RU2374599C2 - Method for throwing of axisymmetric ogive projectile from rifled barrel of arm with pressure of powder gases in underwater and air medium and device for its realisation - Google Patents

Abstract

FIELD: weapons and ammunition.

SUBSTANCE: in method from nose part of axisymmetric ogive projectile a rotary jet of missile powder combustion gases is emitted, which creates double-phase medium with water or air in trajectory of projectile movement. For this purpose in hollow ogive shell of projectile in its nose part there is an axial hole with blades arranged inside at its outlet. Outside hollow shell, a calibrated nozzle is inserted into this hole, being coated with membrane and separated from remaining volume of hollow shell with a transition space that adjoins inlet of nozzle and is limited with diaphragm that fixes charges of missile powder. Blasting cap is closed with stern by ring of conductor with hole for sting of striker connected to round metal plate, which rests against cylindrical protrusion of stern along edge of its diametre and is sealed along its end with a thin plate that contacts with it.

EFFECT: increased distance and stability of projectile flight.

2 cl, 1 dwg

Description

The invention relates to methods and devices of weapons technology and can be used both in underwater and in air for throwing bodies in the form of a bullet from the channels of small arms barrels or a shell from gun trunks.

A known method of movement of axisymmetric animated bodies moving on their trajectories by inertia in the atmosphere, implemented in devices of small arms technology in the form of bullets (See TSB, 3rd edition, M., 1977, art. "Bullet"). Each individual missile bullet is ejected from the threaded bore of the barrel by the pressure of powder gases.

The disadvantage of this method is the impossibility of its use in the underwater environment due to the significant resistance of the aquatic environment and the significant turbulence of the water jets in the cavitation zone resulting from the axial rotation of the bullet.

There is also known a method of moving an axisymmetric body in an underwater environment (see US patent No. 3915092, "Underwater projectile", MKI F42B 11 / 0,00), ejected from a smoothbore weapon by the pressure of powder gases and moving along the trajectory by inertia.

The disadvantages of the above method are the short range of the body along the trajectory due to the significant resistance of the water to movement, especially with increasing depth of the shot, and the unsuitability of using the said method for aimed shooting in air.

Closest to the claimed method of movement of an axisymmetric animated projectile in an underwater environment, thrown by the pressure of powder gases from a rifled barrel of a weapon, is a method implemented in the design of fragmentation-tracing anti-aircraft projectile moving along an inertia trajectory (See A.G. Gorst, “Gunpowder” and explosives ", state publishing house of the defense industry. M., 1957, pp. 171-172).

The disadvantage of the prototype method is the impossibility of its use in the underwater environment due to the significant turbulence of the water jets in the cavitation zone, resulting from the axial rotation of the projectile, and the significant resistance of the aqueous medium to body movement.

Known bullet for small arms, taken in the application for an analogue (see TSB, 3rd edition, M., 1977, the article "Bullet"), consisting of a live shell filled, for example, with lead.

The disadvantage of this bullet is the impossibility of its use in the underwater environment due to the low stability of its movement due to significant resistance and turbulence of water jets in the cavitation zone during axial rotation.

The closest in technical essence and the achieved result to the present invention, which implements a method of moving missile bodies from the channels of arms, is a fragmentation tracer anti-aircraft projectile with self-destruction using a tracer device with an impact device to prevent unexploded shells from falling onto the ground (see A.G. . Gorst, "Gunpowder and Explosives", State Publishing House of the Defense Industry. M., 1957, pp. 171-172).

Such a projectile has a lively hollow stern and a lively hollow body connected to the stern, on the outer surface of which there is a copper belt for abstraction of powder gases when fired in a barrel bore with rifling. The main fuse, the explosive charge along with the detonator and the front of the rod are located in front of the hollow body of the anti-aircraft shell. The second part of the rod, the liquidator and the tracer composition with an igniter are located in another part of the hollow shell of the projectile, hermetically connected to the hollow livestock feed and separated from the front by a partition, into the hole of which the rod is inserted.

The tracer body with the capsule sleeve is screwed into the hollow tail of the stern from the side of its end surface. The capsule sleeve contains a safety sleeve in which the firing pin and the igniter capsule are located. The capsule sleeve is connected to the sleeve in which the powder retarder is placed. The capsule sleeve is connected to the tracer body by a hermetically lead ring.

The disadvantage of the prototype is the impossibility of its use in the underwater environment.

The technical task of the present invention is to increase the range and stability of the bullet or projectile along the trajectory both under water and in the atmosphere of air, with the standard dimensions of the bodies used.

