JP5863165B2 - Aircraft noise monitoring method and aircraft noise monitoring device - Google Patents

Description

  The present invention relates to a method for monitoring aircraft noise using a response signal emitted from an aircraft in response to an interrogation signal radiated from a secondary surveillance radar (SSR) in air traffic control (ATC). It relates to the device.

  Conventionally, in the identification of aircraft noise around airports and the like, there is an acoustic identification method that identifies the noise source aircraft by capturing the arrival direction (elevation angle and azimuth angle) of sound by a three-axis correlation method (for example, Patent Documents). 1). In addition to this acoustic identification method, the noise source identification performance can be further improved by using a radio wave identification method for receiving radio waves of response signals emitted from aircraft.

  In the conventional radio wave identification method, analysis processing of aircraft noise data is performed from the magnitude of the radio wave intensity of the transponder response signal emitted from the aircraft (see, for example, Patent Document 2). Specifically, the time-dependent change in the noise signal captured by the computer and the time-dependent change in the radio field intensity of the transponder response signal generated by the aircraft are displayed, and from there, unnecessary noise data other than for the aircraft is determined by the operator's judgment or automatic program processing. Are repeatedly performed until the degree of contribution to the noise evaluation value set in advance is not more than the final value. Thereby, the noise data obtained when the radio wave intensity of the response signal is large can be finally determined as aircraft noise.

JP 7-43203 A JP 2006-138831 A

  The radio wave identification method described above is considered to be effective to some extent in a measurement environment where a specific aircraft flies alone. However, when multiple aircraft are flying at the same time in the observation area, each of them emits its own response signal, so it is not possible to identify the radio wave source from the received signal strength alone. There is a problem that an error occurs in collation between the noise source and the radio wave transmission source.

  Depending on the measurement environment, the radio signal intensity of a response signal generated from a distant aircraft may be larger than that of a response signal generated from a nearby aircraft due to the influence of a shield such as an airport facility. In this case, even if the noise of an aircraft flying in the vicinity is observed, if the radio wave intensity of the response signal received at the same time is extremely weak, it is difficult to correctly determine the comparison between the two. Alternatively, even if a response signal is received with a relatively strong radio field intensity from an aircraft flying in the distance, it is difficult to correctly determine the comparison between the two unless a large noise is observed at the same time.

  Even if the radio wave intensity is sufficient, noise may be mixed in the response signal depending on the reception environment, and the effect of this makes it difficult to collate the radio wave source and the noise source.

  Accordingly, an object of the present invention is to improve the identification performance of aircraft noise using a radio wave identification method in addition to an acoustic method.

In order to solve the above problems, the present invention employs the following solutions.
That is, the present invention receives response signals emitted from an unspecified number of aircraft in response to interrogation signals radiated from an unspecified number of secondary surveillance radars (SSRs), and performs various arithmetic processes therefrom. Only the response signal group emitted from a specific aircraft is extracted.

  In general, a question signal from a secondary monitoring radar or the like is radiated including a combination of “mode A” for inquiring an aircraft identification code allocated for each flight and “mode C” for inquiring about the current altitude. For this reason, information specific to the aircraft such as altitude information (mode C) and airframe identification code (mode A) is included in the radio wave of the response signal emitted from the aircraft.

  However, since an unspecified number of aircraft may navigate around the airfield, the response signals received at the observation point randomly include signals emitted from the unspecified number of aircraft. When there are a plurality of secondary monitoring radars (SSRs) that emit question signals, response signals are generated in response to the respective radars.

  In order to extract a group of response signals from a specific aircraft to a specific secondary surveillance radar (SSR) interrogation signal, the present invention focuses on the time interval of the response signal. Generally, the response signal emitted from the aircraft is pulsed, and the time interval traces the time interval of the interrogation signal. Therefore, even if response signals are mixed at various time intervals on the same time series, the question signal of a specific secondary monitoring radar (SSR) always holds a constant time interval. If the response signal is filtered using the time interval, it is possible to correctly extract only the response signal group emitted from the aircraft with respect to the interrogation signal emitted from the specific secondary monitoring radar (SSR).

  The aircraft noise monitoring apparatus according to the present invention includes a receiving unit, a time interval calculating unit, a frequency calculating unit, and a filter unit. With these configurations, the aircraft noise monitoring method of the present invention can be executed.

