JP2001305203A - Image object detection device - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a means capable of instantly determining the traveling direction of an object. SOLUTION: In the embodiment shown in Fig. 11, plural image signals having different detection wavelength bands are inputted to plural binary processing parts 17 formed corresponding to the image signals one-on-one along with position data of a significant object. The plural binary processing parts 17 carry out binary processing in relation to the significant object part of the image signal. The plural binary processing image signals binary processed in the binary processing parts 17 are outputted to plural feature amount calculating parts 18 formed corresponding to the plural binary processing parts 7 one-on-one. The plural feature amount calculating part 18 calculate feature amounts such as the area of significant object, the longitudinal center of gravity, the lateral center of gravity, the overall center of gravity, the longitudinal length, the lateral length, the ratio of the longitudinal length to the lateral length or luminance information before the binary processing the feature amount data of the plural feature amount calculating parts 18 ate outputted to an object direction determination part 19. The object direction determination part 19 calculates and outputs the traveling direction of the object.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an image target detecting device for detecting and determining a target from an image signal.

[0002]

2. Description of the Related Art FIG. 27 shows a conventional image target detecting apparatus. In FIG. 27, 1 is an infrared imaging unit, 3 is a target determination unit, and 16 is a threshold value calculation unit.

Next, the operation of FIG. 27 will be described. The infrared imaging unit 1 outputs infrared light from the outside world as an infrared image signal. The threshold value calculator 16 calculates a threshold value t from the input image signal. "Equation 1" is used as an example of a threshold value calculation method. The target determination unit 3 binarizes the image signal using the threshold value calculated by the threshold value calculation unit 16, and determines a significant target based on the binarized image signal. Hereinafter, a case where the infrared imaging unit 1 has sensitivity to far infrared rays and a case where it is sensitive to mid-infrared rays will be described as an example. FIG. 28, FIG.
Reference numeral 9 denotes an example of far-infrared and mid-infrared image signals and a binarized image when the same background is imaged. As shown in FIG. 28, when far infrared rays are used, only the target signal is binarized and determined to be the target. On the other hand, when the mid-infrared ray is used as shown in FIG. 29, the target signal and the cloud signal (clutter) other than the target are binarized and determined as the target. As described above, in a system using only the mid-infrared ray, when there is a high-luminance object other than the target such as a cloud reflecting sunlight, the probability of erroneously detecting a signal component other than the target as the target (hereinafter, false alarm) Probability).

[0004]

(Equation 1)

[0005] Fig. 30 shows an example of transmittance in summer and winter from 1 to 15 [μm]. As shown in this figure, the mid-infrared ray shows a stable transmittance throughout the year, but the far-infrared ray has a significantly lower transmittance in summer than in winter. As an example, a slant pass at an altitude of 60 [m] in the mid-latitudes of LOWTRAN,
In the mid-infrared region, summer transmittance can be as high as 75% in winter, whereas in the far-infrared region, summer transmittance can be as low as 40% in winter. This is because far infrared rays have a large absorption due to the molecular weight of water. For this reason, in a system using far-infrared rays, there is a problem that it is more difficult to secure performance in summer or at sea when the molecular weight of water is large compared to a system using mid-infrared rays.

[0006] The conventional image target detecting device as described above has the following problems. That is, for example, when performing the target determination using only the image signal in the mid-infrared region,
If there is a high brightness object other than the target, such as clouds reflecting sunlight,
There is a problem that the false alarm probability increases. Further, for example, when the target determination is performed using only the image signal in the far-infrared region, there is a problem that it is difficult to secure performance in summer or at sea where the water molecular weight is large.

To solve the above problem, Japanese Patent Application Laid-Open No. 61-769
No. 3 of the 3-5 μm band and the 8-12 μm band shown in
An infrared detection device that uses two infrared wavelength bands and enables target detection regardless of the seasonal location day and night has been invented. FIG. 31 is a block diagram of the present invention. In FIG. 31, 5 is an optical system, 9 is an amplifier unit, 32 is a photodetector, 33 is scan conversion means, 34 is target detection means, 35 is level comparison means,
Reference numeral 6 denotes a determination unit.

