JP2002022399A - Flying body loaded by reflector for radar reflection - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a flying object formed that a wide empty space at the internal part of a flying object is ensured by reducing the internal volume of a flying object itself occupied by loading a reflector and the empty space at the internal part of the flying object can be effectively utilized. SOLUTION: In a flying object that a corner reflector 11 is provided to reflect radar and by flying in the air, an incident electric wave is reflected by a corner reflector 11, a reflector row is provided that a plurality of corner reflectors 11 in a hollow triangular conical state a bottom part 12 of which is released is situated along the longitudinal direction of the drum of the flying object. The reflector row is situated in the direction of each of at least eight equal divisions into which the peripheral direction of the flying body drum body is divided. This structure enables manufacture of the flying object capable of reflecting radar in a whole area and remarkable reduction of a cost.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a flying object such as a target on which a reflector for radar reflection is mounted.

[0002]

2. Description of the Related Art Conventionally, a target towed by a fighter or the like via a towed steel cable is captured by radar on the ground, at sea, or in the air, and training for grasping the position and distance to the target, and further missiles are conducted. Combat training is being launched to fire, track and hit targets.

[0003] As a target used in such battle training, an IR target is disclosed in Japanese Utility Model Publication No. 60-21680. The IR target is a towing target for infrared homing missile shooting training, and is used for training to track infrared radiation from the target.

FIG. 7 shows an example of an IR target. IR target 1
Reference numeral 01 denotes a spherical lens reflector provided at the front end of a body made of a cylindrical outer cylinder 102 for reflecting an X-band radio wave at a wide angle forward, and a spherical lens reflector at a rear end for reflecting an X-band radio wave at a wide angle backward. Lector 108 is provided. Further, two spherical lens reflectors 104 and 105 for reflecting the X-band radio waves to the left and right at a wide angle are provided inside the body composed of the cylindrical outer cylinder 102. Further, around the rear end, a plurality of fins 106 and a flare 107 for jetting backward are mounted.

[0005]

The above-mentioned IR target 101
, Two spherical lens reflectors 104 and 105 for reflecting the X-band radio wave to the left and right at a wide angle are disposed inside a body composed of a cylindrical outer cylinder 102.

However, the spherical lens reflectors 104, 1
Since 05 is buried inside the body of the cylindrical outer cylinder 102, it occupies a large space inside the body, and there is a disadvantage that the space inside the body cannot be effectively used for other purposes. .

For example, the radar reflection coverage of one spherical lens reflector is approximately 120 °, and the IR target 10
At least three spherical lens reflectors are required to cover all directions (360 °) in one direction. In this case, if the diameter of the cylindrical outer cylinder 102 of the IR target 101 is 200 mm and the spherical lens reflector is a sphere inscribed in the cylindrical outer cylinder 102, the diameter is 200 m
The volume equivalent to a cylinder with a length of about 600 mm in m
It will be occupied by a spherical lens reflector.

Furthermore, spherical lens reflectors are generally expensive, and when two spherical lens reflectors are mounted in front of and behind the target 101 and three spherical lens reflectors are mounted inside the fuselage, they are shot down with a missile or the like by training. There is a problem that the cost is too high to use.

The invention according to the present application has been made to solve the above-mentioned problems, and an object of the invention is to provide a flying object such as a target equipped with a reflector for radar reflection. Therefore, the flying object can reduce the internal volume of the flying object itself occupied by mounting the reflector, secure a wide empty space inside the flying object, and effectively use the empty space inside the flying object. Is to provide.

It is another object of the present invention to provide a flying object capable of manufacturing a flying object capable of reflecting radar in all directions at a low cost and achieving a great cost reduction.

[0011]

In order to achieve the above object, a first invention according to the present application is provided with a reflector for reflecting a radar, and flying in the air to reflect an incident radio wave by the reflector. In the body, the reflector having a hollow triangular pyramid shape whose bottom portion is open is provided with a plurality of reflectors along the longitudinal direction of the flying body, and each of the circumferential directions of the flying body is divided into at least eight equal parts. A flying object characterized in that the reflector rows are arranged in a direction.

A second invention according to the present application is directed to the flying device according to the first invention, wherein the reflector is housed inside the flying body made of a material that transmits radio waves. Body.

Further, in the third invention according to the present application, the reflector rows provided in at least eight directions are in contact with adjacent reflector rows, and the inside of the cylindrical body formed by the reflectors is The flying object according to the first or second invention, wherein the flying object is hollow.

