RU2747558C1 - Method of increasing the range of a projectile - Google Patents

Abstract

FIELD: weapons.

SUBSTANCE: invention relates to weapons and in particular to a method for increasing the range of a projectile. The method of increasing the range of the projectile consists in attaching an expelling powder charge to the projectile. A cartridge with a powder charge mixed with TNT particles with a base fuse is attached to the bottom of the projectile with the help of a locking device. The bottom of the projectile has a cruciform tail for flight stability, which does not protrude beyond the maximum diameter of the projectile. The bottom fuse is powered by a capacitor bank controlled by an angle sensor set by a contactless command receiver. The expelling charge is triggered from the angle sensor on the flight path of the charge.

EFFECT: increased range of the projectile.

1 cl, 1 dwg

Description

The invention relates to ammunition, in particular to methods of increasing the flight range of artillery shells.

Known ways to increase the range of artillery shells: 1. By increasing the initial velocity of the projectile and lengthening the barrel. The long barrel length allows you to increase the initial velocity of the projectile, as well as more efficiently use the energy of the propellant gases of the propellant charge. 2. Use of new propelling charges. For example, there are propellants with inclusions of explosives or with a special form of powder grain. 3. For a long time there have been ways to increase this parameter by upgrading the projectile. The ZVOF91 projectile, equipped with a bottom gas generator, has the same weight parameters and characteristics of the propellant charge as the usual ZVOF72 high-explosive fragmentation projectile. 4. An effective, but more complex, alternative to the projectile with a gas generator is the active-rocket projectile.

There is a known method of increasing the flight range of an artillery projectile, which consists in the fact that for the formation of a direct-flow path, in which gaseous products with a lack of oxidizer generated in the gas generator are burned out using outboard air, a body with excessive strength for flight modes is used, which is performed in the form of a telescopic structure, including itself, two coaxial shells, under joint axial loading, are of equal strength with a solid shell of the same mass. After departure from the bore, the projectile body in the tail section is telescopically transformed, as a result of which an air intake device and an afterburner chamber with a nozzle hole are formed, forming a direct-flow path. Using the air intake device, a part of the incoming air flow is taken, which is fed into the afterburner, where it is mixed with the combustion products of the gas generator and afterburned, after which the outflow of the formed gaseous products through the nozzle hole is organized, thereby creating a jet thrust during the combustion time of the fuel charge of the gas generator. (Patent RU 2486452 IPC F42B 10/38, publ. 06/27/2013).

The disadvantages of the prototype include the following:

1. Afterburning of a part of the pyrotechnic composition occurs behind the bottom cut of the projectile, which leads to incomplete use of the energy stored in the pyrotechnic composition, as well as the chemical energy of the air participating in the afterburning process.

2. The projectile on the trajectory, as in the case of the analogue described above, has an excess safety margin of the hull, due to the high level of starting overloads in the bore.

As a result, the energy of the pyrotechnic composition is far from being fully utilized, and the capabilities of the projectile body from the standpoint of structural strength are incomparably higher than it is necessary in flight, based on the loads perceived by the projectile on the trajectory.

Of the known, the closest in technical essence is a method of increasing the flight range of an artillery projectile, which consists in the fact that after the departure of a projectile containing a housing of the aft compartment with a block of stabilizers and a bottom gas generator producing gaseous products with a lack of oxidizer, atmospheric air is taken from the barrel bore, oxygen of which the combustible gaseous mixture obtained in the gas generator is burned, characterized in that the aft compartment housing is made of a composite of telescopically folded outer and inner shells and is transformed twice in flight: the first time the transformation is carried out immediately after the projectile leaves the barrel bore by extending the outer shell with a block of stabilizers, providing the formation of a rocket-ramjet engine with an afterburner, a fuel charge of the gas generator, an air intake device and a nozzle, the second time the transformation is carried out after the burnout of the fuel charge of the gas generator due to return the outer shell of the aft compartment housing to its original position and close the air intake device (Patent RU 2522699 IPC F42B 15/00, publ. July 20, 2014).

The disadvantages of the prototype include the fact that the afterburning of a part of the pyrotechnic composition occurs behind the bottom cut of the projectile, which leads to incomplete use of the energy stored in the pyrotechnic composition, as well as the chemical energy of the air involved in the afterburning process. Also, the projectile on the trajectory has an excess of the strength of the hull, due to the high level of starting overloads in the bore.

This method makes it possible to increase the firing range of an artillery projectile by increasing its flight speed due to the energy stored in the fuel. Placing a ramjet engine on board makes it possible to use air as an oxidizer, however, in this case, it is required to have an afterburner of a certain size on board the projectile, thereby limiting the volume of the payload while keeping the projectile dimensions unchanged. Known aerodynamically stabilized projectile (Application number WO2001SE0133220010613 "Fin stabilized shell"), which implements the telescopic transformation of the glider during flight. This device makes it possible to increase the volume of the projectile during flight and, by displacing the stabilizer block backward, to increase the degree of static stability while maintaining the dimensions of the standard projectile during its storage. However, the additional free volume obtained during the telescopic transformation remains passive and is not used in any way.

