| Astrium GmbH Patent applications |
| Patent application number | Title | Published |
|---|
| 20120044104 | Device and Method for Three-Dimensional Positioning - 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. | 02-23-2012 |
| 20120039599 | METHOD AND SYSTEM FOR TRACKING TWO COMMUNICATIONS PARTICIPANTS OF AN OPTICAL SATELLITE COMMUNICATIONS SYSTEM - Method and system for tracking between two communications participants of an optical satellite communications system to provide a communication connection between the two communications participants. The method includes transmitting a signal from a first of the two communications participants to a second of the two communications participants, in which the second communications participant includes a detector arrangement with a plurality of detectors in a common receiving plane. The method also includes acquiring a phase of the signal at each of the plurality of detectors and determining phase differences between the phases via a phase-processor, determining from the phase differences a phase angle of an alignment of the signal to the receiving plane, processing the phase angle with a tracking computer in order to align the receiving plane of the second communications participant with the signal, whereby the phase difference becomes zero, and continuously calibrating the plurality of detectors of the detector arrangement. | 02-16-2012 |
| 20120038511 | COMPUTING OF ROBUST AND IMPROVED SIGNAL-IN-SPACE ACCURACY PARAMETERS IN A REGIONAL OR GLOBAL NAVIGATION SATELLITE SYSTEM - Method, computer program to implement method, storage medium to store the program and apparatus for computing Signal-in-Space Accuracy (SISA) parameters in a regional or Global Navigation Satellite System (GNSS). The method includes at least of: determining individual Signal-in-Space Error (SISE) vectors; mapping individual SISE vectors to a service area; accumulating empirical sample sets; processing density functions of estimations of accumulated sample sets; individually overbounding density functions in one of an overbounding sense related to the regional or GNSS or in a paired overbounding with excess mass sense; and selecting a worst case according to predefined requirements. | 02-16-2012 |
| 20120026035 | Method for Resolving Sub-Carrier Ambiguities of a Number of Tracking Channels of a Navigation Signal - A method for resolving sub-carrier ambiguities of a total number of tracking channels of a binary offset carrier (BOC) navigation signal is provided. For a simultaneously considered subset of at least four tracking channels, a set of sub-carrier candidate ambiguities is determined based on the sub-carrier modulation. Position and receiver clock error are calculated for each possible combination of sub-carrier ambiguities. Predicted delays are calculated based on each calculated position and receiver clock error. Differences between the predicted delays and the delay candidates originating from each specific combination of subcarrier ambiguities are calculated. A residual is calculated based on the differences and the set of sub-carrier ambiguities and the corresponding position and receiver clock error leading to the smallest residual are selected. | 02-02-2012 |
| 20120019411 | Integrity Method for Differential Corrections - A system and method of calculating corrections to a navigation solution based on accurate data are provided. GNSS ephemeris, clock models and other navigation information are received from at least three GNSS satellites and pseudo-ranging to the GNSS satellites is performed. A PVT solution is resolved from the GNSS ephemeris, clock models, and other navigation information and the pseudo range measurements. The PVT solution includes a statistical measure. Differential GNSS data for calculating the corrections to the PVT solution is received and a corrected PVT solution is calculated based upon the differential GNSS data. The corrected PVT solution is compared to a region defined by the statistical measure and the corrected PVT solution is rejected when the corrected PVT solution is not within the region. | 01-26-2012 |
| 20120019143 | Plasma Generator and Method for Controlling a Plasma Generator - A plasma generator having a housing surrounding an ionization chamber, at least one working-fluid supply line leading into the ionization chamber, the ionization chamber having at least one outlet opening, at least one electric coil arrangement which surrounds at least one area of the ionization chamber, the coil arrangement being electrically connected with a high-frequency alternating-current source (AC) which is constructed such that it applies a high-frequency electric alternating current to at least one coil of the coil arrangement, is wherein a further current source (DC) is provided which is constructed such that it applies a direct voltage or an alternating voltage of a frequency lower than that of the voltage supplied by the high-frequency alternating current source (AC) to at least one coil of the coil arrangement. | 01-26-2012 |
| 20120012766 | COAXIAL VALVE WITH AN ELECTRIC DRIVE - A coaxial valve for regulating and blocking a liquid or gaseous medium having a valve housing having at least one inlet opening, at least one outlet opening and a flow duct connecting the at least one inlet opening to the at least one outlet opening; a tubular valve sleeve disposed in an axially movable manner in a portion of the flow duct and having an inflow and an outflow opening for the medium, wherein the inflow and the outflow openings open into the flow duct; a closure member disposed in the valve housing and arranged coaxially with the valve sleeve and configured to close the inflow opening; and a drive configured to axially move the valve sleeve and having an electric servomotor and a transmission part coupled between the servomotor and the valve sleeve, the transmission part configured to transmit an axial movement to the valve sleeve. | 01-19-2012 |
| 20120004092 | Method for Regenerating an Adsorber or Absorber - A method for regenerating an adsorber or absorber on board a submarine, wherein the adsorber or absorber is present in the interior of the submarine for binding metabolically generated CO | 01-05-2012 |
| 20120001810 | METHOD AND DEVICE FOR CALIBRATING AN ARRAY ANTENNA - A method for calibrating an array antenna having a plurality of branches includes generating a test signal using a pseudo-random sequence assigned to one of the plurality of branches for each of the plurality of branches; adding the test signals to a useful signal of the antenna so as to form a summed signal 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 so as to produce a correlation result; estimating a characteristic of one of the plurality of branches by processing the correlation result; and calibrating the antenna based on the estimated characteristic. | 01-05-2012 |
| 20110316737 | RAIM Algorithm - Methods and apparatus for implementing a receiver autonomous integrity monitoring (RAIM) algorithm are provided. The RAIM algorithm is for determining an integrity risk in a global navigation satellite system (GNSS) by processing several ranging signals received from satellites of the GNSS. The algorithm involves determining several integrity risks at an alert limit for different fault conditions of the ranging signals, and determining an overall integrity risk at the alert limit from the determined several integrity risks. | 12-29-2011 |
| 20110309200 | Apparatus, Satellite and Method for Trapping High-Speed Particles - An apparatus for trapping high-speed particles, such as space debris, is provided. The apparatus includes a first front tapping surface and at least one rear trapping surface. The front and rear trapping surfaces are arranged substantially parallel to each other and are spaced apart from each other in the normal direction. | 12-22-2011 |
