KR20190071215A - THe METHOD AND APPARATUS OF CONVERTING SBAS INTEGRITIES FOR EARTH ORBITING SATELLITES - Google Patents

Abstract

Disclosed are an SBAS integrity information conversion method for an earth orbiting satellite and an apparatus thereof. The SBAS integrity information conversion method for an earth orbiting satellite comprises: a step (a) of receiving a signal comprising terrestrial SBAS integrity information; and a step (b) of converting the terrestrial SBAS integrity information into SBAS integrity information for an earth orbiting satellite. In step (b), the SBAS integrity information for an earth orbiting satellite can be converted from the terrestrial SBAS integrity information to include earth orbit ionosphere integrity information corrected in consideration of a signal delay due to the ionosphere at the altitude of an earth orbiting satellite for terrestrial ionospheric integrity information included in the terrestrial SBAS integrity information. Thus, location estimation accuracy can be increased.

Description

TECHNICAL FIELD [0001] The present invention relates to a method and an apparatus for converting an SBAS integrity information for an earth-

The present invention relates to a method and an apparatus for converting an SBAS integrity information for an earth orbiting satellite.

Global Navigation Satellite System (GNSS) There is a satellite based augmentation system (SBAS) method for improving navigation accuracy and confidence level. SBAS is a system that provides correction information for GNSS signal error as well as integrity information indicating the error covariance of correction information. It is widely used to improve accuracy and reliability in the ground, marine, and aeronautical fields. In reality, the wide-area augmentation system (WAAS) developed in the United States, the multi-functional satellite augmentation system (MSAS) developed in Japan and the European geostationary navigation overlay service (EGNOS) And contributes a lot to the reliability of the estimated value.

The signal transmitted from the SBAS includes correction information and integrity information. The types of correction information include fast correction (FC), long-term correction (LTC), and ionospheric correction information. FC is correction information for a short time signal change and is applicable to GNSS pseudo range information. LTC is provided in the form of rate of change information and correction information for satellite orbits and clocks, and is directly applicable to GNSS satellite orbits and clocks calculated from navigation messages. The SBAS ionospheric correction information is included in MT 26 and includes correction information for the ionospheric map of the lattice point and GIVE (grid ionosphere vertical error) for the estimation accuracy of the ionospheric correction information. The user can calculate the ionospheric correction value by calculating the value at the surrounding lattice point as a weighted sum.

The integrity information (terrestrial SBAS integrity information) is an indicator of the correction information and the estimation error for the location. The integrity information can be obtained by combining the information provided by the SBAS and calculating the covariance of the GNSS signal and ionospheric, convective layer correction information and receiver error, and summing them.

Integrity information is used to calculate the weight of each satellite. Integrity information affects the accuracy of positioning by assigning a small weight to satellites with large estimation errors for each correction information, reducing the contribution to the position and giving large weights to the satellites with small estimation errors.

The integrity information is also used to calculate the protection level for the location. The protection level represents the estimation error for the user location information and is calculated separately for the vertical and horizontal protection levels. The lower the accuracy of the received correction information, the higher the protection level, and the use of the GNSS system should be discontinued if it exceeds the preset alert threshold. For example, these concepts are mainly used in aircraft, and the CAT-I (approach procedures with vertical guidance) conditions defined in ICAO (International Civil Aviation Organization) require a vertical alarm limit of 10 m and a horizontal alarm limit of 40 m , And if the calculated level of protection when entering the runway is greater than the alarm threshold, the satellite navigation system can not be used because it does not satisfy the CAT-I rating. Using this level of protection, it is possible to calculate the estimation error for the user location information, and it is possible to prepare for the failure situation by stopping the use of the satellite navigation system when the protection level exceeds the alarm threshold value, The reliability can be secured.

On the other hand, the SBAS described above generates correction information and integrity information for terrestrial users and aircraft. However, even for low-altitude satellites flying at the lowest altitude range, there is a big difference from the assumed ground environment in SBAS because the altitude is 300 km to 1000 km. Accordingly, there is a limit in which the SBAS correction information and the integrity information can not be directly applied to the earth orbit satellite.