The operation of FIG. 31 will be described. Optical system 5
Infrared rays transmitted through the light detecting elements 32 having different sensitivity wavelengths.
a and 32b. Each output signal of the photodetector is amplified by the amplifier unit 9, scan-converted by the scan conversion unit 33, converted into a serial video signal, and output. Upon receiving one output of the conversion unit 33, the target detection unit 34 detects a target. The level comparing means 35 measures the level of each serial video signal and compares how much one is higher or lower than the other.
Specifically, the signal intensity in the 3-5 μm band is divided by the signal intensity in the 8-12 μm band. The determination means 36 is the target detection means 3
4 to determine whether it is the target or not based on the divided value of the level comparing means 35. That is, if the division value at the target signal portion is equal to or less than the reference value, it is determined that the target is the target. This will be described with reference to FIGS. 28 and 29. When the target is cloud clutter, it is observed in the 3 to 5 μm band, but is not observed in the 8 to 12 μm band, and the division value is a very large value. However, when the target is an aircraft, the division value falls within a certain value because the target is observed in both wavelength bands. However, when the target is flying at a sufficiently high speed compared to the cruising speed, use of afterburner (hereinafter referred to as A / B), missile launch, etc.
If the signal strength in the m band is higher than the signal strength in the 8 to 12 μm band, the target is removed as clutter in this system. Also, in summer or at sea where the water molecular weight is high, targets that are not observed in the 8-12 μm band but are observed only in the 3-5 μm band are also removed.

[0009]

The above-mentioned conventional image target detection apparatus has the following problems. If the detection target is an aircraft, knowing the direction of travel of the target is an important factor for determining the threat level and taking effective measures. However, with the current image target detection device, it is necessary to determine whether the target is head-on or tail-on. Was visually checked, and it was determined that the vehicle was approaching when the brightness became bright, and it was determined that it was moving away when it became dark. When the target is very far away, it is not easy to visually confirm the change in luminance, and it takes several tens of seconds or more. During this time, even if the enemy was flying at cruising speed, the enemy approached several kilometers or more, shortening the time required for effective countermeasures. As described above, there is a problem that the traveling direction of the target cannot be determined instantaneously. Even if it was found that the aircraft was flying in the direction of the aircraft, it was not possible to instantly determine whether the aircraft was heading up, down, left, or right on the monitor displaying the image for the same reason as before.

SUMMARY OF THE INVENTION The present invention has been made to solve such a problem, and an object of the present invention is to provide means capable of instantaneously determining the traveling direction of a target.

[0011]

An image target detecting apparatus according to the present invention includes a plurality of binarizing sections provided corresponding to infrared image signals in a plurality of different wavelength bands for performing binarization near a significant target position. A target area, a vertical center of gravity, a horizontal center of gravity, a vertical length, a horizontal length,
A plurality of feature value calculation units provided corresponding to a plurality of binarization units for calculating a feature value such as a ratio of a vertical length to a horizontal length;
A target direction determining unit that determines a target traveling direction from outputs of the plurality of feature amount calculating units.

The image target detecting apparatus according to the present invention is characterized in that data such as an area for each target wavelength, a center of gravity in a vertical direction, a center of gravity in a horizontal direction, a vertical length, a horizontal length, a ratio of a vertical length to a horizontal length, and the like are obtained. And a servo mechanism that outputs angle information and range information of the target with respect to its own device, and a target identification unit that performs target identification based on outputs from the target direction determination unit, the servo mechanism, and the target data unit. It is comprised by these.

[0013]

DESCRIPTION OF THE PREFERRED EMBODIMENTS Embodiment 1 FIG. 1 is a block diagram showing an embodiment of the present invention. 1 is an infrared imaging unit, 2 is a luminance normalization unit, 3 is a target determination unit, and 4 is a spectral luminance data unit.

