JP2000123271A - Flying object warning system - Google Patents

Abstract

PROBLEM TO BE SOLVED: To make exactly detectable an air-to-air(A/A) flying object flying from a distant place and a ground-to-air(G/A) flying object shot from the ground by defining an absolutely horizontal area or area above its own machine as the cover area of an infrared sensor and defining an area in the shape of a cone with the perpendicularly downside or downside of the own machine as the center as the cover area of a ultraviolet sensor. SOLUTION: This system has both the infrared sensor for detecting the image of a flying object and the ultraviolet sensor for detecting the burning fire of a flying object as optical wave sensors. Then, the upper area including a direction absolutely horizontal or horizontal to the own machine is defined as the cover area of the infrared sensor and the cone-shaped area with the perpendicular downside or the downside of the present machine as the center is defined as the cover area of the ultraviolet sensor. Concerning this system, an infrared sensor cover area 29 of all the periphery upward of 45 deg. and downward of 15 deg. the own machine, for example, is covered by one scanning type infrared sensor. Besides, a ultraviolet sensor cover area 30 of cone of downward of 150 deg. the own machine is covered by four ultraviolet sensors.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a flying object alerting device which detects the presence of a flying object such as a guided flying object which is mounted on an aircraft and flies close to the own aircraft and outputs a warning to the own aircraft. It is.

[0002]

2. Description of the Related Art First, a conventional flying object warning device will be described. FIG. 6 is a configuration diagram showing an example of a conventional flying object alerting device. In FIG. 6, 1 is an ultraviolet sensor, 2 is an ultraviolet optical system, 3 is a short-pass filter, 4 is an image intensifier, 5 is a photoelectric surface, 7 is a video amplifier, 8
Is a signal processor, and 9 is a display device.

[0003] The conventional flying object alerting device shown in FIG. 6 is configured as described above, and operates as follows. When a flying object such as a ground-to-air guided flying object is fired toward an aircraft equipped with this device, the initial acceleration, or the thrust during flight, or both from the combustion flame of the propellant that gives thrust during flight, or both. Ultraviolet radiation is emitted. When the ultraviolet light reaches the ultraviolet sensor 1, the ultraviolet light is condensed and imaged on the photoelectric surface of the image intensifier 4 by the ultraviolet optical system 2 and the short-pass filter 3 installed in the optical path. The short-pass filter 3 blocks light in an unnecessary wavelength band so that only light in a specific wavelength band of the ultraviolet light incident on the optical system reaches the photocathode 5 of the image intensifier 4. The light input impinging on the photocathode 5 is once converted to photoelectrons, amplified by the image intensifier 4 to about tens of thousands times, hits the phosphor screen provided at the rear end of the image intensifier, and becomes light output again. Output as an image. The output light of the image intensifier 4 is input to a two-dimensional CCD and output as an electric signal. The output video signal is amplified by a video amplifier 7 and sent to a signal processor 8. The signal processor 8 extracts a detection signal candidate exceeding the threshold from the CCD output image signal, and refers to data provided in the signal processor in advance such as, for example, a change in signal intensity with time. Determine whether or not. Also, from the change in direction information of the target, the signal strength, the speed of the own aircraft, etc., it is determined whether or not the flying object is approaching the own aircraft, as a detection signal, missile threat alert, threat azimuth information, In the case of a guided flying object fired from the ground, the approximate distance is calculated from the altitude of the own aircraft, and an alarm display is output to a display device 9 in the aircraft such as a head-up display. In the UV sensor, the so-called solar-blind wavelength band, which is absorbed by the ozone layer and hardly reaches the sun on the ground, is selected as the wavelength band for detection, so that almost no noise light is emitted from the background. There is a feature that detection with a low false alarm rate can be performed.

