JP5439350B2 - Multilateration system - Google Patents

Description

  Embodiments described herein relate generally to a receiving device that receives a signal transmitted from an aircraft, and a multilateration system that identifies the position of the aircraft from the received signal.

  In order to ensure flight safety of an aircraft, the aircraft is monitored using a radar such as an SSR device (mode S secondary monitoring radar device) that transmits and receives an inquiry signal and a response signal. In addition, in order to prevent a collision between aircrafts, broadcast-type automatic dependent surveillance (ADS-B) that exchanges position information between aircrafts is also used.

  Further, in recent years, in order to grasp the flight status of an aircraft on the ground, use of a multilateration system that receives signals transmitted from an aircraft by a plurality of receiving devices and identifies the position of the aircraft is being studied. The multilateration system measures the position of an aircraft using information related to reception of signals (extended squitter and squitter response) at a plurality of receiving stations. In addition, the multilateration system transmits a question signal to the aircraft using the measured aircraft position, and obtains a response signal including aircraft identification information and altitude information.

  The transmission of the interrogation signal by the multilateration system is specified so as not to hinder the operation of the adjacent secondary monitoring radar (SSR) (2% or less). However, since the multilateration system cannot grasp the operation of the secondary monitoring radar, it is difficult to determine the timing for transmitting the inquiry signal. In addition, as the number of aircraft increases, the determination of the timing for transmitting the inquiry signal becomes more complicated.

  Since the transponder installed in the aircraft has dead time and does not respond to the interrogation signal to be answered for 125 μs, when the multi-lateration system interrogates first, the secondary surveillance radar will not respond for 125 μs. Does not respond to questions. Also, if the secondary surveillance radar interrogates the transponder first, the transponder will not respond to the interrogation from the multilateration system for 125 μs. For this reason, when the multilateration system transmits an interrogation signal regardless of the operation of the secondary monitoring radar, the detection rate may be lowered in the secondary monitoring radar, which may hinder the monitoring of the aircraft.

  In addition, the response signal from the transponder with respect to the interrogation signal of the multi-lateration system becomes a fruit response to the secondary monitoring radar, which may reduce the detection rate in the secondary monitoring radar. Secondary surveillance radars (especially Mode S secondary surveillance radars) are designed to reduce this fruit response, i.e. not affect other secondary surveillance radars, This may hinder the idea of secondary monitoring radar.

  As described above, in the multilateration system, when an interrogation signal is transmitted regardless of the operation of the secondary monitoring radar, there is a possibility that the detection rate of the secondary monitoring radar is lowered to hinder the monitoring of the aircraft.

Michael C. Stevens “Secondary Surveillance Radar” 1988, ISBN 0-89006-292-7.

  Therefore, the present invention provides a multi-lateration system in which the signal transmission timing corresponds to the operation of the secondary monitoring radar and does not hinder the monitoring of the aircraft in the secondary monitoring radar.

  The multilateration system according to the embodiment of the present invention includes an antenna angle input unit, a conversion unit, a determination unit, and a transmission unit. The antenna angle input means inputs the current antenna angle of the radar apparatus from the radar apparatus. When the position of the aircraft measured from the difference in signal reception time in the plurality of reception devices is input, the conversion means converts the position of the aircraft into a value represented by the angle of the antenna of the radar device. The determination unit determines an angle at which the transmission device stops transmission of the interrogation signal using an antenna angle that identifies the position of the aircraft converted by the conversion unit. The transmission means transmits the interrogation signal when the antenna angle input by the antenna angle input means is other than the angle determined by the determination means.

It is the schematic explaining the multilateration system which concerns on embodiment. It is a block diagram explaining the structure of a transmission / reception apparatus. It is a figure explaining the orientation of the antenna of a radar apparatus, and the positional relationship of an aircraft.

  Below, the multilateration system which concerns on embodiment is demonstrated using drawing. This multilateration system is a system that receives signals transmitted from an aircraft at a plurality of stations, measures the position of the aircraft, acquires flight information of the aircraft separately from the radar device, and monitors the flight of the aircraft. .

  As shown in FIG. 1, the multilateration system 1 according to the embodiment receives signals (DF = 4, 5, 11, 17, 18, 20, 21) transmitted from the aircraft 30 and A transmitting / receiving device 10 that transmits a signal (UF = 4, 5) and a plurality of receiving devices 20a to 20 that receive response signals (DF = 4, 5, 11, 17, 18, 20, 21) transmitted from the aircraft 30. 20c is connected to a processing device 40 that inputs a signal received by the transmission / reception device 10 and the reception devices 20a to 20c and a reception time of the signal to determine the position of the aircraft 30.

