JP3400696B2 - High temperature blooming flare equipment for aircraft - Google Patents

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a flare device for deceiving a flying object that tracks infrared rays emitted from an aircraft or the like as a target.

[0002]

2. Description of the Related Art In a seeker mounted on a flying body that tracks an aircraft and detecting a target, the conventional seeker responded to heat radiated by the aircraft or the like. Therefore, it was possible to deceive this Seeker if a flare having a relatively high temperature (for example, about 2000 ° K) was fired. However, in recent years, in seekers targeting such aviation targets,
Seekers have been proposed that have the ability to distinguish infrared radiation in a given wavelength band. Such a seeker cannot be deceived with the conventional 2000 ° K flare. This will be described below.

FIG. 5 shows, for example, "The Infrared &Electro-O".
ptical Syatem Handbook Volume 7 Countermeasure Syste
FIG. 6 is a spectral characteristic diagram radiated from a conventional flare and an aircraft outlet shown on page 293 of “ms”. Further, FIG. 6 is disclosed in JP-A-4-60399 and JP-A-60-8977.
FIG. 9 is a spectral characteristic diagram radiated by a pseudo heat source at about 100 ° C. (about 373 ° K.) shown in Japanese Patent Laid-Open No. 9-90. The vertical axis represents the relative intensity of infrared rays, and the horizontal axis represents the size of infrared wavelengths.

In FIG. 5, the temperature of flare emitted by a conventional aircraft is set to about 2000 ° K and its spectral characteristic 1
Has the highest intensity of infrared light at the position of wavelength of about 1.5 μm, and then gradually decreases as the wavelength increases. On the other hand, the temperature of the outlet of the aircraft is about 1000
The spectral characteristic 2 is that the infrared ray intensity is strongest at a position of a wavelength of about 3 μm, and then gradually weakens. In addition, 100 ° C (about 373 ° shown in FIG.
In the spectral characteristic 3 of the pseudo heat source of about K), the intensity is strongest at the position of the wavelength of about 7.8 μm, and there is almost no infrared ray at the position of the small wavelength, for example, 0 to 3 μm.

For a target having such spectral characteristics, a seeker having a sensitivity to infrared rays having a wavelength of 1 to 2 μm outputs a voltage proportional to the area of the shaded area 4 in FIG.
On the other hand, the seeker having sensitivity to infrared rays having a wavelength of 3 to 5 μm outputs a voltage proportional to the area of the shaded line 5 in FIG. 5 and the shaded line 6 in FIG. Therefore, when these two seekers are used together and the two voltages output to each target are compared, it is confirmed that the target is an aircraft or 20
It is possible to identify whether it is a pseudo body of 00 ° K or 100 ° C (about 373 ° K).

Further, in recent years, in addition to a seeker having the ability to identify infrared rays in such a predetermined wavelength band, a seeker having the ability to identify an aviation target using an image has been proposed. Seekers that identify aerial targets using such images can identify the size of the target. In conventional flares, explosives are generally released and burned outboard. The light source is smaller than the emission area of the aircraft outlet because the explosive burns instantaneously outside the aircraft. Therefore, such conventional flares have not been able to deceive seekers using images to identify aerial targets.

[0007]

In the conventional flare device and pseudo heat source having such a structure, the temperature thereof is different from that of the discharge port of the aircraft, so that the seeker capable of discriminating infrared rays in a predetermined wavelength band is used. And I couldn't cheat .

The present invention has been made to solve the above-mentioned problems, and is approximately the same as the discharge port of an aircraft.
It is a temperature of 00 ° K and to obtain the aircraft hot blooming flare apparatus is possible.

[0009]

In a high temperature blooming flare apparatus for an aircraft according to claim 1, a container for accommodating a large heat capacity powder and having a temperature detector for detecting the temperature of the large heat capacity powder, The ejection means is provided at the end of the container to eject the large heat capacity powder to the outside of the machine, the heating means provided adjacent to the large heat capacity powder for heating the large heat capacity powder, and the output of the temperature detector. monitors, the exhaust temperature of the large heat capacity powder of aircraft
When the temperature at the outlet is reached, a control device for activating the firing means to fire the large heat capacity powder out of the machine.

A high temperature blooming frame for an aircraft according to claim 2.
In the device, the container is launched outside the aircraft by the launching means.
Large heat capacity powder, which is destroyed by the impact of the firing when fired
Is roughly the same as the aircraft outlet when the container is destroyed
Spread in size.

In the high temperature blooming flare apparatus for an aircraft according to claim 3 , the heating means comprises a conductive powder mixed with the large heat capacity powder and a heating device for heating the conductive powder.

In the high temperature blooming flare device for an aircraft according to claim 4 , the heating device is a high frequency heater.

