Abstract: An ejection device for a flight data recorder includes an ejection spindle, which can be detachably connected to the flight data recorder by means of a bayonet coupling. The bayonet coupling can be released by means of force application by the ejection spindle, a disengaging device, which has a compression-resistant housing and into which the ejection spindle can be screwed, and a gas pressure generator, a valve, which is located within the disengaging device and which permits a flow connection between the outlet of the gas pressure generator and the ejection spindle when the ejection spindle is screwed in and which disables the flow connection between the outlet of the gas pressure generator and the ejection spindle when the ejection spindle is unscrewed.

Abstract: A component includes at least first and second plastics component parts which are interconnected in a connection zone. A reinforcing element includes at least one wire which bridges the connection zone. The first and second plastics component parts are welded together and/or are fused together in the connection zone. The plastics component parts may be bonded to one another.

Abstract: A device for consolidating a thermoplastic preform, in particular a carbon fiber thermoplastic preform includes a heating element, e.g., an LED array, for heating the preform and a consolidation element, e.g., a consolidation roller, for exposing the preform to pressure and for cooling the preform. In order to consolidate the preform, the heating element and consolidation element are arranged and movable relative to each other in such a way that the preform can be exposed to pressure and cooled by the consolidation element after heated by means of the heating element.

Abstract: A welding method for producing an integral bond of fibre-reinforced plastics parts includes a welding head penetrating one of the plastics parts. The method includes reinforcing at least a first plastics part by a plurality of directional fibres. The re-inforcing fibres reorient themselves within the connection region without severing or breaking.

Abstract: A device for machining workpieces a machining tool, a first workpiece-guiding element and a second workpiece-guiding element. The first workpiece-guiding element and the second workpiece-guiding element are designed to guide a workpiece, in a defined way, relative to the machining tool. The machining tool has an axis of rotation and a co-axial opening. The machining tool rotates about the axis of rotation for machining the workpiece. The first workpiece-guiding element is arranged in the opening of the machining tool co-axially to the axis of rotation.

Abstract: A reversible decoupling device is connected to an electromechanical actuator. The reversible decoupling device has an energy storage element configured to store the energy required for a decoupling in the decoupling device. The decoupling device can be re-coupled again after a completed test run so that the decoupling functionality can be easily tested.

Abstract: An automatic learning method for the automatic learning of the forms of appearance of objects in images in the form of object features from training images for using the learned object features in an image processing system comprises determining a feature contribution by a training image to object features by weighted summation of training image features by means of linear filter operations, applied to the feature image, by using a weight image obtained at least from an annotation image and a classification image. This allows faster learning processes and also the learning of a greater variance of forms of appearance of objects and backgrounds, which increases the robustness of the system in its application to untrained images.

Abstract: A pneumatic decoupling device for an electromechanical actuator, in particular, for flight applications includes a pressure accumulator housing for storing a compressed gas, which can be released to a decoupling mechanism of an electromechanical actuator for separating the drive components, so that in the event of a decoupling the electromechanical actuator runs totally freely.

Abstract: A helical actuator includes a plurality of piezo elements for controlling a rotor blade of an aircraft. In this case, the actuator is designed to be arranged so as to be wound around a rotor blade neck and to be fastened to a rotor mast and a rotor blade in each case. Applying a control voltage to the piezo elements causes the actuator to expand, which, in turn, causes the rotor blade to rotate.

Abstract: A satellite communication system includes at least one base station, at least one satellite that can be brought into communication connection with the base station for data transmission, and a plurality of receivers adapted to receive signals transmitted from the satellite. The communication system is designed to transmit data in at least one uplink data stream from the base station to the satellite with a first data transmission rate and to transmit data in at least one downlink data stream from the satellite to the receivers with a second data transmission rate. The first data transmission rate is lower than the second data transmission rate and the satellite is provided with a data storage adapted to store the data transmitted from the base station to the satellite and to supply the data provided for the transmission to the receivers.

Abstract: A flow aid for an infusion structure for infiltrating fibre material with resin to produce a fibre composite component includes a resin-impermeable upper layer and a lower layer which are joined together in a peripheral region of the flow aid and provide a flow space between the two layers. The lower layer provides an outlet for discharging resin out of the flow aid into an interior of the infusion structure. The flow aid includes an inlet for feeding the resin into the flow space, thereby facilitating uniform distribution of the resin over all of the fibre material.