The stated technical problem is achieved by the fact that in the method of moving an axisymmetric animated projectile in underwater and in the air, thrown by the pressure of the powder gases from the rifled barrel of the weapon, a rotating stream of combustion gases of rocket propellant is released from the nose of the projectile, forming a two-phase medium with water or air along the trajectory the movement of the projectile.

In addition, the indicated technical result is achieved by the fact that in an axisymmetric live projectile consisting of interconnected hollow live shells and stern, inside of which is placed a charge of gunpowder with an igniter receiving fire rays through seed holes from the igniter capsule, which is pressed into the bottom of the stern for the impact on him is the sting of the striker in such a way that it rests against the impact composition in the anvil made on the back of the bottom of the stern. An axial hole with blades located inside, at the exit from it, is made in the hollow animated membrane on the bow. A calibrated nozzle is inserted into this hole from the inside of the hollow shell, which is covered by a membrane and separated from the rest of the hollow shell by a transition space adjacent to the nozzle inlet and limited by a diaphragm fixing the charge of rocket propellant. In addition, the igniter capsule is closed by a conductor ring connected to the stern with an aperture for the striker tip connected to a round metal plate abutting along the edge of its diameter in a cylindrical protrusion of the stern sealed at the end with a contacting thin plate.

Due to the formation of a two-phase gas-gas or air-gas medium on the trajectory in front of the body being thrown, with the help of a gas rotating jet ejected from the axial hole on the front of the body when the charge of rocket powder is placed in the internal cavity of the body with an ignition shock device, the problem is solved and the technical result of the invention is achieved to increase the range and stability of the movement of a bullet or projectile with standard sizes of these bodies both in the aquatic environment and in the air.

Due to the fact that in the hollow animated shell on the bow there is an axial hole with the blades located inside, at the exit from it, the blasting nozzle of the rotating stream of combustion gases of rocket powder is released from the bow of the projectile, which forms a two-phase medium with water.

A calibrated nozzle inserted from the inside into the axial hole provides a minimum brake reactive impulse due to the stability of the gas evolution of the combustion of gunpowder and the constant pressure inside the projectile, as well as the constant volume flow of gases in front of the projectile.

The membrane serves as a destructible damper for starting the release of gases at the time of the shot when the required gas pressure equal to the outlet is reached.

The transition space helps to stabilize the gas pressure, and the diaphragm serves to fix the powder charge and the direction of movement of the powder gases to the transition space.

The conductor ring through the hole directs the movement of the stinger of the striker to the igniter capsule and is connected with the stern to exclude the inclined incline of the bottom of the igniter capsule.

A round metal plate resting on the edge of its diameter against a specially provided cylindrical protrusion of the stern is necessary for safety reasons to prevent accidental bending of the igniter capsule during transportation and loading of shells.

A thin plate in contact with a round metal plate isolates the internal space of the projectile from the external environment by sealing with the stern.

A device for implementing the inventive method of moving an axisymmetric animated projectile is illustrated in the drawing, where Fig. 1 shows a General view of the projectile in section.

The axisymmetric animated projectile consists of an animated hollow stern 1, an animated hollow shell 2, an axial hole 3 with blades, a nozzle with a membrane 4, a transition space 5, a diaphragm 6, a charge of rocket powder 7, an igniter 8, the bottom 9 of the stern, anvil 10, a capsule the ignitor 11, the annular conductor 12, the striker 13, the round plate 14, the contact plate 15.

To implement the method of movement of an axisymmetric animated projectile in underwater or in the air during the firing of cartridge loading in the rifled bore of the barrel, the powder gases exert pressure on the bottom of the bullet or projectile. As a result of the pressure, the round plate 14 and the plate 15 in contact with it bend. The firing pin 13, slipping in the hole of the conductor 12, punctures the igniter capsule 11, pressing its impact composition against the anvil 10. The rays of fire from the igniter capsule 11 are transmitted through ignition holes (not shown) in the bottom of the stern 9 to the ignitor 8. Igniter 8 ignites the charge of the rocket gunpowder 7, the pressure inside the body and in the transition space 6 increases to the necessary, and the membrane of the nozzle 4 is destroyed.

A stream of powder gases begins to exit from the hole 3 in the barrel channel in front of the moving body during the shot. Therefore, a biphasic gas-gas mixture is formed in the barrel bore during an underwater shot, essentially a foam, pushing the liquid column out of the barrel bore and smoothing out the force of the hydraulic shock in the barrel due to the compression of the foam gas bubbles. Since the throwing bodies from the rifled channels of the trunks have a gyroscopic torque, the outgoing powder gases from the hole 3 with the blades, thanks to them, are twisted. This contributes to the crushing, uniform and rapid distribution of gas jets in the form of bubbles on the trajectory of movement and around it and to reduce the transverse size of the bubbles.

