JP5422998B2 - Radar tracking device, radar tracking method and program - Google Patents

Description

  The present invention relates to target tracking (radar tracking) by a radar, and more particularly to a radar tracking device, a radar tracking method, and a program using a precision approach radar.

Background of the Invention

  As a related technique of the present invention, a radar control device using a precision approach radar (hereinafter referred to as “PAR”) that captures and tracks a target by two-dimensional electronic scanning is known (Patent Documents 1 and 2). ).

  FIG. 10 is a diagram showing one principle of a PAR beam scanning method according to the related art of the present invention. In this beam scanning method, prior to irradiation with a tracking beam, a search plane is searched sequentially with a search beam, and a target to be tracked is detected in advance.

  In the search mode, the PAR 100 scans from the upper left to the lower side of the search surface 200 as shown in FIG. 10A, and searches to the right end by similar scanning while sequentially shifting the beam to the right. In the tracking mode, the beam is tracked in the target A and B directions detected by the tracking beam 300. In this example, as shown in FIG. 10B, tracking scanning is performed three times for each of the targets A and B during one search data rate (see Patent Document 1, FIG. 3).

  Further, Patent Document 1 discloses a search necessary for PAR by using target wake data obtained by ASR (Airport Surveillance Radar: Airport Surveillance Radar) / SSR (Secondary Surveillance Radar: Secondary Surveillance Radar) for PAR. It is also disclosed that the irradiation time of the tracking beam with respect to the targets A and B is increased by eliminating the beam and allocating the free time to the tracking beam.

  FIG. 11 is a diagram showing an example of a PAR tracking beam setting method according to the related art of the present invention. With respect to the number of tracking beams, the number of tracking beams equal to the required maximum number of simultaneous tracking targets is scheduled in a fixed manner by time division in advance (see Patent Document 2 and FIG. 5). It has also been disclosed to allocate two tracks so that the update rate is quasi-doubled for one target by halving the maximum simultaneous tracking target number from 15 to 7 by mode switching SW ( Patent Document 2, paragraph 0029).

JP-A-3-242579 JP 2008-197034 A

  With respect to the tracking beam, there is a method in which the number of tracking beams equal to the maximum number of simultaneous tracking targets is fixedly scheduled in advance by time division as described in Patent Document 2, but in this method, tracking processing is continued. The search beam and the tracking beam for the maximum number of tracking targets are transmitted and received within a necessary limited tracking cycle (data rate for updating the tracking processing result).

  As described above, in the method of securing the fixed maximum number of tracking targets and the tracking cycle (tracking result update time interval), the tracking beam irradiation time per aircraft is limited, and the detection capability is also limited. There's a problem. This is basically the same even if the maximum number of simultaneous tracking targets is reduced by half from 15 to 7 with the mode switching SW.

  Further, in Patent Document 1, by using the target track data obtained by ASR / SSR for PAR, the search beam necessary for PAR is eliminated, and the free time is allocated to the tracking beam, and the tracking beam Increasing the irradiation time is disclosed.

  However, in the invention of Patent Document 1, no consideration is given to the control of the number of tracking beams, the schedule thereof, and the like with respect to the landing guidance state that changes from moment to moment with respect to the target entering and landing in the covered area.

  Since the precision approaching radar uses microwaves in the high frequency band of the X band, it is more susceptible to power attenuation during rainfall than ASR and SSR. Increasing the number of transmitted and received pulse hits is effective to improve the detection capability during rainfall, but on the other hand, it is desirable to increase the number of aircraft that can be guided to land at the same time. is important.

  From the above, there is a need for a method that can achieve both improvement in detection capability and increase in the number of simultaneous tracking targets in accordance with the target landing guidance status without significantly increasing the scale of the radar tracking device.

(the purpose)
An object of the present invention is to solve the above-described problems, and to provide a radar tracking device, a radar tracking method, and a program capable of improving the detection capability.

A radar tracking device according to a first aspect of the present invention is a radar tracking device using PAR, which calculates the number of landing guidance aircraft for each time based on flight information of an aircraft input from an external system, and Control means for controlling the number of tracking beams for each PAR time according to the number, and the control means uses the flight information of the aircraft input from the external system to enter the PAR coverage area and landing time of each aircraft A means for calculating and predicting the number of landing guides present in the PAR coverage simultaneously from the approach time and the landing time of each aircraft, and according to the number of landing guides Operation mode management data including the number of tracking beams for each time is generated, the PAR is controlled by the operation mode management data, and tracking beacons for each PAR time according to the number of landing guides Characterized in that it comprises means for controlling the.

According to a first radar tracking method of the present invention, in the radar tracking method using the PAR, a first step of inputting aircraft flight information from an external system, and the flight information of the aircraft into the PAR coverage of each aircraft. And calculating the number of landing guides for each time existing in the PAR coverage simultaneously from the approach time and the landing time of each aircraft. A second step of generating operation mode management data including the number of tracking beams for each time according to the number, and the PAR is controlled by the operation mode management data, and the PAR according to the number of landing guides And a third step of controlling the tracking beam for each time .

A first program of the present invention is a radar tracking device program using PAR, wherein a first step of inputting flight information of an aircraft from an external system to a computer, and the PAR of each aircraft from the flight information of the aircraft. Predicting and calculating the approach time and landing time in the coverage area, calculating the number of landing guidance aircraft for each time existing in the coverage area of the PAR simultaneously from the approach time and the landing time of each aircraft, A second step of generating operation mode management data including the number of tracking beams for each time according to the number of landing guides; and the PAR is controlled by the operation mode management data, according to the number of landing guides And a third step of controlling the tracking beam for each time of PAR .

  According to the present invention, it is possible to increase the number of pulse hits per target (tracking beam irradiation time) by minimizing the number of tracking beams that perform time-division transmission / reception according to the number of landing guides, When the number of landing guidance target aircraft is small, it is possible to improve the detection capability of PAR.