FIG. 7 is a diagram showing an example of a covered area of the conventional device. Four ultraviolet sensors 1 are provided, each of which has a 90-degree covered area, and covers the entire 360-degree covered area around the mounted mother machine to detect the presence of an approaching flying object. 7A is a side view, and FIG. 7B is a bottom view. The same numbers indicate the same parts. 10 is an ultraviolet sensor 1, 11 is an ultraviolet sensor 2, 12 is an ultraviolet sensor 3, 13 is an ultraviolet sensor 4, 14 is a coverage area of the ultraviolet sensor 1, 15 is a coverage area of the ultraviolet sensor 2, and 16 is a coverage area of the ultraviolet sensor 3. , 17 are coverage areas of the ultraviolet sensor 4. The ultraviolet sensor 1, the ultraviolet sensor 2, the ultraviolet sensor 3, and the ultraviolet sensor 4 cover about 90 degrees of the front right side, the rear right side, the rear left side, and the front left side with respect to the mounted mother machine, respectively. FIG. 7 (a)
In FIG. 7, the portion hatched with a horizontal broken line indicates the ultraviolet sensor 1.
Is shown.

FIG. 8 is a block diagram showing another example of the conventional flying object alerting device. In the figure, 7 to 9 indicate the same parts as in FIG. The infrared sensor 18 includes an infrared window 19, a visual axis rotation mechanism 20, a rotation correction prism 21, an infrared optical system 22,
It comprises an infrared detector 23 and a visual axis directing mirror 24.

The conventional flying object alerting device shown in FIG. 8 is configured as described above, and operates as follows. That is, the infrared incident light from the outside passes through the infrared window 19, is guided to the visual axis directing mirror 24, passes through the infrared optical system 22, and is condensed and imaged on the infrared detector 23. In the present apparatus, when the visual axis rotating mechanism 20 rotates, the infrared window 19 and the visual axis directing mirror 24 mounted on the rotating part of the visual axis rotating mechanism 20 are directed in the direction to be directed, and the image information in that direction is transmitted to the infrared ray. It can be obtained on the detector 23. At this time, the image formed on the infrared detector 23 also rotates due to the rotational movement for directing, but the rotation correction prism 21 corrects the image on the infrared detector surface in the rotation direction so as not to rotate. The video signal output as an electric signal is amplified by a video amplifier 7 and sent to a signal processor 8. The signal processor 8 performs the following processing in the same manner as the above-described ultraviolet sensor. A detection signal candidate exceeding a threshold is extracted from the output signal, and it is determined whether the object is a guided flying object by referring to data provided in the signal processor in advance, such as a change in signal intensity with time, for example. Also, from the change in direction information of the target, the signal strength, the speed of the own aircraft, etc., it is determined whether or not the flying object is approaching the own aircraft, as a detection signal, missile threat alert, threat azimuth information, In the case of a guided flying object fired from the ground, the approximate distance is calculated from the altitude of the own aircraft, and an alarm display is output to a display device 9 in the aircraft such as a head-up display. In the case of an infrared sensor, for example, when a flying object such as an air-to-air guidance flying object having a relatively long flight distance is fired at its own device, it is excellent in its ability to detect this.

FIG. 9 is a diagram showing an example of the area covered by the conventional device. (A) is a top view and (b) is a side view. Equipped with two infrared sensors, each sensor has a 180-degree coverage,
The entire area covers 360 degrees around the mounted mother machine. In the figure, reference numeral 25 denotes an infrared sensor 1, 26 denotes an infrared sensor 2, 27 denotes a covered area of the infrared sensor 1, and 28 denotes a covered area of the infrared sensor 2.

[0008]

However, the above-mentioned conventional flying object guiding apparatus has the following problems. The first problem is that a flying object such as a ground-to-air guided flying object poses a threat to the own aircraft when the flying altitude of the own aircraft is lower than the range of the guided flying object. If such a guided flying object is fired at the own aircraft, if the own aircraft is within the range of the guided flying object from the launch of the guided flying object to the hit, the flight of the own aircraft The altitude is considered to be sufficiently lower than the range of the guided flying object. Therefore, in a flying object warning device using an ultraviolet sensor, such a ground-to-air guided flying object is often fired within the detection limit distance of the ultraviolet sensor,
Often detectable. However, flying objects such as air-to-air guided flying objects are often fired from outside the detection limit of the UV sensor, and the propellant combustion flame that gives a remarkable initial acceleration of the radiation intensity is only emitted for a specific period after firing. Since the projectile is radiated, the projectile launched from a sufficiently far distance has a problem in that the emission of the combustion flame of the propellant, which provides initial acceleration when approaching within the detection limit distance of the ultraviolet sensor, has already been completed and the detection becomes difficult.