| 20110277444 | Ion Drive for a Spacecraft - An ion drive for a spacecraft, including a high-frequency generator for generating an alternating electromagnetic field for the ionization of a propellant and an acceleration system for the charge carriers, is provided. The ion drive includes a voltage source with which the high voltages that are necessary for the acceleration system can be derived from the currents and/or voltages generated by the high-frequency generator for generating the alternating electromagnetic field. | 11-17-2011 |
| 20110255772 | Method for Screening of Multi-Junction Solar Cells - A method for screening of multi-junction solar cells to be operated in a high sun intensity and high temperature (HIHT) environment. An electroluminescence image of a homogeneous pn-junction at a predefined bias current is acquired for each of the solar cells. The spatial intensity distribution in the electroluminescence image is analyzed to determine whether there are local intensity variations that possibly dissipate power in a HIHT environment. The solar cells are sorted such that solar cells having no local intensity variations in their electroluminescence image are put into a first group and solar cells having at least one local intensity variation in their electroluminescence image are put into a second group cells for further screening. The solar cells of the first group are suitable for a HIHT environment and solar cells of the second group are assumed to be potentially critical in a HIHT environment. | 10-20-2011 |
| 20110254640 | Diplexer for a Reflector Antenna - A diplexer for a reflector antenna includes a common circular signal waveguide to transmit and receive signals. The signal waveguide includes first and second ends with a common port provided at the first end. A waveguide arrangement is disposed coaxially relative to the signal waveguide in the region of the second end of the signal waveguide. A cylindrical coupler section is disposed between the first and second ends of the signal waveguide, and connects the waveguide arrangement to the common signal waveguide. In order to create a first and second coaxial waveguide port, the waveguide arrangement includes a first circular waveguide, an inner conductor is disposed inside, in which a first signal can propagate when the diplexer is operating, and a second circular waveguide, surrounding the first waveguide, in which a second signal can propagate at a lower frequency than the first signal when the diplexer is operating. | 10-20-2011 |
| 20110232733 | Multi-Junction Solar Cell For Space Applications - A multi-junction solar cell includes a first main surface and a second main surface opposite to the first main surface of a semiconductor body. A topmost pn-junction of a plurality of pn-junctions stacked on top of each other adjoins to the first main surface. A cell edge of the semiconductor body defines a shape of the first and the second main surfaces. An encapsulant on the first main surface provides an environmental protection of the semiconductor body. A mesa groove is provided on the first main surface and penetrates at least the topmost pn-junction. The mesa groove is located adjacent to the cell edge and is created around the circumference of the semiconductor body for providing an inner cell area and a mesa wall, the mesa wall being created between the mesa groove and the cell edge. The mesa groove is filled with the encapsulant. | 09-29-2011 |
| 20110221868 | Information Reproducing Apparatus - An information reproducing apparatus includes a display unit and processing unit. The information reproducing apparatus has a position determining device configured to determine the position and alignment of the apparatus and to supply a first signal representing the position and a second signal representing the alignment to the processing unit. The processing unit retrieves information on objects from a database and processes the information. The database includes a plurality of information on objects of locations within a predefined spatial environment. The processing unit determines information for the current alignment of the apparatus on objects in the direction of the alignment of the apparatus and the display unit displays the information. | 09-15-2011 |
| 20110198446 | Device for Eliminating Space Debris in Orbit - A device for eliminating space debris in orbit, the device including a covering that when struck by an object of space debris breaks this up into multiple pieces of predetermined size, and captures and binds at least many of the pieces. The covering includes at least one layer of deformable fabric that encloses a spatial volume of the device, wherein a foam material is disposed inside the at least one layer for the purpose of retaining shape, the initial volume of the foam material being able to be changed into a final volume that is larger relative to the initial volume, wherein the device has its specified shape and function once the foam material attains its final volume. | 08-18-2011 |
| 20110192936 | Towing Apparatus for a Spacecraft when in Orbit and a Towing Spacecraft - 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. | 08-11-2011 |
| 20110192137 | Method for Manufacturing a Regeneratively Cooled Nozzle Extension of a Rocket Combustion Chamber and Nozzle Extension - A method for manufacturing a regeneratively cooled nozzle extension of a rocket combustion chamber, the nozzle extension including a first wall and a second wall arranged coaxially to each other and between which a number of cooling channels is configured that are laterally delimited by cooling channel webs. The first wall and the second wall are connected to each other by a positive fit by cooling channel webs of the first wall engaging with corresponding recesses of the second wall for forming the positive fit. The positive fit is produced by a forming process in the region of the cooling channels of the second wall having the recesses. | 08-11-2011 |
| 20110187594 | Method for Self-Calibration of Frequency Offsets - A method for self-calibration of frequency offsets in a measurement equipment of an interference monitoring system is provided. The method involves sampling I/Q data using the interference monitoring system measurement equipment and acquiring satellite navigation signals from the I/Q data. A carrier frequency of the satellite navigation signal is estimated and an expected carrier frequency of the satellite navigation signal is calculated. The expected carrier frequency of the satellite navigation signal is compared with the estimated carrier frequency of the satellite navigation signal and a frequency offset value is calculated as the difference between the expected and estimated carrier frequencies of the satellite navigation signal. The frequency offset value is stored in a memory and used to compensate the frequency offset of at least one subsequent measurement. | 08-04-2011 |
| 20110169693 | INTEGRITY COMMUNICATION IN A SATELLITE NAVIGATION SYSTEM - Embodiments of the invention are directed to a method for integrity communication in a satellite navigation system having a space segment with several satellites transmitting navigation signals for reception and evaluation by use systems for position determination, and a ground segment with several observation stations that, in their totality, monitor the satellites and their signals, and including at least one transmitting station. The method includes detecting errors that one of have or could have occurred in a determination of a pseudo-range between the satellites and the observation stations and could influence the integrity of the satellite navigation system, forming, from the detected errors, three error budgets for respectively different categories of errors that one of have or could have occurred in the determination of the pseudo-range between the satellites and the observation stations, transmitting the three error budgets one of per ground station or for a group of ground stations with a navigation signal of at least one satellite to the use systems, and receiving the navigation signal and estimating the integrity of the satellite navigation system by evaluating the error budget contained in the received navigation signal | 07-14-2011 |
