Method for Increasing the Availability of a Global Navigation System

Abstract

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.

Description

The invention relates to a process for increasing the availability of a global navigation system comprising several spacecraft which, for the position determination of a terminal, each transmit information to the terminal. The invention also relates to a terminal for determining a position while using a global navigation system.

In a global navigation system that is based on satellites, the precise detection of a specified position with respect to the earth requires a local as well as a global integrity of the information transmitted to the terminal by a plurality of satellites. On the one hand, integrity is the ability of the global navigation system to warn a user, i.e., the terminal, within a predefined time when parts of the system should not be used for the intended purpose. On the other hand, integrity is also the trust a user can have in the reliability of the information which he receives from the navigation system. In particularly, this relates to the accuracy of the information.

Warnings are required, for example, when individual satellite or navigation signals for the position determination have errors. Such errors occur, for example, when a navigation signal of a satellite was generated at the wrong time (so-called “clock or time correction error”) or was created at a faulty location (so-called “faulty satellite orbit”). These errors may influence the actual propagation time of a signal from the satellite to the terminal and may therefore exercise a strong influence on the precision of the navigation.

In order to minimize a measuring error during the position determination by the terminal, in the case of the known global Galileo navigation system, the information of all satellites from which the terminal receives information will be processed. This approach is based on the assumption that, as a result of a maximal number of measurements which can in each case be carried out from the information transmitted by the respective satellites, an error in the position determination can be minimized. Here, it is an existing secondary condition that maximally six of the satellites are permitted to be critical satellites. A critical satellite is defined as a satellite whose information is necessary for the position determination in order to leave an integrity risk below a predefined threshold value (a so-called tolerable or allocated integrity risk). For this reason, the terminal has a function for determining the number of critical satellites in a terminal geometry. Terminal geometry (also: user geometry) is the taking-into-account of those satellites whose information is to be used for the position determination.

Because of the large number of satellites to be taken into account in practice (in the case of the Galileo, as a rule, 11 satellites) and because of the predefined specification of maximally six allowed critical satellites, there is a superproportionally high non-availability of its global navigation system in practice.

It is therefore an object of the present invention to indicate a process for increasing the availability of a global navigation system which comprises several spacecraft which each transmit information to a terminal for the position determination of the terminal. It is also an object of the present invention to indicate a terminal for determining a position while using a global navigation system.

These objects are achieved by means of the characteristics of the independent claims. Advantageous embodiments are contained in the dependent claims.

In the case of a process according to the invention for increasing the availability of a global navigation system comprising several spacecraft which, for the position determination of a terminal, each transmit information to the terminal, information is in each case transmitted to the terminal by a plurality of spacecraft. From the plurality of spacecraft, a first subset with at least a first spacecraft and a second subset with second spacecraft are determined. The second subset of spacecraft is determined from the difference between the plurality of spacecraft and the first subset of spacecraft. An integrity risk is determined exclusively from the information transmitted by the second spacecraft, the first and the second subset of spacecraft being determined such that the integrity risk which is determined from the information transmitted by the second spacecraft is optimized with respect to the integrity risk that was determined from the information of all spacecraft of the plurality of spacecraft.

A terminal according to the invention for determining a position while using a global navigation system comprises devices for carrying out the process according to the invention.

The invention is based on the recognition that the accuracy for the position determination of the terminal does not depend on the number of available measurements which can in each case be carried out from the information transmitted by the respective spacecraft. On the contrary, a high accuracy of the position determination can also be determined from a smaller number of measurements. However, by using a smaller number of spacecraft for a position determination, the availability of the navigation system can simultaneously be increased. This takes place by optimizing the integrity risk.

In this case, the optimization, on the one hand, takes place with respect to falling below a predetermined tolerable integrity risk and/or, on the other hand, with respect to the number of critical spacecraft, particularly the falling below a predefined maximal number of critical spacecraft. The optimization with respect to the integrity risk and/or the number of critical satellites can be achieved in that those spacecraft are eliminated from being taken into account for a position determination whose information results either in an increased integrity risk or in an increased number of critical spacecraft. From the plurality of spacecraft, from which, in each case, the terminal receives information, spacecraft are therefore added in an optimization process to a first subset which should not be used for the position determination, and to a second subset, on the basis of which the position determination should finally take place. In this case, only the information of the second subset of spacecraft is used for the position determination of the terminal, while the information of the first subset of spacecraft is not used for the position determination of the terminal.

