JP5115580B2 - Multilateration system, signal processing method for multilateration receiving station, and processing program therefor - Google Patents

Description

  The present invention relates to a receiving station in an air traffic control multi-lateration system including a plurality of receiving stations, and in particular, thins out (selects and extracts) a mode A response and a mode C response, which are outputs of the receiving station. This reduces the processing load on the system and reduces the loss due to the line for the mode S reception information even when the line capacity between the reception station and the center station is not sufficient to send all the SSR reception information of each reception station. The present invention relates to a multi-lateration receiving station, a received signal processing method, and a processing program thereof.

Conventionally, an air traffic control radar device has been used as an aircraft monitoring sensor system in an air traffic control system.
This air traffic control radar is normally configured to include a primary surveillance radar device (PSR) and a secondary surveillance radar device (SSR).

  Among these, the primary monitoring radar device detects an aircraft and extracts position information based on a reflected signal from the aircraft with respect to an RF signal (Radio Frequency signal: radio signal) radiated from the ground. The secondary monitoring radar device detects the aircraft and extracts the position information from the aircraft's response to its own interrogation signal, as well as the altitude information by the mode A which is the identification information of each aircraft and the barometric altimeter mounted on the aircraft. The mode C is extracted and can be provided to the control engine.

  Some secondary monitoring radar devices include a mode S function. This mode S function is an individual selection call function based on an ID (24-bit address) assigned to each aircraft. In addition to the identification information in mode A and altitude information in mode C, route information, speed information, etc. It is an execution function whose contents are also obtained.

  In such a secondary monitoring radar apparatus, individual questions to the aircraft can be made based on identification information called a mode S address, and information can be exchanged between the ground and the aircraft by a data link function.

  Further, in order to enable the mode S function of the secondary monitoring radar apparatus, the aircraft side needs to mount a mode S transponder. In addition to responding to individual questions with its own mode S code, the transponder Some of them have a function that can transmit alarm information of the collision prevention device, flight parameters of the aircraft, and the like to the ground using a data link function.

  Further, the system according to the mode S transponder has a function of periodically broadcasting the mode S address regardless of questions from the ground. This periodically broadcast information is called a mode S squitter.

  In the field of air traffic control, the time difference when a mode S response to a question from a mode S squitter or an SSR ground station having a mode S function (hereinafter referred to as “mode S ground station”) is simultaneously received by a plurality of receiving stations. Developed a system called a multi-lateration system that specifies the three-dimensional position of an aircraft using the ID, identifies the aircraft with the identification information included in the mode S response, and uses this information to control air traffic Has been.

  In this multilateration system, even for an aircraft not equipped with a mode S transponder, a mode A response and a mode C response (hereinafter referred to as a mode A / C response) to a question from the SSR ground station are used to determine the current position. I have identified.

4A and 4B show a basic configuration of a conventionally known multi-lateration system. 4A, the multilateration system includes a plurality of receiving stations 101, 102,..., 10n .
The plurality of the receiving stations 101 and 102, ..., 10n are omnidirectional antenna 101 A of each L-band, 102 A, ..., has a 10 N A, further, the mode S squitter sent from the aircraft, the mode S reply , And a decoding function for the mode A / C response.

Further, the each of the receiving stations 101, 102, ..., 10n are the respective receiving stations 101 and 102, ..., the information received by 10n, respectively individually transmitted unit with high reception time information accurate D (D1, D2 ,..., Dn), a function of transmitting to the position information calculation means 120 is provided.

The position information calculating unit 120, each of the receiving stations 101, 102, ..., three-dimensional position of the aircraft with Mode S squitter sent from 10n, mode S response, and the difference in the reception time of the mode A / C response 3D position calculation function, and the identification information included in each response signal is sent to the control support means 130.

In FIG. 4, reference numeral 130 denotes a control support means for displaying information sent from the position information calculation means 120 on a control display device or the like.
Here, the plurality of receiving stations 101, 102,..., 10n are arranged at different locations depending on the target search area, and the precise positioning information of these receiving stations 101, 102 ,. Are stored in advance in the position information calculation means 120.

FIG. 4B shows a basic configuration of the receiving station 101.
In FIG. 4B, reference numeral 101A denotes the aforementioned L-band omnidirectional antenna. The receiving station 101 receives and detects a mode S squitter, a mode S response, and a mode A / C response captured by the omnidirectional antenna 101A, and a video obtained by receiving and detecting the reception / detection means 112. SSR response decoding means 113 for decoding information from the aircraft from the signal.

  The receiving station 101 further includes message generation means 117 for receiving the decoded (after decoding) mode S squitter or mode S response via the transmission line 115. The message generation means 117 has a function of receiving the decoded mode A / C response (after decoding) via the transmission line 116.

