RU2356006C1 - Jet-propelled projectile - Google Patents

Abstract

FIELD: weaponry.

SUBSTANCE: invention relates military equipment and can be used if jet-propelled projectiles to be fired from the combat ship grenade guns. The proposed jet-propelled projectile comprises electric igniter and capacitor connected in parallel and arranged in the jet engine nozzle and connected to outer contact buses. The jet engine nozzle is fitted inside the fin the outer surface of which features centering bulges and locking retainers. The latter represent the continuation of the fin stiffening ribs to get destructed on launching. Various-diametre buses are fitted coaxially behind the centering bulges. The capacitor is fitted on the nozzle critical section OD site.

EFFECT: higher efficiency thanks to simpler loading, higher reliability and safety during launching.

3 cl, 2 dwg

Description

The invention relates to the field of military equipment, namely to munitions with a jet engine and an electric igniter, designed for firing from grenade launcher systems deployed on any naval ships afloat.

Ship grenade launcher systems are operated, as a rule, under the influence of pulsed radiation of electromagnetic energy radiated by radar and radio transmitting (RPS) stations, therefore, they are subject to strict requirements for protection against guidance currents, which significantly depend on the design of the electrical circuit, relative position and installation of protection elements.

In addition, ship’s grenade launcher systems can be operated without announcing a combat alert (personnel may be on the deck of the ship), which requires the exclusion or significant reduction of the danger zone behind the breech of the grenade launcher.

Known reactive ammunition (England patent No. 1182275 of 02.25.1970), for locking which in the barrel of a grenade launcher a metal ring with a shoulder and constipation is used. At the time of the shot, the ring is kicked back by a jet of gas from the jet engine, freeing the ammunition.

The disadvantages of this technical solution include:

- the presence of a significant size of the danger zone beyond the breech section of the barrel of the grenade launcher, which virtually eliminates the possibility of operating the grenade launcher in ship conditions;

- lack of technical solutions for the design of the electrical circuit, the relative position and installation of protection elements from guidance currents arising from the operation of shipborne radars and RPMs, which have a significant impact on the reliability and safety of the grenade launcher system.

Known reactive ammunition (US Pat. Germany No. 1216169 from 05/05/1966), containing a jet engine, a solid fuel charge placed in the engine chamber, and an ignitor in a metal casing. The igniter includes a sample of gunpowder and electric fuses and is placed in the nozzle. The igniter housing has one or more central firing holes.

This design of the jet munition allows to reduce the overall mass characteristics of the jet engine, but at the same time, it has all the disadvantages of the technical solution for the patent of England No. 1182275.

Known reactive ammunition containing an electric igniter with a parallel-connected capacitor located in the jet engine nozzle and connected to the external contact tires (US patent No. 2818020 - prototype).

The technical solution according to patent 2818020 provides protection of the ammunition circuit from guidance currents arising from the operation of shipborne radars and RPS, and allows to reduce the overall mass characteristics of a jet engine by placing an electric igniter and a capacitor in the nozzle.

The disadvantages of this technical solution include:

- creating a large danger zone behind the breech of the grenade launcher due to the ejection of an electric igniter and capacitor from the nozzle at the initial moment of operation of the jet engine, which significantly reduces the operational characteristics of the grenade launcher system, especially when operating it in ship conditions;

- lack of technical solutions for fixing the ammunition in the barrel of the grenade launcher, in the design and location of the forcing unit of the jet engine, in the design of the electrical circuit, the relative position and installation of protection elements from guidance currents.

So, for example, the installation of contact tires on the shell of the munition leads to:

- the need to ensure reliable electrical insulation of the contact tires from the mass of the shell of the munition, which significantly complicates the design of the munition;

- complicating the loading conditions of the grenade launcher due to difficulties in ensuring reliable combination of the contact tires of the ammunition and the electrical contacts of the grenade launcher, which, ultimately, reduces the reliable operation of the ammunition.

The task of the invention is to increase the effectiveness of the reactive ordnance.

The technical result consists in simplifying the loading conditions, increasing the reliability of the action and safety at startup.

The technical result is achieved in that the reactive munition contains an electric igniter with a parallel-connected capacitor located in the jet engine nozzle and connected by conductors to the external contact tires, the jet engine nozzle located inside the ring stabilizer, on the outer surface of which a centering thickening is made and its stiffeners are extended the fixing stops destroyed during the shot, and the contact tires are made of different diameters and are placed coaxially for the cent iruyuschim thickening, wherein the capacitor is fixed to the site outside diameter of the nozzle throat.