When an infrared sensor is used to avoid such a problem, the detection distance of a flying object such as an air-to-air guided flying object can be lengthened to some extent. Since the flying object comes from almost the horizontal direction, the background is also empty, and it is uniform and has less clutter than the ground background, so that the false alarm rate can be reduced. However, even in this case, the flying object launched from the ground, such as a ground-to-air guided flying object, has a background that is a landscape on the ground, so there are many clutters and the false alarm rate is higher than that of an ultraviolet sensor. there were.

A second problem is that, when the covered area to be covered by the ultraviolet sensor is covered by one sensor, the difficulty in realizing the ultraviolet optical system increases in design as the covered area becomes wider. For example, since the number of lenses included in the optical system increases, the transmittance decreases, and as a result, adverse effects such as a decrease in the detection distance occur. Further, as the angle of view of the optical system increases, the distortion increases, so that a large angle error occurs in the detected target direction.

A third problem is that, when one infrared sensor having a visual axis rotation mechanism is installed and the entire circumference of the own device is to be covered, regardless of the position on the mounted body, There is a problem that a part of the covered area is blocked by the fuselage, the main wing, the tail wing, or the like of the fuselage, so that the area that can be alerted is considerably limited.

A fourth problem is that when the ultraviolet sensor is installed above or below its own aircraft with its field of view set, when the aircraft is performing a simple horizontal flight, the installed sensor is always upward. Alternatively, it is possible to place the lower part in the covered area and make a warning for the purpose. However, when the own aircraft performs a motion such as turning, the attitude of the aircraft changes, and the field of view of the preset sensor cannot fit within the upper or lower area required for the purpose of caution. There was a problem. This problem is particularly remarkable in aircraft with high athletic ability, such as fighters, and the aircraft may face any direction up and down.Therefore, all directions around the aircraft must be covered by the UV sensor coverage area. There was a problem. Originally, in order to avoid such a problem and warn the desired predetermined upper or lower range even if the attitude of the aircraft changes, it is necessary to widen the field of view for each sensor. But,
This means that in order to view a wide range with a predetermined number of pixels, the angle range assigned to one pixel is widened, and as a result, the angular resolution as a sensor must be set roughly. Roughening the angular resolution is further
When detecting a target smaller than a pixel, the S / N is reduced. That is, there is a problem that the radiation level from the target becomes relatively lower than the noise level, so that the detection distance becomes shorter.

SUMMARY OF THE INVENTION The present invention has been made to solve the above problems, and provides a flying object alerting device for accurately detecting an air-to-air flying object flying from a distance and a ground-to-air flying object launched from the ground. The purpose is to:

[0014]

A flying object alerting device according to a first aspect of the present invention is mounted on an aircraft, and detects an image of a flying object approaching its own device and ejecting a combustion flame, and a light wave sensor for the light wave sensor. In a flying object alerting device having a signal processor that receives an output, detects the presence of the flying object, and outputs a warning signal to the own aircraft, an infrared sensor that detects an image of the flying object as the light wave sensor and the flying object It has both an ultraviolet sensor for detecting the combustion flame of the above, the upper area including the absolute horizontal or the horizontal direction to the own machine as the area covered by the infrared sensor, the center vertically below or below the own machine The area of the conical shape is used as a covering area of the ultraviolet sensor.

A flying object alerting device according to a second aspect of the present invention comprises:
In the invention, at least four UV sensors are provided below the fuselage so as to cover the area covered by the UV sensor.
It has one or more gaze type ultraviolet sensors.

According to a third aspect of the present invention, there is provided a flying object alerting device.
In the invention of the above, at least two upper parts of the body are covered as the infrared sensor so as to cover the area covered by the infrared sensor.
One or more scanning infrared sensors that move the visual axis are provided.