First, a receiving part performs the step which receives the response signal emitted from the unspecified number of aircraft with respect to the inquiry signal from a secondary surveillance radar (SSR).
Next, the time interval calculation unit executes a step of calculating mutual time intervals for a plurality of response signals received within a predetermined time.
The frequency calculation unit executes a step of calculating individual frequencies for a plurality of time intervals calculated by the time interval calculation unit.
The filter unit performs a step of filtering a specific response signal group from among a plurality of response signals received within a predetermined time using a specific time interval at which the frequency calculated by the frequency calculation unit is maximized. To do.

  As a result, even if response signals are mixed at various time intervals on the same time series, the response signals intended for response signals regularly arranged at the most frequent time intervals among them They can be identified as a group and extracted accurately.

The filter unit further executes a step of extracting a pair of response signals received at specific time intervals from a plurality of response signals received within a predetermined time.
The aircraft noise monitoring apparatus further includes a configuration of an information calculation unit.

  The response signal group extracted by the filter unit is information of “mode A” or “mode C” emitted from a specific aircraft. In general, the interrogation signals of “mode A” and “mode C” used in the secondary surveillance radar system of an aircraft have a pattern of “A, A, C, A, A, C,. Since the pattern is divided into “C, A, C,.

Therefore, the response signal after filtering can be determined as “mode A” or “mode C” by executing the following steps. In order to determine the mode, the aircraft noise monitoring apparatus includes a mode determination unit.
In the response signal after filtering by the filter unit, when the pair of response signals received at a specific time interval have the same content, the mode determination unit determines that these response signals are airframe identification code information. The determining step is executed.

  As described above, the response signal pattern is “A, A, C, A, A, C,...” Or “A, C, A, C,. If the response signals indicate the same content, it can easily be determined as “mode A”.

  In addition, the mode determination unit includes a pair of response signals received after a specific time interval in the response signals after filtering by the filter unit, and one response signal is the aircraft identification code information. If it is determined that there is, the step of determining that the other response signal is altitude information is executed.

  In other words, if the pair of response signals is either “A, C” or “C, A”, and there is one that has already been determined as “mode A”, the rest is “mode C”. Can be easily determined.

  In addition, the mode determination unit does not have the same pair of response signals received at specific time intervals in the response signal after filtering by the filter unit, and any response signal is the aircraft identification code information. If it is not determined that there is a step, the response signal pair is stored in the buffer, and the time-dependent changes in the content of the stored response signals of the pair are monitored. The step of determining that the information is information and determining that the change has occurred may be further executed.

  Normally, noise is generated at an observation point when an aircraft is flying at a relatively low altitude. In this case, since the aircraft is in a take-off and landing state around the airport, there is a feature that the altitude (mode C response signal) of the aircraft changes continuously. One aircraft identification code information (mode A response signal) is constant for each flight and has the characteristic of not changing. Therefore, it is possible to easily determine that the changing direction is altitude information, and the non-changing direction is body identification code information.

  Furthermore, the aircraft noise monitoring apparatus may include a configuration as a noise measuring unit and a matching unit. The noise measuring unit executes a step of measuring noise that has arrived at an observation point using an aircraft as a noise source. The matching unit executes a step of matching the response signal after filtering by the filter unit and the result of the aircraft noise measured by the noise measuring unit.

The effect of noise can be removed by pairing the response signals.
In addition, it is possible to accurately grasp the status of the response signal at the time.

  As described above, according to the aircraft noise monitoring method and the aircraft noise monitoring apparatus of the present invention, even if there are a plurality (unspecified number) of control radars and aircraft in the monitored area, the specific noise extracted from the radar The identification accuracy of aircraft noise can be improved using the information of the response signal group.

It is a schematic diagram showing one embodiment at the time of installing an aircraft noise monitoring device in an airfield. It is a block diagram which shows roughly the structure of an aircraft noise monitoring apparatus. It is the figure which showed the pattern of the response signal emitted from several aircraft in time series. It is a figure which shows the example which arranged all the response signals received within the predetermined time in time series. It is a figure which shows the example of the histogram obtained from several kinds of time intervals. It is the figure which showed an example at the time of filtering a response signal using a time gate. It is a flowchart which shows the example of a procedure of the noise monitoring process performed by the observation unit. It is a flowchart which shows the content of the mode determination process in detail. It is a figure which shows the example of an analysis of the time change tendency of a code | cord | chord. It is a figure which shows the example at the time of making time data and noise data match.

  Hereinafter, embodiments of the present invention will be described with reference to the drawings.