Abstract: A transition piece, which can be mounted in a recess, and which can form a continuous surface from a structural component of an airplane to a control surface, which is connected to the structural component in a pivotable manner is described. The transition piece can be mounted between an edge of the structural component and a lateral edge of the control surface such that the transition piece is fastened in a pivotable manner both to the edge of the structural component and to the lateral edge of the control surface. According to an example, the transition piece has a planar design and can be deformed within said plane, that is, the transition piece can be stretched or compressed within this plane.

Abstract: A device for reducing structural vibrations of airfoils in an aircraft comprises, in the region of the airfoil tips, at least one force generator acting substantially in the direction of movement of the vibrations. This arrangement has the advantage that such a force generator is considerably less susceptible to wear than conventional aerodynamic flaps and therefore effective vibration damping is possible with a reduced outlay on maintenance and greater efficiency.

Abstract: A device for producing a three dimensional object from a powdery material by solidifying the powdery material through the application of energy includes a working surface, an application device for applying the powdery material onto the working surface, and a solidifying device for solidifying the powdery material applied onto the working surface. The application device can apply predefined, locally different amounts of powdery material and includes a transfer device, which can be magnetized and/or electrostatically charged and discharged, as well as a magnetizing and/or charging device.

Abstract: A sound absorber comprising a base body and a tongue (24). The base body has a bottom plate, a wall enclosing the bottom plate and an opening enabling the entry of air into the base body. The tongue has a fixed end, a free end and a central portion disposed between the fixed and the free end. The free end of the tongue is spaced from the wall and the bottom plate, and the central portion of the tongue is disposed to extend at least partially straight along a width direction. Furthermore, a sound absorber assembly can include at least two sound absorbers, and an engine, in particular, for an aircraft, comprising such a sound absorber and/or such a sound absorber assembly.

Abstract: An emergency power supply system for providing hydraulic power and electric power in an aircraft includes a fuel cell having an electric outlet for providing electric power, a conversion unit couplable with at least one of an AC bus and a DC bus and the electric outlet, and at least one hydraulic pump having a reconfigurable electric motor and a motor control unit and being couplable with a hydraulic system for providing hydraulic power. The conversion unit is adapted for converting a supply voltage of the electrical outlet to at least one of an AC voltage matching a predetermined voltage at the AC bus and a DC voltage matching a predetermined voltage at the DC bus. The reconfigurable electric motor is couplable with the fuel cell and the AC bus and is adapted for being operated by the supply of electric power either from the fuel cell or the AC bus.

Abstract: A method for image processing involves collecting image data of a scene as electromagnetic radiation and processing the image data to improve the signal-to-noise ratio of the image data. The image processing involves dividing a raw image that contains the image data into lines and columns, to create a raster image, superimposing a central raster filter element of a raster filter having an odd number of lines and an odd number of columns onto a raster image element, determining the brightness values of each of the raster image elements covered by the raster filter, wherein except for the central raster filter element, every other raster filter element has an individual light-reducing property, and adding up the brightness values to produce a total brightness value, and assigning this total brightness value to the raster image element covered by the central raster filter element.

Abstract: A solid propellant gas generator releases a flowing mixture from a solid propellant, separated from a surrounding area, into the surrounding area. The solid propellant gas generator includes a cooling system for cooling the flowing mixture. The cooling system has at least one feed device for feeding a gas from the surrounding area to the flowing mixture in order to mix the flowing mixture prior to entering into the surrounding area with the gas from the surrounding area.

Abstract: A data transmission between a device and a first and a second optical maintenance port involves a transmission reflector in the form of a solid-state bound data line having a gap and a Y coupler. This allows recording of the communication between the device to be read out and the first optical maintenance port in real time by means of the second optical port. Likewise, communication by means of electromagnetic energy is possible between the first and the second optical maintenance ports.

Abstract: An air generation unit for an aircraft, an air generation arrangement, an aircraft and a method for operating an air generation unit in an aircraft are described. The air generation unit for an aircraft includes an air supply means and a control unit. The air supply means is configured to supply air to an air conditioning system of an aircraft's cabin. The air supply means is further or alternatively configured to supply air to a flow control system of an aircraft. The control unit is configured to provide, during cruise conditions of the aircraft, a larger amount of the air to the air conditioning system than to the flow control system. The control unit is further configured to provide, during take-off and/or landing conditions of the aircraft, a larger amount of the air to the flow control system than to the air conditioning system.