JPH08193797A - Guided flight - Google Patents

Abstract

(57) [Summary] [Purpose] A flying object that is effective for high-speed targets. [Structure] A first warhead was provided on the front side of the propulsion device for the flying vehicle, and a second warhead was provided behind the propulsion device.

Description

Detailed Description of the Invention

[0001]

FIELD OF THE INVENTION The present invention relates to a guided vehicle.

[0002]

2. Description of the Related Art First, the structure of a conventional guide vehicle will be described with reference to FIG. In FIG. 3, M is a guided flying object, 1 is a seeker part of the flying object, 2 is a guidance control part, and 3 is an antenna for a proximity fuze, which is located in front of a proximity fuze and an incoming and outgoing tube which will be described later. ing. Reference numeral 4 is a proximity fuze, 5 is an incoming and outgoing tube, 6 is a detonation signal generating circuit, 7 is a warhead, and 8 is a propulsion device.

Next, the manner in which the flying object constructed as described above tracks the target and approaches the target will be described with reference to FIG. 4, 3 to 7 and M are the same as in FIG. It is assumed that T is a flying target of the flying body M and moves in the direction of arrow a in FIG. 4, and the flying body M moves in the direction of arrow B so as to associate with the target T. Suppose you fly towards.

A flying body M flying toward the target T approaches and approaches and tracks the target T by active or passive homing. When the flying body M approaches the target T and the target T reaches the position of point a (hereinafter referred to as the target position), the position of the point a on the proximity fuze antenna 3 at the point a ′ (hereinafter referred to as the target detection position). The target T at is detected. When the target T is detected, a proximity passing signal is sent to the proximity fuze 4, and the detonation pulse generated by the proximity fuze 4 which has received the above-mentioned signal causes the detonation signal generation circuit 6 to generate an detonation signal to detonate the warhead 7. While generating the detonation signal, the flying vehicle M has moved to the b'point (hereinafter referred to as the warhead detonation position), and the warhead 7 detonates at the b'point. Further, the target T moves to the point b (hereinafter referred to as a bullet collision position) while the above-mentioned detonation signal is generated.

As described above, the target T and the flying body M pass each other, and the point b at which the projectile collides and the point b ′ at the point at which the warhead starts are close to each other, and the target T is destroyed. Also, the target T
In the case of a direct hit, the detonation signal is generated by the detonation signal generation circuit 6 by the detonation pulse generated from the landing and emission tube 5, and the warp initiation position b'point (in this case, b'point is the same position as the warhead initiation position b point). Naru) detonates the warhead 7 and destroys the target T.

[0006]

Since the conventional guided vehicle M is constructed as described above and operated as shown in FIG. 4, when the target is a high-speed missile or the like, The speed also increases, and even if they pass each other, they cannot effectively destroy the target as before.

Here, in such a case, a, b, a ',
The correlation of b'will be described with reference to FIG. FIG. 5 is a diagram showing a state in which a conventional guided vehicle approaches or destroys a target having a high relative speed. When the flying body M approaches the target T, the target is detected by the proximity fuze antenna 3 as described above, and the detonation signal is generated by the detonation pulse generated from the proximity fuze 4 by sending the proximity passing signal to the proximity fuze 4. While generating the detonation signal in the generation circuit 6 and detonating the warhead 7, the projectile M collides from the target detection position a ′ to the warp detonation position b ′, and the target T collides from the target position a as shown in FIG. Move to position b. At this time, when the relative velocity is high, the target position is considerably deviated if the projectile is considered to be fixed, and the distance between the target position a and the bullet collision position b becomes long, that is, the warhead 7 (warhead initiation position b ′) And bullet collision position b
There was a problem that the target could not be destroyed effectively because the distance between and became long.

The present invention has been made to solve the above problems, and by providing a warhead behind the propulsion device, the target and the flying object such as when the target is a high-speed missile. The objective is to improve the target destruction ability when the relative speed to and is large.

