JPH01239399A - Deceptive target - Google Patents

Abstract

PURPOSE:To permit an infrared rays tracking system missile to track a spherical dummy heat source as a deceptive target, by a method wherein a multitude of small sized dummy heat sources, having a semi-spherical configuration, is arranged along the surface of a sphere to emit infrared rays from semi-spherical section of the semi-sphere. CONSTITUTION:A semi-spherical body 40-1 has the highest refractive index 2<1/2> in a semi-spherical Luneberg lens 31 and is a ceramics semi-spherical body with a radius (r1) while the outermost periphery hollow semi-spherical body 40-n is provided with the radius (nr1) and a refractive index 1. The semi- spherical body has a point heat source 43. The hollow semi-spherical bodies 40-1, 40-5,... 40-(n-1), 40-n, having a thickness (r1) and different refractive indexes, are superposed toward the outward direction of the semi-spherical body in such a manner. According to this constitution, the radiating energy of the point heat source 43 will never become parallel rays and is radiated with a spreading angle like as radial rays 46. A decoy target 21, in which a multitude of Luneberg lenses 31 are arranged along the surface of the spherical body, is towed by a wire 2, connected to a fuselage 1, to protect the fuselage and the like from the missile of infrared ray tracking system.

Description

DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to a deceptive target for protecting an aircraft etc. from missiles having an infrared tracking function.

[Conventional technology]

Previously, as a tracking and interfering method developed for the same purpose, in order to minimize infrared radiation from the aircraft body, etc., paint using ceramic particles is applied to the entire surface of the aircraft body. 7. By mixing low-frequency air into the engine exhaust. how to reduce heat radiation,
The target position relative to the center of the reticle is detected and a tracking error signal is obtained by ejecting hot particles or high-temperature objects as deceptive targets to the outside of the machine, and by chopping the target's thermal radiation with a reticle. For missiles of this type, there are methods that include an infrared radiator that emits deceptive infrared radiation modulated around the above-mentioned chopping frequency.

[Problem to be solved by the invention]

According to the above method, protection against missiles such as two aircraft is determined by the combat situation and the timing of the activation of the jamming device 1.

In many cases, it depends on the attitude of the aircraft and the attitude of the aircraft, so it is difficult to say that it is high at present. Furthermore, in the case of an infrared radiator that uses a modulation method, it is effective only against missiles that have a reticle among the opposing missiles that use a passive method; It is ineffective against completely passive missiles that track the target's thermal image. In other words, the key to protecting the aircraft from infrared image processing missiles is currently in place.

Doesn't exist.

This invention was made to solve this problem, and aims to obtain a deceptive target that is not limited by the timing of jamming device activation, the aircraft attitude, or the pushing method used by the opponent's missile using infrared rays. .

[Means for resolving billing issues]

The deceptive target according to this invention is a deceptive target whose shape is similar to the aircraft in terms of thermal radiation and whose infrared radiation intensity is several times higher than that of the aircraft in order to protect two aircraft etc. from the above-mentioned infrared tracking missile. The aircraft attempts to fly while towing a pseudo heat source via a mooring wire of approximately 200 nt.

[Effect]

This invention emits a pseudo heat source from the aircraft during flight.

This pseudo heat source is towed via a mooring wire of about 200 m. This Keiji heat source has an almost spherical shape as a whole, and along the surface of this sphere.

A large number of small pseudo heat sources with a hemispherical shape are arranged. Each of these small-sized pseudo heat sources has a point heat source by supplying "one force" from the aircraft body to one point of the hemisphere via a mooring wire, and emits infrared rays to the outside from the hemispherical cross section of the hemisphere. This method attempts to make an infrared tracking missile track a spherical pseudo heat source as a deceptive target.

Operationally, the aircraft side detects missiles heading towards the aircraft at an early stage (using other means such as target detection equipment), and releases a target based on the threat assessment.

The separation distance of approximately 200 meters was determined by determining the missile's field of view and the temperature resolution between the target and the background, within the expected range of the infrared missile.

Of course, the priority is to protect one aircraft, but this can also be changed during flight.

〔Example〕

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

In the figure, (1) is the aircraft body, and (2) is a mooring wire that connects the deception target Qυ and the aircraft body, and has a power supply line inside. Gυ is a hemispherical Luneberg lens that receives energy from the power line and radiates heat to the outside, and is arranged in large numbers on a spherical surface.

As a whole, they form the goal of deception Qυ. Deceptive goal Qυ
The energy supply to the hemispherical Luneberg lens 0υ can be controlled from the fuselage side so that the thermal radiation energy exceeds that of the fuselage (1) and the heat radiation shape resembles the fuselage (1).

When the deceptive target C21) having such a configuration and the aircraft (1) are viewed from a long distance, the angle of view is as shown in FIG. Figure 2 shows the case where the separation distance between Demangetsu Rin and the aircraft is 200m. The distance is 10 mils for 20/a, 20 mils for 10-a, and 100 mils for 2 fats. In terms of search performance on the missile side at long distances, it is very difficult to identify and separate two similar targets, which requires a wide field of view, for example, several tens of degrees. As the missile approaches the two targets, it becomes possible to distinguish between the two targets, but because their shapes are similar and the radiation intensity of the deceptive target CB is several times higher than that of the aircraft (11).