  In addition, when the number of landing guidance target aircraft is large, the number of tracking beams is increased within a predetermined upper limit, and tracking processing can be performed in time division, so that multi-target simultaneous tracking is possible.

(Embodiment of the Invention)
Embodiments of a radar tracking device, a radar tracking method, and a program according to the present invention will be described.

(First embodiment)
FIG. 1 is a diagram showing a configuration of a radar tracking device and a radar tracking method according to a first embodiment of the present invention. As shown in FIG. 1A, the radar tracking device according to the first embodiment has flight information (target tracking information) such as target data of ASR / SSR (airport monitoring radar and secondary monitoring radar), flight plan data, and the like. And an external system 1 that provides a control unit 2 that calculates the number of landing guidance aircraft for each time based on the flight information and sets the number of tracking beams for each PAR time according to the number of landing guidance aircraft; PAR (Precision Approach Radar) 3 in which the number of tracking beams for each time is controlled by the control means 2.

  More specifically, the control means 2 uses the flight plan data of the external system 1 or the track data of the aircraft such as ASR / SSR, and the time of entry of each aircraft heading to its own airport into the PAR3 coverage area and its own airport. Means for calculating the landing time, means for obtaining the number of aircraft (number of aircraft) existing in the coverage area of PAR3 for each time from the relationship between the arrival time and landing time of each arrival aircraft, and a beam schedule corresponding to the number of aircraft Means for creating such operation mode management data and outputting it to the PAR 3 to control the PAR 3 is provided. PAR3 increases or decreases the number of tracking beams for each time according to the operation mode management data.

  As shown in FIG. 1B, the radar tracking method of the first embodiment includes a first step (s1) for inputting flight information from an external system, and landing guidance for each time based on the flight information. It comprises a second step (s2) for calculating the number of aircraft and a third step (step s3) for controlling the number of tracking beams for each PAR time according to the calculated number of landing guidance aircraft.

  According to this embodiment, the maximum number of simultaneous tracking targets can be achieved without increasing the size of the apparatus, such as increasing the size of the PAR antenna by increasing or decreasing the number of tracking beams according to the number of landing guidance aircraft. In addition, it is possible to further improve the tracking target detection ability.

  In other words, when the number of landing guides is small, it is possible to reduce the number of tracking beams and irradiate the tracking beams intensively to aircraft that require landing guidance, thereby increasing the detection capability. . Further, when the number of landing guides is large, simultaneous tracking in time division is possible by increasing the number of tracking beams as in the case of normal PAR.

(Second Embodiment)
(Description of configuration)
Next, a second embodiment of the radar tracking device and radar tracking method of the present invention will be described in detail with reference to a configuration example applied to a radar control device.

  FIG. 2 is a diagram showing the configuration of the radar control apparatus according to the second embodiment of the present invention. This radar control apparatus includes an external system ASR / SSR (airport monitoring radar and secondary monitoring radar) 10 that outputs target data, an external system 40 that outputs flight plan data, and a PAR (precision measurement radar) at each time. ) Of central tracking device 20 having a function of automatically or manually setting the number of tracking beams (target number for performing simultaneous tracking by time division), and an operation including the relationship between the time obtained from central control device 20 and the number of required tracking beams Based on the mode management data, the tracking beam schedule and the PAR 30 in which the system timing (operation mode) is controlled.

Hereinafter, the configuration of the central control device 20 and the PAR 30 and the function of each unit will be described.
The central control device 20 has a function equivalent to that of a central control device of a normal radar control device, and as a means for automatically or manually setting the number of tracking beams of PAR for each time, a tracking processing unit 21 and a flight plan operation A console 22, a control console 23, a coordinate conversion unit 24, a landing guidance time management unit 25, a landing guidance time display control unit 26 installed in one or both of the flight plan console 22 and the control console 23, . The function of each part is as follows.

  The tracking processing unit 21 generates track data of ASR / SSR coordinates (including predicted position and speed vector information of tracking processing) obtained by tracking / identification based on target data and flight plan data from the ASR / SSR 10. It has a function.

  The coordinate conversion unit 24 has a function of converting the wake data into data of a coordinate system (PAR coordinates) whose origin is the PAR 30.

  The flight plan console 22 has a function of inputting flight plan data from the external system 40 and outputting the flight plan data for the arrival aircraft to the landing guidance time management unit 25. The control console 23 has the ASR / SSR coordinates. It has a function of inputting wake data and wake data of PAR coordinates, and performing radar display using a switchable ASR / SSR screen and PAR screen.

  The landing guidance time management unit 25 constitutes the control means of the present invention. As an automatic setting means based on the flight plan, the arrival time (ETA: Estimate Time) of the arrival plan of the flight plan data input from the external system 40 is used. of arrival), predicting the time (entry time) to enter the coverage area of PAR30 and the time to land (landing time), calculate the number of targets arriving at the airport and the time required for landing guidance, It has a function of creating operation mode management data indicating the relationship between the time and the number of tracking beams and outputting it to the PAR 30.

  The landing guidance time display control unit 26 constitutes the display control means of the present invention, and is mounted on one or both of the flight plan console 22 and the control console 23 that are always used by the operator from the viewpoint of operability. The function of changing the contents of the operation mode management data and the like by the manual input operation by the operator as a manual setting means on the display screen displaying the contents of the operation mode management data and the like for the PAR 30 created by the landing guidance time management unit 25 Have In the configuration example shown in FIG. 2, the landing guidance time display control unit 26 is mounted on both the flight plan console 22 and the control console 23, and manual data generated by an operator's operation is determined from either landing guidance time management unit 25. Can be output.

  The PAR 30 includes a tracking control unit 31, a transmission / reception unit 32, an antenna 33, and a target detection unit 34. The function of each part is as follows.

