RU2735318C1 - Reactive ammunition - Google Patents

Abstract

FIELD: military equipment.

SUBSTANCE: invention relates to jet munitions intended for firing from sea (shipborne) grenade launcher systems. Reactive ammunition containing head part with detonating fuze, jet engine with boosting assembly, in parallel connected electric igniter and condenser, arranged in nozzle of jet engine and connected freely laid conductors with external contact buses located on stabilizer. Capacitor is located in the forcing assembly together with the electric igniter on the ammunition rotation axis. Electric igniter is installed in the forcing assembly on the side of the head part, the capacitor is mounted on the opposite side. Conductors are twisted to each other in a single bundle and installed in a protective casing.

EFFECT: technical result consists in improvement of reliability of action and safety of ammunition.

1 cl, 1 dwg

Description

The invention relates to the field of military technology and can be used in the devices of rocket ammunition intended for firing from sea (ship) grenade launcher systems.

Marine grenade launcher systems are usually operated under conditions of exposure to electromagnetic fields (EMF) generated by

- external radio transmitting means (RRS) and radar stations (radar);

- stations of windingless demagnetization;

- electrical equipment of the ship;

- electronic countermeasures;

- charges of static electricity accumulated on the maintenance personnel and the launcher;

- lightning strikes.

Therefore, they are subject to stringent requirements for protection against guidance currents, which significantly depend on the design of the electrical circuit, the relative position and installation of protection elements.

Known rocket ammunition [1], designed for firing from shipborne grenade launcher systems (prototype). It contains a parallel connected electric igniter and a capacitor, placed in the jet engine nozzle and connected by conductors with external contact lines located on the stabilizer. The capacitor is fixed on the site of the outer diameter of the nozzle throat, and the electric igniter is fixed on the axis of the forcing unit located in the nozzle throat, from the side of the jet engine igniter.

When an electrical impulse is applied to the contact rails, an electric igniter is triggered, which ignites the igniter, and the beam of fire from the igniter is transmitted to the solid fuel charge. By the pressure of the engine gases from the nozzle throat, the forcing unit with the spent electric igniter is ejected. Under the action of the thrust, the fixing stops on the stabilizer are cut off, and the ammunition begins to move in the bore of the grenade launcher system, and then along the trajectory.

The technical solution according to patent No. 2356006 provides protection of the electric circuit of the ammunition from the guidance currents arising during the operation of the ship's radar and radar stations, allows to reduce the danger zone with the breech cut of the grenade launcher and the overall mass characteristics of the jet engine by placing an electric igniter and a capacitor in the nozzle.

This technical solution is implemented in the RG-55M, GRS-55, RG-55MI type rocket launchers for the MRG-1, DP-61 and DP-65 marine grenade launchers.

High operational reliability and simplicity of the design, confirmed by the long life of their operation in the fleet, make it advisable to use such a design scheme in newly developed ammunition and all the indicated prototype features in the claimed invention.

However, this technical solution has a number of disadvantages that were identified during the development of new ammunition of increased efficiency for standard shipborne grenade launcher systems:

- it is possible that induced currents (released energies) may occur above the permissible value in hazardous electrical circuits of the ammunition due to freely located conductors, which affects the reliability and safety of the grenade launcher system;

- abrasion of the insulation of conductors is possible during transport and operational influences, which can lead to abnormal functioning of the ammunition when fired;

- the occurrence of an imbalance due to the attachment of the condenser on the site of the outer diameter of the nozzle throat inside the annular stabilizer at some distance from the axis of rotation of the ammunition, as a result of which the accuracy of fire deteriorates.

The task solved by the claimed invention is to increase the effectiveness of the ammunition.

The technical result consists in increasing the operational properties, reliability and safety of the ammunition.

The technical result is achieved by the fact that the jet ammunition contains a warhead with a fuse, a jet engine with a forcing unit, an electric igniter and a capacitor connected in parallel, located in the jet engine nozzle and connected by loosely laid conductors with external contact tires located on the stabilizer. The capacitor is mounted on the same axis with the electric igniter located in the forcing unit, but on the opposite side. The conductors are twisted together into a single bundle and installed in a protective casing.

