RU2765745C1 - Shot to the grenade launcher - Google Patents

Abstract

FIELD: ammunition.

SUBSTANCE: invention relates to ammunition, in particular to shots for grenade launchers. The shot for the grenade launcher contains a warhead of functional equipment, a liner, which includes a jet engine, consisting of a combustion chamber with a fuel stick and an igniter, and a bottom part commensurate with the barrel prechamber. The bottom part contains a combustion chamber equipped with outlet openings and equipped with a propelling powder charge and a central primer-igniter. A special feature is that the central primer-igniter through an axial throttling channel communicates through the igniter with the combustion chamber of the fuel checker of the jet engine, and the combustion chamber of the jet engine through at least one offset from the axis of the throttling channel is connected to the annular combustion chamber of the propellant charge placed at the bottom of the shank and separated from the primer-igniter. The inlet openings of the motor nozzles and the throttling channel have equal diameters and are closed by a common diaphragm.

EFFECT: improvement of the design of an active-reactive shot to the grenade launcher in order to synchronize the processes of the engine reaching the operating mode and ignition of the propellant charge, compensating for the spread in the time of the engine reaching the operating mode, stabilizing the intra-ballistic parameters of the shot and, thus, improving the accuracy indicators.

1 cl, 2 dwg

Description

SUBSTANCE: invention relates to unitary loading ammunition for grenade launchers and can be used in reactive cartridges and other active-reactive shots.

Known artillery cartridge for a grenade launcher according to patent RU 2125226 C1, 20.01.1999, F42B 5/02.

A well-known cartridge (shot) for a grenade launcher contains a warhead with a leading belt profiled with ready-made projections parallel to the longitudinal axis, the width of which is commensurate with the rifling of the barrel, a combustion chamber in which a propellant charge is placed, closed by a horizontal perforated diaphragm with a membrane, a sealing gasket in the form leaf spring, and an igniter cap adjacent to the propellant charge.

A feature of the known shot is that the combustion chamber of the propellant charge is located in the shank, rigidly connected to the body of the grenade and closed at the end by a diaphragm equipped with outlets, the diameter of which is commensurate with the pre-chamber of the barrel, forming a guaranteed minimum installation gap.

The shot is loaded from the muzzle end of the weapon, based on the protrusions of the master device in the spiral grooves of the barrel, while the extra volume of the weapon barrel forms a receiver - a high-pressure chamber for the propellant gases of the burning propellant charge.

The disadvantage of the known shot is the relatively low mass of grenade equipment, which is associated with restrictions on the maximum allowable recoil energy for the shooter.

According to the technical nature and the number of matching features, the closest analogue to the proposed ammunition is the grenade launcher shot adopted by the applicant as a prototype according to patent RU 2525352 C1, 10.08.2014, F42B 5/02.

In this shot, the combustion chamber of the propellant charge through the axial throttling channel communicates through the igniter with the combustion chamber of the fuel checker of the jet engine in the shank, equipped with inclined nozzles, the axes of which are additionally rotated adequately to the angle of elevation of the helical rifling of the barrel.

The disadvantage of the known shot is the lack of accuracy, which makes it difficult to aim shooting. The engine charge in this case is ignited by a propellant charge when the ammunition, under the influence of its combustion products, has already begun to move in the barrel. As a result, the ammunition flies out of the barrel of the weapon before the engine reaches the operating mode with a speed insufficient for gyroscopic stability, and before it is reached, it may deviate somewhat from the direction of fire, which is the reason for its reduced accuracy. This disadvantage is also exacerbated by the natural spread in the time the engine reaches the operating mode, which is especially significant at low temperatures.

The technical problem to be solved by the present invention is to improve the design of an active-rocket shot for a grenade launcher in order to synchronize the processes of the engine entering the operating mode and igniting the propellant charge, compensating for the spread in the time the engine enters the operating mode, stabilizing the intra-ballistic parameters of the shot and, thus , improving accuracy.

A well-known shot for a grenade launcher contains a warhead of functional equipment and a shank, including a jet engine and a bottom part commensurate with the prechamber of the barrel, containing a combustion chamber, equipped with outlets, equipped with a propellant powder charge, a central primer-igniter and through an axial throttling channel connected through an igniter with a chamber combustion of the fuel checker of a jet engine.

