JPS5960199A - Infrared radiator - Google Patents

Abstract

(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.

Description

DETAILED DESCRIPTION OF THE INVENTION The present invention relates to an infrared ray emitting device that causes a flying object that is tracking an aircraft L2 to malfunction, thereby interfering with the tracking of the aircraft by the flying object.

[Technical background of the invention and its problems]

As is well known, flying objects that track infrared rays are aircraft jets (
jet plume).

That is, a flying object is tracked using information such as the intensity, shape, relative angular velocity, etc. of the aircraft's incoherent infrared rays.

Therefore, conventional jamming devices have used, for example, an infrared jamming signal (hereinafter referred to as a flare) that has a high infrared intensity and a speed different from that of an aircraft after being projected. That is, for example, if the intensity of the flare in the guidance zone of the flying object is A, and the intensity of the jet flame of the aircraft is a, then when the flying object uses the AM reception method, the signal Sf due to the flare is Sf = A (1 + kloospt). oosvct,
The signal 8p from the aircraft is 8 p = a ( 1 + 2oos ( p t + θ) ) o
w(u)e t+θ').

θ' = vcθ/p. If we take the sum of these, we get +[cross(1+, oos (p to 10θ))帥θ′]
2 water (arct + state)), and if we perform envelope detection on this and assume that A>a, then S f + Sp = A ( 1 + J oo8+)
t )+8 (1 +, OOs(p t+θ)) on
eθ' is obtained. Therefore, since the component due to the flare in the first term is larger than the second term, the flying object tracks this component.

In addition, if the flying object adopts the FM reception method, both signals Sf and Sp are S f = Aoos (#ct + m, (X)81)
t )S p=am(1I)c t+m2 (X
)Q(p t +θ''+θ'), and the sum of these is S f +S p=A' when A') > a.
(tloosCwc t +m1 oosp t+C
(m, cos(pt+θ)+θ'-ml 001]
p t )). Therefore, the influence of a is very small, and the flying object tracks the flare. In this way, it has conventionally been possible to obstruct tracking of a flying object.

However, in recent years, the performance of flying objects has improved, and it is now possible to avoid flare tracking by using two-color filters for ultraviolet and infrared rays, and by incorporating more tracking information using angular velocity or intensity memory. Ta. For this reason, even if the aircraft detects the tracking of the flying object and throws out flares, it becomes difficult to completely obstruct the tracking of the flying object.

[Purpose of the invention]

The present invention has been made based on the above circumstances, and its purpose is to provide an infrared radiation device capable of interfering with the tracking of a flying object by giving a malfunction signal to the tracking process of the flying object. It is something to do.

[Summary of the invention]

In this invention, infrared rays are intermittently FM-modulated by a chopper, and the FM-modulated signal frequency is set within the signal processing frequency band of the flying object, thereby giving a malfunction signal to the flying object.

[Embodiments of the invention]

An embodiment of the present invention will be described below with reference to the drawings.

First, the principle of this invention will be explained. The infrared radiation intensity from the aircraft jet is a, and the FM-modulated interference signal is A (], -1-oos (1#, t+βcOB
l #2 t ) ) (WI: carrier frequency OJ, : modulation frequency β: variable π) M index) If the reception method of the flying object is the AM method, then % (l −4−ktnsptcoIIILI/ ct
) In the case of FM method, %(1+ωs (tiger ct + mc, oSp t ))
It is.

fil A In the case of the M reception method, the signal detected by the flying object is [a + A (i + cos (jJ/, t + β cos LL
't t ) ) )=-”' (1+koosp
t cosLNct )+radiusq(W,'j+β009
W2 t )2 A −1−−ooIII(w, t+βcos w2 t
) ・cx+sp t oosu c t. Here, the first term is the signal component desired by the flying object, and the second term is W
The third term, which becomes an interfering signal by appropriately selecting and bringing it into the same band as the first term, is generally a component outside the band. Decomposing the above formula into each frequency component, # + (outside band) +2) In the case of FM reception system, Ca+A (1+oos (W, t+βcOIlvJ)
2t))]X' (1-1-Oos(IJ/ct+mo
osui))=-”-A (l-4-arpa (W
c t + moos 'p t ) ) + medicine oos
(Wit+bar2t) 4-4ooq (u), t+βoosVJ2n)
-003 (Wct -1-moospt) 10-Σ J
v (1) 00B(("I+νw2) '+2
'2ν=-+(outside band), the first term is the signal component and the second term is the interference signal component, where 147C=1600Hz, p=1333gHz,
m=211'H=2000Hz, w2=20
011z, β=3 and A=10a, the T-section wave number overlapping tram is shown in FIG.