Since the corrected SBAS correction information for the earth's orbit satellite affects the observation value in the position calculation algorithm and the integrity information affects the weighting matrix for each satellite, if the correction information is not corrected, Is greatly increased. For example, using the unmodified calibration information and the integrity information to calculate the position of the earth orbiting satellite increases the position error with respect to the signal direction, and the degree of protection also increases greatly.

The background of the present invention is described in the paper ["Determination of Low Orbit Ionospheric Delay Scale Using IRI Model", Korean Journal of Remote Sensing, pp. 331-339, 2014, Jung Rae Kim, Min-Kyu Kim and ["Using ionospheric corrections from the space-based augmentation systems for low earth orbiting satellites", GPS Solution, pp. 423-431, 2015, Kim Jeongrae, Lee Young Jae.

The present invention has been made to overcome the above-mentioned problems of the prior art, and it is an object of the present invention to overcome the limitation that the SBAS correction information can not be used for the existing earth-orbit satellite and to use the SBAS integrity information in the earth- And an SBAS integrity information conversion method and apparatus.

It should be understood, however, that the technical scope of the embodiments of the present invention is not limited to the above-described technical problems, and other technical problems may exist.

According to a first aspect of the present invention, there is provided a method for converting an SBAS integrity information for an earth's orbital satellite, the method comprising the steps of: (a) Receiving a signal; And (b) converting the terrestrial SBAS integrity information to a terrestrial orbital satellite SBAS integrity information, wherein in the (b), the terrestrial SBAS integrity information for the terrestrial orbit orbit satellite is included in the terrestrial SBAS integrity information Conversion can be performed from the terrestrial SBAS integrity information to include the terrestrial orbital ionospheric integrity information to which the correction of the terrestrial ionospheric integrity information takes into account the signal delay by the ionosphere at the altitude of the earth orbiting satellite.

According to a second aspect of the present invention, there is provided a method for converting an SBAS integrity information for a global orbit satellite, the SBAS integrity information transformation apparatus for a global orbit satellite, A receiving unit for receiving; And a conversion unit for converting the ground SBAS integrity information into the SBAS integrity information for the earth's orbiting satellite, wherein the SBAS integrity information for the earth's orbital satellite includes information about the ground ionospheric integrity information included in the ground SBAS integrity information The transformation from the terrestrial SBAS integrity information may be performed so as to include the earth orbital ionospheric integrity information to which the correction is applied in consideration of the signal delay caused by the ionosphere at the altitude of the earth orbit satellite.

The above-described task solution is merely exemplary and should not be construed as limiting the present disclosure. In addition to the exemplary embodiments described above, there may be additional embodiments in the drawings and the detailed description of the invention.

According to the above-mentioned problem solving means of the present invention, the SBAS integrity information for the earth orbiting satellite can be used by applying the scale factor derived from the difference between the ground environment and the space environment to the ground SBAS integrity information.

In addition, by applying the SBAS integrity information for the earth orbiting satellite to the earth orbiting satellite and calculating the position estimation and the protection level, it is possible to secure the improved accuracy of position estimation and reliability.

However, the effects obtainable here are not limited to the effects as described above, and other effects may exist.

FIG. 1 is a block diagram for explaining an SBAS integrity information converting apparatus for an earth orbit satellite according to an embodiment of the present invention.
FIG. 2 is a view for explaining a conversion unit of the SBAS integrity information converting apparatus for an earth's orbit satellite according to an embodiment of the present invention.
FIG. 3 shows a result of calculation of the low-orbit satellite position estimation and the protection level by the SBAS integrity information converting apparatus (method) for the earth's orbital satellite according to the embodiment of the present invention.
4 is a flowchart illustrating an operation flow of the SBAS integrity information transformation method for an earth orbit satellite according to an embodiment of the present invention.

