Abstract: A high-frequency measurement setup for measuring a high-frequency test object, in particular, an antenna is provided. The setup includes one or more reflectors for high-frequency signals, a laser tracker, retrotargets for laser beams of the laser tracker that are disposed on the reflectors and are provided to orient the high-frequency test object, and a measuring unit that is designed to actuate the laser tracker in such a way that the high-frequency test object and one or more reflectors are measured in terms of their propagation of high-frequency signals.

Abstract: A rocket stage for a spacecraft includes an engine, a tank for storing a fuel and an oxidizer for combustion in the engine, a rocket stage primary structure, and an engine thrust frame that connects and transmits forces between the engine and the primary structure. The engine thrust frame includes at least an internal part thereof arranged internally within the tank. This internal part of the engine thrust frame forms an imperforate partition that divides an interior space of the tank into at least two chambers for storing the fuel and the oxidizer separately from one another. Propellant management devices including liquid guide vanes and refillable liquid reservoirs may be provided in connection with the partition in the tank interior space.

Abstract: Gear wheel and method for reducing vibrations transmitted by a rotating shaft. The gear wheel includes an inner part, which is connectable to a cause of vibration, a connection element and a ring gear. The connection element is structured and arranged to reduce vibrations.

Abstract: A device and method for three-dimensional positioning are provided. The three-dimensional positioning of a common reference point is determined by fusion of supplied measurements, taking into account a lever arm compensation between the reference point, a global navigation satellite system (GNSS) receiver antenna, at least one radar antenna, and an inertial measuring unit.

Abstract: The invention relates to a waveguide radiator comprising: A slotted waveguide (10) with a plurality of slots (14) inserted in the waveguide (10); and An additional inner conductor (12) installed inside the waveguide (10), which inner conductor is shaped in a polarization-dependent manner such that all of the slots (14) of the waveguide (10) can be excited with identical phase and amplitude.

Abstract: In a recovery and braking device for objects flying freely in space, particularly for capturing satellites and other orbital objects, (at least one,) preferably a larger number of capturing units (2) are arranged on a spacecraft serving as a steerable carrier vehicle (1), wherein the capturing units are separable from the spacecraft, are equipped with a propellant charge of their own, and comprise a closeable capture net (4) releasably connected via a line (5). The carrier vehicle is equipped with position or attitude controlling engines (6), in order to achieve an orienting of the coupled mass configuration in preparation for the separation. In that regard, several capturing units can be combined into a series or parallel connection.

Abstract: A method for transmitting additional information in a satellite navigation system includes providing a navigation message having a plurality of parameters, selecting at least one parameter from the plurality of parameters for the transmitting of the additional information, replacing the at least one parameter, at least partially, by the additional information so as to form a changed navigation message, and sending the changed navigation message.

Abstract: The invention relates to a device for fixing a test person on a standing surface, wherein at least one rope is tensioned between a hip belt placed on the test person and a retaining plate arranged below the standing surface.

Abstract: A towing apparatus for a spacecraft when in orbit is provided. The towing apparatus includes a cable, the first end of which is intended to be permanently connected to a spacecraft that must potentially be towed, and the second end of which is provided to be at least temporarily connected to a towing spacecraft for the purpose of towing. An attachment piece is disposed on the second end of the cable for mechanical attachment to a complementary attachment piece of the towing spacecraft, and a positioning aid is disposed to allow for simplified detection of the attachment piece by the towing spacecraft.

Abstract: A method for removing volatile organic substances from the contained air of closed habitats includes a) conducting contained air through an adsorber bed formed by a hydrophobic zeolite bed, b) closing the adsorber bed, c) extracting the air from the adsorber bed and feeding the air into the closed habitat, d) desorbing the volatile organic substances, in particular freons such as R134a and VOCs, from the adsorber bed by heating the adsorber, e) leading the desorbed substances to an environment outside the closed habitat, wherein water vapor, water, or CO2 is fed to the adsorber bed through a flushing line. The device includes a housing for accommodating an adsorber, a contained-air supply line, a contained-air return line, a flushing line, and least one outlet-air line for returning air from the adsorber bed into the closed habitat and for conducting the desorbate to an environment outside the closed habitat.

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 pivotal connection and a substantially rigid yet disruptable mechanical connection mount a respective foot pad on a distal end of each one of plural landing legs of a lander spacecraft. The mechanical connection includes at least one predetermined rated breaking point designed to break when the foot pad makes contact with a landing ground surface. At least two sensor elements, preferably electrical conductors or switches, are incorporated in the mechanical connection(s) of one or more foot pads. When the foot pad makes ground contact, the mechanical connection breaks at the rated breaking point(s), which also disrupts or actuates the sensor element(s), which thus provides a signal to an evaluating unit, which triggers the shut-down of at least one braking retrorocket or retrothruster.