Even though existing missile seekers have shape recognition capabilities, they are gradually guided to deceptive targets. Normally, when a missile approaches its target and the width of the target within its field of view reaches about 50 inches, guidance control is discontinued and the missile moves straight toward the target by inertia. For example, if the diameter of the deceptive target according to the present invention is 2 m, the distance at which the angle of view is 2 m - 4 m (i.e., the length that the target in the field of view is less than 50 inches) is the narrow field of view. Assuming 20 mils, 4
m/i o o o -200 m. In other words, the aircraft will be safe if it is kept as far away from the aircraft as the distance to the target at the moment when missile guidance control is terminated.

The Luneberg lens constituting the deceptive target QD will be explained.

Figure 3 shows the Luneberg lens.

- Boat fishing is well known in the field of radar technology. In the figure, (4υ is a Luneberg lens manufactured with nine-sphere symmetry, and the incident wave (43) is focused at one point on the spherical surface.

On the other hand, if there is a point heat source (43) on the spherical surface, the infrared rays emitted from the point heat source will be radiated to the outside as parallel rays (hammers) while passing through the lens.Since the Luneberg lens is spherically symmetric, this Focusing is independent of the direction of the incident wave, so in general detection of the incident wave over a wide angle is possible by radial scanning by moving a point source over a spherical surface.

The Luneberg lens has the following relationship between the radius r0 of the refractive index μ1 sphere and the radial distance r of the lens.

・= β zero 7 The refractive index is maximum at the center of the sphere at the bottom, decreases with r, and becomes 1 around 0. Materials whose refractive index changes continuously like this are difficult to manufacture.

In reality, it is manufactured by dividing the refractive index in stages from the center of the sphere.
It attempts to approximate continuous change. The lens materials are ceramic, germanium, zinc sulfide,
Select from magnesium carbide, silicon, etc., which are inexpensive and meet the requirements of the mechanical structure.

FIG. 4(a) shows an embodiment of the present invention.

CD is a hemispherical Luneberg lens (so called) obtained by cutting the Luneberg lens (41) in Fig. 3 into a hemispherical shape, and the radiant energy of the two-point heat source C3 does not form parallel rays. Radial rays (like 1 fP,
A certain expansion is radiated outward from multiple angles.

FIG. 4(b) is a diagram showing the actual structure of the hemispherical Luneberg lens shown in FIG. 4(a). In the figure,
(40-1) has the highest refractive index a and is a ceramic hemisphere with radius rl. (40-2) has a refractive index of 136. Radius 2r1. It is made of ceramic with a thickness rl, and is configured to surround the outside of the hemispherical surface of (4o-1). Is (40-3) a refractive index? , 31. radius 3r1
It is made of ceramic with a thickness rl, and is configured to surround the hemispherical surface of (40-2). Thus, the refractive index differs toward the outside of the hemisphere. Hollow hemisphere of thickness rl (40-4), (40-5)...(4
0(n-4)) and (40-n). The radius of the outermost hollow hemisphere (40-n) is nr1, and the refractive index is 1
shall be. 03 is a point heat source, which is the same as in FIG. 4(a). By configuring as described above, a practical hemispherical Luneberg lens can be formed.

Figure 5(a) shows a deceptive target C in which a large number of hemispherical Luneberg lenses Gυ of Figure 4(a) are arranged along a spherical surface.
υ, which is the same as that explained in FIG.

Figure 5 (1)) is a schematic representation of a practical target. (51) is a practical target with a hollowed-out cylindrical interior to make it suitable for towing. It also serves to cool the point heat source (43) attached to the hemispherical Luneberg lens Gυ. (52) is a cable for anchoring the mooring wire (2) to the practical target (51).

〔Effect of the invention〕

As explained above, this invention has the effect of making it possible to deceive all kinds of missiles that utilize infrared rays and misdirect them to the target direction, thereby protecting the aircraft with high accuracy.

[Brief explanation of the drawing]

Fig. 1 is a diagram showing the aircraft towing a deceptive target, Fig. 2 is a diagram showing the angle of view between the deceptive target and the aircraft, and Fig. 3 is a diagram for explaining the Luneberg lens. FIG. 4(a) is a diagram showing a hemispherical Luneberg lens. FIG. 4(b) is a configuration diagram of a hemispherical Luneberg lens. FIG. 5(a) is a diagram showing a deceptive goal, and FIG. 5(b) is a diagram showing a practical deceptive goal. In the figure, (1) is the fuselage, (2) is the mooring wire, and CD
is a deceptive target, and 0υ is a hemispherical Luneberg lens. (40-1) is a ceramic hemisphere, (40-2)
is a ceramic hollow hemisphere with radius 2r1, (40-
3) is a ceramic hollow hemisphere with radius 3r1, (4
0-n) is the outermost hollow hemisphere, G13 is a point heat source, (
51) is a pragmatic deception goal. In each figure, the same reference numerals indicate the same or corresponding parts. 31!1 Figure 4 (cl) Figure (b)

Claims (1)

[Claims] First hemisphere with refractive index √2, radius r_1, radius 2r_1
a hollow second hemisphere of thickness r_1 surrounding said first hemisphere at 3r_1, a hollow third hemisphere of thickness r_1 surrounding said second hemisphere at radius 3r_1; The radius nr_1 provided at the outermost circumference by overlapping the hollow hemispheres
It has a hollow n-th hemisphere with a thickness r_1 and a refractive index of 1.0, and the refractive index of the first hemisphere is from √2 to the refractive index of the outermost n-th hemisphere of 1.0. It has been changed in stages,
a hemispherical Luneberg lens having a point heat source inside; a sphere with the hemispherical Luneberg lens arranged on its surface;
A deception target characterized by comprising a wire for mooring the sphere to the aircraft body and a power line for supplying electric power to the point heat source.