JP6927633B2 - Guided rockets and how to control them - Google Patents

Description

The present invention relates to a guided rocket for attacking a ship and a control method thereof.

Conventionally, missiles (anti-ship missiles) have been mainly used when attacking ships on the sea from the ground. The missile is equipped with a seeker for searching, finding, and identifying the target, and a guidance device for tracking and guiding the target. Therefore, missiles are very expensive.

On the other hand, it has been proposed to perform terminal guidance using rockets that are cheaper than missiles and have the same flight distance (for example, Patent Document 1).

The "flying object control device" of Patent Document 1 uses a time controller to change the update and transmission interval of the UTDC (up-to-date command) according to the target speed and turning G, and transmits the missile. , The control unit of the radio wave seeker is deleted.

Japanese Unexamined Patent Publication No. 2001-183092

Originally, rockets take the form of attacking from the top of the target. This is because (1) the rocket flies ballistically and flies to the upper surface of the target, (2) the upper surface of the target is generally fragile, and (3) the warhead power determines the terminal velocity energy of the rocket. This is due to the fact that it is used and (4) the range of scattered fragments of the warhead is axisymmetric (circular).

In this case, in order to attack the target from above and damage the ship, it is necessary to improve the impact accuracy so that the target is within the effective range of the warhead.
However, in order to attack a moving target like a ship, it is necessary to set the target position in real time. In order to realize this, it is necessary to take on the function of target detection in an aircraft or the like and replace the seeker. At this time, rockets and aircraft require close cooperation and communication in terms of operation, but if close cooperation cannot be obtained due to the countermeasures of the ship and the operating environment, it will be difficult to obtain the desired effect.

Further, even when the means of Patent Document 1 is applied, the impact accuracy is lowered due to the accumulation of the target speed and the error of the turning G.

The present invention has been devised to solve the above-mentioned problems. That is, an object of the present invention is to provide a guided rocket bullet capable of damaging a ship and a control method thereof even when the impact accuracy is low.

According to the present invention, it is a guided rocket provided with a warhead in which fragments spread in a horizontal direction due to a blast, a rocket motor that generates propulsive force, a steering wing that steers the propulsive direction, and a control device. ,
The warhead has a shell constituting the outer surface of the warhead, a plurality of molded debris bullets filled inside the shell, and an explosive charge located inside the molded debris bullet.
The molded debris bullet has a high loading density in the horizontal direction and a relatively low loading density other than the horizontal direction.
The control device provides a guided rocket that controls the steering wing so that the guided rocket flies at a low altitude corresponding to the target ship's radar height.

Further, according to the present invention, it is the above-mentioned method for controlling a guided rocket.
The control device provides a method for controlling a guided rocket that controls the steering wing so that the guided rocket flies at a low altitude corresponding to the target ship's radar height.

According to the present invention, since the debris has a warhead that spreads in the horizontal direction due to the blast, even if the impact accuracy is low, the molded debris bullet in the warhead can be landed in a wide range in the horizontal direction. Can be done.

In addition, in terminal guidance, the control device controls the steering wing so that the guided rocket flies at a low altitude equivalent to the target ship's radar height, so there is a high probability that the ship will fly with molded debris in the warhead. Can damage the radar.

The elements of electronic warfare are increasing in recent combat, and for ships, even damaging the radar can significantly reduce the combat capability of the ship, and a relatively high effect can be expected.
Therefore, according to the present invention, even if the landing accuracy of the guided rocket is low, it is possible to cause a large amount of damage to the ship with a high probability.

It is an embodiment diagram of the guided rocket according to the present invention. It is explanatory drawing of the control method of the guided rocket according to this invention. It is a flight profile diagram of a guided rocket. It is a figure which shows the positional relationship between the target at the time of the warhead detonation and the guided rocket. It is a 1st embodiment diagram of a warhead. It is a 2nd Embodiment diagram of the warhead. It is a 3rd embodiment diagram of a warhead.

Hereinafter, embodiments of the present invention will be described in detail with reference to the accompanying drawings. In addition, the same reference numerals are given to common parts in each figure, and duplicate description is omitted.

FIG. 1 is an embodiment diagram of a guided rocket 10 according to the present invention.
In FIG. 1A, the guided rocket 10 includes an airframe 11, a warhead 12, a rocket motor 14, a steering wing 16, and a control device 18.

The airframe 11 is an airframe of the guided rocket 10.
In this example, the warhead 12 is provided at the tip end portion (left end portion in the figure) of the airframe 11, and as shown in FIG. 1 (B), the debris is spread in the horizontal direction by the horizontally oriented blast. It has become. The details of the warhead 12 will be described later.
In this case, the fragment scattering range 1 is within an ellipse that is long in the horizontal direction and short in the vertical direction.

The rocket motor 14 is housed in the rear portion (right end portion in the figure) of the airframe 11, generates propulsive force, and flies the airframe 11. The rocket motor 14 is preferably a solid propellant rocket.