  FIG. 1 is a schematic diagram showing an embodiment when an aircraft noise monitoring device is installed in an airfield. Here, the airfield is an example of a target area (measurement environment) for monitoring aircraft noise in the present embodiment. In a target area such as an airfield (or its surroundings), aircraft noise is generated from the sky as the aircraft navigates. The “aircraft noise” referred to in the present embodiment includes noise (other than flight noise) generated when an aircraft takes off or landing.

  As shown in FIG. 1, the aircraft noise monitoring apparatus can be used with a microphone-antenna unit 10 installed at an observation point in an airfield. An observation unit 100 is connected to the microphone-antenna unit 10.

〔Environmental condition〕
Here, for example, control towers CT1 and CT2 are provided at a plurality of locations in an airfield as a target area, and a plurality of secondary monitoring radars SSR1 and SSR2 are installed along with the control towers CT1 and CT2. It shall be. Each of the secondary monitoring radars SSR1 and SSR2 has a strong directivity antenna corresponding to a secondary monitoring radar (SSR) system. At the airfield, an unspecified number of aircraft AP1
AP2 is navigating according to their flight plans.

[Question signal]
Each of the secondary monitoring radars SSR1 and SSR2 emits radio waves of “mode A” and “mode C” as question signals. “Mode A” inquires each aircraft AP1 and AP2 about an ATC code or a squeak (squeak). “Mode C” inquires each aircraft AP1 and AP2 about the current flight altitude. There is “mode S” in addition to this, but since “mode S” is not used in the present embodiment, it is omitted.

[Question signal pattern]
One secondary monitoring radar SSR1 radiates an inquiry signal in the following pattern, for example. Hereinafter, “mode A” is simply abbreviated as “A”, and “mode C” is simply abbreviated as “C”.
(1) A, A, C, A, A, C, ...
Further, it is assumed that the other secondary monitoring radar SSR2 emits a question signal in the following pattern, for example.
(2) A, C, A, C, A, C, ...

[ATC code (aircraft identification code information)]
Each aircraft AP1, AP2 is equipped with an ATC transponder response device (hereinafter referred to as “response device”) corresponding to a secondary monitoring radar system of air traffic control (ATC: Air Traffic Control). The ATC code (unique code) is designated by the controller for each flight of the aircraft AP1 and AP2, and the pilot of each aircraft AP1 and AP2 is input to the response device.

[Flight altitude]
The information indicating the flight altitude is QNE (altitude without pressure correction), which is updated in units of 100 ft. QNE is converted to QNH (pressure corrected altitude) by the ground station computer.

[Response signal pattern]
When the response devices of the aircrafts AP1 and AP2 receive the interrogation signals (1030 MHz band) from the secondary monitoring radars SSR1 and SSR2, they transmit a response signal (1090 MHz band) with a predetermined delay time. At this time, the pattern of the response signal matches the pattern of the question signal.
For this reason, the response signal to the interrogation signal from one secondary monitoring radar SSR1 has the following pattern.
(1) A, A, C, A, A, C, ...
The response signal to the interrogation signal from the other secondary monitoring radar SSR2 has the following pattern.
(2) A, C, A, C, A, C, ...

[Configuration of aircraft noise monitoring device]
FIG. 2 is a block diagram schematically showing the configuration of the aircraft noise monitoring apparatus. The aircraft noise monitoring apparatus can receive response signals emitted from the aircrafts AP1 and AP2 through the radar receiving antenna 12 of the microphone-antenna unit 10. In addition, the aircraft noise monitoring apparatus can observe aviation noise originating from each aircraft AP1, AP2 using the noise measurement microphone 14 of the microphone-antenna unit 10 and the sound arrival direction identification microphone 16.

  The observation unit 100 is configured by computer equipment including a central processing unit (CPU), a semiconductor memory (ROM, RAM), a hard disk drive (HDD), an input / output interface, a liquid crystal display, and the like (not shown). The observation unit 100 causes its hardware resources to function as a plurality of functional elements under software control. The plurality of functional elements are mainly divided into a response signal processing system and a noise measurement system. Hereinafter, functional elements implemented in the observation unit 100 will be described.

[Response signal processing system]
The response signal processing system includes functional elements such as the receiving unit 20 and the target signal group extracting unit 22 that communicate with the radar receiving antenna 12. The target signal group extraction unit 22 includes a temporary memory 24 and a time interval analysis unit 26 (time interval calculation unit).