In the embodiment shown in FIG. 1, the image signals output from the infrared imaging section 1 for outputting the infrared image signals a and b of a plurality of different wavelength bands for the same target are sent to a plurality of luminance normalizing sections 2. Input and normalization of luminance are performed.
The plurality of normalized image signals are input to the target determination unit 3. The spectral luminance data section 4 holds data of various objects (such as a target and clutter other than the target) as a region of a multidimensional luminance coordinate system having a normalized luminance signal for each of the plurality of different wavelength bands as an orthogonal axis. are doing. The target determining unit 3 compares the plurality of normalized image signals with the output of the spectral luminance data unit 4 and determines a significant target based on whether or not it is included in the target area.

The operation will be described below. It is necessary to normalize the image signals of a plurality of different wavelength bands in order to match the luminance scale of the spectral luminance data unit 4 stored in advance. Here, the reference value fin (α,
Using β), the luminance normalization unit 2 performs normalization by the operation of “Equation 2”.

[0016]

(Equation 2)

As an example of a plurality of image signals input to the luminance normalizing section 2, a case where there are two images, a middle infrared region image and a far infrared region image, will be described. First, an example of the contents of the spectral luminance data section 4 is shown in FIG. The vertical axis represents the luminance in the far-infrared region, and the horizontal axis represents the luminance in the mid-infrared region. The drawing shows the aircraft target region, cloud clutter region, and exhaust gas region. The cloud data in this figure is about 30 daytime altitude.
FIG. 2 is a simplified diagram based on data of altocumulus and cirrus taken at 00 [m] and an imager sensitive to mid-infrared and an imager sensitive to far-infrared from the ground. The data of the aircraft in the figure are values calculated on the assumption that the temperature of the cruising aircraft has increased due to aerodynamic heating. Further, the exhaust gas data in the figure is a value calculated from the temperature of the exhaust gas and its components.

Next, the target determining section 3 will be described. The target determination unit 3 creates a brightness map as shown in FIG. 3 from the output of the brightness normalization unit 2. This figure shows the infrared imaging unit
This is a plot of the luminance at the same position (pixels at the same coordinates) on the luminance map in the images of 1a and the infrared imaging unit 1b, and is the result of performing this operation for all the pixels.
FIG. 3 is compared with the target area of the spectral luminance data unit 2 to detect a significant target. FIG. 4 is an example in which a significant target is determined by superimposing FIG. 2 on FIG. In FIG. 4, the plot surrounded by the ellipse of the aircraft target is determined to be the target.

As described above, by using a plurality of image signals having different wavelength bands, only a significant target can be determined by a low / false alarm.

Embodiment 2 FIG. 5 is a block diagram showing Embodiment 2 of the present invention. In the figure, 5 is an optical system, 6 is a filter rotator, 7 is a filter rotator controller,
8, an infrared detector; 9, an amplifier; and 10, a timing unit.

An example of the configuration of the optical system 5, filter rotator 6, and infrared detector 8 will be described below. Optical system 5
Is assumed to transmit light from near infrared to far infrared, and the infrared detector 8 is an infrared detector having sensitivity from near infrared to far infrared. FIG. 6 shows an example of the filter rotator 6, which includes a near-infrared band-pass filter 11, which transmits only infrared rays in the near-infrared region, a middle-infrared band-pass filter 12, and a far-infrared band-pass filter 1.
3 is shown.

Next, the operation will be described. The filter rotator control unit 7 controls the filter rotator 6 by the timing unit 10.
To detect the state of the filter rotating body 6 (which filter is inserted between the optical system 5 and the infrared detector 8). The filter rotator 6 controls the angular velocity ω under the control of the filter rotator controller 7.
Suppose that it is rotating at.

