JPH0798218A - Menace identification device - Google Patents

Abstract

PURPOSE:To provide a menace identification device which identifies menace level of air targets and selects the air target of high menace level. CONSTITUTION:An infrared image detector 1 detects an air target and images an infrared image. A servo mechanism 2 scans and points the direction of axis of sight mechanically and electrically. A length measurement processor 3 measures the entire width, height and length of an aircraft of infrared image. An aspect menace identification processor 4, with the use of the length value measured by the length measurement processor 3, identifies the menace level of the air target based on the entire width, height or length.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a threat identification device.

[0002]

2. Description of the Related Art FIG. 27 is a diagram showing an example of the configuration of a conventional threat identification device. In the figure, 1 is an infrared image detector, 2 is a servo mechanism, and 67 is an image monitor.

The conventional image tracking device is constructed as described above, and the infrared image detector 1 detects an object and generates an infrared image. The servo mechanism 2 mechanically and electrically scans and directs the visual axis direction. The image monitor 67 displays the image obtained as described above.

[0004]

Among the objects generally targeted for aviation, military aircraft equipped with firearms for military / defense purposes are roughly classified into fighters, bombers, reconnaissance aircraft, and transport aircraft. It is hoped that the hostile side will identify military aircraft and effectively guard against high-threat aircraft.
For example, a military aircraft, which has the highest threat to aircraft, is a fighter aircraft, and when a fighter aircraft approaches, it is important to be able to immediately detect and identify its presence and be alert. 28,
29, 30, and 31 are examples of images displayed on the image monitor 67 of the threat identification device, which are 68, 69, and 7 in the figure.
0 and 71 are examples of images of fighters, bombers, reconnaissance planes, and transport planes, respectively. Since the above threat identification device does not have an automatic identification function of the threat level of the military aviation target, the threat level was visually identified based on the shape of the display image.

The present invention has been made in order to solve such a problem, and an object thereof is to realize a threat identification device for automatically identifying the threat level of an aviation target.

[0006]

In the threat identification device according to the present invention, the length measurement processor measures the overall width, total height, total length, etc. of the aviation target on the infrared image, and the aspect threat identification processor performs full width measurement. It is possible to identify the threat target of the aircraft by comparing the ratio between the height and the total height or the ratio between the total length and the total width with a predetermined threshold value.

Further, according to the present invention, the length measuring processor measures the total width, total height, total length, etc. of the aerial target on the infrared image, and the radar interface (I / F) device is used for the existing radar system and I / F. The speed vector of the aviation target to be imaged by F is obtained, and based on this, the aspect correction threat identification processor measures the length of the aviation target with an estimated angle measured by the length measurement processor. After rotation correction to the true length in the direction image or the top-bottom direction image, by comparing the ratio of the total width to the total height or the ratio of the total length to the total width with a predetermined threshold value, the aviation target It realizes the identification of the threat level of.

In the present invention, the radar I / F
The device acquires the velocity vector of the aviation target that is imaged by I / F with the existing radar system, and based on this, the database image orientation conversion processor captures the image of the aircraft shape parameters stored in the aircraft shape database. By rotating the image into the same direction as the target image, the image comparison threat identification processor compares and collates the image with the image captured by the machine to realize the threat level of the aviation target.

Further, according to the present invention, the engine recognition processor recognizes an engine which is a high-luminance body, the engine number threat identification processor counts the number of engines, and compares the value with a predetermined value to perform aviation. It realizes the identification of the target threat level.

Further, according to the present invention, the engine position recognition processor recognizes the engine part which is the brightest point, and the engine position threat identification processor performs binarized imaging and calculation of the center of gravity thereof, and the center of gravity for the entire width. By comparing the point-brightest point length with a predetermined value, it is possible to identify the threat level of the aviation target.