  The receiving unit 20 demodulates the response signal (1090 MHz band) received through the radar receiving antenna 12 into a pulse format, and generates a frame having a predetermined bit length (for example, 13 bits). The generated frame is stored in the temporary memory 24 as a response signal in a pulse format.

  In the temporary memory 24, response signals received within a predetermined time (for example, 1 second) are accumulated in chronological order. The time interval analysis unit 26 calculates a mutual time interval for all of the accumulated response signals.

  The response signal processing system further includes functional elements such as a histogram creation unit 28 (frequency calculation unit) and a filter unit 30. The histogram creation unit 28 creates a histogram using a plurality of time intervals calculated by the time interval analysis unit 26 as statistical data. Note that the histogram need not be visible, and may be any that can be recognized as a histogram in the physical memory space.

  The filter unit 30 removes a response signal that cannot be paired from the response signal stored in the temporary memory 24 from the response signal stored in the temporary memory 24 using the time interval having the highest frequency on the histogram as a time gate. As a result, only the specific response signal group that matches the time gate remains, and all other response signals are screened out.

  The terminal portion of the response signal processing system includes functional elements such as a mode determination unit 34 (mode determination unit), an average intensity appearance number calculation unit 32 (information calculation unit), and a time data creation unit 36 (data array creation unit). It is. The mode determination unit 34 analyzes the response signal group after filtering, and classifies each response signal as “mode A” or “mode C”.

  In addition, the average intensity appearance number calculation unit 32 calculates the average (average intensity) and the number of appearances of the radio wave intensity according to the contents of “mode A” or “mode C” for the response signal group after filtering.

  Then, the time data creation unit 36 creates time data in which the calculated average intensities and appearance counts of “mode A” and “mode C” are arranged for each reception time (for example, 1 second).

[Noise measurement system]
Next, the noise measurement system includes a noise measurement unit 38 that communicates with the noise measurement microphone 14. Here, the noise measurement microphone 14 is a noise measurement microphone, and the sound arrival direction identification microphone 16 has four microphones for identifying the sky sound by the three-axis correlation method.

  The noise measurement unit 38 calculates the elevation angle θ and the azimuth angle δ of the aircrafts AP1 and AP2 (sound sources) by the three-axis correlation method, and the noise arrival direction in the three-axis observation space (vector space) with the observation point as a reference. A vector (unit vector) is calculated. Further, the noise measurement unit 38 calculates the moving direction (from which direction to which direction) the aircraft AP1, AP2 (sound source) with reference to the observation point, based on the calculated value (trajectory) of the arrival direction vector. When the noise level at the observation point exceeds a certain threshold (when a noise event occurs), the noise measuring unit 38 stores the time, the elevation angle θ, and the azimuth angle δ in association with each other.

[Alignment of time data and noise data]
The observation unit 100 includes functional elements of the matching unit 40. The matching unit 40 matches (associates) the time data created by the signal processing system with the noise data created by the noise measurement system. Then, the matching unit 40 acquires information on “mode A” and “mode C” corresponding to the time when the aircraft noise was observed from the matched noise data and time data.

  The acquired information is stored in the data memory 42 and further output from the output unit 44. The output unit 44 includes the liquid crystal display, the external interface, and the like. By connecting a computer or the like to the external interface, the information stored in the data memory 42 can be used by the computer or the like.

  The above is a description of configuration examples and functions of the aircraft noise monitoring apparatus, but the response signal processing performed by the observation unit 100 will be described below with a specific example.

[Operating conditions]
For example, in FIG. 1, it is assumed that the secondary monitoring radar SSR1 of the control tower CT1 emits a question signal having a pattern of A, A, C, A, A, C,... At 370 pps (pulse per second). . On the other hand, it is assumed that the secondary monitoring radar SSR2 of the control tower CT2 emits a question signal having a pattern of A, C, A, C,... At 474.3 pps.

  Here, each of the secondary monitoring radars SSR1 and SSR2 scans all directions (360 °) in the east, west, south, and north directions, and rotates a very directional antenna once every 3 to 5 seconds. Accordingly, the aircrafts AP1 and AP2 receive the interrogation signal at the moment when they are opposed to the antennas of the secondary monitoring radars SSR1 and SSR2, and issue a response signal with a predetermined time delay of 3.5 μs.

  Here, the response time of each aircraft AP1, AP2 can be calculated from the directivity angle and the rotation period of each secondary monitoring radar SSR1, SSR2, and generally the response time is approximately within 30 to 50 ms. can do. That is, the number of responses to the secondary monitoring radar SSR1 is about 11 to 18 times, and the number of responses to the secondary monitoring radar SSR2 is about 14 to 24 times.

