JPS63291173A - Aircraft detector - Google Patents

Abstract

PURPOSE:To always discriminate the presence and the absence of an aircraft by operating a difference between an object temperature signal and a background temperature signal and outputting a difference temperature signal when the aircraft is present. CONSTITUTION:An objective temperature detecting part 1a and a background temperature detecting part 1b are disposed and the difference of the temperature signals from both detecting parts 1a, 1b is operated. Thereby, an influence due to the drift in the background temperature according to the elapse of a time, the change of weather or the like is removed, only the presence of the aircraft is detected, the aircraft can be detected according to a complete automation, for instance, when the aircraft is already present in a detecting area at the time of activating a device, the aircraft can be detected.

Description

[Detailed Description of the Invention] Industrial Field of Application In a control system for aircraft taxiing within an airport,
Determining the location and type of aircraft is an important matter, and the present invention uses a non-contact temperature sensor to detect the presence of an aircraft, and furthermore, determines the type of aircraft based on the temperature pattern output from the detection device. related to a device for

Conventional technology Devices for detecting aircraft and identifying the type of aircraft by temperature measurement are conventional (・.

Generally, when detecting the presence of an object to be measured, the difference in level between the level when the object is not present in the measurement area and the level when the object is present in the measurement area is If the level difference is above a certain threshold, it is determined that the object to be measured exists.An example is an electromagnetic method using a loop coil, which is used in some control systems for aircraft that are grounded within airports. It is used.

Problems to be Solved by the Invention In the case of an electromagnetic method such as the above-mentioned loop coil method, it is easy to determine the threshold value in advance, and it is easy to determine the threshold value in advance, and the measurement value can be easily determined due to weather or other environmental changes within the airport. The temporal change is not sudden, and automatic correction is relatively easy.

However, in temperature measurement systems that target outside air temperature, such as in airports, the outside air temperature changes rapidly over time and the range of change is large. It's not easy.

Furthermore, when considering a fully automated system, if the object to be measured is already present in the measurement area at the time of starting up the detection device to start measurement, so-called system start-up, it may be difficult to even determine the threshold value. Have difficulty.

Furthermore, it was even more difficult to identify the type of aircraft based on temperature measurements.

Means for Solving the Problems The present invention takes the aforementioned problems into account and provides a non-contact temperature sensor, such as an infrared radiation thermometer, which is aimed at an area where an aircraft will definitely pass through, and a non-contact temperature sensor, such as an infrared radiation thermometer, that is aimed at an area where an aircraft will definitely pass through. and a similar non-contact temperature sensor aimed at the area.
This problem is solved by measuring the difference in the levels detected by both temperature sensors and immediately detecting the presence of an aircraft.

In addition, aircraft have structural characteristics depending on the model, and in particular, from the perspective of temperature patterns, there are major characteristics in "number of engines,""relative positions of engines," and "relative distances between engines." The present invention focuses on the above-mentioned points and attempts to provide a device that goes beyond the means of detecting the presence of an aircraft to identify the model of the aircraft by extracting the various characteristic points.

That is, a target temperature detection section that uses a non-contact temperature sensor to detect temperature changes in a portion where an aircraft passes through, a background temperature detection section that uses a non-contact temperature sensor to detect temperature changes in a portion that an aircraft does not pass through, and a background temperature detection section that uses a non-contact temperature sensor to detect temperature changes in a portion that an aircraft does not pass through; A difference calculation unit that calculates a difference between the target temperature signal output from the detection unit and the background temperature signal output from the background temperature detection unit is provided, and only when an aircraft is present, the difference temperature is calculated by the difference calculation unit. The system detects the presence of an aircraft using a device that outputs a signal, and also uses a non-contact temperature sensor and an object temperature detection unit that detects temperature changes in the area where the aircraft passes. a background temperature detection unit that detects the temperature of a portion where the aircraft does not pass; a difference calculation unit that calculates a difference between a target temperature signal output from the target temperature detection unit and a background temperature signal output from the background temperature detection unit; an aircraft detection unit configured to output a differential temperature signal from the difference calculation unit only when an aircraft is present; and a temperature memory that quantizes and stores the output differential temperature signal from the aircraft detection unit. a temperature pattern forming section that forms a temperature pattern of a corresponding aircraft based on the time-series temperature data output from the temperature storage section; and a temperature pattern forming section that normalizes the temperature pattern output from the temperature pattern forming section with respect to the time of existence of the aircraft. a normalization processing unit that calculates the number of peaks, which is a feature quantity, of the aircraft from the normalized temperature pattern output from the normalization processing unit; a feature extraction unit consisting of a peak position measurement unit that calculates the position of the peak position, and a peak-to-peak distance measurement unit that calculates the distance between the peaks when a plurality of peaks exist from the normalized temperature pattern; a known pattern storage section that stores feature data; and an aircraft type determination section that compares the known reference feature data from the known pattern storage section with the feature data from the feature extraction section to determine the model of the aircraft. It is intended that the model of the aircraft can also be identified by the device that is included.

