JP2012122775A - Aircraft position measuring system, time synchronization method, and time synchronization program for use in the system - Google Patents

Abstract

An aircraft position measurement system capable of improving the accuracy of aircraft position measurement is provided.
A squitter signals transmitted from the aircraft is received by the receiving station 51 _i, the target processing station 60, the reception time of the squitter signals at the installation position information and the respective receiving station 51 _i of each of the receiving stations 51 _i Based on the difference information, aircraft flight position information (latitude information, longitude information, and geometric altitude information) is obtained. In this case, at each receiving station 51 _i , time information tm transmitted from the satellites constituting the satellite reinforcement system is received by the time information receiving means (GPS reinforcement system receiver 52). The time synchronization means (timing unit 53, decoding unit 55) synchronizes the reception time when the squitter signal is received by the receiving station 51 _i with the time information tm received by the GPS reinforcement system receiver 52.
[Selection] Figure 2

Description

  The present invention relates to an aircraft position measurement system, a time synchronization method and a time synchronization program used in the system, and in particular, an aircraft suitable for performing wide area air traffic control and improving aircraft position measurement accuracy. The present invention relates to a position measurement system, a time synchronization method and a time synchronization program used in the system.

  A multilateration system has been constructed as an aircraft position measurement system for performing air traffic control and the like. In the multilateration system, signals (skitter signals) transmitted from an aircraft transponder are received by four or more receiving stations, and the position of the aircraft is measured based on a difference in each reception time.

FIG. 3 is a diagram showing a schematic configuration of this type of aircraft position measurement system and an environment in which the system is used.
As shown in the figure, the aircraft position measurement system includes receiving stations 1, 2,..., 5 and a data processing unit 6. This aircraft position measurement system, the receiving station 1, 2, ..., 5, each installation position information is confirmed, the signal w _1, w ₂ are transmitted from the transponder of the aircraft 13, ..., it receives the w _5. Then, the data processing unit 6, each of the receiving stations 1, 2, ..., installation position information and the respective receiving stations 1 and 2 of 5, ..., signal w _1, w ₂ 5, ..., received w _5, respectively Based on the difference information of the reception time, the flight position information of the aircraft 13 is obtained by the hyperbolic positioning method. The flight position information is composed of latitude, longitude, and geometric altitude.

Further, as shown in FIG. 4A, a mode A signal (pulse interval 8 μs) for requesting identification information of the aircraft 13 and an SSR device (Secondary Surveillance Radar) 11 are used. An interrogation signal wa including a mode C signal (pulse interval 21 μs) for requesting altitude information is transmitted to the aircraft 13 and, as shown in FIG. 4B, the aircraft for the interrogation signal wa. The response signal wb by 13 is received. Further, the response by the aircraft 13 to the interrogation signal wa is received at the receiving stations 1, ₂ ,..., ₅ as the signals w ₁ , w ₂ ,. The response signal wb is composed of a 12-bit pulse train having a carrier wave of 1090 MHz. Thus, the maximum identification number is 4096, and the altitude data is encoded from altitude −1000 ft to 126750 ft in units of 100 ft. The 12-bit pulse train includes pulses A ₁ (; 1000), A ₂ (; 2000), A ₄ (; 4000), B ₁ (; 100), B ₂ (; 200), B ₄ (; 400), C ₁ (; 10), C ₂ (; 20), C ₄
(; 40), D ₁ (; 1), D ₂ (; 2), D ₄ (; 4), and corresponds to octal numbers.

In addition to the aircraft position measurement system described above, as this type of related technology, for example, there is an ADS-B ground station described in Patent Document 1.
In this ADS-B (Automatic Dependent Surveillance-Broadcast) ground station, the DBC immediately after the creation of the track information is created for the aircraft in which the track information is newly created based on the received ADS-B signal. The mode S individual question requesting (Discrete Beacon Code, identification code) is performed, and the response signal is received and decoded. Then, the newly created track information and the mode S individual response DBC and distance information match. It is determined whether or not to do. If they match, the aircraft that issued the ADS-B signal and the aircraft that responded to the mode S individual question are treated as the same target, and the newly created track information is Keep holding. On the other hand, if they do not match, it is determined as an erroneous target, and the newly created track information is rejected to reduce the mixture of erroneous targets.

