Abstract: A honeycomb core for dimensionally stable components (e.g., a reflector) in sandwich construction with a plurality of cells with a triangular cell cross section made from carbon fiber reinforced plastic. The honeycomb core is assembled from flat laminate strips by plugging, wherein the laminate strips have slots running transversely to the extension direction respectively on their longitudinal side. The laminate strips are connected to one another in such a way that the slots of three laminate strips engage in a positive-locking manner in one another at a respective intersection point to form the corners of the cells of the honeycomb core.

Abstract: A method for determining a position of a receiver via use of encrypted signals of a public regulated service. The method comprises transmitting PRN code chips to the receiver by an assistance server. The method further comprises storing the transmitted PRN code chips to be used before a designated time interval by the receiver. The method further comprises receiving the encrypted signals during the designated time interval by the receiver from satellites in line-of-sight to the receiver. The method further comprises determining the position of the receiver via use of the encrypted signals and the stored PRN code chips by the receiver.

Abstract: A method of manufacturing a charge dissipative surface layer on a member made from or consisting of a dielectric polymeric material or polymer-based composite which is intended to be used in space and other extreme environments, the member having at least one surface, in particular two opposing surfaces, each of the surfaces having a flat or a three-dimensional shape. The method includes carbonizing the at least one surface of the member in a vacuum environment through ion bombardment with simultaneous surface renewal in a dynamic way, by bombardment of the at least one surface with an ion beam formed in a gaseous linear high-current technological ion beam source of rare gas and added predetermined amount of a carbonaceous gas in the same ion beam gas admixture in order to achieve a treated carbonized surface layer with a uniform surface resistivity in a charge-dissipative range.

Abstract: A modular satellite having a plurality of electronics boxes that accommodate electrical and/or electronic modules. The electronics boxes are or can be electrically connected with one another. The satellite is provided with a basis structural panel, a docking structure disposed on the basis structural panel, and a plurality of device carrier panels that are or can be connected with the docking structure. The docking structure has first electrical connection elements for an electrical connection with the electronics boxes. The device carrier panels have mechanical connection elements for holding the electronics boxes. The respective device carrier panel is configured, at least in certain regions, so that it can be tempered by means of integrated heat sources and/or heat sinks.

Abstract: A waveguide radiator includes a slotted waveguide with a plurality of transverse or longitudinal slots provided in the waveguide and an additional inner conductor provided in the waveguide. The inner conductor is formed, depending on the alignment of the slots in such a manner that the result is a feed according to the traveling wave principle, wherein all slots of the waveguide can be excited with identical phase.

Abstract: A method for computing self-contamination processes of a spacecraft involves receiving a first set of input parameters comprising general definitions of the spacecraft, and a second set of input parameters comprising control parameters for the spacecraft orbital data, physics, numeric. A self-contamination process of the spacecraft is calculated based on the received first and second sets of input data by calculating an analytical solution of a basic equation for calculating a deposit of molecules outgassed from surfaces of the spacecraft in a single computation step with the data processing device. The calculated deposit of molecules is then output.

Abstract: A thrust nozzle, in particular thrust nozzle for a rocket engine, with a convergent wall section, a throat section and a divergent wall section. The divergent wall section has a first region adjacent to the throat section, the wall contour of which region corresponds to a truncated ideal nozzle, and the divergent wall section has a second region facing away from the throat section, which region has a wall contour deviating from the first region.

Abstract: A container for effecting at least one non-lethal change in inherent properties of a non-human biological system, such as a plant or a fungus, under the influence of zero gravity, comprising a carrier plate configured to receive two capacitor plates of a plate capacitor, wherein the plates are situated parallel to one another and in each case perpendicularly on the carrier plate, at least one sample container arranged horizontally on the carrier plate, adjacent to each of the two capacitor plates and configured to receive the biological system, and an electromagnet arranged substantially half way between the capacitor plates and, when seen from the carrier plate, arranged horizontally above the at least one sample container. Additionally, a European modular cultivation system for use in the International Space Station comprises a centrifuge, wherein the container is received in the centrifuge.

Abstract: A hinge assembly comprises first and second tape spring elements, wherein each of the spring elements is configured to connect a first element of a space structure to a second element of the space structure. Each of the first and the second tape spring elements is movable from a folded state into an unfolded state by releasing stored strain energy, to deploy the first and the second element of the space structure. The first tape spring element is connected to a first direct current source and configured to conduct direct current of a first polarity supplied to the first tape spring element from the first direct current source. The second tape spring element is connected to a second direct current source and configured to conduct direct current of a second polarity, opposite to the first polarity, supplied to the second tape spring element from the second direct current source.

Abstract: A wireless communication unit for compensating for Ionospheric group delay in a satellite communication system. The wireless communication unit comprises: a receiver configured to receive a multi-carrier signal from a satellite; and a processor coupled to the receiver. The processor is configured to: process the multi-carrier signal to produce a plurality of digital representations of individual carriers of the multi-carrier signal; estimate, from the plurality of digital representations of individual carriers of the multi-carrier signal, a Total Electron Content, TEC, value associated with a communication path between the satellite and the wireless communication unit through Earth's Ionosphere; and apply compensation for Ionospheric group delay subjected to the multi-carrier signal based on the determined TEC value.