According to an embodiment, the first subset and the second subset of spacecraft are determined iteratively, so that the integrity risk, which is determined from the information transmitted by the second spacecraft, is minimized in comparison to the integrity risk that was determined from information of all spacecraft of the plurality of spacecraft.

For minimizing the integrity risk, a number of spacecraft from a plurality of spacecraft is allocated to the first subset, and the integrity risk of the second spacecraft remaining in the second subset is determined. This step is repeated for particularly all possible combinations of a first subset. In principle, the number of spacecraft may be selected to be arbitrary. It is advantageous to first carry out the iteration with the number “1”. Should this not result in any significant reduction of the integrity risk, the iteration can be repeated, for example, for a number “2”. This approach can be arbitrarily expanded. Those second spacecraft of the second subset where the integrity risk is minimal form the plurality of spacecraft for a next iteration step. The above-mentioned steps are repeated until a minimal integrity risk has been reached. By means of the above-mentioned process steps, those spacecraft are successively excluded from a measurement for determining the position of the terminal which contribute to the greatest reduction of the integrity risk.

In this case, it is checked in a further embodiment whether the integrity risk resulting from the successive removal of at least one spacecraft is lower than a tolerable integrity risk. If this is so, the navigation system will be available.

According to a further embodiment, it is checked for each of the second spacecraft of the second subset whether this spacecraft is a critical spacecraft. In this case, it is to be checked whether the number of critical spacecraft is greater than a number of allowed critical spacecraft. If this is so, it is attempted according to a further embodiment of the invention to reduce the number of the critical satellites to a tolerable number.

For minimizing the number of critical spacecraft, a non-critical spacecraft from the determined, particularly optimal, second subset of spacecraft is allocated to the first subset. This means that the non-critical spacecraft is at first excluded from the measurements. Then the number of critical spacecraft is determined within the remaining second subset. These steps are iteratively repeated until no more non-critical spacecraft can be determined in the second subset. This approach is based on the consideration that also the number of critical spacecraft may change positively as a result of the further removal of a non-critical spacecraft. If no other non-critical spacecraft can be removed from the second subset and if, after the checking of the number of the critical subset, a falling below the predefined number of critical spacecraft has not been reached, the optimization will come to an end at this point.

The minimizing of the number of critical spacecraft is advantageously carried out when the number of critical spacecraft is greater than a maximally permitted number of critical spacecraft.

The invention further comprises a computer program product which can be loaded directly into the internal memory of a digital computer and comprises software code sections by means of which the steps of the process according to the invention can be carried out when the product is running on a computer.

In the following, the invention will be explained by means of the figures.

FIG. 1 is a schematic representation of a global navigation system with, for example, eleven spacecraft which each transmit information to a terminal for its position determination;

FIGS. 2 to 10 each are views of a condition of the global navigation system during the implementation of the process according to the invention; and

FIG. 11 is a view of an example of a flow chart of the process according to the invention.

FIG. 1 illustrates a global navigation system with, for example, eleven spacecraft 1, 2, . . . , 11, which each transmit information to a terminal 20. The terminal 20 is capable of carrying out a position determination from the information transmitted by the spacecraft 1, 2, . . . , 11. In the following, the spacecraft will be called satellites.

According to the process on which the invention is based, the information of not all of the satellites 1, 2, . . . , 11 available in principle is used for the position determination, but a number of satellites optimized with respect to the integrity risk and with respect to the number of critical satellites. For this purpose, it is first attempted to find those satellites whose removal will lead to an improvement of the integrity risk. For this purpose, the integrity risk is first determined which is determined from the information of all satellites 1, 2, . . . , 11.

Satellites whose information is not used for the position determination of the terminal 20 in the further course are considered to be allocated to a first subset. Satellites which, in contrast, are used for the position determination are considered to be allocated to a second subset of satellites. In the FIGS. 2 to 5 described in the following, satellites of the first subset will be illustrated by a broken line. In contrast, satellites allocated to the second subset will be shown by a continuous line.

In a first step, a satellite of the total number of eleven satellites is first added to the first subset. In FIG. 2, the start takes place by means of satellite 1. The integrity risk is determined for satellites 2, . . . 11 allocated to the second subset. In this case, it is checked to what extent the integrity risk is reduced by the removal of satellite 1 in comparison to the integrity risk that was determined for the totality of the plurality of satellites 1, 2, . . . 11.