  Moreover, in the airport surface monitoring apparatus described in Patent Document 2, multilateration receives a signal transmitted by a target from a plurality of ground stations arranged in the airport, and determines the target three-dimensional from the arrival time difference of the received signal. The position information is calculated, and target identification information is obtained. Based on the three-dimensional position information, the target altitude monitoring device determines whether the target is flying over the airport at a low altitude or on the airport surface without flying. The integrated processing device integrates the position information of the target calculated by the airport surface detection radar and multilateration based on the determination result, and adds identification information corresponding to the obtained position information. The display device displays the integrated target position information and identification information on coordinates representing the airport surface.

  Moreover, in the quick and accurate geographical position specification of the cellular telephone using the GPS (Global Positioning System) satellite system described in Patent Document 3, a wireless communication network is connected to each spot beam or a user terminal in the cell. All GPS-IDs of satellites visible in the area, and Doppler and signal strength prediction values for the visible satellites are transmitted. The user terminal includes a GPS terminal and can receive a C / A code from the GPS satellite. The user terminal uses the transmitted GPS assistance data to quickly capture GPS-C / A signals for all visible GPS satellites. The user terminal then returns the GPS-C / A code measurement value to the wireless network and the measurement value is processed along with other GPS data. Thereby, it is not necessary to execute all the calculation functions necessary for specifying the position in the user terminal.

Non-Patent Document 1 describes a reference station system, a single GPS system, and a GPS common view system.
In the reference station method, each receiving station detects a squitter transmitted by a reference station installed at a known position, and time synchronization is achieved from the result of multilateration positioning. In the single GPS system, a GPS receiver is mounted on the receiving station to achieve time synchronization.

FIG. 5 is a block diagram showing a configuration of a GPS common view type evaluation apparatus.
The evaluation device 20 includes receiving stations 21, 22, 23 and 24, a transmitting station 25, a WAN (Wide Area Network) 26, and a processing device 27. The processing device 27 is connected to an integration device 28, and a display device 29 and an SSR mode S ground station 30 are connected to the integration device 28.

FIG. 6 is a block diagram showing the configuration of the receiving station 21 in FIG.
The receiving station 21 includes an SSR antenna 41, a receiving unit 42, a decoding unit 43, a timing unit 44, a GPS receiver 45, an interface 46, and a power supply unit 47. The receiving station 21 receives the squitter and the SSR response, measures the signal detection time, decodes the signal content, collects the information into a target report, and outputs it to the processing device 27. The sampling frequency for signal detection is 500 MHz, and high resolution (2 ns) can be expected. Further, a GPS common view method is adopted for time synchronization. As the signal processing technique, the same system as that of the SSR mode S ground station is adopted. In SSR mode S, an individual address consisting of 24 bits is assigned to all aircraft, and the identification capability of the aircraft is increased to over 16 million compared to 4096 in mode A. In addition, the receiving stations 22, 23, and 24 are configured similarly to the receiving station 21.

  The transmitting station 25 transmits an SSR question to the aircraft in order to complement positioning and position calculation. In the supplement of positioning, when the transmitter 25 cannot detect the squitter due to signal interference or the like, the transmitting station 25 interrogates the aircraft to obtain an SSR response and executes positioning. Further, in the position calculation complementation, the transmitting station 25 converts the time from the question transmission to the response reception into the distance to the aircraft and uses it for the position calculation. The processing device 27 performs correlation processing on the target reports output from the receiving stations 21, 22, 23, and 24 to perform MLAT (multi-lateration) positioning, tracking processing, and control of questions to the transmitting station. In this case, in order to reduce the positioning error, the processing device 27 performs a tracking process on the positioning solution, and uses the smooth position as the positioning result.

  In the GPS common view method, by simultaneously receiving signals from the same GPS satellites between the receiving stations 21, 22, 23, and 24, the clock error of the GPS satellites is offset, and high-precision time synchronization is achieved. . In this case, satellite information is transferred from the GPS receiver 45 mounted in each of the receiving stations 21, 22, 23, and 24, common view processing is performed, and high synchronization accuracy is achieved.

