KR101643192B1 - Missile decoy - Google Patents

Abstract

The present invention relates to a missile decoy. According to one aspect of the present invention, disclosed is a missile decoy comprising: an airframe which is launched by obtaining thrust; a decoy module which is separated from the airframe and inflated in a state that the decoy module is received in the launched airframe and has a reflector for transmitting a decoy signal by reflecting the frequency signal of an opponent missile; and a control module which controls the decoy module to allow the decoy module to be separated from the airframe and inflated. Therefore, the present invention increases the staying time in the air by adding a parachute to the missile decoy.

Description

Missile expiration {MISSILE DECOY}

The present invention relates to a missile deactivator, and more particularly, to a missile deactivator that reflects a frequency signal of a counterpart missile having an RF seeker to deceive a missile, and is equipped with a parachute to increase the time required for a missile.

A typical missile de-warp is mounted on a ship, and when an anti-ship missile fires toward a trap, it detects it and fires a missile-defeating RF signal toward the missile.

The missile recognizes the missile deception device that emits the RF signal as a trap, and attacks it toward the missile deception device. As a result, the trap can safely avoid missile attack.

The missile de-warp machine triggers the missile by slowly moving the side of the trap to deceive the missile by shooting the de-missile near the trap. The deodorizer includes a deodorizing signal sending unit, a main injection nozzle, and an auxiliary injection nozzle for sending a deodorizing signal.

At this time, the main injection nozzle is made to float in the air so as to obtain the thrust of the metering body, and the auxiliary injection nozzle performs direction adjustment and posture adjustment.

However, the missile deck requires a large manufacturing cost and requires a high-level manufacturing process and control.

To solve these problems, a passive dexterity system which reflects the RF signal of the missile to induce and deceive the missile has been developed. The passive termination types are free fall type debris type and negative type deogeum type.

Freefall-type missile deception units are deployed in the air to deceive anti-ship missiles. It falls freely at a certain height and reflects the RF signal during that time. The disadvantage is that if the wind is strong, it will be difficult to predict the time of flight.

The negative type dejae moves slowly to the side of the trap and induces the missile.

The negative degenerator is a missile deception that floats above the sea and reflects the RF signal. Although it is possible to achieve the desired purpose with an inexpensive and simple shape, if the wave height is high, the reflection area is reduced and there is no effect or the desired purpose is difficult to achieve.

Korean Patent No. 10-1420307

It is an object of the present invention to provide a missile de-warp machine to which a parachute for increasing the time of the shooting is added.

SUMMARY OF THE INVENTION It is an object of the present invention to provide a missile deactivator that is relatively inexpensive and simple to operate with logic than the existing expiration date.

The present invention is a structure for reflecting a RF signal of a missile and transmitting a malfunction signal, and can miss a missile having RF signals of various bands.

The problems of the present invention are not limited to the above-mentioned problems, and another problem that is not mentioned can be clearly understood by a person skilled in the art from the following description.

According to an aspect of the present invention, there is provided a gas sensor comprising: a gas to be fired with propulsion; a deflector module including a reflector, which is separated from the gas and accommodated in the fired gas, expanded and reflects a frequency signal of the counterpart missile, And a control module that controls the deactivation module to be separated from the gas, and to expand and deploy the missile dexter.

And a body extension module provided at an upper portion of the deodorization module and separated from the body in a state of being accommodated in the fired body and extending the body time of the deodorization module by supporting the load of the deodorization module as the body is deployed, have.

The body extension module includes a parachute portion that is separated from the base body while being accommodated in the body in a folded state and a driving portion that is coupled with the parachute portion and generates a force to deploy the parachute portion under the control of the control module .

Wherein the reflector is provided with a plurality of reflectors, and the reflector is separated from the base body in a state of being housed in the gas-tight state in a folded state, the bulb is expanded in volume and reflects a frequency signal of the counterpart missile, And an auxiliary driving unit for generating a force by which the reflector is inflated under the control of the control module.

Wherein the reflector is separated from the base body in a state of being held in a folded state and is expanded in volume and reflects a frequency signal of the counterpart missile to transmit a deception signal, wherein the deception module is mounted on the reflector, And a frame for generating an elastic force such that the volume of the reflector is expanded when separated from the gas.