Further, in the present invention, the two-wavelength infrared image detector generates two types of images having different wavelength bodies, the image size measuring device measures the aviation target image size, and the distance arithmetic processing device measures the image size. The visual axis determined by the attitude information of the mother machine and the visual axis information of the servo mechanism, which estimates and calculates the distance of the imaged aviation target on the basis of the aircraft shape database and the atmospheric transmittance calculating means through the inertial device I / F device. Atmospheric transmittance is calculated using the zenith angle of the azimuth and the altitude information of the mother machine, and the output signal calculation processor uses predetermined spectral radiation characteristics and atmospheric transmittance that are assumed for an aircraft in two wavelength bands. The detector output signal strength is calculated, the detector output strength measuring device measures the detector output signal strength of the actual image, and the output comparison threat identification processor calculates the detector output signal strength and the actual image detector output. Comparing with signal strength One in which was realized the identity of the aviation of the goal threat level.

[0012]

The threat identification device constructed as described above can identify the threat level of an aviation target by comparing the ratio of the total width and the total height of the aviation target or the ratio of the total length and the total width.

Further, an I / F with an existing radar system is performed to obtain a velocity vector of an aviation target in the radar information, and based on this, a true width, a full height, a full length and the like with a prospective angle are rotationally corrected and obtained. The threat degree of the aviation target can be identified by comparing and processing the ratio of the full width to the total height or the ratio of the total length to the full width from the length of.

Further, the I / F with the existing radar system is performed to obtain the velocity vector of the imaged aviation target from the radar information, and based on this, the image of the aircraft configuration data stored in the aircraft configuration database is imaged. It is possible to identify the threat level of the aviation target by rotating and converting to the same expected direction and comparing and collating the image with the image captured by the aircraft.

The threat level of the aviation target can be identified by counting the number of engines and comparing the value with a predetermined value.

Further, by measuring the engine position and comparing the distance value from the center of gravity of the binary image to the engine part with respect to the entire width with a predetermined value, the threat level of the aviation target can be identified.

Further, it is estimated from a predetermined spectral radiation characteristic in a two-wavelength band assuming an aircraft and an atmospheric transmittance in a two-wavelength band at a distance determined by an image size when an imaging aircraft is assumed to be a threat. The threat level of the aviation target can be identified by comparing the detector output signal strength of the infrared image obtained from the actual image with the detector output signal strength of two types of infrared images having different wavelength bands.

[0018]

【Example】

Example 1. FIG. 1 is a diagram showing an embodiment of the present invention,
In the figure, 1 and 2 are the same as those in the above-mentioned conventional technique. Reference numeral 3 is a length measurement processor that measures various lengths of the aviation target on the infrared image. An aspect threat identification processor 4 identifies the degree of threat.

In the threat identification device configured as described above, the length measuring processor measures the total width, total height, total length and the like. The aspect threat identification processor 4 compares the ratio of the total width and the total height or the ratio of the total length and the entire width by using the full width and the length thereof, identifies the threat degree, and selects an aviation target having a high threat degree.
FIG. 2 is a diagram showing an outline of processing realized by the length measurement processor 3 and the aspect threat identification processor 4. First, the length measurement processor 3 performs the following processing. Generally, in an infrared image of an aviation target against the background of the sky, clouds, and sea, the background becomes clutter to increase the amount of noise components on the entire screen, and the ratio of the signal component of the aviation target to the background noise signal (S / N) Cause a decrease in the output, and the clutter itself becomes a false target. The clutter suppression processing 5 suppresses / removes the clutter of the sky, clouds, and sea surface images, and increases the S / N of aviation targets on the images. S /
The N calculation process 6 calculates S / N on the image. The signal binarization process 7 duplicates the infrared image detector signal image at a predetermined threshold value, while the length measurement process 8 measures the full width, the full height, the full length, and the like.

