In a container for transporting and for storing in particular cryogenic liquids, for example liquefied natural gas (LNG), having an arrangement for damping the movement of the liquid, the damping means is introduced, in the form of a supporting structure, into the container or tank. The supporting structure consists of rods, connecting elements and a horizontal, oblique and vertical plates and is positioned in the tank, wherein its outer shape is adapted in a form-fitting manner to the geometry of the tank. The supporting structure is arranged in the interior of the tank by way of bulk-material-filled bags, and the bags are connected to one another by screws and washers. The pipes of the supporting structure are filled with the liquid which is to be transported or stored, and emptied of the same, via bores in the pipes. The horizontal, oblique and vertical plates are fastened in a releasable manner, by means of screws, on the pipes and connecting elements.
In a method for the wireless transmission, in closed spaces, of the energy emitted by at least one light source during space missions, the luminous energy emitted by one or more light sources is reflected on a reflective surface inside the closed space and is received in one or more solar cell modules and converted into electricity. The reflective surface consists of a multilayer insulation surface.
H01L 31/042 - Modules PV ou matrices de cellules PV individuelles
H01L 31/052 - Moyens de refroidissement directement associés ou intégrés à la cellule PV, p.ex. éléments Peltier intégrés pour refroidissement actif ou puits thermiques directement associés aux cellules PV
H02S 40/22 - Moyens réflecteurs ou concentrateurs de lumière
3.
Rocket stage having engine thrust frame integrated with tank
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.
F02K 9/60 - Parties de leur structureDétails non prévus ailleurs
F02K 9/42 - Moteurs-fusées, c.-à-d. ensembles fonctionnels portant à la fois le combustible et son oxydantLeur commande utilisant des propergols liquides ou gazeux
4.
METHOD FOR PERFORMING IMMUNOASSAYS UNDER WEIGHTLESS CONDITIONS
The invention relates to a method for controlled movement of magnetic carriers (2) in a sample volume (1) for performing immunoassays under weightless or reduced-weight conditions, wherein the magnetic carriers (2) are moved inside the sample volume (1) by means of permanent magnets (3a, 3b) movably arranged relative to at least one spatial axis (x, y, z) of the sample volume (1).
G01N 33/543 - Tests immunologiquesTests faisant intervenir la formation de liaisons biospécifiquesMatériaux à cet effet avec un support insoluble pour l'immobilisation de composés immunochimiques
The invention relates to a therapy assembly, comprising a platform (1) that can oscillate, wherein a computer (7) for controlling the platform (1) that can oscillate is present, wherein a device (10) for detecting the movements of a test person (8) on the platform (1) that can oscillate and for converting the detected movements into a first control signal for the computer (7) connected to the device (10) is present, and wherein a first element (4c, 4d, 5) connected to the computer (7) for converting a second control signal of the computer (7) into mechanical displacements of the platform (1) that can be oscillated is present.
A61H 1/00 - Appareils pour l'exercice passifAppareils vibrateursDispositifs de chiropractie, p. ex. dispositifs pour appliquer des chocs au corps, dispositifs externes pour étirer ou aligner de façon brève des os non fracturés
A61H 23/02 - Massage par percussion ou vibration, p. ex. en utilisant une vibration ultrasoniqueMassage par succion-vibrationMassage avec des membranes mobiles à entraînement électrique ou magnétique
A tank especially suitable for use as a fuel or oxidizer tank in spacecraft is divided into two tank spaces by a membrane. A liquid is stored on one side of the membrane and a pressure gas is stored on the other side of the membrane. The pressure gas is to drive the liquid out of the tank. The membrane is made of a polymer material and is held by a spring ring in a recess on the outer wall of the tank. The spring ring has a substantially C-shaped cross-section to exert elastic spring holding forces on the membrane in the recess.
B65D 88/12 - Grands réceptacles rigides spécialement conçus pour le transport
F17C 7/00 - Procédés ou appareils pour vider les gaz liquéfiés, solidifiés ou comprimés contenus dans des récipients sous pression, non couverts par une autre sous-classe
B64G 1/40 - Aménagements ou adaptations des systèmes de propulsion
F17C 1/00 - Récipients sous pression, p. ex. bouteilles de gaz, réservoirs de gaz, cartouches échangeables
F15B 1/12 - Accumulateurs utilisant un coussin de gazDispositifs de remplissage de gazIndicateurs ou flotteurs à cet effet avec des moyens de séparation flexibles fixés par leur périphérie
7.
ARTICULATED JOINT FOR DEPLOYING AND LOCKING A SOLAR GENERATOR OR A REFLECTOR
The invention relates to an articulated joint for deploying and locking a solar generator or a reflector or another deployable space travel component is proposed, which consists of two joint halves (4, 10), a joint axle, and a drive. A driving spring (1) of the drive has a spring characteristic line across the unfolding angle of the two joint halves (4, 10), which progressively increases during the deployment, in order to compensate for the friction moment which varies across the unfolding angle.