Hereinafter, embodiments of the present invention will be described in detail with reference to the accompanying drawings so that those skilled in the art can easily carry out the present invention. It should be understood, however, that the present invention may be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. In the drawings, the same reference numbers are used throughout the specification to refer to the same or like parts.

Throughout this specification, when a part is referred to as being "connected" to another part, it is not limited to a case where it is "directly connected" but also includes the case where it is "electrically connected" do.

It will be appreciated that throughout the specification it will be understood that when a member is located on another member "top", "top", "under", "bottom" But also the case where there is another member between the two members as well as the case where they are in contact with each other.

Throughout this specification, when an element is referred to as "including " an element, it is understood that the element may include other elements as well, without departing from the other elements unless specifically stated otherwise.

Throughout the specification, the term 'part' can be understood as a broad concept including a unit realized by hardware, a unit realized by software, a unit realized by using both, and the like. Further, one unit may be implemented using two or more hardware, or two or more units may be implemented by one hardware. Also, some of the operations or functions described in the specification of the terminal, apparatus, or device may be performed in the server connected to the terminal, apparatus, or device. Likewise, some of the operations or functions described as being performed by the server may also be performed in a terminal, device or device connected to the server.

The present invention relates to a method and apparatus for transforming SBAS integrity information for an earth orbiting satellite, and more particularly, to a method and apparatus for converting SBAS integrity information received from the ground into SBAS integrity information applicable to the earth orbiting satellite.

Hereinafter, a description will be given of a SBAS integrity information conversion apparatus for a global orbit satellite (hereinafter referred to as " SBAS integrity information conversion apparatus ") according to an embodiment of the present application.

FIG. 1 is a block diagram for explaining an SBAS integrity information converting apparatus for an earth orbit satellite according to an embodiment of the present invention.

The SBAS integrity information conversion apparatus 100 includes a reception unit 102 and a conversion unit 103. [

The receiving unit 102 is a configuration for receiving a signal including the terrestrial SBAS integrity information 101. [ Further, the signal received by the receiving unit 102 may include the ground SBAS correction information. That is, the signal including the ground SBAS integrity information 101 may include the ground SBAS integrity information 101 as well as the ground SBAS correction information. Since the receiving unit 102 is obvious to a person skilled in the art, a detailed description thereof will be omitted.

For reference, as described above, the terrestrial SBAS correction information may include FC correction information, LTC correction information, and SBAS terrestrial ionospheric correction information. The FC correction information may be correction information for a short time signal change. Further, the LTC correction information may be provided in the form of a correction rate of the satellite orbit and the clock and a rate of change of the correction information. In addition, the LTC correction information is directly applicable to GNSS satellite orbits and clocks calculated from navigation messages. In addition, the SBAS terrestrial ionospheric correction information includes correction information for the ionospheric map of the lattice point shape and GIVE (grid ionosphere vertical error) representing the estimation accuracy of the ionospheric correction information. The user can calculate the ionospheric correction value by calculating the value at the surrounding lattice point as a weighted sum.

The conversion unit 103 is a configuration for converting the ground SBAS integrity information 101 into the SBAS integrity information 104 for the earth's orbiting satellite. Here, the ground SBAS integrity information 101 means SBAS integrity information at the ground level or at the ground level received at the aircraft altitude. As such, the ground SBAS integrity information 101 may include SBAS integrity information about the aircraft.

In the conversion unit 103, the SBAS integrity information 104 for the earth's orbital satellites is subjected to correction with respect to the ground ionospheric integrity information included in the terrestrial SBAS integrity information 101 in consideration of the signal delay due to the ionosphere at the altitude of the earth- And the terrestrial SBAS integrity information 101 to include the earth orbital ionospheric integrity information to which the geostationary ionospheric integrity information is applied.