| 20110157731 | Mirror Module For Fastening to a Structural Element - A mirror module for fastening to a structural element, comprises a mirror arrangement that includes at least one mirror stack and a first receiving device for holding the mirror arrangement. Each of the at least one mirror stack comprises at least one individual mirror made of a first material. The first receiving device is made of a second material which has a coefficient of thermal expansion adapted to the first material. For fastening the mirror module to the structural element, a second receiving device made of Invar is provided which holds the first receiving device of the mirror module. | 06-30-2011 |
| 20110120271 | SCREW PRESTRESSING DEVICE AND METHOD - A screw prestressing device having a piston and a draw pin structured and arranged to be disconnectably coupled to an element and movable, via the piston, to apply a defined prestressing force in the element. | 05-26-2011 |
| 20110115683 | High-Frequency Measurement Setup and Method for Measuring a High-Frequency Test Object - 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. | 05-19-2011 |
| 20110102277 | Method and Device for Measuring a Radiation Field - 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. | 05-05-2011 |
| 20110038440 | Process for Receiving a Signal and a Receiver - A process for receiving a GMSK-modulated signal which, for simultaneously transmitting two services, has an in-phase signal with a pseudo-random code that differs from the quadrature signal. By means of a decomposition filter in a reference signal branch detects one service independently of the other during the correlating with the received signal. | 02-17-2011 |
| 20110037651 | Method of Amending Navigation Data of a Global Navigation System - For amending navigation data of a global navigation system, navigation signals are received from a space vehicle, and a predicted clock phase offset of the clock signal sent from the space vehicle is estimated and stored in a memory. The clock phase offset difference between the current estimated clock phase offset and a previously estimated clock phase offset times (T | 02-17-2011 |
| 20110022309 | Method for Determining the Position of a Spacecraft with the Aid of a Direction Vector and an Overall Spin Measurement - In a system for determining the position of a spacecraft based on vector determinations, a direction vector is measured in a body-fixed coordinate system; a reference direction vector is determined within a reference coordinate system based on the path position of the spacecraft and an orbit model; the overall spin vector of the spacecraft is determined within the body-fixed coordinate system; and a reference overall spin vector of the spacecraft is determined within a reference coordinate system by time propagation of known initial values of the overall spin of the spacecraft or by time tracking of a reference model. The position of the spacecraft is determined based on the four vectors. | 01-27-2011 |
| 20100289696 | Method and device for estimation of the integrity risk in a satellite navigation system - A method for estimating an integrity risk in a satellite navigation system includes receiving a plurality of navigation signals at a user system from at least one satellite, the plurality of navigation signals including data relative to the integrity of the satellite navigation system; and estimating the integrity risk using the data in the at least one user system. The estimating further includes forming a plurality of intervals of an integration variable of an integral function, estimating a maximum of the integrity risk for each interval, comparing the maximum of each interval to find an overall maximum of all the intervals; and using the overall maximum as an estimate of the integrity risk. | 11-18-2010 |
| 20100271262 | METHOD AND ARRANGEMENT FOR MEASURING THE DIRECTIONAL CHARACTERISTIC OF AN ANTENNA TO BE TESTED - A method of measuring a directional graph of a test antenna includes disposing a plurality of measuring probes relative to the test antenna, each being disposed at a different first predetermined height above a reference plane; disposing the test antenna at a second predetermined height above the reference plane; measuring transmission characteristics relative to the test antenna between each of the plurality of measuring probes and the test antenna; determining prevailing scatter characteristics of the reference plane; and determining the directional graph of the test antenna using the prevailing scatter characteristics. | 10-28-2010 |
| 20100271101 | Master Clock Generation Unit for Satellite Navigation Systems - 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. A frequency generator having an input connected to the first matrix output and connected to a number of frequency outputs of the master clock generation unit, derives an output reference frequency from the primary clock, and provides it at the frequency outputs. A phase meter having a first meter input connected to the first matrix output and a second meter input connected to the second matrix output, determines a phase difference between the primary and the secondary clock for detecting abnormal behavior. | 10-28-2010 |
| 20100265136 | METHOD FOR THE TRANSMISSION OF ADDITIONAL DATA ALONG WITH NAVIGATION MESSAGES IN A SATELLITE NAVIGATION SYSTEM - A method for transmitting additional information in a satellite navigation system includes providing a navigation message including a continuous data stream having a prescribed bit rate and structuring the navigation message in a plurality of pages generated according to a prescribed page definition so as to transmit information, wherein each of the plurality of pages includes a checksum calculated as a function of information contained in the page. The method further includes generating at least one new page containing the additional information so as to form a changed, navigation message according to a further page definition that differs from the prescribed page definition such that the checksum calculated as a function of information contained on the page generated according to the prescribed page definition is false; and transmitting the at least one new page. | 10-21-2010 |
| 20100265132 | Method of Amending Navigation Data of a Global Navigation System - In a method for reducing the adverse effect of clock frequency jumps on a user-position determination device in a global navigation system, a plurality of space vehicles each having a clock, transmit position determination information to the position determining device. If a sufficient number of such navigation signals from a first group of space vehicles having clocks in which no jump occurs are available for this purpose, and if a calculated integrity risk is acceptable, position determination is performed using those navigation signals. If not, however, the position determination device receives navigation signals from space vehicles of a second group with clocks in which jumps can occur. The latter signals are combined with signals from the first group in a manner which takes into account possible jumps, and the process is repeated. | 10-21-2010 |
| 20100262369 | METHOD FOR THE TRANSMISSION OF ADDITIONAL DATA ALONG WITH NAVIGATION MESSAGES IN A SATELLITE NAVIGATION SYSTEM - 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 | 10-14-2010 |
| 20100247234 | System for Precisely Adjusting the Space Between Two Elements - A device for precisely adjusting the space between two elements includes a connection member that mutually connects the first element and the second element, a first space adjusting member, and a second space adjusting member. The first space adjusting member has a first thread that interacts with an assigned counterthread of one of the elements, and the second space adjusting member has a second thread that interacts with an assigned counterthread of the first space adjusting member or of the other of the elements. The first thread and the second thread have different thread pitches. | 09-30-2010 |