The message generation means 117 has a function of editing the mode S squitter or the mode S response and the mode A / C response into a message including reception time information. Reference numeral 118 denotes an interface unit for transmitting the message formed by the message generation unit 117 to the position information calculation unit 120 in FIG. This interface means 118 indicates an interface placed for matching with the transmission means D1, D2,..., Dn disclosed in FIG.
The other receiving stations 102, 103,..., 10n are configured in the same manner as the receiving station 101 described above.

  Taking a mode S response to a mode S squitter or a mode S ground station roll call periodically broadcast from a mode S transponder mounted on one aircraft, for example, FIG. The basic operation of the multilateration system shown in FIG.

That is, a mode S squitter or a mode S response having a mode S address that can individually identify an aircraft is received by a plurality of receiving stations 101, 102,..., 10n having the configuration shown in FIG. Thereafter, the plurality of received signals received are decoded by the receiving stations 101, 102,..., 10n , and the mode S code is extracted. Mode S squitter or mode S response information including a high reception time of this mode S code information and accuracy, each of the receiving stations 101, 102 as a received message, ... sent from 10n to the position information calculating unit 120.

Since the position information calculating means 120 can easily associate the received messages sent from the receiving stations 101, 102,..., 10n with the mode S address, the precise information of each receiving station 101, 102 ,. Based on the installation position information, the three-dimensional position at the current position of the aircraft can be calculated from the reception time differences at four or more receiving stations 101, 102,..., 10n of the same mode S squitter.

Thus, in the multilateration system, an aircraft having a mode S transponder (hereinafter referred to as “mode S aircraft”) is a main search target aircraft.
On the other hand, in reality, not all aircraft are equipped with mode S transponders, so the aircraft position is determined from the mode A / C response from the aircraft corresponding to the mode A / C question from the adjacent SSR ground station. Identification is also required from the operational aspect of air traffic control.

However, a receiving station that does not make a mode A / C inquiry by itself cannot simply identify the aircraft from the received mode A / C response. For this reason, in the position information calculation unit 120, for example, all responses are handled as mode A responses, and processing different from the mode S response is performed such that only the set of received messages that can be matched is calculated. There is a need.
In such a case, generally, the position calculation by the mode A / C response requires a larger amount of processing for calculating the position information than the mode S response.

  As techniques related to the above-described multilateration system, Patent Documents 1 to 3 shown below are known.

The Patent Document 1, relates to a secondary surveillance radar system for monitoring a monitoring airspace aircraft and are mixed for mounting an aircraft and mode S transformer responder mounting the ATCRBS transformer responder with conventional, in particular, mode S is obtained by adapted to ensure removal of erroneous response ATCRBS transformer responder for all-call, thereby, the mode S transformer responder invention as may contribute to the safe operation of mounting the aircraft is disclosed Has been.

Further, Patent Document 2 relates to a secondary monitoring radar device, and in particular, it is possible to perform both mode S batch question / response and mode A / C batch question / response processing within each repetition period, and mode. do not detect aircraft equipped transformer responder to respond erroneously S all-call interrogation signal, which the mode S effectively eliminates an adverse effect of false responses to all-call interrogation signal, thereby, the aircraft equipped with mode S transformer responder An invention that can contribute to safe operation is disclosed.

  Further, Patent Document 3 relates to an airport surface monitoring apparatus that scans an airport surface using an airport surface detection radar (ASDE) and calculates and displays target position information on the airport surface. Airport plane monitoring system that complements the detection of aircraft positions in low airspace where position detection is difficult by integrating multilateration information, thereby enabling efficient and safe air traffic control. Is disclosed.

Japanese Patent Laying-Open No. 2005-083815 JP 2006-029872 A JP 2007-333427 A

  In such a multilateration system in which the response of the SSR transponder of the aircraft is received by a plurality of receiving stations having an omnidirectional antenna, if the mode S machine and the mode A / C machine are mixed, The number of responses of the mode A / C machine is larger than the number of responses of the mode S machine, which may affect the system operation.

  Here, the number of responses of the mode S machine and the number of responses of the mode A / C machine are compared under a certain condition as follows.

  Considering one mode S aircraft in the coverage area of the multilateration system, the mode S squitter is about once a second regardless of the presence of the SSR ground station, and the mode S response is the mode S ground for airport monitoring. If the station (the antenna rotation period is about 4 seconds) and the K station (K is an integer) are adjacent to each other, it is received by the receiving station about 4 seconds in response to the roll call. Accordingly, if the actual mode S machine is L machine (L is an integer), the total number of mode S squitter and mode S response reception is approximately L × (K + 4) per 4 seconds.

  On the other hand, for the mode A / C aircraft, since it is considered that a response is received while the antenna beam of the SSR (secondary surveillance radar) ground station faces the aircraft, the antenna beam width of the SSR ground station is set to 2 When the repetition period of the question is 1.4 (milliseconds), the response from the transponder is about 20 times per aircraft as a response to the question of one SSR ground station.