JP 2008-146450 A JP 2007-333427 A Japanese Patent Laid-Open No. 10-300835

Hiroki Miyazaki, et al., “Fundamental Experiment Results of Wide Area Multilateration”, Electronic Navigation Research Institute Presentation (10th June 2010), Electronic Navigation Research Institute Presentation, June 2010, P.17- twenty two

However, the related technology has the following problems.
That is, in the aircraft position measurement system of FIG. 3, the accuracy of aircraft position measurement is determined by the accuracy of time synchronization by each receiving station, but since a simple and highly accurate time synchronization means has not been established, There is a problem that the accuracy becomes insufficient.

  Moreover, in the ADS-B ground station described in Patent Document 1, the reliability of the acquired ADS-B monitoring information is improved while suppressing an increase in the device scale, but the configuration and processing method are different from the present invention.

  In the airport surface monitoring apparatus described in Patent Document 2, airport surface monitoring by an airport surface detection radar is interpolated by integrating multilateration information, and efficient and safe airport control is performed. Is different in configuration and processing method.

  The identification of the geographic location described in US Pat. No. 6,057,096 reduces the acquisition time required to access the GPS signals used to determine the location coordinates of the user associated with the wireless communication system. Differ in configuration and processing method.

  Further, in the reference station system described in Non-Patent Document 1, time synchronization does not reach high accuracy, and the receiving station is configured to perform time synchronization according to the timing of receiving a signal from the reference station. There is a problem that it is difficult to apply each multi-lateration to a wide area, because it is necessary to install each receiving station at a position where the signal is obtained. Further, the single GPS method has a problem that the accuracy of time synchronization becomes insufficient. In the GPS common view method, time synchronization can be realized with high accuracy, but complicated data processing is required, and there is a problem that it cannot be easily realized.

  The present invention has been made in view of the above-described circumstances, and can be applied to multilateration for a wide area, and can improve the accuracy of aircraft position measurement, an aircraft position measurement system, a time synchronization method used in the system, and The purpose is to provide a time synchronization program.

  In order to solve the above-described problem, the first configuration of the present invention includes a predetermined number of receiving stations for receiving a signal transmitted from an aircraft, with installation position information determined, and the installation position information of each receiving station, And a position information processing unit that obtains flight position information of the aircraft based on difference information of reception times of the signals at the respective reception stations. Time information receiving means for receiving time information to be transmitted, and time synchronization means for synchronizing the reception time when the signal is received at the receiving station with the time information received by the time information receiving means. It is characterized by being provided.

  According to a second configuration of the present invention, a predetermined number of receiving stations for receiving a signal transmitted from an aircraft, the installation position information being confirmed, the installation position information of each receiving station, and the signal at each receiving station In accordance with a time synchronization method used in an aircraft position measurement system having position information processing means for obtaining flight position information of the aircraft based on the difference information of the reception time of the time information receiving means in each receiving station, Time information reception processing for receiving time information transmitted from the satellite augmentation system, and the reception time when the time synchronization means receives the signal at the receiving station, the time received by the time information reception means It is characterized by performing time synchronization processing for synchronizing with information.

  According to the configuration of the present invention, it is possible to construct an aircraft position measurement system that can obtain aircraft flight position information with high accuracy with a simple configuration.

1 is a diagram showing a schematic configuration of an aircraft position measurement system according to an embodiment of the present invention and an environment in which the system is used. FIG. 2 is a block diagram illustrating a configuration of a multilateration ground station including a receiving station 51 _i and a target processing station 60 in FIG. 1. 1 is a diagram illustrating a schematic configuration of an aircraft position measurement system and an environment in which the system is used. It is a wave form diagram which shows a question signal and a response signal. It is a block diagram which shows the structure of the apparatus for evaluation of a GPS common view system. It is a block diagram which shows the structure of the receiving station 21 in FIG.

  The satellite augmentation system is composed of an SBAS (Satellite Based Augmentation System), and the time information receiving means (GPS augmentation system receiver) of each of the receiving stations is from satellites constituting the SBAS. An aircraft position measurement system configured to receive the time information transmitted is realized.