When used only to detect active aircraft, the target temperature signal from the object temperature detection unit aimed at the area where the aircraft passes, and the background temperature signal from the background temperature detection unit aimed at the area where the aircraft does not pass. Input the background temperature signal to the difference calculation section,
The aircraft detection device outputs a differential temperature signal to detect the presence or absence of an aircraft.

In addition, when identifying the type of aircraft, the above-mentioned aircraft detection device is used as the aircraft detection section, and the Anajig differential temperature signal from the aircraft detection section is input to the temperature storage section, and the temperature storage section stores the difference temperature. After the signal is A/D converted, it is stored as time series aircraft temperature data. The time-series aircraft temperature data is input to a temperature pattern forming section, noise is removed from the time-series temperature data, and a temperature pattern of the aircraft to be detected is created and output. The temperature pattern is input to the normalization processing unit, and the temperature pattern is normalized to the same time length so that the existence time of the moving aircraft is constant regardless of the type of aircraft, and the aircraft is normalized. Create a temperature pattern. The normalized temperature pattern is input to the feature extraction unit, and from the normalized temperature pattern, for example, the number of peaks and the peak position corresponding to the number 9 positions of the engine, which are structural characteristics of the aircraft, are obtained.

Extract features such as distance between peaks.

The aircraft features extracted by the feature extraction section are compared with a reference feature pattern prepared in advance for each aircraft model, and the model determination section identifies the model of the aircraft.

Example The embodiments shown in the drawings will be described below.

As shown in FIG. 1, the embodiment of the aircraft detection device set forth in claim 1 includes an aircraft detection section 1 comprising a target temperature detection section 1a, a background temperature detection section 1b, and a difference calculation section IC.
Consists only of

As shown in FIG. 4, the target temperature detection section 1a is a section that detects the temperature of a detection area A through which the aircraft 8 passes, and usually uses an infrared radiation thermometer as a non-contact temperature sensor. The detection area A is aimed to include the engine part 9 of the aircraft 8 which is the hottest.

As shown in FIG. 4, the background temperature detection section 1b is a section that detects the temperature of a background detection area B through which the aircraft 8 does not pass, and as a non-contact temperature sensor, an infrared radiation thermometer is usually used as described above. (・The detection area B is the aircraft 8
The target is set to a part of the sky that the aircraft does not pass through.

The difference calculation unit 1c receives the target temperature signal output from the object temperature detection unit 1a and the background temperature signal output from the background temperature detection unit 1b, and calculates the difference between the two temperature signals. Only when the aircraft 8 is present in the detection area A, the difference calculation unit 1c outputs a difference temperature signal.

By providing the above-mentioned target temperature detection section 1a and background temperature detection section 1b, and calculating the difference between the temperature signals from the rain detection sections 1a and 1b, it is possible to prevent the drift of the background temperature due to the passage of time, weather changes, etc. The influence is removed and only the presence of the aircraft 8 is detected, allowing a fully automated detection of the aircraft 8. Therefore, for example, even if an aircraft is already present in the detection area when the device is activated, it is possible to detect the aircraft.