If the adjacent SSR ground station for airport monitoring (mode A / C question) is M site (M is an integer) and mode A / C is N (N is an integer), mode A / C response per 4 seconds The number is approximately 20 × M × N.
Assuming that the number of mode S and mode A / C ground stations K and M sites (M is an integer) are 4 stations, respectively, and 30 mode S machines and 30 mode A / C machines exist, respectively, The mode A / C response is 2400, which is 10 times the mode S response, with respect to the number of mode S responses 240 per 4 seconds.

  As the number of adjacent SSR sites and mode A / C machines in the mode A / C further increase, the difference between the mode S response number and the mode A / C response number becomes larger. Therefore, when trying to operate the multilateration system in such an environment, the following problems occur.

  That is, the transmission capacity of the transmission means D1 to Dn that transmits the reception information from the reception stations 101 to 10N of FIG. 4A to the position information calculation means 120 transmits all response information received by the reception stations 101 to 10N. If there is a large number of mode A / C responses, the mode S squitter or the mode S response information may not be sent depending on the reception timing of each response.

  For this reason, if this is left unattended, even if it is a mode S squitter or mode S response information that can be used to calculate the position information and the aircraft can be identified by the mode S address, There is a problem that the detection performance of the system is deteriorated.

  Furthermore, when a lot of mode A / C response information is sent to the position information calculation unit 120, depending on the processing capacity of the position information calculation unit 120, the position information calculation process in the mode A / C response with a high processing load, There is also a problem that the position information extraction process by the mode S squitter or the mode S response may be limited.

(Object of invention)
The present invention has been made in view of the above points, and reduces overall mode A / C response information captured via each receiving station without removing reception of a specific mode A / C response. Thus, the multilateration system, the signal processing method of the multilateration receiving station, and the signal thereof, which effectively suppress the removal of the information related to the mode S squitter and the mode S response by the mode A / C response information The purpose is to provide a processing program.

To achieve the above object, multilateration system according to the present invention, squitter signal or SSR reply signal target such as an aircraft is provided as a ground station at a predetermined distance from each other is transmitted from the transformer responder to be mounted The three-dimensional position information of the target is calculated from the difference in arrival times of the received signals received by the plurality of receiving stations and the received signals received from the plurality of receiving stations, and the identification information from the corresponding target is obtained from the received signals. In a multilateration system having a center station as a target processing device as described above,

Each of the receiving stations decodes the received and retrieved SSR response signal to analyze information from the aircraft, a mode S squitter decoded by the SSR response decoding unit, a mode S response, and Message generating means for editing information including mode A / C into a message together with reception time information and outputting the message to the center station;
A mode A between the SSR response decoding means and the message generation means, in which the above-mentioned mode A / C is irregularly thinned over time from the received signal output from the SSR response decoding means and sent to the message generation means. A / C signal thinning means is interposed.

To achieve the above object, a signal processing method for multilateration receiver station according to the present invention, the target object such as an aircraft is provided as a ground station at a predetermined distance from each other is transmitted from the transformer responder mounting squitter From a plurality of receiving stations that receive signals or SSR response signals and the arrival time difference between the received signals received by the plurality of receiving stations, the three-dimensional position information of the target is calculated, and from the corresponding target from the received signal A multi-lateration system including a center station as a target processing device that obtains identification information of

SSR response decoding means decodes the SSR response signal received and taken out by one of the receiving stations, and analyzes information from the aircraft,
Of the information including the mode S squitter, the mode S response, and the mode A / C obtained by being decoded and analyzed by the SSR response decoding unit, the information including the mode S squitter and the mode S response is obtained as the SSR response decoding unit. Is transferred to the message generating means, and for the mode A / C, the mode A / C signal decimating means thins irregularly over time and transfers it to the message generating means.

And over time randomly decimated or the mode A / C signal is fed from the information and the mode A / C signal thinning means including the SSR Mode S squitter and mode S reply is sent directly from the response decoding means The message generating means edits the message and outputs it to the center station.

To achieve the above object, multilateration reception station signal processing program according to the present invention, the target object such as an aircraft is provided as a ground station at a predetermined distance from each other is transmitted from the transformer responder mounting squitter From a plurality of receiving stations that receive signals or SSR response signals and the arrival time difference between the received signals received by the plurality of receiving stations, the three-dimensional position information of the target is calculated, and from the corresponding target from the received signal A multi-lateration system including a center station as a target processing device that obtains identification information of

An SSR response signal analysis processing function for analyzing the information from the aircraft by decoding the SSR response signal received and taken out by one of the receiving stations;
Among the information including the mode S squitter, the mode S response, and the mode A / C obtained by decoding and analyzing, the information including the mode S squitter and the mode S response is transferred to the message generation unit, and Outline of processing-out over time irregularly thinning for the message generation also the mode A / C,

And the information and the time irregularly decimated mode A / C signal including the Mode S squitter and Mode S responses identified as for the message generator, to edit the form of the message the center station Message generation output processing function to output,
And each of these functions is realized by a computer.