[Response signal transmission pattern]
FIG. 3 is a diagram showing, in time series, response signal patterns generated from aircrafts AP1 and AP2 under the above operating conditions.

[AP1-SSR1]
For example, as shown in FIG. 3A, the aircraft AP1 is opposed to the secondary monitoring radar SSR1 at a certain time m1, and within a time period during which the interrogation signal (AACAAC...) Can be effectively received from that moment. 11 to 18 response signals (AACAAC...) Are generated. Next, the aircraft AP1 is opposed to the secondary monitoring radar SSR1 at time m5 after the rotation period T1, and from this moment, the aircraft AP1 again issues a response signal (AACAAC...) Of 11 to 18 pulses. Become.

[AP1-SSR2]
On the other hand, the aircraft AP1 is also opposed to the secondary monitoring radar SSR2 at another time m3, and the response signal of 14 to 24 pulses (ACAC... Within the time when the interrogation signal (ACAC...) Can be effectively received from that moment.・) Is issued. The aircraft AP1 then faces the secondary monitoring radar SSR2 at time m7 after the rotation period T2, and the aircraft AP1 again issues a response signal (ACAC...) Of 14 to 24 pulses from this moment. become.

[AP2-SSR2]
Another aircraft AP2 is as follows.
That is, as shown in FIG. 3B, the aircraft AP2 is opposed to the secondary monitoring radar SSR2 at a certain time m2, and effectively receives the interrogation signal (ACAC...) From that moment. A response signal (ACAC...) Of 14 to 24 pulses is generated within a possible time. Next, the aircraft AP2 faces the secondary monitoring radar SSR2 at time m6 after the rotation period T2, and from this moment, the aircraft AP2 again generates a response signal (ACAC...) Of 14 to 24 pulses. It will be.

[AP2-SSR1]
On the other hand, the aircraft AP2 is also opposed to the secondary monitoring radar SSR1 at another time m4, and the response signal of 11 to 18 pulses (AACAAC,...) Within the time when the interrogation signal (AACAAC...) Can be effectively received from that moment.・) Is issued. Although not shown in FIG. 3, the aircraft AP2 next faces the secondary monitoring radar SSR1 after the rotation period T1, and from that moment, the aircraft AP2 again responds with a response signal (AACAAC.・) Will be issued.

[Response signal array]
FIG. 4 is a diagram illustrating an example in which all response signals received within a predetermined time (for example, 1 second) are arranged in time series. Such an array of response signals S _{1 to} S _p represents a result (including a 13-bit code, time, and intensity) in which the response signals stored every one second stored in the temporary memory 24 are arranged. .

[Calculation of time interval]
Time interval analyzer 26 as described above, for all the response signals _S 1 to S _p, calculates the time interval _{t mn} of each other. For example, as shown in figure 4 (A), if the head of the response signal S _1, the time interval t ₁₂ of all the other response signal S ₂ to S _p and (so-called "brute force"), t ₁₃ , t ₁₄ ,... t _1p are calculated. As also shown in FIG. 4 (B), 2 th response signal if _{S 2,} all other response signals _{S 1,} S 3 the time interval between ~S _{p t 21, t 23,} t ₂₄ ,... t _{2 (p−1)} are calculated. As also shown in FIG. 4 (C), 3-th response signal if _{S 3,} any other response signals _{S 1, S 2, S 4} ~S p and the time interval _{t 31,} t ₃₂ , t ₃₄ ,... t _{3 (p−2)} are calculated. Although not particularly shown, to similarly response signal _S 4 to S _p or less, and calculates all the time intervals _{t mn.}

[Create histogram]
FIG. 5 is a diagram illustrating an example of a histogram obtained from the calculated time interval. Here, for the sake of convenience, the visualization is shown, but as described above, the histogram creation unit 28 creates a histogram that can be recognized in the memory space. For convenience, each time interval is represented by the number of received pulses per second (pps).

[Time gate decision]
Next, from the obtained histogram, a time interval t _gate having the highest frequency (the number of receptions is large) is calculated, and the calculated time interval t _gate is set as a time _gate for filtering. For example, the mode value “370 pps” is the first candidate for the time gate, and the next highest frequency “474.3 pps” is the second candidate.

