Abstract: The invention relates to a bus system for transmitting data between data processing units in a network, by means of a bus that consists of two signal lines. The signals at said bus are analog signals which lie within a plurality of non-overlapping frequency bands assigned to the individual data processing units, and these data processing units use a digital communication protocol to communicate with a signal processor unit that comprises a polyphase filter bank, a D/A Converter and a bus-coupling unit being connected downstream of said bank in order to couple the data signal into the bus in a galvanically-isolated manner. The proposed bus system has a simple design with regard to cabling, allows the use of a Standard communication protocol such as Ethernet for the data processing units, and additionally allows data to be transmitted between all network subscribers simultaneously and without restriction.

Abstract: An elongated hollow optical waveguide (1) is described, as can be used in particular in a photobioreactor for supplying phototrophic organisms both with light and with nutrients. The optical waveguide (1) has a casing (3) made from transparent plastic, which surrounds a hollow core (5). The hollow core has a diameter of at least 1 mm, preferably at least 3 mm or at least 1 cm. A plurality of openings (7) with a diameter of at least 0.5 mm, preferably at least 1 mm, is constructed in the casing (3). Light can propagate through the transparent casing and preferably exit laterally (19) along the entire optical waveguide (1). Nutrients (15) can be conveyed through the hollow core (5) into the interior of the photobioreactor. Conversely, portions of the solution, to which organisms have been added, can also be sucked through the hollow core (5), for example in order to analyze the same.

Abstract: An automatic take-off and landing control device for an aircraft is provided. The control device comprises at least two of at least one local tracking device adapted for receiving at least one local signal from at least one local ground station and for determining a position of the aircraft based on the local signals, at least one GNSS tracking device adapted for receiving a GNSS signal and for determining a position of the aircraft based on the GNSS signal; and at least one camera device adapted for observing an environment of the aircraft and for determining a position of the aircraft based on the camera signal.

Abstract: A display assembly for displaying a parameter of an aircraft, comprising a parameter device and a non-transparent display device. The parameter device for gathering a parameter of the aircraft and/or of an equipment of the aircraft includes a sending unit for sending the parameter. The non-transparent display device is detachable, is configured to display the parameter, and comprises a receiving unit for receiving the parameter. The sending unit transmits the parameter directly to the receiving unit.

Abstract: A transmitter unit for wireless transmission of power by way of a bundled laser beam is described. The transmitter unit has a laser fiber bundle having a plurality of laser fibers, wherein each laser fiber is designed to emit a laser beam; positioning optics for adjusting an emission direction of the bundled laser beam; a field lens and a primary lens. The plurality of laser fibers is designed to emit a laser beam from each, passing through the positioning optics, the collimator lens and the primary lens, in this order, so that the laser beam emitted by the transmitter unit is emitted in bundled form. A particularly efficient device with an unlimited flight time and a large radius of use is achieved by the hybrid drive with solar power and laser power from the ground and temporary storage of the power in batteries.

Abstract: A method for monitoring the integrity of a freight container along a transport route, the container having a sensor monitoring the container integrity, wherein the sensing of an event violating the container integrity is followed by event data representing the integrity violation being transmitted to an analysis center, wherein the event data is rated using predetermined criteria in respect of either a sanctioned or an unsanctioned integrity violation, and wherein opening or closing of the container is rated as a sanctioned integrity violation if an electronic authorization code representing the sanction is sent to the analysis center for the event data representing this integrity violation. Different types of opening and/or closing operations are distinguished by using authorization codes from different function groups, and the analysis center uses the type of function code to determine what type of opening operation and/or closing operation has taken, or is meant to take, place.

Abstract: An electrical power supply system for an aircraft includes a plurality of generators, each being couplable to and rotatable by an aircraft engine. and a plurality of electrical conversion units, each having a plurality of inputs and at least one output. Each generator includes at least four AC phases. The inputs of each individual electrical conversion unit are connected to a plurality of phases of at least two of the plurality of generators. The electrical conversion units each includes a rectification and conversion device for providing an output voltage having a predeterminable frequency and voltage level at the output.

Abstract: Specified is a lightning protection layer for an aircraft. The lightning protection layer has a first stratum and a second stratum. The second stratum is coupled to the first stratum along a connecting surface. The first stratum has a metal foil and the second stratum has carbon allotropes. It is thus made possible that damage to a structure of the aircraft by lightning strike is reduced.

Abstract: A welding tool for joining at least two workpieces at a joining region by friction stir welding includes a tool pin arranged along one axis of the welding tool, for applying frictional heat to the workpieces. The welding tool also includes a shoulder surrounding the tool pin, for separating the joining region from the surrounding area. The shoulder is moveable essentially parallel to the axis of the welding tool.

Abstract: In order to provide a simplified inspection of an aircraft for the pilot, an aircraft inspection system is provided which includes at least one movable inspection unit, a position detection arrangement, and at least one data transfer interface. The at least one moveable inspection unit is moveable relative to an aircraft to be inspected. The at least one movable inspection unit includes at least one sensor for detecting a characteristic value, for verifying a characteristic and/or for determining a defect of an aircraft. The movable inspection unit is configured to generate monitoring data. When a defect or a characteristic value is detected, the position detection arrangement detects position data of the movable inspection unit in relation to the aircraft to be inspected, and assigns the position data to the monitoring data. The data transfer interface provides the position data with the assigned monitoring data as inspection data.