In a wireless local messaging system having at least one transmitter and at least one receiver, said at least one transmitter transmitting a local message to said at least one receiver, said at least one receiver is a navigation receiver configured to receive and process navigation messages from satellites of a global navigation satellite system on a given carrier frequency, each of said satellites transmitting the navigation messages with a satellite-individual PRN code, said at least one transmitter is configured to transmit said local message in a local message signal on the given carrier frequency with a local PRN code which is not used by a satellite of said global navigation satellite system, and said at least one receiver is further configured to receive said local PRN code and to process said local message signal.
G01S 19/11 - Éléments coopérantsInteraction ou communication entre les différents éléments coopérants ou entre les éléments coopérants et les récepteurs fournissant des signaux de positionnement supplémentaires dédiés les éléments coopérants étant des pseudolites ou des répétiteurs de signaux de systèmes de positionnement par satellite à radiophares
G01S 19/46 - Détermination de position en combinant les mesures des signaux provenant du système de positionnement satellitaire à radiophares avec une mesure supplémentaire la mesure supplémentaire étant du type signal d'onde radioélectrique
9.
PLATFORM RELATIVE NAVIGATION USING RANGE MEASUREMENTS
The invention relates to a method for platform relative navigation using range measurements, wherein - four or more transmitter (T1-T4) of positioning signals are located on and/or near a platform of a first object and - a second object approaching the platform comprises three or more receivers (A1-A3) for receiving the positioning signals, and wherein the method comprises the acts of - performing for each received positioning signal a range measurement between the transmitter of the positioning signal and the receiver of the positioning signal, and - estimating the relative position and relative attitude of a body frame of the second object with regard to the first object by processing the range measurements with a state space estimation algorithm implementing a model of the system of the first and second object.
G01S 5/14 - Localisation par coordination de plusieurs déterminations de direction ou de ligne de positionLocalisation par coordination de plusieurs déterminations de distance utilisant les ondes radioélectriques déterminant des distances absolues à partir de plusieurs points espacés d'emplacement connu
10.
METHOD AND SYSTEM FOR MONITORING THE INTEGRITY OF FREIGHT CONTAINERS
The invention relates to a method for monitoring the integrity of a freight container along a transport path. The freight container has a monitoring device (10) which is paired with said freight container and which has at least one monitoring sensor (12) that monitors the integrity of the freight container. After the monitoring sensor (12) detects an event that violates the freight container integrity, event data is transmitted to a remote analyzing center (14), in particular an analyzing device (18) that is assigned to the analyzing center (14), said data representing the integrity violation. An evaluation of the transmitted event data is carried out in the analyzing center (14), in particular in the analyzing device (18) that is assigned to said analyzing center, using specified criteria with respect to either an authorized or an unauthorized integrity violation of the freight container. An opening or a closing of the freight container is evaluated as an authorized integrity violation if an electronic authorizing code that represents the authorization of the opening process or the closing process is transmitted to the analyzing center (14) in relation to the event data representing said integrity violation. The method is characterized in that respective authorization codes of different function groups, function codes, are used to differentiate different types of opening processes and/or different types of closing processes so that a determination can be carried out in the analyzing center (14) as to which type of opening process and/or which type of closing process is being carried out or should be carried out using the received respective function code type.
G07C 5/00 - Enregistrement ou indication du fonctionnement de véhicules
G07C 5/08 - Enregistrement ou indication de données de marche autres que le temps de circulation, de fonctionnement, d'arrêt ou d'attente, avec ou sans enregistrement des temps de circulation, de fonctionnement, d'arrêt ou d'attente
G08B 25/10 - Systèmes d'alarme dans lesquels l'emplacement du lieu où existe la condition déclenchant l'alarme est signalé à une station centrale, p. ex. systèmes télégraphiques d'incendie ou de police caractérisés par le moyen de transmission utilisant des systèmes de transmission sans fil
The invention relates to a freight container having an antenna (10) for sending and/or receiving electromagnetic signals transmitted via satellites, preferably in the L band frequency range, wherein the antenna (10) is arranged externally on a side portion (12) of the freight container and has linear polarization.
H01Q 9/30 - Antennes résonnantes avec alimentation à l'extrémité d'un élément actif allongé, p. ex. unipôle
H01Q 19/10 - Combinaisons d'éléments actifs primaires d'antennes avec des dispositifs secondaires, p. ex. avec des dispositifs quasi optiques, pour donner à une antenne une caractéristique directionnelle désirée utilisant des surfaces réfléchissantes
G08B 13/24 - Déclenchement électrique par une interférence avec la distribution d'un champ électromagnétique
G06Q 10/08 - Logistique, p. ex. entreposage, chargement ou distributionGestion d’inventaires ou de stocks
12.