  The tracking control unit 31 has a function of updating the operation mode data at the time when the number of tracking beams is changed based on the operation mode management data obtained from the central control device 20 and outputting the updated data to each component device of the PAR 30. In addition, it has a function of changing the number of tracking beams, that is, the number of simultaneous tracking targets in time division, according to the operation mode data. Furthermore, the target detection data near the predicted position is extracted from the target detection data input from the target detection unit 34, and beam control data for the predicted direction is set for the antenna 33.

  The transmission / reception unit 32 has a function of changing the system timing to the timing of the operation mode in accordance with the operation mode data input from the tracking control unit 31 and outputting it to each component device of the PAR 30.

  The antenna 33 has a function of transmitting and receiving a tracking beam based on the operation mode data and beam control data received from the tracking control unit 31 and the system timing from the transmitting and receiving unit 34 and outputting a received signal to the transmitting and receiving unit 34.

  The target detection unit 34 has a function of detecting a target from the received video data input from the transmission / reception unit 32 by a method such as threshold detection with respect to the amplitude and outputting the target detection data to the tracking control unit 31 for tracking or the like. .

(Description of operation)
Next, the operation of the second exemplary embodiment of the present invention will be described in detail with reference to the drawings.

  The outline of the operation in the central control device 20 of the present embodiment is divided into an operation for generating and displaying wake data from target data of the ASR / SSR 10 and an operation for generating operation mode management data for controlling the PAR 30 from the flight plan data. .

  First, the generation and display operations of wake data in the tracking processing unit 21, the coordinate conversion unit 24, and the control console 23 will be described.

  The tracking processing unit 21 of the central control device 20 provides true data corresponding to the flight plan data input via the flight plan console 22 from the target position data (distance, azimuth, altitude) input from the ASR / SSR 10. The target data is identified and the target data is tracked.

  The track data of the ASR / SSR coordinates obtained by the tracking processing unit 21 (including the predicted position and the velocity vector information of the tracking processing) are stored in the coordinate system (distance, azimuth, elevation angle) that is the origin of the PAR 30 in the coordinate conversion unit 24. It is converted and output to the landing guidance time management unit 25, the control console 23, and the tracking control unit 31 of the PAR 30.

  The control console 23 includes a radar display screen that can be switched between an ASR / SSR screen and a PAR screen. The PAR screen selectively displays the PAR coordinate track data based on the ASR / SSR 10 track data. It is possible.

  As a result, the operator can visually recognize the target as a target being tracked by the ASR / SSR 10 on the PAR screen of the control console 23 even if the PAR 30 has not yet started transmission / reception of the tracking beam. .

  Next, the operation | movement which produces | generates operation mode management data from the flight plan data in the flight plan console 22 and the landing guidance time management part 25 is demonstrated.

  The operation of generating the operation mode management data of the present embodiment is to first predict the entry time of the target aircraft into the PAR 30 coverage area and the landing time of the own airport using the flight plan, and secondly The target number within the predicted landing guidance time is predicted from the approach time and the landing time, and operation mode management data of the PAR 30 is generated.

  First, the operation of calculating (predicting) the approach time and landing time of the target aircraft from the flight plan data in the flight plan console 22 and the landing guidance time management unit 25 will be described.

  FIG. 3 is a diagram showing various data handled by the flight plan console 22 and the landing guidance time management unit 25. (A) shows flight plan data (partial), various data such as average speed at landing, predicted landing guidance time and timetable for landing guidance time, and (B) shows operation mode management including the number of tracking beams. It is data.

  Here, the flight plan data indicates the name of the arrival aircraft, the model, and the final FIX (final position), and includes the estimated arrival time (ETA). Further, the operation mode management data is shown as time vs. number of tracking beams, operation mode and the like.

  The flight plan console 22 refers to flight plan data input from an external system, extracts flight plan data for arrival aircraft from the flight plan data, and outputs the flight plan data to the landing guidance time management unit 25.

  The landing guidance time management unit 25 includes the model of the arrival aircraft, the estimated arrival time (ETA), the flight route FIX (each coordinate on the flight route), and the PAR30 registered in advance as a database. Based on the coverage, the average speed for each model, and the maximum delay time, the entry time and landing time are predicted for each arrival aircraft.

  First, as an example when the final FIX of the flight plan data is the own airport (represented by the symbol RJZZ), the arrival aircraft A1 in FIG. 3 will be described.

  Flight plan data ETA (estimated arrival time) 0020 (time 0:20) is the estimated arrival time at the airport (or above). For this reason, the approach time Ts1 and the landing time Te1 into the PAR coverage area are obtained by the following equations.

Ts1 = ETA (time 0020) -R / v1
However,
R: Maximum PAR coverage distance v1: Average speed of model XX Te1 = ETA (time 0020) + Td1
However, Td1: Maximum delay time of model XX The above formula shows a simple example, and more accurately using the flight route data registered in the flight plan and the approach route determined by the runway direction R in the above equation may be obtained by adding the distances of the flight path from the PAR coverage boundary to the own airport.

  Next, the arrival aircraft A2 in FIG. 3 will be described as an example of the case where the final FIX of the flight plan data is not the own airport (represented by the final FIX = FIX9).

  FIG. 4 is a diagram showing a flight example of the PAR coverage when the final FIX of the flight plan data is not the own airport. The final FIX = FIX9 is located at the route distance from the own airport within the maximum covered area distance R to R9 (between FIX9 and RJZZ).

  In this case, the approach time Ts2 and the landing time Te2 of the arrival aircraft A2 into the PAR coverage area are simply obtained by the following equations.

Ts2 = (Te2-Td2) -R / v2
Te2 = (ETA (fixed FIX9 passing (arrival) time 0015) + R9 / v2) + Td2
However, R9: Path distance between FIX9 and RJZZ R: Maximum PAR coverage distance v2: Average speed of model YY Td2: Maximum delay time of model YY Again, using the flight path and approach path of flight plan data, Ts2 and Te2 may be obtained in more detail.