Known cartridge containing a cylindrical sleeve, in which there is a powder charge with an axial channel in which the projectile is placed, and in its rear part an expelling charge with an ignition means. The expelling charge pushes the projectile out of the cartridge even before the ignition of the main powder charge. This frees up the channel space filled with the combustion products of the expelling charge. As a result, a high-density propellant charge can be burned with the same efficiency as a lower-density charge in a larger liner. In this case, a large initial velocity of the projectile is achieved in comparison with the corresponding characteristic for the cartridge of the classical scheme. Another advantage is achieved by the cylindrical shape of the sleeve. Cartridges of this shape are more convenient for storage and take up half the volume in stacking compared to conventional cartridges. (Patent patent US 5557059 A, published 09.17.1996).

The disadvantage is the dubious creation of additional pressure in the bore, because the charging chamber has certain fixed dimensions. You can vary the size of the projectile to increase the additional charge, but then the power of the projectile decreases. And if you reduce the volume of the main charge, then the pressure will correspondingly decrease during its combustion. Therefore, if you do not change the size of the projectile, then the total volume of the main and additional charge will be equal to the charge of the existing shot. Thus, the average total borehole pressure remains unchanged. Additional charge can provide a flattening pressure curve, so an increase in projectile velocity is unlikely.

The closest analogue of the invention is a telescopic cartridge containing a cylindrical sleeve with a monolithic powder charge located in it, having an axial channel in which the projectile is placed. An igniter is placed in the bottom of the liner, and an expelling charge is placed in the bottom of its cavity. The projectile contains a housing with an explosive charge placed in it and a bottom trajectory-impact fuse with a detonator. The fuse contains an electronic device for trajectory detonation (either temporary, or a revolving number, or non-contact, or command) and an inertial-type percussion detonation device (Patent RU 2346228 IPC F42B 5/045, publ. 10.02.2009).

The disadvantage is the placement of an additional powder charge in the sleeve, i.e. the device is designed to increase the speed of the projectile in the bore. Such a scheme can provide a slight increase in projectile speed.

The proposed invention is aimed at increasing the speed of the projectile on the flight path.

The technical result is to increase the range of the projectile due to additional acceleration on the trajectory by the pressure of the expelling charge. This is achieved by the fact that, in the device of the projectile, a sleeve with an expelling charge is additionally attached to the bottom of its bottom by a lock-locking device, with a bottom fuse powered by a capacitor, controlled by an angle sensor set by a contactless command receiver. Flight stability is ensured by the cross-shaped plumage of the projectile.

The introduction of additional elements provides an increase in the speed of the projectile along the trajectory. When the specified angle of the projectile trajectory is reached, monitored by the angle sensor, the bottom explosive charge fuse is triggered. As a result of the combustion of the powder charge mixed with TNT particles in the liner, a pressure is created, which breaks off the occluding lock-locking device. Under the action of this pressure, the projectile receives additional acceleration, and the walls of the sleeve provide the direction of movement. As a result, the flight range is increased by at least 20%.

The proposed method for increasing the range of the projectile is implemented using the device (Fig. 1). A device that implements the method contains a cylindrical sleeve 1 with an obturating belt 8, in which an expelling charge 7 and a projectile 10 are located, characterized in that the projectile with an impact head fuse 12 on the body has a cruciform tail 11 that does not protrude beyond the maximum diameter of the projectile, but the rear part has a cylindrical cutout with a groove for a stopper at the beginning of the cutout, onto which a cylindrical sleeve 1 is put on and fixed with a stopper 9, which inside the liner is filled with a mixture of a powder charge with TNT particles and in the bottom part has an angle sensor 5, control unit 6, bottom fuse 4 , capacitor bank 2, fixed with a screwed bottom 3.

The method is carried out as follows. Before firing, a special device sets the firing angle of the propelling charge. After a shot on the trajectory, when the projectile occupies a given angle, an expelling charge is triggered, with the pressure of which the projectile receives additional acceleration.

The proposed method makes it possible to increase the flight range by at least 20%.

Claims (1)

A method of increasing the range of the projectile, which consists in attaching an expelling powder charge to the projectile, characterized in that to the bottom of the projectile, which has a cruciform tail for flight stability, not protruding beyond the maximum diameter of the projectile, a sleeve with a powder charge mixed with particles of trinitrotoluene, with a bottom fuse, which is powered by a capacitor bank controlled by an angle sensor set by a contactless command receiver, and the expelling charge is triggered from the angle sensor on the flight path of the charge.

Images