  Since the present invention is configured as described above, according to this, each receiving station receives information from the aircraft and analyzes the information of the extracted SSR response signal to obtain a mode S squitter, a mode S response, and a mode. When the information including A / C is edited into the reception time information and output to the center station, the mode A / C is irregularly thinned over time and sent to the message generating means. The mode A / C response information captured via each receiving station can be reduced overall without removing the reception of the mode A / C response of the mode, and the mode A / C response information can thereby reduce the mode S squitter. In addition, it is possible to effectively suppress the removal of information related to the mode S response, and an unparalleled excellent multi-lateration system, multi-latex Shon signal processing method of the receiving station, and the signal processing program can provide.

It is a block diagram which shows an example of the receiving station in one Embodiment of the multilateration system concerning this invention. It is a block diagram which shows the whole multilateration system containing the receiving station of embodiment disclosed in FIG. It is a timing chart which shows operation | movement of embodiment disclosed in FIG. FIGS. 4A and 4B are diagrams illustrating an example of a multi-lateration system according to related technology, in which FIG. 4A is a block diagram illustrating an entire multi-lateration system including the receiving station, and FIG. 4B is a block diagram illustrating an example of the receiving station. It is.

Hereinafter, an embodiment of the present invention will be described with reference to FIGS. 1 to 3.
First, basic contents will be described, and then specific contents will be described.

In FIGS. 1 and 2, multilateration systems are mutually squitter signal or SSR reply signal aircraft (target) is provided as a ground station at a predetermined distance 60, 70 is transmitted from the transformer responder to be mounted or the like .., N that receives the signals 62 and 63 of the received signal, and the arrival time difference between the received signals 62 and 63 received by the plurality of receiving stations 1, 2,. Position information calculation means (center station) 120 as a target processing device is provided that calculates three-dimensional position information of an object and obtains identification information from the corresponding target object from the received signals 62 and 63.

  Among the above receiving stations 1, 2,..., N, as shown in FIG. 1, the receiving station 1 receives and detects signals from the aircrafts (targets) 60 and 70 via the antenna 1a and detects the SSR response. Receiving / detecting means 11 for extracting a signal, etc., SSR response decoding means 12 for analyzing the information from the aircraft 60, 70 by decoding the SSR response signal taken out by the receiving / detecting means 11, and the SSR response decoding Message generation means 13 for editing the information including the mode S squitter, the mode S response, and the mode A / C decoded by the means 12 together with the reception time information, and outputting the message to the position information calculation means (center station) 120; It has.

Between the SSR response decoding means 12 and the message generation means 13, the mode A / C is irregularly thinned out over time from the received signal output from the SSR response decoding means 12. A mode A / C signal thinning-out means 14 to be sent to the message generating means 13 is interposed.
Thereby, a large amount of mode A / C signals from the aircrafts 60 and 70 are appropriately thinned out and taken into the message generating means 13.

  Here, between the SSR response decoding means 12 and the message generation means 13 described above, one transmission circuit 12A for transmitting a signal related to the mode S response, and the mode A in addition to the one transmission circuit 12A. The other transmission circuit 12B for transmitting a signal related to the / C response is provided. The mode A / C signal thinning means 14 described above is arranged on the other transmission circuit 12B side.

  The SSR response decoding means 12 has a signal distribution / transmission function for separately transmitting the signal relating to the mode S response and the signal relating to the mode A / C response to the message generating means 14 without mixing them. Thereby, each subsequent signal processing with respect to the signal concerning the mode S response and the signal concerning the mode A / C response is smoothly performed.

  The mode A / C signal decimation means 14 described above performs the signal decimation process on the mode A / C response executed by the mode A / C signal decimation means 14 and is irregularly input over time. This is executed based on the random timing gate signal RT for thinning that changes to.

  The mode A / C signal thinning means 14 is actually provided with a pseudo random timing gate signal generating means 15 for generating the thinning random timing gate signal RT. Further, the pseudo random timing gate signal generating means 15 is provided with a reference signal generating means 16 for generating a repetitive regular reference gate signal for generating the random timing gate signal described above. The above-described pseudo-random timing gate signal generating means converts (generates) the repetitive regular reference gate signal into a signal with irregular repetition.

  Here, the reference signal generating unit 16 includes a GPS receiving antenna 16A that receives a GPS signal, and a GPS reception / time information extracting unit 16B that extracts a GPS correct second received by the GPS receiving antenna 16A. Has been. The GPS reception / time information extraction means 16B has a reference gate signal generation function for generating a reference gate signal for generating the random timing gate signal based on the GPS true second.