The location of the capacitor in the forcing unit together with the electric igniter does not increase the danger zone behind the grenade launcher when fired. Tests have shown that over the entire temperature range (from minus 50 to plus 50 ° C), the forcing unit does not penetrate a 3 mm plywood shield at a distance of 30 m from the breech of the grenade launcher. At a temperature of plus 50 ° C, the plug of the forcing unit leaves a dent on the shield no more than 1 mm deep, at a temperature of minus 50 ° C, there are no traces on the shield: fragments of the plug, capacitor housing and electric igniter were found at a distance of up to 15 m.

The location of the capacitor in the forcing unit together with the electric igniter on the axis of rotation of the ammunition eliminates the imbalance, as a result of which the accuracy of fire does not deteriorate, i.e. the effectiveness of the ammunition.

Twisting loosely laid conductors into one bundle protects dangerous circuits from induced currents. For the purpose of an objective assessment, such a scheme was experimentally verified by comparative tests for the effect of EMF in various frequency ranges, which showed its complete safety in comparison with freely located conductors. This is explained by the fact that loosely laid conductors form a kind of accumulating antenna, where the values of induced currents and released energies are much higher at certain frequencies than in a twisted bundle.

The supply of twisted conductors with a protective casing at the point of transition from the internal volume of the nozzle through the slot (groove) at the end of the nozzle to the tires on the annular stabilizer increases the reliability during transport and operational influences, since excludes cutting (or abrasion) of the protective sheath of the conductors on the sharp edges of the groove at the end of the nozzle.

FIG. 1 shows a jet ammunition.

The jet ammunition contains a warhead 1, a fuse 2, a jet engine 3 and an annular stabilizer 4 with fixing stops. The jet engine 3 consists of a chamber 5 with a nozzle and a nozzle 6, closed by a lid 7, inside the chamber 5 there are a powder charge 8, an igniter 9 and a boost unit 10. On the axis of the boost unit 10 from the igniter 9 side, an electric igniter 11 is located, on the opposite side - a capacitor 12. At the points of connection (soldering), cambric 14 and 15 are put on wires 13. Wires 13 at the place of transition from the internal volume of the nozzle through the slot (groove) on the end of the nozzle 6 to the tires 17 on the annular stabilizer 4 are equipped with a protective casing 16.

The work of the jet ammunition is as follows.

During the operation and transportation of ammunition, the protection of wires 13 is provided by the casing 16, and the electric igniter 11 from premature operation - by the capacitor 12 and twisted wires 13, which serve as a filter for high-frequency currents.

When an electrical impulse is applied to the contact tires 17, an electric igniter 11 is triggered, which ignites the propellant charge of the igniter 9. The force of fire from the igniter 9 is transmitted to the propellant charge 8 of the engine 3 and ignites it. The resulting propellant gases, when a certain pressure in the chamber 5 is reached, is ejected from the nozzle throat of the forcing unit 10 with the spent electric igniter 11 and the capacitor 12.

Under the action of the thrust of the jet engine, the fixing stops on the annular stabilizer 4 are cut off, and the ammunition begins to move in the bore of the grenade launcher, and then along the trajectory.

The implementation of the proposed technical solutions in the design of an increased efficiency jet ammunition, confirmed by the results of full-scale ground and sea tests, made it possible to increase its effectiveness by increasing the operational properties, reliability and safety of the ammunition.

Sourse of information:

1. Patent RU No. 2356006 C1, IPC F42B 15/00, publ. 20.05.2009, Bul. fourteen.

Claims (1)

A jet ammunition containing a warhead with a fuse, a jet engine with a boost unit, an electric igniter and a capacitor connected in parallel, located in the jet engine nozzle and connected by loose conductors with external contact buses located on the stabilizer, characterized in that the capacitor is located in the boost unit together with an electric igniter on the axis of rotation of the ammunition, while the electric igniter is mounted in the forcing unit from the side of the head part, the capacitor is on the opposite side, and the conductors are twisted together into a single bundle and installed in a protective casing.

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