Abstract: An electrically powered propulsion system for a spacecraft includes a first center of gravity at a first time of operation and a second center of gravity at a second time of operation, where the second center of gravity is different from the first center of gravity. The electrically powered propulsion system includes a thruster realignment mechanism and at least two thrusters coupled to the thruster realignment mechanism. Each of the at least two thrusters has an individual thrust vector. The thruster realignment mechanism is adapted such that, in a first position, the individual thrust vectors of the at least two thrusters pass through the first center of gravity and that, in a second position, the individual thrust vectors of the at least two thrusters pass through the second center of gravity. The thruster realignment mechanism holds the first position in the event all of the at least two thrusters are without any failure.

Abstract: A fastening device for use in a spacecraft comprises a shaft and a head, which is connected by a first solder to the shaft. The first solder comprises a material of which the melting point is lower than the temperature acting on the fastening device on re-entry of a spacecraft equipped with fastening device into the earth's atmosphere.

Abstract: A flexible, thermal bridge element, particularly for a space flight instrument, a satellite, a transportation device, or a machine component, includes a number of carbon fiber-reinforced plastic (CFK) layers stacked on top of one another. Each of the CFK layers is composed of a plurality of heat-conductive carbon fibers embedded in a matrix. In at least two segments, particularly opposing end segments, the CFK layers are freed of the material of the matrix so that the carbon fibers of a respective CFK layer are exposed in the at least two segments. The exposed segments of the carbon fibers are provided with an associated metallization, by way of which within the framework of a thermally assisted joining process, the bridge element is connected to a thermally conductive connector element.

Abstract: Noise distribution shaping for signals, particularly for the application in receivers for CDMA signals. A method for noise distribution shaping for signals comprises the acts of receiving a signal of interest from a signal transmitter, detecting whether the received signal of interest is present, and if the received signal of interest is present iteratively performing the following acts of adapting at least one blanking threshold or the received signal of interest according to an offset value depending on the amplitude of the received signal of interest, and generating a blanking control signal by comparing the received signal of interest with the at least one blanking threshold, modifying the noise distribution of the received signal of interest by applying blanking of the received signal of interest under control of the blanking control signal.

Abstract: A reflective device for an optical measuring system and for arranging in a measuring object, including an optical deflection device and a retroreflector. The deflection device can deflect a light beam at the optical deflection device from an incident axis. The retroreflector can reflect the beam parallel to its incoming direction for each of various incoming directions of a light beam onto the retroreflector. The reflective device can be arranged in the measuring object such that a measuring beam of the optical measuring system, pointed at the measuring object and arriving at the optical deflection device in a first direction, is deflected by the optical deflection device onto the retroreflector in a different, second direction and, following reflection at the retroreflector, is deflected by the optical deflection device in reverse parallel to the first direction. An optical measuring system, a flying object and a flying object system are further described.

Abstract: A method is provided for noise distribution shaping of signals, particularly for the application in receivers for CDMA signals. The method includes the acts of generating a blanking control signal by comparing a received signal with at least one blanking threshold, adapting the at least one blanking threshold or the received signal according to an offset value depending on the amplitude of the received signal, and modifying the noise distribution of the received signal by applying blanking of the received signal under control of the blanking control signal.

Abstract: A method for the reduction of receive data of a radar includes receiving a radar echo signal emanating from a chirp-like transmit signal and specifying a temporal receive window of the radar echo signal as a function of an area to be detected by a radar. The method also includes dividing the received radar echo signal into a plurality of spectral sub-bands, determining sub-band windows for each of the plurality of spectral sub-bands, activating the sub-band windows within the temporal receive window of the radar echo signal as a function of a receive time of the radar echo signal, and then sampling the radar echo signal using a sampling rate that is adjusted as a function of a number of sub-band windows active at a respective sampling instance.

Abstract: This relates to a method for disseminating data in a navigation or communication system comprising several transmitters for signals, wherein a common frame structure is provided for the signals and each transmitter disseminates common data and transmitter-dedicated data with its transmitted signal, and wherein the method comprises the following acts to be executed by each one of the transmitters: receiving the common data encoded with a first encoding scheme; encoding transmitter-dedicated data onboard the transmitter with a second encoding scheme; assigning the encoded common data to a number of first frames of the frame structure provided for the signals and assigning the encoded transmitter-dedicated data to a number of second frames of the frame structure provided for the signals, wherein the second frames differ from the first frames; assembling a signal to be transmitted from the number of first and second frames; and transmitting the assembled signal.

Abstract: A bending frame extends the travel of an actuator for a mechanically actuated component. The bending frame includes a plurality of bendable longitudinal struts, which are arranged about a longitudinal axis on which the travel of the actuator runs. The longitudinal struts each extend in the direction of the longitudinal axis, and an application of force enacted by the actuator long the actuation path on the longitudinal struts causes same to bend in a direction perpendicular to the longitudinal axis. Respective cross struts extend out toward the longitudinal axis from each of the longitudinal struts, wherein a first end of a respective cross strut is articulated to a respective longitudinal strut and a second end of the respective cross strut opposite to the first end is provided in order to transmit force to the component in the direction of the longitudinal axis for the purpose of actuation thereof.

Abstract: A high electrical conductive, high temperature stable foil material, a process for the preparation of such a high electrical conductive, high temperature stable foil material, a solar cell interconnector including the high electrical conductive, high temperature stable foil material as well as the use of the high electrical conductive, high temperature stable foil material and/or the solar cell interconnector in solar power, aircraft or space applications. The high electrical conductive, high temperature stable foil material includes an aluminum alloy that has at least two elements selected from the group of scandium (Sc), magnesium (Mg), zirconium (Zr), ytterbium (Yb) and manganese (Mn).