FIG. 7 shows the spectral radiance characteristics of an object. When the near-infrared band-pass filter 11 is passing between the optical system 5 and the infrared detector 8 at a certain timing, infrared rays in the near-infrared region shown in FIG. The infrared detector 8 outputs a signal corresponding to the incident infrared energy to the amplifier unit 9. The amplifier 9 amplifies the output signal of the infrared detector 8 and outputs a near infrared image signal. At the next timing, when the bandpass filter for the mid-infrared ray or the far-infrared ray is passing between the optical system 5 and the infrared ray detector 8, the output of the amplifier section 9 is used to output the image signal of the mid-infrared ray or the far-infrared ray. An image signal is output.

As described above, by using the same infrared detector in a time-division manner, a single infrared detector can obtain a plurality of image signals having different detection wavelengths.

Third Embodiment FIG. 8 is a block diagram showing a third embodiment of the present invention, and shows a method of providing a reference value for adjusting a luminance scale to the infrared imaging unit 1 shown in the first embodiment. It is a thing. In the figure, 1 is an infrared imaging unit, 5 is an optical system, 8 is an infrared detector, 9 is an amplifier unit, and 14 is an infrared reference light generation unit.

An infrared reference light generator 14 is provided so as to form an image of light serving as a reference for normalization on a part of the imaging surface of the infrared detector 8. The operation is normalized by the luminance normalization unit 2 using the light generated by the infrared reference light generation unit 14. Subsequent processing is the same as in the first embodiment.

In this manner, a significant target can be determined by a low / false alarm using a plurality of image signals having different wavelength bands.

Fourth Embodiment FIG. 9 is a block diagram showing a fourth embodiment of the present invention, which is an embodiment not using the method shown in the third embodiment. In the figure, 1 is an infrared imaging unit, 2 is a luminance normalization unit, 3 is a target determination unit, 4
Denotes a spectral luminance data section, and 15 denotes a reference value determination section.

As described in the first embodiment, in order to match the luminance scale of the spectral luminance data section 4, it is necessary to normalize the image signal. In general, it can be assumed that the sky temperature is a blackbody and absolute zero. When detecting an aerial target, it is generally considered that the sky is present in all or a part of the image. Therefore, in the present embodiment, a case where normalization is performed using the sky as a reference value will be described.

In the embodiment shown in FIG. 9, image signals in a plurality of wavelength bands are input to a reference value determination unit 15, which searches for a sky portion of an image, adds reference data to a part of the plurality of image signals, and outputs the result. . Subsequent processing is the same as in the first embodiment.

The operation of the reference value judgment section 15 will be described below. Among a plurality of image signals having different detection wavelength bands input to the reference value determination unit 15, a portion having the lowest common brightness among the image signals is assumed to be a black body and an absolute zero degree. Judge as the sky. Then, the luminance value of that position is determined by the reference value position fin (α,
Write to β). The plurality of image signals to which the reference value has been added in this manner are output to the plurality of luminance normalization units 2.

As described above, by using the brightness of the sky as the reference brightness, a significant target can be reduced by using a plurality of image signals having different wavelength bands even for an image signal having no reference value for adjusting the brightness scale. Can be determined by false alarm.

Embodiment 5 FIG. FIG. 10 is a block diagram showing a fifth embodiment of the present invention. There is no reference value for adjusting the luminance scale to a part of the image signal as shown in the third embodiment, and the fifth embodiment is shown in the fourth embodiment. This is an embodiment in which normalization is not performed in such a sky portion. 1 is an infrared imaging unit, 3 is a target determination unit, and 16 is a threshold value calculation unit.

In the embodiment shown in FIG. 10, a plurality of image signals having different detection wavelength bands are input to the target determination section 3 and the threshold value calculation section 16. The threshold calculator 16 calculates a target area based on a plurality of image signals. Subsequent processing is the same as in the above embodiment.

The operation of the threshold value calculator 16 will be described below. It is assumed that there are two input image signals as an example of the operation of the threshold value calculation unit 16. The respective threshold values are calculated using, for example, “Equation 1” from two input image signals having different detection wavelength bands. This gives two thresholds t1
And t2 are calculated. From this value, a threshold area is calculated using "Equation 3". Thereby, the same effects as in the third and fourth embodiments can be obtained.

