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: 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: 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: 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 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.

Abstract: An onboard cloud detection system comprising: a camera (1000) configured to acquire images of the Earth at predetermined acquisition intervals; and a data processing unit (2000) comprising: a cloud detection unit (2210) configured to use artificial intelligence, AI, algorithms to detect clouds; a packet utilization standard, PUS, application layer (2230) configured to issue telemetry and/or telecommands corresponding to a predetermined parameter of the output of the cloud detection unit (2210); and an interface configured to distribute the telemetry and/or telecommands to an external hardware and/or an external software terminal (3000, 4000).

Abstract: In order to improve usability of hybrid or fully electric aircraft, a fuel cell having improved efficiency and increased volume/weight specific energy density is provided. The fuel cell has a self-supporting membrane structure that is formed as a triply periodic level surface, which separates a first cavity supplied with gaseous fuel from a second cavity supplied with gaseous oxidizer in a gas-sealed manner while connecting the cavities in an ion-conductive manner.

Abstract: A system and a method for evaluating performance of a porous skin of an aircraft including the porous skin, and a boundary layer control system. The performance evaluation system includes a first sensor providing data related to the performance of the porous skin. The performance evaluation system is further configured to clean the porous skin based on the performance of the porous skin determined using the data received from the first sensor in order to ensure that the porous skin operates at its maximum capability.

Abstract: A cooling system containing a two-phase refrigerant that comprises a condenser, an evaporator and a conveying device. The evaporator is integrated in a heat source or thermally coupled thereto. Gaseous refrigerant from the evaporator is expanded in an expander, converted into mechanical energy and used to drive a generator for generation of electricity. Furthermore, an aircraft comprising a cooling system, wherein an electrical drive is supplied with electricity from a fuel cell, cooled using the cooling system, and the generator of the cooling system.

Abstract: A fiber composite laying method for producing a fiber composite scrim for forming a fiber composite component. The method includes supplying a reinforcement fiber band to a laying head, laying and compacting the supplied reinforcement fiber band on a laying surface at an average compaction pressure by a compaction roller, and detecting a local compaction pressure on the laid reinforcement fiber band by pressure sensors on the compaction roller.

Abstract: A composite component system includes a base component with a first component fiber ply and a second component fiber ply and a repair insert with a first repair fiber ply and a second repair fiber ply. The base component is connected to the repair insert by an adhesive joint. The first component fiber ply has an interface surface connected to the interface surface of the first repair fiber ply by the adhesive joint. The second component fiber ply has an interface surface connected to the interface surface of the second repair fiber ply by the adhesive joint. The first component fiber ply has a fiber orientation corresponding substantially to a fiber orientation of the first repair fiber ply. The interface surface of the first repair fiber ply completely overlaps the interface surface of the first component fiber ply.

Abstract: A fuselage for an aircraft. The fuselage has a control element with an integrated engine outlet. The control element is integrated at a rear end of the fuselage, so that the control element terminates flush with an outer skin of the fuselage in a circumferential direction of the fuselage. An outer wall of the control element surrounds the engine outlet wherein the engine outlet is directed towards an open rear side of the control element. The control element is connected to the fuselage such that the control element jointly the engine outlet is pivotable about a rotation axis with respect to the fuselage. The rotation axis runs transversely to a longitudinal direction of the fuselage and the control element functions as a tailplane when pivoting about the rotation axis.

Abstract: An apparatus for releasing received command data includes a processor unit with a code generator, a cryptography module, and a comparison module. The code generator generates a transaction code. The apparatus has a transmitting unit which provides the transaction code via an unsecured data connection, a receiving unit which receives an external authentication code and command data via the unsecured data connection, and a memory unit which stores data of a predefined private key. Also disclosed is a transmission apparatus for command data. The transmission apparatus has a basic receiving unit which receives the transaction code, an input unit which receives the command data, a basic memory unit which stores the data of the predefined private key, a basic processor unit which has a basic cryptography module, and a basic transmitting unit which provides the external authentication code and the command data via the unsecured data connection.

Abstract: A system for monitoring the state of an unmanned aircraft includes a first communication unit, a second communication unit that can be integrated within the aircraft, a state transmission unit that can be integrated within the aircraft for transferring state data of the aircraft, a receiving unit integrated within the aircraft for receiving control commands, a computing unit assigned to the aircraft for validating the state of the aircraft, and an external control and monitoring unit connected to the computing unit. The computing unit executes a simulation model of the aircraft, which is based on numerical integration of a system of equations with a simulation state vector. The computing unit sends a warning signal to the control and monitoring unit on the occurrence of one or repeated instances of a model error correction term exceeding specified interval limits.

Abstract: A method for synchronizing wireless network nodes of a wireless communication network involves a base station of the wireless communication network to determine or obtain a maximum value for a frequency content per unit of time of an FMCW radio-frequency signal interfering with the wireless communication network, transmit a first synchronization frame containing a first synchronization sequence in a first wireless communication frequency bandwidth, and transmit a second synchronization frame simultaneously to the first synchronization frame, the second synchronization frame containing a second synchronization sequence in a second wireless communication frequency bandwidth that is spaced apart from the first wireless communication frequency bandwidth by a spectral distance larger or equal to the product of the determined maximum value for the frequency content per unit of time of the FMCW radio-frequency signal and duration of the first and second synchronization sequences.

Abstract: An interconnector plate for a fuel cell and a fuel cell system for an aircraft. For better extraction of the energy generated by the fuel cell, an interconnector plate can be attached by form fit to fixing studs of the fuel cell by retaining eyes. The interconnector plate may additionally be secured using glass solder. In preparation for a higher power density, a fuel cell can be produced in ceramic by 3D-printing and has an improved power density because of its helical shape.