3 and 4 are diagrams showing an example of binarization and length measurement of an aerial target image. FIG. 3 is a binarized image of the direction in which the target is facing the front (head-on), where 10 is the total width and 11 is the total height. FIG. 4 shows a binarized side image, in which 11 is the same as the above and 12 is the total length. The aspect threat identification processor 4 performs the aspect comparison threat identification processing 9 using the length measured by the length measurement processing 8. The aspect comparison threat identification processing 9 identifies the threat level of the aviation target by comparing the ratio of the total width and the total height of the imaged aviation target or the ratio of the total length and the total width with a predetermined threshold value. Calculating (width / height) for various fighters and other non-fighters among aviation targets, generally (width / height) <3 for the former and (width / height) for the latter. ) ≧ 3, and when (total length / width) is calculated, generally (full width / height) ≧
1.2, for the latter (total length / width) <1.2. Paying attention to this, the aspect threat identification processing unit 4 identifies the degree of threat of the aviation target, and when the presence of the aviation target having a high degree of threat is detected, the aspect threat identification processor 4 can be warned with priority.

Example 2. Further, in the embodiment shown in FIG. 5, reference numerals 1 and 2 in the drawing are the same as those in the above-mentioned conventional technique.
The reference numeral 3 in the figure is the same as the technique of the first embodiment.
Reference numeral 13 denotes a radar I / F device that interfaces with an existing radar system to obtain radar information such as a velocity vector of an aviation target. Reference numeral 14 is an aspect-corrected threat identification processor that corrects the length with the expected angle and identifies the threat level.

In the threat identification device configured as described above, the radar I / F device 13 obtains radar information such as a velocity vector of an aviation target which is imaged by I / F with an existing radar system, and the aspect correction threat It is transmitted to the identification processor 14. The aspect correction threat identification processor 14 determines the total length, the total height, the total width, etc. of the aerial target image with the deviation angle (prospect angle) from the target front (head-on) direction based on the radar information in the head-on direction image or the upper limit surface direction. The image is subjected to rotation correction to the true length in the image, and this is subjected to comparison processing of the ratio of the entire width to the entire height or the ratio of the entire length to the entire width with a predetermined threshold value in the same manner as in the first embodiment, and the threat degree of the aviation target is calculated. Identify and select high threat aviation targets. FIG. 6 shows the aspect correction threat identification processor 14.
It is a figure which shows the processing outline implement | achieved by. 9 in the figure is the same as that of the first embodiment. The azimuth conversion processing 16 rotationally corrects the total length, the total width, the total height, etc., which have an expected angle, to the true length based on the velocity vector of the imaged aerial target. Radar information 15
Is information such as a velocity vector required for the azimuth conversion processing 16.

FIG. 7 is a diagram showing the definition of the coordinate system in the direction conversion processing 16. In the figure, 17 is an elevation axis, 18 is a boresight axis, 19 is an azimuth axis,
The x-axis, the y-axis, and the z-axis are respectively set. 20 is a position vector of length r, 21 is its azimuth angle α, and 22 is its elevation angle β. The known radar information 15 is data of the polar coordinate axis system, and the position vector 20 is represented by "Equation 1",
The velocity vector is "Equation 2", and the plane coordinates of the two end points whose origin is an arbitrary point on the imaged aerial target are expressed in the Cartesian coordinate system.
If the length of the rotation-corrected captured aerial target image is L, the L when rotation-corrected in the head-on direction processed by the azimuth conversion processing 12 is expressed by "Equation 4".

[0024]

[Equation 1]

[0025]

[Equation 2]

[0026]

[Equation 3]

[0027]

[Equation 4]

When L is corrected in the vertical direction, L is "
It is represented by the number 5 ".

[0029]

[Equation 5]

This makes it possible to identify the threat of the aviation target regardless of the expected angle.

Example 3. Further, in the embodiment shown in FIG. 8, reference numerals 1 and 2 in the figure are the same as those in the prior art. Further, 13 in the figure is the same as the technique shown in the second embodiment. An aircraft shape database 23 stores aircraft shape specification information. Reference numeral 24 is a database image orientation conversion processor for rotationally converting an image based on the shape information of the aircraft based on the velocity vector of radar information into an image of a deviation angle (expected angle) from the same target front (head-on) direction as the imaging target. is there. Reference numeral 25 is an image comparison threat identification processor that identifies the threat level by comparing and collating the converted image by the database image orientation conversion processor 24 with the captured image.

