RU2038570C1 - Shell for smoothbore artillery systems - Google Patents

Abstract

FIELD: artillery equipment. SUBSTANCE: shell control system gyro 7 is installed in the shell bottom part, it is made as a gas turbine, whose chamber communicates with the shell tail space and shell side surface. It is a subcaliber shell with the front (3) and rear driving bands with through longitudinal ducts 4. Grooves 6 for retardation of gas flow are provided on the side surface between the bands. EFFECT: improved design. 1 dwg

Description

 The invention relates to weapons and can be used in industries engaged in the production of artillery shells.

 Known projectile for artillery systems, consisting of a hull, warhead, host device.

 The advantage of smooth-bore artillery systems is that the friction of the projectile during the shot is reduced, its flight speed is increased, and the survivability of the artillery barrel is increased.

 Also known is a projectile for smoothbore artillery systems, consisting of a hull, a warhead, extendable wings and aerodynamic control elements, a control system with a gyroscope and a master device.

 The well-known projectile for smooth-bore artillery systems has a serious drawback and requires considerable time to prepare the projectile for launch.

 In order to reduce the preparation time for the projectile to launch, the gyroscope is installed in it in the bottom of the body and is made in the form of a gas turbine, the cavity of which is communicated by means of a central hole with a projection space and by means of tangential holes with the side surface of the gyroscope, while the body is made of subcaliber, and its leading a device in the form of front and rear belts with through longitudinal channels, and through holes are made in the wall of the body at the installation site of the gyroscope, and on the side surface STI housing between the front and rear by shoulder grooves to brake the gas stream. At the same time, the launch time of the projectile is reduced by the following constructive technique: a powerful gas turbine is used as an engine to spin the gyroscope. Structurally, the gas turbine and the gyro disc are combined. The promotion of the gyroscope is performed through part of the energy of the main powder charge.

 For this purpose, the projectile region is connected with the entrance to the gas turbine through an opening in this part of the projectile and tangential holes on the side surface of the gyroscope.

 To ensure the operation of the gas turbine, the shell of the shell is made of sub-caliber, which allows the exhaust of the gases exhausted in the gas turbine through the barrel to the outside. Next, a part of the gas stream of the main powder charge is used to accelerate the movement of the projectile through the through channels of a longitudinal shape on the front and rear belts and grooves located between the belts on the shell of the projectile, which, interacting with the gas stream, slow down its speed, converting the kinetic energy of the gas stream into mechanical moving the projectile along the bore.

 The drawing shows the proposed projectile, a cut along the centerline to illustrate the location of the retractable wings (shown recess).

 The projectile for smooth-bore artillery systems consists of a projectile 2 placed in the barrel 1, equipped with a front driving belt 3 with through longitudinal holes (channels) 4 for passing part of the gas stream. The rear drive belt is similarly arranged. The area of the longitudinal through channels 4 of the front driving belt 3 is larger than the area of the channels of the rear driving belt. The shell of the shell 2 is made subcaliber in order to interact with the gas stream with its side surface and to ensure the release of exhaust gases in the gas turbine. The projectile is equipped with retractable wings 5, equipped with aerodynamic control, and also contains a warhead. The side surface of the shell of the projectile between the front and rear driving belts is provided with grooves 6 for braking the gas flow, which contributes to an increase in the velocity of the projectile along the bore. In the bottom of the projectile installed gyroscope 7, made in the form of a gas turbine. Gyroscope 7 provides orientation of the projectile in flight, increasing accuracy and range. The gyroscope 7 can be installed at an angle to the longitudinal axis of the shell of the projectile to ensure stabilization of the projectile in flight in four directions. A gas turbine (gyroscope) 7 is connected to the projection space through a central opening 8, through which the products of the combustion of the powder charge enter the gas turbine. On the lateral surface of the gyroscope 7 there are tangential openings 9 for the exit of the gases exhausted in the gas turbine. In the lateral surface of the housing at the place where the gyroscope 7 is located, through holes 10 are made for the exhaust gases exhausted in the turbine.

 The projectile operates as follows.

 With the ignition of the powder charge, the pressure in the projectile space increases. Part of the powder gases passes through the through channels of the rear driving belt, expanding at the same time, and acquires supersonic speed. This gas stream is inhibited by interacting with grooves 6 on the side surface of the projectile. In this case, the kinetic energy of the gas stream is converted into mechanical force, leading to the movement of the projectile along the bore. This force is additional to the buoyancy force of the powder gases acting on the bottom of the projectile. Both forces act in the same direction and therefore summarize. Next, the gas stream exits through the through channels 4 of the front driving belt 3 into the cavity of the barrel 1, reducing the pressure in front of its head part, which also helps to accelerate the projectile. At the same time, part of the gas flow passes through the central hole 8 into the cavity of the gas turbine 7 and through the tangential channels 9 and holes 10 into the barrel channel. When this gas turbine 7 comes into rotation and energy is accumulated in the gyroscope to stabilize the projectile in flight. The promotion of the gyro continues throughout the movement of the projectile along the bore. The gas stream from the holes 10 moves along the shell of the projectile, interacts with the grooves 6, increasing the velocity of the projectile, and exits through the through longitudinal channels 4 into the cavity of the barrel 1. When the projectile leaves the barrel, the retractable wings 5 are thrown outward, supporting the projectile in flight. The force created by the wings is equal to the weight of the projectile and therefore the projectile in flight implements almost all of the kinetic energy received from the powder charge to increase the flight range. The gyroscope stabilizes the projectile in the direction of flight. The wing control system can change the altitude and direction of flight by program or radio control. In this case, the gyroscope may have relative freedom of position, which is necessary to change the direction of flight.

 The proposed projectile has a number of significant positive qualities: a large flight range, the accuracy of hitting the target, which makes it competitive in comparison with medium-range missiles. At the same time, the projectile has advantages in the initial flight speed, speed of launch and size.

Claims (1)

 A projectile for smooth-bore artillery systems, including a hull, warhead, extension wings and aerodynamic controls, a control system with a gyroscope, a master device, characterized in that, in order to reduce preparation time for launch, the gyroscope is installed in the bottom of the hull and made in the form of a gas turbine, the cavity of which is connected by means of a central hole to the projection space and by means of tangential holes with the side surface of the gyroscope, while the body is made of a horseshoe Hibernia and its driving device is configured as a front and rear belts with through longitudinal channels, wherein in the housing wall at the installation location of the gyroscope is provided with through holes, and the side surface of the housing between the front and rear by shoulder grooves to brake the gas stream.