| 20100194598 | Arrangement for Transmitting Information Concerning an Operating Condition of a Vehicle - An arrangement for transmitting information concerning an operating condition of a vehicle, such as an aircraft or spacecraft, exerts tactile stimuli as information via a stimulus generator on at least one operator of the vehicle. The stimulus is exerted on a sense organ or body part of the operator that is not used for active transmission of information during trouble-free and proper operation of the vehicle. | 08-05-2010 |
| 20100170223 | CONTROL AND/OR DRIVE DEVICE FOR A FLYING BODY - Control and/or drive device for a flying body for ejecting hot gas streams of a combusted fuel combination of at least a first and second component. Device includes a first hollow chamber body structured and arranged to contain first component, a second hollow chamber body structured and arranged to contain second component, a controllable fuel valve arranged between first hollow chamber body and second hollow chamber body to control feed of first component to second hollow chamber body, and a plurality of outlets structured and arranged to eject respective hot gas streams for influencing a flight path of flying body. Second hollow chamber body is formed as a combustion chamber for combusting the at least first and second components within second hollow chamber body to generate respective hot gas streams, and plurality of outlets are connected to the second hollow chamber body. | 07-08-2010 |
| 20100156720 | Method and Apparatus for Optimizing the Accuracy of Position Determination and Reducing the Integrity Risk of a Receiver in a Global Satellite Navigation System - In a method for optimizing the accuracy of position determination, and/or for reducing the integrity risk, of a receiver in a global satellite navigation system having a plurality of satellites, for at least one satellite that is visible to the receiver (E), a deviation error (AF) is determined which is a function of the geometric orientation of the satellite relative to the receiver, and of at least one system parameter. The deviation error is determined based on an additional deviation error generated by an error projection into a coordinate system of the receiver. A first or a second value, whichever is smaller of the two, is used as the deviation error. The first value for the at least one system parameter is determined using a respective specified parameter value. The second value is determined for the at least one system parameter, using a modified parameter value which is modified with respect to the specified parameter value in such a way that a lower error in the modified parameter value of the at least one system parameter is accepted as true. | 06-24-2010 |
| 20100150428 | METHOD AND APPARATUS FOR DETECTING MECHANICAL DEFECTS IN A SEMICONDUCTOR DEVICE, PARTICULARLY IN A SOLAR CELL ARRANGEMENT - A process detects defects in a semiconductor device, particularly a solar cell or solar cell arrangement, having at least one pn junction in a semiconductor layer of a semiconductor material with an indirect band junction. A voltage is applied to the at least one pn junction to operate it in the transmitting direction; and the radiation behavior of the semiconductor layer generated by the applied voltage, at least for partial ranges of the semiconductor layer, is optically detected and automatically examined for essentially one-dimensional intensity changes in order to detect mechanical defects. | 06-17-2010 |
| 20100146934 | Hot Gas Chamber - A hot gas chamber, such as a combustion chamber for a power unit for the discharge of a hot gas flow, particularly for a rocket propulsion unit, has a combustion chamber wall, which has an internal surface and cooling ducts adjoining the latter. The internal surface of the combustion chamber wall facing the combustion chamber is further developed at least in areas for avoiding a film condensation. | 06-17-2010 |
| 20100141512 | Method and Apparatus for Integrity Communication in a Navigation Satellite System - For integrity communication, a navigation satellite system has a space segment with satellites that emit navigation signals for reception and analysis by user systems, and a ground segment with observation stations that monitor the satellites. The ground segment controls cause distribution of integrity information concerning the satellites to user systems with the navigation signals. The integrity information has a first SISMA value and a second broadcast SISMA value for the accuracy of the satellite monitored by the ground segment. The second broadcast SISMA value takes into account a failure of an observation station of the ground segment, and a threshold value for the second broadcast SISMA value is provided. The threshold value with the integrity information for a satellite is transmitted instead of the second broadcast SISMA value when the latter exceeds the threshold value and the first SISMA value is lower than the threshold value for the satellite. The integrity information to be transmitted when the second broadcast SISMA value and the first SISMA value for the satellite each exceed the threshold value. | 06-10-2010 |
| 20100141511 | Method for Increasing the Availability of a Global Navigation System - A process for increasing the availability of a global navigation system that includes a plurality of spacecraft, each of which transmits information for determining the position of a terminal. From the plurality of spacecraft, a first subset, with at least one spacecraft, and a second subset are determined. the second subset being constituted by those spacecraft that are not included in the first subset. The integrity risk is determined for the information transmitted only by the second spacecraft. The first and the second subsets of spacecraft are determined such that the integrity risk, for information transmitted by the second subset spacecraft minimized relative to the integrity risk for information of all spacecraft included in the plurality of spacecraft. | 06-10-2010 |
| 20100091820 | Position Indicating Process - A position indicating process includes the steps of receiving at least four radio signals emitted by different transmitter stations; determining a channel pulse response of the transmission channel for each of the received radio signals; estimating the direct signal path for each of the received radio signals based on the respectively determined channel pulse response; and determining the receiving position of the radio signals by evaluating the estimated direct signal paths of the received radio signals. | 04-15-2010 |
| 20100079340 | METHOD AND DEVICE METHOD FOR DETECTING FREQUENCY JUMPS OF A NAVIGATION SATELLITE'S MASTER CLOCK - A method for detecting frequency jumps of a navigation satellite's master clock, comprising the steps of i) monitoring the master clock signal that is generated by a master clock onboard of the satellite for a frequency jump, and ii) signaling a detected frequency jump of the master clock signal, | 04-01-2010 |
| 20100066623 | WAVEGUIDE RADIATOR, ESPECIALLY FOR SYNTHETIC APERTURE RADAR SYSTEMS - The invention relates to a waveguide radiator comprising:
| 03-18-2010 |
| 20100052979 | METHOD AND APPARATUS FOR THE OPTIMIZATION OF STATUS MESSAGES IN A SATELLITE NAVIGATION SYSTEM - In a method for optimization of status messages in a satellite navigation system, which comprises a space segment having a plurality of satellites that emit navigation signals to be received and evaluated by utilization systems for position determination, and a ground segment having a plurality of observation stations that monitor the satellites, a threshold value is determined, as a function of location, for a message indicating that the error of a satellite is no longer acceptable. | 03-04-2010 |