In the threat identification device configured as described above, the database image orientation conversion processor 24 uses the velocity vector of radar information and the aircraft images in the head-on direction and the vertical plane stored in the aircraft shape database 23.
From the dimensional information, the database image is rotationally converted into an image having the same prospect angle as the imaged aircraft. The image comparison threat identification processing 25 compares and collates this with the captured image to identify the threat level. FIG. 9 is a diagram showing an outline of processing realized by the database image orientation conversion processor 24. In the figure, reference numeral 15 indicates the second embodiment.
It is the same technology. Reference numeral 26 is aircraft shape specification information of a three-dimensional image stored in the aircraft shape database 23.

FIG. 10 shows an example of the aircraft shape specification information 26 of the three-dimensional image stored in the aircraft shape database 23. (a) is a head-on image,
(B) is a bottom image, (c) is a top image, and (d) is a side image. In the figure, 28 is the shape specification information of the head-on image,
Reference numeral 29 is shape information of the bottom image, 30 is shape information of the top image, and 31 is shape information of the side image. Reference numeral 27 in FIG. 9 is a database azimuth conversion process for rotationally converting the image of the aircraft shape specification information 26 into an image having the same projected angle as the imaged aviation target. In the definition of the coordinate system shown in FIG. 7,
The position vector 18 is "number 1", and its velocity vector 18
Is the numerical formula 2, the aircraft shape specification information 26 is the spatial coordinate with the arbitrary point on the image as the origin in the rectangular coordinate system, and the coordinate of the image after the rotation conversion is the numerical formula 7, the database The conversion formula processed by the direction conversion process 27 is represented by "Equation 8".

[0034]

[Equation 6]

[0035]

[Equation 7]

[0036]

[Equation 8]

FIG. 11 shows an image comparison threat identification processor 25.
It is a figure which shows the processing outline implement | achieved by. In the figure, 5, 6 and 7 are the same as those of the technique of the first embodiment. The shape comparison threat identification processing 32 identifies and compares the threat degree of the aviation target by comparing and collating the image 33 of the projected angle converted by the above equation and the captured image. FIG. 12 is a diagram showing an example of an image that has undergone rotation conversion processing into an image having the same projected angle as that of the imaging aircraft. Reference numeral 34 in the drawing is a contour image of the aircraft having a prospective angle. FIG. 13 is a diagram showing an example of a binarized captured image. Reference numeral 35 in the figure is a binarized captured image. Shape comparison threat identification processing 32
Compares 34 and 35, and recognizes the type of aviation target based on whether there is a difference between the assumed threat image and the non-threat image and identifies the threat level.

Example 4. Further, in the embodiment shown in FIG. 14, reference numerals 1 and 2 in the figure are the same as those in the above-mentioned conventional technique.
An engine recognition processor 36 recognizes the engine on the infrared image. Reference numeral 37 is an engine number threat identification processor that counts the recognized engines and identifies threats.

In the threat identification device constructed as described above, the engine recognition processor 36 recognizes the engine section which is the high brightness section on the infrared image. The engine number threat discrimination processor 37 counts the recognized engines and compares them with a predetermined value to identify the threat degree of the aviation target. FIG. 15 is a diagram showing an outline of processing realized by the engine recognition processor 36. In the figure, 5 and 6 are the same as the technique of the first embodiment. Reference numeral 38 is a high brightness recognition process for recognizing the engine part based on the brightness of each part. In general, the engine part is a high brightness part on the infrared image, and its brightness is several times or more that of other parts. Focusing on this, the high-luminance recognition processing 38 regards the luminance portion having a predetermined level or higher as the engine portion. Reference numeral 39 is an engine part storing process for storing all the recognized engine parts. 16 is a diagram showing an outline of processing realized by the engine number threat identification processing unit 37. In the figure, reference numeral 40 denotes an engine number counting process for counting the stored engine parts. Reference numeral 41 is engine number threat identification processing for identifying the degree of threat of an aviation target based on the number of engines. For example, the number of engines of an aircraft is generally 2 or less for fighters and 3 or more for non-fighters. 17 and 18 are examples of infrared images of aviation targets for explaining the recognition of the engine unit. FIG. 17 is an infrared image of a fighter, and FIG. 18 is an infrared image of a bomber. In the figure, 42 is an airframe, and 43 is an engine part. Since the engine part 43 has a higher temperature than the background and the body, the reception intensity is high. Therefore, 43 is a high brightness portion on the image. Focusing on this, the engine number threat identification processing 32 counts the number of engines and identifies the threat degree of the aviation target by this number.