[0014]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Embodiments of the present invention according to the present invention will be described below in detail with reference to FIGS.

FIG. 1A is a perspective view showing an appearance of a target 1 which is an embodiment of a flying object according to the present invention.

The outer shape of the target 1 has a substantially cylindrical shape, and both ends have a torpedo shape which draws a gentle curve and narrows toward the end. At the front end of the body composed of the cylindrical outer cylinder 2, there is provided a spherical lens reflector 3 for reflecting radio waves forward at a wide angle, and at the rear end there is provided a spherical lens reflector 8 for reflecting radio waves at a wide angle backward. As the spherical lens reflectors 3 and 8 provided on the front and rear sides, for example, Luneberg lenses are used. Alternatively, a corner reflector can be used.

The cylindrical outer cylinder 2 has a diameter of about 200 mm and the entire length of the target 1 is about 3000 mm. R. P. (Fiber reinforced plastic) or the like. The frequency of the radio wave can take various values depending on the radar used for training.

At the center of the cylindrical outer cylinder 2, wings 17
18 are provided. Also, at the back of the target 1 body,
Stabilizing wings 5 and 6 are provided in the left-right direction of the target 1 main body, and stabilizing wings 7 are provided in the vertical direction of the target 1 main body. At the rear ends of the left and right stabilizer blades 5, 6, control surfaces 5a, 6a whose ends are rotatable vertically are provided.

The stabilizing wing 7 functions to prevent the target 1 from swinging in the left-right direction, and has a control surface 7a rotatable in the left-right direction at the rear end. Stable wings 5, 6,
The control surfaces 5a, 6a, and 7a of 7 are linked with a control unit 9 provided inside the cylindrical outer cylinder 2, and rotate according to a command from the control unit 9 to change the flight direction of the target 1. be able to.

The target 1 in the present embodiment is not a towable target towed by a fighter or the like, but a self-propelled target to fly by its own power. Therefore, it is necessary to fly by remote wireless operation, and the control unit 9 is provided in an empty space inside the cylindrical outer cylinder 2.

A jet engine 10 serving as propulsion power is provided below the outer shell of the cylindrical outer cylinder 2 of the target 1 main body, and a fuel tank 16 for storing fuel to be supplied to the jet engine 10 is provided. , In the empty space inside the cylindrical outer cylinder 2.

According to the present invention, in addition to the above-described structure, a radar reflector is provided on the middle portion of the cylindrical outer cylinder 2 so as to be able to reflect radio waves in all directions (360 °) in the vertical and horizontal directions of the target 1. A reflector 4 is provided. The composite reflector 4 is
Corner reflector 11 (hereinafter referred to as cornerref 11)
Is a complex formed by bonding a plurality of.

FIG. 1B is an enlarged view of the corner reflex 11 constituting the composite reflector 4 used in the present embodiment.

As shown in FIG. 1 (b), one corner reflex 11 has a hollow triangular pyramid shape in which a bottom portion 12 (hatched portion) is open, and the bottom portion 12 has an equilateral triangle and three slopes respectively. It has a right-angled isosceles triangle shape. Cornerref 11
Is to reflect a radio wave incident from the open bottom portion 12 inside the triangular pyramid, and then emit it in the incident direction again. The triangular plate 13 forming three slopes facing the inside of the triangular pyramid needs to be a material that reflects radio waves, and is made of an aluminum plate or a plate material on which a metal such as silver is deposited. Each triangular plate 13 joins a ridge 13a, which is two sides forming a right-angled vertex, with each ridge 13a of another triangular plate 13 to form a triangular pyramid-shaped cornerref 11.

The triangular pyramid-shaped corner reflex 11 has the three slopes facing each other as radio wave reflection surfaces, and the radio wave incident from the bottom portion 12 is reflected by three or two slopes inside the triangular pyramid. Sequentially reflected, or 1
The light is reflected by the surface and emitted again in the incident direction.

Here, a radar cross section (hereinafter, referred to as a radar cross section) representing the reflectivity of the radar is as follows.
RCS) will be described. The RCS is 4π times the ratio of the output per unit solid angle scattered in a certain direction to the output per unit area of a plane wave incident on the scatterer from that direction. In the present embodiment, an X band radio wave (for example, a frequency of 10 GHz and a wavelength of 30 mm)
The following description is based on the premise that it is required to secure RCS2m ² for the RP.

