Astrium Gmbh

Eads Astrium Gmbh

Airbus Defence and Space Gmbh

European Space Agency

Airbus Ds Gmbh

Hans L Trautenberg

Tanja Rang

Michael Kirchner

Jan M W Krueger

Bruno Lobert

Harald Frankenberger

Hugues Favin-Leveque

Johann Vilzmann

Thomas Weber

Alexandre Mudrak

Bertrand Boutteau

Veit Oehler

Marcel Abele

Jan M Krueger

Tanja Beck

Jan MW Krüger

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.

Integrated positioning solution for global navigation satellite systems

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

Combined use of different satellite navigation systems

A device for detection of falsified signals in a satellite navigation system includes at least two antennas having one or more receivers for receiving navigation signals, a phase difference measuring unit for determining phase differences of the received navigation signals for each antenna, and a detection unit for detecting falsified navigation signals among the received navigation signals on the basis of the phase differences determined.

Detection of falsified signals in a satellite navigation system

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.

Method of automatically determining a landing runway

A method for determining the integrity risk at an alert limit of a position solution determined with a satellite navigation system involves calculating a first integrity risk at the alert limit assuming that one satellite j of the satellites is faulty. A first position solution is determined with the signals from all of the satellites and a second position solution is determined with the signals from all of the satellites except for the signal received from the satellite j. A difference between the first and the second position solution is identified and subtracted from the alert limit to create a reduced alert limit. A second integrity risk at the reduced alert limit is calculated with the signals received from all satellites except the signal received from the satellite j. The integrity risk at the alert limit is determined using the minimum of the first and second integrity risks.

Enhancement of the integrity concept of a satellite navigation system

In a satellite-based augmentation system a data stream is generated that includes user messages having different message types. A plurality of predetermined unique sequences of message types are formed and each formed sequence is allocated to one of a plurality of data sources that are used for generating user messages in the satellite-based augmentation system. A data source is selected for generating a data stream that includes user messages. The selected data source generates the data stream including user messages by using the predetermined unique sequence of message types that is allocated to the selected data source.

Generation of a data stream comprising user messages in a satellite-based augmentation system

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

Satellite-based SAR services

A method for determining overbounds comprises the steps of determining conservative overbounds (q) of at least one error (&#x3b5;) in a first phase space, multiplying the conservative overbounds (q) of errors (&#x3b5;) in the first phase space by a first parameter (&#x3b8;(&#x2212;x)&#xb7;2) and a second parameter (&#x3b8;(x)&#xb7;2), and determining an upper bound for the integrity risk at the alert limit (p(AL)) in a second phase space using overbounds (q) of errors (&#x3b5;) in the first phase space by the first parameter (&#x3b8;(&#x2212;x)&#xb7;2) and the second parameter (&#x3b8;(x)&#xb7;2).

Method and apparatus for transforming overbounds

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.

Integrity method for differential corrections

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.

RAIM algorithm

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.

Method for the transmission of additional data along with navigation messages in a satellite navigation system

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&#x2014;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.

Method and device for determining protection levels for satellite navigation systems

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.

Method and device for estimation of the integrity risk in a satellite navigation system

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.

Radio signal-based positioning device and method

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.

Growing community of inventors

Ottobrunn, Germany

Hans L Trautenberg