  Reference numeral 18 denotes an interface means for transmitting the message formed by the message generating means 13 to the position information calculating means 120 in FIG. This interface means 18 indicates an interface placed for matching with the transmission means D1, D2,..., Dn disclosed in FIG. The other receiving stations 2, 3,... N are also configured in the same way as the receiving station 101 described above.

[Specific contents]
Next, the contents of the above embodiment will be described more specifically.
In the present embodiment, in order to achieve the above-described object, as described above, the mode A / C response between the mode A / C responses that is thinned out at irregular timings and sent out at the irregular timing reception station 1 is sent. And a pseudo-random timing gate that generates an irregular pseudo-random timing gate signal (a gate signal for extracting a mode A / C response) that regulates the operation of the mode A / C response thinning-out means 14 And generating means 15.

  Further, reference signal generation means (GPS reception / time extraction means) 16 for generating a reference gate signal that is a source of the gate signal for mode A / C response decimation based on the timing of the GPS signal is provided. Based on this, the above-described pseudo-random timing gate signal RT is formed.

  Here, the pseudo random timing gate generating means 15 receives a time timing signal (1PPS signal: time signal) once per second from a GPS receiver, for example, and extracts a mode A / C response as a gate signal having a time width Tac. Gt is generated (see FIG. 3). The generation timing of the gate signal Gt is assumed to be delayed by Td time after receiving the 1PPS signal, and this delay time is irregularly changed between 1-Tac time every reception of 1PPS signal.

  When the rotation period of the adjacent SSR ground station is close to an integer second, the generation of the gate signal Gt synchronized with 1 PPS may eliminate the mode A / C response from the aircraft in a specific area. By generating the signal Gt at an irregular timing with respect to the 1PPS signal, the mode A / C response output from each receiving station is thinned out while preventing the mode A / C response from the aircraft in a specific region from being removed. be able to.

This will be described in further detail.
As shown in FIG. 1, the GPS reception / time extraction means 16B, which is a GPS time synchronization system, has a function of receiving a GPS signal via a GPS antenna 16A and outputting a highly accurate time signal (eg, 1PPS signal). ing.

  The pseudo random timing gate generating means 15 includes a counter, a pseudo random data generator (random number generator), a comparator, a flip-flop circuit, and the like. The counter output cleared by the 1PPS signal is a random number generator. When the value coincides with the value of, the gate signal is raised, and after a predetermined time (Td), the gate signal is lowered.

  The pseudo-random data corresponding to the delay time is set so that the delay time falls within the “1-Tac” time, and the above-described receiving stations 1, 2, 3,..., N can use the same value in advance. Scheduled.

The mode A / C response decimation means 14 is an AND gate, and outputs a mode A / C response to the message generation means 13 when the mode A / C response extraction gate 14 is active. That is, the mode A / C response obtained by thinning out (selecting and extracting) is output to the message generation unit 13.
Other basic configurations are the same as the contents disclosed in FIG. 4 described above.

[Description of operation]
Next, the overall operation of the above embodiment will be described based on the time chart of FIG.
First, FIG. 2 described above is also a system diagram showing an operating environment of the multilateration system. FIG. 2 is a basic configuration diagram of the receiving station 1 shown in FIG. 1, and is an adjacent SSR site 50, mode A / C machine 60, mode A / C question / response signal 61, mode S squitter or mode S response. A signal 62, a mode A / C response signal 63, and a mode S machine 70 are added.

In an actual environment, there are a plurality of adjacent SSR sites 50, mode A / C machines 60, and mode S machines 70, but one site and one machine are shown for simplicity of explanation.
In FIG. 2, in each of the receiving stations 1, 2,..., N, in addition to the mode S response from the mode S machine 70, the response signal from the mode A / C machine that responds to the question from the adjacent SSR site 50 is For example, the receiving station N receives the signal as indicated by reference numeral 63.

In the time chart shown in FIG. 3, symbol S1 indicates the north timing signal of the adjacent SSR site 50, and symbol S2 receives and detects the mode A / C response from the mode A / C machine 60 by the reception / detection means 12. A signal (mode A / C response data) obtained by decoding by the SSR response decoding means 12 is shown.
Symbol S3 indicates a GPS 1PPS signal (time signal) extracted by the GPS reception / time extraction means 16B, and symbol S4 indicates a mode A / C extraction gate signal (generated and output at a timing synchronized with the symbol S3). An example of a reference gate signal) is shown.

  Further, symbol S5 is a mode A / C extraction gate signal RT whose generation timing is made irregular using pseudo random data, and shows an example of the irregular gate signal generated and outputted by the pseudo random timing gate generation means 15. .