FIG. 4 is a characteristic diagram showing a radar reflection covering area of the corner reflex 11. Since the above-mentioned spherical lens reflector has a radar reflection coverage of about 120 °, three spherical lens reflectors are rotated by 120 ° each in order to reflect radar in all directions, up, down, left, and right of the target. Had to be placed in a different position. However, the cornerref 11 used in the present embodiment is, as shown in FIG.
It was detected that the radar reflection coverage was about 45 °. Therefore, in order to reflect the radar in all directions, up, down, left, and right of the target 1, it is necessary to arrange at least eight cornerrefs 11 at positions rotated sequentially by 45 °.

According to the spherical lens reflector having a diameter of 200 mm inscribed in the body composed of the cylindrical outer cylinder 2, it is possible to secure RCS of ² m ² or more in the radar reflection covering area. In order to secure RCS ² m ² by disposing the corner reflex 11, it is necessary to use the corner reflex 11 whose one side 12 a of the bottom portion 12 is about 200 mm. In this case, the volume that the corner reflex 11 cuts into the inside of the cylindrical outer cylinder 2 is large, and occupies a large space inside the body. Therefore, Cornerref 1
It is necessary to minimize the volume of the bite 1 that enters the inside of the cylindrical outer cylinder 2 as much as possible.

In consideration of the minimum size of one corner reflex 11, it is desirable that the length of one side 12a of the triangular pyramid bottom portion 12 be at least twice the radar wavelength.

Therefore, in this embodiment, a plurality of corner reflexes 11 as small as possible in the longitudinal direction of the target 1 are provided in one direction obtained by dividing the outer periphery of the cylindrical outer cylinder 2 into at least eight equal parts in the circumferential direction. The structure is provided. As a result, the volume that the corner reflex 11 cuts into the inside of the cylindrical outer cylinder 2 is reduced, and the occupation of the empty space inside the target 1 by the corner reflex 11 can be reduced, and the empty space inside the fuselage can be effectively used for other purposes. It is configured to be available.

Specifically, as shown in FIG. 1B, the length of the ridge 13a of the corner reflex 11 is set to 60 mm, and the outer circumference of the cylindrical outer cylinder 2 is divided into at least eight equal parts in the circumferential direction. In addition, a reflector row 15 (see FIG. 2B) in which six corner reflexes 11 are continuously formed in the longitudinal direction of the target 1 is provided. Accordingly, in the entire target 1, eight consecutive reflector rows 15 are prepared, and each reflector row 15 is provided in eight different directions, so that 48
The configuration is such that a number of corner reflexes 11 are provided. According to this configuration, RCS ² m ² can be substantially secured in the vertical and horizontal directions (360 °) of the target 1. In addition, the length of one side 12a of the triangular pyramid bottom portion 12 of the corner reflex 11 having the length of the ridge 13a of 60 mm is about 85 mm, which satisfies the requirement that it is twice or more the radar wavelength (30 mm).

The reflector row 15 does not necessarily have to be one in which the individual corner reflexes 11 are formed continuously and integrally, but may be one in which the individual corner reflexes 11 are arranged in the longitudinal direction of the target 1. .

FIG. 2A shows a front view of the composite reflector 4 and FIG. 2B shows a side view of the composite reflector 4. As shown in FIG. 2A, the composite reflector 4 of the target 1 configured as described above has an outer diameter of about 200 mm, an inner diameter of about 100 mm, and a length of the target 1 in the longitudinal direction of about 300 mm.
Into a hollow cylindrical shape. Therefore, as compared with the case where a spherical lens reflector is used, the target 1 is compact and has a hollow cylindrical shape, so that the empty space inside the target 1 can be effectively used without bisecting the empty space.

Next, a method of manufacturing the composite reflector 4 will be described with reference to FIGS.

The corner reflex 11 needs to be made of a material that reflects radar and is made of a lightweight material.
As shown in (a), in the present embodiment, the manufacturing is performed using the aluminum sheet metal 14. A single aluminum sheet metal 14 is pressed by a press equipped with a triangular pyramid-shaped mold, and a plurality of triangular pyramids serving as corner reflexes 11 are formed on the surface of the aluminum sheet metal 14 as shown in FIG. I do. At this time, as shown in FIG. 2B, the corner reflexes 11 to be arranged in the longitudinal direction of the target 1 are arranged upside down with the corner reflexes 11 adjacent to the left and right, and are arranged so as to be alternated. It is desirable to do. With this arrangement, the length of the composite reflector 4 in the longitudinal direction can be reduced as much as possible.