In this example, the steering wing 16 is composed of a horizontal wing and a vertical wing provided at the rear end of the airframe 11, and steers the propulsion direction. The horizontal and vertical wings should be variable wings.
In this example, the steering wing 16 is provided at the rear end portion of the airframe 11, but the position of the steering wing 16 is not limited to the rear end portion and may be any other position.

The control device 18 controls the steering wing 16 so that the guided rocket 10 flies at a low altitude corresponding to the target radar height of the ship 2 in the terminal guidance. Hereinafter, unless necessary, the target ship 2 is referred to as "target ship 2" or simply "target 2".
The position of the target 2 is given by the latitude and longitude, and the approach to the target 2 is determined by the self-position measured by the mounted GPS.
For example, the "radar height of ship 2" is known in advance as to what kind of ship it is, and the approximate height of the radar is also known, so it is better to input it to the control device 18. ..
Further, the control device 18 prevents the guided rocket 10 from rolling (rotation around the axis) in the terminal guidance, determines that it has approached the target 2, and detonates the warhead 12.
Terminal guidance means guidance at the target hit stage. The present invention is not limited to terminal guidance, and it is preferable to use other guidance methods (for example, intermediate guidance methods) in combination.

FIG. 2 is an explanatory diagram of a control method for the guided rocket 10 according to the present invention.
In this figure, 2 is a target ship, and 3 is an aircraft that measures a target position and transmits it to a guided rocket 10.
The guided rocket 10 of the present invention flies in the path of ABCD in the figure.
The guided rocket 10 fires at target 2 from land or another ship at A and then receives the target position at B. Next, in C, gliding by wing steering and low-altitude flight are performed, and in D, the warhead 12 is detonated.

In this example, the terminal guidance is from the reception of the target position (B) to the detonation of the warhead 12 (D), during which the target position is transmitted from the aircraft 3 to the guided rocket 10.
The transmission from the aircraft 3 is preferably by the well-known UTDC (up-to-date command) guidance.
Further, UTDC guidance is not essential, and a route may be stored in advance in the control device 18 so as to autonomously fly along this route.

As shown in this figure, in the control method of the present invention, in the terminal guidance, the steering wing 16 is operated by the control device 18 so that the guided rocket 10 flies at a low altitude corresponding to the target radar height of the ship 2. To control.

FIG. 3 is a flight profile diagram of the guided rocket 10.
In this figure, (A) shows the relationship between the range and altitude, (B) shows the relationship between time and velocity, and (C) shows the relationship between time and attitude angle.

In FIG. 3A, the altitude of the guided rocket 10 is the same as that of the conventional rocket, and after reaching the upper surface of the target 2, the control device 18 controls the radar of the ship 2 as the target 2. It is controlled to fly at a low altitude corresponding to the height.
In FIG. 3B, the flying speed of the guided rocket 10 is, after launching (A), burning in a short time like a normal rocket of the rocket motor 14, accelerating at once and trajectorying halfway. Let's fly. Next, in the final stage (at the time of terminal guidance), lift is gradually generated by the steering wing, and the altitude is gradually lowered so as to try to glide and the speed does not decrease, and the altitude is approached to the target altitude.
In FIG. 3C, the attitude angle of the guided rocket 10 is set at a high angle at the time of launch (A), and gradually changes from horizontal to downward at the time of ballistic flight. Next, in the terminal guidance, the steering wing 16 is controlled so as to finally fly at a low altitude corresponding to the radar height of the target ship 2, so that the attitude angle is controlled slightly downward from the horizontal when the target is reached. ..

FIG. 4 is a diagram showing the positional relationship between the target 2 and the guided rocket 10 at the time of detonating the warhead.
In this figure, (A) is a top view and (B) is a side view.

The control device 18 prevents the guided rocket 10 from rolling, determines that it has approached the target 2, and detonates the warhead 12.
That is, the guided rocket 10 is prevented from rolling, and the warhead 12 is detonated by adjusting the direction (angle) of the warhead 12 to a position where the fragments spread in the horizontal direction.
Therefore, in FIG. 4A, the fragment scattering range 1 is within a long ellipse in the horizontal direction, and even when the impact accuracy is low, the molded fragment bullets in the warhead can be landed on a wide range of the target ship 2. ..

On the other hand, in FIG. 4B, the fragment scattering range 1 is within a short ellipse in the vertical direction. However, in the terminal guidance, since the steering wing 16 is controlled so as to fly at a low altitude corresponding to the radar height of the target ship 2, there is a high probability that the radar of the target ship 2 will be damaged by the molded debris bullets in the warhead. Can be done.

FIG. 5 is a first embodiment view of the warhead 12. This figure corresponds to the CC cross-sectional view of FIG. 1 (A), and the left-right direction is the horizontal direction. In this figure, (A) is before the detonation and (B) is at the time of detonation.

As shown in FIG. 5A, the warhead 12 is formed inside the shell 12a forming the outer surface of the warhead 12, a plurality of molded debris bullets 12b filled inside the shell 12a, and the inside of the molded debris 12b. It has an explosive charge 12c, which is located. A detonation point 12d is provided inside (preferably at the center) of the explosive charge 12c.

