RU2647715C1 - Method of increasing the distance plane of a charger and the device for its implementation (options) - Google Patents

Abstract

FIELD: weapons and ammunition.

SUBSTANCE: invention relates to the field of armament. Way in which the movement of the projectile in the gun barrel is effected by the pressure of the combustion products of the main propellant charge, and the charge of solid fuel, located in the device for increasing the range of flight of the projectile, is ignited after the projectile emits from the barrel of the gun, combustion products of solid fuel flow through holes located on the lateral surface of the ballistic tip, forming a boundary layer on the surface of the projectile. Device (according to variants 1–4) consists of a projectile body with a ballistic tip, combustion chamber, solid fuel charge, igniter, power supply and conversion unit, control unit, pressure sensor, combustion chamber is located in the ballistic tip. In the device (according to the variant 1) the holes are made on the lateral surface of the ballistic tip and equipped with plugs. In the device (according to variant 2), the ballistic tip consists of a body and a bow part connected to a rod capable of translational motion in the central channel. In the device (according to the variant 3) the ballistic tip contains a pressure control valve. In the device (according to the variant 4) the ballistic tip contains a breakthrough membrane.

EFFECT: invention can be used for projectiles of small-caliber artillery systems.

15 cl, 11 dwg, 1 tbl

Description

The invention relates to the field of weapons and can be used for shells of small-caliber artillery systems.

For artillery weapon systems, including small-caliber, one of the criteria for effectiveness is the maximum effective firing range. The use of traditional throwing means, as well as traditional design solutions, does not ensure the fulfillment of the requirements for promising small-caliber artillery systems of 23-30 mm caliber to ensure the destruction of openly located and concealed (in trenches, trenches) enemy forces located in individual armor protection systems ( NIB) II level of protection (anti-fragmentation), as well as unarmored vehicles at ranges up to 4500 m, and medium armored vehicles at ranges up to 3000-3500 m.

The traditional methods of increasing the maximum efficiency of the firing range include:

- the use of promising propellant charges in ammunition (including through the use of super-progressive powders, pasty fuels, etc.), providing an increased initial velocity of the projectile;

- optimization of the geometric parameters of the projectile in order to reduce aerodynamic drag.

A known method of controlling the flow around a supersonic air stream of an aircraft (see RF patent No. 2268198, 07/09/2004, B64C 21/08, B64C 30/00), in which through the hollow aerodynamic needle installed in front of the nose of the aircraft, the working fluid is released from pressure the longitudinal channel of the needle to the outside in the form of separate jets, while the aerodynamic cone is filled with a finely dispersed gas-liquid medium and the cones touch the boundary layer on the head of the aircraft.

A device that implements this method consists of a needle with a channel connected to the working fluid through a pipeline located in the frontal part of the aircraft.

The disadvantage of this method is the low ballistic efficiency of the shot due to the location in the front of the needle, which increases the dimensions of the projectile, complicates its design and reduces reliability.

There is a method of increasing the muzzle velocity of a projectile and, as a result, its flight range (see. Rusyak I.G., Ushakov V.M. Intra-chamber heterogeneous processes in barrel systems. Ekaterinburg: Ural Branch of the Russian Academy of Sciences, 2001, 259 pp.) Using a convective candy bar combustion or beam monoblock, in which the movement of ammunition in the gun’s barrel is effected by the pressure of the products of combustion of the main propellant charge (granular or tubular) and bonded to the shell of a monoblock.

The disadvantages of this method are:

- low ballistic efficiency of the shot due to the gap between the monoblock and the end of the projectile and, as a result, a decrease in the muzzle velocity of the projectile due to the low reliability of the adhesive connection, through which the monoblock is connected to the end of the projectile;

- increase the size of the projectile.

There is a method of increasing the flight range of the projectile (options) and a device for its implementation (see RF patent No. 2462686, 12.24.2010, F42B 10/40), selected as the closest analogues of the method and device.

A method of increasing the range of a projectile (according to option 2), in which the movement of the projectile in the gun’s barrel is effected by the pressure of the products of combustion of the main propellant charge, the solid fuel charge located in the device for increasing the range of the projectile is ignited after the projectile leaves the gun’s barrel.

The disadvantage of this method is the low ballistic efficiency of the shot due to the increase in the size of the projectile.

A device for increasing the flight range of a projectile comprises a housing with a combustion chamber, a solid fuel charge, an igniter, a power and conversion unit, a control unit, and a pressure switch. The housing is made with nozzle holes. The housing is attached to the projectile by means of a mounting unit, which consists of pistons, latches, compression springs, plugs, at least three pieces, as well as a charge of the pyrotechnic composition and the ignition device.