  As described above, the landing guidance time management unit 25 determines the approach time, the landing time, and the landing guidance time for each of the arrival aircrafts A1, A2, A3, etc. based on the flight plan data. It is possible to generate a timetable.

  Next, an operation for generating operation mode management data for the PAR 30 from the timetable data shown in FIG.

  The landing guidance time management unit 25 obtains the number of tracking beams required for each time from the timetable shown in FIG. 3A, generates operation mode management data including the time versus number of tracking beams for the PAR 30, and the like. Output to the tracking control unit 31 and the landing guidance time display control unit 26 of the central control device 20.

  The landing guidance time display control unit 26 includes a radar display screen, and displays a timetable relating to each arrival aircraft in the form shown in FIGS. 3A and 3B, for example. Therefore, it is possible for the operator to manually edit the timetable of each arrival aircraft.

  Here, the contents of the operation mode management data generated by the landing guidance time management unit 25 are selected from the cases (a) to (c) of FIG. Make it possible.

  Hereinafter, the cases (a) to (c) shown in FIG. 3B will be described in detail.

Fig. 3 (a): Case where importance is placed on detection ability (minimum number of tracking beams)
When the detection capability is given the highest priority, it is effective to reduce the number of tracking beams and irradiate the tracking beam intensively on the target target. Therefore, the minimum required tracking target number (minimum required tracking beam number) Nmin for each time is obtained by counting the number of targets that exist simultaneously from the approach time to the landing time of each target. The PAR operation mode is set according to the number of Nmin. In this case, the number of tracking beams can be the number of landing guides for each time.

Fig. 3 (b): Case of simplifying control of operation mode (maximum number of tracking beams)
In order to simplify the control of the operation mode, it is effective to prohibit the change of the operation mode during the tracking beam irradiation. In this case, the operation mode is set in accordance with the maximum number Nmax of aircraft with which landing guidance time zones overlap.

  In this case, as the case where a plurality of landing guidance time zones overlap at least partially, the number of tracking beams in the plurality of landing guidance time zones is the maximum number of landing guidance aircraft in the plurality of landing guidance time zones. Can be a number.

Fig. 3 (c): Intermediate case of the above (a) and (b) At the beginning of landing guidance, since the target is relatively far away, emphasis is placed on detection ability as much as possible, but at the end of landing guidance, control is easier than detection ability If you want to focus on. In this case, as shown in FIG. 3C, the operation mode is set so that Nmin is prioritized at the start of tracking and Nmax is prioritized (that is, continued without changing the operation mode) at the end of tracking.

  In this case, as the case where a plurality of landing guidance time zones partially overlap, the number of tracking beams in the plurality of landing guidance time zones is the highest since the earliest tracking start of the plurality of landing guidance time zones. The period from the start of the slowest tracking to the end of the latest tracking is the maximum number of landing guides in the period from the start of the latest tracking to the end of the latest tracking. be able to.

  Furthermore, examples of contents of the operation modes T1 and T2 in the cases (a) to (c) of FIG. 3B will be described in detail below.

  FIG. 5 is a diagram showing an example of the operation mode. It is an example of a search no mode, a search existence mode, and a high data rate mode. Each of these operation modes can also be selected by the operator using the landing guidance time display control unit 26.

Fig. 5 (1) (2): Search-free mode (T1, T2)
When the highest priority is placed on the target detection performance, the time within the tracking period is allocated to the tracking beams for the required number of tracking targets.

Fig. 5 (3) (4): Search mode (ST1, ST2)
When it is desired to monitor the coverage area with the PAR 30 at the same time as tracking, both search time and tracking time are allocated within the tracking period. That is, T1 and T2 in FIG. 3 are replaced with ST1 and ST2 in FIGS. 5 (3) and 5 (4), respectively. However, in this case, the tracking beam detection capability is lower than in the search-free mode.

5 (3) and (4): High data rate mode (DT1, DT2)
When priority is given to the continuity of tracking, the tracking data rate (tracking cycle) is improved as shown in FIGS. That is, T1 and T2 in FIG. 3 are replaced with DT1 and DT2 in FIGS. 5 (5) and (6), respectively.

  Here, every time the number of tracking beams (number of tracking targets) within one tracking cycle increases, the number of pulse hits per target is limited and the detection capability decreases. Therefore, it is necessary to set an upper limit for the number of tracking beams according to the operational requirements of the PAR 30.

  In order to realize the operation mode as described above, the landing guidance time management unit 25 determines the number of tracking for each aircraft within the tracking period of the PAR 30 and the tracking order of the aircraft in addition to the relationship between the time and the number of tracking beams. Operation mode management data including data to be controlled is generated, and the operation mode management data is output to the landing guidance time display control unit 26 and the tracking control unit 31 of the PAR 30, and the tracking number of each PAR 30 for each aircraft, the tracking order of the aircraft, etc. The operation mode can be controlled.

  Next, the general operation of the PAR 30 will be described.

  The tracking control unit 31 of the PAR 30 obtains the operation mode management data from the landing guidance time management unit 25 prior to the start of the landing guidance, and is designated by the operation mode management data when the approach time of the landing guidance target is included. It waits to perform the tracking process for the target aircraft in the operation mode including the number of tracking beams.

  The position of the landing guidance target aircraft is detected by the ASR / SSR 10, and the wake data is converted into the PAR coordinate system via the coordinate conversion unit 24 of the central control device 20 and sequentially input to the tracking control unit 31.

  The tracking control unit 31 of the PAR 30 updates the operation mode data when it reaches the target entry time into the PAR coverage area that has been input in advance as the operation mode management data, and sends it to each component device of the PAR 30 and also performs coordinate conversion. Beam control data for the direction of the target predicted position obtained from the unit 24 is generated and output to the antenna 33. In addition, a transmission start instruction signal is output to the transmission / reception unit 32.