Then, the aluminum sheet metal 14 on which a plurality of corner reflexes 11 are formed by a press machine is bent as shown in FIG. 3C to form a cylindrical shape having an octagonal outer peripheral surface. At this time, the aluminum sheet metal 14 is bent so that the apex of the triangular pyramid that becomes the corner reflex 11 projects toward the inside of the cylindrical shape. After bending so as to form an octagonal cylindrical shape, the ends of the sheet metal are connected by welding so that the aluminum sheet metal 14 is not opened. In this way, an octagonal composite reflector 4 having a hollow interior is formed.

Incidentally, the method of forming the composite reflector 4 from the aluminum sheet metal 14 as described above is not limited. For example, a body having an octagonal outer surface and a hollow cylindrical inside and a plurality of concave triangular pyramids formed on the outer surface is molded with resin or the like, and a metal such as silver is deposited on the outer surface. To form the composite reflector 4.

The composite reflector 4 formed as described above
Is housed inside the cylindrical outer cylinder 2 this time. The cylindrical outer cylinder 2 is formed in a hollow cylindrical shape with a material that transmits radio waves, and is formed to have a size in which the composite reflector 4 is housed inside the cylinder. In this example, a cylindrical outer cylinder 2 having a diameter of about 200 mm is formed, and a composite reflector 4 is accommodated therein. Thus, the cylindrical outer cylinder 2
By providing the composite reflector 4 inside the target, the target 1
Air resistance on the outer surface of the
The surface irregularities are prevented from hindering the stable flight of the target 1.

In the present embodiment, the cylindrical outer cylinder 2 is formed of a material that transmits radio waves, and the composite reflector 4 is accommodated therein. A structure in which the reflector 4 is provided may be employed.

In this embodiment, the composite reflector 4 is described using a composite reflector 4 in which a reflector row 15 is integrally formed and has a hollow octagonal column shape long in the longitudinal direction of the target 1. The composite reflector 4 is not limited to the above embodiment. Alternatively, the composite reflector 4 may be divided in the longitudinal direction and a plurality of composite reflectors formed like a slice may be arranged in the longitudinal direction. Further, as the reflector in the present invention,
The target is not necessarily a composite reflector, and a plurality of independent corner reflexes 11 may be arranged in the longitudinal direction and the circumferential direction of the target 1.

After the cylindrical outer cylinder 2 is formed, a control unit 9 for remote operation and a fuel tank 16 are provided inside the body, and spherical lens reflectors 3 and 8 are provided at the front end and the rear end of the cylindrical outer cylinder 2. I do. Then, left and right wings 7 and 18 are provided in the middle abdomen, and stable wings 5, 6 and 7 are provided in the rear, and a jet engine 10 is provided below the target 1.

In the target 1 manufactured as described above, a wide empty space inside the fuselage can be secured, and the space inside the fuselage can be effectively used for other purposes.

Further, since the empty space inside the target is not divided into the front part and the rear part, it is possible to mount equipment continuous over the front part and the rear part inside the target.

Further, although spherical lens reflectors are generally expensive, they can be manufactured at low cost because spherical lens reflectors are not used inside the body, and are more expensive than spherical lens reflectors. Equivalent RCS can be secured.

In this embodiment, the structure is such that the octagonal composite reflector 4 inscribed in the cylindrical outer cylinder 2 is provided, but the composite reflector 4 does not necessarily have to be connected in eight directions.

FIG. 6 shows a target 1 'according to another embodiment.
FIG. As shown in FIG. 6, eight reflector rows 15 composed of a plurality of corner reflexes 11 extending in the longitudinal direction of the target 1 'may be formed, and the direction may be sequentially shifted by 45 ° in eight directions. In the target 1 ', the reflector rows 15 arranged in eight directions are not closely attached to each other, but are arranged at intervals. Therefore, the corner reflex 11 forming one reflector row 15
It is necessary to provide a plurality of such that the degree of radar reflection becomes a desired RCS.

The targets 1, 1 'produced as described above are:
For example, it is remotely controlled by a transmitter on the ground or at sea, and flies through the air. Radio waves are transmitted by a radar on the ground, at sea, or in the air, and reflected waves from the targets 1, 1 'are detected by the radar to capture the targets 1, 1'.