According to a fourth aspect of the invention, there is provided a flying object alerting device.
In the invention of the present application, at least four infrared sensors are provided above the fuselage so as to cover the area covered by the infrared sensor.
One or more gaze-type infrared sensors are arranged.

According to a fifth aspect of the present invention, there is provided a flying object alerting device comprising:
In the invention, a visual axis movable mechanism that freely rotates around two orthogonal axes, a gyro mounted inside the visual axis movable mechanism, and a stabilizing visual axis using an output of the gyro The visual axis stabilizing device includes a signal processor that outputs a drive signal to the visual axis movable mechanism, and the ultraviolet sensor is mounted inside the visual axis movable mechanism of the visual axis stabilizing device.

[0019]

DESCRIPTION OF THE PREFERRED EMBODIMENTS Embodiment 1 Hereinafter, a flying object alerting device according to a first embodiment of the present invention will be described with reference to FIG. In the first embodiment, four ultraviolet sensors and two infrared sensors are provided. In the figure, reference numeral 29 denotes an infrared sensor cover area, which is hatched by an oblique broken line. One scanning-type infrared sensor covers the entire area covered by 45 degrees above and 15 degrees below the aircraft. 30 is an ultraviolet sensor covering area,
Four UV sensors cover the area covered by the lower 150 ° cone. The angle of 150 degrees is to be set as a sufficient angle mainly for guarding a guided flying object or the like launched from the ground. In Embodiment 1, the angle is set to 150 degrees as an example. The angle is determined in consideration of the range, flight pattern, flight altitude, flight speed, and the like of the target guided flying object. In the figure, a portion 30b hatched by a vertical broken line indicates an area of the 150-degree cone where the right front sensor is projected on the screen of the square detector on a spherical surface centered on the fuselage. The infrared sensor cover area 29 and the ultraviolet sensor cover area 30 can be overlapped, for example, by increasing the cover area of the ultraviolet sensor to a region of 180 degrees below. Conversely, the area covered by the infrared sensor may be, for example, a range of 30 degrees upward and 30 degrees downward. In this way, the area covered by the infrared sensor and ultraviolet sensor is mainly the infrared sensor on the horizontal and upper sides, and the ultraviolet sensor on the lower side, the type of the mounted aircraft, the assumed threat target, and the system concept of the flying object warning device Thus, the area covered by the boundary can be set freely.

Further, the ultraviolet sensor of this embodiment
It has the same configuration as the example of the conventional device shown in FIG. 6, and each component has the same function. Further, the infrared sensor of this embodiment has the same configuration as the example of the conventional device shown in FIG. 8, and each component has the same function.

The flying object alerting device of this embodiment is configured as described above and operates as follows. That is, the radiation of infrared rays or ultraviolet rays from the outside is sent to the signal processor 8 as a video signal as in the conventional apparatus.
The signal processor 8 extracts a detection signal candidate, determines whether or not the flying object is approaching the own aircraft, and outputs various detection signals to a display device 9 in the body such as a head-up display to output an alarm display. I do. When a flying object such as an air-to-air guided flying object with a relatively long flight distance is fired at the aircraft, and approaches the aircraft from the area covered by the infrared sensor above and horizontally, it is detected by the infrared sensor. Detects and outputs a warning signal to its own device.

On the other hand, when a flying object such as a ground-to-air guided flying object is fired from the ground toward its own aircraft,
The ultraviolet sensor detects the combustion flame of the propellant injected by the guided flying object, thereby detecting the presence of the flying object approaching the own aircraft and outputting a warning signal to the own aircraft.

Embodiment 2 FIG. FIG. 2 is a diagram showing Embodiment 2 of the flying object alerting device according to the present invention. Hereinafter, a flying object alerting device according to a second embodiment of the present invention will be described with reference to FIG. In FIG. 2, reference numerals 6 to 8, 22, and 23 denote portions having the same functions as the same numbered portions shown in FIG. The staring infrared sensor 31 includes an infrared optical system 22, an infrared detector 23, a bandpass filter 32, a video amplifier 7, a signal processor 8, and a display device 9.