The reflector is separated from the base body while being accommodated in the folded state and is expanded in volume and reflects a frequency signal of the counterpart missile to transmit a beacon signal. The beacon module surrounds the outer surface of the reflector, And a connecting line connecting the reflector and the balloon to transmit the inflation force to the reflector.

The reflector may be formed of a metal material reflecting the frequency signal of the counterpart missile.

Wherein the base includes a receiving portion for receiving the deactivated module and the body extension module, a selectively detachable head coupled to an upper portion of the receiving portion, and a booster mounted on a lower portion of the receiving portion to generate power for emitting the gas. .

The gas may further include a connecting portion connecting the receiving portion and the head portion, and selectively detonating to separate the receiving portion and the head portion.

The missile deck unit according to the embodiment of the present invention can protect the traps from a large number of threats for a long time by increasing the time of the flight through the parachute.

The missile deck according to the embodiment of the present invention can be applied to various deception techniques as the time required for the flight is increased through the parachute.

The missile dexter according to the embodiment of the present invention can be relatively simple to manufacture and can be driven with simple logic.

The effects of the present invention are not limited to the effects mentioned above, and other effects not mentioned can be clearly understood by those skilled in the art from the following description.

FIG. 1 is a view showing the inside and the outside of a missile period mat according to a first embodiment of the present invention; FIG.
FIG. 2 is a view illustrating a state in which the body extension module of the missile period shown in FIG. 1 is driven;
FIG. 3 shows the gas of the missile period shown in FIG. 1 being separated; FIG.
FIG. 4 is a diagram illustrating driving of a deactivated module of a missile-based maturity according to the first embodiment; FIG. And
FIG. 5 is a diagram illustrating driving of a missile module of a missile-based mat according to the second embodiment; FIG.
FIG. 6 is a diagram illustrating driving of a missile module of missile-based maturity according to the third embodiment; FIG. And
FIG. 7 is a view showing the correlation between the missile deactivator of FIG. 1, the counterpart missile and the battleship.

Hereinafter, embodiments of the present invention will be described in detail with reference to the accompanying drawings. It is to be understood, however, that the appended drawings illustrate the present invention in order to more easily explain the present invention, and the scope of the present invention is not limited thereto. You will know.

Furthermore, the terms used in the present invention are used only to describe specific embodiments, and are not intended to limit the present invention. The singular expressions include plural expressions unless the context clearly dictates otherwise.

In the present invention, the term "comprises" or "having ", etc. is intended to specify that there is a feature, number, step, operation, element, But do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, or combinations thereof.

1 is a front view showing the inside and the outside of the missile period according to the first embodiment of the present invention.

As shown in FIG. 1, the missile dexter according to the first embodiment of the present invention may include a deformation module 200, a base 100, a body extension module 300, and a control module 400.

The deactivator module 200 separates from the base body 100 while being accommodated in the fired body 100 and is expanded so as to reflect a frequency signal of the counterpart missile 10 and transmit a fake signal through a reflector 220 .

At this time, the counterpart missile 10 may be a component that mounts an RF seeker for sensing the battleship 20 and finds a position of the battleship 20 through an RF signal to damage the battleship.

The base 100 is inserted into a launching platform disposed in the battleship 20 and can be fired from the launching platform by obtaining propulsion through the rocket engine.

At this time, the launching platform may be a chaff launching platform mounted on a general battleship 20, but is not limited thereto.

At this time, the base body 100 may be formed of a substantially cylindrical shape elongated in the longitudinal direction, but is not limited thereto.

On the other hand, the control module 400 stores three-dimensional position information about a target position of the base 100, and the control module 400 transmits the three-dimensional position information to a remote place such as a battleship 20 or a military base .

The body 100 may also include a receiving portion 120, a head portion 140, a booster 160, and a connection portion 500.

The accommodating portion 120 can accommodate the degeneration module 200 and the body extension module 300 therein. At this time, the deformation module 200 and the body extension module 300 may be accommodated in the accommodating portion 120 in a folded or compressed state.