  That is, the symbols T6, T7, and T8 are arrows indicating that the SSR response of the symbol S2 is a timing at which the mode A / C extraction gate does not continuously enter. Symbol T9 is an arrow indicating that there is a timing when the SSR response of symbol S2 enters the mode A / C extraction gate.

  In FIG. 3, in order to thin out (extract) the mode A / C response from the receiving station 1, a mode A / C extraction gate RT (irregular extraction gate signal) having a Tac time width per second is generated. The mode A / C response is output from the receiving station 1 to the position information calculating means 120 only for the time.

  Considering a plurality of aircraft and a plurality of SSR ground stations as an actual environment, a response as shown in S2 is input to the receiving station over all time zones. However, for the sake of simplicity, the response from one mode A / C machine is displayed here.

  As indicated by this symbol S5, the extraction timing is shifted pseudo-randomly with respect to the GPS second, so there is a mode A / C response that is thinned out, but at an extraction gate at some timing as shown at timing T9. Since it is picked up, there is no inconvenience that a specific mode A / C response is always removed regularly.

  Now, suppose that the extraction gate S4 synchronized with GPS true second is applied. If the antenna rotation speed of the adjacent SSR site 50 is a value close to an integral multiple of 1 second, as shown in timings T6 to T8, the signal S4 is always extracted in the same manner as the signal S1 in the mode A / C extraction. A situation occurs in which it is output at a timing that does not enter the gate.

  In this case, when applied to the mode A / C response of the adjacent SSR site 50, the mode A / C response in a certain azimuth range is almost always removed. Therefore, in order to thin out the mode A / C response with the mode A / C extraction gate signal, the pseudo randomness of the gate signal generation is required. Here, thinning out means that in this embodiment, the mode A / C response is specified for this time and transmitted from the receiving station 1 to the position information calculating means 120. The same applies to the description of each content described above.

[Effect of the embodiment]
As described above, in this embodiment, with respect to the mode A / C response received in a large amount at each receiving station 1, 2,... N, each receiving station 1, 2,. By selectively extracting the mode A / C response (transmitting the thinned mode A / C gate signal) by the mode A / C extraction gate signal generated at a predetermined pseudo-random timing, It has the feature that the number of mode A / C responses from each receiving station can be reduced without continuously deleting mode A / C responses from a specific aircraft.

  Regarding the embodiment described above, the main points of the new technical contents are summarized as follows. The present invention is not necessarily limited to this.

(Appendix 1)
A plurality of receiving stations for receiving a squitter signal or SSR reply signal target is transmitted from the transformer responder for mounting such as an aircraft is provided as a ground station at a predetermined distance from each other, it is received by the plurality of receiving stations A multi-lateration comprising a center station as a target processing device that calculates the three-dimensional position information of the target from the arrival time difference of each received signal and obtains identification information from the corresponding target from the received signal In the system,
Each of the receiving stations decodes the received and retrieved SSR response signal to analyze information from the aircraft, a mode S squitter decoded by the SSR response decoding unit, a mode S response, and Message generating means for editing information including mode A / C into a message together with reception time information and outputting the message to the center station;
Between the SSR response decoding means and the message generation means, the mode A / C is sent out to the message generation means after irregularly decimating the mode A / C from the received signal output from the SSR response decoding means. A multilateration system characterized by interposing C signal thinning means.

(Appendix 2)
In the multilateration system described in appendix 1,
Between the SSR response decoding means and the message generating means, one transmission circuit that transmits a signal related to the mode S response, and a signal related to the mode A / C response transmitted together with the one transmission circuit And the other transmission circuit
A multi-lateration system, wherein the mode A / C signal thinning means is arranged on the other transmission circuit side.

(Appendix 3)
In the multilateration system described in appendix 2,
The mode A / C signal decimation means performs the mode A / C signal decimation process executed by the mode A / C signal decimation means for decimation that is externally input and changes irregularly over time. A multilateration system characterized by being executed based on a random timing gate signal.

(Appendix 4)
In the multilateration system described in appendix 3,
In addition to the mode A / C signal thinning means, a pseudo random timing gate signal generating means for generating the random timing gate signal for the thinning is provided,
A multilateration system comprising reference signal generation means for generating a reference gate signal for generating the random timing gate signal in addition to the pseudo random timing gate signal generation means.

(Appendix 5)
In the multilateration system described in appendix 4,
The reference signal generating means includes a GPS receiving antenna that receives a GPS signal, and a GPS reception / time information extracting means that extracts the received GPS second,
The multi-lateration system, wherein the GPS reception / time information extraction means includes a reference gate signal generation function for generating a reference gate signal for generating the random timing gate signal based on the GPS second.

