JPH06213599A - Broken piece discharging device of missile - Google Patents

Abstract

PURPOSE:To enable a target coinciding probability to be improved by a method wherein some broken pieces are dispersed under explosion of explosive and in the case that a target is broken, a group of a plurality of broken pieces are arranged in an aft-and-fro direction in a plurality of blocks, and each of the blocks is discharged with a time difference. CONSTITUTION:First to fourth independent blocks are arranged along a fore and aft direction of a missile while a plurality of broken pieces 2 are being applied as a unit block within an outer cylinder case 1. Each of them is arranged separate from the explosive 3 for every blocks. Each of the explosives 3 is set such that their communications are shut/released by a safe releasing mechanism including a sliding plate and a safety pin against a discharging electrical detonator 5. The safe releasing mechanism and the electrical detonator 5 are controlled by a micro-processor 18 in its electrical energization. This micro-processor 18 calculates a relative position where the target and the released broken pieces 2 are coincided to each other and outputs a releasing command for discharging the broken pieces 2 with a time difference at the time when the most much amount of broken pieces 2 strike against the target in response to a result of calculation.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a debris ejecting device for a flying object that expels and disperses debris to the surrounding area to destroy a target object.

[0002]

2. Description of the Related Art A debris ejecting device for a flying object aims to destroy the target object by penetrating into the target object by utilizing the explosive energy of explosives to scatter the debris around. FIG. 4 is a schematic side view (partially cut away) of a conventional debris ejecting device for a flying body, in which debris 21 is arranged on the outer periphery of the body of the flying body. That is, a plurality of fragments 21 are arranged around the outer cylinder 20 filled with the explosive 19, and the outer periphery thereof is covered with the cover 22. The outer cylinder 20 constitutes a part of the fuselage structure of the flying body. In this debris discharge device, the detonator 23 detonates the explosive 19.
The cover 22 is destroyed by the energy of this explosive, and the fragments 21 are scattered around at high speed (initial velocity of 1000 to 2000).
m / s). The explosive 19 has both the energy for the debris 21 to reach the target and the energy necessary for destroying the structure of the target after reaching the target, and these are equipped with the necessary amount of explosive 19. .

As shown in FIG. 5, the fragment 21 is a target object 0.
Detonation occurs on the side of 3 and scatters and penetrates to destroy the target 03. In this case, the debris discharging device 02
The velocity of the flying object 01 having a large velocity is large, and the relative velocity between the two is generally used in the range of about 100 m / s to 1000 m / s, and the mutual crossing angle is most within 90 °. This is the range used.

[0004]

The above-mentioned conventional debris discharging device has the following problems to be solved.

That is, the conventional debris ejector is used in the form of overtaking from behind or crossing over from the side of the target. In this case, the relative speed at the time of overtaking is approximately 100 m / s to 1000 m / s. Therefore, in order to destroy the target, it is necessary to scatter the fragments at a high speed, and there is a problem that a large amount of explosive is required. Further, it is effective only under the condition that the relative velocity is limited to a relatively narrow range, and there is a problem that the fragment may not collide with the target and may not be destroyed depending on the condition.

In order to solve the above-mentioned problems, the present invention provides a device for ejecting debris of a flying object, in which a group of a plurality of debris is used as a unit block and a plurality of blocks are provided in the front-rear direction of the flying object and are ejected and scattered one after another. The purpose is to provide.

[0007]

Means for Solving the Problems As a means for solving the above-mentioned problems, the present invention provides a debris ejecting device for a flying object that ejects and disperses debris and associates with a target, in which a group of a plurality of debris is used as a unit block. A plurality of blocks provided in the front-rear direction, a debris discharging means independently provided for each block, and a control device for operating the discharging means with a required time lag. It is intended to provide a characteristic flying object debris discharging device.

[0008]

Since the present invention is constructed as described above, it has the following actions.

That is, a group of a plurality of fragments is set as a unit block, and a plurality of blocks are provided in the front-back direction of the flying body.
Since each block is provided with a device for discharging debris independently, and a control device for operating the discharging device with a required time difference is provided, the controller causes the control device to operate each discharging device with a required time difference. Then, when operating one after another,
Correspondingly, a plurality of fragments of each unit block are successively emitted and scattered. As a result, the target is exposed to the curtain of the debris group for a certain period of time rather than in a moment as in the conventional case, and the probability of association between the debris and the target is significantly increased.

