JPH09264700A - Warhead of airframe - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a warhead, use of only one of which does not provide an excessive destroying capacity but provide a destroying capacity necessary and enough for a plurality of types of targets having different characteristics. SOLUTION: In an antiaircraft airframe, a warhead 1 of an airframe 8 comprises fragments 2 of a shell, a bursting charge 3, priming points 4a, 4b, 4c and a fuse 5, and the warhead 1 is provided with the fragments 2 of the shell an interior of which is packed with the bursting charge 3. In this structure, a plurality of priming points 4 are provided in a frame axis direction of the airframe 8 and the fuse 5 has an ignition outputting section 6 and a calculating section 7, which performs selection of the priming points 4 and calculation of priming times for the respective priming points on the basis of information about targets inputted from outside. Result of the calculation is outputted to the ignition outputting section 6 and the maximum energy of the fragments 2 of the shell and expansion of energy in the frame axis direction of the airframe are adjusted according to fragility of the target to form the most appropriate energy distribution of the fragments 2.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a warhead of an anti-aircraft missile capable of coping with (destroying) from an aircraft to a warhead of a projectile (hereinafter also referred to as a missile). INDUSTRIAL APPLICABILITY The present invention can be applied to general warheads of anti-aircraft missiles.

[0002]

[Prior art]

(A) In a conventional projectile warhead, as shown in FIG. 3, a large number of projectiles are arranged around a cylinder, and an explosive charge is filled inside the projectile to set an initiation point at the center of the projectile in the machine axis direction. Set up. Then, an ignition signal transmitted from the fuze is used to detonate the detonation point, thereby forming a uniform fragment energy distribution in a wide range. (B) In a conventional directional warhead of a projectile, as shown in FIG. 4, a bullet piece is arranged around a cylinder and an explosive charge is filled inside thereof, but four initiation points are provided in four quadrants around the explosive charge ( 4e, 4f,
4g, 4h).

Then, the seeker or the proximity fuze detects the passing direction of the target, and based on the information, the fuze 5 outputs an ignition signal to the initiation point in the opposite direction to the passing of the target.

In this case, the bullet 2 scatters in a direction orthogonal to the machine axis of the projectile with a certain scattering angle, and within this range, a substantially uniform energy distribution is obtained. Fig. 4 shows the third detonation point 4
When g is detonated, a large warhead energy distribution is formed only in the passing direction of the target.

[0005]

[Problems to be Solved by the Invention]

(A) In the case of attempting to destroy by the conventional warhead of a flying object, a flying object warhead (hereinafter, referred to as a robust target) compared to a case where the target object is an aircraft (hereinafter also referred to as an aircraft target) In order to deal with a warhead (also referred to as a projectile warhead target), the mass of the projectile 2 and the amount of explosive charge must be increased as compared with a warhead intended only for an aircraft target. (B) On the other hand, it is not necessary to increase the energy of the projectile 2 in order to deal with a normal aircraft target that is large in size and weak in vulnerability, and it is better to scatter the projectile 2 in a wider range because of its destructive performance. Good. (C) As described above, it is extremely difficult to keep a warhead capable of dealing with a plurality of types of targets having different characteristics in a limited space and a limited required mass of a projectile while ensuring the defeating performance. is there. (D) In the conventional directional warhead of a flying object, in order to direct the energy of the warhead to the target, it is necessary to know the direction in which the target passes, but the accuracy is not sufficient. is there. An object of the present invention is to provide a warhead of a flying vehicle that can solve these problems.

[0006]

[Means for Solving the Problems]

(First Means) A warhead of a flying object according to the present invention is a warhead of an anti-aircraft flying object which copes with a target such as an aircraft or a flying object of a flying object. ,
(B) The warhead fills the inside of the bullet with explosive charge and has a plurality of initiation points in the axial direction of the projectile. (C) The fuze has an ignition output. Department,
(D) The computer unit has a computer unit, selects the detonation point and calculates the detonation time of each detonation point based on the information about the target input from the outside, and outputs the calculation result to the ignition output unit. (E) The ignition output unit outputs an ignition signal to the initiation point, and (F) adjusts the maximum energy of the projectile and the energy spread in the axial direction of the projectile according to the vulnerability of the target. To form an optimum energy distribution of bullets.

Therefore, it operates as follows. (1) The maximum energy of the projectile 2 and the energy distribution in the axial direction of the projectile are selected by appropriately selecting the detonation point of the projectile 2 and calculating the detonation time of each detonation point according to the vulnerability of the target. Can be adjusted. Therefore, it is possible to set the optimum energy distribution of the bullet 2 that can obtain the required destruction performance for each target. (2) Further, a uniform energy distribution can be formed around the warhead 2.

[0008]

BEST MODE FOR CARRYING OUT THE INVENTION

(First Embodiment) FIG. 1 shows a first embodiment of the present invention.
2 to FIG. FIG. 1 is a schematic diagram of a warhead of a projectile according to a first embodiment of the present invention, and FIG. 2 is an energy distribution diagram of a warhead of a projectile according to the first embodiment of the present invention.