  The transmission / reception unit 32 generates a system timing signal according to the operation mode data input from the tracking control unit 31, outputs the system timing signal to each component device of the PAR 30, and performs a tracking beam transmission / reception process with respect to the antenna 33.

  As a result, the PAR 30 can operate by changing the operation mode at each time according to the operation mode management data.

The operation of the PAR of this embodiment after the operation mode is changed is as follows.
That is, the antenna 33 performs transmission / reception by the tracking beam and outputs a reception signal to the transmission / reception unit 32. The transmission / reception unit 32 outputs the reception signal received from the antenna 33 to the target detection unit 34 as reception video data. The target detection unit 34 performs target detection processing using the received video data, and outputs the result to the tracking control unit 31 as target detection data.

  Next, the tracking control unit 31 extracts target detection data in the vicinity of the predicted position from the target detection data, sets beam control data for the predicted direction for the antenna 33, and the antenna 33 transmits and receives the next tracking beam. By repeating the above operation, the target tracking process using the tracking beam is performed.

  Hereinafter, the operation mode changing operation of the PAR 30 of this embodiment will be described in detail focusing on the vicinity of the times Ts1 and Ts2 in the modes (a) and (c) of FIG.

  FIG. 6 is a diagram showing an operation example for controlling the operation mode for each tracking period per target. An example is shown in which the tracking control unit 31 applies the operation mode to the next tracking cycle in which the content of the operation mode is instructed to each component device in the PAR. However, these timing control procedures are merely examples, and are not limited as operations of the embodiment of the present invention.

First, the operation near the time Ts1 will be described.
At a time before time Ts1, according to the contents set by the landing guidance time display control unit 26 by the operator, the search process in the PAR coverage area is performed by the search beam when there is a search, and the beam is not transmitted when there is no search. stand by. Note that the non-transmission state when no search is performed also contributes to a reduction in the power consumption of the PAR.

  As shown in FIG. 6 (1), the tracking control unit 31 transmits the operation mode management data “T1” to each component of the PAR such as the transmission / reception unit 32, the antenna 33, the target detection unit 34, etc. in the next tracking cycle that has reached Ts1. Send to device. Further, the tracking control unit 31 transmits beam control data based on the track data input from the ASR / SSR 10 to the antenna 33 before starting transmission / reception, and outputs a tracking beam transmission / reception start instruction to the transmission / reception unit 32. .

  As shown in FIG. 6 (2), the transmission / reception unit 32 receives the operation mode management data “T 1” from the tracking control unit 31, and the system timing corresponding to the operation mode for each component device inside the PAR 30. Output a signal. In addition, a transmission signal is transmitted to the antenna 33 at the system timing, reception video data is created from the signal received via the antenna 33, and is output to the target detection unit 34.

  The target detection unit 34 performs target detection processing by a method such as threshold detection for the amplitude of the received video, and outputs target detection data obtained as a result thereof to the tracking control unit 31.

  The tracking control unit 31 extracts data having the highest reliability (for example, data closest to the predicted position) from the target detection data, predicts the target position in the next tracking cycle, and outputs the beam in the predicted direction. Control data is set for the antenna 33.

  By repeating the above operation, the target tracking process in the operation mode “T1” is performed.

Next, the operation at time Ts2 will be described.
When the time Ts2 is reached, as shown in FIG. 6A, the tracking control unit 31 outputs the next operation mode management data “T2” to each component device in the PAR 30.

  Further, as shown in FIG. 6 (2), in this next tracking cycle, each component device simultaneously switches the operation mode to “T 2” and operates in synchronization with the system timing input from the transmission / reception unit 32. Here, in order to facilitate system timing control, the transmission / reception timing per pulse in the operation modes “T1” and “T2” may be the same.

  When the operation mode “T2” is applied, as shown in FIGS. 6 (3) and 6 (4), the time within the tracking period is divided into processes for the arrival aircrafts A2 and A1, and for each of the arrival aircrafts A2 and A1. Tracking beam transmission / reception processing is performed.

  Here, when the initial tracking of the arrival aircraft A2 starts, beam control data is generated based on the track data for the arrival aircraft A2 of the ASR / SSR 10.

  For the arrival aircraft A1, the number of transmission / reception pulse hits is reduced to about ½ of the operation mode “T1”, but the tracking for the arrival aircraft A1 is performed based on the target detection result with the reduced number of pulse hits. Continue processing.

  With the above processing, the PAR 30 tracks both the arrival aircraft A1 and A2 targets.

  When the target is lost, the tracking processing unit 31 continues to track the predicted position (coast tracking) over a preset tracking period, as in the case of normal PAR and general tracking radar. However, when the target is completely lost after the coast tracking is completed, if the track data of the target is continuously input from the ASR / SSR 10, beam control data is generated based on the track data and newly tracked. Resume processing.

  As for the end of tracking, the tracking process is not continued at the landing time Te1 or Te2 predicted in FIG. 3, but the tracking process is continued as long as the target is detected within the coverage area of the PAR.

  As described above, according to the present invention, the number of tracking beams can be changed according to the target number for landing guidance. Therefore, when the number of landing guidance target aircraft is small, the detection capability and tracking data rate per target can be improved, and when the number of landing guidance target aircraft is large, multiple target simultaneous transmission / reception can be performed by time-division tracking beam transmission / reception. Landing guidance is possible.

  According to the present embodiment, since means for increasing or decreasing the number of tracking beams according to the number of landing guidance is provided, regardless of the increase in the scale of the apparatus such as increasing the size of the PAR antenna, It is possible to further improve the tracking target detection capability while securing the maximum number of simultaneous tracking targets.

  Thereby, in the time zone when the number of landing guidance machines is small, the number of tracking beams can be reduced, and the tracking beams can be intensively irradiated to the landing guidance target. When the number of landing guides is large, the number of tracking beams is increased to enable simultaneous tracking in time division.