The performance of the capacitor as an integral part of the ammunition (not dismantled at the time of the shot) by attaching it to the outer diameter of the critical section of the nozzle located inside the annular stabilizer, significantly increases safety at launch by reducing the danger zone behind the breech of the grenade launcher. For example, if a capacitor is ejected from a jet engine nozzle, due to its high specific penetration energy, it leaves through holes in a 3-mm plywood shield at a distance of up to 35 m from the breech of the grenade launcher.

The implementation of the ammunition contact tires with rings of different diameters and their alignment coaxially behind the centering thickener of the stabilizer simplifies the conditions for loading the ammunition by ensuring reliable combination of the electrical contacts of the ammunition and the grenade launcher in working condition near the breech of the latter, and also increases the reliability of the ammunition by eliminating the possibility of shorting contact tires under the influence of salt fog and sea water.

The execution on the outer surface of the annular stabilizer by the extension of its stiffening ribs of the fixing stops destroyed during firing significantly increases safety at launch by reducing the danger zone behind the breech of the grenade launcher (particles of the destroyed stops do not extend beyond the zone of action of the jet engine gas jet) and increases the reliability of the munition by providing reliable fixation of electrical contacts of ammunition and a grenade launcher.

The ammunition can be equipped with a forcing unit located in the critical section of the nozzle and made in the form of a plug made of thermoplastic, into which an electric igniter is mounted on the side of the ignition side of the jet engine to reduce the danger zone behind the breech of the grenade launcher. When ejected from the nozzle, the plug (due to the displacement of the center of gravity) rotates through 180 ° and at the moment of encounter with the obstacle, the body of the triggered electric igniter moves in the direction of the obstacle, thereby extinguishing the reflection energy of the plug. The best results in reducing the danger zone behind the breech of a grenade launcher were obtained with an electric igniter drowning value of 0.09 ÷ 0.11 of the plug diameter.

In a reactive munition, the conductors of an electric igniter and a capacitor can be connected in the same segment of the diametrical plane of the munition at an equal distance from the contact tires, which eliminates premature operation when the munition is in a pulsed electromagnetic field.

In figure 1, 2 shows a rocket ammunition.

The ammunition contains a jet engine 1 with a solid fuel charge 2 and an igniter 3, a nozzle 4, a forcing unit consisting of a plug 5 and an electric igniter 6, a capacitor 7, an annular stabilizer 8, including a centering thickening 9, stiffeners 10, contact tires 11, fixing stops 12.

The electric igniter 6 is mounted in the plug 5 with a guaranteed drowning "a".

The work of rocket ammunition is as follows.

During the storage and transportation of ammunition, the protection of the electric igniter 6 from premature operation is provided by a capacitor 7, which serves as a high-frequency current filter.

When an electric pulse is applied to the contact buses 11, an electric igniter 6 is activated, which ignites the powder charge of the igniter 3. The flame beam from the igniter is transmitted to the charge of solid fuel 2 and ignites it. The gas pressure of the engine 1 from the critical section of the nozzle 4 ejects the plug 5 with the housing of the electric igniter 6.

Under the influence of the thrust of the jet engine, the locking stops 12 of the stabilizer 8 are cut off, and the ammunition begins to move in the barrel of the grenade launcher.

The implementation of the proposed technical solutions in the design of rocket munitions, confirmed by the results of ground and ship tests, allows to increase the efficiency of its action by simplifying the loading conditions, increasing the reliability of the action and safety at launch.

Claims (3)

1. A rocket ammunition containing an electric igniter and a parallel-connected capacitor located in the jet engine nozzle and connected by conductors to the external contact tires, characterized in that the jet engine nozzle is placed inside an annular stabilizer, on the outer surface of which a centering thickening and fixing stops in the form of extensions the stabilizer stiffeners destroyed during the shot, and the contact tires are made of ring of different diameters and placed coaxially behind the center thickening, while the capacitor is fixed on the site of the outer diameter of the critical section of the nozzle. 2. The rocket ammunition according to claim 1, characterized in that it is equipped with a forcing unit located in the critical section of the nozzle and made in the form of a plug of thermoplastic, into which an electric igniter is mounted with a recession from the ignition side of the jet engine. 3. The reactive ammunition according to claim 1 or 2, characterized in that the conductors of the electric igniter and capacitor are connected in one segment of the diametrical plane of the ammunition at an equal distance from the contact tires.

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