Example 5. Further, in the embodiment shown in FIG. 19, reference numerals 1 and 2 in the figure are the same as those in the above-mentioned conventional technique.
An engine position recognition processor 44 recognizes the engine and measures the position. An engine position threat identification processor 45 identifies a threat based on the engine position.

In the threat identification device configured as described above, the engine position recognition processor 33 recognizes the brightest point on the infrared image in the engine section. The engine position threat identification processor 34 measures the distance between the centers of gravity of the binary images from the brightest point, and identifies the degree of threat of the aircraft based on the ratio of this to the overall width. FIG. 20 is a diagram showing an outline of processing realized by the engine position recognition processor 44. In the figure, 5 is the same as the technique of the first embodiment. Reference numeral 46 is a brightest point recognition process for recognizing the engine portion position which is the brightest point as the engine portion. Reference numeral 47 is a brightest point position threat identification process for storing the position of the brightest point recognized as the engine unit. For example, the brightest point on an infrared image of an aircraft is generally the engine section. Focusing on this, the brightest point recognition processing 46 regards the brightest point as an engine portion, and the brightest point position storage processing 47 stores this position. FIG. 21 is a diagram showing an outline of processing realized by the engine position threat identification processing unit 45. In the figure, 7 and 8 are the same as those of the technique of the first embodiment. Reference numeral 48 is a center-of-gravity point calculation process for calculating the center-of-gravity point of the binarized infrared image. Reference numeral 49 denotes engine position threat identification processing for identifying the threat level of the aviation target by comparing the length from the brightest point to the center of gravity determined by 48 and the full width of the aviation target determined by the length measurement processing 8. is there. 22 and 23 are examples of infrared images showing the brightest point and the center of gravity of the aviation target. FIG. 22 is an infrared image of a fighter, and FIG. 23 is an infrared image of a bomber. In the figure, 10 is the same as that of the above-described first embodiment. Further, 42 is the same as that of the fourth embodiment. Reference numeral 50 is the center of gravity of the binarized image, 51 is the brightest point of the engine, and 52 is the length between the brightest point 51 and the center of gravity 50. Generally, the ratio of the length from the center of gravity of the front of the aircraft to the engine section and the overall width is less than 0.2 for fighters,
Non-fighters, 0.2 and above are the mainstream. Focusing on this,
The engine position threat identification processing 49 identifies the threat level of the aviation target based on the ratio between the brightest point and the distance between the centers of gravity of the binarized image and the full width.

Example 6. Further, in the embodiment shown in FIG. 24, reference numeral 2 in the drawing is the same as the above-mentioned prior art. Reference numeral 23 in the figure is the same as the technique of the third embodiment. 5
Reference numeral 3 is a dual-wavelength infrared image detector that images an object in two different wavelength bands. Reference numeral 54 is an image size measuring device that measures the size of the image captured by 53. Reference numeral 55 is a distance calculation processor that estimates and calculates the distance to the object. Reference numeral 56 denotes an inertial device I / F device that interfaces (I / F) with the inertial device of the mother machine. Reference numeral 57 is an atmospheric transmittance calculating means typified by Rotoran or the like. Reference numeral 58 is an output signal calculation processor for estimating and calculating the output signal intensity of the infrared image detector in two types of wavelength bands. Reference numeral 59 is a detector output intensity measuring device for measuring the output signal of the actual dual wavelength infrared image detector. Reference numeral 60 is an output comparison threat identification processor that identifies the degree of threat by comparing the estimated value of the output signal intensity of the infrared image detector in the two wavelength bands obtained by 58 and 59 with the actual value. .