[0009]

The guiding projectile according to the present invention is also provided with a warhead behind the propulsion device, thereby shortening the distance between the warhead and the bullet collision position.
Even when the relative speed between the flying object and the target is large, it is possible to effectively destroy the target.

[0010]

The guide vehicle according to the present invention is provided with a warhead behind the propulsion device so that the target is effectively destroyed even when the relative speed between the projectile and the target is large.

[0011]

【Example】

Example 1. An embodiment of the present invention will be described below. FIG. 1 is a diagram showing an embodiment of the present invention, and FIG. 2 is a diagram showing a state in which the guided flying object of FIG. 1 approaches or destroys a target having a large relative speed. Flying body seeker section, 2 guidance control section, 3 proximity fuze antenna, 4 proximity fuze, 5 arrival and departure tube, 6 detonation signal generation circuit, 7 first warhead, 8 propulsion device, 9 Is a second warhead, which is a feature of the present invention, and is mounted behind the propulsion device 8. T is a target, a is a target position, a'is a target detection position, b is a bullet collision position, and b'and b "are warhead detonation positions.

Next, the operation of the flying object in the present invention will be described. In FIG. 2, the guide vehicle M flying toward the target T captures and tracks the target T by active or passive homing guidance and approaches. When approaching the target T, the proximity fuze antenna 3 detects this and sends a proximity passing signal to the proximity fuze 4 to generate a detonation pulse from the proximity fuze 4, and when the target T is hit directly, An initiation signal is generated by the initiation signal generation circuit 6 by the initiation pulse generated from 5, and the first and second warheads 7 and 9 are initiated. At this time, by adjusting the detonation timing of the first and second warheads 7 and 9, if the relative speed between the flying vehicle M and the target T is not so large, the first warhead 7 (warhead detonation position b ') is the second when the target T is a high-speed missile or the like and the relative speed is large.
The target T is destroyed by effectively operating the warhead 9 (warhead initiation position b ″).

[0013]

As described above, according to the present invention, the first
In addition to the warhead, the second warhead was placed behind the propulsion device for the guided projectile, so when the relative velocity between the projectile and the target is high, the target position a collides with the projectile. When the distance to the position b becomes long, the distance between the first warhead (warhead detonation position b ′) and the bullet collision position b becomes long, but the second warhead (warhead detonation position b ″) and the bullet piece Collision position b
Since the distance to and does not become long, it has the effect of effectively destroying the target. Also, since each warhead can be made effective for the target, it has an effect of improving the target defeat ability. In addition, it is possible to deal with the case where the relative velocity between the flying body and the target is not so large or large with one guided flying body. Furthermore, the variation of the center of gravity is less than before, and flight stability is improved.

[Brief description of drawings]

FIG. 1 is a diagram showing a configuration of a guide vehicle in Embodiment 1 of the present invention.

FIG. 2 is a diagram showing a manner in which the guided vehicle approaches and destroys a target having a high relative speed according to the first embodiment of the present invention.

FIG. 3 is a diagram showing a configuration of a conventional guide vehicle.

FIG. 4 is a diagram showing a state in which a conventional guided vehicle follows and approaches a target.

FIG. 5 is a diagram showing a state in which a conventional guided vehicle approaches or destroys a target having a high relative speed.

[Explanation of symbols]

1 flying body seeker section, 2 induction control section, 3 proximity fuze antenna, 4 proximity fuze, 5 landing transmitter tube, 6 detonation signal generating circuit, 7 first warhead, 8 propulsion device, 9 second warhead, a Target position (target position) at the time of target detection, b
Bullet collision position, target detection position of a'guide projectile (target detection position), b'warhead initiation position, b "warhead initiation position, M projectile, T target.

Claims (1)

[Claims] 1. A guided projectile having a warhead on the front side of the propulsion device, characterized in that a warhead is also provided on the rear side of the propulsion device.