The disadvantages of this device is the low ballistic efficiency of the shot due to the increase in the size of the projectile and the complexity of manufacturing the mount.

The task of the group of inventions (method and device) is to increase the ballistic efficiency of the shot.

The technical result of the method of increasing the flight range of the projectile is to increase the flight range of the projectile by reducing the force of aerodynamic drag when the projectile moves in dense layers of the atmosphere.

This object is achieved in that the inventive method in which the movement of the projectile in the gun’s barrel is effected by the pressure of the main propellant’s combustion products, and the solid fuel charge located in the device for increasing the projectile’s flight distance is ignited after the projectile leaves the gun’s barrel, solid fuel combustion products expire through openings located on the lateral surface of the ballistic tip, forming a boundary layer on the surface of the projectile.

The technical result of the device increasing the range of the projectile is to reduce the drag of the projectile and, as a result, increase the range of the projectile.

The task is achieved in that the device for increasing the flight range of the projectile (according to option 1) consists of a shell of a projectile with a ballistic tip, a combustion chamber, a solid fuel charge, an ignitor, a power and conversion unit, a control unit, a pressure sensor, the combustion chamber is located in the ballistic tip and connected through a Central channel with holes made on the side surface of the ballistic tip and equipped with plugs.

In addition, the holes on the lateral surface of the ballistic tip are configured to direct the outflow of gases upward or at an angle to the longitudinal axis of symmetry of the projectile.

The device (according to option 2) consists of a shell with a ballistic tip, a combustion chamber, a solid fuel charge, an ignitor, a power and conversion unit, a control unit, a pressure sensor, a combustion chamber is located in a ballistic tip, a ballistic tip consists of a body and a nose, connected to a rod made with the possibility of translational motion in the Central channel.

The nose of the ballistic tip is configured to direct the outflow of gases upward or at an angle to the longitudinal axis of symmetry of the projectile.

The device (according to option 3) consists of a shell with a ballistic tip, a combustion chamber, a solid fuel charge, an igniter, a power supply and conversion unit, a control unit, a pressure sensor, a combustion chamber is located in the ballistic tip and is connected through a central channel with holes made on the side surface of the ballistic tip, the ballistic tip contains a pressure control valve to prevent premature discharge of combustion products.

The holes on the lateral surface of the ballistic tip are configured to direct the outflow of gases upward or at an angle to the longitudinal axis of symmetry of the projectile.

The device (according to option 4) consists of a shell with a ballistic tip, a combustion chamber, a solid fuel charge, an igniter, a power supply and conversion unit, a control unit, a pressure sensor, a combustion chamber is located in the ballistic tip and connected through a central channel with holes made on the lateral surface of the ballistic tip, the ballistic tip contains a breakthrough membrane to prevent premature discharge of combustion products.

The holes on the lateral surface of the ballistic tip are configured to direct the outflow of gases upward or at an angle to the longitudinal axis of symmetry of the projectile.

The invention is illustrated by drawings, which depict:

in FIG. 1 is a general view of the device (according to embodiment 1) with openings through which the outflow of gases is directed upward;

in FIG. 2 is a general view of the device (according to embodiment 1) with openings through which the outflow of gases is directed at an angle to the longitudinal axis of symmetry of the projectile;

in FIG. 3 is a general view of the device (according to embodiment 2), in which the ballistic tip consists of a body and a bow, the outflow of gases is directed upward;

in FIG. 4 is a general view of the device (according to embodiment 2), in which the ballistic tip consists of a body and a bow, the gas outflow is directed at an angle to the longitudinal axis of symmetry of the projectile;

in FIG. 5 is a general view of a device (according to embodiment 3) containing a pressure control valve and with openings through which the gas flow is directed upward;

in FIG. 6 is a general view of a device (according to embodiment 3) containing a pressure control valve and with openings through which the gas flow is directed at an angle to the longitudinal axis of symmetry of the projectile;

in FIG. 7 is a general view of the device (according to embodiment 4) containing a breakthrough membrane in the central channel and with openings through which the gas flow is directed upward;

in FIG. 8 is a general view of the device (according to embodiment 4) containing a breakthrough membrane in the central channel and with openings through which the gas flow is directed at an angle to the longitudinal axis of symmetry of the projectile;

in FIG. 9 is a general view of the device (according to embodiment 4), containing breakthrough membranes in the holes through which the gas flow is directed upward;

in FIG. 10 is a general view of the device (according to embodiment 4), containing breakthrough membranes in the holes through which the gas flow is directed at an angle to the longitudinal axis of symmetry of the projectile;

in FIG. 11 is a graph comparing external ballistic characteristics of shells of various designs.