This procedure is repeated in a corresponding manner, in which case, according to FIG. 3, satellite 2 is added to the first subset. Here, the integrity risk is determined for ten satellites 1, 3, 4, . . . , 11 remaining in the second subset. This operation is repeated in a corresponding manner for satellites 3, 4, 5, 6, 7, 8, 9, 10 and 11, which is illustrated in FIGS. 4 and 5 as an example for satellites 10 and 11.

Within the scope of the first step, the integrity risk was thereby determined for the removal of one satellite of all possible eleven combinations. In the example, it is assumed that the integrity risk could be reduced the most by the removal of satellite 2. For a further consideration, the removal of satellite 2 from the plurality of the eleven satellites is therefore final. This is symbolized by the striking-out of satellite 2. Satellite 2 is thereby added to the first subset, while the second subset is formed by the satellites 1, 3, 4, 5, 6, 7, 8, 9, 10 and 11. This is schematically illustrated in FIG. 6.

In a second iteration step, the second subset illustrated according to FIG. 6 forms the plurality of satellites. This means that the same procedure as described in FIGS. 2 to 5 is repeated for the remaining ten satellites 1, 3, 4, 5, 6, 7, 8, 9, 10 and 11. In this case, it is determined, for example, that, as a result of the further removal of satellite 10, the integrity risk can be maximally reduced. Satellite 10 is therefore added to the first subset. This is symbolized by the striking-out of satellite 10. Satellites 1, 3, 4, 5, 6, 7, 8, 9 and 11 therefore remain in the second subset.

In a third iteration loop, the described procedure is repeated again. In the embodiment, it is assumed that a further maximal reduction of the integrity risk can be achieved by the removal of satellite 3. Satellite 3 is therefore also added to the first subset. Satellites 1, 4, 5, 6, 7, 8, 9 and 11, whose information is to be used for the position determination for the terminal 2, therefore remain in the second subset. This is schematically illustrated in FIG. 7.

Three iteration steps of the described type are carried out in the embodiment. In practice, more or fewer iteration steps may also take place.

It is assumed that the integrity risk, which was determined by using the information of satellites 1, 4, 5, 6, 7, 8, 9 and 11, is below a tolerable integrity risk. It is therefore further checked for each of satellites 1, 4, 5, 6, 7, 8, 9 and 11 whether this satellite is a critical satellite. In FIG. 8, critical satellites are illustrated by means of a bold continuous line. As easily visible in FIG. 8, satellites 1, 4, 5, 6, 8 and 11 represent critical satellites, while satellite 9 is a non-critical satellite. Critical satellite means in this case that, as a result of the removal of a critical satellite from the remaining second subset, the integrity risk of the remaining satellites would rise again over the tolerable integrity risk.

Furthermore, it is checked whether the number of critical satellites is greater than a predefined maximally tolerated number of critical satellites. In the embodiment, it is assumed that the number of maximally tolerable critical satellite is six. In practice, this number may deviate from the selected value. As easily visible in FIG. 8, the navigation system in the embodiment has a total of seven critical satellites.

It is therefore further checked whether the second subset also contains non-critical satellites. In the embodiment according to FIG. 8, satellite 9 represents a non-critical satellite. The latter is therefore removed from the second subset and allocated to the first subset. It was found that, as a result of the described strategy, the number of critical satellites can also be influenced. Satellites 1, 4, 5, 6, 7, 8 and 11 therefore at first remain in the second now also considered subset. The integrity risk is determined again, and it is further determined for each of these satellites whether the latter is a critical satellite. In the embodiment according to FIG. 9, satellite 4 has become a non-critical satellite as a result of the removal of satellite 9. Satellites 1, 5, 6, 7, 8 and 11 remain as critical satellites.

In the described manner, the non-critical satellite 4 is now also removed from the second subset and allocated to the first subset. The integrity risk for the remaining satellites 1, 5, 6, 7, 8 and 11 is determined again as well as whether the satellites continue to be critical satellites. In the embodiment, the number of critical satellites cannot be further reduced by the removal of the non-critical satellite 4, so that the second subset finally comprises satellites 1, 5, 6, 7, 8 and 11 which each are critical satellites. However, since the number of critical satellites in the embodiment no longer exceeds the number of maximally allowed critical satellites, the availability of the navigation system is ensured. In addition, the integrity risk is below the tolerable integrity risk.