SALVAGING AND BRAKING DEVICE FOR OBJECTS FLYING FREELY IN SPACE
The invention relates to a salvaging and braking device for objects flying freely in space, in particular for capturing satellites and other orbital objects. At least one, preferably a large number of capturing units (2) are arranged on a spacecraft that can be used as a steerable carrying vehicle (1), wherein said capturing units can be separated from the spacecraft, are equipped with an independent propellant charge, and have a capturing net (4) which is removably connected via a line (5) and which is closeable. The carrying vehicle is equipped with position controlling engines (6) in order to achieve an orientation of the coupled mass configuration in preparation for the separation. Multiple capturing units can be combined into a serial or parallel connection. The passive stability of the arrangement is used after the oriented deployment/separation, sufficient position stability and accuracy being ensured even without active position control, taking into account the system behavior of the flexibly coupled objects.
The invention relates to an electrolysis method for electrolytic cells having an electrode-membrane-electrode assembly comprising two porous electrodes (3, 6) having a porous membrane (1) located therebetween and filled with electrolyte (22) or having an ion exchange membrane located therebetween, one or more liquids (22, 5) being led directly into the membrane (1) of the electrode-membrane-electrode assembly (3, 1, 6), wherein the one or more liquids (22, 5) are guided in a channel structure (20) arranged in the membrane (1). The invention further relates to an electrolytic cell (18) comprising porous electrodes (3, 6), between which a porous membrane (1) is arranged, wherein a liquid electrolyte (22) is fixed in the pores of electrodes (3, 6) and membrane (1), a product gas chamber (2, 15) adjoining the cathode (3), a further product gas chamber (7, 16) adjoining the anode (6), and an arrangement for feeding a liquid (22, 5) to the electrodes (3, 6), wherein a channel structure (20), in which distribution of the liquid (22, 5) is provided, is arranged in the membrane (1).
C25B 9/00 - Cellules ou assemblages de cellulesÉléments de structure des cellulesAssemblages d'éléments de structure, p. ex. assemblages d'électrode-diaphragmeCaractéristiques des cellules relatives aux procédés
C25B 11/03 - ÉlectrodesLeur fabrication non prévue ailleurs caractérisées par la configuration ou la forme perforées ou foraminées
C25B 13/02 - DiaphragmesÉléments d'espacement caractérisés par la configuration ou la forme
14.
METHOD FOR SEPARATING OFF CARBON DIOXIDE IN BIOGAS PLANTS
The invention relates to a method for separating off carbon dioxide in biogas plants, comprising an adsorption phase in which the carbon dioxide is separated off in an adsorber (A1,A2, A3, A4) and the biomethane obtained is fed as biogas (3) to a natural gas grid, and a regeneration phase, in which the adsorber is regenerated and the carbon dioxide (10) that is separated off from the biogas is fed to the ambient air (11), wherein crude biogas (2) that is treated in the adsorption phase is passed at ambient pressure through an adsorber made of an adsorber resin suitable for adsorption of carbon dioxide, and in the regeneration phase the adsorber is regenerated with a purge gas (7) at temperatures between 20 and 100°C, and also ambient pressure, wherein the crude biogas is treated upstream of the carbon dioxide separation method, wherein the crude biogas is desulphurized and dried and minor components can be removed, and wherein, for avoiding impurities in the biogas, at the start of the adsorption phase a purge process is carried out on the adsorber with treated crude biogas, wherein the purge process is controlled with respect to time via a number of valves and a sensor.
B01D 53/04 - Séparation de gaz ou de vapeursRécupération de vapeurs de solvants volatils dans les gazÉpuration chimique ou biologique des gaz résiduaires, p. ex. gaz d'échappement des moteurs à combustion, fumées, vapeurs, gaz de combustion ou aérosols par adsorption, p. ex. chromatographie préparatoire en phase gazeuse avec adsorbants fixes
15.
APPARATUS FOR STABILIZATION OF MARINE VESSELS BY MEANS OF INFLATABLE BUOYANT BODIES
In an apparatus for production of gas for filling buoyant bodies for bodies which are located in the water with gases stored in a compressed form, a compressed-gas reservoir (11) is combined with a hot-gas generator (12), which is known per se. The hot-gas generator can be arranged both inside and outside the compressed-gas reservoir and, furthermore, the hot-gas generator can be integrated in a mixing chamber (14). The hot-gas generator is based on the catalytic decomposition of a liquid energy carrier, preferably hydrazine, or generates the buoyancy gas by combustion or by the chemical reaction of a solid energy carrier, preferably lithium hydride, with the surrounding seawater. The compressed-gas reservoir (11) is filled with a gas. The hot-gas generator (12) is preferably designed such that, when the apparatus is activated, the cooling down of the compressed gas is compensated for by the heat generated by the hot-gas generator, or pressure is built up or decreased in a controlled manner within the compressed-gas reservoir.
B63C 7/10 - Renflouement de navires désemparés, échoués ou coulésRécupération d'éléments de navires ou d'ameublements, p. ex. de coffres fortsRécupération d'autres objets immergés dans lequel l'action de relevage a sa source dans ou en dehors du navire ou de l'objet avec emploi de flotteurs gonflables extérieurs au navire ou à l'objet
16.