The device (according to options 1-4) comprises a projectile 1, consisting of a housing 2 with a ballistic tip 3, which is connected, for example, by a threaded connection, to the shell 2 of the projectile. In the case 2 of the projectile there is a combustion chamber 4 and a charge of solid fuel 5. A central channel 6 is made in the ballistic tip 3. In the case 2 of the projectile is an electronic control unit 7 and a power and conversion unit 8. On the surface of the charge of solid fuel 5 is installed, for example, using an adhesive joint igniter 9. A pressure sensor 10 is installed in the central channel.

The device according to embodiment 1 comprises openings 11 on the lateral surface of the ballistic tip, which are connected to the central channel 6. The openings 11 can be configured to direct the outflow of gases upward (Fig. 1) or at an angle to the longitudinal axis of symmetry of the projectile (Fig. 2). In the holes 11 are installed, for example, by means of an interference fit of the plug 12.

In the device according to option 2, the ballistic tip 3 consists of a housing 13 and a nose 14 connected to a rod 15, which is capable of translational movement in the central channel 6. The nose portion 14 of the ballistic tip is configured to direct the outflow of gases upward (Fig. 3) or at an angle to the longitudinal axis of symmetry of the projectile (Fig. 4).

The device according to option 3 contains a pressure control valve 16 to prevent premature discharge of combustion products. The holes 11 can be made with the possibility of the direction of the flow of gases up (Fig. 5) or at an angle to the longitudinal axis of symmetry of the projectile (Fig. 6).

The device according to embodiment 4 comprises a breakthrough membrane 17 for preventing premature outflow of combustion products located in the central channel 6. The openings 11 can be configured to direct the outflow of gases upward (Fig. 7) or at an angle to the longitudinal axis of symmetry of the projectile (Fig. 8) . In the holes 11 are installed, for example, by means of an interference fit of the plug 12.

Also, the device according to embodiment 4 may contain breakthrough membranes 18 located in the holes 11. The holes 11 can be configured to direct the outflow of gases upward (Fig. 9) or at an angle to the longitudinal axis of symmetry of the projectile (Fig. 10).

The device (according to options 1-4) works as follows.

When undermining the main propellant charge as a result of mechanical impact, the projectile 1 begins to move along the bore. The pressure sensor 10 detects the back pressure that occurs due to air pressure in front of the projectile 1, and transmits a signal to the electronic control unit 7, which at the time of the projectile 1’s departure from the barrel channel generates a signal to ignite the charge of solid fuel 5 and sends it to the power supply and conversion unit 8 . Upon receipt of this signal, the power supply and conversion unit 8 sends an electric pulse to the igniter 9 and starts it. The products of combustion of the igniter 9 warm up and ignite the charge of solid fuel 5. The products of combustion of solid fuel 5 begin to fill the central channel 6.

According to option 1, under the pressure generated by filling the central channel 6 with the solid fuel charge combustion products 5, the plugs 12 are disconnected. The solid fuel charge combustion products 5 under high pressure begin to flow through the openings 11 into the atmosphere. Outgoing gases envelop the shell 1, forming a boundary layer on its surface, which provides an increase in the aerodynamic characteristics of the shell due to a decrease in the aerodynamic drag forces.

According to option 2, at the initial time, the nose portion 14 of the ballistic tip is pressed against the body 13 of the ballistic tip. As a result of the combustion of the charge of solid fuel 5, the pressure in the central channel 6 increases and the pressure of the combustion products acts on the rear surface of the bow 14. When the force from the pressure of the combustion products in the central channel is greater than the force of the aerodynamic drag of the nose 14, the nose 14 and the rod 15 advance. After the extension of the bow 14, the combustion products of the charge of solid fuel 5 begin to flow into the atmosphere.

In option 3, a pressure control valve 16 is located in the central channel 6 of the ballistic tip 3. The pressure control valve 16 opens when a certain pressure is reached in the central channel 6, and the combustion products of the solid fuel charge 5 begin to flow into the atmosphere.

