Abstract: A cabin interior arrangement 1 for an aircraft is proposed that comprises a first cabin interior object and a second cabin interior object 3a, b, comprising a power transmitting device 5 for transmitting power from an aircraft electrical system 7, wherein the power transmitting device 5 is arranged on the first cabin interior object 3a, comprising a power receiving device 6 for receiving the power from the power transmitting device 5, wherein the power receiving device 6 is arranged on the second cabin interior object 3b, wherein the power transmitting device 5 and the power receiving device 6 are embodied as a power transfer arrangement 2 for supplying the power to a mobile terminal 4, wherein the power transmitting device 5 and the power receiving device 6 are designed to transfer power over a distance of several centimetres, wherein the power transmitting device 5 and the power receiving device 6 are deigned to set up a wireless and/or cordless supply connection segment 10 between the power transmitting de

Abstract: A cabin interior arrangement 1 for an aircraft is proposed that comprises a first cabin interior object and a second cabin interior object 3a, b, comprising a power transmitting device 5 for transmitting power from an aircraft electrical system 7, wherein the power transmitting device 5 is arranged on the first cabin interior object 3a, comprising a power receiving device 6 for receiving the power from the power transmitting device 5, wherein the power receiving device 6 is arranged on the second cabin interior object 3b, wherein the power transmitting device 5 and the power receiving device 6 are embodied as a power transfer arrangement 2 for supplying the power to a mobile terminal 4, wherein the power transmitting device 5 and the power receiving device 6 are designed to transfer power over a distance of several centimetres, wherein the power transmitting device 5 and the power receiving device 6 are deigned to set up a wireless and/or cordless supply connection segment 10 between the power transmitting de

Abstract: A transmission arrangement for an aircraft for transmitting data within the aircraft, wherein the aircraft includes an electrical wiring system of coherent lines for providing electric power for loads in the aircraft, has at least two PLC elements, connectable to a respective one of the lines, for transmitting the data between at least two of the PLC elements via the wiring system, wherein at least one of the PLC elements has at least one filter connection, wherein the filter connection has at least one PLC connection, connectable to a respective one of the lines, and a power connection, connectable to a respective one of the lines, wherein the PLC connection carries power and data and the power connection carries power and is free of data.

Abstract: A transmission arrangement for an aircraft for transmitting data within the aircraft, wherein the aircraft includes an electrical wiring system of coherent lines for providing electric power for loads in the aircraft, has at least two PLC elements, connectable to a respective one of the lines, for transmitting the data between at least two of the PLC elements via the wiring system, wherein at least one of the PLC elements has at least one filter connection, wherein the filter connection has at least one PLC connection, connectable to a respective one of the lines, and a power connection, connectable to a respective one of the lines, wherein the PLC connection carries power and data and the power connection carries power and is free of data.

Abstract: A wing flap sensor unit (2) having a position sensor (18) for detection of a rotation position of a shaft for operation of wing flaps and having a housing (4) which surrounds the position sensor (18), having an attachment component (20, 22) for attachment in an aircraft wing and having a connecting point (24) for an electrical connector of the position sensor (18). Hereby, the housing (4) is at least partially manufactured from titanium using a precision-casting method. The titanium precision-casting method makes it possible to achieve a particularly robust and lightweight housing.

Abstract: In order to relieve the power supply system of commercial aircraft of one absolutely essential load, specifically a galley with heating and cooling appliances, the appliances are provided with at least one autonomous power supply device which can be handled without any problems and is installed in a galley trolley (1) of standardized dimensions, preferably with a fuel cell (2) together with its fuel tanks (3, 4) and voltage converters (5) in order to be replaced at the same time by catering lifting loaders in the course of galley supply and disposal. Instead of or in addition thereto, an autonomous, mobile power supply unit such as this can also be installed in one of the standardized baggage or cargo containers for accommodation in the cargo bay of the aircraft, and then in particular also to feed electrical heating and cooling appliances in other containers.

Abstract: The invention relates to a multichannel controller module for integrated modular avionics, having at least two channels, wherein, in each of the channels, at least one first interface, which is intended for communication with a control computer, a processor, at least one second interface, which is intended for communication with a peripheral, and a first memory, which is provided with an operating system, are connected in order to interchange data with one another, wherein a second memory is provided for selective storage of at least one application program for communication with the peripheral, wherein a selection means is provided, by means of which the application program is selectively assigned a first or a second mode of operation, wherein the first mode of operation is a redundant duplex mode of operation, in which both channels are used to execute the application program, and the two channels are in this case connected to one another via a data interchange and fault monitoring means, and wherein the

Abstract: In order to relieve the power supply system of commercial aircraft of one absolutely essential load, specifically a galley with heating and cooling appliances, the appliances are provided with at least one autonomous power supply device which can be handled without any problems and is installed in a galley trolley (1) of standardized dimensions, preferably with a fuel cell (2) together with its fuel tanks (3, 4) and voltage converters (5) in order to be replaced at the same time by catering lifting loaders in the course of galley supply and disposal. Instead of or in addition thereto, an autonomous, mobile power supply unit such as this can also be installed in one of the standardized baggage or cargo containers for accommodation in the cargo bay of the aircraft, and then in particular also to feed electrical heating and cooling appliances in other containers.

Abstract: A wing flap sensor unit (2) having a position sensor (18) for detection of a rotation position of a shaft for operation of wing flaps and having a housing (4) which surrounds the position sensor (18), having an attachment component (20, 22) for attachment in an aircraft wing and having a connecting point (24) for an electrical connector of the position sensor (18). Hereby, the housing (4) is at least partially manufactured from titanium using a precision-casting method. The titanium precision-casting method makes it possible to achieve a particularly robust and lightweight housing.

Abstract: An aircraft cabin equipment control system has control hardware that includes a data processing apparatus and a plurality of interfaces for connection to items of cabin equipment of an aircraft, as well as equipment programs for controlling the cabin equipment. To simplify manufacture of the aircraft cabin equipment control system and to achieve more flexible power distribution within the aircraft, there is provided an aircraft cabin equipment control system which has a configuration manager that records and stores equipment data which characterize both the number of the items of cabin equipment to be controlled and also the type of the items of cabin equipment themselves, and on the basis of the equipment data in conjunction with data characterizing the aircraft to set up configurations which form the basis for control of the cabin equipment.

Abstract: An aircraft cabin equipment control system has control hardware that includes a data processing apparatus and a plurality of interfaces for connection to items of cabin equipment of an aircraft, as well as equipment programs for controlling the cabin equipment. To simplify manufacture of the aircraft cabin equipment control system and to achieve more flexible power distribution within the aircraft, there is provided an aircraft cabin equipment control system which has a configuration manager that records and stores equipment data which characterize both the number of the items of cabin equipment to be controlled and also the type of the items of cabin equipment themselves, and on the basis of the equipment data in conjunction with data characterizing the aircraft to set up configurations which form the basis for control of the cabin equipment.

Abstract: The invention relates to a method for reading programmes into a device which processes data using a processor, according to a programme stored in a programme memory. A programming device sends programme data to the programme memory of the device to be programmed in the form of a data stream. The inventive method comprises the following steps: a) activating a light transmitter in accordance with the programme data, so that said light transmitter generates digital light signals in accordance with the programme data; b) receiving the light signals with a light receiver which is permanently installed on the device to be programmed and c) applying the signals of the light receiver of the device to be programmed to the programme memory of the same. The invention also relates to a device for carrying out this method.