The head portion 140 is engaged with the upper portion of the receiving portion 120 and can be selectively separated. At this time, the width of the head part 140 is smaller than the width of the receiving part 120, so that the head part 140 can be inserted into the receiving part 120. The head 140 may also be separate from the receiving portion 120 optionally.

The booster 160 may be mounted on a lower portion of the receiving portion 120 to generate power for emitting the base 100.

The gas 100 can obtain a thrust through the high-speed jet stream which is discharged while the air that has been burned in the booster 160 is expanded.

FIG. 2 is a view illustrating a state in which the body extension module 300 of the missile period shown in FIG. 1 is driven.

2, the body extension module 300 is provided on the upper portion of the deodorization module 200 and is separated from the body 100 while being accommodated in the deployed body 100. As the deodorization module 200 is deployed, So as to extend the time required for the deformation of the deodorization module 200. At this time, the control module 400 and the body extension module 300 may be connected by a wire.

Also, as the duration of the hanging module 200 increases, the deception module 200 can protect the ship from a large number of threats for a long time, and can also use various deception techniques.

The parachute portion 320 may be deployed in the upper portion of the deformation module 200 while being separated from the base 100 in a state of being accommodated in the base 100 in a folded state.

At this time, the parachute unit 320 forms a curved surface and receives the resistance of the air to support the load of the deodorization module 200, thereby extending the deodorization time of the deodorization module 200.

The driving unit may be coupled to the parachute unit 320 to generate a force for deploying the parachute unit 320 under the control of the control module 400. At this time, the control module 400 is a component for controlling the deactivation module 200, and can separate the control module 400 from the base 100, and expand and deploy it. At this time, the deception module 200 and the control module 400 may be connected by wires.

At this time, the driving unit may be a facility including an igniter, sodium azide capsule, and iron oxide (not shown).

The driving unit is controlled by the control module 400 and can operate the igniter through the current.

The igniter can generate a flame, bursting the sodium azide capsule and reacting the sodium azide with iron oxide. At this time, sodium azide is decomposed into sodium and nitrogen, and the force of movement of the nitrogen gas generated in this process can develop into the parachute portion 320.

However, the driving unit is not limited thereto, and various driving methods for generating a force for deploying the parachute unit 320 may be provided.

Meanwhile, the control module 400 may transmit the three-dimensional position information of the base 100 and the operating status information of the parachute unit 320 and the reflector 220 to the transit box 20.

And the control module 400 may receive signals transmitted from the battleship 20. For example, the control module 400 may stop the operation of the reflector 220 or receive a signal that blows the balloon 240.

FIG. 3 is a view showing that the base body 100 of the missile period shown in FIG. 1 is separated.

2 and 3, the connection part 500 may be inserted into the hole formed by the receiving part 120 and the head part 140 to fix the head part 140 to the receiving part 120. [ At this time, the connection part 500 may be a cylindrical rod, but is not limited thereto.

When the missile deactivator arrives at a point where the counterpart missile 10 is to be deceived, the connection unit 500 is detonated and removed, and the head unit 140 can be separated from the receiving unit 120.

FIG. 4 is a diagram showing the driving of the deactivator module 200 of the missile period according to the first embodiment.

4, the ignition module 200 of the missile period according to the first embodiment is separated from the base body 100 while being accommodated in the fired body 100, It is possible to transmit the signal only by reflecting the frequency signal of FIG.

The reflector 220 of the deactivation module 200 is provided in an angular shape in a plurality of directions, so that the reflectance of the reflected RF signal can be increased.

Although not shown in the drawing, a plurality of reflectors 220 may be provided to increase the reflectance of the RF signal.

However, the number of the plurality of reflectors 220 is not limited to a specific number, and the number may vary depending on the load and the reflectance of the reflector 220.

At this time, the deception module 200 causes the counterpart missile 10 to receive the reflected deceptive signal, thereby causing the missile deactivator according to the first embodiment of the present invention to be mistaken as a target.

In this case, the missile expiration module 200 according to the first embodiment may include a reflector 220 and an auxiliary driver (not shown).