  The satellite augmentation system is composed of a GBAS (Ground Based Augmentation System), and the time information receiving means (GPS augmentation system receiver) of each receiver station configures the GBAS. The time information transmitted from the ground reference station is received.

  Each of the receiving stations is configured to receive a squitter signal transmitted from the aircraft. Further, a question signal (SSR mode A / C) including a mode A signal for requesting identification information of the aircraft and a mode C signal for requesting altitude information of the aircraft is transmitted to the aircraft. A secondary monitoring radar is provided, and each receiving station is configured to receive a response signal of the aircraft corresponding to the interrogation signal of the secondary monitoring radar. The secondary monitoring radar includes an SSR mode S signal for giving an individual address to the aircraft in the interrogation signal (SSR mode A / C).

Embodiment

FIG. 1 is a diagram showing a schematic configuration of an aircraft position measurement system according to an embodiment of the present invention and an environment in which the system is used.
As shown in the figure, the aircraft position measurement system of this embodiment has receiving stations 51 ₁ , 51 ₂ ,..., 51 _n and a target processing station 60, and an SBAS (Satellite Based Augmentation System, satellite link) in the sky. A global augmentation system) satellite 70 and a GNSS (Global Navigation Satellite System) satellite 71, such as a GPS satellite, are present and used in an environment in which an aircraft 72 flies. These SBAS satellite 70 and GNSS satellite 71 constitute a satellite reinforcement system.

Receiving stations 51 ₁ , 51 ₂ ,..., 51 _n (hereinafter also referred to as “receiving stations 51 _i ”) are installed at predetermined locations such as airports, for example, and installation position information is determined. A signal to be transmitted (eg, a squitter signal) is received. Target processing station 60, based on the difference information of the reception time of the signal at the installation position information and the receiving station 51 _i for each receiving station 51 _i (time difference), flight position information (latitude information of the aircraft 72, the longitude Information and geometrical height information). In particular, in this embodiment, each of the receiving stations 51 _i receives time information (GNSS signal) satisfying a predetermined accuracy transmitted from the GNSS satellite 71 constituting the satellite reinforcement system, and receives the squitter signal. Is synchronized with the received time information. The target processing station 60 transmits the obtained flight position information to the SBAS satellite 70, and the SBAS satellite 70 transmits the flight position information to the aircraft 72 as a reinforcement message.

FIG. 2 is a block diagram showing a configuration of a multilateration ground station including the receiving station 51 _i and the target processing station 60 in FIG.
As shown in FIG. 2, the receiving station 51 _i includes a GPS reinforcement system receiver 52, a timing unit 53, a receiving unit 54, a decoding unit 55, a data processing unit 56, an interface unit 57, and a power supply unit. 58. The GPS reinforcement system receiver 52 has a GPS antenna 52a, and receives the time information of the GPS reinforcement system signal wg transmitted from the GNSS satellite 71 (transmission satellite reinforcement system) with a time accuracy of several ns. The timing unit 53 decodes the data (time information tm) of the GPS reinforcement system receiver 52.

The receiving unit 54 receives the squitter signal sq transmitted from the transponder of the aircraft 72. The decoding unit 55 decodes the squitter signal sq received by the receiving unit 54, and also converts the reception time when the squitter signal sq is received into the data decoded by the timing unit 53 (that is, the GPS reinforcement system receiver 52). Is synchronized with the time information tm) output from The data processing unit 56 processes the data (time information) output from the decoding unit 55 into a data transmission format. The interface unit 57 transmits the data (time information) processed by the data processing unit 56 to the target processing station 60. As the interface unit 57, a communication means that considers data capacity, transmission time, cost, feasibility, and the like, such as a dedicated telephone line, satellite line, LAN (local area network), serial communication, and the like is used. The power supply unit 58 supplies necessary power to each unit of the receiving station 51 _i .

The target processing station 60 includes an interface unit 61 and a target processing unit 62. The interface unit 61 receives data (time information) from the interface unit 57 of the receiving station 51 _i . The target processing unit 62 integrates the data of each receiving station 51 _i received by the interface unit 61 and performs multilateration positioning. The aircraft position measurement system is composed of a computer that functions based on a time synchronization program.