| 20100052816 | Signal Branch for Use in a Communication System - A signal branch for use in a communication system, in particular in a reflector antenna, for the transmission of microwave signals is provided. The signal branch includes a common signal wave guide for transmitting a transmission signal and a received signal that has one first end and one second end as well as an exterior and interior. Moreover, a plurality of transmission signal wave guides is provided for feeding the transmission signal, with the transmission signal wave guides being disposed on the exterior of the common signal wave guide in a symmetrically distributed manner and each being communicatively connected to the common signal wave guide. A plurality of receiver signal wave guides is provided for transmitting the received signal, with the receiver signal wave guides being symmetrically adjacent to the second end of the common signal wave guide and each being communicatively connected to the common signal wave guide. | 03-04-2010 |
| 20100033369 | Method and Apparatus for Determining an Integrity Risk in a Satellite Reference System - Methods and apparatus of determining an integrity risk of a satellite reference system are provided. Galileo parameters according to the Galileo integrity concept are detected. The Galileo parameters are imaged onto satellite based augmentation system (SBAS) parameters used in the SBAS. The integrity risk of the satellite reference system is determined according to the SBAS integrity concept using the SBAS parameters. | 02-11-2010 |
| 20100023256 | Process for Automatically Determining a Bypass Route - A navigation system automatically determines one or more bypass routes for a vehicle, based on a continuously determined vehicle position, according to a process having the following steps: receiving data concerning a hindrance in a region in the proximity of a current position; automatically determining one or more destinations which can be reached via the region affected by the hindrance; automatically determining additional regions via which the determined destinations can be reached; calculating an evaluation factor for each of the determined additional regions; and automatically determining one or more routes for bypassing the region affected by the hindrance, based on the evaluation factor. | 01-28-2010 |
| 20100019961 | Method and Apparatus for Operating a Navigation Satellite System - Operation of a satellite navigation system utilizes a method of generating a sufficiently smooth and very flexible parameterization of satellite orbits and/or satellite clock corrections of a satellite. For description of the satellite orbit(s) and/or of the satellite clock corrections, a first system of advancing differentiable functions (first function system) is provided which has a high approximation quality and a long range of influence. The satellite orbits and/or satellite clock corrections parameterized from the first function system are transmitted from a central ground processing unit to one or more satellites and then to a user device. (Alternatively, the transmission may take place without utilizing the space segment, via only a ground infrastructure.) In addition, a second advancing system (second function system) of at least continuous functions of a moderate approximation quality and a very short range of influence may be provided, which, particularly by means of the user terminal, permits a conversion to the first function system. As a result, the time required to determine the first navigation information (the time to the first fix) can be significantly shortened. | 01-28-2010 |
| 20100017051 | Method of Automatically Determining a Landing Runway - A method of automatically determining a landing runway for an aircraft includes the steps of i) determining control points assigned to a landing runway along a landing approach of an airplane; ii) determining the spatial deviation of the airplane from the determined control points; and iii) determining an appropriate landing runway while taking into account the determined spatial deviation. | 01-21-2010 |
| 20100013611 | Method and Apparatus for Informing a User of the Position of an Information Source Relative to the User Position - In a process for informing a user regarding the position of an information source relative to the user's position, the position of an information source is first determined relative to the user. Thereafter, a tactile or electrical stimulus is generated, for directly affecting the user in a location that corresponds to the determined position of the information source. In one embodiment of the invention, tactile or electrical actuators are disposed at locations within a garment, such as a pilot's uniform at locations which correspond to possible locations of the information source. | 01-21-2010 |
| 20100011850 | Method and Apparatus for Measuring the Amount of Fuel Aboard a Spacecraft - A method and apparatus for measuring the amount of fuel aboard a spacecraft under weightless conditions utilize at least one orifice, at least one flow latch valve for the selection of an orifice to be used, and at least one control valve for releasing a stream of a pressurizing gas from at least one high-pressure tank in order to restore pressure in a fuel tank following a pressure reduction due to withdrawal of fuel. The amount of fuel remaining in the fuel tank is determined based on the time required to restore fuel tank pressure bv a flow of gas from the high pressure tank to the fuel tank, via the orifice. | 01-21-2010 |
| 20100008611 | Arrangement for Holding a Bearing System - An arrangement for force-free retention of a bearing system having an axis of rotation comprises a cylindrical hollow axle for concentrically receiving and holding the bearing system. By means of a hold-down and release mechanism a bearing shell can be fastened to the hollow axle in such a manner that when the bearing system is not acted upon by a load, all lateral and axial forces applied to the arrangement can be transmitted via the cylindrical hollow axle into axle receiving devices. | 01-14-2010 |
| 20090322602 | INTEGRATED POSITIONING SOLUTION FOR GLOBAL NAVIGATION SATELLITE SYSTEMS - The invention includes a process for one's own global navigation satellite system and at least one other global navigation satellite system including the following: Receiving ranging signals and navigation messages or ranging signals only from the at least one other global navigation satellite system, and processing the received ranging signals and navigation messages in a similar way as the ranging signals and navigation messages of the owned global navigation satellite system. | 12-31-2009 |
| 20090322515 | DISSEMINATION OF CRITICAL ATMOSPHERIC CONDITIONS WITHIN GLOBAL AND REGIONAL NAVIGATION SATELLITE SYSTEMS - The invention relates to an apparatus for a regional or global navigation satellite system that includes an arrangement for receiving additional data or navigation messages from the navigation satellite system, and an arrangement for informing or alarming the user that critical atmospheric conditions occur, whereby the additional data or the navigation messages include atmospheric information. | 12-31-2009 |
| 20090310877 | Lossless Compression Process for Interferograms - A process and apparatus for lossless data compression including the step of generating characteristic tables for predicted intensities as a function of radius values f(i,j)) on at least one type of preferred axes. Intensity signals of a detector matrix (I(i,j)) are used to implement the invention. | 12-17-2009 |
| 20090308451 | ARRANGEMENT FOR THE INDIRECT INTENSITY-SELECTIVE ILLUMINATION OF SOLAR CELLS - An arrangement and method for illumination of solar cells. The arrangement includes at least one mirror with at least one predetermined surface geometry and at least one solar cell. The at least one predetermined surface geometry is structured and arranged to distribute primary radiation striking the at least one mirror in one of a targeted manner and homogenously on the at least one solar cell. | 12-17-2009 |