One of the differences between the environment of the earth orbit satellite and the ground environment is the difference due to the influence of the ionosphere. The ionosphere is distributed from 70 km to 1000 km in the sky, and a signal delay occurs when the signal of the GNSS system passes through the corresponding region. In the case of terrestrial users, the ionosphere is influenced by the ionosphere as much as the length of the GNSS system from the altitude to the ground. However, in the case of the earth orbiting satellite, the ionosphere is influenced only by the length from the altitude of the GNSS system to the altitude of the earth orbit satellite. In other words, the signal received from the earth's orbit satellite is less affected by the ionosphere than the signal received from the ground. For this reason, there is a difference from the received value of the terrestrial user as well as the correction information of the ionospheric satellite of the earth orbit satellite as well as the integrity information. As a result, ionospheric integrity information needs to be corrected to account for ionospheric delay differences in the terrestrial and terrestrial satellite environments.

It is preferable that the conversion unit 103 calculates the scale factor reflecting the difference between the ground environment and the space environment (the altitude environment of the earth orbiting satellite) when converting the SBAS integrity information for the earth's orbiting satellite. For example, the transforming unit 103 may generate the earth orbital ionospheric integrity information by multiplying the terrestrial ionospheric integrity information by a scale factor.

As described above, the signal received by the receiving unit 102 may include the terrestrial SBAS correction information, and the terrestrial SBAS correction information may include a signal delayed by the ionosphere at the ground level, a signal by the ionosphere at the altitude of the earth orbiting satellite The correction corresponding to the ratio of the delay amount can be applied and converted to the earth orbit satellite correction information. The scale factor may be set to the square of the ratio (the ratio of the signal delay by the ionosphere at the ground to the ratio of the signal delay by the ionosphere at the altitude of the earth orbit satellite). In other words, the transforming unit 103 can calculate the ionospheric delay in each of the ground and the space (altitude of the earth orbit satellite) using the IRI model, and use the square of the ratio as a scale factor of the ionospheric integrity information.

The converting unit 103 may correct the ground SBAS correction information to the SBAS correction information for the orbital satellite in consideration of the ratio of the signal delay amount by the ionosphere on the ground to the ratio of the signal delay amount by the ionosphere at the altitude of the earth orbiting satellite have. In other words, the ground SBAS correction information can be converted to the earth orbit satellite correction information by applying a correction corresponding to the ratio of the amount of signal delay by the ionosphere at the altitude of the earth orbit satellite to the signal delay amount by the ionosphere at the ground On the other hand, since the integrity information has a concept of covariance, it can be corrected by considering the scale factor corresponding to the square of the ratio.

In the conversion unit 103, the SBAS integrity information 104 for the earth orbital satellites is converted from the ground SBAS integrity information 101 so as not to include the ground convection layer integrity information included in the ground SBAS integrity information 101 .

One of the differences between the environment of the earth orbiting satellite and the terrestrial environment is the difference due to the influence of the troposphere. In the case of GNSS signals, signal delays occur not only in the ionosphere, but also in dry gas and water vapor distributed from the ground up to about 10 km. However, for terrestrial users, it is necessary to compensate for the signal delay occurring in the troposphere, but in the case of earth-orbit satellites flying at altitudes greater than 10 km, there is no effect of the troposphere, . In other words, the amount of signal delay due to the convection layer is 0 for the earth orbit satellite environment.

Therefore, the convective layer correction is not performed for the earth orbit satellite, and the scale factor of the convective layer integrity information may be set to 0 (the convective layer integrity information value for the earth orbit satellite is 0). That is, when the SBAS integrity information 104 for the earth orbiting satellite is converted to the ground SBAS integrity information 101, the ground convection layer integrity information included in the ground SBAS integrity information 101 may be omitted.

For example, low-orbit satellites at 500 km above the Earth's orbital satellite have only one-third the amount of ionospheric delay of the ionospheric delay from the ground, so the scale factor of the ionospheric integrity information is the ratio of the amount of delay 0.10 can be used, and the scale factor of the integrity information for the convective layer correction information can be used as zero.