However, 1. The solid line is the component of the first term, and the lIl& line is the component of the second term.

By the way, the optical system of a normal flying object is a gyro mount [7]. There is a 1:1 correspondence between the rotation speed of this gyro and the set meal, at a normal power supply of 40' OHZ,
The rotation speed determined by 2 poles and 4 frames is 400 Hz, respectively.
200 H2 roars. The number of divisions of the reticle depends on the size,
Due to manufacturing reasons, the optical system is divided into 24 parts (12 cycles).
) has no stomach.

The detector's i/f & (chopping frequency for sound reduction is approximately 1500-25001 (z).

From the above, the chopping frequency of the reticle is 15 (
It is between 10 and 2500 Hz, and has a bandwidth (index 2) of ±200 Hz for the AM reception system and ±4 + 1011 z (index 2) for the FM reception system, depending on the modulation index, relative to the carrier frequency.

Therefore, we will next find the optimal modulation method for the interference signal.

The interference signal is A(1+(9)(W, l+β lid vJ, t)),
It is desirable that vJI be in the center of the expected range of chopping frequencies of the flying object, so 's = 2000.
Hz. If the receiving band of the flying object is wC±B, then the power of the interfering signal is N=, □C. It is YaB. This varies depending on v(, B, but the optimal modulation is to maximize its lowest value, that is, the minimum disturbance power. Therefore, with B constant, wC is changed from 1500 Hz to 2
The lowest value Nm1n of N when changing to 500 Hz is determined as shown in Fig. 2 (2).

In this figure, when 't' = 200 Hz, N
The peak of m1n is β= both at B=200 and 400 Hz.
2.5, I) For J2 = 133% Hz, for B = 200 Hz, β = 4.5, B = 4 (l
OI-]z and β=4.6. The beeb value is 't = 2 (10Hz is larger. From this, the optimal variation of the interfering signal is determined as Wl = 2000 IIz = 2 (l Ol - 1z β = 2.5. The S/Nm1n at the receiving input is B ~ 400 H2.

a+A =2.0(-τ-)2 becomes. Here, if A=108, S/Nm1n=3.9 dB.

Next, an example will be described based on the above principle.

In FIG. 3, 31 is an infrared radiation source.

This radiation source 31 is a heat source 3 using propane gas, for example.
2 and ceramic plates 3 and 7 provided near this heat source 32.
3 is heated, and infrared rays are emitted from this ceramic plate 33. A chopper 34 is provided facing the ceramic plate 33. For example, as shown in FIG. 4, this chopper 34 is made up of an infrared transmitting section 348 and an infrared blocking section 342 that are arranged alternately along the circumferential direction, the width of which gradually increases from the center to the circumferential direction. By rotating 34 by 1-, the generated infrared rays are chopped. This chopped infrared rays are radiated through the iT visual blocking filter 35. This infrared radiation device is mounted on an aircraft, for example.

In the above configuration, when the chopper 34 is rotated, as shown in FIG. 5, infrared oil is generated intermittently, making it possible to perform FM modulation of infrared light.

Here, the infrared transmitting portion 34° and the blocking portion 34. The width of the groove in the circumferential direction gradually changes in the circumferential direction.

Therefore, the FM modulation number vJ, , u72. By setting the rotational speed, pattern shape, and division ratio of Chiyo/J so that β becomes the value described above (7), it is possible to optimally interfere with the flying object.

According to the second embodiment, the infrared rays go up the chopper and F'
M modulation is performed, and the carrier frequency, FM modulation frequency, and modulation index of this modulation are set within the signal processing frequency of the flying object and its band. Therefore, it is possible to interfere with a flying object that has recently received a lot of tracking information, and to prevent tracking.

〔Effect of the invention〕

As described in detail above, according to the present invention, by emitting FM modulated infrared rays, it is possible to cause a malfunction in the tracking process of a flying object and to disturb the tail of a flying object. A regular culm can be served.

[Brief explanation of the drawing]

Figures 11-1 and 2 are diagrams for explaining the present invention in detail, Figure 3 is a configuration diagram showing one embodiment of the infrared radiation device according to the present invention, and Figure 4 is the same as that shown in Figure 3. FIG. 5 is a diagram showing the configuration of the chopper, and is a diagram showing an example of infrared rays output through the chopper shown in FIG. 4. 3. Infrared radiation, 34. Chopper. Applicant's agent Patent attorney Takehiko Suzue Figure 3 31 Figure 4

Claims (1)

[Claims] An infrared radiation device comprising an infrared radiation source and means for FM modulating the emitted infrared rays, the FM modulated signal frequency being set within a signal processing frequency band of a flying object.