| 20090303614 | APOCHROMATIC LENS - An apochromatic lens with an aperture and exclusively refractive optical elements, comprising a plurality of lenses arranged in lens groups along an optical axis, wherein lenses of different materials are provided and wherein the lenses respectively comprise one of the following listed materials: calcium fluoride (CaF | 12-10-2009 |
| 20090295625 | Method for Optimizing the Operation of an Active Lateral-View Sensor When the Height Above the Surface to be Detected is Variable - A process for optimizing the operation of an active lateral-view sensor when the height above the surface to be detected is variable, includes the following steps: i) continuously determining the height of the lateral-view sensor above the surface to be detected, and ii) adjusting the scanning beams emitted by the lateral-view sensor for scanning the surface to be detected by roll rotation as a function of the determined height of the lateral-view sensor such that variation of the surface to be detected is reduced during the orbit of the lateral-view sensor. | 12-03-2009 |
| 20090293937 | DEVICE FOR THE INDIRECT FREQUENCY-SELECTIVE ILLUMINATION OF SOLAR CELLS - Apparatus, satellite, and method for illumination of at least one solar cell. Apparatus includes at least one solar cell and at least one optical device structured and arranged for an indirect frequency-selective illumination of the at least one solar cell. The at least one optical device reflects spectral components relevant for energy conversion onto the solar cells and guides the spectral components not relevant for energy conversion away from the solar cells. | 12-03-2009 |
| 20090293729 | Tank with a gas supply and extraction device for storing cryogenic liquid or fuel for spacecraft - A gas supply and extraction device is arranged preferably on a tank lid or a tank wall in a tank for storing a pressurized driving gas and a liquid such as fuel or oxidizer for operation of a spacecraft. A device housing defines an interior reservoir space. Upper trumpet-shaped passage bodies and a lower trumpet-shaped passage body communicate from the interior reservoir space into the interior space of the tank. By capillary effects, baffle plates, deflector plates, capillary plates, a separation chamber and other components separate liquid from gas entering the device, so that the gas can be extracted while the liquid is stored in the reservoir space of the device until it is drained back into the tank during an accelerated operation phase of the spacecraft. | 12-03-2009 |
| 20090289842 | Process for Improving the Continuity in the Case of a Two-Frequency Navigation Satellite System - A process for improving continuity in a two-frequency navigation satellite system includes steps of i) observing the ionosphere by measurements in the two or more frequency bands; and ii) transmitting an alert message which informs user systems of a change of the ionosphere when at least one measurement indicates a change of the ionosphere that deviates from one or more predefined conditions. | 11-26-2009 |
| 20090289840 | Process for Optimizing Status Notifications in the Case of a Navigation Satellite System - A process for optimizing status notifications in the navigation satellite system includes the following steps: the determination of information concerning a communication network of the navigation satellite system; and the transmission of the determined information as a status notification in at least one navigation message. | 11-26-2009 |
| 20090284417 | Arrangement and Method for the Wireless Transmission of Phase-Critical Signals when the Length of the Transmission is Variable - A method and apparatus for wireless transmission of electrically complex or phase-critical signals includes a device for measuring the length of a transmission route to a moving platform, and a device for transmitting complex measuring or reference signals. According to the invention, components of the device for transmitting the signals are arranged adjacent components of the device for measuring the length of the transmission route, so that changes of the length of the transmission route are the same for both devices. | 11-19-2009 |
| 20090284410 | Vehicle System And Earth-Based Receiver System - In a vehicle, a vehicle system is provided that includes a position determination module for determining the position of the vehicle using an estimation of the error of satellite signals which are received by an earth-based receiver system, and an integrity module for determining an integrity risk for the position data for a vehicle, the risk being derived using time determinations performed by a satellite navigation system. When a threshold value for the integrity risk for the position data is exceeded, the vehicle system generates a warning signal which, by means of modules that are connected to the vehicle system, is designed to prevent the use of the position data for the vehicle. The integrity risk is determined using an estimated value for the error in the received satellite signal, and the receiver system functionally interacts with a plurality of satellites to determine and transmit data to a vehicle system containing a position determination module for determining the position of the vehicle. | 11-19-2009 |
| 20090238741 | Flying apparatus and method for removing harmful gases from the atmosphere - An apparatus for removing harmful gas components out of the earth's atmosphere is a free-flying autonomous lightweight aircraft with an onboard gas processing system including gas separation or extraction devices, and inlets and outlets connected to the devices. Solar cells and/or thermoelectric generators provided on the craft produce electrical energy to operate the individual devices. The system may include a cryogenic closed-loop circulation system that participates in liquefying the extracted gas components. The apparatus is preferably a lighter-than-air craft like a dirigible. A method of extracting harmful gas components from the atmosphere involves flying the apparatus at a prescribed altitude level and operating the gas processing system to remove the harmful gas component from the atmosphere, then returning the apparatus to earth to offload the liquefied stored harmful gas component. | 09-24-2009 |
| 20090204324 | Device and Method for Orbit Determination and Prediction of Satellites Providing Signals to Users - A device and method for orbit prediction of satellites are provided. An accelerometer measures non-gravity forces acting on a satellite. A processor receives measured non-gravity forces from the accelerometer, estimates the contributions of the measured non-gravity forces to the movement of the satellite, and predicts the orbit of the satellite based on the estimated contributions of the non-gravity forces to the movement of the satellite. | 08-13-2009 |
| 20090195899 | Mirror Module for Fastening to a Structural Element - A mirror module for fastening to a structural element, comprises a mirror arrangement that includes at least one mirror stack and a first receiving device for holding the mirror arrangement. Each of the at least one mirror stack comprises at least one individual mirror made of a first material. The first receiving device is made of a second material which has a coefficient of thermal expansion adapted to the first material. For fastening the mirror module to the structural element, a second receiving device made of Invar is provided which holds the first receiving device of the mirror module. | 08-06-2009 |
| 20090183573 | High Temperature Pressure Sensor Element, Particularly for Measuring Pressures Inside Jet Engines, Method for the Production Thereof and Component for Jet Engines - A high-temperature pressure sensor element for power units includes a substrate, in which an interior space is developed, a deformable membrane, which separates the interior space from the exterior space in order to deform when the exterior pressure changes, and a strain measuring element, which is arranged on the membrane, for measuring the deformation of the membrane. The substrate, the membrane, and the strain measuring element are manufactured from the same high-temperature-stable material, such as an alloy. By way of example a nickel base alloy may be used. A component for a power unit, such as a turbine blade for an airplane or rocket engine, includes an integrated high-temperature pressure sensor element of this type. | 07-23-2009 |