Next, an embodiment of the aircraft detection device set forth in claim 2 has a configuration shown in FIG. As described above, an aircraft detection section 1 includes an object temperature detection section 1a, a background temperature detection section 1b, and a difference calculation section 1c as shown in FIG.
A temperature storage unit 2 that quantizes and stores the differential temperature signal output from the aircraft detection unit 1; and a temperature pattern that forms a temperature pattern of the corresponding aircraft 8 based on the time-series temperature data output from the temperature storage unit 2. a forming section 3; a normalizing processing section 4 that normalizes the temperature pattern output from the temperature pattern forming section 3 with respect to the detected presence time of the aircraft 8; and a normalizing temperature pattern output from the normalizing processing section 4. A feature extraction unit 5 that extracts and outputs feature data, and a known pattern storage unit 6 that stores reference feature data for each aircraft model in advance.
and an aircraft type determination unit 7 that compares the known reference feature data from the known pattern storage unit 6 with the feature data from the feature extraction unit 5 to determine the model of the aircraft. As shown in FIG. 3, a peak number measuring section 5 calculates the number of peaks, which is a feature quantity regarding the temperature of the aircraft 8, from the normalized temperature pattern output from the normalization processing section 4.
a, a peak position measurement unit 5b that calculates the position of a peak from the normalized temperature pattern, and an inter-peak distance measurement unit 5C that calculates the distance between the peaks when a plurality of peaks exist from the normalized temperature pattern. Became(・ru)

The temperature storage section 2 is a section that A/D converts the analog differential temperature signal input from the aircraft detection section 1 and stores it as time series temperature data, and the storage of the temperature data is predetermined. It is done at certain fixed time intervals. The fixed time interval is determined according to the processing time required by the aircraft detection system, and the lower limit of the time interval is determined by the response speed of the infrared radiation thermometer, which is a non-contact temperature sensor. The time-series temperature data from the temperature storage unit 2 that is input to the temperature pattern forming unit 3 may contain various types of noise, and after removing the noise, the temperature pattern forming unit 3 removes the noise. First 10 and last 11 of 8
is detected, and a temperature pattern of the aircraft 8 from the leading end 10 to the trailing end 11 is formed.

Possible causes of the noise include cracks in the temperature pattern, short sensing times, etc.
These are removed by off-delay processing and on-delay processing, respectively.

In the normalization processing section 4, in order to identify various aircraft having different body lengths by the temperature patterns inputted from the temperature pattern forming section 3, the time axis of the temperature pattern from the head 10 to the tail 11 of the aircraft 8 is calculated. Direction normalization processing is required. As shown in FIGS. 5 and 6, the normalization process performs time axis processing on the temperature pattern obtained by the temperature pattern forming section 3 so that the existence time of all aircraft of different types is constant. By this process, as shown in FIG. 5, in the case of the same model B-747, NLl, &2. Na
, 3, a normalized temperature pattern characteristic of the B-747 can be obtained, and as shown in Fig. A normalized temperature pattern is obtained that characterizes the aircraft.

As mentioned above, the normalized temperature pattern input to the feature extraction unit 5 has various structural characteristics depending on the aircraft model, but when the aircraft 8 is inspected from the leading end 10 to the trailing end 11 in the longitudinal direction of the aircraft 8, The thing that has the biggest influence on the temperature pattern when the engine is heated, and that differs from model to model, is the structure of the engine part that reaches the highest temperature. Therefore, as described above, the feature extraction unit 5 of the present invention includes a peak number measurement unit 5a, a peak position measurement unit 5b, and an inter-peak distance measurement unit 5c,
The characteristics of the number of engines, the relative positions of the engines, and the relative distances between the engines are measured from the input normalized temperature patterns.

The aforementioned measurement of the number of engine bases is performed by measuring the number of peaks in the normalized temperature pattern, as shown in FIGS. 5 and 6.

The normalized temperature pattern has the same number of peaks as the number of engines scanned, and can be classified as follows based on the number of peaks.

When the number of peaks is O... It is a small aircraft with no engine in the scanned detection area.

If the number of peaks is 1, it is a two-engine aircraft with one engine on the left and right.

If the number of peaks is 2, it is a three-engine aircraft with engines on the left and right and in the tail, or a four-engine aircraft with two engines on the left and right.

FIG. 4 shows a model with two peaks.

The above-mentioned relative position of the engine is measured by measuring the peak position of the normalized temperature pattern.

The normalized temperature pattern has a peak depending on the relative position of the engine, and can be classified as follows based on the difference in peak position based on the difference in the relative position of the engine.

A peak position in the front center of the normalized temperature pattern indicates the presence of a main wing engine.

A peak position at the rear of the normalized temperature pattern indicates the presence of a tail engine.

The above-described relative distance between the engines is measured by measuring the distance between peaks of the normalized temperature pattern.

Measuring the relative distance between engines is effective for classifying aircraft with three or more engines.