[0036]

(Equation 3)

Embodiment 6 FIG. FIG. 11 is a block diagram showing Embodiment 6 of the present invention. 17 is a binarization unit, 1
Reference numeral 8 denotes a feature value calculation unit, and 19 denotes a target direction determination unit.

In the embodiment shown in FIG. 11, a plurality of image signals having different detection wavelength bands are sent to a plurality of binarizing sections 17 provided in one-to-one correspondence with the image signals together with significant target position data. Is entered. Plural binarization units 17
Then, binarization is performed on the significant target portion of the image signal.
The plurality of binarized image signals binarized by the plurality of binarization units 17 are output to a plurality of feature amount calculation units 18 provided in one-to-one correspondence with the plurality of binarization units 17. Is done. In the plurality of feature value calculating units 18, the area of the significant target, the center of gravity in the vertical direction, the center of gravity in the horizontal direction, the total center of gravity, the vertical length, the horizontal length,
A feature amount such as a ratio between the vertical and horizontal lengths or luminance information before binarization is calculated. The feature data of the plurality of feature calculators 18 is output to the target direction determiner 19. The target direction determination unit 19 calculates and outputs a target traveling direction.

The operation will be described below. Where 2
The images input to the value conversion unit 17 are, for example, an image captured in the mid-infrared region and an image captured in the far-infrared region. It is assumed that the target is an aircraft as an example. FIG. 12 is an image in which the side surface of the aeronautical target is captured in each wavelength range. FIG. 13 is an image in which the front of the aviation target is captured in each wavelength range. The mid-infrared region is more sensitive to hot objects than the far-infrared region. Therefore, as shown in the figure, the mid-infrared image clearly shows the exhaust gas (plume) emitted from the aircraft. In contrast, far-infrared images show the plume smaller than the former. Therefore, the horizontal center of gravity position P1 of the mid-infrared image is closer to the plume (rear side) than the center of gravity P2 of the far-infrared image. In FIG. 13, since the plume is not visible, the horizontal center of gravity position of the mid-infrared image and the far-infrared image are at the same position. From the above, by comparing the horizontal center of gravity position of the mid-infrared image with the horizontal center of gravity position of the far-infrared image, it is possible to determine whether the target is moving left or right on the image monitor. An example of a specific determination is “Equation 4”
Shown in In addition, by comparing the center of gravity in the vertical direction, it is possible to determine whether the vehicle is moving up or down on the image monitor. In the case of head-on, the far-infrared image has higher brightness than the middle-infrared image, and in the case of tail-on, the middle-infrared image has higher brightness, contrary to the former. Thereby, when the image is taken on the monitor, the depth direction can be known.

[0040]

(Equation 4)

As described above, by using a plurality of image signals having different wavelength bands, it is possible to instantly determine in which direction the image signal is traveling on the image monitor. Thus, a target with a high threat level can be selected.

Embodiment 7 FIG. 14 is a block diagram showing a seventh embodiment of the present invention, in which the sixth embodiment is further advanced and a target identification function is added.
Up to 19 target direction determination units are the same as in the sixth embodiment, reference numeral 20 denotes a target identification unit, reference numeral 21 denotes a target data unit, and reference numeral 22 denotes a servo mechanism.

In this embodiment, it is assumed that the target is a ship. The target data section 21 includes the height of the hull, the height of the center of gravity of the chimney,
Information such as the total length and the total width is stored in advance. The target identification unit 20 identifies a target based on data of the target data unit 21 and target depression angle information and range information of the servo mechanism 22 with respect to the own device. It is assumed that the image signals input to the binarization unit 17 are a middle infrared ray and a far infrared ray as in the fifth embodiment. The difference between a ship and an aircraft is that the exhaust gas from the ship is exhausted from the chimney and that the ship is considered to have almost no vertical movement. FIG.
5 shows a mid-infrared image and a far-infrared image. As for the mid-infrared ray, the exhaust gas part looks better than the far-infrared ray.
By comparing this, the traveling direction can be determined.