The shell 12a is preferably made of metal (for example, made of high tensile strength alloy steel or titanium alloy), and in this example, has a cylindrical shape or a conical shape centered on the axis of the body 11.

The molded debris bullet 12b is a large number of steel balls, steel pieces, tungsten pellets, and the like. The molded debris bullet 12b preferably has a destructive force that, when colliding with the target 2 at high speed, can break through the non-metal cover covering the radar of the target ship 2 and damage the internal radar.
This destructive force does not have to be large enough to damage the hull itself of the target ship 2.

The explosive charge 12c is a high-performance explosive, and when the detonation point 12d is detonated, a blast wave 13 is generated, and the molded debris bullet 12b is scattered outward at high speed in the radial direction.

In FIG. 5A, the molded debris bullet 12b has a high loading density in the horizontal direction and a relatively low loading density other than in the horizontal direction.
That is, in this example, the explosive charge 12c has an elliptical shape having a short horizontal cross section and a long vertical cross section, and is filled with more molded debris bullets 12b in the horizontal direction than in the vertical direction.

With this configuration, as shown in FIG. 5B, the detonation at the detonation point 12d generates a blast 13 by the explosive charge 12c, and the horizontally oriented blast 13 causes the molded debris 12b together with the debris of the shell 12a. It can be directed horizontally and scattered.

FIG. 6 is a second embodiment view of the warhead 12. In this figure, as in FIG. 5, the left-right direction is the horizontal direction, (A) is before detonation, and (B) is at the time of detonation.

In FIG. 6A, the molded debris bullet 12b has a high loading density in the horizontal direction and a relatively low loading density other than in the horizontal direction.
That is, in this example, the explosive charge 12c has a circular cross-sectional shape, but the explosive charge 12c is located eccentrically upward with respect to the shell 12a, and more molded debris bullets 12b are located below and to the left and right of the shell 12a. Is filled.
Other configurations are the same as in FIG.

With this configuration, as shown in FIG. 6B, the detonation at the detonation point 12d generates a blast 13 by the explosive charge 12c, and the horizontally oriented blast 13 causes the molded debris 12b together with the debris of the shell 12a. It can be directed horizontally and scattered.

FIG. 7 is a third embodiment view of the warhead 12. In this figure as well, as in FIG. 5, the left-right direction is the horizontal direction, (A) is before detonation, and (B) is at the time of detonation.
In this example, the explosive charge 12c has a directivity that causes a detonation in the horizontal direction and gives the molded debris bullet 12b an initial velocity.
Other configurations are the same as in FIG.

With this configuration, as shown in FIG. 7B, the detonation at the detonation point 12d generates a blast 13 by the explosive charge 12c, and the horizontally oriented blast 13 causes the molded debris 12b together with the debris of the shell 12a. It can be directed horizontally and scattered.

According to the above-described embodiment of the present invention, since the warhead 12 has a warhead 12 in which debris spreads in the horizontal direction due to the blast 13 directed in the horizontal direction, a wide range in the horizontal direction is wide even when the impact accuracy is low. The molded debris bullet 12b in the warhead can be landed on.

Further, in the terminal guidance, the control device 18 controls the steering wing 16 so that the guided rocket 10 flies at a low altitude corresponding to the radar height of the target ship 2, so that there is a high probability that the molded debris bullet in the warhead will fly. 12b can damage the radar of target ship 2.

The elements of electronic warfare are increasing in recent combat, and for ships, even damaging the radar can significantly reduce the combat capability of the ship, and a relatively high effect can be expected.
Therefore, according to the present invention, even if the landing accuracy of the guided rocket 10 is low, it is possible to give a large damage to the ship with a high probability.

It should be noted that the present invention is not limited to the above-described embodiment, and it goes without saying that various modifications can be made without departing from the gist of the present invention.

1 Debris scattering range, 2 Targets (target ships), 3 Aircraft, 10 Guided rockets,
11 Airframes, 12 Warheads, 12a Shells, 12b Molded Fragment Bullets, 12c Explosives,
12d detonation point, 13 blast, 14 rocket motor, 16 steering wing,
18 Control device

Claims (4)

A guided rocket equipped with a warhead in which fragments spread in the horizontal direction due to a blast, a rocket motor that generates propulsive force, a steering wing that steers the propulsive direction, and a control device.
The warhead has a shell constituting the outer surface of the warhead, a plurality of molded debris bullets filled inside the shell, and an explosive charge located inside the molded debris bullet.
The molded debris bullet has a high loading density in the horizontal direction and a relatively low loading density other than the horizontal direction.
The control device is a guided rocket that controls the steering wing so that the guided rocket flies at a low altitude corresponding to the target ship's radar height. The guided rocket according to claim 1, wherein the control device prevents the guided rocket from rolling, determines that the target has been approached, and detonates the warhead. The guided rocket according to claim 1, wherein the explosive charge has a directivity of generating a detonation in the horizontal direction and giving an initial velocity to the molded debris bullet. The method for controlling a guided rocket according to claim 1.
A method for controlling a guided rocket, in which the control device controls the steering wing so that the guided rocket flies at a low altitude corresponding to the radar height of a target ship.

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