(Third embodiment)
In the above second embodiment, the configuration example in which the operation mode management data is created based on the flight plan has been shown. However, the radar tracking device, the radar tracking method, and the program according to the present invention provide the operation mode management data to the tracking processing unit. 21 can be configured to be created on the basis of the track data of the ASR / SSR 10 according to 21.

  FIG. 7 is a diagram showing the configuration of the central control apparatus according to the third embodiment of the present invention. In the third embodiment, the track data generation and display operations by the tracking processing unit 21, the coordinate conversion unit 24, and the control console 23 are the same as those in the second embodiment, but the landing guidance time management of the central control device 20 is performed. The configuration and functions of the units are different from those of the second embodiment.

  The landing guidance time management unit 27 of the third embodiment inputs tracking data output from the coordinate conversion unit 24 instead of the flight plan data as flight information. That is, the landing guidance time management unit 27 performs tracking based on target data from the ASR / SSR 10 and flight plan data input via the flight plan console 22 as automatic setting means based on tracking information of the ASR / SSR 10. The track data of the ASR / SSR coordinates obtained by tracking / identifying by the processing unit 21 is used as the PAR coordinate track data by the coordinate conversion unit 24, and the track is determined from the predicted position of the track data and the speed vector information of the tracking process. It has a function of creating operation mode management data and outputting it to the PAR 30 by predicting the entry time and the landing time when entering the PAR 30 coverage area set in advance.

  Next, an operation for calculating (predicting) the approach time and the landing time of the target aircraft from the track data of the ASR / SSR 10 in the third embodiment will be described.

  The tracking processing unit 21 of the central control device 20 provides true data corresponding to the flight plan data input via the flight plan console 22 from the target position data (distance, azimuth, altitude) input from the ASR / SSR 10. The target data is identified and the target data is tracked.

  The track data of the ASR / SSR coordinates obtained by the tracking processing unit 21 (including the predicted position and the velocity vector information of the tracking processing) are stored in the coordinate system (distance, azimuth, elevation angle) that is the origin of the PAR 30 in the coordinate conversion unit 24. It is converted and output to the landing guidance time management unit 27, the control console 23, and the tracking control unit 31 of the PAR 30.

  The control console 23 includes a radar display screen that can be switched between an ASR / SSR screen and a PAR screen. The PAR screen selectively displays the PAR coordinate track data based on the ASR / SSR 10 track data. It is possible.

  As a result, the operator can visually recognize the target as a target being tracked by the ASR / SSR 10 on the PAR screen of the control console 23 even if the PAR 30 has not yet started transmission / reception of the tracking beam. .

  The landing guidance time management unit 27 uses the predicted position of the track data of the PAR coordinates input from the coordinate conversion unit 24 and the speed vector information of the tracking process, and thereby arrives in the coverage area of the PAR 30 registered in advance as a database. Predict each entry time and landing time at your airport. Further, the landing guidance time management unit 27 calculates the number of tracking beams from the target number of landing guidance for each time based on the approach time and landing time for each arrival aircraft.

  As described above, from the flight plan data and the ASR / SSR track data, the timetable for the arrival time, landing time and landing guidance time, number of tracking beams, etc. for each arrival aircraft as shown in FIG. Therefore, it is possible to generate operation mode management data.

  Also in the present embodiment, the operation mode management data can be edited by manual input by the operator from the landing guidance time display control unit 26. In addition, since the operations shown in FIGS. 3, 5, and 6 of the PAR 30 controlled by the generated operation mode management data are the same as those in the second embodiment, their descriptions are omitted.

(Fourth embodiment)
As a fourth embodiment of the present invention, by using flight plan data, flight plan data, and ASR / SSR track data, the accuracy of creation of operation mode management data in the landing guidance time management unit is improved. Is possible.

  FIG. 8 is a diagram showing the configuration of the fourth exemplary embodiment of the present invention. In the present embodiment, the landing guidance time management unit 28 inputs flight plan data and tracking data, predicts an approach time, landing time, and the like equivalent to those of the second embodiment from the flight plan data, and flight plan data. And the ASR / SSR track data, and a function of correcting the approach time prediction.

  In the prediction method based on the track data, the closer the target is to the PAR coverage, the higher the accuracy of the prediction of the approach time. Therefore, the prediction result of the approach time according to the flight plan is corrected when the target approaches the PAR coverage. Used for.

For example, an airspace for detecting that the target has approached the outside of the PAR coverage area is set, and when the target enters the airspace, the approach (predicted) time is determined from the flight plan, and the wake data This can be achieved by changing to
The correction of the approach time of the landing guidance time management unit 28 can be configured so as to be automatically executed by an operator's manual input from the landing guidance time display control unit 26.

  In the present embodiment, the landing guidance time management unit 28 inputs the flight plan data and the ASR / SSR track data, so the second embodiment (FIG. 2) and the third embodiment (FIG. 7). ) Of the landing guidance time management unit can be provided, and any one of the flight plan data and the ASR / SSR track data can be manually input from the landing guidance time display control unit 26 by an operator. It is possible to generate operation mode management data based on this and output it to the PAR 30 and the landing guidance time display control unit 26.

  That is, either flight plan data or flight plan data based on flight plan data and ASR / SSR is used as flight information for controlling the number of tracking beams of the PAR 30 by the landing guidance time management unit 28 by manual input of the landing guidance time display control unit 26. Can be switched (selected).

  Further, the landing guidance time display control unit 26 displays the landing speed, approach time, landing time, landing guidance time, and tracking beam timetable for each aircraft based on flight information such as flight plan data or the tracking data. It can be configured so that any one can be changed on the display screen by manual input.

