions can be brought to flush conformity with each other and which are arranged so as to be spaced apart from each other, through which partial regions the mechanical reinforcement means that can subsequently be bonded-in with synthetic resin have been passed.

Abstract: An interface device for a cabin monument, in particular for assembly in an aircraft or spacecraft, including a routing device, a first plurality of interface connection sockets, which are connected to the routing device via a first plurality of connection lines and to which a vehicle interface of the aircraft or spacecraft can be connected. A second plurality of interface connection sockets are provided which are connected to the routing device via a second plurality of connection lines and to which a cabin monument can be connected. The routing device is constructed so as to selectively electrically connect interface connection sockets of the first plurality of interface connection sockets to interface connection sockets of the second plurality of interface connection sockets.

Abstract: An attachment arrangement for attaching a component to a base item, with at least one fixing device for fixing one section of the component on a section of the base item. At least one connecting device with a connecting element and at least one receiving element are provided. One of the elements is arranged on a component section and the other of the elements is arranged on a base item section. The two elements detachably engage with one another in a form fit. Loads can be transferred at least in the direction of a first axis, and a relative movement is possible between the elements in the direction of a second axis, different from the first axis. A connecting device is disclosed for such an attachment arrangement. A method is disclosed for purposes of attaching a component to a base item by means of such an attachment arrangement.

Abstract: A method for controlling the operation of an auxiliary power unit supplying an aircraft air conditioning system with compressed process air includes determining a heating or cooling requirement of an aircraft region to be air-conditioned, determining a desired value of at least one process air flow parameter in dependence on the determined heating or cooling requirement of the aircraft region to be air-conditioned, controlling the operation of the auxiliary power unit in dependence on the determined process air flow parameter desired value, acquiring an actual value of the at least one process air flow parameter, comparing the process air flow parameter actual value with the process air flow parameter desired value and controlling the operation of the auxiliary power unit in dependence on the result of the comparison of the process air flow parameter actual value with the process air flow parameter desired value.

Abstract: The present invention relates to the use of a process for producing an aluminium material which can be exposed to high temperatures and is alloyed with scandium. In this process, a precursor material made of an alloy comprising the metals aluminium and scandium is introduced into a vacuum chamber, the precursor material is subjected to vacuum degassing and the precursor material is treated with nitrogen gas. This is followed by final vacuum degassing of the precursor material.

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: An electrical consumer of an aircraft comprises an electric motor and an inverter for producing an alternating voltage for the electric motor. A method for controlling the electrical consumer comprises determining a rotational frequency for the electric motor. The method also includes establishing whether the rotational frequency leads to oscillations in the input current of the inverter which are below a predefined threshold, the oscillations being produced by the inverter when producing a supply voltage for the electric motor, and changing the rotational frequency if it has been established that the rotational frequency leads to oscillations below the predefined threshold.

Abstract: A cabin attendant seat (14) comprises a backrest element (20) and a seat element (22) which is secured to the backrest element (20). The backrest element (20) is rotatable about a rotation axis (24a, 24b) in order to move the cabin attendant seat (14) between a rest position and an operating position. A fastening device (18) for fastening the cabin attendant seat (14) to a side wall (16) of an aircraft monument (12) is constructed and sized in such a manner that it is capable of directing away a predetermined maximum force which can be introduced into the cabin attendant seat (14) during operation of the cabin attendant seat (14) via the side wall (16) of the aircraft monument (12).

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: A cooling system of a vehicle with a fuel cell includes an absorbent circuit with an absorber tank, a regenerator tank, an absorbent pump and a first pressure reduction means and a coolant circuit with a condenser connected to a steam outlet of the regenerator tank, a second pressure reduction means and an evaporator arranged between a steam inlet of the absorber tank and the second pressure reduction means. The regenerator tank is designed to desorb the coolant in solution in the absorbent by absorbing a first quantity of heat and to introduce it in a vaporous state into the condenser. The evaporator is designed to evaporate the coolant while absorbing a second quantity of heat and to introduce it in the vaporous state into the absorber tank. At least one of the first and of the second quantity of heat could be provided by the fuel cell.

Abstract: A mixing device for an aircraft air conditioning system includes a plurality of cold-air supply lines, which are devised to supply cold air to the mixing device. A plurality of warm-air supply lines is further provided, which are devised to supply warm air to the mixing device. A first premixing chamber is connected to the cold-air supply lines and devised to mix the cold air that is fed through the cold-air supply lines into the first premixing chamber. A second premixing chamber is connected to the warm-air supply lines and devised to mix the warm air that is fed through the warm-air supply lines into the second premixing chamber. Finally, a main mixing chamber is connected to the first and the second premixing chambers and devised to mix the cold air premixed in the first premixing chamber with the warm air premixed in the second premixing chamber.

Abstract: A mounting device for mounting a cable or a line on a structural component of an aircraft or spacecraft. The mounting device comprises at least two parts, one of these parts being configured as an attachment part and being provided to be attached to the structural component. The other part is configured as a receiving part and is provided to receive a portion of the cable or of the line. Both parts can be coupled together by means of at least a first ball-and-socket joint. This coupling is configured such that the two parts can be brought into a plurality of spatial positions relative to one another. Also provided is an aircraft or spacecraft, in particular an aircraft, which has a structural component and a cable or a line which is mounted on the structural component by a mounting device of this type.

Abstract: A gas turbine engine, especially a turbojet or turbofan for an aircraft, includes a combustion section and an exhaust section produces an exhaust gas. The emission products can be reduced by using a gas treatment device with a reactor and an injection device. The reactor produces a nitrogeneous substance such as ammonia. This reducing agent is injected in the gas phase in the exhaust section of the gas turbine engine. By selective non catalytic reaction the Nitrogen oxides of the exhaust gas can be reduced. Furthermore the injection device is arranged such that the temperature window of this reduction process is ranging from 850° C. to 1100° C. The reactor for producing gaseous ammonia can either be a thermal reactor or a high pressure plasma device.