Further, since the probability of the fragments and the target to associate with each other increases, it is also expected that the range where the fragments, which have been scattered in the air for a long time and have a small residual kinetic energy, will meet (collide) with the target as in the conventional case. Since it is not necessary to do so, the probability of meeting the target in a short time after the release increases, that is, the meeting occurs when the collision speed is high.
The energy of is small and sufficient.

[0011]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of the present invention will be described with reference to FIGS. FIG. 1 is a side view of the present embodiment (the main part is shown broken away)
2 (a) is an overall view, FIG. 2 (b) is an enlarged view representatively showing one side of the block of the first stage fragment 2, explosive 3 etc. of (a). FIG. 2 is a functional block of this embodiment. FIG. 3 and FIG. 3 are side views schematically showing a meeting situation between a flying object equipped with this embodiment and a target object.

Before the detailed description is given, in order to facilitate understanding, first, the basic concept of the embodiment will be outlined. According to this embodiment, the target object 03 (FIG. 3) is a debris emitted from the device of this embodiment. In order to be destroyed by 2, the assembly position calculation circuit 13 shown in FIG. 2 and four series after the ignition timing command circuit 14 for ejecting the fragments 2 with a time difference with respect to the target are provided. This increases the chances of colliding with the target object 03. When calculating the meeting position with the target object 03, the calculation is performed based on the relative distance from the guide device, the relative approach speed, the line-of-sight angle, etc., and the distance with the target object 03 approaches and the signal from the guide device disappears. Also, the calculation based on the signals so far is continued, and the calculation of the meeting position with the target object 03 is performed by using the trajectory flight calculation together. Therefore, the meeting position with the target object 03 becomes more precise.

In this embodiment, the relative approach speed at the time when the meeting with the target object 03 is predicted is large (1000 m / s).
Since the explosive 3 can be used even at ˜2000 m / s), a small amount of explosive 3 is required, the number of fragments 2 is increased, the chance to collide with the target object 03 is increased, and the destruction effect is increased. Further, a safety release mechanism 17 is built in. This is provided with two series of circuits for preventing the indefinite release of the fragments 2 in a series of sequences from pre-use maintenance to firing and target destruction before the target destruction distance of 1 to 5 km. For this reason,
This is a system that emphasizes safety when the device of this embodiment is used, and these are characteristic points of the device of this embodiment.

As described above, according to this embodiment, the target object 03
The condition for colliding with is effective even when the relative approach speed with the target object 03 is large (1000 m / s to 2000 m / s). That is, when the flight directions of the target object 03 and the flying object 30 are opposite to each other, they pass each other. In this case, even if the speed of the fragment 2 to be discharged is small, if the target object 03 and the target object 03 collide with each other, Because the relative speed of both is large,
The kinetic energy resulting from the relative velocity when the fragment 2 collides is used, and it is not necessary to eject the fragment 2 at high speed. Therefore, only the amount of explosive required to discharge the fragments 2 is sufficient, and the explosive required to penetrate and destroy the target object 03 is unnecessary. Therefore, a smaller amount of explosive than in the past is sufficient. Conventionally, the fragments 2 are discharged only once, and the discharge timing is also set in advance. When the approaching speed is increased, the destructive effect of the conventional one is limited, but in the present embodiment, the calculation result of the position of association with the target object 03 is used, and even if the relative speed fluctuates, the release timing of the fragment 2 is flexible. It is possible to make a more effective collision with the target object 03, and the destructive effect is improved several steps compared to the conventional example. The timing of the discharged fragments 2 is set to 4 times, and it is based on the result of the target collision position calculated for each individual block. Target 03
The chances of colliding with are greater than in the past, so the probability of destruction is high.

Further, a mechanism for preventing the indefinite explosion (release) from occurring by the built-in safety release mechanism 17 from the time of pre-use maintenance of this embodiment to the launch of the flying object 30 and immediately before the destruction of the target object 03. In addition, it has higher safety.

Next, details of this embodiment will be described.