In the threat identification device configured as described above, the two-wavelength infrared image detector 53 has two different wavelength bands.
Generate seed images. The image size measuring device 54 measures the edge length on the image of one wavelength band generated by 53 by the number of edge pixels or the like, and sets this as the length. The distance calculation processor 55 calculates the distance from the size measured by 54 on the assumption that the imaged aviation target is an aircraft previously stored in the aircraft shape database 23 and the object. The inertial device I / F device 56 I / Fs the inertial device of the mother machine to obtain attitude information of the mother machine. The atmospheric transmittance calculating means 57 is based on the distance calculated by the distance calculation processor 55, the zenith angle of the visual axis direction determined by the attitude of the mother machine and the visual axis direction information directed by the servo mechanism 2, and the altitude information of the mother machine. The atmospheric transmittance in two different wavelength bands is calculated. The output signal processor 58 has a radiant emittance in two wavelength bands,
The detector output signal strength is estimated and calculated by assuming that the spectral transmittance and the detector sensitivity are predetermined.

The output comparison threat discrimination processor 60 discriminates the threat level of the aviation target by comparing the two types of detector output signal intensities measured by 59 and having different actual wavelength bands with the detector output signal intensities calculated by 58. To do. For example, if the difference between the actual detector output signal and the calculated detector output signal is within a predetermined value, this is considered as a threat, and if not, it is considered as a non-threat.

FIG. 25 is a diagram showing an outline of processing realized by the distance calculation processor 55. FIG. 26 is the same as the technique of the third embodiment. Reference numeral 61 is an image size measuring process for converting the image size of the pixel number display measured by the image size measuring device 54 into an occupied angle. 62 is aircraft shape specification information 26
And an estimated distance calculation process for calculating a distance based on the above-mentioned occupied angle. FIG. 26 is a diagram showing the relationship between the occupation angle of the aviation target and the distance. In the figure, 63 is an aviation target, 64 is an aircraft size T in the aircraft shape specification information 26, 65 is an occupancy angle θ, and 66 is a distance R. At this time, the estimated distance calculation process 6
The operation of 2 is represented by "Equation 9".

[0046]

[Equation 9]

In addition, the atmospheric transmittance at the wavelength λ obtained by the atmospheric transmittance calculating means 57 represented by Lotran is
Numeral 10 ", the predetermined spectral emissivity of the aircraft at wavelength λ is" Numerical equation 11 ", and radiant emittance at wavelength λ is" Numerical equation 1 "
2 ", the detector sensitivity at the wavelength λ is" Equation 13 ", the instantaneous viewing angle is φ, and the wavelength band is λ1 to λ2, the detector output signal intensity E calculated by the output signal arithmetic processor 58 is" Equation 1 ".
4 ".

[0048]

[Equation 10]

[0049]

[Equation 11]

[0050]

[Equation 12]

[0051]

[Equation 13]

[0052]

[Equation 14]

[0053]

Since the present invention is configured as described above, there is an effect that it is possible to realize a threat identification device capable of effectively identifying the threat level of an aviation target.

[Brief description of drawings]

FIG. 1 is a configuration diagram showing a first embodiment of the present invention.

FIG. 2 is a diagram showing a processing outline of a length measurement processor and an aspect threat identification processor according to the present invention.

FIG. 3 is a diagram showing a binarized head-on image of an infrared image of an aviation target.

FIG. 4 is a view showing a binarized side image of an infrared image of an aviation target.

FIG. 5 is a configuration diagram showing a second embodiment of the present invention.

FIG. 6 is a diagram showing a processing outline of an aspect-corrected threat identification processor of the present invention.

FIG. 7 is a diagram showing the definition of a coordinate system.