| 20090135055 | METHOD AND APPARATUS FOR IMPROVING INTEGRITY COMMUNICATION IN A SATELLITE NAVIGATION SYSTEM - In a method of improving the integrity communication in a satellite navigation system which comprises a space segment having multiple satellites which emit navigation signals for the reception and evaluation by use systems for position determination, and a ground segment having several observation stations which monitor the satellites, an error budget for different observation stations or groups of observations stations is transmitted with the navigation signal of a satellite. The navigation signal is received and an error budget contained therein is evaluated by computing a scalar value from the error budget. The scalar value indicates the precision of the error estimate for the generation of the navigation signal. | 05-28-2009 |
| 20090128409 | METHOD AND APPARATUS FOR MONITORING THE INTEGRITY OF SATELLITE NAVIGATION SIGNALS - A method for monitoring the integrity of satellite navigation system includes a first detection of integrity problems, in which the same entity of a navigation signal from a particular satellite is received at different sites, and evaluated to estimate the error of the entity and the error made during the error estimation process. In a second detection, navigation signals received from a specific satellite are measured and evaluated to estimate the error of the entity and the error in the error estimation process. Finally, in a third detection, several navigation signals from different satellites are measured, and evaluated to estimate the error of the entity and the error made in the error estimation process. Integrity problems which are detectable in the first and second detections are taken into account only if it is probable that they occur during the third detection, and have not been discovered during the first and second detection | 05-21-2009 |
| 20090120056 | Microthruster, in particular for use as a position adjustment thruster, thruster and method for producing a microthruster - 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. This Abstract is not intended to define the invention disclosed in the specification, nor intended to limit the scope of the invention in any way. | 05-14-2009 |
| 20090119002 | Terminal For Satellite Navigation System - A terminal for satellite navigation services includes a first receiver for receiving navigation messages emitted by satellites; an output interface for the output of navigation information; and an activating unit. | 05-07-2009 |
| 20090116163 | Process and System for Discharging a Test Mass Free-Floating in a Satellite - In a process for discharging a test mass that is free-floating in a surrounding electrode casing on board a satellite, the electrode casing is enclosed by a vacuum tank, and has one or more first electrodes for the application of electrostatic forces and/or moments to the test mass. In addition, the electrode casing also has one or more second electrodes for modulating alternating voltages (particularly, high frequency voltages) for measuring purposes onto the test mass as well as one or more light-emitting elements, which irradiate the test mass, the electrode casing and/or the electrodes particularly with ultraviolet light for generating a photoelectric effect. Automatically and iteratively, a test mass charge of the test mass is determined. A control operation for eliminating the determined test mass charge is carried out until the test mass charge has reached a defined target value. | 05-07-2009 |
| 20090102720 | METHOD AND DEVICE FOR AUTOMATICALLY DETERMINING THE POSITION OF TRANSCEIVERS OF NAVIGATION SIGNALS - A method and system for automatically determining the position of transceivers of navigation signals using a utilization system for the navigation signals are provided. First, coarse calibration of the coordinates of the transceivers is performed. Next, a trajectory of the utilization system is estimated. Finally, fine calibration of the coordinates of the transceivers and the trajectory of the utilization system is performed. | 04-23-2009 |
| 20090080367 | Method and Device for Efficient Dissemination of Information in a Satellite Navigation System - A system and method for the efficient dissemination of information in a satellite navigation system is provided. The system includes a satellite system comprising a plurality of satellites, a network of observation stations for observing the signals of the satellites, one or more redundant central processing center(s) for evaluating the observations of the observation stations and for generating information, based on the observations, for the dissemination to utilization systems, and a communication network for transmitting the observations from the observation stations to the one or more redundant central processing center(s). The one or more redundant central processing center(s) send(s) the information to the selected satellites, and upon receiving the information, each of the selected satellites sends this information to the neighboring satellites. | 03-26-2009 |
| 20090066573 | RADIO SIGNAL-BASED POSITIONING DEVICE AND METHOD - A radio signal-based positioning device includes a receiver that receives a plurality of radio-transmitted positioning signals, a frequency determiner that determines a frequency of each of the plurality of positioning signals, a send time determiner that determines a send time of each of the plurality of positioning signals, and an evaluation unit that determines a position location from the determined frequencies and send times of the plurality of positioning signals. | 03-12-2009 |
| 20090058722 | REGIONAL SATELLITE POSITIONING SUPPLEMENTARY SYSTEM - Systems and methods for a navigation satellite of a satellite positioning supplementary system are provided in which a unit generates a navigation signal with a signal strength being dimensioned in such a way that it is still possible to receive signals of other satellite navigation systems. | 03-05-2009 |
| 20090058721 | Regional Navigation Satellite Supplementary System - A device of a supplementary navigation satellite is provided. The device includes a unit for generating navigation signals, the signal strength of the navigation signals being dimensioned in such a way that it is still possible to receive signals of other satellite navigation systems. | 03-05-2009 |
| 20090058303 | High Frequency Generator for Ion and Electron Sources - A device for coupling ionization energy into an ion or electron source, which is excited inductively or inductively-capacitively is provided. The device includes: a discharge vessel for a gas, which is to be ionized; a coupling coil, which is wound around the discharge vessel and feeds in a high frequency energy, which is required for plasma excitation; a coupling capacitor, which is electrically coupled to the coupling coil; a high frequency generator, which is electrically coupled to the coupling coil. The high frequency generator forms, together with the at least one coupling capacitor, a resonant circuit. The high frequency generator includes a PLL controller for automatic impedance matching of the resonant circuit, so that the resonant circuit can be driven at a resonant frequency. | 03-05-2009 |
| 20090043503 | Method and Device for Determining Protection Levels for Satellite Navigation Systems - A method and apparatus for determining protection levels in a satellite navigation system includes the following steps: (1) determining an integrity risk at the alert limit for a plurality of application situations—for example, starting from approaches in category I (Category I precision approach) up to the operation “oceanic enroute;” (2) determining an interval of the alert limits between the largest set of alert limits which produces too high an integrity risk, and the smallest set of alert limits which produces an acceptable integrity risk; and (3) carrying out an interval nesting for the interval of the alert limits that was determined in the previous step, the integrity risk between the horizontal and the vertical being divided in the same way as it is obtained from the relationship between these integrity risks in the largest set of alert limits. | 02-12-2009 |