A plurality of reflectors 220 are provided in a folded state and are separated from the base body 100 in a state of being accommodated in the base body 100 and expanded in volume so as to reflect a frequency signal of the counterpart missile 10 to transmit a deception signal .

At this time, the plurality of reflectors 220 of the missile period mat according to the first embodiment are provided adjacent to each other, and the reflectors 220 can be simultaneously expanded under the control of the control module 400.

Also, the reflector 220 is made of a metal material capable of reflecting the RF signal and can be accommodated in the accommodating portion 120 in a reduced volume because it can be compressed or folded. For example, the material of the reflector 220 may be a metal coated fabric or a metallic flexible material.

In other words, the reflector 220 is formed of a thin fabric or film and is a simple structure unfolded by an elastic force, which can be more economical in manufacturing and driving than a conventional one.

The auxiliary driving unit can be mounted on the reflector 220 and generate a force that expands the reflector 220 under the control of the control module 400.

At this time, the auxiliary driving unit may generate gas inside the folded reflector 220 by generating sodium azide according to the signal of the control module 400. Accordingly, the reflector 220 may be filled with gas and swollen to expand and expand to reflect the RF signal.

For example, the auxiliary driving unit may be similar to the driving unit, and the auxiliary driving unit may be an apparatus including an igniter, sodium azide capsule, and iron oxide.

The auxiliary driving unit is controlled by the control module 400 and can operate the igniter through the current.

The igniter can generate a flame, bursting the sodium azide capsule and reacting the sodium azide with iron oxide. At this time, the sodium azide is decomposed into sodium and nitrogen, and the force of movement of the nitrogen gas generated in this process can develop the reflector 220.

FIG. 5 is a diagram showing the driving of the deactivator module 200 of the missile period according to the second embodiment.

As shown in FIG. 5, the missile-based deception module 200 according to the second embodiment of the present invention may include a reflector 220 and a frame. However, the description of the components similar to those of the first embodiment will be omitted, and the deceptive module 200, which is different from the first embodiment, will be mainly described.

The frame is a component that generates elastic force and is mounted on the inner surface of the reflector 220 and can generate an elastic force to expand the volume of the reflector 220 when the reflector 220 is separated from the base 100. [

At this time, the frame may be folded and automatically unfolded while being accommodated in the base 100 and separated from the base 100, thereby expanding the volume of the reflector 220.

That is, when the frame 100 is received in the folded state, the frame has an elastic force to be unfolded. When the base body 100 is separated, the reflector 220 mounted with the frame by the elastic force can be deployed.

At this time, since the reflector 220 of the missile period according to the second embodiment is expanded by the elastic force of the frame, a separate gas generating device may not be provided.

FIG. 6 is a diagram showing the driving of the deactivator module 200 of the missile period according to the third embodiment.

However, the description of the components similar to those of the first embodiment will be omitted, and the deceptive module 200, which is different from the first embodiment, will be mainly described.

6, the missile expiration module 200 according to the third embodiment may include a reflector 220, a balloon portion 240, and a connecting line 280.

The inflatable part 240 may have a spherical shape with an open inside and may be accommodated in an expanded state of the reflector 220 so as to surround the outer surface of the reflector 220.

The connecting line 280 connects the reflector 220 and the balloon 240 so that the balloon 240 can transmit the inflation force to the reflector 220.

At this time, the reflector 220 may be connected to the inner surface of the balloon 240 by a connection line 280, and the position of the reflector 220 may be fixed.

The connection line 280 may be disposed in the form of a wire, and may be disposed on the upper and lower sides and the left and right sides of the reflector 220 and the balloon 240, but is not limited thereto.

As shown in FIG. 6, the balloon 240 is received in a folded state inside the body 100, and a spring (not shown) having elasticity may be mounted therein.

When the base 100 is separated, the balloon 240 spreads in a spherical shape due to the elasticity of the spring, so that the connection line 280 connecting the balloon 240 and the reflector 220 is pulled, Can be unfolded.

That is, the missile deaerator according to the third embodiment is not provided with a separate gas generating device since it is deployed by the elastic force of the spring.