Next, the processing content of the time synchronization method used for the aircraft position measurement system of this embodiment will be described.
In this aircraft position measurement system, the squitter signal sq transmitted from the transponder of the aircraft 72 is received by each receiving station 51 _i , and the installation position information of each receiving station 51 _i and each receiving station 51 _i are received by the target processing station 60. The flight position information (latitude information, longitude information, and geometric altitude information) of the aircraft 72 is obtained based on the difference information (time difference) of the reception time of the squitter signal sq. In this case, in each receiving station 51 _i , time information transmitted from the GNSS satellite 71 constituting the satellite augmentation system (SBAS) is received by the time information reception means (GPS augmentation system receiver 52) (time information reception). processing). The time synchronization means (timing unit 53, decoding unit 55) synchronizes the reception time when the reception station 51 _i receives the squitter signal sq with the time information tm received by the GPS reinforcement system receiver 52. (Time synchronization processing).

  That is, the GPS reinforcement system receiver 52 receives the time information tm of the GPS reinforcement system signal wg transmitted from the GNSS satellite 71 with a time accuracy of several ns. The GPS augmentation system signal wg is a GPS satellite pseudorange, carrier phase, ephemeris information, and almanac. When the satellite augmentation system is SBAS, the SBAS message, the pseudorange of the SBAS satellite 70, and the carrier wave phase are also included in the GPS augmentation system signal wg. Note that the ephemeris and almanac of the SBAS satellite 70 are generally included in the SBAS message. The time information tm of the GPS reinforcement system is output using these signals. This time information tm is taken into the timing unit 53.

The receiving unit 54 receives the squitter signal sq of the aircraft 72, and the decoding unit 55 decodes the squitter signal sq. In the decoded result, address information of the aircraft 72 is included. In the decoding unit 55, the time information tm fetched by the timing unit 53 is added to this address information and sent to the data processing unit 56. The data processing unit 56 performs data format processing for sending to the target processing station 60. The formatted data is sent to the target processing station 60 via the interface unit 57. In the target processing station 60, data from each receiving station 51 _i is integrated, and multilateration positioning of the aircraft 72 is performed. In multilateration positioning, based on the installation position information of each receiving station 51 _i and the reception time difference information when the squitter signal sq of the aircraft 72 is received by each receiving station 51 _i by the target processing unit 62, The flight position information of the aircraft 72 is obtained by the hyperbolic positioning method. The flight position information is composed of latitude, longitude, and geometric altitude.

As described above, in this embodiment, each receiving station 51 _i receives highly accurate time information transmitted from the GNSS satellite 71 constituting the satellite augmentation system (SBAS), and the receiving station 51 _i the reception time when receiving the squitter signal sq 72, in synchronization with said received time information, the target processing station 60, installation position information of each receiving station 51 _i, and the time information in the respective receiving station 51 _i Since the flight position information of the aircraft 72 is obtained based on the difference information (time difference) of the reception time of the squitter signal sq synchronized with tm, the accuracy of the flight position information is improved with a simple configuration.

The embodiment of the present invention has been described in detail with reference to the drawings. However, the specific configuration is not limited to the embodiment, and even if there is a design change without departing from the gist of the present invention, Included in the invention.
For example, an SSR device (secondary monitoring radar) similar to the SSR device 11 in FIG. 3 is provided, and the SSR device requests a mode A signal for requesting aircraft identification information and altitude information of the aircraft. The interrogation signal (SSR mode A / C) including the mode C signal is transmitted to the aircraft so that each receiving station 51 _i receives the response signal of the aircraft corresponding to the interrogation signal of the SSR device. It may be (corresponding to claims 5 and 11). The SSR device may include an SSR mode S signal for giving an individual address to the aircraft in the question signal (SSR mode A / C) (corresponding to claims 6 and 12).

Further, the satellite reinforcement system is not limited to SBAS, and may be configured by a GBAS (Ground Based Augmentation System). In this case, the time information receiving means (GPS augmentation system receiver 52) of each receiving station 51 _i receives time information satisfying a predetermined accuracy transmitted from the ground reference station constituting the GBAS (Claims 3 and 9). Correspondence). GBAS is a GNSS navigation reinforcement system that uses a ground station, and the accuracy of flight position information is higher than that of SBAS, but the service is limited to the range that the ground station can reach.