〔filtering〕
FIG. 6 is a diagram showing an example when the response signal is filtered using a time gate. That is, the filter unit 30 filters a target response signal group using the most frequently _occurring time interval t _gate as a time gate. Although both the first candidate and the second candidate may be handled depending on the specification, in the present embodiment, only the first candidate is used.

For example, all of the response signal _S 1 to S _p received per second shown in FIG. 6 (A), the can be a pair of time intervals _{t Gate} shown in FIG. 6 (B) ~ (D) as a time gate When a set of response signals is extracted and filtered, only the target response signal group remains (for example, S ₁ , S ₄ , S ₆ ), as shown in FIGS. As shown in C), the other response signals are removed. Moreover, noise can be removed by pairing response signals.

[Ground noise observation processing]
FIG. 7 is a flowchart showing a procedure example of noise monitoring processing executed by the observation unit 100 of the aircraft noise monitoring apparatus. Further, the contents of each step used in the aircraft noise monitoring method will be clarified by the following description. Note that the observation unit 100 can execute the noise monitoring process with a time interruption every second.

  Step S10: The observation unit 100 executes a response signal reception process in the reception unit 20. In this process, a response signal is received every second as described above.

  Step S20: Next, the observation unit 100 executes data alignment processing in the target signal group extraction unit 22. In this processing, time and intensity are associated with the received response signal and stored in the temporary memory 24, and the data is aligned in time series (FIG. 4).

Step S30: The observation unit 100 executes time interval analysis processing in the time interval analysis unit 26. In this process, all of the response signal _S 1 to S _p as described above, to calculate the time interval _{t mn} cross (Fig. 4).

Step S40: Next, the observation unit 100 executes histogram processing in the histogram creation unit 28. In this process, a histogram is created from a plurality of time intervals t _mn as described above.

Step S50: The observation unit 100 executes filter processing in the filter unit 30. In this process, the time interval t _gate which is the maximum frequency is calculated as described above, and the target response signal group is filtered using this as a time gate (FIG. 6). At this time, the filter unit 30 extracts a pair of response signals matching the time interval t _gate from all the response signals.

  Step S60: The observation unit 100 executes pair information calculation processing in the average intensity appearance number calculation unit 32. In this process, the average and number of appearances of the radio field strengths of pairs having the same content (code) among the response signals after filtering are calculated.

  Step S70: In addition, the observation unit 100 executes mode determination processing in the mode determination unit 34. In this process, it is determined whether the response signals extracted in pairs correspond to “mode A” or “mode C”, respectively. The details of the mode determination process will be further described later using another flowchart.

  Step S80: The observation unit 100 executes data arrangement processing in the time data creation unit 36. In this process, time data is generated for the response signal for which the mode has been determined, by arranging the reception time and “mode A” or “mode C”, the radio wave intensity and the number of appearances.

  Step S90: Then, the observation unit 100 executes the matching process in the matching unit 40. In this processing, time data and noise data are matched as described above, and information on “mode A” and “mode C” of observed aircraft noise is acquired.

[Mode judgment processing]
FIG. 8 is a flowchart showing details of the mode determination process. The mode determination unit 34 of the observation unit 100 determines whether the response signal after filtering corresponds to a code “mode A” or “mode C” through the following procedure. Further, the determined response signal is labeled as “A ₁ , A ₂ , A ₃ ,...” Or “C ₁ , C ₂ , C ₃ ,. Hereinafter, it demonstrates along a procedure.

  Step S100: The mode determination unit 34 confirms whether the extracted pair of response signals have the same code (for example, 13-bit code). The extracted response signal pair is theoretically one of “A, A”, “A, C”, or “C, A”, so if the pair codes are the same, it is a pair of “A, A”. Yes (Yes → go to step S102).

Step S102: Therefore, the mode determination unit 34 determines a pair having the same code as “mode A”.
Step S104: Further, the mode determination unit 34 labels as “A ₁ , A ₂ , A ₃ ,...” For each code content (for each machine identification code information). The labeled code is appropriately stored in an internal memory (not shown) and can be referred to as necessary.

Step S106: If all the data after filtering has not been extracted yet at this stage (No), the mode determination unit 34 returns to Step S100.
Step S100: The mode determination unit 34 checks whether the next extracted pair of codes are the same. When the codes of the pairs are not the same (No), the mode determination unit 34 proceeds to step S108.

Step S108: The pair whose codes are not the same is either “A, C” or “C, A”. Therefore, if either one is “mode A” and already labeled as “A ₁ , A ₂ , A ₃ ,...”, The other code is “mode C” (Yes (→ Go to step S110).