As shown in FIG. 1, in a warhead 1 which is installed in a substantially central portion of a projectile 8, bullets 2 are arranged around a cylinder, and an explosive charge 3 is filled in the inside of the projectile 2, so that A plurality of boosters (three in the center 4b, the frontmost 4a, and the rearmost 4c in FIG. 1) are provided in the direction.

Then, one-point detonation at the central detonation point 4b,
Detonation points at both ends (frontmost detonation point 4a, rearmost detonation point 4c)
Simultaneous detonation is used properly according to the goal. The bullet 2 has a cubic shape with one side of 5 mm to several tens of mm, and is fixed around the housing in which the explosive 3 is loaded with an epoxy adhesive, and the outside of the bullet 2 is attached to the outer cylinder of the projectile. It is covered with a corresponding housing.

Each initiation point is separately initiated by the ignition signal from the ignition output section 6 of the fuze 5 to rupture the warhead. The fuze 5 obtains information about the target (type of target and approach speed) from an external device in the computer unit 7,
The starting point is selected, and the starting time of each starting point is calculated individually and transmitted to the ignition output unit 6.

FIG. 2 shows an example of operating the warhead according to the first embodiment (FIG. 1). (A) When the target type is not so hard as in an aircraft, only the central detonation point 4b is detonated as shown in FIG. 2 (a).

At this time, the energy distribution of the bullet 2 is evenly distributed over a wide range. (B) On the other hand, when the target type is extremely hard, such as a projectile warhead, as shown in FIG.
And the rear detonation point 4c is detonated at the same time.

At this time, as shown in FIG. 2 (b), the energy is concentrated only near the center of the scattering range of the bullets.
The target defeat ability is improved compared to the case of (a). (C) When the target type is intermediate between the aircraft and the warhead, as shown in FIG. 2 (c), the starting points of the forward starting point 4a and the rear starting point 4c are shifted in time to start the detonation.

FIG. 2 (c) shows an example in which the front detonation point 4a is detonated slightly earlier than the rear detonation point 4c. At this time, the maximum energy of the bullet 2 is slightly lowered, but the high energy range is slightly widened. (D) In this way, by adjusting the maximum energy of the projectile 2 and the energy spread in the axial direction of the projectile according to the target fragility, the optimum projectile capable of obtaining the required defeating performance. An energy distribution of 2 can be formed. (E) Therefore, by varying the scattering range of the bullet 2 in accordance with the type of target, one warhead is provided for each of a plurality of types of targets having different characteristics, and destroying performance is secured and weight reduction is achieved. Both objectives of can be realized.

[0016]

Since the present invention is constructed as described above, it has the following effects. (1) With a single warhead, it is possible to provide a warhead that does not have an excessive destruction performance but has a necessary and sufficient destruction performance for each of a plurality of types of targets having different characteristics. (2) Therefore, the mass and size of the warhead can be reduced. (3) Further, since the energy is evenly distributed around the warhead, it is possible to eliminate the need to grasp the quadrant through which the target passes.

[Brief description of drawings]

FIG. 1 is a schematic view of a warhead of a flying object according to a first embodiment of the present invention.

FIG. 2 is an energy distribution diagram of a warhead of a flying object according to the first embodiment of the present invention.

FIG. 3 is a conventional warhead warhead energy distribution diagram.

FIG. 4 is an outline of a conventional directional warhead of a flying vehicle and an energy distribution diagram of the warhead.

[Explanation of symbols]

 1 ... warhead 2 ... bullet 3 ... explosive charge 4 ... detonation point 4a ... forward detonation point 4b ... central detonation point 4c ... rear detonation point 4e ... first detonation point 4f ... second detonation point 4g ... third detonation point 4h ... third point 4 Detonation point 5 ... Fuze 6 ... Ignition output section 7 ... Computer section 8 ... Flying body

Claims (1)

[Claims] 1. A warhead of an anti-aircraft flying vehicle for coping with a target such as a warhead of an aircraft or a flying vehicle. (A) The warhead (1) of the flying vehicle (8) comprises a piece (29) and an explosive charge (3). It consists of the detonation point (4) and the fuze (5). (B) The warhead (1) fills the inside of the bullet (2) with the explosive charge (3) and moves in the axial direction of the projectile (8). (C) The fuze (5) has an ignition output section (6) and a computer section (7), and (D) the computer section (7) is external. Based on the information about the target input from, the starting point (4) is selected and the starting time of each starting point is calculated, and the calculation result is output to the ignition output section (6), and (E) the ignition output section. (6) outputs an ignition signal to the detonation point (4), and (F) the maximum energy of the projectile (2) and the aircraft of the projectile according to the vulnerability of the target. A warhead of a projectile characterized by forming an optimum energy distribution of a bullet (2) by adjusting the spread of energy in the axial direction.