FIG. 8 is a configuration diagram showing a third embodiment of the present invention.

FIG. 9 is a diagram showing a processing outline of a database image orientation conversion processor of the present invention.

FIG. 10 is a diagram showing an example of aircraft shape specification information.

FIG. 11 is a diagram showing a processing outline of the image comparison threat identification processor of the present invention.

FIG. 12 is a diagram showing an example of a rotation-converted image.

FIG. 13 is a diagram showing an example of a binarized aviation target image.

FIG. 14 is a configuration diagram showing a fourth embodiment of the present invention.

FIG. 15 is a diagram showing a processing outline of an engine recognition processor of the present invention.

FIG. 16 is a diagram showing a processing outline of the engine number threat identification processor of the present invention.

FIG. 17 is a diagram illustrating an example of an infrared image of an aviation target for explaining recognition of an engine unit of a fighter.

FIG. 18 is a diagram showing an example of an infrared image of an aviation target for explaining the recognition of the engine part of the bomber.

FIG. 19 is a configuration diagram showing a fifth embodiment of the present invention.

FIG. 20 is a diagram showing a processing outline of an engine position recognition processor according to the present invention.

FIG. 21 is a diagram showing a processing outline of an engine position threat identification processor according to the present invention.

FIG. 22 is a diagram showing an example of an infrared image of a fighter in which the brightest point and the center of gravity of the binarized image are marked.

FIG. 23 is a diagram showing an example of an infrared image of a bomber in which a brightest point and a center of gravity of a binarized image are described.

FIG. 24 is a configuration diagram showing a sixth embodiment of the present invention.

FIG. 25 is a diagram showing a processing outline of the distance arithmetic processing unit of the present invention.

FIG. 26 is a diagram showing a relationship between an occupation angle of an aviation target and a distance.

FIG. 27 is a configuration diagram showing a conventional example.

FIG. 28 is a diagram showing an example of an infrared image of a fighter.

FIG. 29 is a diagram showing an example of an infrared image of a bomber.

FIG. 30 is a diagram showing an example of an infrared image of a reconnaissance aircraft.

FIG. 31 is a diagram showing an example of an infrared image of a transportation machine.

[Explanation of symbols]

 1 infrared image detector 2 servo mechanism 3 length measurement processor 4 aspect threat identification processor 5 clutter suppression processing 6 S / N arithmetic processing 7 signal binarization processing 8 length measurement processing 9 aspect comparison threat identification processing 10 full width 11 Overall height 12 Full length 13 Radar I / F device 14 Aspect correction threat identification processor 15 Radar information 16 Direction conversion processing 17 Elevation axis 18 Boresite axis 19 Azimuth axis 20 Position vector 21 Azimuth angle 22 Elevation angle 23 Aircraft shape database 24 Database image conversion processor 25 Image comparison threat identification processor 26 Aircraft shape information 27 Database orientation conversion processing 28 Head-on image 29 Lower surface image 30 Upper surface image 31 Side image 32 Shape comparison threat identification processing 33 Prospective orientation image 34 Oriented image 35 Captured image 36 Engine recognition processor 37 Engine number threat identification processor 38 High brightness recognition processing 39 Engine part storage process 40 Engine number counting process 41 Engine number threat identification process 42 Aircraft body 43 Engine part 44 Engine position recognition processor 45 Engine position threat identification processor 46 Brightest point recognition processing 47 Brightest point position storage processing 48 Centroid calculation processing 49 Engine location threat identification processing 50 Binary image centroid 51 Brightest point 52 Brightest point Centroid distance 53 dual-wavelength infrared image detector 54 image size measuring device 55 distance calculation processing device 56 inertial device I / F device 57 atmospheric transmittance calculating means 58 output signal calculation processing device 59 detector output intensity measuring device 60 output comparison threat identification processing Vessel 61 image size measurement processing 62 estimated distance calculation processing 63 aviation target 64 aircraft size 65 Image example of the chromatic angle 66 range 67 images of the image monitor 68 fighter image Example 69 bomber image Example 70 reconnaissance aircraft of 71 transport plane