The flying object alerting device of this embodiment is configured as described above and operates as follows. That is, when a flying object such as an air-to-air guided flying object is fired toward the own aircraft, the infrared radiation emitted from the combustion flame of the propellant, which provides initial acceleration and / or thrust during flight, or both, is infrared optical The light is focused and imaged on the infrared detector 23 by the system 22 and the band-pass filter 32 provided in the optical path. The bandpass filter 32 blocks light in unnecessary bands so that only light in a specific band required for detection among infrared lights incident on the infrared optical system 22 reaches the infrared detector surface. The light strikes the detector surface and is output as an electric signal. The signal is amplified by the video amplifier 7 and sent to the signal processor 8. The signal processor 8 extracts a detection signal candidate, determines whether or not the flying object is approaching the own aircraft, and outputs various detection signals to a display device 9 in the body such as a head-up display to output an alarm display. I do.

The area covered by the flying object alerting device of this embodiment is almost the same as that of the first embodiment. FIG. 3 is a view showing the area covered by the flying object alerting device of this embodiment. 9,2
Reference numerals 9 and 30 denote the same parts as in FIG. 4 infrared sensors
Each sensor is clockwise 45 degrees forward, 45 degrees back right, 45 degrees back left, 4 left
It has a field of view with a vertical and horizontal angle of view of about 90 degrees, centered 5 degrees forward. Each sensor is oriented approximately 15 degrees above the horizontal in the elevation direction. In the figure, the hatched inner portion 29b shows an area where the sensor 45 degrees forward on the right side is projected on the screen of the square detector on a spherical surface around the fuselage. When one sensor is intended to cover a specific area above and below the horizontal direction with reference to the horizontal direction, for example, the main wing and the tail wing are shielded to narrow the field of view. Based on the idea of installing a plurality of gaze-type infrared sensors as in the example, it is possible to select a position where the field of view is not obstructed on the main wing, the tail wing, or the like, and install each sensor. It is also possible to install the same number of the infrared sensors as the number of the ultraviolet sensors and share the visual fields corresponding to the upper and lower directions in the same turning direction.

Embodiment 3 FIG. FIG. 4 is a diagram showing Embodiment 3 of the flying object alerting device according to the present invention. Hereinafter, a flying object alerting device according to a third embodiment of the present invention will be described with reference to FIG. In FIG. 4, reference numeral 1 denotes an ultraviolet sensor having the same function as that of the same numbered portion shown in FIG.
Is a rotation axis, 35 is a visual axis movable mechanism, 36 is a gyro, 37
Is a control system signal processor, and 38 is a visual axis stabilizing device including all of them.

The flying object alerting device of this embodiment is configured as described above, and the operation of the ultraviolet sensor 1 is the same as that of the prior art. The elevation axis 33 and the rotation axis 34 are perpendicular to each other, and the visual axis movable mechanism 35 freely rotates around these two axes. The gyro 36 is mounted inside the visual axis movable mechanism 35, detects the angle of the ultraviolet sensor 1 with respect to the inertial system, and outputs the detection result to the control system signal processor 37. The control system signal processor 37 calculates an angle error using the output of the gyro 36, amplifies the angle error signal, and outputs a drive signal of the visual axis movable mechanism 35. As a result of these actions, the visual axis stabilizing device 38 achieves visual axis stabilization, and continues to look in a certain direction even when the aircraft flies at various angles.

The area covered by the flying object alerting device of this embodiment is almost the same as that of the first embodiment. FIG. 5 is a diagram showing an example of mounting the flying object alerting device of this embodiment. (A) is a diagram of the body viewed from obliquely below, and (b) and (c) are diagrams of the body viewed from the front. Ultraviolet sensors mounted on each visual axis stabilizing device cover four regions of the body divided into four directions based on the body. 5 (b) and 5
(C) shows the area covered by the ultraviolet sensor.
In (b), the body is flying horizontally, and the ultraviolet sensor covers the lower part of the body by pointing to the reference position. Even when the airframe is inclined during flight as shown in FIG. 5 (c), it continues to point in a certain direction by the function of the visual axis stabilizing device 38, and consequently keeps on watching a predetermined lower range. it can. Note that the same configuration can be applied to an infrared sensor.