In FIG. 1, 1 is an outer case, 2 is a block of a plurality of fragments for destroying a target,
Fragments placed in each block as independent blocks of the first to fourth stages in the front-back direction of the flying body (left-right direction in the figure), 3
Explodes the debris 2. Therefore, explosives are provided independently for each block, 4 is a liner, 5 is an electric detonator for ejection provided in each block, 6 is a main body of the ejection device, and 7 is a flat plate for ejection electric power. A slide plate that constitutes a part of a safety release mechanism having a through hole for communicating the detonator 5 and the explosive 3 (however, the through hole is shown at a position where the above communication is cut off), and 8 is a safety for fixing the slide plate 7. Pins, 9 are pistons for operating the slide plate 7, 10 are explosives for operating the pistons, 1
Reference numeral 1 is an electric detonator for safety release, and 30 is a debris discharging device of this embodiment having the above configuration.

Next, in the functional block diagram of FIG.
Is a signal processing circuit for matching various signals such as a relative distance from the guidance device, a relative approach speed, and a line-of-sight angle (horizontal direction and vertical direction) with the target to the calculation circuit, and 13 is a signal of the signal processing circuit 12. Based on the calculation result of the meeting position calculation circuit 13, a meeting position calculation circuit 14 calculates the relative position (distance and direction) at which the target and the emitted fragments 2 meet. A discharge command for discharging the fragments 2 with a time difference, an ignition timing command circuit for controlling, 5 is an electric detonator for discharge, and 15 is an operation of the slide plate 7 for preventing an untimely operation of discharging the fragments 2. , A safety release timing calculation circuit for calculating a timing for controlling, 16 is a safety release command circuit for receiving a result of the safety release timing calculation circuit 15, and a safety release command circuit for controlling, 18 is the meeting position calculation circuit 1 , Ignition timing command circuit 14, the arming time 15, integrated arming command circuit 16, a microprocessor which integrates each circuit, the arming electric detonators described above 11, 17 the piston 9, explosive 10,
Slide plate 7, safety pin 8 and safety detonator 11
It is a safety release mechanism consisting of.

Next, the operation, that is, the operation of the above configuration will be described.

The signal processing circuit 12 adjusts various signals from the guiding device to signal levels that can be matched with the meeting position calculation circuit 13. The meeting position calculation circuit 13 uses a signal detecting and tracking a target among the signals output from the guiding device, and based on the relative distance, the relative approach speed, and the line-of-sight angle (horizontal and vertical directions) signal. Prediction calculation of the meeting position of both parties is executed until the point of maximum proximity. Calculations are performed up to the minimum tracking distance and maximum line-of-sight angle of the guidance device, but predictive calculations are performed on the assumption that the ballistic flight will be performed until the closest point thereafter. The ignition timing command circuit 14 has a known relationship between the discharge time and the discharge distance in the present fragment discharge device mechanism, and matches the result of the meeting position calculation circuit 13 so that the largest number of fragments 2 collide with the target. Then, the time difference between the discharge timing of the first-stage block and the discharge timing of each of the second and subsequent blocks is commanded and controlled. These signals are individually command-controlled by the electric detonator 5 for discharging the explosive 3, and the fragments 2 are discharged.

The safety release timing calculation circuit 15 performs a calculation based on the signal from the signal processing circuit 12 for the safety release mechanism 17 to operate at the time when the target front is 1 to 5 km. The safety release command circuit 16 receives a signal from the safety release timing calculation circuit 15 and commands and controls the signal so that the safety release electric detonator 11 can be operated. Before the safety release mechanism 17 is activated by the instruction of the safety release command circuit 16, the transmission circuit by the explosive 10 is kept closed by the slide plate 7 provided between the discharge detonator 5 and the explosive 3. And
The transmission system of the explosive powder 10 is cut off, and is responsible for preventing the explosive powder 3 from being operated undesirably. The explosive charge 10 and the piston 9 are actuated by the operation of the safety releasing electric detonator 11, and the slide plate 7 cuts and moves the safety pin 8, whereby the through hole provided in the slide plate 7 and the discharging electric detonator 5, The explosive transfer circuit is formed by aligning the explosives 3 in line.

That is, as the safety release mechanism in this device, the safety release timing calculation circuit 15, the safety release command circuit 16, and the safety release electric detonator 11 of the safety release mechanism 17 shown in FIG.
And a series of the safety releasing electric detonator 11, explosive 10, piston 9, safety pin 8 and slide plate 7 mainly shown in FIG. 1 as described above.