(Appendix 6)
A plurality of receiving stations for receiving a squitter signal or SSR reply signal target is transmitted from the transformer responder for mounting such as an aircraft is provided as a ground station at a predetermined distance from each other, it is received by the plurality of receiving stations A multi-lateration comprising a center station as a target processing device that calculates the three-dimensional position information of the target from the arrival time difference of each received signal and obtains identification information from the corresponding target from the received signal In the system,
SSR response decoding means decodes the SSR response signal received and taken out by one of the receiving stations, and analyzes information from the aircraft,
Of the information including the mode S squitter, the mode S response, and the mode A / C obtained by being decoded and analyzed by the SSR response decoding unit, the information including the mode S squitter and the mode S response is obtained as the SSR response decoding unit. Is transferred to the message generating means, and for the mode A / C, the mode A / C signal decimating means thins irregularly over time and transfers it to the message generating means.
And over time randomly decimated or the mode A / C signal is fed from the information and the mode A / C signal thinning means including the SSR Mode S squitter and mode S reply is sent directly from the response decoding means A signal processing method of a multilateration receiving station, wherein the message generating means edits the message and outputs the message to the center station.

(Appendix 7)
In the signal processing method of the multilateration system receiving station according to attachment 6,
The mode A / C signal decimation process executed by the mode A / C signal decimation means is a random decimation process that is externally input to the mode A / C signal decimation means and irregularly changes over time. A signal processing method of a multilateration receiving station, which is performed based on a timing gate signal.

(Appendix 8)
In the signal processing method of the multilateration system receiving station according to attachment 7,
The random timing gate signal for decimation generates a reference gate signal for capturing a mode A / C signal based on the timing of the received GPS signal while the reference signal generating means receives the GPS signal.
A multilateration receiving station, wherein the output timing of each gate pulse constituting the generated reference gate signal is generated by controlling the output so that the pseudo-random timing gate signal generating means irregularly changes. Signal processing method.

(Appendix 9)
A plurality of receiving stations for receiving a squitter signal or SSR reply signal target is transmitted from the transformer responder for mounting such as an aircraft is provided as a ground station at a predetermined distance from each other, it is received by the plurality of receiving stations A multi-lateration comprising a center station as a target processing device that calculates the three-dimensional position information of the target from the arrival time difference of each received signal and obtains identification information from the corresponding target from the received signal In the system,
An SSR response signal analysis processing function for analyzing the information from the aircraft by decoding the SSR response signal received and taken out by one of the receiving stations;
Of the information including the mode S squitter, the mode S response, and the mode A / C obtained by decoding and analyzing, the information including the mode S squitter and the mode S response is used for message generation , and the mode A / C also for irregularly thinning out over time for message generation ,
And the information and the time irregularly decimated mode A / C signal including the Mode S squitter and Mode S responses identified as for the message generator, to edit the form of the message the center station Message generation output processing function to output,
And a multi-lateration receiving station signal processing program characterized in that each of these functions is realized by a computer.

(Appendix 10)
In the signal processing program for a multi-lateration system receiving station according to attachment 9,
A thinning process execution function for executing the thinning process of the mode A / C signal based on a random timing gate signal for thinning that is input externally and changes irregularly with time is provided, and this is realized by the computer. A signal processing program for a multi-lateration receiving station.

  This is a method suitable for signal processing of a signal centralized receiving station in which a plurality of pieces of information are sent continuously and continuously from a plurality of locations at a constant period.

1, 2... N receiving station 1a, 2a,... Na L-band omnidirectional antenna 11 receiving / detecting means 12 SSR response decoding means 12A one transmission circuit 12B other transmission circuit 13 message generating means 14 mode A / C signal Thinning means (mode A / C signal selection extracting means)
15 Pseudo random gate generation means 16 Reference signal generation means 16A GPS antenna 16B GPS reception / time extraction means 60 Mode A / C machine 61 Mode A / C question and response 62 Mode S response 63 Mode A / C response 70 Mode S machine 120 Position information extraction means 130 Control support means S1 North signal timing of adjacent SSR site S2 Mode A / C response example to question from adjacent SSR site S3 Time signal from GPS (1PPS signal)
S4 Mode A / C extraction gate signal synchronized with the 1PPS signal S5 Mode A / C extraction gate signal generated at random timing Td Delay time from GPS exact second Tac Mode A / C extraction gate signal Time span

Claims (10)