As a result of the approach according to the invention, the availability of the navigation system as a whole has therefore been increased.

FIG. 11 illustrates an example of the process on which the invention is based with respect to its sequence. In Step S1, a plurality of spacecraft is determined which provide information concerning a position determination. In Step S2, the integrity risk of the plurality of spacecraft is determined. This means that the integrity risk is determined for that number of spacecraft which maximally can be used for the position determination of the terminal. In a Step S3, the minimizing of the integrity risk takes place by the iterative removal of one or more spacecraft from the plurality of spacecraft. In Step S4, it is checked whether the determined integrity risk is lower than a tolerable integrity risk. If this is not so, the optimization algorithm will end at this point. In the positive case, it is checked in Step S5 for each spacecraft of the second subset whether the latter is a critical spacecraft. If at least one non-critical spacecraft is contained in the second subset (Step S6), this spacecraft is removed from the second subset in Step S7. This takes place until no non-critical spacecraft is contained in the second subset. The optimization algorithm ends at this point.

By means of a targeted selection of available satellites for the position determination of a terminal, the availability of the global navigation system can be improved in a simple manner.

LIST OF REFERENCE SYMBOLS

• 1 Spacecraft
• 2 Spacecraft
• 3 Spacecraft
• 4 Spacecraft
• 5 Spacecraft
• 6 Spacecraft
• 7 Spacecraft
• 8 Spacecraft
• 9 Spacecraft
• 10 Spacecraft
• 11 Spacecraft
• 20 Terminal
• S1 Process step
• S2 Process step
• S3 Process step
• S4 Process step
• S5 Process step
• S6 Process step

Claims

1.-12. (canceled)

13. A process for increasing the availability of a global navigation system comprising a plurality of spacecraft, each of which transmits information for determining the position of a terminal, said method comprising: each of said spacecraft transmitting information to the terminal;from the plurality of spacecraft, determining a first subset including at least one of said spacecraft, and a second subset, with the second subset being constituted by those spacecraft that are not included in the first subset; anddetermining an integrity risk exclusively for the information transmitted by the second subset of spacecraft;wherein, the first and the second subsets of spacecraft are determined such that the integrity risk determined for the information transmitted by the second subset of spacecraft is optimized relative to the integrity risk that was determined for the information of all spacecraft included in the plurality of spacecraft.

14. The process according to claim 13, wherein only the information of the second subset of spacecraft is used for position determination of the terminal.

15. The process according to claim 13, wherein the information of the first subset of spacecraft is not used for position determination of the terminal.

16. The process according to claim 13, wherein the first and the second subsets of spacecraft are determined iteratively, so that the integrity risk determined for information transmitted by the second spacecraft is minimized relative to the integrity risk determined for the information of all spacecraft of the plurality of spacecraft.

17. The process according to claim 16, wherein, for minimizing the integrity risk: a) a number of spacecraft from the plurality of spacecraft is allocated to the first subset and the integrity risk of the spacecraft remaining in the second subset is determined;b) step a) is repeated for possible combinations of a first subset;c) those spacecraft of the second subset whose integrity risk is minimal form the plurality of spacecraft for a next iteration step,d) steps a) to c) are repeated until a minimal integrity risk has been reached.

18. The process according to claim 17, wherein it is checked whether the integrity risk is lower than a maximum tolerable integrity risk.

19. The process according to claim 18, wherein it is checked for each of the spacecraft of the second subset, whether it is a critical spacecraft.

20. The process according to claim 19, wherein it is checked whether the number of critical spacecraft is greater than a number of allowed critical spacecraft.

21. The process according to claim 19, wherein, for minimizing the number of critical spacecraft: a) a non-critical spacecraft from the determined second subset is allocated to the first subset;b) the number of critical spacecraft within the second subset is determined; andc) steps a) and b) are repeated iteratively until no non-critical spacecraft can be determined in the second subset.

22. The process according to claim 21, wherein minimizing of the number of critical spacecraft is carried out when the number of critical satellites is greater than a maximum permitted number of critical satellites.

23. A terminal for determining a position using a global navigation system comprising a plurality of spacecraft which, for position determination of the terminal, each transmit information to the terminal, the terminal comprising devices for implementing the process according to claim 13.

24. A computer program product which is loadable into the internal memory of a digital computer and comprises software sections for carrying out the steps according to claim 13, when the product is running on a computer.