─────────────────────────────────────────────────── ─── Continuation of the front page (51) Int.Cl. ⁶ Identification code Internal reference number FI technical display location G06T 1/00 // F41G 7/22

Claims (6)

[Claims] 1. An infrared image detector for imaging an object, a servo mechanism for mechanically or electrically scanning and directing the visual axis direction of the infrared image detector, and the infrared image detector. The length measurement processor that measures the total width, total height, total length, etc. of the aviation target on the infrared image and the output of this length measurement processor are input, and the ratio of the total width to the total height or the ratio of the total length to the total width is input. A threat identification device characterized by having an aspect threat identification processor for identifying the threat level of an object based on the above. 2. An infrared image detector for picking up an image of an object, a servo mechanism for mechanically or electrically scanning and directing the visual axis direction of the infrared image detector, and the infrared image detector. The length measurement processor that measures the total width, total height, and total length of the aviation target on the infrared image that has the deviation angle (projection angle) from the target frontal state (head-on) direction, and the position of the object to be imaged Radar I / F that interfaces (I / F) with a radar system to quote vector and velocity vector information
The device, the full width with the above-mentioned angle, the total height, the aspect correction processor for obtaining the true length based on the velocity vector information from the length such as the total length, and input the output of the length measurement processor,
A threat identification device, comprising: an aspect threat identification processor for identifying the threat level of an object based on the ratio of the true full width to the full height and the ratio of the true full length to the full width. 3. An infrared image detector for picking up an image of an object, a servo mechanism for mechanically or electrically scanning and directing the visual axis direction of the infrared image detector, and shape data of the aircraft are stored in advance. Radar I / F that interfaces (I / F) with the radar system to cite the aircraft shape database and the position vector and velocity vector of the imaged object.
F device and a database for rotationally converting an image of aircraft shape data of database information into an image of a deviation angle (expected angle) from the same target front (head-on) direction as the imaging target based on the velocity vector information of the radar system. An image orientation conversion processor, and an image comparison threat identification processor that identifies the threat level of the object by comparing and collating the image after conversion by the database image orientation conversion processor with the captured image. Threat identification device. 4. An infrared image detector for imaging an object, a servo mechanism for mechanically or electrically scanning and directing the visual axis direction of the infrared image detector, and the infrared image detector. An engine recognition processor that recognizes the engine part that becomes a high-brightness part from the acquired infrared image, and the number of engines recognized by this engine recognition processor is counted, and the threat level of the object is identified based on the number of engines. A threat identification device having a number of engines threat identification processor. 5. An infrared image detector for picking up an image of an object, a servo mechanism for mechanically or electrically scanning and directing the visual axis direction of the infrared image detector, and the infrared image detector. An engine position recognition processor for recognizing the position of the engine part, which is the brightest point from the infrared image obtained, and calculating the center of gravity of the infrared image of the engine part, and based on the engine position relative to the position of the center of gravity of the object A threat identification device comprising: an engine position threat identification processor that identifies a threat level. 6. A dual-wavelength infrared image detector for imaging an object in two wavelength bands, a servo mechanism for mechanically or electrically scanning and directing the visual axis direction of the detector, and a detector. An image size measuring device for measuring an image size, an aircraft shape database for preliminarily storing the shape data of an aircraft, a distance calculating device for estimating and calculating a distance to an object, an inertial device of a mother machine, and an interface (I / F) inertial device I / F device, atmospheric transmittance calculation processing means for calculating atmospheric transmittance in the above two wavelength bands, and two types of wavelength bands assuming that the spectral radiation characteristics of the aircraft are predetermined. Output signal calculation processor to estimate the infrared image detector output signal strength at, the detector output intensity measurer to measure the actual infrared image detector output signal strength, and the above estimated output signal strength and actual Of infrared image detector output signal intensity A threat identification device characterized by having a degree output comparison threat identification processor for identifying a threat of an object by comparison.