In the high temperature blooming flare device for an aircraft according to claim 5 , the heating device is an ohmic heater.

In the high temperature blooming flare device for an aircraft according to claim 6 , the heating device is a high frequency radio wave heater.

In the high temperature blooming flare device for an aircraft of claim 7 , the heating means is an explosive powder mixed with the large heat capacity powder and an ignition device for igniting the explosive powder.

In the high temperature blooming flare apparatus for an aircraft of claim 8 , the large heat capacity powder is alumina ceramic powder.

In the high temperature blooming flare apparatus for an aircraft according to claim 9 , the large heat capacity powder is magnesium oxide powder.

In the high temperature blooming flare apparatus for an aircraft according to claim 10 , the large heat capacity powder is zirconium oxide powder.

[0019]

BEST MODE FOR CARRYING OUT THE INVENTION Embodiment 1. FIG. 1 is a side view with a partial cross section showing a high temperature blooming flare device for an aircraft of the present invention. In FIG.
7 is a mixed powder of alumina ceramics powder which is a large heat capacity powder and carbon powder which is a conductive powder. 8 is mixed powder 7
It is a case that is a container for storing. Reference numeral 9 denotes a thermocouple, which is a temperature detector for detecting the temperature of the mixed powder 7, which is disposed in the case 8 with one end supported by the case 8 and embedded in the mixed powder 7. Reference numeral 10 denotes a propellant which is provided at the end of the case 8 and is a means for ejecting the mixed powder 7 together with the case 8 to the outside of the machine. Reference numeral 10a is a detonator provided on the propellant powder 10.

Reference numeral 12 is a high-frequency heater which is a heating device for heating the carbon powder. The high frequency heater 12 is composed of a coil 12a wound around the case 8 and supplied with a high frequency current to generate a high frequency magnetic field, and a high frequency power supply 12b supplying a high frequency current to the coil 12a. The high frequency heater 12 and the carbon powder form a heating means for heating the alumina ceramic powder. 13 is electrically connected to the thermocouple 9 and the detonator 10a, has a built-in computer,
The control device monitors the output of the thermocouple 9 and outputs a signal to the detonator 10a to detonate the propellant powder 10 when the output of the thermocouple 9 reaches a predetermined value.

In the high temperature blooming flare device for an aircraft thus constructed, when the high frequency power source 12b is turned on, a high frequency current is supplied to the coil 12a, and the coil 12a produces a high frequency magnetic field. The mixed powder 7 is exposed to this high-frequency magnetic field, and first the conductive carbon powder absorbs the energy of the high-frequency magnetic field to reach a high temperature. Next, the carbon powder having a high temperature raises the temperature of the alumina ceramic powder.

The thermocouple 9 detects the temperature of the mixed powder 7 and outputs it to the controller 13. The control device 13 monitors this output, and when the temperature of the mixed powder 7 reaches about 1000 ° K, which is the same as the discharge port of the aircraft, outputs a signal to the detonator 10a to detonate the explosive powder 10 to cause the mixed powder 7 and the case 8 are fired outside the aircraft. The case 8 is destroyed by the impact when it is launched outside the aircraft. Then, the mixed powder 7 spreads spherically outside the machine. The amount of the explosive powder 10 and the shape of the case 8 are adjusted in advance so that the size of the sphere is approximately the same as the size of the discharge port of the aircraft. Of the mixed powder 7 that has spread outside the machine, the alumina ceramic powder has a large heat capacity, so it maintains a high temperature near 1000 ° K for several seconds.

In the high temperature blooming flare device for an aircraft constructed as described above, the temperature of the large heat capacity powder is the same as that of the discharge port of the aircraft, so that infrared rays in a predetermined wavelength band can be identified. You can deceive Sika. Also, since the large heat capacity powder spreads outside the aircraft to a size similar to the outlet of the aircraft, it is possible to deceive a seeker who uses the image to identify the target.

The temperature detector for detecting the temperature of the powder mixture 7 is not limited to the thermocouple 9, but may be a thermoelectric element such as a thermistor, and the temperature of the powder mixture 7 has reached a predetermined temperature. Can be replaced with the thermocouple 9 and used.

Embodiment 2. FIG. 2 is a partial cross-sectional side view showing another example of the aircraft high temperature blooming flare device of the present invention. In FIG. 2, 14 is an ohmic heater which is a heating device for heating the carbon powder of the mixed powder 7. The ohmic heater 14 includes a pair of electrodes 14a embedded in the mixed powder 7 at a predetermined interval inside the case 8 and an electrode 14a.
And a power supply 14b for supplying current to the. The ohmic heater 14 and the carbon powder form a heating means for heating the alumina ceramic powder. Other configurations are similar to those of the first embodiment.