  In the multilateration system 1, when the transmission / reception device 10 and the reception devices 20a to 20c installed in different places receive a signal transmitted from the transponder of the aircraft 30, the processing device associates the reception time of the signal with the received signal. Output to 40. The processing device 40 measures the position of the aircraft 30 from the difference in reception time between the devices 10, 20a to 20c for the same signal. Here, if the reception times associated with the signals are not accurate in the transmission / reception device 10 and the reception devices 20a to 20c, the position of the aircraft 30 to be measured is not accurate. Therefore, in the multilateration system 1, the time measured by the transmission / reception device 10 and the reception devices 20 a to 20 c is synchronized in order to accurately measure the position of the aircraft 30 by the processing device 40.

  In the multilateration system 1 according to the embodiment, the transmission / reception device 10 is connected to the radar device 50. The radar device 50 is a secondary monitoring radar that transmits an interrogation signal to the aircraft 30 and receives a response signal transmitted from the aircraft in response to the interrogation signal and monitors the aircraft 30. The transmission / reception device 10 inputs the antenna angle of the radar device 50 from the radar device 50. As a result, the transmission / reception device 10 can transmit a question signal to the aircraft 30 at a timing that does not affect transmission / reception of signals between the aircraft 30 and the radar device 50.

  Specifically, as illustrated in FIG. 2, the transmission / reception device 10 includes a reception device 10 a that receives a signal transmitted from the aircraft 30 and a transmission device 10 b that transmits a question signal to the aircraft 30. The receiving device 10a associates the signal received time with the signal received by the antenna 10d and outputs the signal to the processing device 40. Since this receiving apparatus 10a has the same configuration as that of a receiving apparatus conventionally used in the multilateration system 1, description of the configuration of the receiving apparatus 10a is omitted.

  The transmission device 10b includes an information processing unit 11, a transmission management unit 12, a signal conversion unit 13, and a high frequency processing unit 14, as shown in FIG. In addition, the information processing unit 11 includes a position information input unit 111, a coordinate conversion unit 112, a determination unit 113, an antenna angle input unit 114, and an extraction unit 115.

  The position information input unit 111 inputs data (position data) related to the position of the aircraft 30 measured from the processing device 40, and outputs the input position data to the coordinate conversion unit 112. This position data is data for specifying the position of the aircraft 30 by latitude and longitude.

  The coordinate conversion unit 112 converts the position of the aircraft 30 specified by the input position data into a value represented by the antenna angle of the radar apparatus 50, and outputs the obtained antenna angle to the determination unit 113. Since the positional relationship between the transmission / reception device 10 and the radar device 50 is registered in the coordinate conversion unit 112 in advance, the coordinate conversion unit 112 uses the input position data to convert the aircraft 30 to the antenna angle of the radar device 50. Can be converted into a value represented by.

  For example, when the radar apparatus 50, the aircraft 30a, and the aircraft 30b are in a positional relationship as shown in FIG. 3, the antenna angle that represents the position of the aircraft 30a is α, and the antenna angle that represents the position of the aircraft 30b is β. It becomes. Here, since the positions of the aircrafts 30a and 30b always change, the antenna angle also changes. Therefore, when the new position data is input from the position information input unit 111, the coordinate conversion device 112 uses the input position data to convert it into an antenna angle representing the position of the new aircraft 30a, 30b.

  The determination unit 113 determines a stop angle at which the transmission of the inquiry signal to each aircraft is stopped from the antenna angle specifying the position of each aircraft 30 input from the coordinate conversion unit 112, and the determined stop angle is extracted to the extraction unit 115. Output. The beam width is about 3 ° with respect to the antenna angle, and the radar apparatus 50 transmits a signal to an aircraft existing in this beam range. Therefore, the determination unit 113 determines a range of ± 1.5 ° as a stop angle with reference to the antenna angle.

  Specifically, as shown in FIG. 3, when the position of the aircraft 30a is specified by the antenna angle α, a range from “α−1.5 °” to “α + 1.5 °” is defined between the radar device 50, the aircraft 30a, and the aircraft 30a. Is the timing of answering questions. Therefore, the determination unit 113 sets the range from “α−1.5 °” to “α + 1.5 °” as the stop angle, and sets the stop period as a period for stopping transmission of the inquiry signal from the transmission / reception device 10 to the aircraft 30a. . Further, when the position of the aircraft 30b is specified by the antenna angle β, the range of “β−1.5 °” to “β + 1.5 °” is the timing of the question response between the radar device 50 and the aircraft 30b. Therefore, the determination unit 113 sets the range of “β−1.5 °” to “β + 1.5 °” as the stop angle, and stops the transmission of the transmission signal from the transmission / reception apparatus 10 to the aircraft 30b. To do.

  When the current antenna angle is input from the radar apparatus 50, the antenna angle input unit 114 outputs the input antenna angle to the extraction unit 115.