On the other hand, in the conversion unit 103, the SBAS integrity information 104 for the earth orbital satellites is stored in the terrestrial SBAS integrity information 101 (FIG. 1) so as to include the FC integrity information and LTC integrity information included in the terrestrial SBAS integrity information 101 without correction ). ≪ / RTI > In the conversion unit 103, the SBAS integrity information 104 for the earth orbit satellite is converted from the terrestrial SBAS integrity information 101 so as to include the receiver integrity information included in the terrestrial SBAS integrity information 101 without correction . In this paper, FC integrity information, LTC integrity information, and receiver integrity information commonly use integrity information (terrestrial SBAS integrity information) on the ground, since this does not greatly affect the error. That is, in the case of the FC integrity information, the LTC integrity information, and the receiver integrity information, the same value can be directly included without correction when converted from the ground SBAS integrity information 101 to the SBAS integrity information 104 for the earth's orbiting satellite.

The scaling factors applied to the integrity information need not apply to GNSS trajectory and clock correction information and integrity information for the receiver. GNSS satellite orbits, clocks, and integrity information for receivers are not different between terrestrial and space environments (altitude environments of earth orbiting satellites). Accordingly, the SBAS integrity information for the earth orbiting satellite for one satellite can be calculated so as to satisfy the following equation (1).

는 i번째 위성에 대한 지구궤도 인공위성용 SBAS 무결성정보,

는 지상에서의 FC 무결성정보 및 LTC 무결성정보,

는 지상에서의 지상 전리층 무결성정보,

는 지구궤도 인공위성에 탑재된 수신기에 대한 수신기 무결성정보,

는 척도인자를 나타낸다.here,

Is the SBAS integrity information for the earth orbiting satellite for the i- th satellite,

RTI ID = 0.0 > FC < / RTI > integrity information and LTC integrity information on the ground,

Is information on the ground's ionosphere integrity on the ground,

Receiver integrity information for the receiver mounted on the earth orbiting satellite,

Represents a scaling factor.

FIG. 3 shows a result of calculation of the low-orbit satellite position estimation and the protection level by the SBAS integrity information converting apparatus (method) for the earth's orbital satellite according to the embodiment of the present invention. Low - Earth satellites used GRACE (Gravity Recovery and Climate Experiment) satellites of US NASA / DLR and SBAS of US WAAS. Scale factor 0.09 was used for ionospheric integrity information for day 22 June 2015 and zero was used for convective layer integrity information. For each calibration information, the scale factor was applied by taking the square root of the scale factor for the integrity information and applied to GPS observations and GPS satellites / clocks. In this case, the maximum value of vertical error is 5 m, the horizontal protection level is 18 m and the vertical protection level is 25 m. This corresponds to the APV-I (approach with vertical guidance) class defined in the ICAO. If the low-earth orbit satellite must always satisfy the APV-I integrity, the APV-I condition is always satisfied in the time zone of FIG. .

Hereinafter, an SBAS integrity information transformation method for an earth orbit satellite according to an embodiment of the present invention (hereinafter referred to as " SBAS integrity information transformation method ") will be described. However, the SBAS integrity information conversion method for the earth's orbiting satellite is performed by the SBAS integrity information conversion apparatus for the earth's orbiting satellite according to one embodiment of the present invention, which includes the same or a corresponding technical feature The same reference numerals will be used for the same or similar components as those described above, and redundant descriptions will be simplified or omitted.

4 is a flowchart illustrating an operation flow of the SBAS integrity information transformation method for an earth orbit satellite according to an embodiment of the present invention.

This SBAS integrity information conversion method includes the steps of receiving a signal including the ground SBAS integrity information 101 and converting the ground SBAS integrity information 101 into the SBAS integrity information 104 for the earth orbiting satellite S120).

In step S110, the signal may include the terrestrial SBAS integrity information as well as the terrestrial SBAS integrity information. Note that, as described above, the terrestrial SBAS integrity information may include SBAS integrity information at the ground level received at the altitude of the ground or the aircraft . As such, the ground SBAS integrity information may include SBAS integrity information about the aircraft.