When a voltage is applied to the electrode 14a, an electric current first flows through the carbon powder, and the carbon powder generates heat due to ohmic resistance. Next, the carbon powder having a high temperature raises the temperature of the alumina ceramic powder. After that, as in the first embodiment, when the mixed powder 7 reaches about 1000 ° K, it is ejected to the outside of the machine.

Also in the aircraft high temperature blooming flare device configured as described above, the same effect as in the first embodiment can be obtained. Further, the ohmic heater 14, which is a heating device, has a simple structure and can be manufactured at low cost.

Embodiment 3. FIG. 3 is a partial cross-sectional side view showing another example of the aircraft high temperature blooming flare device of the present invention. In FIG. 3, reference numeral 15 is a high frequency radio wave heater which is a heating device for heating the carbon powder of the mixed powder 7. High frequency wave heater 15
Is composed of a high-frequency radio wave source 15a for generating high-frequency radio wave, and a waveguide 15b extending from the high-frequency radio wave source 15a and extended so as to cover the side surface of the case 8 and irradiating the generated high-frequency radio wave to the case 8. ing. The expanded portion of the waveguide 15b is not in contact with the case 8. The high frequency radio wave heater 15 and the carbon powder form a heating means for heating the alumina ceramic powder. Other configurations are similar to those of the first embodiment.

The high frequency radio wave generated by the high frequency radio wave source 15a is transmitted to the case 15 through the waveguide 15b. Then, the mixed powder 7 exposed to the high frequency radio wave is heated to a high temperature by the carbon powder absorbing energy. Next, the carbon powder having a high temperature raises the temperature of the alumina ceramic powder. After that, as in the first embodiment, the mixed powder 7 is about 100
When it reaches 0 ° K, it is launched outside the aircraft.

Also in the aircraft high temperature blooming flare device configured as described above, the same effects as in the first embodiment can be obtained. Further, in the high frequency radio wave heater 15 which is a heating device, since the case 8 and the mixed powder 7 are not in contact with each other, the case 8 and the mixed powder 7 are smoothly ejected, and the safety is improved.

Fourth Embodiment FIG. 4 is a partial cross-sectional side view showing another example of the aircraft high temperature blooming flare device of the present invention. In FIG. 4, 16 is a mixed powder of alumina ceramic powder, which is a large heat capacity powder, and explosive powder. Reference numeral 17 is an ignition device for igniting explosive powder. The igniter 17 is composed of a filament 16a embedded in the mixed powder 16 and a power source 16b supplying an electric current to the filament 16a. The igniter 17 and the explosive powder form a heating means for heating the alumina ceramic powder. Other configurations are similar to those of the first embodiment.

In the aircraft high temperature blooming flare device thus constructed, when the power source 16b is turned on, the filament 16a is energized to ignite the explosive powder. The explosive powder burns to raise the temperature of the alumina ceramic powder having a large heat capacity. After that, as in the case of the first embodiment, when the alumina ceramic powder reaches about 1000 ° K, it is ejected to the outside of the machine.

Also in the high temperature blooming flare device for an aircraft constructed as described above, the same effect as in the first embodiment can be obtained. Further, since the heating means for heating the alumina ceramic powder is the explosive powder and the igniter 17, the structure can be simplified and the cost can be reduced.

In the first to fourth embodiments, the alumina ceramic powder is used as the large heat capacity powder, but the large heat capacity powder is not limited to the alumina ceramic powder, and may be magnesium oxide powder or zirconium oxide powder, for example. The effect of can be obtained.

[0035]

According to the high temperature blooming flare device for an aircraft of claim 1, a container for accommodating a large heat capacity powder and a temperature detector for detecting the temperature of the large heat capacity powder is provided,
The ejection means is provided at the end of the container to eject the large heat capacity powder to the outside of the machine, the heating means provided adjacent to the large heat capacity powder for heating the large heat capacity powder, and the output of the temperature detector. And a controller for activating the discharging means to discharge the large heat capacity powder to the outside of the aircraft when the temperature of the high heat capacity powder reaches the temperature of the outlet of the aircraft . Therefore, the temperature of the large heat capacity powder is set to a temperature similar to that of the discharge port of the aircraft, and thus it is possible to deceive a seeker capable of identifying infrared rays in a predetermined wavelength band.

A high temperature blooming frame for an aircraft according to claim 2
In the device, the container is launched outside the aircraft by the launching means.
Large heat capacity powder, which is destroyed by the impact of the firing when fired
Is roughly the same as the aircraft outlet when the container is destroyed
Spread in size. Large heat capacity powder is discharged from the aircraft outside the aircraft.
Using the image by spreading to a size similar to the exit
Seekers who identify the target can be deceived.