METHOD AND DEVICE FOR REMOVING VOLATILE ORGANIC SUBSTANCES FROM THE CONTAINED AIR OF CLOSED HABITATS
The invention relates to a method for removing volatile organic substances from the contained air of closed habitats, comprising the following steps: a) conducting contained air through an adsorber bed (3) 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 (1), d) desorbing the volatile organic substances, in particular freons such as R134a and VOCs, from the adsorber bed (3) by heating the adsorber (3), e) leading the desorbed substances to an environment (13) outside the closed habitat, wherein water vapor, water, or CO2 is fed to the adsorber bed (3) through a flushing line (SL). The device comprises a housing (14) for accommodating an adsorber (3), a contained-air supply line (RZL), a contained-air return line (RRL), a flushing line (SL), and least one outlet-air line (AL, AL1, AL2) for returning air from the adsorber bed into the closed habitat (1) and for conducting the desorbate to an environment (13) outside the closed habitat (1), wherein a vacuum pump (9) and a three-way valve (11) are arranged in the outlet-air line (AL) and wherein one outlet of the three-way valve (11) is connected to the closed habitat (1) and the other outlet of the three-way valve (11) is connected to the environment (13) outside the closed habitat (1).
B01D 53/04 - Séparation de gaz ou de vapeursRécupération de vapeurs de solvants volatils dans les gazÉpuration chimique ou biologique des gaz résiduaires, p. ex. gaz d'échappement des moteurs à combustion, fumées, vapeurs, gaz de combustion ou aérosols par adsorption, p. ex. chromatographie préparatoire en phase gazeuse avec adsorbants fixes
A62B 7/14 - Appareils respiratoires pour vol à haute altitude
17.
SATELLITE COMMUNICATION SYSTEM AND METHOD FOR TRANSMITTING DATA
A satellite communication system comprises: - at least one base station (1); - at least one satellite (2) which can be brought into communication connection with the base station (1) for data transmission; and - a plurality of receivers (32) adapted to receive signals transmitted from the satellite (2); - wherein the communication system is designed • to transmit data in at least one uplink data stream (U) from the base station (1) to the satellite (2) with a first data transmission rate and • to transmit data in at least one downlink data stream (D) from the satellite (2) to the receivers (32) with a second data transmission rate; - wherein the first data transmission rate is lower than the second data transmission rate and - wherein the satellite (2) is provided with a data storage means (22) adapted to store the data transmitted from the base station (1) to the satellite (2) and to supply the data provided for the transmission to the receivers (32).
The invention relates to a flexible GNSS receiver RF frontend (10) comprising an adjustable input band-pass filter unit (12) for filtering a carrier frequency signal being modulated with GNSS information and received by means of an antenna (20), a mixer unit (14, 15) for mixing the output signal of the input band-pass filter unit with a reference clock signal and generating a low- or band-pass filtered output signal comprising GNSS information modulated onto the carrier frequency, wherein the filter-characteristic of the mixer unit are adjustable in order to adapt it to the dedicated bandwidth requirements of the received carrier frequency signal, an adjustable gain amplifier (16) for amplifying the low- or band-pass filtered output signal, and an analog-to-digital converter (18) for digitizing the amplified low- or band-pass filtered output signal.
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.
The invention relates to a satellite‑based SAR system having a space segment (10) with a plurality of satellites (12, 14) and a ground segment (16) with one or more ground stations (18), wherein a satellite (12) receives a position report (20) from an emergency transmitter (22) in its service area (24) and forwards it to a ground station (18), the ground segment (16) stores the position of the emergency transmitter, received with the last position report, in a management system (26) for emergency transmitters, the emergency transmitter sends position reports (21) to the satellite such that the reception of position reports on the satellite is co‑ordinated such that at any time only position reports are received which differ in terms of their signal parameters such that simultaneous reception is possible, and 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 prescribed period.
The invention relates to a peristaltic pump for conveying fluids, comprising a stator and a rotor supported therein, wherein a flexible hose is integrated in the stator, and the rotor comprises radially arranged conveying elements, which squeeze the hose over a section containing the fluid, and wherein the squeezed fluid section moves progressively in the hose under the effect of a motor connected to the rotor, wherein the conveying elements are designed as rotatably supported rollers, which comprise at least two rolling-element bearings, the outer rings of which are connected by means of a common outer sleeve and the inner rings of which are connected to the rotor, wherein under the effect of the motor, the rotor moves in the stator and the outer rings of the conveying elements roll on the inner surface of the stator.