[0029]

Since the present invention is configured as described above, it has the following effects.

According to the first aspect of the invention, when a flying object such as a ground-to-air guidance flying object is fired toward itself, the direction of the flying object is usually within the coverage area of the ultraviolet sensor and within the detection limit distance. Can be detected with a low false alarm rate. on the other hand,
For example, when a flying object such as an air-to-air guidance flying object is launched, the flying object comes from almost the horizontal direction, so it is inside the coverage area of the infrared sensor, and a longer detection distance can be obtained as compared with the ultraviolet sensor. . In this way, by utilizing the characteristics of each sensor and dividing the area covered by the sensor, the flying object can be detected more correctly and earlier, and the time required for coping with it can be increased.

According to the second aspect of the present invention, by providing a plurality of ultraviolet sensors, a wide covering area can be covered as a whole of the ultraviolet sensor, and the design of the ultraviolet optical system is relatively easy and the number of lenses can be reduced. It is possible to avoid adverse effects such as a decrease in the transmittance and a detection distance due to the increase. Further, since a visual axis rotation mechanism is not required, a small sensor can be realized, and a large number of sensors can be easily installed on the mounting base machine. For this reason, it is easy to widen the area covered by the ultraviolet sensor.

Further, according to the third aspect of the present invention, by providing a plurality of scanning infrared sensors, even if one sensor, for example, blocks the main wing or the tail wing and narrows the field of view, the main wing or the tail wing can be used. Each sensor can be installed at a position where the field of view is not obstructed. as a result,
The area covered by the infrared sensor can be widened. In addition, by providing a plurality of scanning sensors, the search range is only about 180 degrees, which is half of the search range in the case of two sensors, compared to the case of searching 360 degrees with one sensor.
When the search is performed at the same search speed, the search period of the two sensors can be conceptually shortened to about half of that of the one sensor. Usually, a target is detected in each search cycle, and an identification process for recognizing that the target is the same as the target detected in the previous search cycle is performed. However, a search from one search to the next search is performed. The shorter the time, the smaller the target moving distance and the smaller the change in the attitude of the aircraft itself.This makes identification processing easy and can be compared with a target moving at high speed or when the attitude of the aircraft itself changes rapidly. The target can be easily and continuously captured. In addition, since the search cycle is fast, after the target is first detected, the movement information of the target can be grasped at a relatively early stage, so that there is an advantage that a time margin for determining a more appropriate coping method can be extended. .

According to the fourth aspect of the present invention, a plurality of fixation type infrared sensors are mounted, and similarly to the third aspect of the present invention, a position where the field of view is not obstructed by the main wing or the tail wing is selected and each sensor is installed. And the area covered by the infrared sensor can be widened. Further, the gaze type sensor does not perform the mechanical scanning as performed by the scanning type sensor, and the search time depends on the frame rate of reading out of the infrared detector, so that the search time can be further shortened as compared with the third invention. In addition to this, in general, the gaze type sensor can take longer exposure time on the light receiving surface of the infrared detector, so that the sensitivity is higher than the scanning type sensor.
The detection distance for a flying object flying within the range of the coverage area to be covered by the infrared sensor can be made longer than in the third invention.

According to the fifth aspect of the present invention, since the visual axis stabilizing device is provided with the ultraviolet ray sensor, the same direction can be maintained even if the mounted base unit flies at various angles. As a result, the coverage area covered by the plurality of ultraviolet sensors mounted on the mother device can always be lower when viewed from the mother device. Further, since it is not necessary to widen the field of view for each sensor, the angular resolution of the sensor is not reduced, and the detection distance does not need to be shortened.

[Brief description of the drawings]

FIG. 1 is a diagram showing Embodiment 1 of a flying object alerting device of the present invention.