Step S110: Therefore, the mode determination unit 34 determines that the code paired with “A ₁ , A ₂ , A ₃ ,...” Is “mode C”.
Step S102: The mode determination unit 34 labels “C ₁ , C ₂ , C ₃ ,...” For each code content (altitude information). The labeled code is stored in an internal memory (not shown) as described above and can be referred to as necessary.

As described above, “A ₁ , A ₂ , A ₃ ,...” Or “C ₁ , C ₂ , C ₃ ,. When finished (step S106), the mode determination unit 34 returns to the caller's noise monitoring process (FIG. 7).

[In case of AC, CA]
As described above, if the response signal is a pattern of “A, A, C, A, A, C...”, “Mode A” is determined from the same pair of codes, and “mode C” is also determined therefrom. Can be determined. On the other hand, when the response signal is a pattern of “A, C, A, C...”, Since there is no pair having the same code, determination of “mode A” or “mode C” is performed from the extracted pair. I can't. In this case, the mode determination unit 34 executes the following procedure.

  Step S100: That is, when the mode determination unit 34 confirms that the newly extracted pair of codes are not the same (No), the process proceeds to step S108.

Step S108: As described above, a pair whose codes are not the same is either “A, C” or “C, A”, but “A ₁ , A ₂ , A ₃ ,. "Mode A" or "mode C" cannot be determined at this stage because there is nothing labeled as "" (No → to step S114).

Step S114: In this case, the mode determination unit 34 temporarily stores the pair of codes in the buffer.
Step S116: The mode determination unit 34 analyzes the temporal change tendency of the stored code.

  Step S118: Since a considerable number of samples are required for the analysis of the change tendency, the change tendency does not appear remarkably in several sets of samples. Therefore, if the change tendency cannot be analyzed sufficiently with the current number of samples (No), the mode determination unit 34 proceeds to step S106 and checks whether all data has been extracted. If all data has not yet been extracted (step S106: No), the mode determination unit 34 returns to step S100 and continues the process.

Then, the code of the next extracted pair is not the same (step S100: No), and there is no pair labeled as “A ₁ , A ₂ , A ₃ ,... Step S108: No), the mode determination unit 34 also stores the next pair in the buffer.

If all the data for one second has been extracted in step S106 (Yes), the process returns to the caller's noise monitoring process (FIG. 7), but the pair code is “A, C” or “C, A ”, and if there is no label labeled“ A ₁ , A ₂ , A ₃ ,... ”In the pair, the next call will also step S100 (No) → step S108 (No) → step The procedure of S114 is executed.

  In this way, when a considerable number of samples are stored in the buffer, the temporal change tendency of the code becomes clear.

[Change trend analysis example]
FIG. 9 is a diagram illustrating an analysis example of the temporal change tendency of the code. “Data” on the vertical axis is aircraft identification code information if it is “mode A”, and altitude information if it is “mode C”, but since the mode is unknown at the time of storage in the buffer, it is a pair for the time being. Is recognized as “data (13-bit value)”.

  When a certain number of samples (several to several tens) are stored in time series, it is easily determined that the code whose value does not change is “mode A” and the code where the change appears is “mode C”. be able to.

[See Figure 8: Mode determination process]
Step S120: When the analysis of the temporal change tendency of the code is completed (Step S118: Yes), the mode determination unit 34 sets each of “mode A” and “mode C” according to the code contents (by the machine identification code information). , Classified by altitude information) as “A _n , A _{n + 1} , A _{n + 2} ,...”, “C _n , C _{n + 1} , C _{n + 2} ,.
When labeling is performed in this manner, the mode determination unit 34 returns to the caller noise monitoring process (FIG. 7).

[Data alignment example]
FIG. 10 is a diagram illustrating an example in which time data and noise data are matched. 10A shows an example of the structure of time data, and FIG. 10B shows an example of the structure of noise data.

  As described above, the time data is created from the response signal every second, and for example, a structure in which “time”, “code (mode A or mode C)”, “radio wave intensity”, “number of appearances”, etc. are arranged Have The noise data is created when a noise event occurs as described above, and has a structure in which, for example, “time”, “elevation angle”, “azimuth angle”, and the like are arranged.

  Since the noise data includes “elevation angle” and “azimuth angle”, it is possible to know the direction of arrival of the noise source from the observation point based on such information. At this time, since the occurrence time of the noise event is recorded together, if the information of “mode A” and “mode C” is acquired from the time data that matches this time, “airframe identification code information” and “altitude The accuracy of collation with noise sources (specific information such as aircraft AP1, AP2) can be improved from "information".