Abstract: A sensor for detecting and localizing laser beam sources, includes a beam-sensitive detector which is arranged in the image field of an imaging optic, an electric image processing device which is connected to the detector, and an optical diffraction element which is arranged in the beam path. The diffraction properties of the optical diffraction element are such that incident laser light on different wavelength bands produce diffraction patterns with different shapes, and the electronic image processing device is designed such that it can detect and evaluate the different forms of the diffraction pattern.

Abstract: A laying head for a fibre placement device, in particular for fibre placement according to the AFP method, includes a placing roller which is permeable to laser light, at least in part, a laser light feed unit which is arranged in an inner space of the placing roller and a sensor which is designed and arranged to receive laser light reflected from a component on which the placing roller places a fibre band.

Abstract: An aircraft fuselage structure is disclosed herein and includes an outer skin, with circumferential ribs, such that a recess is provided for receiving a wing torsion box in the outer skin, and the ribs are interrupted in the region of the recess. An object of the disclosure includes providing an aircraft fuselage structure designed such that the wing torsion box is able to extend at least partially through the upper region of the fuselage, without the stability of the fuselage being significantly reduced. This can include providing first longitudinal members which are adjacent to the recess and which extend along the longitudinal edges beyond the entire length thereof. End regions of the first longitudinal members are connected to ribs which extend circumferentially at intervals from the transverse edges of the recess along the outer skin over the vertical longitudinal central plane.

Abstract: A fiber application tool for a fiber application process designed, in particular, as an AFP, has a fiber contact surface area, which has a fiber contact surface for applying and/or pressing the fibers onto a work surface. The tool further includes an activation device for activating an adhesive, matrix, resin, or binder material provided at the fibers by means of an activation radiation so that the fibers are tacked onto the work surface. The fiber contact surface area for the activation radiation may be transparent and that the activation device may be designed so to guide and/or deliver the activation radiation through the transparent fiber contact surface area to the fibers to be pressed by the fiber contact surface.

Abstract: An electrical drive system for an aircraft includes: at least one first and one second electrical direct voltage sources for supplying a direct voltage, and a first and a second electrical machine modules configured to convert electrical alternating voltage into mechanical movement and vice versa. The first and second modules are connected to a first and a second power inverters, respectively. The first and second inverters are connected in series and the first and the second direct voltage sources are connected in series to generate an overall direct voltage to which the inverters are connected. The power inverters each has one voltage measuring device for measuring the power inverter direct voltage present at the respective inverter and a power inverter control device for controlling the operation of the inverters in accordance with the power inverter direct voltage.

Abstract: A system for navigating an aircraft includes a first aircraft with a first communication unit and a second aircraft with a second communication unit. The first aircraft is adapted for determining coordinates of a position of a waypoint. The first communication unit is adapted to transmit the coordinates of the position of the waypoint to the second communication unit. The second aircraft is adapted to navigate to the position of the waypoint. Several waypoints can be provided in this manner such that a flight trajectory is established along which the second aircraft may follow the first aircraft. In addition, the second aircraft may be adapted to follow the first aircraft based on a received identification signal. In certain embodiments, the system can be used such that the second aircraft can follow the first aircraft in case of a failure of systems of the second aircraft.

Abstract: A wireless local messaging system includes a transmitter transmitting a local message to a navigation receiver configured to receive and process navigation messages from satellites of a global navigation satellite system on a given carrier frequency, each of the satellites transmitting the navigation messages with a satellite-individual PRN code. The transmitter transmits the local message in a local message signal on the given carrier frequency with a local PRN code that is not used by a satellite of the global navigation satellite system, and the receiver receives the local PRN code and processes the local message signal.

Abstract: A control circuit system for influencing at least one process variable includes a plurality of sensors which each detect at least one measurement variable, a plurality of actuators which each manipulate at least one control variable, wherein the sensors and actuators are each assigned electronic circuits for control, and at least one control mechanism which controls and/or coordinates each of the plurality of sensors and actuators by means of at least one control unit. The control circuit system is sub-divided into a plurality of sub-units which are each provided with at least one sensor, at least one actuator and at least one control unit, and for a plurality of the sub-units, in particular all of the sub-units, each to be set up to operate a control circuit system.

Abstract: An aluminum alloy, a method for producing a lightweight metal workpiece, a lightweight metal workpiece including the aluminum alloy, as well as the use of the aluminum alloy for producing high-strength lightweight metal workpieces by additive layer manufacturing (ALM) and/or spraying methods for load-optimized components, in particular in automobile manufacturing or in aviation and aerospace applications, plant engineering, medical technology, or as coating material for structural components are described herein.

Abstract: An automatic landing system contains a control device for providing positional data for controlling an aircraft, a first position or range measuring device for detecting first positional data of the aircraft, a second position or range measuring device for detecting second positional data of the aircraft, and a sensor device for detecting sensor data from which a direction in which a landmark is located and/or a distance of the landmark to the aircraft can be determined. The control device may be configured to generate, based on the first positional data, a first hypothesis for the direction and distance of the landmark and, based on the second positional data, a second hypothesis for the direction and distance of the landmark. Moreover, the control device may be configure to confirm or discard the first hypothesis and the second hypothesis, respectively, using the sensor data detected by the sensor device.