In step S120, the SBAS integrity information 104 for the earth's orbital satellites is transmitted to the earth (earth) satellite information integrity information 101 based on the ground ionospheric integrity information included in the ground SBAS integrity information 101, And may be converted from the terrestrial SBAS integrity information 101 to include orbital ionospheric integrity information.

In step S120, the SBAS integrity information 104 for the earth's orbiting satellite can be converted from the ground SBAS integrity information 101 so as not to include the ground convection layer integrity information included in the ground SBAS integrity information 101. [

In step S120, the SBAS integrity information 104 for the earth orbiting satellite can be converted from the terrestrial SBAS integrity information 101 so as to include the FC integrity information and the LTC integrity information included in the terrestrial SBAS integrity information 101 without correction. have. In step S120, the SBAS integrity information 104 for the terrestrial orbital satellites is converted from the terrestrial SBAS integrity information 101 so that the receiver integrity information for the receiver mounted on the earth's orbiting satellite is included in the altitude- .

In step S120, the orbital ionospheric integrity information may be generated by multiplying the terrestrial ionospheric integrity information by a scale factor. The ground SBAS correction information included in the signal received in step S110 is corrected by applying a correction corresponding to the ratio of the amount of signal delay by the ionosphere at the altitude of the earth orbit satellite to the signal delay amount by the ionosphere on the ground, It can be converted into correction information for the earth orbiting satellite. That is, the scale factor may be set to a square value of the ratio.

In step S120, the SBAS integrity information 104 for the earth orbiting artificial satellite can satisfy the above-described equation (1).

Meanwhile, the SBAS integrity information transformation method for the earth's orbital satellite according to an embodiment of the present invention may be implemented in the form of a program command which can be executed through various computer means and recorded in a computer readable medium. The computer-readable medium may include program instructions, data files, data structures, and the like, alone or in combination. The program instructions to be recorded on the medium may be those specially designed and constructed for various embodiments of the invention or may be available to those skilled in the art of computer software. Examples of computer-readable media include magnetic media such as hard disks, floppy disks and magnetic tape; optical media such as CD-ROMs and DVDs; magnetic media such as floppy disks; Magneto-optical media, and hardware devices specifically configured to store and execute program instructions such as ROM, RAM, flash memory, and the like. Examples of program instructions include machine language code such as those produced by a compiler, as well as high-level language code that can be executed by a computer using an interpreter or the like. The hardware devices described above may be configured to operate as one or more software modules to perform the operations of the various embodiments herein, and vice versa.

In addition, the SBAS integrity information transformation method for the earth orbit satellite according to one embodiment of the present invention described above may be implemented in the form of a computer program or application executed by a computer stored in a recording medium.

It will be understood by those of ordinary skill in the art that the foregoing description of the embodiments is for illustrative purposes and that those skilled in the art can easily modify the invention without departing from the spirit or essential characteristics thereof. It is therefore to be understood that the above-described embodiments are illustrative in all aspects and not restrictive. For example, each component described as a single entity may be distributed and implemented, and components described as being distributed may also be implemented in a combined form.

The scope of the present invention is defined by the appended claims rather than the detailed description, and all changes or modifications derived from the meaning and scope of the claims and their equivalents should be construed as being included within the scope of the present invention.

100: SBAS Integrity Information Transformer for Earth Orbital Satellites
101: Ground SBAS integrity information
102:
103:
104: SBAS Integrity Information for Earth Orbit Satellite
201: Scale factor

Claims (13)