  The present invention is not limited to the embodiments described above, and can be implemented with various modifications. In one embodiment, the airfield is the target area. However, the aircraft noise monitoring method and the aircraft noise monitoring apparatus can be used outside the airfield.

  The configuration of the observation unit 100 is an example, and the observation unit 100 may be configured by integrating a plurality of functional elements into one, or dividing one functional element into a plurality of functions.

DESCRIPTION OF SYMBOLS 10 Microphone-antenna unit 12 Radar receiving antenna 14 Noise measurement microphone 16 Sound direction-of-arrival identification microphone 20 Reception unit 22 Target signal group extraction unit 24 Temporary memory 26 Time interval analysis unit 28 Histogram creation unit 30 Filter unit 32 Appearance of average intensity Number calculation section 34 Mode determination section 36 Time data creation section 38 Noise measurement section 40 Matching section 100 Observation unit

Claims (8)

Receiving a response signal from an unspecified number of aircraft in response to an interrogation signal from an unspecified number of secondary surveillance radars (SSRs);
Calculating a mutual time interval for a plurality of response signals received within a predetermined time; and
Calculating individual frequencies for the calculated time intervals;
Filtering a specific group of response signals from among a plurality of response signals received within the predetermined time using a specific time interval at which the calculated frequency is maximized ;
An aircraft noise monitoring method comprising: matching the filtered response signal with the measured aircraft noise result . The aircraft noise monitoring method according to claim 1,
The filtering step includes:
An aircraft noise monitoring method comprising: extracting a pair of response signals received at the specific time interval from a plurality of response signals received within the predetermined time. The aircraft noise monitoring method according to claim 2 ,
In the response signals after filtering, when the response signal pairs received at the specific time interval have the same content, the response signals are determined to be body identification code information; and
In the response signal after filtering, when the response signal pair received at the specific time interval is not the same as each other, and it is determined that one response signal is the body identification code information, The aircraft noise monitoring method further comprising the step of determining that the other response signal is altitude information. In the aircraft noise monitoring method according to claim 3,
In the response signal after filtering, when the response signal pair received at the specific time interval is not the same as each other, and it is not determined that any response signal is the aircraft identification code information, Storing a pair of response signals in a buffer;
The accumulated response signals of the pair are monitored for changes in their contents over time, and those that do not change are determined to be aircraft identification code information, and those that have changed are determined to be altitude information. An aircraft noise monitoring method further comprising a step. In response to an interrogation signal from an unspecified number of secondary surveillance radars (SSR), a receiving unit that receives response signals emitted from an unspecified number of aircraft;
A time interval calculation unit for calculating a mutual time interval for a plurality of response signals received within a predetermined time by the receiving unit;
A frequency calculation unit that calculates individual frequencies for a plurality of time intervals calculated by the time interval calculation unit;
A filter unit for filtering a specific response signal group from among a plurality of response signals received within the predetermined time using a specific time interval at which the frequency calculated by the frequency calculation unit is maximized ;
A noise measurement unit for measuring aircraft noise;
An aircraft noise monitoring apparatus comprising: a matching unit that matches a response signal after filtering by the filter unit and a result of aircraft noise measured by the noise measurement unit . In the aircraft noise monitoring apparatus according to claim 5 ,
The filter unit is
An aircraft noise monitoring apparatus, wherein a pair of response signals received at the specific time interval is extracted from a plurality of response signals received within the predetermined time. The aircraft noise monitoring device according to claim 6 ,
A mode in which, in the response signals after filtering by the filter unit, when response signal pairs received at the specific time interval have the same contents, these response signals are determined to be body identification code information. A determination unit;
The mode determination unit
Among the response signals after filtering by the filter unit, it is determined that the pairs of response signals received at the specific time interval are not the same as each other, and one response signal is the body identification code information If so, an aircraft noise monitoring apparatus characterized in that the other response signal is determined to be altitude information. The aircraft noise monitoring device according to claim 7 ,
The mode determination unit
Among the response signals after filtering by the filter unit, it is determined that the pairs of response signals received at the specific time interval do not have the same contents, and any response signal is the body identification code information. If not, the response signal pair is stored in the buffer, the time-dependent changes in the contents of the stored response signals are monitored, and it is determined that the change does not appear is the machine identification code information. An aircraft noise monitoring apparatus characterized by determining that a change has occurred as altitude information.

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