| 20090037105 | Positioning Device and Positioning Method for a Satellite Navigation System - A positioning device for a satellite navigation system includes a receiver that receives atmospheric correction data and an evaluation unit that determines a position location and estimates its quality on the basis of a plurality of positioning signals, with inclusion of the atmospheric correction data. | 02-05-2009 |
| 20090011703 | Global Information and Hazard Warning System Using Satellite Navigation Systems and User Terminals - A method and device for a global information and early warning system, based on satellite navigation systems and user terminals, comprising the following steps and/or devices for carrying out this step: transmitting at least one warning message about one or more hazard area(s) by way of a satellite navigation system to user terminals in at least one information coverage area; receiving at least one warning message by means of a user terminal in the at least one information coverage area; and checking the warning message by means of the user terminal whether the user terminal is affected by the warning message. | 01-08-2009 |
| 20090009762 | Method and Apparatus for Detecting Optical Spectra - In a method and apparatus for detecting optical spectra, two or more partial beams are generated from an incident beam, each of said partial beams being assigned to a different spectral region. The partial beams travel through a spectrometer lens system and are detected in a spatially separated manner. For this purposes, the partial beams generated from the incident beam are directed to respective spatially separated diffraction gratings that are virtually superimposed in the beam path, and are assigned to different spectral regions. After passing through the diffraction gratings, the spectrally separated partial beams are combined to a joint beam path traveling through the spectrometer lens system. Preferably, the partial beams comprising the different spectral regions can be spectrally separated after passing through the spectrometer lens system and can be detected in spatially separated detectors assigned to the different spectral regions. | 01-08-2009 |
| 20080288167 | Method and Apparatus for Providing Integrity Information for Users of a Global Navigation System - In a method for providing integrity information for users of a global navigation system, which comprises several space vehicles like satellites transmitting information to a device for position detection, the transmitted information comprises first information from the global navigation system about the accuracy of a signal in space error SISE of a faulty space vehicle, and second information whether or not the global navigation system assesses the faulty space vehicle as faulty. The invention is based on the assumption how exact a fault can be detected, so that performance the global navigation system can be increased; and no unfounded assumption is used which improves the quality of service. | 11-20-2008 |
| 20080271387 | High-Frequency Measuring Hangar for Measuring Large Test Objects - A high-frequency measuring enclosure for measuring large test objects is formed by an air-supported membrane or textile construction of a spherical or ellipsoidal contour, which is substantially pervious to electromagnetic radiation. For absorption of residual electromagnetic radiation that may be reflected by the interior of the surface, the floor is covered with absorber material. | 11-06-2008 |
| 20080259645 | Converter for an Ion Propulsion System - A converter includes a converter for an ion propulsion system is provided. The converter includes a bridge circuit with a first and second bridge circuit connection and four switches. The converter also includes a storage inductance and a high voltage transformer with a primary and a secondary winding. The converter further includes a switch control unit, which opens or closes the fourth switch at a control time delayed in relation to the first switch. | 10-23-2008 |
| 20080245072 | Damping of Vibration of a Combustion Chamber By Resonators - Device for damping oscillations of a combustion chamber that includes at least one resonator connected to a pre-chamber in a vibration-damping manner. The pre-chamber is connected to a combustion chamber in a vibration-damping manner via at least one passage channel. This abstract is not intended to define the invention disclosed in the specification, nor intended to limit the scope of the invention in any way. | 10-09-2008 |
| 20080243349 | Method and Apparatus for Speed Control - A device for automatically controlling the speed of a vehicle comprises a positioning sensor, which is designed to emit a position signal with the current position of the vehicle, a navigation database, in which the positions of the city limits are stored, and a speed control unit, to which the position signal is fed. The speed control unit is configured such that it determines, as a function of the position signal, the distance of the vehicle from the nearest city limits or a region with a speed limit in the direction of travel of the vehicle, based on data of the navigation database. It then generates, as a function of the determined distance, a speed setting signal, which reduces the current speed of the vehicle in such a manner that a predefined speed of the vehicle is reached no later than at the nearest city limits or the region with a speed limit. | 10-02-2008 |
| 20080243286 | METHOD FOR COMPUTER-ASSISTED DETERMINATION OF AN OPTIMUM-FUEL CONTROL OF NOZZLES - Method for the computer-assisted determination of an optimum-fuel control of nozzles according to a control instruction b=Ax. A defined matrix transformation of starting constraints for the mass flow of the nozzles and of the minimization criterion thereby takes place in a computer-assisted manner, a data processing representation of a geometric description of the matrix-transformed starting constraints, a computer-assisted determination of limiting point sets of the geometric description of the starting constraints through a computer-assisted geometric search procedure in the vector space and the application of the matrix-transformed minimization criterion to the points of the limiting point sets. | 10-02-2008 |
| 20080211718 | Method and Apparatus for Determining the Position and Orientation of a Missile - A system for determining the position and orientation of a flying object such as a missile includes a ground segment having at least one pseudolite station located on the earth's surface which transmits into space a navigation signal that uniquely identifies the pseudolite station, and a user segment having at least one sensor which is situated in the missile and is designed to receive the navigation signal from the at least one pseudolite station and to determine its absolute position and orientation in space on the basis of the received navigation signal. | 09-04-2008 |
| 20080210786 | Injection head for the combustion chamber of A rocket propulsion unit - An injection head for the combustion chamber of a rock propulsion unit has a base area with a plurality of injection elements distributed on it. Propellant constituents can be injected from each outlet of the injection elements into the combustion chamber, generating hot gases by a mixing and combustion of the propellant constituents in the combustion chamber, which hot gas can be accelerated to a high velocity for generating thrust. The base area of the injection head had a contoured shape which prevents or reduces the formation of zones of a reduced pressure, particularly between directly adjacent outlets. | 09-04-2008 |