A method for converting an SBAS integrity information for an earth orbiting satellite,
(a) receiving a signal comprising terrestrial SBAS integrity information; And
(b) converting the ground SBAS integrity information to SBAS integrity information for the earth's orbiting satellite,
In the step (b), the SBAS integrity information for the earth orbital satellite includes at least one of an earth orbit to which a correction is applied in consideration of a signal delay due to the ionosphere at the altitude of the earth orbiting satellite for the ground ionospheric integrity information included in the above- Wherein the SBAS integrity information is converted from the terrestrial SBAS integrity information so as to include ionospheric integrity information. The method according to claim 1,
In the step (b), the SBAS integrity information for the earth's orbital satellite is converted from the ground SBAS integrity information so as not to include the ground convection layer integrity information included in the ground SBAS integrity information, Integrity information conversion method. 3. The method of claim 2,
In the step (b), the SBAS integrity information for the terrestrial orbit satellite is converted from the terrestrial SBAS integrity information so as to include the FC integrity information, the LTC integrity information, and the receiver integrity information included in the terrestrial SBAS integrity information without correction SBAS integrity information transformation method for earth orbit satellite, which is one. The method according to claim 1,
Wherein in the step (b), the orbital ionospheric integrity information is generated by multiplying the terrestrial ionospheric integrity information by a scale factor. 5. The method of claim 4,
Said signal comprising terrestrial SBAS correction information,
The ground SBAS correction information is converted into earth orbit satellite correction information by applying a correction corresponding to a ratio of a signal delay amount by an ionosphere on the ground to a signal delay amount by an ionosphere at an altitude of an earth orbit satellite,
Wherein in the step (b), the scale factor is a square value of the ratio. 5. The method of claim 4,
In the step (b), the SBAS integrity information for the orbiting earth satellites satisfies the following formula (1)
[Equation 1]

here,

Is the SBAS integrity information for the earth orbiting satellite for the i- th satellite,

RTI ID = 0.0 > FC < / RTI > integrity information and LTC integrity information on the ground,

Is information on the ground's ionosphere integrity on the ground,

Receiver integrity information for the receiver mounted on the earth orbiting satellite,

Is a measure factor. ≪ / RTI > An apparatus for converting an SBAS integrity information for an earth orbiting satellite,
A receiver for receiving a signal including the ground SBAS integrity information; And
And a conversion unit for converting the ground SBAS integrity information into SBAS integrity information for the earth's orbiting satellite,
In the conversion unit, the SBAS integrity information for the earth's orbital satellite includes at least one of earth orbital ionospheric integrity information to which the correction of the ground ionospheric integrity information included in the above-described ground SBAS integrity information is applied considering the signal delay by the ionosphere at the altitude of the earth- Information is converted from the ground SBAS integrity information so as to include information of the SBAS integrity information for the earth orbiting satellite. 8. The method of claim 7,
Wherein the SBAS integrity information for the earth orbital satellites is converted from the ground SBAS integrity information so as not to include the ground convection layer integrity information included in the ground SBAS integrity information, Conversion device. 9. The method of claim 8,
In the conversion unit, the SBAS integrity information for the earth orbital satellite is transformed from the ground SBAS integrity information so as to include the FC integrity information, the LTC integrity information, and the receiver integrity information included in the terrestrial SBAS integrity information without correction , SBAS Integrity Information Transformer for Earth Orbit Satellite. 8. The method of claim 7,
Wherein the geostationary ionospheric integrity information is generated by multiplying the terrestrial ionospheric integrity information by a scale factor in the conversion unit. 11. The method of claim 10,
Said signal comprising terrestrial SBAS correction information,
The ground SBAS correction information is converted into earth orbit satellite correction information by applying a correction corresponding to a ratio of a signal delay amount by an ionosphere on the ground to a signal delay amount by an ionosphere at an altitude of an earth orbit satellite,
Wherein in the conversion unit, the scale factor is a square value of the ratio. 11. The method of claim 10,
In the conversion unit, the SBAS integrity information for the earth orbiting satellite satisfies the following formula (1)
[Equation 1]

here,

Is the SBAS integrity information for the earth orbiting satellite for the i- th satellite,

RTI ID = 0.0 > FC < / RTI > integrity information and LTC integrity information on the ground,

Is information on the ground's ionosphere integrity on the ground,

Receiver integrity information for the receiver mounted on the earth orbiting satellite,

Represents a scaling factor. ≪ RTI ID = 0.0 > A < / RTI > A computer-readable recording medium recording a program for causing a computer to execute the method of claim 1.

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