The required technical result is achieved by the fact that in the well-known shot, the igniter primer through an axial throttling channel communicates through the igniter with the combustion chamber of the jet engine fuel checker, and the combustion chamber of the engine through at least one throttling channel offset from the axis is connected to the annular combustion chamber of the propellant powder charge, separated from the igniter capsule, while the inlets of the engine nozzles and the throttling channel have equal diameters and are closed by a common membrane.

Distinctive features of the proposed technical solution make the actuation of the propellant charge dependent on reaching a certain pressure in the engine, capable of breaking through the membrane and overcoming the gas-dynamic resistance of the throttling channel displaced from the axis, connecting the engine chamber with the combustion chamber of the propellant charge. As a result, the propellant charge is activated only after the pressure in the engine has risen to a certain level, which makes it possible to synchronize the process of the engine entering the operating mode and ignition of the propellant charge.

The connection of the engine chamber through a throttling channel with the combustion chamber of the propellant powder charge, which is formed after the membrane breaks, ensures reliable ignition of the propellant charge from the jet engine when fired. The throttling channel prevents the reverse penetration of high pressure from the propellant charge (up to 80 MPa) into the engine combustion chamber, where the operating pressure is much lower (up to 5 MPa). Thus, the calculated mode of operation of the engine is preserved, which makes it possible to reduce the mass of its structure.

To increase the reliability of propellant charge initiation from the engine, the number of throttling channels connecting them can be increased and amount to at least two.

The central primer-igniter through the axial throttling channel communicates through the igniter with the combustion chamber of the fuel block of the jet engine. The igniter ensures reliable ignition of the fuel pellet, and the axial throttling channel prevents the high pressure of the engine from penetrating to the igniter cap, while maintaining the design mode of the engine.

The primer-igniter is structurally separated from the annular combustion chamber of the propellant charge, which makes it impossible to prematurely ignite this charge when the primer is fired.

The inlets of the engine nozzles and the throttling channel have equal diameters and are closed by a common membrane. The operation of the igniter and the combustion of the fuel pellet is accompanied by a rise in pressure in the combustion chamber of the engine. When a certain pressure is reached, a simultaneous breakthrough of the common membrane covering the inlets of the engine nozzles equal in diameter and at least one throttling channel occurs, after which the outflow of fuel combustion products begins through the nozzles, and the propellant charge ignites through the displaced throttling channel. To ensure simultaneous rupture of the membrane, the inlets of the engine nozzles and the throttling channel must have equal diameters. Thus, the propellant charge is triggered in the process of raising the pressure in the engine, which ensures the synchronism of their action.

Each essential feature of the proposed technical solution is necessary, and their combination in a stable relationship is sufficient to achieve a new required technical result.

The essence of the invention is illustrated by a drawing, which is purely illustrative and does not limit the scope of claims of the totality of the features of the formula. The drawing shows:

in fig. 1 - the proposed shot to the grenade launcher;

in fig. 2 - sectional view of a shot to a grenade launcher.

In FIG. 1, as an example, a shot with a spin-stabilized grenade is shown. The effectiveness of the proposed technical solution does not depend on the method of stabilization of the ammunition: plumage, or rotation. This technical solution can also be used in feathered ammunition.

A grenade launcher shot contains a warhead 1 with a head fuse or a remote tube 2, the initiating devices of which are in contact with functional equipment (for example, explosive, thermobaric or aerosol-forming substances, pyrotechnic equipment from lighting, signal, etc. actions).

The shank 3 adjoins the warhead 1, the bottom part 4 of which is made to match the diameter of the prechamber of the weapon barrel with a guaranteed minimum installation gap.

On the periphery of the shank 3, a leading belt is made in the form of an annular row of protrusions 5 with a width commensurate with the spiral grooves of the weapon barrel.

At the end of the shank 3, a diaphragm 6 is fixed, having outlet openings 7 along the periphery, closed by an annular membrane 8. In the center of the diaphragm 6, an igniter primer 9 is installed, which interacts through the axial throttling channel 10 and the igniter 11 with the fuel block 13 placed in the combustion chamber 12, installed between gratings 14.