The number of the receiving stations 51 _i is generally 3 or more, but the accuracy of the flight position information is improved by adding the receiving stations 51 _i . In this case, as the number of receiving stations 51 _i increases, more accurate positioning can be performed. However, since the cost increases, it is common to determine the number of stations so that the accuracy and cost of the required flight position information are balanced. Is. In addition, the interface unit 61 in FIG. 2 serves as a communication unit that faces the interface unit 57. However, if the communication unit is capable of one-to-many connection, there is one, and only one-to-one communication is possible. In the case of means, the same number of receiving stations 51 _i is required. The satellite reinforcement system may include, for example, the European “Galileo” and the Japanese “Quasi-Zenith Satellite”.

  A part or all of the above embodiment can be described as in the following supplementary notes, but is not limited to the following.

(Appendix 1)
A predetermined number of receiving stations that receive the signals transmitted from the aircraft when the installation position information is confirmed;
An aircraft position measurement system comprising: position information processing means for obtaining flight position information of the aircraft based on the difference between the installation position information of each receiving station and the reception time of the signal at each receiving station; ,
Each receiving station is
Time information receiving means for receiving time information transmitted from the satellite reinforcement system;
An aircraft position measurement system provided with time synchronization means for synchronizing the reception time when the signal is received at the receiving station with the time information received by the time information reception means.

(Appendix 2)
The satellite reinforcement system includes:
Consists of SBAS (Satellite Based Augmentation System, wide area reinforcement system by satellite line),
The time information receiving means of each receiving station is:
The aircraft position measurement system according to appendix 1, wherein the time information transmitted from the satellites constituting the SBAS is received.

(Appendix 3)
The satellite reinforcement system includes:
It consists of GBAS (Ground Based Augmentation System).
The time information receiving means of each receiving station is:
The aircraft position measurement system according to appendix 1, wherein the time information transmitted from a ground reference station constituting the GBAS is received.

(Appendix 4)
Each receiving station is
4. The aircraft position measurement system according to appendix 1, 2, or 3, wherein a squitter signal transmitted from the aircraft is received.

(Appendix 5)
A secondary monitoring radar is provided that transmits an interrogation signal including a mode A signal for requesting identification information of the aircraft and a mode C signal for requesting altitude information of the aircraft to the aircraft;
Each receiving station is
The aircraft position measurement system according to claim 1, 2, 3, or 4, wherein the aircraft response signal corresponding to the interrogation signal of the secondary monitoring radar is received.

(Appendix 6)
The secondary monitoring radar is
The aircraft position measurement system according to appendix 5, wherein the interrogation signal includes an SSR mode S signal for assigning an individual address to the aircraft.

(Appendix 7)
A predetermined number of receiving stations that receive the signals transmitted from the aircraft when the installation position information is confirmed;
It is used for an aircraft position measurement system having position information processing means for obtaining flight position information of the aircraft based on the installation position information of each receiving station and difference information of the reception time of the signal at each receiving station. A time synchronization method,
In each receiving station,
A time information receiving means for receiving time information transmitted from the satellite reinforcement system;
A time synchronization method in which time synchronization means performs time synchronization processing for synchronizing the reception time when the signal is received at the receiving station with the time information received by the time information reception means.

(Appendix 8)
The satellite reinforcement system is composed of SBAS (Satellite Based Augmentation System, a wide-area reinforcement system using a satellite line),
The time synchronization method according to appendix 7, wherein the time information receiving means of each receiving station receives the time information transmitted from the satellites constituting the SBAS.

(Appendix 9)
The satellite reinforcement system is composed of GBAS (Ground Based Augmentation System).
The time synchronization method according to appendix 7, wherein the time information receiving means of each receiving station receives the time information transmitted from a ground reference station constituting the GBAS.

(Appendix 10)
The time synchronization method according to appendix 7, 8 or 9, wherein each receiving station receives a squitter signal transmitted from the aircraft.