In option 4, a breakthrough membrane 17 is placed in the central channel 6, which breaks at a certain pressure in the central channel 5. Also, breakthrough membranes 18 that break at a certain pressure can also be placed in the holes 11. This provides the required initial pressure at the time of the outflow of gases through the holes 11 of the ballistic tip 3. In the case of installing breakthrough membranes 18 in the holes 12 of the ballistic tip, they serve as plugs.

The operability of the device for increasing flight range was tested on the OFZ-30-GSh projectile. For the given design of the shells, the aerodynamic characteristics were determined for the speed range from 800 m / s to 500 m / s, the external ballistics was calculated.

The results of the calculations presented on the graph (Fig. 11), where the black color represents the graph of the flight range from the free-stream velocity of the standard OFZ-30-GSh shell, and the red and blue graphs of the OFZ-30-GSh shells with installed range increasing devices flight, indicating that the use of the proposed device increases the range of the projectile.

The results of calculating the flight range from the speed of the incident flow are presented in the table.

The results presented in the table indicate that the use of the proposed device reduces the drag force.

The proposed method for increasing the projectile range and the device for its implementation can increase the ballistic efficiency of the shot by increasing the projectile range and reducing drag.

Claims (15)

1 A method of increasing the range of a projectile, in which the projectile in the gun’s barrel is exposed to the pressure of the main propellant’s combustion products, the solid fuel charge located in the device for increasing the projectile’s range is ignited after the projectile leaves the gun’s barrel, characterized in that the solid’s combustion products fuels flow out through openings located on the lateral surface of the ballistic tip, forming a boundary layer on the surface of the projectile. 2 A device for increasing the range of a projectile, consisting of a shell of a projectile with a ballistic tip, a combustion chamber, a solid fuel charge, an igniter, a power supply and conversion unit, a control unit, a pressure sensor, characterized in that the combustion chamber is located in the ballistic tip and connected through a central channel with holes made on the lateral surface of the ballistic tip and equipped with plugs. 3 The device according to claim 2, characterized in that the holes on the side surface of the ballistic tip are made with the possibility of the direction of flow of gases up. 4 The device according to claim 2, characterized in that the holes on the lateral surface of the ballistic tip are made with the possibility of directing the flow of gases at an angle to the longitudinal axis of symmetry of the projectile. 5 A device for increasing the flight range of a projectile, consisting of a shell of a projectile with a ballistic tip, a combustion chamber, a solid fuel charge, an igniter, a power supply and conversion unit, a control unit, a pressure sensor, characterized in that the combustion chamber is located in a ballistic tip, the ballistic tip consists of the body and the bow connected to the rod, made with the possibility of translational motion in the Central channel. 6 The device according to claim 5, characterized in that the nose of the ballistic tip is made with the possibility of the direction of flow of gases up. 7 The device according to claim 5, characterized in that the nose of the ballistic tip is configured to direct the flow of gases at an angle to the longitudinal axis of symmetry of the projectile. 8 A device for increasing the range of a projectile, consisting of a shell of a projectile with a ballistic tip, a combustion chamber, a solid fuel charge, an ignitor, a power supply and conversion unit, a control unit, a pressure sensor, characterized in that the combustion chamber is located in the ballistic tip and connected through a central channel with holes made on the side surface of the ballistic tip, the ballistic tip contains a pressure control valve to prevent premature failure combustion products. 9 The device according to claim 8, characterized in that the holes on the side surface of the ballistic tip are made with the possibility of the direction of flow of gases up. 10 The device according to claim 8, characterized in that the holes on the lateral surface of the ballistic tip are made with the possibility of directing the flow of gases at an angle to the longitudinal axis of symmetry of the projectile. 11 A device for increasing the range of a projectile, consisting of a shell of a projectile with a ballistic tip, a combustion chamber, a solid fuel charge, an igniter, a power supply and conversion unit, a control unit, a pressure sensor, characterized in that the combustion chamber is located in the ballistic tip and connected through a central channel with holes made on the lateral surface of the ballistic tip, the ballistic tip contains a breakthrough membrane to prevent premature leakage uktov combustion. 12 The device according to claim 11, characterized in that the holes on the lateral surface of the ballistic tip are made with the possibility of the direction of flow of gases up. 13 The device according to claim 11, characterized in that the holes on the lateral surface of the ballistic tip are configured to direct the flow of gases at an angle to the longitudinal axis of symmetry of the projectile. 14 The device according to p. 12 or 13, characterized in that the breakthrough membrane is installed in the Central channel of the ballistic tip. 15 The device according to p. 12 or 13, characterized in that the breakthrough membrane is installed in the holes on the side surface of the ballistic tip.

Images