This property of gas jets swirling up to 700-900 rpm helps to improve the visibility of the space under water, which, when fired, is obscured by relatively large gas bubbles for a rather long time, since the rate of rise of gas bubbles in water is small. For this reason, special measures are used in underwater weapons to crush and reduce the size of the bubbles to prevent deterioration in visibility during shots due to the appearance of many bubbles of powder gases from the barrel channels.

The resulting two-phase water-gas mixture in front of the bullet or projectile has a significantly lower density than water. Therefore, the resistance to the movement of bodies in such a two-phase medium is less than directly in water (See. "Collection of works of the International Symposium on Unsteady Water Flows at High Velocities", B. B. Kogarko, "The Movement of a Liquid and Gas Bubbles", Moscow: Science, 1973, p. 243-246 and in other articles of the collection of the same author).

For all aerodynamic calculations of the parameters of the motion of bodies in air, including the calculation of their aerodynamic drag, the adiabatic index k is used. Since the adiabatic index k = 1.4 for air is 85.7% higher than the adiabatic index for powder gases k = 1.2, the claimed design of the projectile that implements the method of movement in the atmosphere of air according to this application has aerodynamic resistance to its movement by 14.3% less than existing designs. Therefore, the remaining motion parameters of these propelled bodies in the aerogas medium also improve proportionally: motion stability, speed, impact range, trajectory distance, dispersion, gyroscopic moment, trajectory flatness and all other aerodynamic-dependent parameters.

The choice of rocket propellant is determined by the need to obtain a small and constant pressure of powder gases in the internal cavity of a bullet or projectile during movement along a trajectory that depends on the diameter of the nozzle. In addition, the choice of rocket powder allows you to accurately calculate the magnitude of the reactive braking torque of the gases flowing out of the hole, which is chosen to be minimal for the proposed design of propelling bodies.

To calculate the required amount of gas evolution and the burning time of the rocket propellant, the nozzle diameter, the weight and loading density of the internal cavities of the shell and the stern of the projectile or the bullet with the propellant powder, the minimum reactive inhibitory pulse of the outgoing gases in front of the body, accepted, tested, well-known methods were used (See Serebryakov M. E. "Internal ballistics of barrel systems and powder rockets", Moscow: Oborongiz, 1962, pp. 298-300).

For a 9 mm bullet with a powder charge (rocket ballistic missile MRN) and a nozzle orifice diameter of 1.35 mm, the estimated time of burning of gunpowder in the internal cavities of the shell and stern was 0.138 s, the estimated time of flight of the bullet along the trajectory was 0.12 s, the gas concentration in two-phase water-gas mixture of the trajectory volume - 6.5%. The range of the bullet along the trajectory in the fresh water pool at a depth of 1.7 meters was about 43 meters.

Due to the formation of a two-phase gas-gas or air-gas medium on the trajectory in front of the body being thrown, with the help of a gas rotating jet ejected from the axial hole on the front of the body when the charge of rocket powder is placed in the internal cavity of the body with an ignition shock device, the problem is solved and the technical result of the invention is achieved to increase the range and stability of the movement of a bullet or projectile with standard sizes of these bodies.

Claims (2)

1. The method of throwing an axisymmetric animated projectile from a rifled weapon barrel by the pressure of powder gases in the underwater and in the air, characterized in that from the axial hole made in the nose of the projectile on the projectile’s path, a rotating stream of combustion gases of rocket propellant is formed, forming with water or air two-phase medium. 2. An axisymmetric animated projectile for throwing guns from a rifled barrel with the pressure of powder gases in the underwater and in the air, containing a hollow animated shell hermetically connected to each other with a stern, inside which a charge of rocket powder with an igniter is placed, and an igniter capsule is pressed into the bottom of the stern resting against its anvil anvil, made at the bottom of the stern, and made with the possibility of interaction with the sting of the striker and the transfer of rays of fire to the igniter, characterized in that in the nose The main part of the shell has an axial hole with blades located inside, at the outlet, into which a calibrated nozzle is inserted, covered by a membrane and separated from the rest of the hollow shell by a transitional space adjacent to the nozzle inlet and limited by a diaphragm fixing the charge of rocket propellant, In this case, the igniter capsule is closed by a conductor ring connected to the stern with an aperture for the striker tip, which is connected to a metal round plate abutting against its cylindrical edge stupa of the stern and a thin plate sealed at the end of the stern in contact with it.