In the aircraft high temperature blooming flare apparatus according to a third aspect of the present invention, the heating means includes the conductive powder mixed with the large heat capacity powder and the heating device for heating the conductive powder. Therefore, the whole of the large heat capacity powder can be heated on average and can be surely heated.

In the high temperature blooming flare device for an aircraft according to claim 4 , the heating device is a high frequency heater.
Therefore, the large heat capacity powder can be surely heated to a high temperature in a short time.

In the high temperature blooming flare device for an aircraft according to claim 5 , the heating device is an ohmic heater.
Therefore, the structure can be simplified and the device can be manufactured at low cost.

In the high temperature blooming flare device for an aircraft according to claim 6 , the heating device is a high frequency radio wave heater. Therefore, the high frequency radio wave heater and the container are not in contact with each other, so that the large heat capacity powder can be smoothly ejected, and the safety is improved.

In the high temperature blooming flare device for an aircraft of claim 7 , the heating means is an explosive powder mixed with the large heat capacity powder and an ignition device for igniting the explosive powder. Since the heating means is the explosive powder and the ignition device, the structure can be simplified and the manufacturing cost can be reduced.

In the aircraft high temperature blooming flare device according to the eighth aspect , the large heat capacity powder is alumina ceramic powder. Therefore, the temperature can be high, and the high temperature can be maintained for several seconds after being launched outside the aircraft.

In the aircraft high temperature blooming flare apparatus according to claim 9 , the large heat capacity powder is magnesium oxide powder. Therefore, the temperature can be high, and the high temperature can be maintained for several seconds after being launched outside the aircraft.

In the high temperature blooming flare device for an aircraft of claim 10 , the large heat capacity powder is zirconium oxide powder. Therefore, the temperature can be high, and the high temperature can be maintained for several seconds after being launched outside the aircraft.

[Brief description of drawings]

FIG. 1 is a partial cross-sectional side view showing a high temperature blooming flare device for an aircraft of the present invention.

FIG. 2 is a partial cross-sectional side view showing another example of the aircraft high temperature blooming flare device of the present invention.

FIG. 3 is a partial cross-sectional side view showing another example of the aircraft high temperature blooming flare device of the present invention.

FIG. 4 is a partial cross-sectional side view showing another example of the aircraft high temperature blooming flare device of the present invention.

FIG. 5 is a spectral characteristic diagram radiated from a conventional flare and an aircraft outlet.

FIG. 6 is a spectral characteristic diagram radiated by a pseudo heat source at about 100 ° C.

[Explanation of symbols]

8 cases (containers), 9 thermocouples (temperature detectors), 10
Explosive powder (launch means), 10a detonator (launch means),
12 high-frequency heater (heating device), 13 control device, 1
4 ohm heater (heating device), 15 high frequency radio wave heater (heating device), 17 ignition device.

Claims (10)

(57) [Claims] 1. A container for accommodating a large heat capacity powder and a temperature detector for detecting the temperature of the large heat capacity powder, and a container provided with an end portion of the container for applying the large heat capacity powder. The temperature of the large heat capacity powder is monitored by monitoring the output of the discharging means for discharging to the outside, the heating means provided adjacent to the large heat capacity powder and heating the large heat capacity powder, and the temperature detector. A high temperature blooming flare device for an aircraft, comprising: a control device for activating the launching device to launch the large heat capacity powder to the outside of the aircraft when the temperature of the outlet of the aircraft is reached. 2. The container is removed from the aircraft by the launching means.
When it is launched, it will be destroyed by the impact of the launch,
Volume powder is ejected from the aircraft when the above container is destroyed.
2. The same size as the mouth is spread out.
A high temperature blooming flare device for an aircraft as described. 3. The aircraft according to claim 1 or 2, wherein the heating means comprises a conductive powder mixed with the large heat capacity powder and a heating device for heating the conductive powder. High temperature blooming flare device. 4. The high temperature blooming flare apparatus for an aircraft according to claim 3 , wherein the heating device is a high frequency heater. 5. The high temperature blooming flare device for an aircraft according to claim 3 , wherein the heating device is an ohmic heater. 6. The high temperature blooming flare apparatus for aircraft according to claim 3 , wherein the heating device is a high frequency radio wave heater. 7. The heating means, aircraft hot according to any one of claims 1, characterized in that the ignition device for igniting the explosive powder and該火drug powder is mixed with the large heat capacity powder 6 Blooming flare device. 8. the large heat capacity powder, aircraft hot blooming flare apparatus according to any one of claims 1 to 7, characterized in that an alumina ceramic powder. 9. the large heat capacity powder, aircraft hot blooming flare apparatus according to any one of claims 1 to 7, wherein the magnesium oxide powder. 10. The large-capacity powder, aircraft hot blooming flare apparatus according to any one of claims 1 to 7, wherein the zirconium oxide powder.