  As described above, the landing guidance time management unit 28 can generate timetables such as the landing guidance time and the number of tracking beams for each arrival aircraft as shown in FIG. 3 from the flight plan data and the track data of ASR / SSR. Accurate operation mode management data can be output. Also in the present embodiment, the operations shown in FIGS. 3, 5, and 6 of the PAR 30 controlled by the generated operation mode management data are the same as those in the second embodiment, and thus the description thereof is omitted.

(Other embodiments)
Next, the processing of the above embodiment can be executed by hardware and can be executed by software. When a series of processing is executed by software, a storage unit storing software program codes for realizing the functions of the above embodiments is provided in an information processing device in the radar control device, and a computer (CPU (Central Processing Unit)) of the device is provided. Processing Unit)) reads and executes the program code.

  Further, a storage medium storing the program code can be used, and the program code can be read from the storage medium and stored in the storage unit. In this case, the program code itself read from the storage medium realizes the functions of the embodiments described above.

  FIG. 9 is a diagram showing a configuration example of the information processing apparatus of the present invention that executes the processing of each embodiment by a program. The information processing apparatus 100 includes a CPU 101, a ROM, a RAM (Random Access Memory), and the like that constitute a computer mutually connected by a bus, an input interface unit 103 with an external system, a display unit, and an operation unit. The display control unit 104 includes the output interface unit 105 with the PAR.

  Various programs including the control program of the above embodiment are stored in the storage unit 102. The CPU 102 reads the program of the storage unit 102, is controlled by the read program, and is a flight from an external system input from the input interface unit 103. In response to flight information such as plan data and ASR / SSR track data, and instructions from the display control unit 104, processing for realizing the various functions described above is executed, operation mode management data is generated, and the output interface unit 103 To PAR to control the operation mode such as the number of PAR tracking beams.

  As described above, according to the present invention, in the PAR (precisely approaching radar) using an electronic scanning antenna or the like, the number of tracking beams is controlled in accordance with the number of aircrafts that perform landing guidance, thereby tracking the landing guidance target aircraft. The irradiation time of the beam can be increased and the detection ability can be improved.

  Specifically, each arrival is based on the flight plan arrival data input from an external system (external organization) and target track data obtained from ASR (airport surveillance radar) and SSR (secondary surveillance radar). The time range in which the machine is present in the PAR coverage area is obtained, then the required number of tracking beams in each time range is obtained, and the operation of the PAR is controlled so that this tracking beam is transmitted and received in a time division manner.

  Thereby, it becomes possible to irradiate the tracking beam intensively to the target aircraft that performs the landing guidance. As a result, the number of pulse hits and the tracking data rate increase, and the PAR detection capability can be improved.

  Thus, since the number of tracking beams can be changed according to the number of landing guides at each time, the detection capability can be improved when the number of landing guides is small. Further, when the number of landing guides is large, the number of tracking beams to be transmitted and received in a time division manner is set in the same manner as in normal PAR, and multi-target landing guidance is possible.

  The embodiments of the present invention are not limited to the above-described embodiments, and it goes without saying that various modifications can be made without departing from the scope of the present invention.

  Since the present invention controls the number of PAR tracking beams for each time based on aircraft flight information, it can be applied to a radar device for air traffic control.

It is a figure which shows the structure of the radar tracking apparatus and radar tracking method of the 1st Embodiment of this invention. It is a figure which shows the structure of the radar control apparatus of the 2nd Embodiment of this invention. It is a figure which shows the various data handled by a flight plan console and landing guidance time management part. It is a figure which shows the example of a flight of the PAR covering area in case the last FIX of flight plan data is not an own airport. It is a figure which shows the example of an operation mode. It is a figure which shows the operation example which controls an operation mode for every tracking period per target. It is a figure which shows the structure of the central control apparatus of the 3rd Embodiment of this invention. It is a figure which shows the structure of the 4th Embodiment of this invention. It is a figure which shows the structural example of the information processing apparatus of this invention which performs the process of each embodiment by a program. It is a figure which shows the principle of the beam scanning method of PAR of the related technology of this invention. It is a figure which shows the example of the setting method of the tracking beam of PAR of the related technology of this invention.

Explanation of symbols

1, 40 External system 2 Control means 3, 30 PAR (Precision Approach Radar)
10 ASR / SSR
20 Central Controller 21 Flight Plan Operator Console 22 Tracking Processor 23 Controller 24 Coordinate Converters 25, 27, 28 Landing Guide Time Management Unit 26 Landing Guide Time Display Controller 30 PAR
31 Tracking Control Unit 32 Transmission / Reception Unit 33 Antenna 34 Target Detection Unit 100 Information Processing Device 101 CPU
102 storage unit 103 input interface unit 104 display control unit 105 output interface unit

Claims (31)

