RU2540987C1 - Fuse for missile projectiles and method of its application - Google Patents

Abstract

FIELD: weapons and ammunition.

SUBSTANCE: invention relates to the field of armaments, in particular to fuses for missile projectiles, mainly of valley fire systems. The fuse for missile projectiles comprises an inertial contactor, a power supply, a sensor of generation of command for demolition, the electronic unit, the detonator, the fuse safety and arming mechanism comprising a safety valve, an electric detonator, in the housing of which the explosive charge and the initiator are mounted, connected to the electronic unit. The explosive charge comprises two samples: outlet, made of secondary high density explosive, and the initiating sample made of explosive diperchlorate (5-nitrotetrasolato)pentaamincobalt (III), connected with the initiator, which is used as a semiconductor energy conversion element. Height of the initiating sample along the longitudinal axis of the charge is made following the condition of providing the transition of combustion of the initiating sample into the detonation when triggering of the semiconductor energy conversion element.

EFFECT: invention provides high reliability of combat use and improved safety in the service operation.

2 cl, 4 dwg

Description

The invention relates to the field of armaments, in particular to fuses for rockets, mainly multiple launch rocket systems.

A device is known that contains a sleeve with an explosive charge placed in it, made in the form of hinges: output from a secondary high-density explosive and initiating, coupled to an initiator mounted on a sealing block with current leads (AS No. 1746778, IPC F42C 19 / 12, published on January 20, 1995).

Disadvantages: a low-density secondary explosive charge was used as an initiating explosive charge, which lengthens the convective combustion stage, increasing the response time of the electric detonator, and requires high-voltage initiation, which is caused by the use of an exploding bridge, the manufacture of which is technologically difficult.

A device is known that contains a sleeve with an explosive charge placed in it, made in the form of hinges — an outlet from a high-density secondary explosive and initiating, coupled to an initiator mounted on a sealing block with current leads, equipped with a spark gap placed between the sealing block and current leads, and equipped with a liner installed in the sleeve with an explosive charge and an intermediate sample of low-density deflagrating explosive located m forward output and initiating weighed, the weighed initiating deflagrating made of high density with axial height explosive determined by the formula h = (22 26 .._) D _and where D _and - initiator diameter (RF Patent No. 2389971, IPC F42C 19 / 12, published on 05/20/2010 - prototype).

The specified device operates as follows.

When a subversive electrical impulse is supplied to the initiator, a hitch from a high-density deflagrating explosive is initiated and the following attachments are sequentially activated: intermediate, from a low-density deflagrating explosive, and the output from a high-density secondary explosive.

The main disadvantages are the need to use three attachments - initiating, intermediate and output, which leads to a complication of the design and manufacturing technology of the electric detonator.

The task to which the proposed technical solution is directed is to create a fuse for shells of multiple launch rocket systems, providing high reliability of combat use and increased safety in official use.

The solution to this problem is achieved by the fact that the proposed fuse for rockets contains an inertial contactor, a power source, a detonation command sensor, an electronic unit, a detonator, a safety-actuating mechanism containing a safety shutter with an intermediate charge, a transfer charge, an electric detonator, in the body of which installed explosive charge, the initiator connected to the electronic unit, and the explosive charge consists of two attachments: output, of a high-density secondary explosive, and an initiating sample made of the explosive diperchlorate (5-nitrotetrazolato) pentaamine cobalt (III), coupled to the initiator, which is used as a semiconductor energy-converting element, while the height of the initiating sample along the longitudinal axis of the charge is made of conditions for ensuring the transition of combustion of the initiating sample to detonation upon operation of the semiconductor energy-converting element.

For this fuse, a method of its application is proposed, using which, according to the invention, after launching a rocket, the fuse electronic unit is activated using an inertial contactor and the safety-actuating mechanism is moved to the firing position, while the safety shutter is moved and the fire circuit closes: electric detonator - intermediate charge - transfer charge - detonator. Then, if there is a target, the detonation command generation command sends the detonation command to the electronic unit, which generates an electric pulse at the current outputs of the electric detonator, which triggers the semiconductor energy-converting element, by which an initiating hinge is used, the detonation pulse from which is transmitted to the output hinge and then on fire chain on the detonator.

The invention is illustrated by drawings, in which Fig. 1 is a diagram of a fuse, Fig. 2 is a structural diagram of a safety-actuating mechanism in the initial position, Fig. 3 is a structural diagram of a safety-actuating mechanism in a combat position, Fig. 4 is a cross-sectional view. electric detonator.

The fuse for rockets includes an inertial contactor 1, a detonation command generation sensor 2, a power supply 3, an electronic unit 4, a safety-actuator 5, a detonator 6. A safety-actuator 5 contains a safety shutter 7, an intermediate charge 8, a transfer charge 9 , an electric detonator 10, in the case 11 of which an initiator is installed, which is used as a semiconductor energy-converting element 12 mounted on the block 13, with current leads 14 connected to the electric nym unit 4, an explosive charge, consisting of two batches of: output sample 15 made of a secondary explosive and an initiating hinge 16, made of a substance diperhlorat (5-nitrotetrazolato) pentaaminkobalta (III).

The proposed method and device operation is as follows.

After the launch of the projectile, the electronic unit 4 is activated using the inertial contactor 1, the safety-actuating mechanism 5 is cocked, while the safety shutter 7 moves, closing the fire circuit, the electric detonator 10 - intermediate charge 8 - transfer charge 9 - detonator 6. If there is a target, the sensor 2 generates a detonation command, after which the electronic unit 3 supplies an electrical impulse to the current outputs 14 of the electric detonator 10, the semiconductor energy-converting element 12 is activated, which initiates weighed guide 16 forming a detonation pulse. Then the detonation is transmitted to the output hinge 15 and then to the transfer charge 9, which uses the detonator 6.

The positive effect achieved when using the invention is expressed in improving the safety of the fuse in official circulation and ensuring reliability during combat use.

Claims (2)

1. A fuse for rockets, characterized in that it contains an inertial contactor, a power source, a detonating command generation sensor, an electronic unit, a detonator, a safety-actuating mechanism comprising a safety shutter, an electric detonator, in which the explosive charge and initiator are installed, connected to the electronic unit, and the explosive charge consists of two attachments: output, made of high-density secondary explosives, and initiating a sample made of explosive diperchlorate (5-nitrotetrazolato) pentaamine cobalt (III), paired with an initiator, which is used as a semiconductor energy-converting element, while the height of the initiating sample along the longitudinal axis of the charge is made from the condition of ensuring the transition of combustion of the initiating sample to detonation when triggered semiconductor energy converting element. 2. The method of using the fuse according to claim 1, characterized in that after launching the rocket, the fuse electronic unit is activated using the inertial contactor and the safety-actuating mechanism is moved to the firing position, while the safety shutter is moved and the fire circuit closes the detonator - detonator, then, if there is a target, the detonation command generation sensor sends a detonation command to the electronic unit, which generates an electric pulse at the current outputs of the detonator sensing triggering of a semiconductor energy converting element, by means of which an initiating hinge is used, the detonation pulse from which is transmitted to the output hinge and then through the fire circuit to the detonator.

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