Abstract: A method for measuring a radiation field in the direct vicinity of a measured object is provided. One or more antenna measurement probe(s) are moved in any desired fashion within the radiation field, and a number of high-frequency measurement points is thus recorded. During the movement of the antenna measurement probe, a position determination of a respective antenna measurement probe is conducted simultaneously with or in close temporal proximity to the capture of a respective high-frequency measurement point, in order to assign a position to each high-frequency measurement point so as to generate a spatially defined measurement point cloud. Finally, radiation patterns at any distance from the measured object may be determined from the spatial measurement point cloud by means of a field transformation method.

Abstract: Microthruster includes a combustion chamber comprising a substrate material, a fuel inlet, and a gas outlet. A first resistance heater is arranged in the combustion chamber. A catalyst is structured and arranged to decompose fuel entering the combustion chamber. First substrate material sections are heated by the first resistance heater to at least one of a predetermined temperature and a predetermined temperature range.

Abstract: A master clock generation unit for satellite navigation systems, comprises a plurality of frequency inputs for receiving a respective atomic clock signal, each having a first or a second reference frequency, and a number of frequency converters each having an input connected to one of the frequency inputs and an output. Each of the frequency converters receives an offset frequency (selected according to the first and second reference frequency at the assigned frequency input) from at least one frequency synthesizer, for providing the same intermediate frequency at each of the converter outputs. A switching matrix is connected to each of the converter outputs for selecting one of the intermediate frequencies as a primary clock provided at a first matrix output, and another of the intermediate frequencies as a secondary clock provided at a second matrix output.

Abstract: In a propellant tank, which especially stores cryogenic propellants, for example a fuel or an oxidizer for a spacecraft, and which operates with a driving gas to drive or convey the propellant, the propellant is separated from the driving gas in a propellant extraction apparatus using sieves with hydrostatic forces and capillary forces. The extraction apparatus includes a refillable reservoir, which is mounted near the tank floor outside of the tank shell, and which is connected via plural holes with the interior of the propellant tank. The extraction apparatus includes a double-walled housing that is thermally insulated. Capillary plates and struts are inserted in an L-shape into the reservoir. To substantially prevent the penetration of gas out of the propellant line, a cylinder-shaped pleated sieve is mounted at the end of the propellant line.

Abstract: Method, arrangement and system for improving a combined use of a plurality of different satellite navigation systems, in which each of the plurality of different satellite navigation systems includes a constellation of at least one satellite. The method includes broadcasting from each satellite of the constellation of a first satellite navigation system the clock models for all satellites of the constellation of a second satellite navigation system.

Abstract: A signal transponder for frequency conversion of signals from unknown signal sources is provided. The transponder includes an input for receiving a signal from an unknown signal source, an input filter for filtering the received signal, an input signal amplifier for amplifying the received signal, a mixer for converting the frequency of the amplified and filtered received signal to a predetermined frequency, a local oscillator for generating a clock signal supplied to the mixer for frequency conversion, an output filter for filtering the frequency converted signal, an output signal amplifier for amplifying the frequency converted signal, and an output for transmitting the filtered and amplified frequency converted signal.

Abstract: A satellite-based SAR system having a space segment with a plurality of satellites and a ground segment with one or a plurality of ground stations is provided. A satellite receives a position report from an emergency transmitter in its service area and forwards it to a ground station. The ground segment stores the position of the emergency transmitter, received with the last position report, in a management system for emergency transmitters. The emergency transmitter sends position reports to the satellite such that the reception of position reports at the satellite is coordinated such that at any time only position reports arrive which differ with regard to their signal parameters such that simultaneous reception is possible. A rescue operation is initiated for the emergency transmitter if no deactivation message has been received from the emergency transmitter and no position report is received from the emergency transmitter within a specified period.

Abstract: Solar cell including a substrate with first p-n-junction, separating the substrate into front portion having first doping and rear portion having second doping, being located close to front surface of substrate. A front layer having a p-n-junction, separating the front layer into front portion having first doping and rear portion having second doping. At least one first electric contact provided on front side of the solar cell electrically connected to front portion of the front layer, and second electric contact provided on rear side of solar cell electrically connected to a contact point provided on front side of the solar cell. Contact point is placed on a bottom surface of a groove open to front side of the cell and extending to rear portion of substrate, and an electrical connection between the second electric contact and the contact point is provided by the rear portion.