Then, the detected reflected wave is analyzed and used for training for grasping the position and the distance to the target 1, 1 '. At this time, by combining with the spherical lens reflectors at the front and rear ends, the necessary radar reflection can be obtained from the target 1, 1 'from any direction.

Further, since the targets 1, 1 'in the present invention can be manufactured at a lower cost than those having the same reflection characteristics as conventional products, a function of detecting the reflected waves from the targets 1, 1' is provided. It can also be used for combat training in which a missile with a target is fired and the target 1, 1 'is tracked and shot down.

In the present embodiment, a self-propelled target has been described. However, it is needless to say that the present invention is not limited to a self-propelled target and can be applied to a towed target.

In the present embodiment, the target is divided into eight equal parts in the circumferential direction of the body, and the corner reflex is provided so as to face in eight different directions. However, the target is limited to eight directions. However, it is sufficient that the number of directions is eight or more.

In the above embodiment, a target mainly used for combat training has been described.
The present invention is not limited to a target, and can be used for tracking a rocket's tracks in outer space by applying it to a rocket, for example.

As described above, the invention according to the present application is provided with the corner reflex 11 that reflects radar, and in a flying object that reflects an incident radio wave by the corner reflex 11 by flying in the air, the hollow bottom portion 12 is opened. A plurality of reflector rows 15 each having a triangular pyramid-shaped corner reflex along the longitudinal direction of the flying body are provided, and the reflector rows 15 are formed in respective directions obtained by dividing the circumferential direction of the flying body into at least eight equal parts. It is a flying object arranged.

The flying object is characterized in that the corner reflex 11 is housed inside a flying body made of a material that transmits radio waves.

Further, the reflector rows 15 provided in at least eight directions are in contact with adjacent reflector rows 15 and the interior of the cylindrical body formed by the corner reflex 11 is hollow. It is.

[0056]

As described above, according to the present invention, the internal volume of the flying object itself occupied by the reflector can be reduced, and a wide empty space can be secured inside the flying object.

Further, a flying object capable of reflecting the radar in all directions can be manufactured at low cost, and the cost can be greatly reduced.

[Brief description of the drawings]

FIG. 1 (a) is a perspective view of a target of the present invention, FIG.
(B) is an enlarged perspective view of a corner reflector.

FIG. 2A is a front view of a composite reflector of the present invention, and FIG. 2B is a side view of the composite reflector.

3 (a) is a perspective view of an aluminum sheet metal, and FIG. 3 (b)
FIG. 3C is a perspective view of the aluminum sheet metal after pressing, FIG. 3C is a perspective view of the aluminum sheet metal after bending, and FIG. 3D is a perspective view showing a state where the composite reflector is housed in a cylindrical outer cylinder.

FIG. 4 is a data diagram showing a radar reflection coverage of a corner reflector;

FIG. 5 is a conceptual diagram showing a radar reflection coverage area of the composite reflector.

FIG. 6 is a cross-sectional view showing a target according to another embodiment of the present invention.

FIG. 7 is a side view showing a conventional target.

[Explanation of symbols]

 1, 1 'target 2 cylindrical outer cylinder 3 spherical lens reflector 4 composite reflector 5, 6, 7 stable wings 5a, 6a, 7a control surface 8 spherical lens reflector 9 control unit 10 Jet engine 11 ... Corner reflector 12 ... Bottom part 12a ... Side 13 ... Triangular plate 13a ... Edge 14 ... Aluminum sheet metal 15 ... Reflector row 16 ... Fuel tank 17,18 ... Wing 101 ... IR target 102 ... Cylindrical outer cylinder 103 ... Spherical Lens reflectors 104, 105: spherical lens reflector 106: fin 107: flare 108: spherical lens reflector.

Claims (3)

[Claims] 1. A flying object that includes a reflector that reflects radar and that reflects an incident radio wave by the reflector when flying in the air, the reflector having a hollow triangular pyramid shape having an open bottom surface. A flying object comprising: a plurality of reflector rows provided along a longitudinal direction of the flying body, wherein the reflector rows are arranged in respective directions obtained by dividing a circumferential direction of the flying body into at least eight equal parts. 2. The flying object according to claim 1, wherein the reflector is housed inside the flying body made of a material that transmits radio waves. 3. The reflector row provided at least in eight directions is in contact with adjacent reflector rows, and the inside of a cylindrical body formed by the reflector is hollow. 1 or Claim 2
The flying object described in.