A plurality of receiving stations for receiving a squitter signal or SSR reply signal target is transmitted from the tiger down Suponda mounting such as an aircraft is provided as a ground station at a predetermined distance from each other, it is received by the plurality of receiving stations A multi-lateration comprising a center station as a target processing device that calculates the three-dimensional position information of the target from the arrival time difference of each received signal and obtains identification information from the corresponding target from the received signal In the system,
Each of the receiving stations decodes the received and retrieved SSR response signal to analyze information from the aircraft, a mode S squitter decoded by the SSR response decoding unit, a mode S response, and Message generating means for editing information including mode A / C into a message together with reception time information and outputting the message to the center station;
Between the SSR response decoding means and the message generation means, the mode A / C is sent out to the message generation means after irregularly decimating the mode A / C from the received signal output from the SSR response decoding means. A multilateration system characterized by interposing C signal thinning means. The multilateration system according to claim 1,
Between the SSR response decoding means and the message generating means, one transmission circuit that transmits a signal related to the mode S response, and a signal related to the mode A / C response transmitted together with the one transmission circuit And the other transmission circuit
A multi-lateration system, wherein the mode A / C signal thinning means is arranged on the other transmission circuit side. The multilateration system according to claim 2,
The mode A / C signal decimation means performs the mode A / C signal decimation process executed by the mode A / C signal decimation means for decimation that is externally input and changes irregularly over time. A multilateration system characterized by being executed based on a random timing gate signal. The multilateration system according to claim 3, wherein
In addition to the mode A / C signal thinning means, a pseudo random timing gate signal generating means for generating the random timing gate signal for the thinning is provided,
A multilateration system comprising reference signal generation means for generating a reference gate signal for generating the random timing gate signal in addition to the pseudo random timing gate signal generation means. The multilateration system according to claim 4,
The reference signal generating means includes a GPS receiving antenna that receives a GPS signal, and a GPS reception / time information extracting means that extracts the received GPS second,
The multi-lateration system, wherein the GPS reception / time information extraction means includes a reference gate signal generation function for generating a reference gate signal for generating the random timing gate signal based on the GPS second. A plurality of receiving stations for receiving a squitter signal or SSR reply signal target is transmitted from the tiger down Suponda mounting such as an aircraft is provided as a ground station at a predetermined distance from each other, it is received by the plurality of receiving stations A multi-lateration comprising a center station as a target processing device that calculates the three-dimensional position information of the target from the arrival time difference of each received signal and obtains identification information from the corresponding target from the received signal In the system,
SSR response decoding means decodes the SSR response signal received and taken out by one of the receiving stations, and analyzes information from the aircraft,
Of the information including the mode S squitter, the mode S response, and the mode A / C obtained by being decoded and analyzed by the SSR response decoding unit, the information including the mode S squitter and the mode S response is obtained as the SSR response decoding unit. Is transferred to the message generating means, and for the mode A / C, the mode A / C signal decimating means thins irregularly over time and transfers it to the message generating means.
And over time randomly decimated or the mode A / C signal is fed from the information and the mode A / C signal thinning means including the SSR Mode S squitter and mode S reply is sent directly from the response decoding means A signal processing method of a multilateration receiving station, wherein the message generating means edits the message and outputs the message to the center station. In the signal processing method of the multilateration system receiving station according to claim 6,
The mode A / C signal decimation process executed by the mode A / C signal decimation means is a random decimation process that is externally input to the mode A / C signal decimation means and irregularly changes over time. A signal processing method of a multilateration receiving station, which is performed based on a timing gate signal. In the signal processing method of the multilateration system receiving station according to claim 7,
The random timing gate signal for decimation generates a reference gate signal for capturing a mode A / C signal based on the timing of the received GPS signal while the reference signal generating means receives the GPS signal.
A multilateration receiving station, wherein the output timing of each gate pulse constituting the generated reference gate signal is generated by controlling the output so that the pseudo-random timing gate signal generating means irregularly changes. Signal processing method. A plurality of receiving stations for receiving a squitter signal or SSR reply signal target is transmitted from the tiger down Suponda mounting such as an aircraft is provided as a ground station at a predetermined distance from each other, it is received by the plurality of receiving stations A multi-lateration comprising a center station as a target processing device that calculates the three-dimensional position information of the target from the arrival time difference of each received signal and obtains identification information from the corresponding target from the received signal In the system,
An SSR response signal analysis processing function for analyzing the information from the aircraft by decoding the SSR response signal received and taken out by one of the receiving stations;
Of the information including the mode S squitter, the mode S response, and the mode A / C obtained by decoding and analyzing, the information including the mode S squitter and the mode S response is used for message generation , and the mode A / C also for irregularly thinning out over time for message generation ,
And the information and the time irregularly decimated mode A / C signal including the Mode S squitter and Mode S responses identified as for the message generator, to edit the form of the message the center station Message generation output processing function to output,
And a multi-lateration receiving station signal processing program characterized in that each of these functions is realized by a computer. In the signal processing program for a multi-lateration system receiving station according to claim 9,
A thinning process execution function for executing the thinning process of the mode A / C signal based on a random timing gate signal for thinning that is input externally and changes irregularly with time is provided, and this is realized by the computer. A signal processing program for a multi-lateration receiving station.

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