The operation after the target direction judging section 19 will be described below. As shown in FIG. 16, by optimizing the binarization processing, it is possible to selectively display only the chimney portion with the mid-infrared ray. FIG. 17 shows the center of gravity P1 of the hull portion and the center of gravity P2 of the chimney portion of a ship traveling at an aspect of 俯 with respect to the own ship in the depression angle θ direction. Assuming that the point on the draft surface opposite to the traveling direction is (0, 0), P1 (X1, Y1), P2
(X2, Y2) can be calculated by "Equation 5". The scale m of the ship on the screen can be calculated by "Equation 6" from the range information d of the servo mechanism 22. Since the depression angle information θ is known from the servo mechanism 22, there are five unknowns and four equations, so that the ratio of the height of the hull, the height of the chimney center of gravity, the total length, and the total width can be known. As a result, identification of the target is possible.

[0045]

(Equation 5)

[0046]

(Equation 6)

Embodiment 8 FIG. FIG. 18 is a block diagram showing Embodiment 8 of the present invention. 23 is a RAM, 24 is a rise time measurement unit, and 25 is an identification unit.

In the following, as an example, a tracking target is an aircraft, and attention is paid to its maximum brightness to distinguish between A / B use and missile launch. First, FIG. 19 shows the maximum luminance-time characteristics when the A / B is used and when the missile is fired. FIG. 19 shows a time t1 (hereinafter referred to as a rise time) from the time when the rate of increase of the maximum luminance becomes equal to or more than the threshold value to a time when the maximum value is maintained, and a time t2 (hereinafter referred to as a maximum luminance maintenance time) when the maximum value is maintained. The time from the maximum value to the steady state t3 (hereinafter, the time from the maximum value to the steady value), the ratio of the maximum value NM to the steady brightness value NK (the maximum / stationary ratio), Luminance from steady state to steady state-
The half width t4 of the time characteristic is shown.

The operation will be described below. RAM23
Stores the maximum luminance, average luminance, area, etc. of the tracking target for a plurality of frames. The rise time measuring unit 24 of this example monitors the rate of change of the maximum luminance per Δt time, and when the rate of change exceeds the rate of change caused by shaking of the optical system 5 or the like, the rise from that point in time is started. The time t1 is measured. The discrimination unit 25 discriminates the rise time t1 between A / B use and missile launch using, for example, "Equation 7" and outputs the result.

[0050]

(Equation 7)

By measuring the rise time as described above, it is possible to monitor the A / B use of the tracking target and the missile launch.

Embodiment 9 FIG. FIG. 20 is a block diagram showing Embodiment 9 of the present invention. Reference numeral 26 denotes a maximum value maintaining time measuring unit, and the other components are the same as those of the eighth embodiment.

In this embodiment, a maximum maintaining time measuring section 26 is provided instead of the rising time measuring section 24 of the eighth embodiment. In the operation, the maximum maintenance time t2 shown in FIG. 19 is measured, and A / A is calculated using, for example, “Equation 8”.
B Use and missile launch are identified and the result is output. As a result, it is possible to monitor the A / B use of the tracking target and the missile launch.

[0054]

(Equation 8)

Embodiment 10 FIG. FIG. 21 is a block diagram showing a tenth embodiment of the present invention. Reference numeral 27 denotes a time measuring unit from the maximum value to the steady value, and the other components are the same as in the eighth embodiment.

In this embodiment, instead of the rise time measuring section 24 of the eighth embodiment, a time measuring section 27 from a maximum value to a steady value is provided. In the operation, the time t3 from the maximum value to the steady value shown in FIG. 19 is measured, A / B use and missile launch are discriminated using, for example, "Equation 9", and the result is output. As a result, it is possible to monitor the A / B use of the tracking target and the missile launch.

[0057]

(Equation 9)

Embodiment 11 FIG. FIG. 22 is a block diagram showing an eleventh embodiment of the present invention. Reference numeral 28 denotes a ratio measuring unit, and the other components are the same as in the eighth embodiment.