The electric circuit for discharging the fragments 2 is configured as a functional block integrated in the integrated microprocessor 18. The discharging electric detonators 5 that have received the command from the ignition timing command circuit 14 are set as a set of two, and the first stage of the discharging electric detonators 5 located at the position of the central axis is operated to activate the first explosive 3 first. The second stage explodes and receives the energy, and the first stage of the fragment 2 destroys the outer cylinder case 1 and destroys the fragment 2.
Is released. In the same manner, the fragments 2 of the fourth stage are discharged in a similar manner, and the fragments 2 of each block are discharged into the space as a group, and collide with the flying target to effectively destroy the target. The state of discharge of the fragments 2 is shown in FIG.

In FIG. 3, 30 is a flying object, 31 is the debris discharging device shown in FIG. 1, 03 is a target object, and 04 is a structure of the target object 03. V _M is the velocity of the flying object 30, V
_T indicates the speed of the target object 03. Therefore, if the flight axes of the flying object 30 and the target object 03 flying in the opposite direction are parallel to each other, if the fragments 2 are emitted perpendicularly to the axis of the flying object 30, The relative velocity component between the fragment 2 and the target 03 is approximately V _M + V _T. As can be easily seen from the figure, for example, in the conventional case, since only the first-stage fragments 2 are scattered by one discharge, the probability of colliding with the target object 03 is 0 in the situation of the figure, In the case of the present embodiment, since the fragments 2 are discharged with the time difference, the second stage, the third stage, and so on, the probability that the fragments 2 of the third stage and the fourth stage collide is extremely high in the figure.

The guidance device shown in FIG.
A guidance device when it is mounted on a vehicle and is used for the purpose of being used in a flight-controlled situation in which a control device is actuated based on a command signal of this device and the target object 03 is met. It is a point.

As described above, according to this embodiment, a group of a plurality of fragments 2 is provided as a unit block in the first to fourth stages in the front-back direction of the projectile, and the explosive 3 and other discharging means are provided. Separately provided, the signal processing circuit 12 and other control devices cause the explosive 3 to explode one after another at the most appropriate timing with respect to the target object 03, and the fragments 2 of the blocks from the first stage to the fourth stage are separated with an appropriate time difference. Since the particles are discharged and scattered, there is an advantage that the probability of association between the target object 03 and any of the fragments 2 is significantly increased.

Further, since the debris 2 is discharged by the control device at an optimum timing and the debris 2 is associated with the target object 03 when the airborne distance is still small, the relative velocity between the target object 03 and the debris 2 is very large, and However, there is an advantage that a small amount of explosive 3 for discharging the fragments 2 is sufficient.

[0028]

Since the present invention is constructed as described above, it has the following effects.

That is, a group of a plurality of pieces is set as a unit block, and a plurality of blocks are provided in the front-back direction of the flying body, and the control apparatus releases the pieces one after another with a required time difference. The chances of meeting debris with the target are significantly increased.

Further, since the probability of association between the fragments and the target is significantly increased, the scattering time of the fragments from the release to the association is short, and the residual kinetic energy is large. The energy of is small and sufficient.

[Brief description of drawings]

FIG. 1 is a view of a debris discharging device for a flying object according to an embodiment of the present invention, in which (a) is a side view (partially cut away),
(B) is an enlarged view of one side of the block of the first-stage fragment 2 of (a),

FIG. 2 is a functional block diagram of the above embodiment,

FIG. 3 is a side view schematically showing a meeting situation between a flying object equipped with the apparatus of the above embodiment and a target object,

FIG. 4 is a schematic side view of a conventional debris discharging device (partially cut away),

FIG. 5 is a side view schematically showing a state of association between a flying object equipped with a conventional debris discharging device and a target object.

[Explanation of symbols]

 1 Outer case 2 Fragment 3 Explosive 4 Liner 5 Discharge electric detonator 6 Discharge device body 7 Slide plate 8 Safety pin 9 Piston 10 Explosive 11 Safety detonator electric detonator 12 Signal processing circuit 13 Meeting position calculation circuit 14 Ignition timing command circuit 15 Safety release timing calculation circuit 16 Safety release command circuit 17 Safety release mechanism 18 Microprocessor 30 Flying body 31 Debris ejector

Claims (1)

[Claims] 1. A debris ejecting device for a flying object, which ejects and scatters debris to associate with a target, wherein a plurality of blocks are provided as a unit block in the front-back direction of the flying object, and each block. A debris ejecting device for a flying object, comprising: debris ejecting means independently provided for each and a control device for operating the ejecting means with a required time lag.