The configuration of the balloon 240 and the connection line 280 may be applied to the first embodiment and the second embodiment. That is, the balloon 240 and the connection line 280 may be externally provided to the reflector 220 of the first and second embodiments to apply a pulling force to the reflector 220 so that the reflector 220 is unfolded . As shown in FIG. 1, the control module 400 may separate and expand and deploy the deception module 200 and the body extension module 300 from the base 100.

The control module 400 can perform a weighting function to control the falling speed of the module 200 with proper weight.

At this time, the control module 400 can be operated by the user's wireless communication through a preset program.

7 is a diagram showing the correlation between the missile deactivator of FIG. 1, the counterpart missile 10, and the carrier 20. FIG.

As shown in FIG. 7, the process of protecting the ship 20 from the missile-based counterpart missile 10 of the present invention is as follows.

The other party's missile 10 is fired to destroy the battleship 20. At the front end of the counterpart missile 10, there is a small RF radar, which searches for and finds the carrier 20 and rushes in the direction of the carrier 20.

The radar of the battleship (20) detects that the missile is flying through its own radar. The battleship 20 launches the missile dexter of the present invention to deceive the missile.

The missile de-warp unit is launched in a predetermined direction and height from the battleship 20 by a pre-input program, and the parachute is spread and free-falled. The deceptive module 200 of the present invention reflects the RF frequency emitted by the counterpart missile 10, thereby causing the missile deck to be mistaken for a trap.

The other party's missile 10 is reflected by the deactivator module 200 and flies toward the direction of the returning radio wave. The trap escapes along the safe path between them and escapes the attack of the other missile (10).

It will be apparent to those skilled in the art that the present invention may be embodied in other specific forms without departing from the spirit or scope of the invention as defined in the appended claims. . Therefore, the above-described embodiments are to be considered as illustrative rather than restrictive, and the present invention is not limited to the above description, but may be modified within the scope of the appended claims and equivalents thereof.

10: Other missile
20: Battleships
100: gas
120:
140: Head
160: Booster
200: Deception module
220: Reflector
240: balloon
280: Connecting cable
300: extension module
320:
400: control module
500: Connection

Claims (9)

A gas launched with propulsion;
A reflector for separating and expanding from the gas in the state of being accommodated in the fired body and reflecting a frequency signal of the counterpart missile to send a fake signal and an auxiliary driving unit mounted on the reflector for generating a force for expanding the reflector Deception module;
A control module for controlling the deactivation module to be separated from the gas, and to be expanded and deployed; And
And a driving unit coupled to the parachute unit and generating a force for deploying the parachute unit under the control of the control module, wherein the parachute unit comprises: A body extension module for supporting a load of the deodorization module and extending the deodorization time of the deodorization module according to the extension; / RTI >
The driving unit includes an igniter, a sodium azide capsule, and iron oxide. The igniter generates a flame by the control module, reacts the sodium azide with the iron oxide to generate nitrogen gas, Wherein the missile-based maturity is determined based on at least one of: delete delete The method according to claim 1,
Wherein the reflector is provided in a plurality of the reflectors and is separated from the base body in a state of being held in a folded state, expanded in volume, and reflects a frequency signal of the counterpart missile to transmit a deception signal. delete The method according to claim 1,
Wherein the reflector is separated from the base body while being accommodated in the folded state and expanded in volume, reflects a frequency signal of the counterpart missile,
A balloon unit which surrounds the outer surface of the reflector and is made of a material through which a frequency signal of a counterpart missile is transmitted; And
A connecting line connecting the reflector and the balloon to transmit the inflation force to the reflector;
Missile period maturity, including. 7. The method according to any one of claims 4 to 6,
Wherein the reflector is made of a metal material reflecting the frequency signal of the counterpart missile. The method according to claim 1,
The gas,
A receiving portion for receiving the deactivation module and the body extension module;
A selectively removable head coupled to an upper portion of the receiving portion; And
A booster mounted on a lower portion of the receiving portion to generate power for emitting the gas;
Missile expiration including. 9. The method of claim 8,
The gas,
Further comprising a connecting portion connecting the receiving portion and the head portion and selectively detonating to separate the receiving portion and the head portion.

Images