In this embodiment, a ratio measuring unit 28 is provided instead of the rise time measuring unit 24 of the eighth embodiment. The operation measures the maximum / steady ratio shown in FIG. 19, discriminates between A / B use and missile launch using, for example, "Equation 10", and outputs the result. This makes it possible to monitor the A / B usage of the tracking target and the missile launch.

[0060]

(Equation 10)

Embodiment 12 FIG. FIG. 23 is a block diagram showing a twelfth embodiment of the present invention. Reference numeral 29 denotes a half width width measurement unit, and the other components are the same as those in the eighth embodiment.

In this embodiment, a half width width measuring unit 29 is provided instead of the rise time measuring unit 24 of the eighth embodiment. In the operation, the half width is measured as shown in FIG. 19, and A / B use and missile launch are discriminated using, for example, "Equation 11", and the result is output. This allows
It is possible to monitor A / B usage and missile launch of tracking targets.

[0063]

[Equation 11]

Embodiment 13 FIG. FIG. 24 is a block diagram showing a thirteenth embodiment of the present invention. 25 is an identification unit,
Numeral 30 denotes a calculation unit.

In the following, a distinction will be made between an example, the use of A / B as an aviation target, and the launch of a missile. First, in FIG.
4 shows an example of the spectral luminance of smoke exhausted from an A / B and a missile. As shown in this figure, both the smoke emission from the A / B and the missile have peaks in the wavelength bands A and B, and the areas (luminance) SA and S
The ratio with B is different.

The operation will be described below. Image signals of a plurality of tracking targets having different wavelength bands are input to the arithmetic unit 30. Here, as an example, it is assumed that the image signal of the tracking target has been captured in the wavelength band A and the wavelength band B. The calculation unit 30 calculates the ratio between SA and SB and outputs the result to the identification unit 25.

The discriminator 25 discriminates between A / B use and missile launch according to "Equation 12" and outputs the result. As a result, it is possible to monitor the A / B use of the tracking target and the missile launch.

[0068]

(Equation 12)

Embodiment 14 FIG. FIG. 26 is a block diagram showing a fourteenth embodiment of the present invention. Reference numeral 31 denotes a general identification unit.

The operation will be described below. A plurality of identification results of A / B use and missile launch as an example of the eighth to thirteenth embodiments are input to the overall identification unit 31. Comprehensive identification unit 31
Then, as shown in "Expression 13", the outputs of the respective identification units are weighted to perform overall identification, and the result is output. This makes it possible to comprehensively distinguish between A / B use and missile launch.

[0071]

(Equation 13)

[0072]

According to the present invention, by using a plurality of image signals having different detection wavelength bands, the position of the center of gravity in the horizontal direction, the position of the center of gravity in the vertical direction, or the length of each wavelength is measured. Direction can be determined instantly.

According to the present invention, the advancing direction of the target can be determined by measuring the horizontal center of gravity, the vertical center of gravity, or the length of each wavelength using a plurality of image signals having different detection wavelength bands. It is possible to make an instantaneous decision and identify a target.

[Brief description of the drawings]

FIG. 1 is a block diagram showing an image target detection device according to a first embodiment of the present invention.

FIG. 2 is a diagram showing an example of the content of a spectral luminance data section.

FIG. 3 is a diagram illustrating an example of creating a luminance map.

FIG. 4 is a diagram showing an example in which a significant goal is determined.

FIG. 5 is a block diagram showing an image target detection device according to a second embodiment of the present invention.

FIG. 6 is a diagram illustrating an example of a filter rotating body.

FIG. 7 is a diagram showing wavelength and spectral luminance.

FIG. 8 is a block diagram showing an image target detection device according to a third embodiment of the present invention.

FIG. 9 is a block diagram showing an image target detection device according to a fourth embodiment of the present invention.

FIG. 10 is a block diagram showing an image target detection device according to a fifth embodiment of the present invention.

FIG. 11 is a block diagram illustrating an image target detection device according to a sixth embodiment of the present invention.