The invention relates to a method and to a system for the monitoring, in particular real-time monitoring, of the integrity of a freight container, preferably a transport container, wherein the freight container has a monitoring device (10) that is associated therewith and that has at least one monitoring sensor (12) monitoring the integrity of the freight container. The method is characterized by the following measures: - following the detection by the monitoring sensor (12) of an event damaging the integrity of the freight container, event data which represent the damaging of the integrity are transmitted to a remote analysis center (14), in particular an analysis device (18) associated with the analysis center (14), - in the analysis center (14), in particular in the analysis device (18) associated therewith, the transmitted event data are assessed by using predetermined criteria with regard to either authorized or unauthorized damaging of the intensity of the freight container, - the damaging of the integrity, in particular opening or closing a freight container, is judged to be authorized if, in particular at the time of the arrival of the event data in the analysis center (14) or in an in particular predetermined time interval before or after the arrival of the same, an authorization code representing the authorization of the damaging of the integrity in relation to the event data representing the damaging of the integrity is present in the analysis center (14).
G07C 5/08 - Enregistrement ou indication de données de marche autres que le temps de circulation, de fonctionnement, d'arrêt ou d'attente, avec ou sans enregistrement des temps de circulation, de fonctionnement, d'arrêt ou d'attente
G07C 9/00 - Enregistrement de l’entrée ou de la sortie d'une entité isolée
G08B 13/14 - Déclenchement mécanique par l'enlèvement ou les essais de déplacement d'articles portatifs
G08B 25/10 - Systèmes d'alarme dans lesquels l'emplacement du lieu où existe la condition déclenchant l'alarme est signalé à une station centrale, p. ex. systèmes télégraphiques d'incendie ou de police caractérisés par le moyen de transmission utilisant des systèmes de transmission sans fil
The invention relates to an ion drive (1) for a spacecraft, comprising a high frequency generator (4) for generating an alternating electromagnetic field for the ionization of a propellant and an acceleration system (7) for the charge carriers. The ion drive comprises a first means, by which the high voltages required for the acceleration system (7) can be derived from the currents and/or voltages produced by the high frequency generator (4) in order to produce the alternating electromagnetic field.
The invention relates to a plasma generator comprising a housing (20) that surrounds an ionisation chamber (5); at least one working fluid supply line (30) leading into the ionisation chamber (5), said ionisation chamber (5) comprising at least one outlet (21); and at least one electric coil arrangement (4) that surrounds at least one area of the ionisation chamber (5); said coil arrangement (4) being electrically connected to a high-frequency alternating current source (AC) that is designed such that a high frequency electric alternating current is applied to at least one coil of the coil arrangement (4). Said plasma generator is characterised in that an additional current source (DC) is designed such that a DC current or an alternating voltage is applied at a lower frequency than the voltage supplied by the high frequency alternating current source (AC) to at least one coil of the coil arrangement (4), is provided.
H01J 27/16 - Sources d'ionsCanons à ions utilisant une excitation à haute fréquence, p. ex. une excitation par micro-ondes
H01J 27/18 - Sources d'ionsCanons à ions utilisant une excitation à haute fréquence, p. ex. une excitation par micro-ondes avec un champ magnétique axial appliqué
H01J 37/32 - Tubes à décharge en atmosphère gazeuse
F03H 1/00 - Utilisation du plasma pour produire une poussée propulsive par réaction
25.
METHOD FOR THE TRANSMISSION OF ADDITIONAL DATA ALONG WITH NAVIGATION MESSAGES IN A SATELLITE NAVIGATION SYSTEM
The invention relates to a method for transmitting additional data along with navigation messages in a satellite navigation system, a navigation message containing one or more parameters. Said method comprises the following steps: at least one parameter of a navigation message is selected for transmitting the additional data (S10); the at least one selected parameter is replaced at least in part by the additional data (S12); and the navigation message that has been modified in this way is transmitted (S14).
G01S 5/14 - Localisation par coordination de plusieurs déterminations de direction ou de ligne de positionLocalisation par coordination de plusieurs déterminations de distance utilisant les ondes radioélectriques déterminant des distances absolues à partir de plusieurs points espacés d'emplacement connu
G01S 1/00 - Radiophares ou systèmes de balisage émettant des signaux ayant une ou des caractéristiques pouvant être détectées par des récepteurs non directionnels et définissant des directions, situations ou lignes de position déterminées par rapport aux émetteurs de radiophareRécepteurs travaillant avec ces systèmes
26.
METHOD FOR THE TRANSMISSION OF ADDITIONAL DATA ALONG WITH NAVIGATION MESSAGES IN A SATELLITE NAVIGATION SYSTEM
The invention relates to a method for transmitting additional data along with navigation messages in a satellite navigation system, a navigation message being a continuous data flow that has a predefined bit rate. Said method comprises the following steps: - a navigation message is structured into several pages for transmitting data according to a predefined page definition (S10), each page having a test sum which is calculated in accordance with the data contained on the page formed according to the predefined page definition; - new pages of the navigation message are formed according to a page definition that differs from the predefined page definition (S12) such that the test sum calculated in accordance with the data contained on the page formed according to the predefined page definition is wrong; and - additional data is transmitted using the newly formed pages (S14).
G01S 1/00 - Radiophares ou systèmes de balisage émettant des signaux ayant une ou des caractéristiques pouvant être détectées par des récepteurs non directionnels et définissant des directions, situations ou lignes de position déterminées par rapport aux émetteurs de radiophareRécepteurs travaillant avec ces systèmes
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.
