Abstract: A multiple hold-down and release device for spacecraft includes a central structure including a central section with a cylindrical inner hole, an inner axial shaft insertable into the inner hole. A release bolt aligns with the inner axial shaft. A main bushing is partially arranged inside the inner hole and axially guided by guiding bushings on the main bushing and the inner hole. The main bushing includes a protrusion and internal retainer spring. Arms protruding from the central section are axially preloaded by a pusher opposite the central section. Connecting levers each connect to the end of the corresponding arm by the pusher. Hold-down assemblies on the periphery of the device each include a hold-down support and a fastener with conical contact surfaces, a torsion spring around a torsion spring shaft, and articulated with the corresponding hold-down support by the corresponding torsion spring shaft.

Abstract: A device for orienting a load about a main axis X and a secondary axis Y is disclosed having a first shaft, called transmission shaft, intended to support the load and configured to be rotated about the main axis and the secondary axis, a second shaft configured to be rotated about the main axis X, a third shaft configured to be rotated about a third axis of rotation, in the same direction as the main axis, a first connection component between the transmission shaft and the second shaft, configured to prevent relative movements between the transmission shaft and the second shaft in, on the one hand, a degree of rotational freedom about the main axis X and, on the other hand, three degrees of translational freedom.

Abstract: A system for extracting oxygen from powdered metal oxides, the system comprising a container comprising an electrolyte in the form of meltable or molten salt, at least one cathode, at least one anode, a power supply, and a conducting structure, wherein the cathode is shaped as a receptacle having a porous shell, which has an upper opening, the cathode being arranged in the electrolyte with the opening protruding over the electrolyte, wherein the conducting structure comprises a plurality of conducting elements and gaps between the conducting elements, wherein the power supply is connectable to the at least one cathode and the at least one anode to selectively apply an electric potential across the cathode and the anode, wherein the conducting structure is insertable into the cathode, such that the conducting elements reach into an inner space of the cathode, wherein the conducting structure is electrically connectable to the cathode, and wherein the system is adapted for reducing at least one respective metal

Abstract: A communication system with increased throughput for providing communication between transceivers via a wireless communication channel through multiple, N, single input, single output, SISO, links provided for a corresponding number, N, of data sequences, wherein each transceiver includes a transmitter having spreading units each configured to spread in an operation mode of the communication system a data sequence with an associated predefined unique spreading code sequence to generate a spread data sequence multiplexed to an antenna unit of the respective transceiver configured to transmit the spread data sequences via the wireless communication channel to antenna units of other transceivers of the communication system.

Abstract: A space station includes a housing that defines an interior space. An inner chamber is located in the interior space and defines an inner cavity that is sealable from the remainder of the interior space. At least one bulkhead is arranged in the interior space to partition the interior space into at least two compartments that are hermetically sealable from one another. One compartment can be accessed from another compartment via the inner cavity of the inner chamber. The inner cavity is sealable against each compartment. Openings in an outer surface of the housing enable crew members to leave a damaged compartment through the opening. Thus, alternative routes exist to leave a damaged compartment, i.e., either through the inner cavity or through the opening in the outer surface of the housing. When one compartment is damaged, the adjacent compartments are still operative because they are sealed from the damaged compartment.

Abstract: A display arrangement for presenting video information to a human operator in a vehicle senses vehicle movements and movements of a head mounted display unit. Based on vehicle movements and movements of the display unit, a virtual scenario with background video data and application video data are generated to a display arrangement. The background video data are modified so background video moves opposite to vehicle movements. The application video data are modified so application video moves according to vehicle movement. A perspective onto the application video can be modified based on relative movements of the display unit with respect to the vehicle. This may reduce conflicts between sensory impressions of the vestibular system and eyes of the operator because movements of the vehicle and movements of the display unit are considered when generating and modifying the background and application video data presented to the operator.

Abstract: A structural component for an aircraft, spacecraft or rocket has a ply of fiber reinforced polymer, a first carbon nanotube mat; and a metallic layer, wherein the carbon nanotube mat and the metallic layer are arranged on the ply of fiber reinforced polymer to form a hybrid lightning strike protection layer. A component for manufacturing such a structural component, a method for manufacturing a component of this type, a method for manufacturing a structural component and an aircraft or spacecraft with such a structural component are described.

Abstract: An anticorrosion coating and an article coated with an anticorrosion coating, especially for use in an aircraft, and a method of producing a coated article and a vehicle, especially an aircraft, including an anticorrosion coating or at least one such coated article. An anticorrosion coating includes an aluminum alloy having 0.03-0.5% by weight of tin. A coated article produced at least partly from a material and having at least partly been coated with the anticorrosion coating including an aluminum alloy having 0.03-0.5% by weight of tin. A method of producing the anticorrosion coating is also disclosed.

Abstract: An assembly for supplying power to an aircraft is disclosed having at least one battery housed in a respective housing, each housing comprising a wall in which a through-opening is arranged, and an exhaust device including a discharge duct connecting each housing opening to a common discharge port, a valve mounted on each opening. Each valve includes a membrane arranged so as to seal the opening closed and having a surface of pressure application towards the inside of the housing and a surface of pressure application towards the outside of the housing. The surface of pressure application towards the outside of the housing is larger than the surface of pressure application towards the inside of the housing, so that the membrane bursts at a bursting pressure inside the housing that is lower than a bursting pressure reached outside the housing.

Abstract: A transmitter device of a bi-static or multi-static radar system is disclosed and implemented for aerial surveillance. The transmitter device is intended to be on board a satellite orbiting the Earth. Once in orbit, the transmitter device is configured to obtain information relating to a region of interest monitored by at least one receiver device of the radar system, and to transmit a signal in a radio beam illuminating at least one portion of the region of interest.