FIG. 12 is a diagram showing image centroids of mid-infrared rays and far-infrared rays on the side of the aircraft.

FIG. 13 is a diagram showing image centroids of mid-infrared rays and far-infrared rays in front of an aircraft.

FIG. 14 is a block diagram showing an image target detection device according to a seventh embodiment of the present invention.

FIG. 15 is a diagram showing the center of gravity of images of mid-infrared rays and far-infrared rays on the side of a ship.

FIG. 16 is a selection diagram of a chimney portion.

FIG. 17 is a diagram showing the center of gravity of a ship and the center of gravity of a chimney.

FIG. 18 is a block diagram showing an image target detection device according to an eighth embodiment of the present invention.

FIG. 19: Maximum brightness when using A / B and when launching a missile
FIG. 4 is a diagram showing time characteristics.

FIG. 20 is a block diagram showing an image target detection device according to a ninth embodiment of the present invention.

FIG. 21 is a block diagram showing an image target detection device according to a tenth embodiment of the present invention.

FIG. 22 is a block diagram showing an image target detection device according to an eleventh embodiment of the present invention.

FIG. 23 is a block diagram showing an image target detection device according to a twelfth embodiment of the present invention.

FIG. 24 is a block diagram showing an image target detection device according to a thirteenth embodiment of the present invention.

FIG. 25 is a diagram showing spectral luminance characteristics of A / B and missiles.

FIG. 26 is a block diagram showing an image target detection device according to a fourteenth embodiment of the present invention.

FIG. 27 is a block diagram showing a conventional image target detection device.

FIG. 28 is a diagram showing a far-infrared image signal and a binarized image.

FIG. 29 is a diagram showing a mid-infrared image signal and a binarized image.

FIG. 30 is a diagram showing an example of atmospheric transmittance in summer and winter.

FIG. 31 is a block diagram showing a conventional image target detection device.

[Explanation of symbols]

DESCRIPTION OF SYMBOLS 1 Infrared imaging part, 2 Luminance normalization part, 3 Target judgment part, 4 Spectral luminance data part, 5 Optical system, 6 Filter rotator, 7 Filter rotator control part, 8 Infrared detector, 9 Amplifier part, 10 Timing part ,
Reference Signs List 11 near-infrared band-pass filter, 12 mid-infrared band-pass filter, 13 far-infrared band-pass filter, 14 infrared reference value generation unit, 15 reference value determination unit, 16 threshold value calculation unit, 17 binarization unit, 18 feature amount calculation unit, 19 target direction determination unit,
20 target identification section, 21 target data section, 22 servo mechanism, 23 RAM, 24 rise time measurement section, 25 identification section, 26 maximum value maintenance time measurement section,
27 Time measurement unit from the maximum value to the steady value, 2
8 Ratio measurement unit, 29 Half width width measurement unit, 30 calculation unit, 31 general identification unit, 32 photodetector, 33
Scanning conversion means, 34 target detection means, 35 level comparison means, 36 judgment means

Claims (2)

[Claims] 1. A plurality of binarization units provided corresponding to infrared image signals in a plurality of different wavelength bands for performing binarization in the vicinity of a significant target position, and a target from outputs of the plurality of binarization units. Are provided in correspondence with a plurality of binarizing units for calculating characteristic amounts such as the area, vertical center of gravity, horizontal center of gravity, vertical length, horizontal length, and ratio of vertical length to horizontal length. An image target detection device, comprising: a plurality of feature value calculation units; and a target direction determination unit that determines a target traveling direction from outputs of the plurality of feature value calculation units. 2. Target data storing data such as a target area for each wavelength, a vertical center of gravity, a horizontal center of gravity, a vertical length, a horizontal length, a ratio of a vertical length to a horizontal length, and the like. Unit, a servo mechanism that outputs angle information and range information of the target with respect to the own device, and a target identification unit that performs target identification from outputs of the target direction determination unit, the servo mechanism, and the target data unit. The image target detection device according to claim 1, wherein