  The extraction means 115 extracts the aircraft 30 that transmits the question signal. Specifically, the aircraft 30 that is the transmission target of the interrogation signal is the aircraft 30 in which the position data is input from the processing device 40 and the antenna angle for specifying the position is obtained. Further, the extraction unit 115 transmits a trigger signal that causes the extracted aircraft 30 to transmit a question signal from the stop angle of each aircraft input from the determination unit 114 and the current antenna angle input from the antenna angle input unit 113. 12 is output. Specifically, the extraction unit 115 outputs a trigger signal for transmitting a question signal when the antenna angle is other than the stop angle.

  For example, as shown in FIG. 3, when the aircrafts 30a and 30b are flying, the extraction unit 115 extracts the aircraft 30a and the aircraft 30b. In addition, the extraction unit 115 has timings when the antenna angle of the radar apparatus 50 is other than “α−1.5 °” to “α + 1.5 °” and other than “β−1.5 °” to “β + 1.5 °”. To output a trigger signal for transmitting a question signal.

  When receiving the trigger signal from the extraction unit 115, the transmission management unit 12 generates a question signal to be transmitted to the aircraft 30 specified by the trigger signal, and outputs the generated question signal to the signal conversion unit 13. Data regarding the number of signals to be transmitted and the signal transmission interval is input in advance to the transmission management unit 12, and the transmission management unit 12 generates a query signal to be transmitted according to the data.

  The signal conversion unit 13 converts the input signal into a transmission format and outputs it to the high frequency processing unit 14. The high frequency processing unit 14 performs high frequency processing on the input signal and transmits the processed signal to the aircraft 30 via the switch 10c and the antenna 10d.

  As described above, the transmission device 10b does not transmit the interrogation signal to the aircraft 30 in the range of the beam width of 3 ° by the extraction by the extraction unit 115. Therefore, the question signal transmitted from the transmission / reception device 10 to the aircraft 30 does not affect the question response between the radar device 50 and the aircraft 30. In addition, since the radar apparatus 50 performs processing other than the beam width by RSLS processing, the interrogation signal transmitted by the transmission apparatus 10b outside the range of 3 ° with respect to the antenna direction (antenna angle) of the radar apparatus 50 is The radar apparatus 50 is not affected.

  In the example illustrated in FIG. 1, the number of transmission / reception devices 10 is 1 and the number of reception devices 20 a to 20 c is 3. However, the number of transmission / reception devices and reception devices is not limited. Therefore, it is possible to have more transmission / reception devices and reception devices, and to determine the position of the aircraft 30 using signals received by these devices.

  Further, the number of radar devices 50 connected to the transmission / reception device 10 is not limited. Therefore, when the transmission / reception device 10 is connected to a plurality of radar devices and inputs aircraft position data from each radar device, the antenna angles of the plurality of radar devices are input, and the aircraft 30 is interrogated in consideration of the plurality of antenna angles. Send a signal.

  As described above, in the multilateration system 1 according to the embodiment, since the question signal is transmitted to each aircraft 30 in consideration of the antenna angle of the radar device 50, the question between the radar device 50 and each aircraft 30 is transmitted. The influence on the response can be prevented.

  As mentioned above, although this invention was described by embodiment, it should not be understood that the description and drawing which form a part of this indication limit this invention. From this disclosure, various alternative embodiments, examples and operational techniques will be apparent to those skilled in the art. Further, the present invention naturally includes various embodiments not described herein.

DESCRIPTION OF SYMBOLS 1 ... Multilateration system 10 ... Transmission / reception apparatus 10a ... Reception apparatus 10b ... Transmission apparatus 11 ... Information processing part 111 ... Position information input means 112 ... Coordinate conversion means 112 ... Coordinate conversion apparatus 113 ... Antenna angle input means 114 ... Determination means 115 ... extraction means 12 ... transmission management section (transmission means)
DESCRIPTION OF SYMBOLS 13 ... Signal conversion part 14 ... High frequency processing part 10c ... Switch 10d ... Antenna 20a-20c ... Receiving device 30, 30a, 30b ... Aircraft 40 ... Processing device 50 ... Radar device

Claims (1)

The position of the aircraft is determined by using the difference in reception time of the same signal received by a plurality of receiving devices, and the interrogation signal is transmitted from the transmitting device to the aircraft whose position is determined. A multi-lateration system for acquiring information,
Antenna angle input means for inputting the current antenna angle of the radar device from the radar device;
Conversion means for converting the position of the aircraft into a value represented by the angle of the antenna of the radar device, when the position of the aircraft measured from the difference in signal reception time in the plurality of reception devices is input;
A determination unit that determines an angle at which the transmission device stops transmitting the interrogation signal by using an antenna angle that identifies the position of the aircraft converted by the conversion unit;
Transmitting means for transmitting an interrogation signal at an angle other than the angle determined by the determining means, the angle of the antenna input by the antenna angle input means;
A multi-lateration system comprising:

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