The combustion chamber 12 of the fuel pellet through the throttling channel 15, which is off-axis, communicates with the propellant charge 17, pressed by the perforated gasket 16 and placed in the annular combustion chamber 18 of the propellant charge, which is structurally separated from the igniter cap 9. To improve the reliability of ignition of the propellant charge, 17 such channels can be, for example, at least two. In FIG. 1, as an example, a chamber 18 with two offset throttling channels 15 is shown. The combustion chamber 12 of a jet engine fuel pellet has inclined nozzles 19 evenly distributed over the bottom part 4 of the shank 3. The inlets 21 of the nozzles and the inlets of the throttling channels 22 equal in diameter are closed common membrane 20.

Inclined nozzles 19 are additionally rotated adequately to the angle of elevation of the helical rifling of the weapon barrel, so that the tangential component of the thrust force coincides with the direction of rotation of the ammunition obtained during firing.

The proposed shot to the grenade launcher functions as follows.

When firing, the primer-igniter 9 is initiated, from which the igniter 11 and the fuel cartridge 13 are ignited through the throttling channel 10.

The combustion products of the igniter 11 and the fuel pellet 13 fill the combustion chamber 12 of the engine fuel pellet and, when sufficient pressure is reached (about 0.5 MPa), they break through the membrane 20 that closes the inlets of the nozzles 21 and the throttling channels 22. The combustion products of the fuel begin to flow through the inclined nozzles and at the same time come through the throttling channel 15 through the perforated gasket 16 to the propellant charge 17 and ignite it.

The propellant gases of the propellant charge 17 break through the annular membrane 8 and fill the pre-chamber of the barrel through the holes 7, where the pressure rises sharply, under the influence of which the ammunition receives linear acceleration.

Throttling channel 15 prevents the reverse penetration of high pressure from the combustion chamber 18 of the propellant charge into the combustion chamber 12 of the engine fuel pellet.

According to experimental data, the response time of the propellant charge is from 0.002 to 0.004 s, and the engine operation time is from 0.4 to 0.6 s.

Thus, the operation of the propellant charge 17 occurs in the process of raising the pressure in the combustion chamber 12 of the fuel pellet 13, and the operating pressure in the engine is reached by the time the ammunition leaves the barrel, which ensures the stability of the shot parameters.

At negative temperatures, and also due to the natural scatter of engine parameters, depending on design and technological factors, some delay in the ignition of the fuel pellet 13 and the operation of the propellant charge 17 from the engine igniter 11 are not excluded. In this case, the pressure from the propellant charge 17, reduced by throttle holes 15 to a safe value for the engine, passes into the combustion chamber 12 of the fuel pellet 13 of the engine and reduces the time it takes to reach the operating mode.

When moving in the barrel due to the interaction of the protrusions 5 and the spiral grooves of the bore and, after leaving the barrel of the weapon, from the tangential component of the thrust force of the inclined nozzles 19, the ammunition is spun relative to the longitudinal axis to a rotational speed that provides gyroscopic stability on the flight path.

Depending on the type of equipment and the type of fuse corresponding to it, or remote tube 2, the ammunition is triggered when it meets the target, or at a given range and height.

A comparative analysis of the proposed technical solution with the identified analogues of the prior art showed that it is unknown, and taking into account the possibility of serial production of shots for a grenade launcher in the current production, it can be concluded that this solution meets the patentability criteria.

Claims (1)

A shot for a grenade launcher, containing a warhead of functional equipment and a shank, including a jet engine, consisting of a combustion chamber with a fuel cartridge and an igniter, and a bottom part commensurate with the prechamber of the barrel, containing a combustion chamber equipped with outlets and equipped with a propellant powder charge and a central primer - an igniter, characterized in that the igniter capsule through an axial throttling channel communicates through the igniter with the combustion chamber of the jet engine fuel cartridge, and the combustion chamber of the jet engine fuel cartridge through at least one throttling channel offset from the axis is connected to the annular combustion chamber of the propellant powder charge, separated from the igniter capsule, while the inlets of the nozzles of the jet engine and the throttling channel have equal diameters and are closed by a common membrane.

Images