(Appendix 11)
A secondary monitoring radar is provided that transmits an interrogation signal including a mode A signal for requesting identification information of the aircraft and a mode C signal for requesting altitude information of the aircraft to the aircraft;
11. The time synchronization method according to appendix 7, 8, 9 or 10, wherein each receiving station receives a response signal of the aircraft corresponding to the interrogation signal of the secondary monitoring radar.

(Appendix 12)
The time synchronization method according to claim 11, wherein the secondary monitoring radar includes an SSR mode S signal for giving an individual address to the aircraft in the interrogation signal.

(Appendix 13)
A time synchronization program for causing a computer to function as the aircraft position measurement system according to any one of appendices 1 to 6.

  The present invention can be applied to all aircraft position measurement systems, and is particularly effective when the position of an aircraft needs to be measured with high accuracy.

51 ₁ , 51 ₂ ,..., 51 _n Receiving station 52 GPS reinforcement system receiver (time information receiving means)
53 Timing part (part of receiving station)
54 Receiver (part of receiving station)
55 Decoding unit (time synchronization means, part of receiving station)
56 Data processor (part of receiving station)
57 Interface section (part of receiving station)
58 Power supply (part of receiving station)
60 Target processing station (location information processing means)
61 Interface part (part of position information processing means)
62 Target processing unit (part of position information processing means)
70 SBAS (Satellite Based Augmentation System) satellite (part of satellite augmentation system)
71 GNSS (Global Navigation Satellite System) satellite (part of satellite augmentation system)
72 aircraft

Claims (10)

A predetermined number of receiving stations that receive the signals transmitted from the aircraft when the installation position information is confirmed;
An aircraft position measurement system comprising: position information processing means for obtaining flight position information of the aircraft based on the difference between the installation position information of each receiving station and the reception time of the signal at each receiving station; ,
Each receiving station is
Time information receiving means for receiving time information transmitted from the satellite reinforcement system;
An aircraft position measurement system, comprising: time synchronization means for synchronizing the reception time when the signal is received at the receiving station with the time information received by the time information reception means. The satellite reinforcement system includes:
Consists of SBAS (Satellite Based Augmentation System, wide area reinforcement system by satellite line),
The time information receiving means of each receiving station is:
The aircraft position measurement system according to claim 1, wherein the time information transmitted from the satellites constituting the SBAS is received. The satellite reinforcement system includes:
It consists of GBAS (Ground Based Augmentation System)
The time information receiving means of each receiving station is:
The aircraft position measurement system according to claim 1, wherein the time information transmitted from a ground reference station constituting the GBAS is received. Each receiving station is
4. An aircraft position measurement system according to claim 1, wherein the aircraft position measurement system is configured to receive a squitter signal transmitted from the aircraft. A secondary monitoring radar is provided that transmits an interrogation signal including a mode A signal for requesting identification information of the aircraft and a mode C signal for requesting altitude information of the aircraft to the aircraft;
Each receiving station is
5. The aircraft position measurement system according to claim 1, wherein the aircraft position measurement system is configured to receive a response signal of the aircraft corresponding to the interrogation signal of the secondary monitoring radar. The secondary monitoring radar is
The aircraft position measurement system according to claim 5, wherein the interrogation signal includes an SSR mode S signal for giving an individual address to the aircraft. A predetermined number of receiving stations that receive the signals transmitted from the aircraft when the installation position information is confirmed;
It is used for an aircraft position measurement system having position information processing means for obtaining flight position information of the aircraft based on the installation position information of each receiving station and difference information of the reception time of the signal at each receiving station. A time synchronization method,
In each receiving station,
A time information receiving means for receiving time information transmitted from the satellite reinforcement system;
A time synchronization method in which time synchronization means synchronizes the reception time when the signal is received at the receiving station with the time information received by the time information reception means. . The satellite reinforcement system is composed of SBAS (Satellite Based Augmentation System),
8. The time synchronization method according to claim 7, wherein the time information receiving means of each receiving station receives the time information transmitted from the satellites constituting the SBAS. The satellite reinforcement system is composed of GBAS (Ground Based Augmentation System),
8. The time synchronization method according to claim 7, wherein the time information receiving means of each receiving station receives the time information transmitted from a ground reference station that constitutes the GBAS.   The time synchronization method according to claim 7, wherein each receiving station receives a squitter signal transmitted from the aircraft.

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