FIG. 2 is a view showing a flying object alerting device according to a second embodiment of the present invention.

FIG. 3 is a view showing a flying object alerting device according to a second embodiment of the present invention.

FIG. 4 is a diagram showing Embodiment 3 of a flying object alerting device of the present invention.

FIG. 5 is a view showing a flying object alerting device according to a third embodiment of the present invention.

FIG. 6 is a view showing one embodiment of a conventional flying object alerting device.

FIG. 7 is a view showing one embodiment of a conventional flying object alerting device.

FIG. 8 is a view showing an embodiment of a conventional flying object alerting device.

FIG. 9 is a view showing an embodiment of a conventional flying object alerting device.

[Explanation of symbols]

REFERENCE SIGNS LIST 1 UV sensor, 2 UV optical system, 3 short pass filter, 4 image intensifier, 5 photocathode, 6 2D CCD, 7 video amplifier, 8 signal processor, 9 display device, 10 UV sensor 1, 11
UV sensors 2, 12 UV sensors 3, 13 UV sensors 4, 14 Coverage of UV sensor 1, 15 Coverage of UV sensor 2, 16 Coverage of UV sensor 3, 17
Coverage area of ultraviolet sensor 4, 18 scanning infrared sensor, 19
Infrared window, 20 visual axis rotation mechanism, 21 rotation correction prism, 22 infrared optical system, 23 infrared detector, 24
Visual axis directing mirror, 25 infrared sensor 1, 26 infrared sensor 2, 27 coverage of infrared sensor 1, 28 coverage of infrared sensor 2, 29 infrared sensor coverage, 30 ultraviolet sensor coverage, 31 staring infrared sensor, 32 Band-pass filter, 33 elevation axis, 34 rotation axis, 35 visual axis movable mechanism, 36 gyro, 37 control system signal processor, 38 visual axis stabilizing device.

 ──────────────────────────────────────────────────続 き Continued on the front page (72) Inventor Hideaki Izumi 2-3-2 Marunouchi, Chiyoda-ku, Tokyo Mitsui Electric Co., Ltd. (72) Inventor Hiroshi Asano 2-3-2 Marunouchi, Chiyoda-ku, Tokyo F term in Ryo Electric Co., Ltd. BA11 BA35 BB21 CA27 CA34 CA67 DA09 EA05 EA07

Claims (5)

[Claims] A light wave sensor mounted on an aircraft for detecting an image of a flying object approaching the own aircraft and emitting a combustion flame; receiving an output of the light wave sensor to detect the presence of the flying object; A flying object alerting device having a signal processor that outputs an alert signal to the aircraft, wherein the light wave sensor has both an infrared sensor that detects an image of the flying object and an ultraviolet sensor that detects a combustion flame of the flying object, The upper region including the horizontal or horizontal direction with respect to the own device is defined as the covered region of the infrared sensor, and the cone-shaped region centered vertically or below the own device is defined as the covered region of the ultraviolet sensor. A flying object alerting device, characterized in that: 2. The flying object alerting device according to claim 1, wherein the ultraviolet sensor has at least four gaze type ultraviolet sensors disposed below the fuselage so as to cover the area covered by the ultraviolet sensor. apparatus. 3. The infrared sensor according to claim 1, wherein at least two infrared sensors are arranged above the body so as to cover the area covered by the infrared sensor, and include a scanning infrared sensor that moves a visual axis. The flying object warning device as described. 4. The flying object warning system according to claim 1, wherein the infrared sensor has at least four gaze-type infrared sensors disposed above the fuselage so as to cover the area covered by the infrared sensor. apparatus. 5. A visual axis movable mechanism that freely rotates around two orthogonal axes, a gyro mounted inside the visual axis movable mechanism, and a stabilizing visual axis using an output of the gyro. A visual axis stabilizing device comprising a signal processor for outputting a drive signal to the visual axis moving mechanism, wherein the ultraviolet sensor is mounted inside the visual axis moving mechanism of the visual axis stabilizing device. The flying object alerting device according to claim 1.