The invention relates to a method for calibrating an array antenna, comprising generating a test signal by using a pseudo-random sequence assigned to a certain branch, adding the generated test signals in the different branches of the array to a useful signal, which leads to a summed signal to be emitted via the array antenna, receiving the summed signal with a receiver antenna, correlating the received summed signal with a replica of the pseudo-random sequence identical to this used for the generation of the test signal, estimating the characteristics of the branch by processing the correlation result, and calibrating the antenna based on the estimated characteristics.
H01Q 3/26 - Dispositifs pour changer ou faire varier l'orientation ou la forme du diagramme de directivité des ondes rayonnées par une antenne ou un système d'antenne faisant varier la phase relative ou l’amplitude relative et l’énergie d’excitation entre plusieurs éléments rayonnants actifsDispositifs pour changer ou faire varier l'orientation ou la forme du diagramme de directivité des ondes rayonnées par une antenne ou un système d'antenne faisant varier la distribution de l’énergie à travers une ouverture rayonnante
A coaxial valve for regulating and blocking a liquid or gaseous medium is described. Said coaxial valve comprises a valve housing (1) which has at least one inlet opening (E) and one outlet opening (A) and also a flow duct which connects said inlet opening (E) and outlet opening (A) to one another. A tubular valve sleeve (2) is provided in an axially movable manner in a section of the flow duct, and has an inflow opening and an outflow opening for the medium, which inflow opening and outflow opening both open out into the flow duct. A closure body (3) is provided in the valve housing (1), which closure body (3) is arranged coaxially with respect to the valve sleeve (2) and is designed to close off the inflow opening of the valve sleeve (2). Also provided is a drive (4) for axially moving the valve sleeve (2), with the drive (4) being formed by an electric actuating motor and by a transmission part (8), which is coupled between the actuating motor and the valve sleeve (2), for transmitting an axial movement to the valve sleeve (2). The transmission part (8) is formed by a drive sleeve (9), which is coaxial with respect to the valve sleeve (2), with a driver (10) which is arranged thereon and which can be placed in engagement with the valve sleeve (2) in order to move the valve sleeve (2) in a first direction. Also provided is a spring pack (12) which is coaxial with respect to the valve sleeve (2) and which acts in the axial direction and which is supported on the drive sleeve (9) and on the valve sleeve (2) in order to move the valve sleeve (2) in a second direction which is opposite to the first direction.
F16K 1/12 - Soupapes ou clapets, c.-à-d. dispositifs obturateurs dont l'élément de fermeture possède au moins une composante du mouvement d'ouverture ou de fermeture perpendiculaire à la surface d'obturation à corps de soupape profilé autour duquel le fluide s'écoule quand la soupape est ouverte
F16K 31/04 - Moyens de fonctionnementDispositifs de retour à la position de repos électriquesMoyens de fonctionnementDispositifs de retour à la position de repos magnétiques utilisant un moteur
The invention relates to a satellite constellation composed of a master satellite and one or more slave satellites, where at least one of the control circuits required by the slave satellite is closed by the master satellite.
B64G 1/10 - Satellites artificielsSystèmes de tels satellitesVéhicules interplanétaires
B64G 1/24 - Appareils de guidage ou de commande, p. ex. de commande d'assiette
B64G 1/28 - Appareils de guidage ou de commande, p. ex. de commande d'assiette par inertie ou par effet gyroscopique
B64G 1/36 - Appareils de guidage ou de commande, p. ex. de commande d'assiette par des capteurs, p. ex. par des capteurs solaires, des capteurs d'horizon
G05D 1/08 - Commande de l'attitude, c. à d. élimination ou réduction des effets du roulis, du tangage ou des embardées
B64G 1/32 - Appareils de guidage ou de commande, p. ex. de commande d'assiette par le champ magnétique terrestre
B64G 1/64 - Systèmes pour réunir ou séparer des véhicules spatiaux ou des parties de ceux-ci, p. ex. aménagement pour l'accostage ou l'amarrage
31.
Tank with a gas extraction device for storing cryogenic liquid or fuel for spacecraft
A tank arrangement includes a tank for storing a liquid such as fuel or oxidizer for operation of a spacecraft and a pressurized driving gas for conveying the liquid out of the tank, and a gas supply and extraction device. The device includes a housing shell and plural outwardly expanding passage bodies providing openings that communicate the interior space of the tank to the inner reservoir space of the device. A baffle plate shields the outer opening of each passage body. Deflector plates are arranged in each passage body. Capillary plates extend longitudinally along the inner wall of the housing shell. By a capillary effect, the plates separate liquid from gas entering the device, so that the gas can be extracted while the liquid is stored in a reservoir of the device until it is drained back into the tank during an accelerated operation phase of the spacecraft.