That is, when a plurality of peaks exist in the normalized temperature pattern, the model is classified by determining the distance between the peaks. For example, if the distance between the first and second peaks is large...there are three engines. That is, it has a main wing engine and a tail engine.

If the distance between the first and second peaks is small...the aircraft has four engines, that is, two main wing engines are provided on each side.

The known pattern storage section stores known reference characteristic data for each model corresponding to the number of engines, the relative positions of the engines, and the relative distances between the engines.

As mentioned above, different types of aircraft are characterized by differences in the structure of their engine parts. The device of the present invention attempts to identify the model by utilizing the above-mentioned characteristics, and as described above, information regarding the engine can be obtained from information regarding the peak of the normalized temperature pattern.

The known pattern storage section stores reference characteristic data of "number of peaks", "peak position", and "distance between peaks" for each aircraft by model.

The model determination section extracts "peak number", "peak position", and "peak position" extracted by the feature extraction section from the normalized temperature pattern.
Each feature data of "distance between peaks" and reference feature data stored in advance in the known pattern storage section are input and compared to identify the model of the corresponding aircraft.

Effects of the Invention The present invention uses two non-contact temperature sensors to aim at an area where an aircraft will definitely pass and an area where an aircraft will definitely not pass, thereby determining the presence or absence of an aircraft. It is possible to immediately detect the presence of an aircraft from the difference in the detection levels of both non-contact temperature sensors, regardless of whether or not there is an aircraft at the time of starting the measurement, without considering any possible threshold value. It is possible to detect and extract the structural characteristics of aircraft models and instantly identify the aircraft model, which is useful for identifying the presence or absence of aircraft moving within an airport at any given time.

[Brief explanation of the drawing]

Fig. 1 is an explanatory diagram of the structure of an embodiment of the aircraft detection unit, Fig. 2 is an explanatory diagram of the arrangement of an embodiment capable of identifying the type of aircraft, Fig. 3 is an explanatory diagram of the configuration of the feature extraction unit same as above, and Fig. 4 is an explanatory diagram of the structure of the embodiment of the aircraft detection unit. 5 and 6 are normalized temperature pattern diagrams for each model. ■=Aircraft detection section, 1a: Target temperature detection section, 1b=Background temperature detection section, 1c: Difference calculation section, 2: Temperature storage section, 3:
Temperature pattern forming section, 4: Normalization processing section, 5: Feature extraction section, 6: Known pattern storage section, 7 Two model determination section, 8: Aircraft.

Claims (2)

[Claims] (1) A target temperature detection unit that uses a non-contact temperature sensor to detect a temperature change in a part where an aircraft passes, a background temperature detection unit that uses a non-contact temperature sensor to detect a temperature in a part that an aircraft does not pass, and the target temperature A difference calculation unit that calculates a difference between the target temperature signal output from the temperature detection unit and the background temperature signal output from the background temperature detection unit is provided, and the difference calculation unit calculates the difference only when an aircraft is present. An aircraft detection device characterized by outputting a temperature signal (2) A target temperature detection unit that uses a non-contact temperature sensor to detect temperature changes in the area where the aircraft passes, a background temperature detection unit that uses a non-contact temperature sensor to detect the temperature of the area that the aircraft does not pass, and the target temperature detection unit. and a difference calculation unit that calculates a difference between the target temperature signal output from the background temperature detection unit and the background temperature signal output from the background temperature detection unit, and only when an aircraft is present, the difference temperature signal is output from the difference calculation unit. An aircraft detection section configured to output temperature signals, a temperature storage section that quantizes and stores the differential temperature signal output from the aircraft detection section, and time-series temperature data output from the temperature storage section. A temperature pattern forming section that forms a temperature pattern of an aircraft, a normalization processing section that normalizes the temperature pattern output from the temperature pattern formation section with respect to the existence time of the aircraft, and a normalization processing section output from the normalization processing section. A peak number measuring unit that calculates the number of peaks, which is a feature quantity regarding the temperature of an aircraft, from the temperature pattern; a peak position measuring unit that calculates the position of the peak from the normalized temperature pattern; and a case where there are multiple peaks from the normalized temperature pattern. a feature extraction unit comprising a peak-to-peak distance measurement unit that calculates the distance between the peaks; a known pattern storage unit that stores reference feature data for each aircraft model in advance; An aircraft detection device comprising: an aircraft type determination unit that compares reference feature data and feature data from the feature extraction unit to determine the type of aircraft.