Abstract: A structural component for an aircraft including at least one heatable component section having a layer structure including an inner base structure, at least one heating layer having carbon allotropes embedded in a matrix material, at least one first group of consecutive layers including at least one anode layer, at least one first insulating layer, and at least one cathode layer having an electroactive coating. The first group of layers are arranged between the inner base structure and the at least one heating layer, and at least one protective layer is arranged outside the heating layer. The first group of layers constitute a structural battery. The at least one anode layer and the at least one cathode layer are electrically connectable with the heating layer.

Abstract: A radar system for determining a distance to another radar system includes a transceiver. The transceiver transmits a first Frequency Modulated Continuous Wave, FMCW, radar signal. The first FMCW radar signal includes a first sweep profile. The transceiver is receives a second FMCW radar signal. The second FMCW radar signal includes a second sweep profile which differs from the first sweep profile. The radar system further includes a mixer which generates a beat signal based on the first and second FMCW radar signals. The radar system further comprises a deskewing unit which deskews the beat signal by matching the sweep profiles of the first and second FMCW radar signals. Further a method for determining a distance between radar systems, a system for determining a distance between first and second radar systems and a method for determining a distance between first and second radar systems.

Abstract: A radar system for providing position information to a mobile unit is provided. The radar system comprises a receiving interface. The receiving interface is adapted to receive radio frequency, RF, signals. The radar system further comprises a processing unit. The processing unit is adapted to process the received RF signals. The processing unit is adapted to determine an occupation of a predetermined time-frequency space by the received RF signals. The radar system further comprises a transmitting interface which adapted to transmit information on an intention of the radar system to occupy a specific portion of the predetermined time-frequency space. The radar system further comprises a plurality of beacon units. The beacon units are adapted to provide position information of the radar system on the specific portion in the predetermined time-frequency space, when it is determined that the specific portion of the predetermined time-frequency space is not occupied.

Abstract: An aircraft includes a control computer, load determining unit, first central inertial measurement device and a second inertial measurement device. The load determining unit is coupled to the first inertial measurement device and the second inertial measurement device. The load determining unit can receive instantaneous first accelerations detected by the first inertial measurement device and instantaneous second accelerations detected by the at least one second inertial measurement device and from this to determine instantaneous loads acting on the aircraft and to store them in a memory unit and/or to transmit them to an external unit. The load determining unit can determine expected maneuver accelerations. The load determining unit can subtract the expected maneuver accelerations from detected first accelerations and second accelerations and determine externally induced dynamic accelerations.

Abstract: The device includes a database (8) storing a digital cartography (MAP) of a terrain, an acquisition unit (4) configured to acquire a digital image (IMG) of the terrain, as well as a processing unit (2) configured to receive from the acquisition unit (4) the digital image (IMG) and determine a similarity between the digital cartography (MAP) and the digital image (IMG), so as to deduce a position (POS) of said machine from a result of said similarity.

Abstract: In order to allow or improve a laminar air flow in a transition region between aerodynamic profile elements, a pressure plate arrangement is proposed. The pressure plate arrangement comprises a pressure plate body and at least one cover strip, in particular a sealing strip. The pressure plate body has an outlet region from which free-flowing sealant can exit during pressing. The cover strip already contains cured sealant and presses the free-flowing sealant flat in order to be able to form the transition region.

Abstract: Measures for managing satellite bearer resources of a satellite telecommunications network. A corpus of data based on historical satellite bearer resource allocations is maintained. A machine learning agent is trained with the corpus to determine a plurality of weights for use in directing satellite bearer resource management in the satellite telecommunications network. A satellite bearer resource allocation request is received. A set of features is extracted from a current environment of the satellite telecommunications network. The set of features defines currently allocated satellite bearer resources. On the basis of the determined plurality of weights and the set of features, satellite bearer resources of the satellite telecommunications network are managed to satisfy the request.

Abstract: Computer systems (100) for satellite image acquisition and mission-plan calculation devices (120) for satellite and also Earth observation satellites (110). Based on the observation that the uncertainty connected with meteorological conditions can lead to the development of mission plans, for satellites, with low effectiveness, the uncertainty is characterized and used to improve the preparation of mission plans for satellite. A model of the uncertainties is built upon observations and/or past meteorological forecasts. Next, at the time of planning, the model is used by presenting the observations and/or the current forecast as input to the model. In that way, the acquisition zones for which it is unlikely to get acceptable images on the preferred acquisition date may be identified.

Abstract: A battery and an electrical battery monitoring device are disclosed having a first group of sensing switches connected in series on a first monitoring circuit, the sensing switches, a second group of electrical sensing switches connected in series on a second monitoring circuit, an input unit to provide an input to the first and second monitoring circuits, a monitoring unit to receive an output from the first and second monitoring circuits, wherein the monitoring unit receives at least two outputs from two measuring points of the first monitoring circuit, the two measuring points being separated by at least one sensing switch. The location of a defective battery cell may be early detected and precisely located by the monitoring of the battery cells in rows and columns.

Abstract: A method for position calculation of an antenna is provided. The method comprises calculating ranges between the antenna and the at least three transponders. The calculation includes range measurements between an antenna and at least three transponders. Respective positions of the at least three transponders are known. The method further comprises providing a first coordinate of three coordinates. The three coordinates indicate a position of the antenna. The method further comprises calculating second and third coordinates of the three coordinates based on the calculated ranges between the antenna and the at least three transponders. The method further comprises predicting ranges between the antenna and the at least three transponders based on the provided first coordinate and the calculated two coordinates. The method further comprises performing an optimization process based on the calculated ranges and the predicted ranges to infer an optimized position of the antenna.