The invention relates to a method for the production of a component, comprising a base body (1) made of ceramic reinforced with carbon fibers, and a protective layer (2) applied to the base body (1). The method according to the invention comprises the following steps: providing the base body (1); applying a first layer (3) to the base body (1), wherein the first layer (3) comprises slip having reactive carbon. Applying a second layer (4) to the first layer (3), wherein the second layer (4) comprises slip having silicon. The application of the layers can be carried out by means of painting/brushing/stopping and immersion techniques, or by means of fully automated spraying apparatuses. Carrying out a thermal treatment, in which the silicon of the second layer (4) is liquefied. The liquid silicon penetrates into the first layer (3), and together with the reactive carbon forms a reaction protective layer (6) from a silicon carbide compound.
The invention relates to a method for detecting defects in a semiconductor component (10), in particular a solar cell or solar cell arrangement, having at least one pn junction (22) in a semiconductor layer of a semiconductor material (16) with an indirect band transition, wherein a voltage (23) for operating the pn junction (22) in the forward direction is applied (70) to the at least one pn junction (22), the radiation behaviour of the semiconductor layer, which is produced by the applied voltage (23), is optically detected (74) at least for partial regions of the semiconductor layer and is automatically examined (76) for essentially one-dimensional changes in intensity in order to detect mechanical defects.
G01N 21/66 - Systèmes dans lesquels le matériau analysé est excité de façon à ce qu'il émette de la lumière ou qu'il produise un changement de la longueur d'onde de la lumière incidente excité électriquement, p. ex. par électroluminescence
G01R 31/26 - Test de dispositifs individuels à semi-conducteurs
34.
METHOD FOR INCREASING THE AVAILABILITY OF A GLOBAL NAVIGATION SYSTEM
Disclosed is a method for increasing the availability of a global navigation system comprising several spacecraft (1, 2,..., 11), each of which transmits data to a terminal (20) in order to determine the position of said terminal (20). In a first step, a plurality of spacecraft (1, 2,..., 11) transmits data to the terminal (20). A first subset encompassing at least one first spacecraft and a second subset encompassing second spacecraft (1, 2,..., 11) are then determined from among the plurality of spacecraft (1, 2,..., 11), the second subset of spacecraft (1, 2,..., 11) being determined from the difference between the plurality of spacecraft (1, 2,..., 11) and the first subset of spacecraft (1, 2,..., 11). Furthermore, the integrity risk is determined exclusively from the data transmitted by the second spacecraft (1, 2,..., 11). The first and the second subset of spacecraft (1, 2,..., 11) are determined such that the integrity risk which is determined from the data transmitted by the second spacecraft (1, 2,..., 11) is optimized, particularly minimized, with respect to the integrity risk determined from the data of all (1, 2,..., 11) of the plurality of spacecraft (1, 2,..., 11).
G01S 1/00 - Radiophares ou systèmes de balisage émettant des signaux ayant une ou des caractéristiques pouvant être détectées par des récepteurs non directionnels et définissant des directions, situations ou lignes de position déterminées par rapport aux émetteurs de radiophareRécepteurs travaillant avec ces systèmes
35.
WAVEGUIDE RADIATOR, ESPECIALLY FOR SYNTHETIC APERTURE RADAR SYSTEMS
The invention relates to a waveguide radiator comprising a slit wave guide (10) in which a plurality of slits (14) are formed, and an additional inner conductor which is applied inside the wave guide (10) and formed in a polarisation-dependent manner in such a way that all of the slits (14) of the wave guide (10) can be excited equally in terms of phase and amplitude.
The invention relates to a method for lossless data compression, comprising the step of producing characteristic tables for predicted intensities as a function of radius values f(i,j) on at least one type of preferred axes using intensity signals of a detector matrix (I(i,,j)). The invention also relates to a device for lossless data compression, used to carry out said method.
Apparatus for measuring the amount of fuel aboard a spacecraft under weightless conditions, including at least one orifice (FL1, FL2), at least one check valve (FLV1, FLV2) for selection of the orifice to be used, at least one control valve (FCV1, FCV2) for releasing a stream of pressurizing gas from at least one high-pressure tank (THe).
F02K 9/50 - Alimentation en propergols utilisant du fluide pressurisé pour mettre les propergols sous pression
B64G 1/40 - Aménagements ou adaptations des systèmes de propulsion
G01F 22/02 - Procédés ou appareils pour la mesure du volume des fluides ou des matériaux solides fluents, non prévus ailleurs comportant un mesurage de pression
G01F 23/14 - Indication ou mesure du niveau des liquides ou des matériaux solides fluents, p. ex. indication en fonction du volume ou indication au moyen d'un signal d'alarme par mesurage de la pression
38.