In radar tracking equipment using PAR,
Based on the flight information of the aircraft input from the external system, the number of landing guidance aircraft for each time is calculated, and control means for controlling the number of tracking beams for each PAR time according to the number of landing guidance aircraft ,
The control means includes
Means for predicting and calculating the entry time and landing time of each aircraft into the PAR coverage from the flight information of the aircraft input from the external system;
Means for determining the number of landing guides present in the PAR coverage simultaneously for each time from the approach time and the landing time of each aircraft;
Operation mode management data including the number of tracking beams at each time is generated according to the number of landing guides, the PAR is controlled by the operation mode management data, and each PAR time according to the number of landing guides A radar tracking device comprising means for controlling a tracking beam of the radar. 2. The radar tracking device according to claim 1, wherein the operation mode management data includes data for controlling the number of tracking for each aircraft within the tracking period of the PAR and the tracking order of the aircraft. The radar tracking device according to claim 1, further comprising display control means capable of changing the operation mode management data generated by the control means on a display screen by manual input. The display control means can display the landing speed, approach time, landing time and landing time schedule for each aircraft based on the flight information, and any of them can be changed on the display screen by manual input. The radar tracking device according to claim 3, wherein the radar tracking device is provided. The radar tracking device according to any one of claims 1 to 4 , wherein the number of tracking beams is the number of landing guides for each time. When a plurality of landing guidance time zones overlap at least partially, the number of tracking beams in the plurality of landing guidance time zones is the maximum number of landing guidance aircraft in the plurality of landing guidance time zones. The radar tracking device according to any one of claims 1 to 4 . When a plurality of landing guidance time zones partially overlap, the number of tracking beams in the plurality of landing guidance time zones is the period from the earliest tracking start time to the latest tracking start time in the plurality of landing guidance time zones. , the landing induction machine number of each time the period, the period of until the slowest tracking finished from the time the latest tracking started, claim 1, characterized in that the maximum number of landings induction machine number of the period The radar tracking device according to any one of claims 1 to 4 . The radar tracking device according to any one of claims 1 to 7 , wherein the flight information is flight plan data. The radar tracking device according to any one of claims 1 to 7 , wherein the flight information is flight plan data and wake data based on ASR / SSR. The flight information, of claim 1, wherein 7 of that it is possible to switch to one of track data based on the flight plan data or flight plan data and ASR / SSR by manual input of the display control unit A radar tracking device according to claim. The flight information is flight plan data, flight plan data and wake data based on ASR / SSR, and the control means corrects at least the approach time generated based on the flight plan data based on the approach time based on the wake data. The radar tracking device according to any one of claims 1 to 4 , wherein the radar tracking device is characterized in that: In the radar tracking method using PAR,
A first step of inputting aircraft flight information from an external system;
From the flight information of the aircraft, the entry time and the landing time of each aircraft are predicted and calculated, and the landings that exist in the PAR coverage simultaneously for each time from the entry time and the landing time of each aircraft. A second step of calculating the number of guides and generating operation mode management data including the number of tracking beams for each time according to the number of landing guides;
A radar tracking method comprising: a third step of controlling the PAR according to the operation mode management data and controlling a tracking beam of the PAR at each time according to the number of landing guides . 13. The radar tracking method according to claim 12, wherein the operation mode management data includes data for controlling the number of tracking for each aircraft within the tracking period of the PAR and the tracking order of the aircraft. The radar tracking method according to claim 12 or 13, wherein the operation mode management data can be changed on a display screen by manual input. The radar tracking method according to any one of claims 12 to 14 , wherein the third step controls the number of tracking beams as the number of landing guides for each time. In the third step, when a plurality of landing guidance time zones overlap at least partially, the number of tracking beams in the plurality of landing guidance time zones is set to the maximum number of landing guidance aircraft in the plurality of landing guidance time zones. The radar tracking method according to claim 12, wherein the radar tracking method is controlled as follows. In the third step, when a plurality of landing guidance time zones partially overlap, the number of tracking beams in the plurality of landing guidance time zones is the latest from the earliest tracking start time in the plurality of landing guidance time zones. The period until the tracking start time is the number of landing guidance aircraft at each time of the period, and the period from the latest tracking start time to the latest tracking end time is controlled as the maximum number of landing guidance aircraft in the period. The radar tracking method according to any one of claims 12 to 14 , wherein the radar tracking method is performed. The radar tracking method according to claim 12 , wherein the flight information is flight plan data. 18. The radar tracking method according to claim 12 , wherein the flight information is flight plan data and wake data based on ASR / SSR. The radar according to any one of claims 12 to 17 , wherein the flight information can be switched to any one of flight plan data or flight plan data and wake data based on ASR / SSR by manual input. Tracking method. The flight information is flight plan data and track data based on flight plan data and ASR / SSR, and the second step corrects at least the approach time generated based on the flight plan data based on the approach time based on the track data. The radar tracking method according to any one of claims 12 to 17 , wherein the radar tracking method is performed. In a radar tracking device program using PAR,
A first step of inputting aircraft flight information from an external system;
From the flight information of the aircraft, the entry time and the landing time of each aircraft are predicted and calculated, and the landings that exist in the PAR coverage simultaneously for each time from the entry time and the landing time of each aircraft. A second step of calculating the number of guides and generating operation mode management data including the number of tracking beams for each time according to the number of landing guides;
And a third step of controlling the PAR according to the number of landing guidance aircraft and controlling the tracking beam at each time of the PAR according to the number of landing guidance aircraft . The program according to claim 22, wherein the operation mode management data includes data for controlling the number of times of tracking for each aircraft within the tracking period of the PAR and the tracking order of the aircraft. 24. The program according to claim 22, wherein the operation mode management data can be changed on a display screen by manual input. The program according to any one of claims 22 to 24 , wherein the third step controls the number of tracking beams as the number of landing guides for each time. In the third step, when a plurality of landing guidance time zones overlap at least partially, the number of tracking beams in the plurality of landing guidance time zones is set to the maximum number of landing guidance aircraft in the plurality of landing guidance time zones. 25. The program according to claim 22 , wherein the program is controlled as follows. In the third step, when a plurality of landing guidance time zones partially overlap, the number of tracking beams in the plurality of landing guidance time zones is the latest from the earliest tracking start time in the plurality of landing guidance time zones. The period until the tracking start time is the number of landing guidance aircraft at each time of the period, and the period from the latest tracking start time to the latest tracking end time is controlled as the maximum number of landing guidance aircraft in the period. 25. The program according to any one of claims 22 to 24 , wherein: The program according to any one of claims 22 to 27 , wherein the flight information is flight plan data. The program according to any one of claims 22 to 27 , wherein the flight information is flight plan data and wake data based on ASR / SSR. The program according to any one of claims 22 to 27 , wherein the flight information can be switched to either flight plan data or flight plan data based on manual input and wake data based on ASR / SSR. . The flight information is flight plan data and track data based on flight plan data and ASR / SSR, and the second step corrects at least the approach time generated based on the flight plan data based on the approach time based on the track data. 28. The program according to any one of claims 22 to 27 , wherein:

Images