HIGH TEMPERATURE PRESSURE SENSOR ELEMENT, PARTICULARLY FOR MEASURING PRESSURES INSIDE JET ENGINES, METHOD FOR THE PRODUCTION THEREOF AND COMPONENT FOR JET ENGINES
The invention relates to a high temperature pressure sensor element (10; 20), in particular for jet engines, comprising a substrate (11) with an inner region (12) configured therein, a defomable membrane (13) which separates the inner region (12) from the outer region and deforms during operation in the event of a change of pressure, and a strain gauge element (14a, 14b, 14c) disposed on the membrane (13) for measuring the deformation of said membrane (13). The substrate (11), the membrane (13) and the strain gauge element (14a, 14b, 14c) are all made of the same high temperature stable material, particularly an alloy, such as a nickel-based alloy. A component for a jet engine, such as for example a turbine blade for an aircraft or a rocket engine, comprises such an integrated high temperature pressure sensor element (10; 20).
G01L 9/04 - Mesure de la pression permanente, ou quasi permanente d’un fluide ou d’un matériau solide fluent par des éléments électriques ou magnétiques sensibles à la pressionTransmission ou indication par des moyens électriques ou magnétiques du déplacement des éléments mécaniques sensibles à la pression, utilisés pour mesurer la pression permanente ou quasi permanente d’un fluide ou d’un matériau solide fluent en faisant usage des variations de la résistance ohmique, p. ex. de potentiomètre de jauges de contrainte à résistance
G01L 23/18 - Dispositifs ou appareils pour la mesure ou l'indication ou l'enregistrement des changements, rapides, tels que des oscillations, de la pression des vapeurs, des gaz ou des liquidesIndicateurs pour déterminer le travail ou l'énergie des moteurs à vapeur, à combustion interne ou à autres pressions de fluides à partir de la condition du fluide moteur mis en œuvre électriquement par des jauges de contrainte à résistance
G01L 19/04 - Moyens pour compenser les effets des variations de température
39.
GLOBAL INFORMATION AND HAZARD WARNING SYSTEM USING SATELLITE NAVIGATION SYSTEMS AND USER TERMINALS
The invention relates to a method and devices for a global information and early warning system, based on satellite navigation systems and user terminals, comprising the following steps and devices for carrying out said steps: transmission of at least one warning message about one or more danger zones via a satellite navigation system to user terminals in at least one information coverage region, reception of the at least one warning message by a user terminal in the at least one information coverage region and checking by the user terminal whether the user terminal is affected by the warning message.
G08B 27/00 - Systèmes d'alarme dans lesquels la condition déclenchant l'alarme est signalée par une station centrale à plusieurs sous-stations
G01S 5/00 - Localisation par coordination de plusieurs déterminations de direction ou de ligne de positionLocalisation par coordination de plusieurs déterminations de distance
40.
HIGH-RESOLUTION SYNTHETIC APERTURE RADAR DEVICE AND ANTENNA FOR ONE SUCH RADAR DEVICE
The invention relates to a high-resolution synthetic aperture radar device (10) comprising: at least one emission antenna (TX1-TX3) for generating and emitting radar pulses for scanning an object (12), and a reception antenna (14) for receiving the emitted radar pulse beams (20, 22, 24) reflected off an object, the reception antenna (14) comprising a plurality of sub-apertures (RX1-RX17) which are arranged along the elevation and form a minimum number of azimuthal apertures. The high-resolution synthetic aperture radar device is embodied in such a way that pulse signals (18) are emitted at irregular time intervals.
G01S 13/90 - Radar ou systèmes analogues, spécialement adaptés pour des applications spécifiques pour la cartographie ou la représentation utilisant des techniques d'antenne synthétique
41.
HIGH-FREQUENCY MEASURING HALL FOR MEASURING LARGE TEST OBJECTS
Disclosed is a high-frequency measuring hall for measuring large test objects. Said measuring hall is composed of an air-supported membrane structure or textile structure which has a spherical or elliptic contour and is largely permeable to electromagnetic radiation and in which the floor is covered with absorber material in order to absorb the electromagnetic radiation reflected by the inner side of the surface. The structure and the material used, which is largely permeable to electromagnetic waves, make it possible to create a structure that is less expensive than conventional hall structures, allowing a substantial reduction of the amount of absorber material used.
The invention relates to an assembly for determining the position and orientation of a flying object (12, 14), in particular a flying object in space. Said assembly comprises a ground segment (16), which has at least one pseudolite station (18) that is located on the earth's surface and transmits a navigation signal (20), uniquely identifying said pseudolite station, into space and a user segment that comprises at least one sensor (46) that is situated in the flying object (12, 14). The sensor is configured to receive the navigation signal (20) of the pseudolite station or stations (18) and to determine its absolute position and orientation in space using the received navigation signal (20).
B64G 1/36 - Appareils de guidage ou de commande, p. ex. de commande d'assiette par des capteurs, p. ex. par des capteurs solaires, des capteurs d'horizon
G01S 1/00 - Radiophares ou systèmes de balisage émettant des signaux ayant une ou des caractéristiques pouvant être détectées par des récepteurs non directionnels et définissant des directions, situations ou lignes de position déterminées par rapport aux émetteurs de radiophareRécepteurs travaillant avec ces systèmes
brevets
